| Entries |
| Document | Title | Date |
|---|
| 20080199321 | Parabolic radial flow impeller with tilted or offset blades - An impeller assembly, comprising a generally planar disc oriented in a first plane and having a circular outer edge; and a plurality of blades mounted to the disc and extending beyond the edge of the disc, with the blades in cross-section having a shape that is substantially symmetrical along a center line and having a first segment and a second segment disposed on opposite sides of the center line, with one segment being symmetrical with at least a portion of the other segment, and with the blades mounted so that the respective center line of each blade is at an angle relative to the first plane in which the disc lies. In another variation, the blades are mounted so the center line of each blade is offset from the plane in which the disc lies. | 08-21-2008 |
| 20080219848 | Propeller - The inventive propeller consists of a shaft comprising at least two hubs which are mounted thereon and provided with blades fixed to each of them. Each blade has a front and rear sharp edges and is embodied in such a way that the greater airfoil thickness thereof is equal to (0.10-0.25)b along the blade span, wherein b is the mean chord of the blade. The greatest airflow thickness of each blade is located in the middle of each mean chord and is twisted around an axis passing through the middles of the mean chords along the blade span. The blade can be fixed to each hub at an angle of <90° with respect to the radius thereof, thereby reducing a local aerodynamic drag and aerodynamic loads. The inventive propeller can be provided with a fixed cylindrical enclosure which embraces all blades and extended in front of the blades of the front hub at a distance which is equal to or greater than the blade span, thereby increasing a torque effect value. | 09-11-2008 |
| 20080219849 | Low camber microfan - A cooling fan comprises an impeller which includes a plurality of radially extending blades, each of which includes a blade hub, a blade tip and a blade midspan approximately midway between the hub and the tip. In addition, each blade comprises a blade suction surface, and substantially the entire blade suction surface is visible from the forward looking aft direction. | 09-11-2008 |
| 20080219850 | Wind Turbine - A method of designing a rotor for a horizontal axis wind turbine. The method combines an actuator disk analysis with a cascade fan design method to define the blade characteristics, including the shape and size of the blades, such that the maximum amount of energy is extracted from the air at the lowest rotational speed. A method of manufacturing a wind turbine and a turbine designed in accordance with the method are also disclosed. | 09-11-2008 |
| 20080232970 | Mold Assembly and Method for Injection Molding of an Impeller, and Impeller Formed by Said Method - A mold assembly and a method for injection molding of an impeller, and an impeller formed by the method are provided. The mold assembly comprises a first mold, a central mold, and a second mold. The central mold encircles the first mold, and the second mold matches with the first mold and the central mold to form a mold cavity, complementary in shape to the impeller. The melted plastic material is injected into the aforementioned mold cavity. After the plastic material is cured, the central mold is adapted to enclose the cured plastic material. The cured plastic material is removed from the first mold, and then is removed from the central mold and the second mold to form the impeller. The blade portion of the impeller is radially connected to an edge of a central portion of the impeller. The blade portion has a plurality of blades, equally spaced apart with one another in sequence along the edge. Each of the blades comprises a smooth surface without an ejector pin mark. | 09-25-2008 |
| 20080240923 | ROTOR BLADE FOR A WIND TURBINE HAVING A VARIABLE DIMENSION - A rotor blade | 10-02-2008 |
| 20080240924 | TURBINE BLADE - An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vain root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of ±2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion. | 10-02-2008 |
| 20080253896 | High efficiency fan blades with airflow-directing baffle elements - Fan blades are provided that increase aerodynamic and operational efficiency, and which include baffle elements positioned on the distal ends of the fan blades. The baffle elements operate by shearing blade tip vortices, thereby minimizing turbulent fluid effects, and further providing fluid shunt that imparts a radial velocity component to the fluid. The baffle elements produce a more focused and collimated fluid flow perpendicular to the plane of rotation during forward rotation, and produce a more diffuse, radially-outward directed fluid flow during reverse rotation. The baffle elements are positioned such that they are characterized by a first angle with respect to the radial axis of the fan blade and a second angle with respect to the low pressure surface of the fan blade. | 10-16-2008 |
| 20080253897 | Axial Flow Fan - In an axial flow fan provided with a plurality of impeller blades ( | 10-16-2008 |
| 20080260536 | BLADE ARRANGEMENT - A blade assembly for a rotary component comprises an aerofoil member and a displacement apparatus on the aerofoil member for displacing a detached first portion of the aerofoil member in a rearward direction relative to a second portion of the aerofoil member. On failure of the aerofoil member, the displacement apparatus displaces the first portion from the second portion in the rearward direction. | 10-23-2008 |
| 20080267782 | PROPELLER - A propeller attached to an output shaft of a boat motor is provided. The propeller may have a plurality of blades which define a leading edge. The leading edge may define leading edge angles which increase in a logarithmic manner from a base of the blade to a tip of the blade. This allows the blades of the propeller to cut and shed seaweed and/or kelp off of the blades when the boat is maneuvered into waters containing seaweed and/or kelp. Additionally, boats that employ the propeller of the present invention are quieter compared to boats that utilize prior art propellers. | 10-30-2008 |
| 20080273984 | External profile for turbine blade airfoil - A turbine blade including an airfoil having a pressure sidewall and a suction sidewall joined together along an upstream leading edge and a downstream trailing edge. The leading edge and trailing edge are formed as substantially straight edges, and portions of the pressure sidewall and suction sidewall adjacent the trailing edge form substantially planar surfaces. The airfoil has an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein Z represents a perpendicular distance from a plane normal to a radius of a turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radially innermost aerodynamic section of the airfoil, and X and Y represent coordinate values defining the airfoil profile at each distance Z which, when connected by smooth continuing arcs, define profile sections at each distance Z. | 11-06-2008 |
| 20080279691 | Three-part stator blade - A blade for a stator in a torque converter, including: a first blade segment connected to an inner circumferential section of the stator; at least one second blade segment, separately formed from the first blade segment, and connected to the inner circumferential section; and a third blade segment, separately formed from the first and second blade segments, and connected to the inner circumferential section. In some aspects, the first, second, and third blade segments include respective outer radial portions and the outer radial portions are fixedly connected. In some aspects, the first and second blade segments are in contact and the second and third blade segments are in contact. In some aspects, the first, second, and third blade segments include respective edges and the first and second blade segments are in contact along the respective edges and the second and third blade segments are in contact along the respective edges. | 11-13-2008 |
| 20080292466 | Method to center locate cutter teeth on shrouded turbine blades - The present application further describes a method for extending the operating life of a tip shrouded turbine blade that includes the steps of: 1) removing an end located cutter tooth from a seal rail of a tip shroud, the end located cutter tooth including a cutter tooth located at the end of one of the suction side and pressure side of the seal rail of the tip shroud; and 2) attaching a center located cutter tooth to the seal rail of the tip shroud, the center located cutter tooth including a cutter tooth that is located in the approximate center of the seal rail of the tip shroud. In such method, the center located cutter tooth may be attached to the seal rail such that the center located cutter tooth is inside the airfoil if it were projected radially outward from the narrowest point below a tip shroud fillet. | 11-27-2008 |
| 20080298973 | Turbine vane with divided turbine vane platform - A turbine vane with endwalls, wherein at least one endwall is formed from two or more sections configured such that the sections form releasable joints with a generally elongated airfoil of the turbine vane. The sections may be configured to both support the generally elongated airfoil and to establish cooling fluid flowpaths between the sections and the generally elongated airfoil to cool the aspects of the turbine vane proximate to the intersection of the endwalls and the generally elongated airfoil. In addition, the joints between the generally elongated airfoil and the sections may be formed from a connection system that enables forces to be transmitted from the generally elongated airfoil to the endwalls without creating stresses found in conventional turbine vane fillets at the intersection between the generally elongated airfoil and the endwalls. | 12-04-2008 |
| 20080298974 | Blade of a fluid-flow machine featuring a multi-profile design - A blade of a fluid-flow machine has a cross-section, which in at least one part of the blade height in at least one flow-line profile section is formed by at least two partial profiles separated from each other, with each of the individual partial profiles having the shape of a blade profile. | 12-04-2008 |
| 20080304974 | FIRST STAGE DUAL-ALLOY TURBINE WHEEL - A first-stage turbine that is adapted for receiving high energy air directly from a combustion chamber in a gas turbine engine auxiliary power unit includes a disk formed from a first alloy and having an outer surface, and a unitary blade wheel formed from a second alloy that is different than the first alloy. The unitary blade wheel includes an annular member having an inner surface that is joined to the disk, and blades that are integrally formed with the annular member. | 12-11-2008 |
| 20080310963 | ROTARY BLOOD PUMP - Various “contactless” bearing mechanisms including hydrodynamic, hydrostatic, and magnetic bearings are provided for a rotary pump as alternatives to mechanical contact bearings. These design features may be combined. In one embodiment, the pump apparatus includes a rotor having a bore, a ring-shaped upper rotor bearing magnet, and a ring-shaped lower rotor bearing magnet. The bearing magnets are concentric with the bore. The lack of mechanical contact bearings enables longer life pump operation and less damage to working fluids such as blood. | 12-18-2008 |
| 20080317600 | Wind turbine rotor blade with vortex generators - A wind turbine rotor blade with an airfoil having a suction side and a pressure side is provided. The airfoil comprises an inner airfoil portion and an outer airfoil portion, where the inner airfoil portion is comparatively thicker than the outer airfoil portion and provided with vortex generators. The thickness of the inner airfoil portion is between 30% and 80% of the inner airfoil portion's chord length, and the vortex generators are located at the suction side of the inner airfoil portion between 8% and 12% of the chord length, as measured from the leading edge of the airfoil portion. | 12-25-2008 |
| 20090004020 | Water Pump - A water pump has a pump housing having a water inlet and a water outlet. A driven pump impeller is arranged in the pump housing. The pump impeller is a diagonal impeller with a carrier plate having a conical shape. The water inlet and the water outlet are arranged such that a water intake direction and a water exit direction are substantially perpendicular to one another. | 01-01-2009 |
| 20090010763 | PROPELLER - A propeller has a hub | 01-08-2009 |
| 20090016891 | Wind turbine blade tip vortex breakers - A wind turbine includes a tower supporting a drive train with a rotor, at least one blade extending radially from the rotor; and a plurality of substantially flat flaps extending substantially perpendicular from a suction surface of the blade and along different chord lines near a tip of the blade for capturing and directing tip vortices toward a trailing edge of the blade. | 01-15-2009 |
| 20090016892 | VERTICAL SHAFT WIND TURBINE AND METHOD OF INSTALLING BLADES THEREIN - This invention relates to a vertical shaft wind turbine, and particularly to an installation method of blades that can effectively improve the efficiency of a vertical shaft wind turbine. A supporting plane is connected to vertical shaft and a blade is installed on supporting plane. The airfoil of the blade is an asymmetrical camber airfoil. The convex surface of blade is installed facing the vertical shaft. The blade rotary angle is in the range of 0-15 degrees. This invention represents a remarkable progress in the field of wind power generation and is applicable industrially. | 01-15-2009 |
| 20090022597 | Apparatus For The Generation Of Power From A Flowing Fluid - Apparatus for the generation of electrical or mechanical energy from a flowing fluid. The apparatus includes at least one blade of substantially helical configuration. The blade has a plurality of blade sections. Action of the flowing fluid on the blade causes it to rotate around its axis. The rotational motion is used to generate electrical or mechanical energy. Also disclosed is a helical blade wherein the pitch length and/or radii varies along the length of the helical blade profile. | 01-22-2009 |
| 20090022598 | Wind turbine rotor blade and wind turbine rotor - A wind turbine rotor blade is provided which includes a root end and a tip end located opposite the root end. A leading edge extends from the root end to the tip end. A trailing edge extends from the root end to the tip end. A span direction is defined by a line extending linearly from the root end to the tip end. A chord direction is perpendicular to the span direction and lies in the plane extending through the leading edge and the trailing edge. A shoulder is the point of the maximum chord-wise extension. An airfoil portion extends from the shoulder to the tip end. The airfoil portion comprises a span-wise interval begging before the tip end and extending to or close to the tip end and in which the distribution of the chord-wise extension is increased as compared to the load optimised distribution of the chord-wise extension. | 01-22-2009 |
| 20090028713 | Centrifugal multiblade fan - A plurality of curved rectangular blades are arranged in a circumferential direction on a periphery of a disc, forming a pipe-like basket shape with an opening on a front side of the disc. Rotation of the disc draws in air from the opening and draws out the air in a centrifugal direction through a space between the blades. The blades are formed of a thick plate part close to the disc and a thin plate part that is thinner than the thick plate part and farther than the thick plate part from the disc. A bulge serving as a boundary between the thick plate part and the thin plate part is formed on a negative pressure surface of the blades, which is of curved convex shape. | 01-29-2009 |
| 20090028714 | METHOD OF DESIGNING TOOL AND TOOL PATH FOR FORMING A ROTOR BLADE INCLUDING AN AIRFOIL PORTION - A method of designing a tool for forming a rotor blade including an airfoil portion includes generating a computer model of a rotor blade having an airfoil portion, and determining a curvature and radius of curvature at sections of the rotor blade. An inner and outer diameter of a circumferential forming portion of a tool operable to form the rotor blade may then be calculated. A method of designing a tool path for forming a rotor blade including an airfoil portion includes generating a computer model of a cylindrical tool operable to form a rotor blade including an airfoil portion and of a rotor having a plurality of the rotor blades. The computer models of the rotor and tool are used to generate a first and second tool motion corresponding to airfoil suction and pressure portions. A method of forming a rotor with integral blades is also disclosed. | 01-29-2009 |
| 20090028715 | Impeller - An impeller includes a hub having a top portion and an annular wall extending from a circumference of the top portion in a direction perpendicular to the top portion. The top portion includes a shaft base for coupling with a shaft located in an inner space defined by the top portion and the annular wall. A plurality of blades are mounted to an outer periphery of the annular wall. A metal ring is mounted in the inner space of the hub. The annular wall has a thickness substantially smaller than that of the top portion, allowing the metal ring to be inserted into the inner space by tight coupling. | 01-29-2009 |
| 20090028716 | Impeller - An impeller includes a plurality of portions, a plurality of bends, and a plurality of blades. A substantial thickness of a portion is smaller than a substantial thickness of another portion more adjacent to a central axis of the impeller. Each bend is interconnected between two portions adjacent to each other. The blades are formed on the portion most distant to the central axis. The overall weight of the impeller is reduced. Furthermore, the impeller has improved mass uniformity and hence improved overall balancing precision. | 01-29-2009 |
| 20090028717 | FAN BLADE - The present invention relates to the field of blades, particularly fan blades, intended for turbojets, particularly of the aeronautical type. | 01-29-2009 |
| 20090028718 | Wind turbine rotor blade and pitch regulated wind turbine - A wind turbine rotor blade with an airfoil profile having an upwind side, a downwind side is provided. A stall inducing device is located at the upwind side of the airfoil profile. | 01-29-2009 |
| 20090028719 | Multi-Blade Fan - In a multi-blade fan provided with a plurality of notches in a blade edge in an outer side of each impeller blade, it is possible to direct an impeller blade outlet in a portion of the notches to a circumferential direction. Also, it is possible to direct an air flow blown out of the fan to the circumferential direction. Further, it is possible to effectively increase a pressure, by setting a projection protruding along a thickness direction of the impeller blade in a rear portion of each notch, in a pressure surface of the impeller blade receiving air pressure on the basis of rotation of the multi-blade fan. | 01-29-2009 |
| 20090035146 | Airfoil shape for a turbine bucket and turbine incorporating same - Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z′ set forth Table I wherein X and Y values are in inches and the Z′ values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z′ values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +/−.0.040 inches in directions normal to the surface of the airfoil. | 02-05-2009 |
| 20090035147 | Blade For an Impeller Wheel - Blade for an impeller wheel which is suitable for use for an impeller wheel power station. The special design of the blade ensures relatively low swirling of the water flow behind the blade and increases the utilization of the inflowing water flow as a result. | 02-05-2009 |
| 20090047134 | Turbine Wheel with Backswept Inducer - An exemplary blade ( | 02-19-2009 |
| 20090053066 | Turbine Blade Cascade End Wall - In the turbine blades set to a large outflow angle, the performance of the entire turbine is improved by reducing a cross flow generated on the turbine end wall and a whirling up of flow on the suction side of a blade irrespective of the difference of the blade shape, thereby reducing the loss. There is provided a turbine blade cascade end wall positioned on the hub-side and/or the tip side of a plurality of turbine blades arranged in an annular shape, including a first projection having a ridge extending downward from the trailing edge of a turbine blade toward the downstream side gently at the beginning and steeply at the end, and along the suction side of an adjacent turbine blade. | 02-26-2009 |
| 20090068018 | WINDTURBINE WITH SLENDER BLADE - Wind turbine with a rotor blade relatively insensitive to turbulence because it is more slender than prior blades and is nevertheless able to generate sufficient lift by virtue of the fact that flow enhancing elements such as vortex generators combat flow separation. The slenderness is defined by the chord numbers C and D of which C is defined as C=Nc | 03-12-2009 |
| 20090074583 | Rotor blade for a wind turbine - A rotor blade of a wind power installation in which the rotor blade, in particular in the central region of the rotor, the so-called main board, has a lift-drag ratio which in the region of about ±2° from the optimum pitch angle has a lift-drag ratio value of more than 80%, preferably 90% and more of the maximum value of the lift-drag ratio. | 03-19-2009 |
| 20090074584 | NICKEL-BASED ALLOY FOR TURBINE ROTOR OF STEAM TURBINE AND TURBINE ROTOR OF STEAM TURBINE - A Nickel-based alloy for a turbine rotor of a steam turbine contains C: 0.01 to 0.15, Cr: 18 to 28, Co: 10 to 15, Mo: 8 to 12, Al: 1.5 to 2, Ti: 0.1 to 0.6, B: 0.001 to 0.006, Ta: 0.1 to 0.7 in % by weight, and the remaining portion is composed of Ni and unavoidable impurities. The Nickel-based alloy is composed of the above-stated chemical composition range, and thereby, a mechanical strength improves while maintaining forgeability as same as a conventional steel. | 03-19-2009 |
| 20090081047 | MULTI-ELEMENT BLADE WITH AERODYNAMIC PROFILES - The objective of this invention is to obtain rotor blades for large-sized horizontal axis wind turbines that allow easy transport, handling and storage at the same time guaranteeing greater efficiency in the use of wind energy. The present invention results in a blade ( | 03-26-2009 |
| 20090097983 | METHOD FOR RESTORING AIRFOIL TIP CONTOUR - A blade is repaired by utilizing a super abrasive machining quill and/or wheel to form the contour and restore the height of the blade. By utilizing super abrasive machining, the contour and height can be quickly returned to desired dimensions by removing unwanted added material. | 04-16-2009 |
| 20090104039 | Curved Blade for Wind Turbines - A curved blade for use on horizontal wind turbines, the blade comprising a substantially semicircular tip portion, a substantially semicircular counter-tip portion opposite the tip portion, and a body portion extending between the tip portion and the counter-tip portion, the body portion being further defined by a concave curved trailing edge and a convex curved leading edge. | 04-23-2009 |
| 20090110558 | FAN - A fan includes a hub and a plurality of blades formed on the hub with a rake angle. In an axial direction of the hub, no part of a trailing edge of any of the blades is disposed past an air outlet end of the hub at more than a distance approximately equal to 25% of a diameter of the hub. | 04-30-2009 |
| 20090123289 | Quiet Airfoils For Small and Large Wind Turbines - Thick airfoil families with desirable aerodynamic performance with minimal airfoil induced noise. The airfoil families are suitable for a variety of wind turbine designs and are particularly well-suited for use with horizontal axis wind turbines (HAWTs) with constant or variable speed using pitch and/or stall control. In exemplary embodiments, a first family of three thick airfoils is provided for use with small wind turbines and second family of three thick airfoils is provided for use with very large machines, e.g., an airfoil defined for each of three blade radial stations or blade portions defined along the length of a blade. Each of the families is designed to provide a high maximum lift coefficient or high lift, to exhibit docile stalls, to be relatively insensitive to roughness, and to achieve a low profile drag. | 05-14-2009 |
| 20090136353 | Turbine blade - A blade arrangement ( | 05-28-2009 |
| 20090136354 | BLADE - A blade surrounded by: a leading edge portion, which is where fluid flows in; a pressure surface which is a concave curve shape concaved along a direction the fluid flows; a suction surface which is a convex curve shape convexed along a direction the fluid flows; and a trailing edge portion, which is where the fluid flows out, in which a disturbance addition portion is provided on the suction surface closer to the leading edge portion than a maximum velocity point, where the flow velocity of the fluid is maximized on the suction surface, for disturbing a laminar flow on the suction surface and for transitioning to a turbulent flow. | 05-28-2009 |
| 20090142196 | Rotor for centrifugal compressor - The present disclosure provides an improved rotor of a centrifugal compressor. The rotor includes a blade arrangement and geometry that increase the overall efficiency of the rotor. In particular, blades within the rotor are curved and inclined in a manner that improves the overall efficiency of the rotor. The present disclosure also provides a method of manufacturing the improved rotor. | 06-04-2009 |
| 20090142197 | Wind Turbine Rotor Blade - A wind turbine rotor blade with a suction side and a pressure side is provided. The blade includes a cylindrical root portion, an airfoil portion defining the suction side and the pressure side, and a transition portion which is located between the airfoil portion and the root portion. The transition portion has a transition profile changing from the airfoil of the airfoil portion to the cylindrical profile of the root portion. The leading section of the transition profile is cylindrical and the trailing section of the transition profile is elongated. In the rotor blade, the maximum chord length of the airfoil portion is at least the maximum chord length of the transition portion. In addition, the transition profile includes a section with a concave curvature on the pressure side of the rotor blade | 06-04-2009 |
| 20090148300 | MODULAR WIND TURBINE BLADES WITH RESISTANCE HEATED BONDS - A blade for a wind turbine includes a first structural component; a second structural component; and at least one conductive bond for joining the first and second structural components. | 06-11-2009 |
| 20090148301 | MAIN ROTOR BLADE WITH REMOVABLE TIP CAP - A main rotor blade assembly includes a tip cap removably mountable to an outboard end section of a forward tip spar section and an aft tip spar section. | 06-11-2009 |
| 20090155083 | METHOD FOR REPAIRING AN AIRFOIL - An example method of repairing an airfoil includes securing a cap to an end portion of a worn airfoil and securing additional material to the cap. The method includes altering some of the cap to form a desired airfoil contour. | 06-18-2009 |
| 20090155084 | WIND BLADE JOINT BONDING GRID - A method and system for assembling large wind turbine blades that includes providing a plurality of wind turbine blade segments. An adhesive distribution arrangement is disposed on a surface of at least one of the plurality of the wind turbine blade segments. The adhesive distribution arrangement includes a bonding grid having a plurality of adhesive distribution openings. The wind turbine blade segments are directed together and sufficient adhesive is provided to the bonding grid to substantially fill an area between the wind turbine segments. The adhesive is then cured to form a bonded joint, the bonding grid being incorporated into the bonded joint. A bonding grid for use with the method and system and a segmented wind turbine blade are also disclosed. | 06-18-2009 |
| 20090155085 | TURBOMACHINE BLADE THAT IS CAST WITH A LOCAL FATTENING OF THE SECTION OF THE AIRFOIL - The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, comprising:
| 06-18-2009 |
| 20090162206 | MULTI-SEGMENT WIND TURBINE BLADE AND METHOD FOR ASSEMBLING THE SAME - A multi segment wind turbine blade comprises at least two blade segments. A first blade segment comprises an outer skin, a bulkhead, and first alignment brackets removably coupled to the outer skin of the first blade segment. A first portion of a flange of the bulkhead is bonded to the first blade segment and a second portion of the flange of the bulkhead projects out from the first blade segment. A second blade segment comprises an outer skin and second alignment brackets removably coupled to the outer skin of the first blade segment. The first and second alignment brackets are alignable upon the outer side of the second blade segment being inserted over the second portion of the flange of the bulkhead. | 06-25-2009 |
| 20090175730 | FAN AND IMPELLER - A fan includes a housing, an impeller and a motor. The impeller includes a hub, a ring and a plurality of flat blades. The ring surrounds the hub without substantial contact therewith and is connected to the hub by at least one connecting arm. The flat blades are disposed on the ring and the active surface of each flat blade has an imaginary extending lines which is which is tangent to a rim of the hub | 07-09-2009 |
| 20090185910 | Gas-turbine blade root - A gas-turbine blade root | 07-23-2009 |
| 20090196754 | IMPELLER AND COOLING FAN INCORPORATING THE SAME - A cooling fan ( | 08-06-2009 |
| 20090202354 | Wind turbine blade - An aerodynamic profile and a wind turbine comprising a wind turbine blade with reduced sensitivity towards surface irregularities are provided. The invention is mainly directed towards pitch-regulated wind turbines, which are operated at variable rotor speed and have blades longer than about 30 meters. | 08-13-2009 |
| 20090208341 | BLADE FOR WIND-POWER GENERATORS - The invention relates to a blade for wind-power generators. The inventive blade is divided transversely into two or more independent sections, each section comprising aerodynamic skins or walls ( | 08-20-2009 |
| 20090232656 | Blade for a wind Turbine Rotor | 09-17-2009 |
| 20090246031 | METHOD OF RESTORING AN AIRFOIL BLADE - A method of repairing an airfoil blade involves the steps of providing an airfoil blade have a leading edge, a trailing edge, a tip and a base. A length of the airfoil blade is defined by the tip and the base and a width of the airfoil blade is defined by the leading edge and the trailing edge. A weld is made along a first direction of the length of the airfoil blade and then made in a second direction along the width of the airfoil blade to form a first weld layer. The first weld layer has a first portion extending across the length of the airfoil blade and a second portion extending across its width. A second weld layer is welded onto the first layer such that an end wall of the second weld layer abuts the second portion of the first weld layer. | 10-01-2009 |
| 20090246032 | METHOD OF MACHINING AIRFOIL ROOT FILLETS - An airfoil root fillet having a predetermined compound curve profile can be flank milled with a single flank milling cutter having a generally conical flank milling portion and a rounded tip portion defining a compound curve. | 10-01-2009 |
| 20090257880 | Conical helicoid wind turbine - The present invention discloses an article of manufacture comprising a conical helicoid wind turbine. The conical helicoid is configured such that its apex faces toward the on-coming wind which allows airflow to transverse through the curved sail from the front center to the outer rear extremity. This dynamic shape produces the optimum amount of force by distributing the wind load to the outer edges of the wind turbine's rotation. In addition, by channeling the flow of air through the conical helix to convert to motive force, the turbine forces the wind into a vortexual formation which entrains wind flow in tandem with the turbine's rotational force, thus reducing backflow turbulences. | 10-15-2009 |
| 20090263251 | REDUCED WEIGHT BLADE FOR A GAS TURBINE ENGINE - A rotor blade for a gas turbine engine having an edge buttress having an aperture. A method of reducing rotor blade weight includes removing material from within a truss area bounded by a platform section, an internal airfoil cooling passage, and an underplatform fillet. | 10-22-2009 |
| 20090263252 | WIND GENERATOR BLADE WITH DIVERGENT TRAILING EDGE - A wind turbine blade having an aerodynamic profile ( | 10-22-2009 |
| 20090274559 | ROTOR BLADE OF A WIND ENERGY UNIT - The invention relates to a rotor blade ( | 11-05-2009 |
| 20090285691 | Blade for a Wind Turbine Rotor | 11-19-2009 |
| 20090297352 | DEBRIS REMOVAL SYSTEM AND METHOD FOR WIND TURBINE BLADES - A system is provided for cleaning debris from horizontal axis wind turbine blades. The system includes a wiper with arms extending partially around the blade adjacent the leading edge and a line engaging the leading edge so as to scrape debris from the blade edge as the arms move along the length of the blade. The arms are carried outwardly along the blades by aerodynamic and centripetal forces, and are retracted by cables attached to the arms. The system is activated by a PLC in response to sensors on the turbine to automatically clean the blade when wind conditions typically allow insects to fly and contaminate the blades. A grease control system is also provided on the blades to prevent grease or oil from the turbine hub from leaking onto the blade. | 12-03-2009 |
| 20090297353 | WIND TURBINE BLADES WITH TWISTED TIPS - A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to approximately 10 percent of a rotor radius of the blade. | 12-03-2009 |
| 20090297354 | WIND TURBINE BLADES WITH TWISTED AND TAPERED TIPS - A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to approximately 10 percent of a rotor radius of the blade; and a total normalized chord change of between approximately one percent and approximately two percent between the outer approximately 1 percent to approximately 10 percent of the rotor radius of the blade. | 12-03-2009 |
| 20090297355 | WIND TURBINE BLADE PLANFORMS WITH TWISTED AND TAPERED TIPS - A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to 10 percent of a rotor radius of the blade; and an approximate planform distribution within the following ranges | 12-03-2009 |
| 20090304518 | TURBOFAN ENGINE - A hub-side leading edge part of a fan first-stage rotating blade | 12-10-2009 |
| 20090324416 | WIND TURBINE BLADES WITH MULTIPLE CURVATURES - A blade for a wind turbine includes a chord plane having one spanwise portion with a first curvature and another spanwise portion with a second curvature that is different from the first curvature. | 12-31-2009 |
| 20100003141 | Strengthening Structure For A Wind Turbine Blade, A Wind Turbine Blade, A Method For Assembling A Wind Turbine Blade And Use Hereof - A strengthening structure for a wind turbine blade includes at least one first reinforcement part adapted to be connected to a first blade part of the wind turbine blade, and at least one second reinforcement part adapted to be connected to a second blade part of the wind turbine blade. The strengthening structure is characterized in that the at least one first reinforcement part and/or the at least one second reinforcement part includes an adjusting mechanism enabling that the first reinforcement part and the second reinforcement part are displaceable in relation to each other, at least during the assembly of the wind turbine blade and wherein the adjusting mechanism includes a force mechanism capable of forcing the first reinforcement part and the second reinforcement part away from each other. A wind turbine blade, a method for assembling a wind turbine blade and a use thereof are also contemplated . | 01-07-2010 |
| 20100008784 | COMPRESSOR TURBINE BLADE AIRFOIL PROFILE - A turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 1. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z arc joined smoothly to one another to form a complete airfoil shape. | 01-14-2010 |
| 20100008785 | DYNAMICALLY TUNED TURBINE BLADE GROWTH POCKET - A turbine blade growth pocket provides a feature to measure blade growth due to engine operation while maintaining dynamic characteristics of the turbine blade within acceptable limits by providing a variable radius fillet between the pocket and a side rail of the pocket. | 01-14-2010 |
| 20100008786 | Apparatus and method for electric spark peening of gas turbine components - Peening provides compression of component ( | 01-14-2010 |
| 20100008787 | Wind Turbine Blades With Vortex Generators - An advantageous new design of a wind turbine blade and rotor is obtained by providing one, two or more parallel rows of sub-boundary layer vortex generators, whereby a blade is obtained, which is resistant to stall and provides for a high maximum lift coefficient C | 01-14-2010 |
| 20100014979 | REINFORCED AERODYNAMIC PROFILE - The present invention relates to the prevention of deformations in an aerodynamic profile caused by lack of resistance to the bending moment forces that are created when such a profile is loaded in operation. More specifically, the invention relates to a reinforcing element inside an aerodynamic profile and a method for the construction thereof. The profile is intended for, but not limited to, use as a wind turbine blade, an aerofoil device or as a wing profile used in the aeronautical industry. | 01-21-2010 |
| 20100021307 | Dual impeller generator - This invention is using exist present laws of physics to produce and concentrate existing available fluid flow energy into usable commercial energy. It will concentrate on using wind energy to make Electrical and/or Compressed air energy. This will require the invention of a new impeller, air concentrator (compressor), storage unit, and the combination of these units into an “Energy Station”. This patent application will concentrate on a new impeller only. This new impeller will redirect the atmospheric wind forces, (and increase them), to create usable Electrical and/or Compressed air energy. There are no Federal and/or Private sponsored research grants and/or developments in this project and it's intended usage is in a windmill electrical and/or air compressor generator. | 01-28-2010 |
| 20100028157 | WIND TURBINE BLADE TIP SHAPES - A blade for a wind turbine includes a chord of length “c” positioned with a leading edge tip chord angle and trailing edge tip chord angle of between approximately 45 and 75 degrees; a tip having a shear web plane radii distribution in the ranges of | 02-04-2010 |
| 20100028158 | HIGH-PRESSURE TURBINE BLADE AND PROCEDURE FOR REPAIR OF HIGH-PRESSURE TURBINE BLADES - The invention relates to a procedure for repair of high pressure turbine blades of an aircraft engine, with the steps: —separating a damaged section of the high pressure turbine blade; and—generating a section to replace the separated section on or upon the high pressure turbine blade by means of laser beam generation from the powder bed, as well as a high pressure turbine blade. | 02-04-2010 |
| 20100028159 | Semi-Rigid Wind Blade - An airfoil | 02-04-2010 |
| 20100040475 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE - When cold and in the uncoated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance from the point in question to a reference plane P | 02-18-2010 |
| 20100054946 | COMPRESSOR BLADE WITH FORWARD SWEEP AND DIHEDRAL - An airfoil for use as rotor blades in compressors for turbomachines, such as gas turbine engines. The airfoil includes increased forward sweep and forward dihedral effective to reduce losses generated by interaction of tip clearance flow, secondary flows and passage shocks. | 03-04-2010 |
| 20100054947 | BLADES OF A CEILING FAN (1) - The blades of a ceiling fan are respectively provided with a top surface, a bottom surface and a wind-confronting portion obliquely formed along an edge of the top surface and the bottom surface. The wind-confronting portion is composed of two slopes respectively tapered symmetrically from the top surface and the bottom surface to an outmost tip of the blades. No matter if the top surface or the bottom surface faces downward after having the blades fixed with a shaft of a motor, the are a of the wind-confronting portion confronting air is always such minimized that air drag can be lowered. Moreover, with the top surface and the bottom surface attached with different patterns, various pattern combinations can be obtained to diversify the outlook of the ceiling fan. | 03-04-2010 |
| 20100054948 | BLADES OF A CEILING FAN (2) - The blades of a ceiling fan are respectively provided with a top surface, a bottom surface, a front wind-confronting portion and a rear wind-confronting portion respectively formed along an edge of two sides of the top surface and the bottom surface. The front wind-confronting portion and the rear wind-confronting portion wind-confronting portion are respectively formed of a slope having the same inclined direction. No matter if the top surface or the bottom surface faces downward after having the blades fixed with a shaft of a motor, the area of the front wind-confronting portion or the rear wind-confronting portion confronting air is always such minimized that air drag can be lowered. Moreover, with the top surface and the bottom surface attached with different patterns, various pattern combinations can be obtained to diversify the outlook of the ceiling fan. | 03-04-2010 |
| 20100054949 | RANDOM PITCH IMPELLER FOR FUEL PUMP - A random pitch impeller for a fuel pump has number of blades. An incremental angle of the blades is set by the expression: | 03-04-2010 |
| 20100061860 | STEAM TURBINE ROTATING BLADE FOR A LOW PRESSURE SECTION OF A STEAM TURBINE ENGINE - A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a skewed axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. The blade includes an exit annulus area of about 30.5 ft | 03-11-2010 |
| 20100061861 | STEAM TURBINE ROTATING BLADE FOR A LOW PRESSURE SECTION OF A STEAM TURBINE ENGINE - A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a tangential entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. The blade includes an exit annulus area of about 18.1 ft | 03-11-2010 |
| 20100061862 | AIRFOIL SHAPE FOR A COMPRESSOR BLADE - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape. | 03-11-2010 |
| 20100074755 | METHOD FOR REPAIRING TURBINE BLADES - A method for repairing turbine blades by replacing at least a part of the blade profile, the method having: a) manufacture of a replacement blade part; b) separation of the damaged area with a standardized cutting plane, leaving behind a remaining blade; c) matching of the replacement blade part to the actual geometry of the remaining blade; d) connecting or joining of the replacement blade part to the remaining blade by soldering of at least one web and welding of an outer contour. | 03-25-2010 |
| 20100074756 | PROPELLER FOR BOAT - A propeller for a boat includes a hub having a tail portion with an outlet, and a plurality of blades equiangularly disposed on the hub. The outer periphery of the tail portion defines with a center axis of the hub a distance gradually decreasing toward the outlet. Thus, the propeller has the advantages of reducing the drag and increasing the propulsive force of the boat when it rotates. | 03-25-2010 |
| 20100080709 | WIND TURBINE BLADE - Disclosed is a blade including a blade body including a leading edge and a trailing edge, and at least one trailing edge cavity defined by a blade area disposed in at least partial alignment with the trailing edge, the at least one cavity extending a desired depth into said blade body in a direction of the leading edge. | 04-01-2010 |
| 20100080710 | Stator vanes of a stator vane cascade of an aircraft gas turbine - A method for manufacturing a stator vane | 04-01-2010 |
| 20100086410 | MIXING IMPELLER - An impeller for use in association with an extraction plate adapted for defibering liquid slurry stock and causing defibered material to pass through the extraction plate. The impeller includes a cylindrical central body portion and a plurality of vanes extending outwardly in a generally tangential direction from the central body portion. The vane leading face height from an extraction side to an air foil surface is substantially constant from the vane outer end to where the vane is attached to the central body portion at the radially outward edge of the central body portion, and then thereafter gradually decreasing in height from the radially outward edge of the body central portion to the airfoil surface at the vane inner end. | 04-08-2010 |
| 20100092298 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. | 04-15-2010 |
| 20100092299 | HELICOPTER ANTITORQUE TAIL ROTOR BLADE - A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has an end portion extending between a reference section and a radially outer end of the blade with respect to a rotation axis of the blade; the rotation axis is outside the blade and crosswise with respect to the longitudinal axis; the length of the chord at the end portion decreases from the reference section to the radially outer end; and the leading and trailing edges are joined at the radially outer end. | 04-15-2010 |
| 20100098548 | Mixed Flow Turbine or Radial Turbine - Intended is to provide a mixed flow turbine or a radial turbine, which can suppress an abrupt increase in a load to be applied to the front edge portion of a blade, thereby to reduce an incidence loss. The mixed flow turbine or the radial turbine comprises a hub ( | 04-22-2010 |
| 20100104444 | BLADE FOR WIND TURBINES | 04-29-2010 |
| 20100104445 | Fan Blade Modifications - A winglet is coupled with an end of a fan blade. The fan blade has an upper surface, a lower surface, a leading edge, and a trailing edge. The fan blade defines a chord and a maximum thickness. The winglet comprises a substantially vertical member that has a perimeter defined by a lower edge, an upper edge, and a rear edge, which meet at rounded corners. The rear edge of the vertical member has a length that is greater than the maximum thickness of the end of the fan blade. The vertical member has a length that is greater than the chord of the fan blade. The rear edge of the vertical member protrudes rearwardly relative to a vertical plane tangential to the trailing edge of the end of the fan blade. A mounting member may extend from the vertical member to couple the winglet with the fan blade. | 04-29-2010 |
| 20100119372 | COOLED COMPONENT WITH A FEATURED SURFACE AND RELATED MANUFACTURING METHOD - An improved type of cooled component is disclosed. The cooled components, such as turbine airfoils and combustors, have a base metal structural member, including a metal sheet or blank, with a featured surface. The features, such as fins, pins, and other protrusions, as well as divots, indentions, slots, channels, and holes, are formed by lithographic processes. The protrusions can be formed from a different material than the metal sheet or blank, preferably one with superior heat-conductive or oxidation properties. A related method of manufacturing is also disclosed. | 05-13-2010 |
| 20100119373 | Wind Turbine Rotor Blade - A wind turbine rotor blade is provided, the rotor blade comprising a root portion and a tip portion extending therefrom. The root portion comprises a plurality of inserts embedded therein, each insert being configured to receive respective connecting means for connecting the wind turbine rotor blade to a wind turbine hub. The inserts are of at least two different lengths such that they extend into the rotor blade by different distances. | 05-13-2010 |
| 20100119374 | WIND TURBINE & WIND TURBINE BLADE - A wind turbine blade to be mounted to a wind turbine hub configured to be mounted for rotation in a hub plane of rotation so as to generate electricity is provided. The blade extends lengthwise between a hub mounting root end and a blade tip end. The blade extends a blade width between a leading edge and trailing edge such that when mounted to the hub the blade is twisted at the root end by an angle of between 19° to 21° relative to the plane of rotation of the hub and wherein the blade is twisted at a tip end to rotate in a plane parallel to the plane of rotation of the hub to within ±1°. | 05-13-2010 |
| 20100124505 | Fan and Fan Wheel Thereof - A fan and a fan wheel thereof are provided. The fan comprises the fan wheel and a fan cowl. The fan wheel comprises a hub and a plurality of blades. The hub can define an axial direction and a radial direction, and each of the blades has an axial length and a radial length. The portion of each of the blades that extends along the axial direction over a top edge of a side wall of the hub accounts for the axial length in a ratio between one third and two thirds. A connection portion connecting a central portion to the side wall of the hub, and a tip and a tail of each of the blades, as well as a flow conducting portion connecting a top wall to a central hole of the fan cowl, are all rounded. Thereby, the fan and the fan wheel thereof can strengthen the flow rate and reduce the noise generated by the fan. | 05-20-2010 |
| 20100135813 | TURBINE BLADE FOR A GAS TURBINE ENGINE - The turbine blade comprises an airfoil having opposite pressure and suction sidewalls extending from a platform to a free end tip and in a chordwise direction from a leading edge to a trailing edge. The blade has two winglets extending in a chordwise direction from adjacent the leading edge to adjacent the trailing edge. Each winglet extends from the pressure sidewall upwardly and outwardly from the sidewall to provide a channel between them. Each winglet has a free end extending laterally beyond a surface defined by the pressure sidewall offset. | 06-03-2010 |
| 20100135814 | RETROFIT SLEEVE FOR WIND TURBINE BLADE - A wind turbine blade includes a body having a first surface characteristic; and a sleeve, arranged on the body, having a second surface characteristic which is different from the first surface characteristic. | 06-03-2010 |
| 20100150728 | CYLINDRICAL WIND TURBINE - A vertical wind turbine includes a blade which has opposite force producing sides that lie on opposite sides of the longitudinal axis along its direction of travel. The aerodynamic surfaces are driven by the wind through four phases of rotation. Driving torque is produced during three of the four phases. The blade includes a v-shaped nosepiece with rearward facing surfaces on each side that cup the wind during three of the four phases. The split tail of the blade captures the wind during a down wind phase of rotation. | 06-17-2010 |
| 20100150729 | GAS TURBINE ENGINE AIRFOIL - A rotor blade for a gas turbine engine includes an airfoil that extends in span between a root and a tip region. A leading edge and a trailing edge of the airfoil section extend between a chord line of the airfoil. A sweep angle is defined at the leading edge of the airfoil section, and a dihedral angle is defined relative to the chord line of the airfoil section. The sweep angle and the dihedral angle are localized at the tip region of the airfoil section. | 06-17-2010 |
| 20100158692 | Wind energy conversion apparatus - A wind energy conversion apparatus comprising supporting structure is presented. The apparatus further comprises shaft having a first and a second end, which is rotatably journalled in said supporting structure, as well as at least one rotor blade having a first end and a second end, which rotor blade is mounted on said shaft with both ends. The object of the presented wind energy conversion apparatus is to improve the known apparatus and to provide an apparatus which is capable of converting a larger amount of wind energy into other forms of energy. Accordingly wind energy conversion apparatus according to the invention is to that end characterised in that the rotor blade is provided with additional wind capturing means. | 06-24-2010 |
| 20100158693 | TEST BLADE - The present invention relates to a test blade for a blade-release test. The blade is arranged in use to be mounted on a hub for rotation, and to be released therefrom by the action of a controlled explosion. The blade is arranged to receive at least one explosive charge and at least one detonator for detonating the charge. The blade further comprises a cut-through portion extending completely through the blade from a front face to a rear face, the cut-through portion also extending part way along the blade in an axial direction between a leading edge and a trailing edge of the blade. | 06-24-2010 |
| 20100166564 | TURBINE BLADE COOLING CIRCUITS - A turbine blade with a generally hollow airfoil having an outer wall that defines a chamber for receiving cooling air, the airfoil comprising a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, a concave pressure side, and an insert disposed within the chamber that is configured to initially receive at least a portion of the cooling air entering the chamber and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall, the insert further comprising a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto, wherein the chamber and insert narrow as they extend toward the trailing edge, the insert eventually terminating and the chamber eventually terminating at a pin array section, wherein a first distance exists that comprises the generally axial distance between the position of downstream termination point of the insert and the position of an upstream beginning point of the pin array section, wherein the pin array section, at a downstream end, comprises a plurality of openings that define an inlet to a plurality of trailing edge cooling apertures, and wherein the chamber, the insert, and the pin array section are configured such that the first distance is approximately minimized. | 07-01-2010 |
| 20100183445 | BLADE STRUCTURE FOR HEAT SINK FANS - A fan blade for heat sink fans is provided. The fan blade includes a wheel hub and a plurality of blades which is disposed around the rim of the wheel hub. The surfaces of the blade fans are designed with protruding or recessing inhibiting part. The flow rate on the blade surfaces is made unsteady by the inhibiting part as the airflow is flowing by to form a constant air flow impact and generate a boundary layer on the blades effectively. The effective second order distribution of the pressure rise is formed, and the effective working area of the fan is expanded. The improvement increases the static pressure and lowers the noise. | 07-22-2010 |
| 20100196165 | STIRRING DEVICE FOR ACTIVATED SLUDGES - The invention relates to a stirring device for activated sludges comprising a hyperboloid stirring body ( | 08-05-2010 |
| 20100196166 | Optimised layout for wind turbine rotor blades - A wind turbine rotor blade defined by a tip point, a shoulder, a maximum chord interval which is defined as the radial interval over which the blade chord is no less that 95% of the shoulder chord and which extends over at least 15% of the entire blade length, and an outer blade interval extending from the maximum chord interval to the tip point, wherein the outer blade interval has a concave hyperbolic chord distribution from the maximum chord interval towards the tip point. Further a method for optimizing the chord distribution of a wind turbine blade layout is provided, wherein the chord distribution is optimized by optimizing the chord distribution in the maximum chord interval by maximizing the ratio of the annual energy production to the loads acting on the blade and in the outer blade interval with respect to the annual energy production alone. | 08-05-2010 |
| 20100215504 | PUMP ROTOR AND PUMP COMPRISING A PUMP ROTOR OF SAID TYPE - The pump rotor ( | 08-26-2010 |
| 20100215505 | BLOWER IMPELLER AND BLOWER - A blower impeller includes a substantially cylindrical cup portion, and a plurality of blades arranged on an outer circumferential surface of a circumferential wall portion of the cup portion. The cup portion includes on an inner circumferential surface of the circumferential wall portion thereof a plurality of axially extending first ribs and a plurality of second ribs arranged between the first ribs. The first and second ribs are arranged in a circumferential direction. A virtual envelope joining radially inner end portions of the first ribs has a smaller diameter than that of a virtual envelope joining radially inner end portions of the second ribs. | 08-26-2010 |
| 20100221116 | ROTOR FOR GENERATING ELECTRICAL POWER FROM A FLOW MEDIUM - A power generation system that generates power in low flow situations is disclosed. The system includes a set of vanes, wherein each vane is mounted on a corresponding mast, so as to selectively transmit energy from the flow medium to a rotor shaft or to freely deflect in the direction of flow, depending on whether the flow impinges on the vanes in an energy-producing or a non-energy-producing direction. This is achieved by mounting each vane on its mast, so that it deflects in the flow direction when the vane is subjected to non-energy-producing flow energy, and also coupling each vane to the mast of an adjacent vane, so that the vane exerts a pull force on the mast of the adjacent vane, when the vane is capturing energy-producing flow energy. | 09-02-2010 |
| 20100226779 | Ni-Base Superalloy, Method for Producing the Same, and Turbine Blade or Turbine Vane Components - A Ni-base superalloy having a chemical composition comprising Cr: 3.0-5.0 wt %, Co: 5.0-10.0 wt %, Mo: 0.5-3.0 wt %, W: 8.0-10.0 wt %, Ta: 5.0-8.0 wt %, Nb: 3.0 wt % or less, Al: 4.5-6.0 wt %, Ti: 0.1-2.0 wt %, Re: more than 3.0-4.0 wt %, Ru: 0.2-4.0 wt %, Hf: 0.01-0.2 wt %, and the balance being Ni and unavoidable impurities, a method for producing the same, and turbine blade or turbine vane components are disclosed. The Ni-base superalloy has high creep strength and textural stability under high temperature environment, and is excellent in applicability to turbine blade or turbine vane components of large-sized gas turbines. | 09-09-2010 |
| 20100226780 | VARYING FLUENCE AS A FUNCTION OF THICKNESS DURING LASER SHOCK PEENING - A method for simultaneously laser shock peening opposite laser shock peening surfaces on opposite sides of an article, such as a gas turbine engine airfoil, with varying thickness using oppositely aimed laser beams and varying surface fluence of the laser beams over the laser shock peening surfaces as a function of the thickness of the article beneath each one of a plurality of laser shock peened spots formed by the beams on the surfaces. The fluence may be equal to the thickness multiplied by a volumetric fluence factor, the volumetric fluence factor being held constant over the laser shock peening surface. The volumetric fluence factor may be in a range of about 1200 J/cm | 09-09-2010 |
| 20100232971 | AIR FAN MODULE AND A FLOW DIRECTING BLADE ASSEMBLY THEREOF - An air fan module and a flow directing blade assembly thereof aim to reduce noises generated during operation of the air fan caused by friction between blades and air and improve cooling efficiency. The air fan module includes a fan frame which has an air inlet, an air outlet and a housing space formed between them to hold a flow directing blade assembly. The flow directing blade assembly has an axis and a plurality of blades mounted onto the axis. Each blade has a first end surface and a second end surface. The first and second end surfaces have respectively a plurality of first flow directing portions and second flow directing portions that are respectively spaced from each other and formed in an asymmetrical manner. Air can form steady airflow by channeling of the first flow directing portions and the second flow directing portions of two neighboring blades. | 09-16-2010 |
| 20100232972 | ROTOR BLADE FOR A WIND POWER PLANT - The invention concerns a rotor blade of a wind power installation and a wind power installation. One advantage of the present invention is to provide a rotor blade having a rotor blade profile, and a wind power installation, which has better efficiency than hitherto. A rotor blade of a wind power installation, wherein the rotor blade has a thickness reserve approximately in the range of between 15% and 40%, preferably in the range of between about 23% and 28%, and wherein the greatest profile thickness is between about 20% and 45%, preferably between about 32% and 36%. | 09-16-2010 |
| 20100247320 | WIND TURBINE BLADE - A turbine blade ( | 09-30-2010 |
| 20100247321 | ANTI-FOULING COATINGS AND ARTICLES COATED THEREWITH - An article including a metallic substrate is presented. The article further includes a sacrificial layer disposed on a surface of the substrate and an anti-fouling layer disposed on the sacrificial layer. The anti-fouling layer includes a metal-polymer composite. An article including an anti-fouling layer having a nitride is also presented. | 09-30-2010 |
| 20100254817 | High performance low noise rotorcraft blade aerodynamic design - One embodiment of the present invention is a main rotor helicopter blade for generating higher lift with less drag and delaying stall at high Mach numbers. A cross-section of this blade includes aft camber. The difference between a chord line of the cross-section and a camber line of the cross-section increases from a leading edge of the cross-section to a maximum between a trailing edge of the cross-section and a midpoint of the chord line and decreases to the trailing edge producing the aft camber of the blade. The aft camber generates higher lift with less drag and delays stall at high Mach numbers. | 10-07-2010 |
| 20100254818 | Process for preparing turbine blades or vanes for a subsequent treatment, and associated turbine blade or vane - Process for preparing turbine blades or vanes for a subsequent treatment, for example the application of a coating and/or a material-removing operation, wherein the turbine blade or vane has an airfoil, which is delimited at at least one end by an endplate with peripheral surfaces, wherein at least one of the peripheral surfaces is at least partially covered prior to the treatment of the turbine blade or vane. In the process a covering strip is fitted onto at least one peripheral surface to form a plug connection. | 10-07-2010 |
| 20100260609 | Advanced booster rotor blade - A rotor airfoil having a leading edge extending from a root to a tip, an inner span region and an outer span region the leading edge having a sweep angle profile such that the sweep angle increases from the root a first height location at a first rate of change of sweep angle that is substantially constant and thereafter increases at a second rate of change of sweep angle that is substantially constant. | 10-14-2010 |
| 20100260610 | BLADE FOR AN AXIAL COMPRESSOR AND MANUFACTURING METHOD THEREOF - The disclosure provides blades, and the modification thereof, for stages | 10-14-2010 |
| 20100266414 | FLUID ENERGY CONVERTER - A fluid energy converter, such as windmill or a wind turbine, includes a rotor having a front rotatable hub and a back rotatable hub. In some embodiments, a plurality of blades extends from the front hub to the back hub. A suitable blade includes a front section, a tip, and a back section. In one embodiment, the chord of the tip cross section is at an angle relative to the tangent of the rotor radius. The tip chord can be perpendicular to the direction of movement of the fluid. In some cases, the profile of a blade front section, from its root to the tip, forms a concave curve. In one case, the profile of the blade tip, from a junction root to the tip, forms a convex curve. A front section, an apex, and a back section of a blade form a generally parabolic shape. | 10-21-2010 |
| 20100272573 | RESIN FAN - There is provided a resin fan capable of enhancing the mechanical strength in a weld part in view of the direction of reinforcing fiber. On the outer peripheral surface | 10-28-2010 |
| 20100278653 | VERTICAL AXIS TURBINE AND METHOD OF MAKING SAME - A vertical axis turbine and method of making same is disclosed. The device and method comprise a plurality of blades rotatably disposed around an axis of rotation at a plurality of blade locations, each blade being twisted at a first angle about its longitudinal axis, each blade having its distal ends located a predetermined distance from the axis of rotation, each blade being bent at one or more central locations along the longitudinal axis so the one or more central locations are the same predetermined distance from the axis of rotation as the distal ends, each blade having a foil cross section perpendicular to the axis of rotation for maintaining unidirectional rotation of that blade about the axis of rotation in a fluid flow, and each blade having its longitudinal axis tilted at a second angle with respect to the axis of rotation. | 11-04-2010 |
| 20100290916 | ROTOR BLADE FOR A WIND TURBINE - A rotor blade of a wind power installation in which the rotor blade, in particular in the central region of the rotor, the so-called main board, has a lift-drag ratio which in the region of about ±2° from the optimum pitch angle has a lift-drag ratio value of more than 80%, preferably 90% and more of the maximum value of the lift-drag ratio. | 11-18-2010 |
| 20100303629 | FLUID FLOW MACHINE WITH A BLADE ROW GROUP FEATURING A MERIDIONAL EDGE DISTANCE - A main flow path of a fluid flow machine includes N adjacent member blade rows firmly arranged relative to each other in both a meridional direction m and a circumferential direction u. A number of the member blade rows, N, is greater than/equal to 2 and (i) designates a running index with values between 1 and N. A trailing edge HK (i) of a blade of the member blade row (i) is spaced from a leading edge VK(i+1) of a blade of the adjacent, downstream member blade row (i+1) by a meridional edge distance D in a meridional plane established by axial direction x and radial direction r. A value of D along a height of the main flow path increases towards the main flow path confinement at least along a part of the area between the main flow path center and the main flow path confinement. | 12-02-2010 |
| 20100303630 | VARIABLE CHORD MORPHING HELICOPTER ROTOR - A variable chord morphing helicopter rotor blade is disclosed. The variable chord morphing helicopter rotor blade includes an extensible quasi-static chord section connected to the rotor blade, an adjusted airfoil chord length of the rotor blade corresponding to extension of the quasi-static chord section relative to a baseline airfoil chord length, the adjusted airfoil chord length determined according to helicopter flight conditions. | 12-02-2010 |
| 20100310378 | DYNAMIC PUMP WHEEL FOR A PUMP AND A PUMP DEVICE COMPRISING A DYNAMIC PUMP WHEEL - A pump wheel for a pump has a base body that can be rotated about a rotational axis and on which at least one wing element is arranged for conveying a fluid during the rotation of the pump wheel. The pump wheel has a pivoting device by which the at least one wing element is mounted in such a way that it can pivot about a pivoting axis arranged at an angle larger than zero degrees in relation to the rotational axis of the pump wheel, according to a rotational direction, between an action position in which a conveyor pressure for the fluid can be generated, and an idle position in which there is essentially no conveyor pressure. | 12-09-2010 |
| 20100316500 | Wind turbine rotor blade and airfoil section - The present invention includes a set of airfoils, U rails and V rails taken together to describe a blade for use with a horizontal axis wind turbine. The blade's design includes a maximum thickness higher than conventional blades employed for the same use thereby providing better load bearing structural characteristics while at the same time maintaining the requisite aerodynamic qualities for similar blades. The blade has a Reynolds number in the range of about 1.1 to 1.3×10 | 12-16-2010 |
| 20100329875 | ROTOR BLADE WITH REDUCED RUB LOADING - An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip portion, wherein the tip-grinder capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-rake that facilitates reducing loading induced to said airfoil during tip rubs. | 12-30-2010 |
| 20100329876 | NICKEL-BASE SUPERALLOYS AND COMPONENTS FORMED THEREOF - Gamma prime nickel-base superalloy and components formed therefrom. The alloy contains, by weight, 11.3 to 13.3% cobalt, 12.4 to 15.2% chromium, 2.1 to 2.7% aluminum, 3.6 to 5.8% titanium, 3.5 to 4.5% tungsten, 3.1 to 3.8% molybdenum, 0.0 to 1.2% niobium, 0.0 to 2.3% tantalum, 0.0 to 0.5% hafnium, 0.040 to 0.100% carbon, 0.010 to 0.046% boron, 0.030 to 0.080% zirconium, the balance nickel and impurities, wherein the Nb+Ta content is 0.0-3.5%. | 12-30-2010 |
| 20100329877 | METHOD FOR PRODUCING A FORGING FROM A GAMMA TITANIUM ALUMINUM-BASED ALLOY - Method for producing a forging from a gamma titanium aluminum-based alloy. The method includes heating at least a portion of a cylindrical or rod-shaped starting or raw material to a temperature of more than 1150° C. over a cross section of the at least a portion. The at least a portion corresponds to points at which the forging to be shaped has volume concentrations. The method also includes deforming the at least a portion through an applied force to form a biscuit having different cross sectional areas over a longitudinal extension of the biscuit, and finishing the forging through a second heating to a deformation temperature and at least one subsequent step. | 12-30-2010 |
| 20100329878 | ADJUSTABLE CAMBER AEROFOIL - The present invention relates to an aerofoil ( | 12-30-2010 |
| 20110002788 | METHOD OF FORMING AN INTERNAL STRUCTURE WITHIN A HOLLOW COMPONENT - A method of forming an internal structure within a hollow component ( | 01-06-2011 |
| 20110002789 | METHOD FOR PRODUCING AND REPAIRING A PART, AND PART OF A GAS TURBINE - The invention relates to a method for producing and repairing a part comprising at least two joined metal components, especially components of a gas turbine. In said method, corresponding joining surfaces of the components are joined together and connected by means of a pressure welding process, a machining allowance in the area of a joining zone of the two joining surfaces is upset during the joining process, and once the two components have been joined together, the machining allowance is machined by means of a precise electrochemical machining (PECM) process until a predefined final contour of the part has been obtained. The invention further relates to a gas turbine part obtained by means of the disclosed method. | 01-06-2011 |
| 20110008174 | Application of elastomeric vortex generators - A method of improving aerodynamic performance of foils by the application of conformal, elastomeric vortex generators. The novel use of elastomers allows the application of various forms of vortex generators to sections that have been problematic from engineering and cost considerations. A novel and efficient vortex generator profile is identified, which develops an additional co rotating vortex at low energy expenditure. The mechanisms allow for the application of transverse vortex generators, or Gurney Flaps/Lift Enhancement Tabs/Divergent Trailing Edges, to propellers, rotorblades, and to wings/flaps/control trailing edges. Cove Tabs are additionally described using an elastomeric transverse vortex generator to achieve performance improvements of a high lift device. | 01-13-2011 |
| 20110014057 | ENGINE BLADE WITH EXCESSIVE LEADING EDGE LOADING - A free end of a blade of a fluid flow machine has a skeleton line camber distribution having an excessive value to a relative skeleton line camber of at least α*=0.35 for a related running length of s*=0.1 in a blade profile flow line section between the free end and a blade section at 30% of a main flow path width from the free end. S* is a local running length relative to a total running length of the profile skeleton line and α* is an angular change of the skeleton line relative to a total camber of the skeleton line from a leading edge to a related running length s*. The skeleton line camber distribution runs between leading edge point V (s*=0, α*=0) and trailing edge point H (s*=1, α*=1). | 01-20-2011 |
| 20110014058 | PROPELLER - On a propeller, more particularly one for aircraft applications, an efflux slot ( | 01-20-2011 |
| 20110020129 | REVERSIBLE SYSTEM FOR DIVIDING AEROGENERATOR BLADES INTO SEVERAL PARTS - Aerogenerator blades of several sections or sectors are joined by specifically designed inserts that allow assembly to be carried out at a wind farm, particularly, at the base of a tower. These inserts are disposed both inside and outside of the original blades, in a single piece or several pieces and joined to the blades by any mechanical, physical or material fusion connection. Adhesives and other type of joints can also be used for this purpose. | 01-27-2011 |
| 20110020130 | GAS TURBINE ENGINE BLADE FOR AIRCRAFT AND MANUFACTURING METHOD THEREOF - A gas turbine engine blade for aircraft which has a 3-dimensional blade surface shape twisted around a center line at an angle of 45 degrees or more and 70 degrees or less, wherein the aforementioned blade is provided with multiple composite material prepregs which contain reinforced fiber and which are integrally molded after being laminated in the thickness direction, and the aforementioned reinforced fiber runs continuously without interruption within each layer of the aforementioned composite material prepregs. | 01-27-2011 |
| 20110027094 | BLOWER FOR A PARTICULATE LOADER AND TRANSFER APPARATUS - A blower for a particulate loader and transfer apparatus, comprising, at least one blade having a proximal and distal end, means for rotating the at least one blade in a direction about an axis of rotation, wherein the proximal end of the blade is nearer to the axis of rotation than the distal end of the blade is to the axis of rotation and wherein the blade is angled so that as the blade rotates about the axis, the proximal end of the blade precedes the distal end of the blade. | 02-03-2011 |
| 20110033304 | Device for a Runner - A device for a runner ( | 02-10-2011 |
| 20110033305 | Turbine vane for a stationary gas turbine - A turbine vane for a stationary gas turbine is provided. The turbine vane includes a hollow vane blade, wherein a rib is provided inside the vane blade to allow a pressure side wall and a suction side wall to support one another. The rib has an opening penetrating the rib near a wall at a height of an external fillet between a side wall, and a platform surface for extending a life of the turbine vane. By the opening, material accumulations in a transition region are avoided or the accumulation is reduced, whereby increases in stiffness and higher temperature gradients associated therewith are avoided. | 02-10-2011 |
| 20110033306 | CROSS-FLOW FAN AND AIR CONDITIONER EQUIPPED WITH SAME - A crossflow fan includes an impeller formed by plate-like blades | 02-10-2011 |
| 20110044819 | Water Turbine Drive Wheel - The object of the invention is a drive wheel of a water turbine which makes it possible to convert kinetic energy of the water stream into rotational mechanical energy of the turbine. The water turbine drive wheel, according to the invention, is characterized by such features that the angle B between the rotation plane of wheel P and the water stream direction s ranges between 3° to 87° and that the wheel is immersed only partially in the water stream up to the blade height L which is within 0.003 to 0.497 of the outer diameter of the water turbine drive wheel D. | 02-24-2011 |
| 20110044820 | CONSOLIDATED COMPOSITE PRE-FORM - The present invention relates to a consolidated composite pre-form for reinforcing a composite structure, said pre-form comprising fibres and a binding agent, said pre-form having a sheet-like structure with an upper major surface and a lower major surface, and said pre-form being provided with recesses on at least a portion of at least one of said major surfaces. | 02-24-2011 |
| 20110052400 | Horizontal axis wind turbine (HAWT) - A horizontal axis wind turbine (HAWT | 03-03-2011 |
| 20110052401 | JOINED TURBINE ROTOR COMPONENTS AND METHOD THEREOF - A method is disclosed for joining steel and nickel alloy turbine rotor components as is a joined turbine rotor combination produced by the method. The method includes: providing a steel rotor component; providing (e.g., laying down) a nickel alloy butter layer on the steel component; providing a nickel alloy rotor component; and welding the nickel alloy butter layer to the nickel alloy component using a nickel alloy weld filler so as to join together the components. The butter layer, laid first to the steel component, can enable reliable testing, for defects, of a nickel alloy/steel fusion line. | 03-03-2011 |
| 20110052402 | FASTENING OF THE ROTOR OF A CENTRIFUGAL PUMP BEFESTIGUNG DE LAUFRADES EINER KREISEL PUMPE - The invention relates to a rotor wheel constructed of sheet metal for a centrifugal pump, particularly a multi-stage centrifugal pump, with means for fastening to the drive shaft of an electric motor, wherein the rotor wheel has a central coaxial opening in which a sleeve is fastened coaxially, wherein the sleeve projects out of the rotor wheel on at least one side of the rotor wheel, and wherein the sleeve has, in its inner wall, projecting, axially parallel ridges for fastening into axially parallel notches or grooves of the motor drive shaft. | 03-03-2011 |
| 20110064582 | WIND TURBINE BLADE WITH HIGH-LIFT DEVICES - Wind turbine blade with high-lift devices in the leading edge and/or trailing edge (the latter has a relative thickness) in the root area, so that aerodynamic performance is improved and therefore the amount of energy extracted from the wind compared to traditional blades with cylindrical or oval roots. | 03-17-2011 |
| 20110070090 | WINGTIP DEVICE FOR THE TIP OF A WING, BLADE OF A WIND GENERATOR OR MARINE GENERATOR FOR REDUCING OR EVEN ELIMINATING MARGINAL SWIRL - A wing-tip device for the tip of a wing, or a blade of a wind generator, or a blade of a marine generator that makes it possible to reduce or even cancel what are known as wing-tip vortices. In the case or a wind generator, the result provides a start-up with less wind, control and energy efficiency that are highly productive throughout its use while at the same time significantly reducing the noise caused by the vortex. | 03-24-2011 |
| 20110076149 | SYSTEMS AND METHODS OF ASSEMBLING A ROTOR BLADE EXTENSION FOR USE IN A WIND TURBINE - A method of assembling a blade extension assembly for use with a wind turbine. The method includes removing a tip end of a tip portion of a rotor blade and coupling a tip wall to the tip portion. The tip wall extends between a first sidewall and a second sidewall and includes a plurality of slots defined therein. A blade extension assembly is coupled to the tip portion. | 03-31-2011 |
| 20110076150 | AIRFOIL SHAPE - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the TABLE. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape. | 03-31-2011 |
| 20110085911 | FIXING DEVICE - A fixing device for fixating a segment of a wind turbine blade to a mold in which the blade segment is manufactured, wherein the blade segment has a fixating portion. The fixing device comprises: a first portion for removably fixating the blade segment at its fixating portion to the mold; and a second portion for fixating the fixing device to the mold. | 04-14-2011 |
| 20110091325 | Tool and Method for Rapid Design and Reduction of Rotor Mass - Wind turbine rotors are designed by means of computationally intensive algorithms, simulation tools and various models. These art methods, however, have not been successful in relating the blade mass directly to the aerodynamic, rotational dynamics and material parameters. Consequently, modelers are often grappling with discrepancies and ambiguities. Prior art generally constructs the empirical relation M | 04-21-2011 |
| 20110103961 | METHOD OF PRODUCING AN OXIDE DISPERSION STRENGTHENED NICKEL-BASE SUPERALLOY - A method of producing an oxide dispersion strengthened nickel-base superalloy, comprising introducing an oxide dispersoid material into a plasma gun of a plasma spray apparatus, where it is sublimed and turned to vapour; and introducing a nickel-base superalloy material into the plasma spray apparatus at a cooler location, downstream of the plasma gun, such that the oxide dispersoid material condenses on the superalloy material to produce the oxide dispersion strengthened nickel-base superalloy. | 05-05-2011 |
| 20110110787 | STATOR VANE FOR 3D COMPOSITE BLOWER - A method of fabricating a guide vane. The method produces a fiber preform by 3D weaving a single piece, the preform including a first portion extending along the longitudinal axis and constituting the preform for an airfoil of the vane, and at a longitudinal end of the first portion, a second portion constituting the preform for the platform of the vane, the second portion being produced as a first layer and a second layer facing the first layer and separated from the first layer by unlinking without cutting while producing the preform; folding the first and second layers such that each of them lies in a plane perpendicular to the longitudinal axis, substantially symmetrically to each other relative to the first portion, and such that a first region of the first layer covers a second region of the second layer in front of a front edge of the first portion; conforming the preform in a mold; and densifying the preform with a polymer matrix. | 05-12-2011 |
| 20110116934 | PUMPING ELEMENT DESIGN - A pumping element and method of turbomachinery design includes a blade having an incidence angle (α) and a blade angle (β), wherein a ratio of α/β is less than approximately 0.3. | 05-19-2011 |
| 20110123342 | COMPRESSOR WITH ASYMMETRIC STATOR AND ACOUSTIC CUTOFF - A method of manufacturing a compressor section includes the steps of defining a compressor section having a number of blades, and having one or more stator sections, each with numbers of vanes. Each stator section has at least two sections wherein the spacing between the vanes in a first of the sections is not equal to a spacing between the vanes in a second of the sections. The number of blades, and the number of vanes where all of the sections are selected to achieve acoustic cutoff. | 05-26-2011 |
| 20110129347 | PROCESS FOR PRODUCING A JOIN TO SINGLE-CRYSTAL OR DIRECTIONALLY SOLIDIFIED MATERIAL - A process for producing a join between a first component and a second component is disclosed. The second component contains a single-crystal or directionally solidified material. A polycrystalline layer is produced on a joining surface of the second component for joining the second component to the first component. The joining surface of the second component is joined to the first component by friction welding. | 06-02-2011 |
| 20110135483 | COMPOSITE TURBINE BLADE AND METHOD OF MANUFACTURE THEREOF - A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice. | 06-09-2011 |
| 20110135484 | Fluidic torque transfer device - A fluidic torque transfer device configured with a pump impeller that includes a pump shell, a pump blade attached to the pump shell, and a pump core attached to the pump blade; a turbine runner that includes a turbine shell, a turbine blade attached to the turbine shell, and a turbine core attached to the turbine blade; and a stator that includes a stator blade, and rectifies a flow of a hydraulic fluid from the turbine runner to the pump impeller. The outer contour line of the turbine blade extends outward in an extending direction of a rotation center axis of the pump impeller and the turbine runner on the fluid outlet side of the turbine runner more than an outer contour line of the pump blade on the pump shell side. | 06-09-2011 |
| 20110142659 | VERTICAL AXIS WIND TURBINE WITH SELF-STARTING CAPABILITIES - A vertical axis wind turbine and vertical axis wind turbine assembly comprising a rotary body and a plurality of blades. A cross section through each blade of the plurality of blades transverse to the rotary axis comprises an inner camber line, an outer camber line, and a chord line. The outer camber line comprises a first portion, a transition portion and a second portion. The second portion is longer, in the lengthwise direction, than a combined length of the first portion and the transition portion. The average second portion thickness is less than half an average first portion thickness. A magnitude of an average rate of change in a transition portion thickness is at least twice a magnitude of an average rate of change in a first portion thickness, and a magnitude of an average rate of change in a second portion thickness. | 06-16-2011 |
| 20110142660 | WIND TURBINE BLADE WITH INTEGRATED HANDLING MECHANISM ATTACHMENT BORES - A wind turbine blade includes a leading edge, a trailing edge, a suction side, and a pressure side. At least one integrated attachment bore is configured in each of the suction side and pressure side between the leading edge and trailing edge. The attachment bores are structurally configured for receipt of a handling mechanism therein for supporting the blade during a transportation, installation, or maintenance procedure. | 06-16-2011 |
| 20110150660 | AIRFOIL FOR A COMPRESSOR BLADE - The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD), stagger angle (γ) and camber angle (Δβ). The stagger angle (γ) and camber angle (Δβ) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight. | 06-23-2011 |
| 20110158816 | ROTOR BLADE FOR A WIND POWER PLANT - The present invention concerns a rotor blade for a wind power plant having an aerodynamic profile. The rotor blade has a main rotor body with an aerodynamic profile and a tip. The tip extends away from a plane of the rotor blade and in a direction of at least one of a low pressure side or a high pressure side of the main rotor body. The tip includes a tip upper edge, a tip leading edge, and a tip trailing edge. At least a portion of the tip leading edge is curved such that a width of the tip defined between the tip leading edge and the tip trailing edge is reduced towards the upper edge. | 06-30-2011 |
| 20110164985 | CONICAL FLUID TURBINE RUNNER - A turbine includes a cone and a plurality of curvilinear blades extending substantially along the length of the cone, from at or near the apex of the cone to at or near the base of the cone. In one embodiment, each of the curvilinear blades includes two walls, a first wall oriented substantially upstream with respect to the direction of fluid flow and a second wall oriented substantially downstream with respect to the direction of fluid flow. The first and second walls come together to form the edges of the curvilinear blades. | 07-07-2011 |
| 20110171032 | METHOD OF MANUFACTURING A SPAR FOR A WIND TURBINE FROM ELEMENTS HAVING GEOMETRICALLY WELL-DEFINED JOINT SURFACE PORTIONS - The invention provides a method of manufacturing a spar ( | 07-14-2011 |
| 20110171033 | POWER-GENERATING WIND TURBINE AND ITS MANUFACTURING METHOD - A power-generating wind turbine has a plurality of streamline-wing-shaped blades provided every predetermined angle around a rotation shaft, and the blades have lift coefficients of 1.0 or larger. Apertures are provided within a range of 55 to 95% from a front rim for a length of a chord on a rear face being the rotation shaft side to the chord. Thus, the turbine can be activated with a gentle breeze by drag on the apertures. Since the apertures are provided at a position of 55 to 95% for the chord length distant from the front rim of the rear face of the blade, in a high wind speed region where the turbine rotates by the lift of the blades, less disturbance of the wind flow is observed on the rear faces to be resistance, and thus high rotation torque can be obtained. | 07-14-2011 |
| 20110171034 | SEMI-PREG MATERIAL WITH A PROPERTY-ENHANCING SURFACE FILM FOR IMPROVED PROPERTIES - Semi-preg material is disclosed adapted for use in composite material comprising a) a first resin layer, b) covered on both side by layers of fibrous reinforcements whereby c) one of the two fabric layers is coated with a second resin layer and d) wherein said second resin layer has a tack level of not more than 100 N. Such semi-preg material has improved handling properties and contributes to the superior mechanical properties of the composite material formed therewith. | 07-14-2011 |
| 20110176926 | WIND TURBINE WITH LOW INDUCTION TIPS - A wind turbine having a rotor blade geometric design which reduces blade loads in particular, blade root bending moments, tilt moments and yaw moments. | 07-21-2011 |
| 20110182738 | METHOD AND APPARATUS FOR A SEGMENTED TURBINE BUCKET ASSEMBLY - A turbine bucket that includes a platform and an airfoil extending radially outward from the platform. The airfoil includes a root segment and a tip segment. The root segment includes a first end and a second end. The root first end extends from a radially outer surface of the platform. The root segment extends from the root first end to the root second end. The tip segment includes a tip first end and a tip second end. The tip first end is removably coupled to the root second end. The tip segment extends outward from the root second end to the tip second end. | 07-28-2011 |
| 20110182739 | VERTICAL AXIS TURBINE HYBRID BLADES - Blade designs for combining elements of drag and lift for vertical axis turbines are presented. Doing so may combine the best features of both types of turbine. | 07-28-2011 |
| 20110189023 | BLADE WITH NON-AXISYMMETRIC PLATFORM: RECESS AND BOSS ON THE EXTRADOS - A blade for a turbomachine impeller including an airfoil, and at least one platform at one of the ends of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring around a ring axis. In the blade, a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil and a first boss-like part located axially downstream of the first recessed part. Due to this configuration, efficiency of the blade is improved. | 08-04-2011 |
| 20110189024 | Wind Turbine Airfoil Family - Airfoils are provided for a wind turbine blade that is associated with a wind turbine hub. Each airfoil includes a blunt trailing edge, a substantially oval shaped suction side, and a substantially S-shaped pressure side. The airfoils decrease in cross-sectional area along the turbine blade in a direction extending away from the wind turbine hub. | 08-04-2011 |
| 20110194940 | WELDING PROCESS AND COMPONENT PRODUCED THEREFROM - A process of fabricating a rotating component and components formed thereby. The process includes fabricating preforms corresponding to portions of the component. Each preform has an interface surface at which the preforms can be joined to locate a first of the portions in a radially outward direction from a second of the portions. The preforms are then inertia welded together to form a profile having a solid-state weld joint containing a finer-grained material than other portions of the profile. The profile is then forged with dies to produce a forging. At least one of the dies has a recess into which the finer-grained material from the weld joint is expelled during forging to purge a joint region of the forging between the forging portions of the finer-grained material. The joint region contains grains distorted in an axial direction of the forging. | 08-11-2011 |
| 20110200443 | Nickel Base Gamma Prime Strengthened Superalloy - A nickel base gamma prime strengthened superalloy with a unique blend of adequate hot corrosion resistance, high oxidation resistance, high coating compatibility, adequate phase stability, adequate creep resistance and low density is disclosed. The composition comprises: Up to 20 wt % Co, between 12 and 14 wt % Cr, between 1 and 2 wt % Mo, between 1.4 and 2.8 wt % W, between 5.1 and 5.9 wt % Al, between 1.1 and 1.6 wt % Ti, between 3 and 7 wt % Ta, between 0.01 and 0.3 wt % of C+Zr+B, between 0.05 and 1 wt % Hf, between 0.05 and 1 wt % Si, and between 0.01 and 0.2 wt % of the sum of rare earths such as Sc, Y, the actinides and the lanthanides. The composition is intended for use in hot components such as gas turbine blades, and said components are preferably produced by clean casting. | 08-18-2011 |
| 20110200444 | MULTI-PANEL WIND TURBINE BLADE WITH IMPROVED JOINTS ON THE TRAILING EDGE - A multi-panel wind turbine blade with improved joints on the trailing edge, with an aerodynamic profile with a leading edge ( | 08-18-2011 |
| 20110200445 | PROPELLER FAN, FLUID FEEDER AND MOLDING DIE - In a propeller fan, a plurality of blades for blowing are coupled together with a space in a rotational direction kept therebetween, and a coupled region has a form for performing the blowing according to the rotation thereof. This structure provides a propeller fan greatly contributing to energy-saving properties and resource-saving design. | 08-18-2011 |
| 20110206526 | VERTICAL-AXIS WIND TURBINE HAVING LOGARITHMIC CURVED AIRFOILS - A vertical-axis, stator-less wind turbine includes a rotor rotatable about a vertical axis. The rotor has a plurality of vertically oriented rotor airfoils disposed circumferentially and with equiangular symmetry about the vertical axis. Each rotor airfoil has a substantially logarithmic curvature. | 08-25-2011 |
| 20110206527 | COMPRESSOR AEROFOIL - An aerofoil ( | 08-25-2011 |
| 20110206528 | Wing Structure for WIG Vehicle - The wing structure of a WIG vehicle comprising left and right main wings, left and right downward wings, and a rudder unit. The left and right main wings protrude out from the central portions of left and right sides of the WIG vehicle. The panel of the main wing is flat and tapers successively toward the lateral edge, whereof the cross-section is airfoil-shaped and has the shape of a tadpole. The panel shaped left and right downward wings are connected with both ends of the left and right main wings without a joint and are formed heading downward to suppress vortex and guidance drag generated in both ends of the main wings. The rudder units are mounted on the rear surface of the left and right downward panels with a slight gap in order to compensate asymmetry between left and right lateral ends caused by movement under control of the fuselage driving unit of the WIG vehicle and to turn the fuselage left or right. Therefore, the wing structure of the WIG vehicle is capable of minimizing vortex and guidance drag generated in both ends of the left and right main wings by maximizing ground effect. Additionally, the wing structure has advantages for absorbing impact from the fuselage when taking off and landing and stabilizing horizontal disturbance of the fuselage because the left and right downward wings occupy much more volume than a winglet. | 08-25-2011 |
| 20110211965 | HOLLOW FAN BLADE - A blade includes a hollow metal airfoil having an opening to an internal cavity in a first major surface. A metal cover is adhesively bonded to a socket formed around the opening. The cover encloses the cavity and provides a continuous first major surface. | 09-01-2011 |
| 20110211966 | Wind power generation system - A wind turbine blade forming a root at an inner end, a tip at an outer end, a plurality of power sections intermediate the root and the tip, and a plurality of aerodynamic section dividers located intermediate each of the other sections. The aerodynamic section dividers are configured to aerodynamically isolate their adjoining sections to limit the lateral flow of air between them while in use on the wind turbine. The blade has a low aspect ratio and is operated at a high advance rate. The aerodynamic section dividers are close enough together to soften the stall characteristics of the blade, and thus the blade can be operated at high angles of attack. | 09-01-2011 |
| 20110217177 | Stepped Surface Propeller - A marine surface propeller, and blade therefore, which is surface piercing and partially submerged, and includes a blade geometry that improves distribution of pressure and control to wetted and ventilated regions. Preferably, the feature has a positive step (ramp, cup, interceptor, indent or other geometric addition or intervention) between one fifth and four fifths chord length so as to create a high pressure peak or zone in what is now a low pressure zone on either the blade face or back or both and to create speed controllable wetted and ventilated regions. | 09-08-2011 |
| 20110223028 | Arrangement and method to retrofit a wind turbine - A blade of the wind turbine is prepared to be connected with the hub of the wind turbine. An extension unit is designed and prepared to elongate the blade. The extension unit is connected with the tip of the blade by a pressure, which is applied between the tip of the blade and the extension unit. The applied pressure is a low-pressure in relation to the ambient barometric pressure. | 09-15-2011 |
| 20110223029 | EXTRACTION FAN AND ROTOR - An extraction fan rotor including a hub and a plurality of vanes extending radially therefrom, wherein said vanes have an aerofoil profile in cross-section. | 09-15-2011 |
| 20110229329 | Propeller augmentation - The invention relates a fluid or air propeller propulsion apparatus using the state of the art propeller that reduces the typical propeller slipstream disc contraction taking place very close to the propeller tips, containing an inlet slot on the leading edge of the propeller some distance measured from the propeller tips and connected internally to an exit tip slot at the propeller trailing edge. Fluid or air enters the leading edge slot during rotation of the propeller and is acted upon by centrifugal force varying directly with the propeller speed causing the fluid or air to be accelerated thru the internal passage and out the trailing edge exit slot parallel to the cambered face of the propeller at less than a right angle to the trailing edge, inducing flow at zero or low forward speed previously with little or no flow at the propeller tips and at greater speeds, increasing the propeller capacity, and adding an additional jetting action or bootstrapping which causes the propeller to turn more easily, all of which increases the propeller thrust and efficiency. | 09-22-2011 |
| 20110229330 | AXIAL FLOW FAN - An axial flow fan comprises a central hub ( | 09-22-2011 |
| 20110229331 | Wind Turbine Rotor Blade - Wind turbine rotor blade with a longitudinal axis, a blade tip, a blade root, a leading edge, a trailing edge and a cross-section arranged orthogonally to the longitudinal axis and changing from the blade root to the blade tip, is the cross-section being formed at the blade root and in the middle of the rotor blade by an aerodynamic profile, and an imaginary reference plane arranged with respect to the rotor blade which includes the longitudinal axis of the rotor blade, wherein, in a cross-section, an angle α | 09-22-2011 |
| 20110229332 | Wind Turbine Rotor Blade - Wind turbine rotor blade with a blade tip, a blade root, a leading edge, a trailing edge, a pressure side, a suction side and a cross-section, which changes from the blade tip to the blade root, the longitudinal portion being arranged between the blade root and the middle of the rotor blade, has the following:
| 09-22-2011 |
| 20110229333 | SHEAR WEB CONNECTION - A shear web ( | 09-22-2011 |
| 20110250073 | ROTOR AND ASSEMBLY FOR REDUCING LEAKAGE FLOW - In a rotary machine such as a steam turbine, pressurized fluid flows through a series of stationary and rotary components. Minimizing leakage flow of the fluid enhances the operation and efficiency of the machine. At least one rotor land has a groove formed thereon to generate a vortex as the fluid passes over. The vortex resists the axial flow of the fluid, which reduces the leakage flow. | 10-13-2011 |
| 20110250074 | MULTI-ALLOY ARTICLE, AND METHOD OF MANUFACTURING THEREOF - An article includes a first section extending from an outer periphery to a predetermined surface located inward from the outer periphery. The first section comprises a nanostructured ferritic alloy. The article includes a second section extending from an inner periphery to the predetermined surface located outward from the inner periphery. The second section comprises at least one other alloy different from the nanostructured ferritic alloy. | 10-13-2011 |
| 20110255985 | BLADES - A rotor blade | 10-20-2011 |
| 20110255986 | BLADES - A turbine blade ( | 10-20-2011 |
| 20110262280 | ROTOR BLADE AND METHOD FOR PRODUCING SAME - The invention relates to a rotor blade for wind energy installation, comprising at least one flange running in a longitudinal direction from a rotor blade root to a rotor blade tip, whereby a width of the flange decreases along the longitudinal direction. The invention also relates to a method for producing a rotor blade in that at least one flange with a width decreasing in the longitudinal direction is applied to a rotor blade inner wall, and to a laying assistance device for positioning strips of the flange. | 10-27-2011 |
| 20110262281 | PROFILE OF A ROTOR BLADE AND ROTOR BLADE OF A WIND POWER PLANT - The profile ( | 10-27-2011 |
| 20110262282 | METHOD FOR INJECTION MOLDING A PUMP IMPELLER AND PUMP IMPELLER - A method for injection molding a pump impeller ( | 10-27-2011 |
| 20110280732 | Diffused Refractory Metal Alloy Coated Products - A material is diffused into an electrically conductive substrate to enhance and add desirable properties through a metalliding process employing an electrolytic bath within an atmosphere substantially free of oxygen. The substrate to be coated is submerged within the bath as a cathode along with multiple anodes, each anode having a distinctive composition from the other. A variable power source provides preselected current densities to each of the anodes so as to result in a diffusing of material from each anode for coating the substrate in proportion to the current densities applied to each anode. Products of the invention include an electrically conductive substrate and an alloy coating diffused into a surface of the substrate, wherein the alloy coating comprises a compound of beryllium, boron or silicon, plus at least one refractory metal. | 11-17-2011 |
| 20110286849 | BLADE FOR A GAS TURBINE - A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width. | 11-24-2011 |
| 20110286850 | AIRFOIL FOR A COMPRESSOR BLADE - The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD) stagger angle (γ) and camber angle (Δβ). The stagger angle (γ) and camber angle (Δβ) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight. | 11-24-2011 |
| 20110286851 | Guide blade arrangement for an axial turbo-machine - A guide blade arrangement for an axial turbo-machine is provided. The guide blade arrangement includes at least one annular guide blade carrier and an inner ring arranged concentrically with respect to the guide blade carrier, between which guide blade carrier and inner ring a number of guide blades are arranged in a radial configuration. To obtain a low-wear and particularly durable fastening of the guide blade, which is supported by the guide blade carrier, to the inner ring, it is proposed that the guide blades are fastened resiliently to the inner ring. Here, the fastening is provided by means of a spring element. By means of the spring element, it is possible to ensure a uniform contact pressure of the guide blade head against the inner ring or if appropriate against a further spring element, such that occurring stresses and wear can be reduced. | 11-24-2011 |
| 20110286852 | WIND TURBINE BLADE - Disclosed is a blade including a blade body including a leading edge and a trailing edge, and at least one trailing edge cavity defined by a blade area disposed in at least partial alignment with the trailing edge, the at least one cavity extending a desired depth into said blade body in a direction of the leading edge. | 11-24-2011 |
| 20110293432 | SECTIONAL WIND TURBINE BLADE - Wind turbine blade comprising two or more blade sections each of which defines a non-joint zone and, at one or each of its ends, a joint zone. The blade sections are connected in pairs such that the joint zones of each pair are connected at a joint, whereby the joint is positioned between two non-joint zones. At least one of the joints have an increased thickness and a wider chord relative to the thickness and the chord of the two non-joint zone between which the joint is positioned so as to increase the second moment of inertia in the area of the joint. | 12-01-2011 |
| 20110299991 | SCREW PROPELLER (VARIANTS) AND THE INVOLUTE OF THE BLADES THEREOF - The invention relates to a screw propeller and its variants for converting mechanical energy in a fluid medium, and can be used in the form of water and air screws for engines and propulsers, making it possible to simplify the production method of propeller blades, to reduce the dimensions and material consumption of propeller blades, and to simultaneously increase a thrust produced thereby without decreasing the strength and efficiency thereof. The inventive propeller comprises at least two scimitar-shaped blades whose basic sections are fixed to the hub of a driven shaft. The basic section of each blade is straight and scimitar in shape, wherein the front edge of the blade is bent backwards in relation to the direction and plane of rotation and gradually transforms into the inverse, scimitar-shaped end section. Moreover, the front edge of the blade is forwardly bent in relation to the direction and plane of rotation. The blades are arranged along the propeller axis and fastened by means of the end sections in such a way that an axially symmetric figure is formed. The involute of all the blades of the propeller is shaped in the form of a single integral flat figure provided with one or more holes ( | 12-08-2011 |
| 20110299992 | ROTOR ASSEMBLY FOR GAS TURBINE ENGINE - A rotor assembly for a gas turbine engine includes a rotor airfoil and a first rotor disk. The rotor airfoil extends along a radial axis. The first rotor disk includes an outer rim, a bore and a web extending between the outer rim and the bore. The first rotor disk is axially offset from the radial axis of the rotor airfoil. | 12-08-2011 |
| 20110305577 | AGGREGATE VANE ASSEMBLY - An aggregate vane assembly is disclosed herein. The aggregate vane assembly includes a core vane assembly encircling a central longitudinal axis. The core vane assembly has a plurality of core vanes each extending radially between an inner hub and an outer band. The core vane assembly extends along the central longitudinal axis between a first forward end and a first aft end. The aggregate vane assembly also includes a bypass vane assembly disposed on a radially opposite side of the outer band relative to the plurality of core vanes. The bypass vane assembly includes at least one bypass vane extending radially outward from a platform. The bypass vane assembly extends along the central longitudinal axis between a second forward end and a second aft end. The aggregate vane assembly also includes at least one boss fixed with the outer band and operable to engage the bypass vane assembly proximate to the second forward end. | 12-15-2011 |
| 20110305578 | Component for a gas turbine and a method for the production of the component - A component for a gas turbine, especially a blisk or a bling, whereby the component includes a rotor base ( | 12-15-2011 |
| 20110305579 | AIRFOIL HAVING REDUCED WAKE - An airfoil of varying span-wise thickness comprising a suction side and a pressure side coupled together at a leading edge and a trailing edge, with the trailing edge comprising a plurality of spaced-apart wave-shaped projections. Exemplary embodiments provide airfoil geometry and/or trailing edge features to influence downstream wake flow. Methods of fabricating an airfoil for improved wake flow are also provided. | 12-15-2011 |
| 20110311367 | STATOR AND TORQUE CONVERTER - It is an object of the present invention to inhibit generation of a vortex in the position where operating oil separates from a stator and to increase a capacity coefficient by allowing the operating oil to efficiently flow from a turbine to an impeller. A torque converter stator of the present invention is configured to regulate the flow of operating oil returning from a turbine to an impeller within a torque converter. The torque converter stator includes an annular stator shell, a plurality of stator blades and an annular stator core. The stator blades are radially extended from the stator shell. The stator blades respectively include a corrugated operating-oil outlet-side edge. The stator core is disposed on the outer peripheries of the stator blades. | 12-22-2011 |
| 20120003098 | FLARED TIP FAN BLADE AND METHOD OF MANUFACTURING SAME - A fan blade assembly is provided. The fan blade assembly may include; a fan blade having an airfoil shaped section, formed by being run lengthwise though a die and a flap portion integral with the airfoil section also run lengthwise through the die, the fan blade having a hub end and a tip end, a tapering trailing edge on a trailing edge of the fan blade defined by removing a portion of the trailing edge of the fan blade after it has been run through the die, the tapering trailing edge defining the fan blade to be narrower moving from the hub end toward the tip end, and a flared portion interrupting the tapering trailing edge near the tip end, the flared portion defining the fan blade to become wider from the beginning of the flared portion to the tip end. A method for making a fan blade may also be provided. | 01-05-2012 |
| 20120003099 | MOLTEN METAL IMPELLER - According to one embodiment, a molten metal impeller is provided. It includes a generally cylindrical graphite body having a plurality of passages extending from a top surface to a side wall. A hub is formed in the center of the graphite body. A ceramic cap member is secured to the top surface of the graphite body. The cap member is comprised of a ring forming a central passage shaped cooperatively to overlap the hub and a plurality of vanes extending radially from the ring to an outer rim. The rim has a height between adjacent vanes which increases in the direction of intended impeller rotation. The rim further has a height which decreases from its radially outer most edge to an inner most edge. | 01-05-2012 |
| 20120020797 | VORTEX REDUCING DEVICE FOR A GAS TURBINE ENGINE - A gas turbine engine has a vortex reducing device therein that includes a retainer and paddles. The retainer is arcuate in shape and has a plurality of circumferentially spaced slots that extend through it. The paddles are circumferentially spaced about the retainer and extend outward thereform. Each paddle is disposed between adjacent slots. | 01-26-2012 |
| 20120020798 | FAIRING FOR WIND TURBINE BLADE - The invention relates to a fairing adapted to be mounted on a wind turbine blade ( | 01-26-2012 |
| 20120020799 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE, IN PARTICULAR FOR A ROTARY WHEEL OF THE THIRD STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P | 01-26-2012 |
| 20120020800 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE VANE, IN PARTICULAR FOR A NOZZLE OF THE THIRD STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P | 01-26-2012 |
| 20120020801 | STRUCTURAL ELEMENT FOR AN AIRCRAFT OR SPACECRAFT AND METHOD FOR PRODUCING SUCH A STRUCTURAL ELEMENT - The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimise the natural vibration behaviour of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behaviour of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behaviour of the structural element is optimised. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element. | 01-26-2012 |
| 20120027607 | NICKEL ALLOY AND ARTICLES - Articles suitable for use in high temperature applications, such as turbomachinery components, and methods for making such articles, are provided. One embodiment is an article. The article comprises a material comprising a plurality of L12-structured gamma-prime phase precipitates distributed within a matrix phase at a concentration of at least 20% by volume, wherein the gamma-prime phase precipitates are less than 1 micrometer in size, and a plurality of A3-structured eta phase precipitates distributed within the matrix phase at a concentration in the range from about 1% to about 25% by volume. The solvus temperature of the eta phase is higher than the solvus temperature of the gamma-prime phase. Moreover, the material has a median grain size less than 10 micrometers. The method comprises providing a workpiece, the workpiece comprising at least about 40% nickel, from about 1.5% to about 8% titanium, and from about 1.5% to about 4.5% aluminum. A weight ratio of titanium to aluminum is in the range from about 1 to about 4, and the workpiece further comprises a plurality of A3-structured ordered eta phase precipitates distributed within the matrix phase at a concentration in the range from about 1% to about 25% by volume. The method further comprises mechanically working the workpiece at a temperature below a solvus temperature of the eta phase; and heat treating the workpiece at a temperature sufficiently high to dissolve any gamma prime phase present in the workpiece but below the solvus temperature of the eta phase. | 02-02-2012 |
| 20120027608 | Rotor Blade Section and Method for Assembling a Rotor Blade for a Wind Turbine - A rotor blade section and a method for assembling a rotor blade for a wind turbine are disclosed. The rotor blade section includes a plurality of ribs each extending in a generally chord-wise direction. Each of the plurality of ribs includes an outer surface. The outer surface has a generally aerodynamic contour. The rotor blade section further includes at least one cross-member extending between adjacent ribs of the plurality of ribs, and an outer body mounted to the plurality of ribs. The outer body has an aerodynamic contour generally corresponding to the aerodynamic contour of the plurality of ribs. | 02-02-2012 |
| 20120034089 | COMPOSITE MATERIAL AND METHOD - A composite material and method for manufacturing the material, the material including: a plurality of plies layered one on top of the other; and one or more through-thickness fibres which join one or more of the plurality of plies to one another; wherein the one or more through-thickness fibres form a boundary which delineates one or more discrete regions of the material. | 02-09-2012 |
| 20120070299 | WIND TURBINE BLADE - A blade for a rotor of a wind turbine has a root region with a substantially circular or elliptical profile closest to the hub and an airfoil region with a lift generating profile furthest away from the hub. A transition region has a base part with an inner dimension that varies linearly in the radial direction of the blade in such a way that an induction factor of the first base part without flow altering devices at a rotor design point deviates from a target induction factor. The first longitudinal segment is provided with a number of first flow altering devices arranged so as to adjust the aerodynamic properties of the first longitudinal segment to substantially meet the target induction factor at the design point. | 03-22-2012 |
| 20120076660 | CONDUCTION PEDESTALS FOR A GAS TURBINE ENGINE AIRFOIL - An airfoil for a gas turbine engine includes an airfoil which defines a leading edge cavity and a forward cavity between a pressure side wall and a suction side wall, the leading edge cavity at least partially defined by a leading edge wall which extends between the pressure side wall and the suction side wall. A rib between the pressure side wall and the suction side wall separates the forward cavity and the leading edge cavity. A pedestal extends between the leading edge wall and the rib. | 03-29-2012 |
| 20120093655 | IMPELLER - An impeller includes a hub and a plurality of blades. The blades are disposed around an outer periphery of the hub. Each of the blades includes a connecting end, a sweep-back part and a sweep-forward part. The connecting end is coupled with the hub. The sweep-back part is disposed at an edge of the blade and extended from the connecting end. An extending direction of the sweep-back part is opposed to a rotating direction of the impeller. The sweep-forward part is extended from the sweep-back part. An extending direction of the sweep-forward part is the same as the rotating direction of the impeller. | 04-19-2012 |
| 20120100000 | AEROFOIL STRUCTURE - An aerofoil structure for a rotating blade-row in a casing, the aerofoil structure comprising a suction side, a pressure side and a tip therebetween, wherein at least a portion of the tip comprises a shaped feature provided on a surface of the tip, the shaped feature comprising a convergent portion orientated to reduce a gap between the tip and the casing in a direction from the pressure side to the suction side of the aerofoil structure. | 04-26-2012 |
| 20120107127 | FAN BLADE ASSEMLBY - A fan blade assembly comprises: a motor-mounting seat and a plurality of spaced-apart fan blades extending from a periphery of the motor-mounting seat. The fan blades each are provided with a vibration-blocking unit in the form of a concave structure, which makes the fan blades become a non-flat structure. The vibration-blocking unit reduces the vibration and noise of the fan blade assembly, it further increases the structural strength while relatively reducing the thickness of the fan blades, so that the material cost of the fan blades is reduced. | 05-03-2012 |
| 20120114491 | DIE CASTING TO PRODUCE A HYBRID COMPONENT - An example die casting system includes a die that defines a cavity having a first section and a second section. The first section is configured to receive a first portion of a component. The second section is configured to receive a molten material. The die holds the molten material as the molten material solidifies to form a second portion of the component. | 05-10-2012 |
| 20120114492 | METHOD OF MODIFYING A STEAM TURBINE - A method of modifying a steam turbine to change from a first maximum thermal power of the steam generator to a second maximum thermal power of the steam generator. The method can include replacing, in the high-pressure module, at least one set of fixed blades sized for the first maximum thermal power by at least one set of fixed blades sized for the second maximum thermal power. The at least one set of moving blades are sized to operate at the first and second maximum thermal powers. The rotor and the at least one set of moving blades of the high-pressure module remain unchanged on changing from the first maximum thermal power to the second maximum thermal power. | 05-10-2012 |
| 20120114493 | WIND ENERGY USE - The invention provides wind energy use. One application provides wind energy use for water harvesting from natural humid air. The method is based on changing thermodynamic state parameters of ambient wind air portions passed through a device comprising convergent-divergent and wing-like components. Those components transform the ambient wind portions into fast and cooled outflowing air portions. A decrease in static pressure and temperature triggers condensation of water-vapor into water-aerosols. Another application of the method provides an effective mechanism for harvesting electrical energy from naturally warm air using renewable wind energy, including the wind inertia, internal heat, and potential energy stored in the air mass in the Earth's gravitational field. The electrical energy harvesting mechanism is also applicable to use of natural renewable energy of streaming water. | 05-10-2012 |
| 20120128499 | STRUCTURAL ADHESIVE COMPOSITIONS - Disclosed herein are 2K structural adhesive compositions comprising (a) a first component comprising (i) an epoxy-adduct formed as a reaction product of reactants comprising a first epoxy compound, a polyol, and an anhydride and/or a diacid; and (ii) a second epoxy compound; and (b) a second component that reacts with the first component. In one embodiment, the second component is an amine compound. These adhesives may be used to bond together substrate materials such as two half shells of wind turbine blades. | 05-24-2012 |
| 20120128500 | TURBINES - The invention generally relates to turbines that efficiently process air or fluid flow while producing substantially no vibrational effects. In one embodiment, the invention provides a turbine including a rotatable shaft and three helical blades connected to the rotatable shaft, where each of the blades has a helical twist of about 360°. | 05-24-2012 |
| 20120134836 | BLADE EXTENSION FOR ROTOR BLADE IN WIND TURBINE - A blade extension for a rotor blade and a rotor blade assembly for a wind turbine are disclosed. The rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge each extending in a generally span-wise direction between a tip and a root. At least one of the leading edge or the trailing edge has a modified aerodynamic contour. The rotor blade assembly further includes a blade extension including a first panel and an opposed second panel. Each of the first panel and the second panel includes an interior surface and an exterior surface each extending between a proximal end and a distal end. The distal end of each of the first panel and the second panel is spaced apart from the rotor blade in a generally chord-wise direction in a standard operation position. | 05-31-2012 |
| 20120148413 | METHOD FOR REPLACING A BLADE OF A ROTOR HAVING INTEGRATED BLADES AND SUCH A ROTOR - A method for replacing a blade ( | 06-14-2012 |
| 20120156047 | AIRCRAFT ENGINE BLADING - A blading for a turbine, in particular a gas turbine, is disclosed. The blades of the blading in a section near the tip have a distribution ratio (t/l) of at least 0.70, in particular at least 0.9, and/or at most 0.97, in particular at most 0.95. A downstream flow angle (α) is at most 167°, in particular at most 165°, and at least 155°, in particular at least 160°. In addition, or alternatively, an acceleration ratio (w | 06-21-2012 |
| 20120163979 | PROCESSES FOR PRODUCING COMPONENTS CONTAINING CERAMIC-BASED AND METALLIC MATERIALS - Processes for producing a component containing a ceramic-based material and having detailed features formed from materials other than ceramic materials. Such a process entails producing the component to include a first subcomponent and at least a second subcomponent having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent. The first subcomponent is formed of a ceramic-based material, and the second subcomponent and its off-axis geometric feature are separately formed of a metallic material and attached to the first subcomponent to yield a robust mechanical attachment. The component may be, for example, a gas turbine airfoil component. | 06-28-2012 |
| 20120163980 | IMPELLER FOR A PUMP AND CORE ARRANGEMENT AND METHOD FOR CASTING AN IMPELLER FOR A PUMP - An impeller ( | 06-28-2012 |
| 20120171041 | THIN-WALLED STRUCTURAL COMPONENT, AND METHOD FOR THE PRODUCTION THEREOF - A method for producing a thin-walled structural component from a casting material. The casting material is supplied as a powder, and the powder is deposited on a support ( | 07-05-2012 |
| 20120171042 | PROPELLER FAN, MOLDING DIE, AND FLUID FEEDER - A propeller fan with two blades includes a blade and a blade, and a connection portion connecting the blades together. Each blade has a peripheral edge portion extending in an arc having a diameter D with a center axis as a center thereof, a front edge portion arranged on a forward side in a rotational direction, a rear edge portion arranged on an opposite side in the rotational direction, and a leading blade edge portion connecting the front edge portion and the peripheral edge portion. A plane which includes each intersection between the rear edge portion and the peripheral edge portion and is perpendicular to the center axis is defined as γ. When the propeller fan is viewed in a direction parallel to a plane including the leading blade edge portions and the center axis, a distance H between plane γ and a connected portion between the front edge portion of the blade and the rear edge portion of the blade, on a line of the center axis, satisfies 0.028≦H/D≦0.056. With such a structure, a propeller fan, a molding die, and a fluid feeder which make a significant contribution in terms of energy-saving properties and resource-saving design can be provided. | 07-05-2012 |
| 20120189454 | IMPELLER OF CENTRIFUGAL COMPRESSOR - Providing an impeller of a centrifugal compressor, the impeller including, but not limited to: a plurality of full blades provided from the fluid inlet part to the fluid outlet part of the impeller, each full blade being arranged next to the adjacent full blade; a plurality of splitter blades provided on the hub surface, each splitter blade being provide between a full blade and the adjacent full blade from a location on a part way of the flow passage between the full blades to the fluid outlet part of the impeller, wherein the geometry of the flow entering part of the splitter blade is compatible with the complicated flow inside the compressor so that the evenly distributed flow rate distribution, the increased pressure ratio and the enhanced efficiency are achieved. An impeller of a centrifugal compressor, wherein, the leading edge blade angle θ in the tip end part of the flow entering front-end-part of the splitter blade | 07-26-2012 |
| 20120189455 | WIND TURBINE ROTOR BLADE ELEMENT AND WIND TURBINE ROTOR BLADE - A wind turbine rotor blade element includes a first portion and a second portion connected to each other is described. The first portion includes a rear surface for facing a surface of a wind turbine rotor blade and the second portion includes a top surface which includes an angle between 90° and 180° with the rear surface of the first portion. | 07-26-2012 |
| 20120189456 | GUIDE GEOMETRY FOR HALF-AXIAL FAN WHEELS - A fan wheel ( | 07-26-2012 |
| 20120195763 | ENERGY CONVERSION ASSEMBLY - An energy conversion assembly, which comprises at least one central blade with an S-shaped transverse cross-section, the blade being able to rotate about a central axis which is parallel to its generatrices due to the action of a fluid current, with consequent transmission of mechanical energy to a shaft which can be associated with the blade. The assembly comprises at least one pair of substantially wedge-shaped bodies which are jointly connected to the blade and face it on opposite sides; each one of the three lateral faces of each substantially wedge-shaped body is affected by the action of the fluid current for respective useful sectors of rotation and provides, substantially in each one of the sectors, an active contribution to the motor moment transmitted by the fluid current to the blade, for optimizing the value of the transmitted mechanical energy. | 08-02-2012 |
| 20120195764 | WIND TURBINE BLADE WITH PLURALITY OF LONGITUDINALLY EXTENDING FLOW GUIDING DEVICE PARTS - A wind turbine blade with a plurality of flow guiding device parts attached to a profiled contour on a pressure side of the blade is described. The longitudinally extending flow guiding device parts are grouped together to form a first flow guiding device group in the transition region of the blade. | 08-02-2012 |
| 20120201686 | METHOD OF PRODUCING A GUIDE VANE - The invention relates to a method of producing a guide vane, the method comprising a step of fabricating at least a portion of a metal body of the guide vane by additive fabrication, with at least one outside surface thereof presenting a plurality of cavities; and a step of filling said cavities with a material of lower density than the metal body in order to form at least one substantially smooth airfoil surface. | 08-09-2012 |
| 20120207608 | FINAL-STAGE ROTOR BLADE OF A STEAM TURBINE - A turbine blade is provided that includes at least certain regions made of fiber reinforced composite material. Also, the turbine blade has at least one anti-erosion component for protecting against erosion. The turbine blade could be, for example, a last stage blade of a steam turbine. Furthermore, methods for producing a turbine blade of this type using an impregnation mold are provided. | 08-16-2012 |
| 20120207609 | WING STRUCTURE AND FAIRING DEVICE - A wing structure includes: a main wing that extends in a second direction intersecting a first direction as a fluid flow direction; and an auxiliary wing that is disposed so as to be separated from the main wing and faces the main wing at the front part side of the main wing, wherein a wing chord length of the auxiliary wing is shorter than a wing chord length of the main wing. A fluid contacts the auxiliary wing which is formed at the front part side of the main wing, the fluid is guided between the auxiliary wing and the main wing, and the fluid is compressed when passing between the auxiliary wing and the main wing, thereby appropriately forming a fluid compression process region on the surface of the main wing and increasing an acting force. | 08-16-2012 |
| 20120207610 | WIND TURBINE BLADE - A wind turbine blade is provided which includes a root section, a transition section, a conventional section and a tip section. The root section may include a chord length that is greater than a chord length calculated using conventional equations by a factor of approximately 1.3. The root section may also include a blade setting angle that is greater than a blade setting angle calculated using conventional equations by a factor of approximately 1.3. The conventional section may include a chord length and/or a blade setting angle that is approximately equal to a chord length and/or a blade setting angle calculated using conventional equations. In the transition section, the chord length and/or blade setting angle may transition from the chord length and/or blade setting angle in the root section to the chord length and/or blade setting angle in the conventional section. The tip section may include a winglet. | 08-16-2012 |
| 20120207611 | CASTING LONG PRODUCTS - A method of production of a component having at least one dimension that is more than 200 mm, said method comprising the steps of: a) providing a titanium aluminide melt; b) providing a cold sand casting mould; c) mounting the mould and the melt in a vacuum or inert atmosphere chamber; d) rotating the mould at a distance from a rotation axis to generate an artificial gravity in all parts of the mould of at least 30 g; e) pouring the melt along said axis of rotation into a gateway that leads the melt to a radius greater than a maximum radius of any part of the mould, the gateway being arranged to open into the mould in a direction contrary to that of said artificial gravity; f) wherein said pouring is at a speed that fills the mould in less than 5 seconds. The method is useful for the casting of long turbine airfoils used in electricity generation industry or large automotive turbocharger wheels. | 08-16-2012 |
| 20120213638 | Method of moulding a wind-turbine blade - A method of moulding a wind-turbine blade in a mould is described. The method includes arranging a number of markers on an interior of the mould; arranging a composite layup in the mould; and assembling and curing the composite layup in the mould such that a negative impression of a marker is formed on a surface of the composite layup, which negative impression facilitates correct positioning of the blade relative to a component in a subsequent assembly step. A mould for moulding a wind-turbine blade; a wind-turbine blade moulded using such a mould; and a positioning device for positioning a drilling and/or milling tool relative to a root portion of a wind-turbine blade moulded using the inventive method are disclosed. A method of manufacturing a wind-turbine blade is also disclosed. | 08-23-2012 |
| 20120213639 | ROTARY STRUCTURES - A method of contactlessly machining a workpiece ( | 08-23-2012 |
| 20120219423 | Wind Turbine Rotor Blade with Varying Blade Depth - A wind turbine rotor blade has a blade root, a blade tip and a blade depth varying over the length of the rotor blade. The rotor blade has a maximum blade depth at a longitudinal position between the blade root and the blade tip. The blade depth in an outer longitudinal section, which extends over a length of 20% or more of the blade length, lies in a range from 20% to 30% of the maximum blade depth. | 08-30-2012 |
| 20120230830 | ARRANGEMENT TO IMPROVE THE SURFACE OF A WIND TURBINE BLADE - An arrangement to improve a surface of a wind turbine blade is proposed. A plastic tape is arranged at a specific location of the blade to reinforce the blade surface there. The plastic tape shows a sandwich structure with at least two layers. The plastic tape has a first layer, which has a carbon fiber. The carbon fiber is used for reinforcement purposes of the plastic tape. The plastic tape has a second layer on a first side of the plastic tape, which is connected with the first layer. The second layer has a pure thermoplastic fluoropolymer. | 09-13-2012 |
| 20120230831 | COOLING FAN FOR DRIVING DEVICE AND COOLING FAN STRUCTURE - A cooling fan for cooling a mechanical section of a driving device attached to a rotary shaft including a plurality of blades configured to generate an airflow toward an outside of the rotary shaft in directions along radius directions of the rotary shaft with rotation of the rotary shaft, and a plurality of ribs that have widths in directions crossing the blades, extend toward outsides along the radius directions with respect to a center axis of the rotary shaft, reinforce the corresponding plurality of blades, and are directed on a side of the mechanical section at tips of the plurality of ribs, wherein at least parts of the blades exist inside the ribs along the radius directions of the ribs. | 09-13-2012 |
| 20120237353 | COMPRESSIBLE ROTOR FOR A FLUID PUMP - The invention relates to a rotor ( | 09-20-2012 |
| 20120237354 | Aerofoil - An aerofoil has a main portion of aerofoil cross section, an inner spanwise root end where the aerofoil is in use secured to a supporting structure, and at an outermost spanwise end outboard of the main portion, beyond a tip station, a tip region which includes a tip edge. The planform configuration of the tip edge lies on a first Bezier curve constructed from at least four control points, P | 09-20-2012 |
| 20120251330 | TURBINE AIRFOIL COMPONENT AND METHOD FOR MAKING - A component such as a turbine bucket or blade, and method for making the component, are presented. One embodiment is an article that comprises an airfoil casting portion comprising a plurality of integral regions, wherein the plurality of integral regions comprises a single-crystalline region and a columnar-grained region. Another embodiment is a method for fabricating an article. The method comprises providing a quantity of molten metal; providing a mold defining an airfoil portion having an axial direction and a transverse direction, wherein the airfoil portion of the mold comprises a single-crystal growth region and a columnar growth region disposed along the transverse direction from the single crystal growth region; introducing the molten metal into the mold; and solidifying the metal such that a solidification front progresses in the axial direction to produce an airfoil casting portion comprising a single-crystalline region and a columnar-grained region. | 10-04-2012 |
| 20120257977 | VORTEX GENERATOR DEVICE WITH TAPERED SECTIONS - A vortex generator device ( | 10-11-2012 |
| 20120257978 | MOUNTING OF VORTEX GENERATOR DEVICES VIA MOUNTING PLATE - A method of retrofitting flow-altering devices to an outer surface of a wind turbine blade is disclosed. The flow-guiding devices are of the type having a base comprising an inner side for attaching onto the surface of the wind turbine blade, and an outer side with protruding flow-altering device parts. The method comprises the steps of: a) inserting the protruding flow-altering device parts into a mounting plate so that the inner side of the flow-guiding devices are exposed from a first side of the mounting plate, b) adhering the inner side of the flow-altering devices to the surface of the wind turbine blade by applying the first side of the mounting plate onto an area of application on the surface of the wind turbine blade, and c) removing the mounting plate from area of application on the surface of the wind turbine blade. | 10-11-2012 |
| 20120257979 | FLOW GUIDING DEVICE WITH BASE HAVING RECESS FOR ADHESIVE STRIP OR TAPE - A vortex generator device ( | 10-11-2012 |
| 20120257980 | IMPELLER OF FUEL PUMP FOR VEHICLE - Provided is an impeller of a fuel pump for a vehicle. More particularly, an impeller of a fuel pump for a vehicle, which can improve delivery pressure and a delivery speed of fuel by modifying a shape of an impeller blade that is provided between an upper casing and a lower casing of a fuel pump and is joined to a rotational shaft of a driving motor to deliver fuel by using rotational force at the time of suctioning fuel from a fuel tank and supplying fuel to an engine of an internal combustion engine. | 10-11-2012 |
| 20120263600 | METHOD FOR MANUFACTURING A WORK PIECE BY VACUUM ASSISTED RESIN TRANSFER MOULDING - A method for manufacturing a work piece by Vacuum Assisted Resin Transfer Moulding is includes the steps of placing fibre rovings in a mould of a closed mould system which comprises a mould cavity, placing at least one resin distribution device between the fibre rovings, and applying vacuum to the closed mould system and injecting resin into the mould cavity. | 10-18-2012 |
| 20120263601 | Wind Turbine With Deployable Air Deflectors - An apparatus and system for compensating for various load situations in a turbine includes the use of one or more deployable devices configured to extend an air deflector outwardly from a surface of a rotor blade. The air deflector may subsequently be retracted into the rotor blade once the load falls below a certain threshold. Mechanisms for extending and retracting the air deflector may include pneumatic, hydraulic and/or electromechanical devices. Air deflectors are generally configured to modify the air flow around the rotor blade to increase or decrease power generation, or reduce loads so that the risk of potential damage to components of the wind turbine is minimized. Deflectors may be positioned at various chordwise stations including leading-edge, mid-chord, and trailing-edge locations on the upper and lower surfaces at spanwise positions. Accordingly, a plurality of devices can be actuated to aerodynamically control rotor performance and loads based on wind conditions. | 10-18-2012 |
| 20120269638 | COMPRESSOR HAVING BLADE TIP FEATURES - A compressor having a compressor blade with a blade tip portion configured to reduce stresses in the blade tip of the compressor blade is provided. The compressor blade includes a first and second faces extending to the blade tip portion. The blade tip portion includes a blade tip, a first recess extending between the first face and the blade tip, and a second recess extending between the second face and the blade tip. | 10-25-2012 |
| 20120269639 | PROPELLER FOR OUTBOARD MOTOR - An outboard motor is generally mounted to a hull of a boat, for example, and includes a propeller fixed to a rear portion of a propeller shaft pivotally supported in an anteroposterior direction of the hull on a lower portion of the outboard motor. The propeller includes a cylindrically formed propeller hub, and blades provided radially on an outer side of the propeller hub, and having surfaces of the blades, including blade body and root portion, to which a shot-peening treatment is applied. The propeller may be formed of a metal material having a surface on which an oxide coating is formed by heating the metal material. | 10-25-2012 |
| 20120269640 | SPOILER FOR A WIND TURBINE BLADE - A spoiler for a rotor blade includes a base member, which base member has a mounting face for mounting onto a surface of the rotor blade, and an aerodynamic member for detachably connecting onto the base member. Further, a wind turbine includes a number of rotor blades attached to a hub, wherein at least one rotor blade has such a spoiler mounted on a surface strip of the rotor blade. Also, a method of constructing a wind turbine is provided. A rotor blade is manufactured. A base member of the spoiler is mounted onto the rotor blade. The rotor blade is connected to a hub of the wind turbine. An aerodynamic member of the spoiler is attached onto the base member, wherein at least the mounting of the base member onto the rotor blade is performed prior to the connecting of the rotor blade to the hub. | 10-25-2012 |
| 20120269641 | Wind Turbine Rotor Blades Sharing Blade Roots for Advantageous Blades and Hubs - A wind turbine blade grouping includes at least two wind turbine blades. Each of the blades includes a blade root. The blade roots merge to form a single, unitary blade base structure that can be attached to a wind turbine hub. | 10-25-2012 |
| 20120269642 | METHOD FOR FUSION WELDING A MONOCRYSTALLINE WORKPIECE TO A POLYCRYSTALLINE WORKPIECE AND ROTOR - A method for fusion welding a metal workpiece, which has a monocrystalline structure, to a metal workpiece, which has a polycrystalline structure, using a fiber laser and producing an I seam, is disclosed. A rotor produced according to the method is also disclosed. | 10-25-2012 |
| 20120275923 | ROTOR FOR A TURBO-MACHINE - A radial compressor includes a rotor arrangement having a rotating shaft, a rotor wheel that is arranged on the shaft and corotates with the shaft, and a shaft bearing arranged on the shaft. To achieve improved rotor dynamics, the rotor wheel has a recess toward the shaft, in which the shaft bearing is at least partially arranged. | 11-01-2012 |
| 20120288374 | AIR PROPELLER ARRANGEMENT AND AIRCRAFT - An air propeller arrangement for propulsion of a fixed-wing aircraft includes a first air propeller that includes a first hub member and at least a first and a second propeller blade, the first and second blades being configured to contribute significantly to the propulsion and having a substantially equal length. Each of the blades has an inner, root end arranged at the first hub member and an outer, tip end positioned at a distance from the first hub member such that each blade extends in a radial direction from the first hub member. The first and second blades are interconnected at their outer ends. An aircraft provided with such an air propeller arrangement is also provided. | 11-15-2012 |
| 20120294723 | WIND TURBINE AND WIND TURBINE BLADE - A partial pitch wind turbine is described wherein the wind turbine blade has an inner blade section designed for stall-controlled operation and an outer blade section designed for pitch-controlled operation. The different blade profiles for the different sections allow for the efficient operation of the blade while providing for the control of the wind turbine to effectively reduce blade root moments. The outer blade sections can be pitched out of the wind to reduce root moments due to the outer blade sections, while the increasing power capture of the inner blade section maintains nominal power output. | 11-22-2012 |
| 20120294724 | AERODYNAMIC FAIRING FOR A WIND TURBINE AND A METHOD OF CONNECTING ADJACENT PARTS OF SUCH A FAIRING - A method for connecting adjacent parts ( | 11-22-2012 |
| 20120294725 | ROTOR DISK - Disclosed is a rotor disk ( | 11-22-2012 |
| 20120294726 | MULTIBLADE IMPELLER - The multiblade impeller of the present invention comprises a main plate, a side plate having a suction port at a center thereof, and a large number of blades provided between the main plate and the side plate and extend in the radial direction in an arc form. The main plate and the side plate each have a large number of ridge portions, each extending in the radial direction in an arc form so as to coincide with the shape of the blade extending in the radial direction in an arc form. End portions of the blades are inserted in grooves formed inside the ridge portions of the main plate and the side plate and are fixed to the ridge portions by being bent. | 11-22-2012 |
| 20120301309 | DISSIMILAR METAL WELDS AND ITS MANUFACTURING METHOD OF LARGE WELDED STRUCTURES SUCH AS THE TURBINE ROTOR - Dissimilar metal welds including a buttering portion with a small variation in strength distribution in a plate thickness direction are formed by welding two parent materials having at least one of different compositions and different refining conditions through a buttering for alleviating mismatch between one of the different compositions and the different refining conditions of the two members and through a welded metal for joining one of the parent materials and the buttering. The buttering is formed of welding metals laminated in a plate thickness direction, and a dilution ratio of the buttering with the parent materials is 50% or less. The manufacturing method includes performing butt welding on a dummy material formed by increasing a groove depth by providing a member on a bottom side of a welding groove and on parent materials by using the buttering; and processing a groove within a welding metal formed of the buttering. | 11-29-2012 |
| 20120301310 | Wind Turbine Rotor Blade and Airfoil Section - The present invention includes a set of airfoils, U rails and V rails taken together to describe a blade for use with a horizontal axis wind turbine. The blade's design includes a maximum thickness higher than conventional blades employed for the same use thereby providing better load bearing structural characteristics while at the same time maintaining the requisite aerodynamic qualities for similar blades. The blade has a maximum thickness of about 30% and a maximum lift coefficient of about 1.3. | 11-29-2012 |
| 20120301311 | STEAM TURBINE ROTOR BLADE ASSEMBLY - The present invention is a steam turbine rotor blade assembly including: an airfoil; a shroud provided at a tip of the airfoil; a blade root (dovetail) projecting toward a radially internal circumferential side of a turbine rotor and fitted to a root attachment provided on an outer circumferential portion of the turbine rotor; a platform provided between the airfoil and the blade root; a pin provided between the blade root and the root attachment; a bore formed between respective surfaces of the shrouds facing each other and included in the respective adjacent rotor blades; and a bar-like member provided in the bore. | 11-29-2012 |
| 20120308393 | NI-BASED ALLOY, AND GAS TURBINE ROTOR BLADE AND STATOR BLADE EACH USING SAME - This invention provides an Ni-based alloy, which is particularly used for standard casting and is provided with properties such as strength at high temperatures, corrosion resistivity, and oxidation resistivity in a more balanced manner, compared with existing materials. The Ni-based alloy comprises Cr, Co, Al, Ti, Ta, W, Mo, Nb, C, B, and unavoidable impurities, with the balance consisting of Ni. Composition of the alloy is represented by mass: 13.1% to 15.0% Cr, 1.0% to 15.0% Co, 2.3% to 3.3% Al, 4.55% to 6.0% Ti, 3.05% to 4.0% Ta, 4.35% to 4.9% W, 0.1% to 2.0% Mo, 0.05% to 0.5% Nb, less than 0.05% Zr, 0.05% to 0.2% C, and 0.01% to 0.03% B. | 12-06-2012 |
| 20120315145 | Rotor blade for a wind turbine - A rotor blade for a wind turbine is provided. The rotor blade includes an elongate blade base body with a number of connecting elements each having at least one axially extending connecting portion adapted to be connected with at least one corresponding connecting portion of a rotor hub of a wind turbine, wherein the respective connecting elements are connected to at least two circumferentially extending connecting members with the connecting members being adjacently disposed in circumferential direction so as to build a ring-like shape. Further, a wind turbine with such a rotor blade is provided. | 12-13-2012 |
| 20120315146 | MANUFACTURING METHOD OF WIND TURBINE BLADES OF VARIABLE LENGTH - A method of manufacturing wind turbine blades of variable length with connection means with the rotor hub comprising steps of providing and using enlarged manufacturing moulds ( | 12-13-2012 |
| 20120321478 | PRECIPITATE HARDENING STAINLESS STEEL AND LONG BLADE USING SAME FOR STEAM TURBINE - This invention provides a precipitate hardening stainless steel having excellent structure stability, strength, toughness, and corrosion resistance, which requires no sub-zero treating and thus is excellent in terms of productivity, and a long blade for a steam turbine using the same. The following are provided: a precipitate hardening stainless steel, which comprises C at 0.05 mass % or less, N at 0.05 mass % or less, Cr at 10.0 mass % to 14.0 mass %, Ni at 8.5 mass % to 11.5 mass %, Mo at 0.5 mass % to 3.0 mass %, Ti at 1.5 mass % to 2.0 mass %, Al at 0.25 mass % to 1.00 mass %, Si at 0.5 mass % or less, and Mn at 1.0 mass % or less, and the balance is composed of Fe and inevitable impurities; and a long blade for a steam turbine composed of the precipitate hardening stainless steel. | 12-20-2012 |
| 20130004320 | METHOD OF ROTATED AIRFOILS - A method for forming a nozzle segment for a turbine stage of a gas turbine engine to a specific measurement range for a throat area. The nozzle segment comprising an inner platform, and outer platform, and a plurality of airfoils between the inner platform and outer platform. A requested throat area measurement is obtained for the nozzle segment, and a starting stacking angle for a plurality of through holes and pockets corresponding to the airfoils for both the inner platform and outer platform is selected, which are then machined. The airfoils, inner platform, and outer platform are assembled to form a vane segment that is machined to obtain a finished throat area. The finished throat area is measured, and a determination is made if the measured finish throat area complies with the requested throat area. | 01-03-2013 |
| 20130004321 | TURBINE WHEEL - A turbine wheel includes a plurality of blades having a scallop cut-out profile. The scallop cut-out profile is formed by cutting-out a back side wall part of the blade between the suction surface side of a blade part and the pressure surface side of the adjacent blade. | 01-03-2013 |
| 20130011267 | HUB STRUCTURE - A hub structure includes an annular body and a flow guide unit. The annular body has a top end and a receiving space. The flow guide unit is disposed at the top end of the annular body. At least one raised section is formed on one face of the flow guide unit opposite to the receiving space. A motor set is disposed in the receiving space. When the motor set operates, the annular body and the flow guide unit are driven to rotate around the axis of a shaft rod. At this time, airflow is conducted through the raised section into the receiving space to dissipate the heat generated by the motor set. Accordingly, the temperature of the motor set can be effectively lowered to prolong the lifetime of the motor set. | 01-10-2013 |
| 20130011268 | Impeller Assembly and Method - Embodiments of the invention provide an impeller and a method of producing the impeller. The impeller includes a first molded piece coupled to a second molded piece. The first molded piece includes impeller vanes, a motor hub, a nose, and an eye. The second molded piece includes a cover and a hole through the cover. The cover is coupled to the impeller vanes around the motor hub so that the motor hub extends through the hole. | 01-10-2013 |
| 20130011269 | MOLD FOR A CENTRIFUGAL IMPELLER, MOLD INSERTS AND METHOD FOR BUILDING A CENTRIFUGAL IMPELLER - A mold for a centrifugal impeller for a turbomachine is provided. The mold comprises at least one annular insert, wherein the annular insert comprises a plurality of aerodynamic vane inserts configured to reproduce an annular assembly of aerodynamic vanes of a finished centrifugal impeller. | 01-10-2013 |
| 20130022470 | TORQUE CONVERTER BLADE TAB UNDERCUTS - A blade for a torque converter, including: a body with first and second blade side surfaces and a blade edge surface connecting the first and second blade side surfaces; and a tab extending from the blade edge surface and arranged for insertion through an opening in a core ring for the torque converter. The tab includes: a distal end furthest from the blade edge surface; first and second tab edge surfaces in communication with the distal end; and first and second indentations in the first and second tab edge surfaces, respectively, between the distal end and the blade edge surface. The core ring forms at least respective portions of respective inner circumferences for a turbine and pump for the torque converter. After insertion through the opening, the tab is arranged to be bent along a line connecting the indentations so that a portion of the tab engages the core ring. | 01-24-2013 |
| 20130034446 | TURBINE BLADE POCKET PIN STRESS RELIEF - A turbine blade comprises an airfoil having a pressure side and a suction side, and extending from a leading edge to a trailing edge. The airfoil has a tip remote from a mounting root, and a pocket extending inwardly of the tip. The pocket has spaced walls with one wall associated with the pressure side of the airfoil, and an opposed wall associated with the suction side. A pin extends across the pocket and connects the opposed walls. A slot is formed in the pin at a location intermediate ends of the pin which connect to the opposed walls. A method for identifying a location for the pin along a distance between a leading edge and a trailing edge of the pocket utilizes a modal analysis, and seeks to find a location where both a reaction force and a moment are lower than they might be at other locations. | 02-07-2013 |
| 20130039772 | SYSTEM AND METHOD FOR CONTROLLING FLOW IN TURBOMACHINERY - A system includes a turbine. The turbine includes a first turbine blade comprising a leading edge, a blade platform coupled to the first turbine blade, and a protrusion disposed on the blade platform adjacent the leading edge of the first turbine blade. The protrusion is configured to increase a first static pressure of a cooling flow near the leading edge above a second static pressure of a hot gas flow near the leading edge. | 02-14-2013 |
| 20130039773 | METHOD OF MEASURING TURBINE BLADE TIP EROSION - A method of designing a turbine blade includes the steps of forming at least two notches on a tip of a turbine blade, each of the at least two notches having a known dimension. The turbine blade has a pressure side and a suction side. The method further includes the step of operating a gas turbine engine including the turbine blade to expand a length of the turbine blade such that the tip of the turbine engages a casing. The method further includes the steps of viewing the tip of the turbine blade after the step of operating of the gas turbine engine, determining an appearance of the notches on the tip and determining a manufacturing length of the turbine blade based on the step of determining the appearance the notches. | 02-14-2013 |
| 20130052027 | HYDROFOIL WITH FEATURES TO GENERATE CAVITATION - A hydrofoil includes a hydrofoil body that extends between a base and a tip, a leading end and a trailing end, and a suction side and a pressure side that define a thickness there between. The hydrofoil body includes a discontinuous slope on at least one of the suction side or the pressure side. The discontinuous slope extends in a span-wise direction between the base and the tip such that the discontinuous slope decreases the thickness of the hydrofoil body from the leading end to the trailing end. | 02-28-2013 |
| 20130052028 | TURBINE ASSEMBLIES - A turbine assembly comprising a plurality of turbine blades, each blade having a setting angle distribution such that the thrust coefficient of the blade increases with rotational speed of the turbine assembly up to a first rotational speed and decreases significantly beyond the first rotational speed up to a runaway speed for the turbine assembly. | 02-28-2013 |
| 20130064672 | METHOD OF MANUFACTURING A TURBINE ROTOR - A method for joining a cast metal material blade ring and a metal material hub structure into a turbine rotor. One of the blade ring and the hub structure is mounted in a holder and the other is mounted in a rotation holder for being rotated. At least one of these mountings is heated, and then they are pressed together with a selected force while rotating to weld the ring interior wall and the disk side to form the assembled structure. | 03-14-2013 |
| 20130064673 | VORTEX GENERATORS FOR GENERATING VORTICES UPSTREAM OF A CASCADE OF COMPRESSOR BLADES - A blade assembly for a turbomachine compressor includes a plurality of individual devices acting on the flow. The individual devices are provided upstream of the blade assembly and are formed at least so as to generate vortices. Each of the individual devices is arranged on an upstream face of a shroud around which a recirculating flow passes, circulating in a cavity. The recirculating flow is reinjected into the principal flow such that the individual devices act simultaneously on the principal flow and on the recirculating flow. | 03-14-2013 |
| 20130071250 | PROCESS OF WELDING A TURBINE BLADE, A PROCESS OF WELDING A NON-UNIFORM ARTICLE, AND A WELDED TURBINE BLADE - A process of welding an article and a welded turbine blade are disclosed. The process includes fusion welding over a primary symmetry line determined from a center of gravity on a first side of the article or blade and fusion welding over the primary symmetry line determined from the center of gravity on a second side of the article or blade. The fusion treating includes multiple fusion treatments. | 03-21-2013 |
| 20130071251 | VIBRATION DAMPING BLADE FOR FLUID - The vibration damping blade for fluid of the present invention has an integrally formed wedge damper, in which a thickness h(x) at a distance x from an imaginary line outside of an outer edge is h(x)=εx | 03-21-2013 |
| 20130089428 | METHOD FOR PRODUCING A METAL REINFORCEMENT FOR A TURBOMACHINE BLADE - A method for producing a solid component which in succession includes deforming a metal bar by forging using two dies in order to obtain an intermediate component including two fins one on each side of a solid part capable of forming the base of the metal reinforcement, the two fins being at a divergent angle α; deforming the two fins of the intermediate component, altering the divergent angle α, so as to obtain the final shape of the turbomachine blade leading edge or trailing edge metal reinforcement. | 04-11-2013 |
| 20130094970 | WIND TURBINE BLADE, WIND TURBINE GENERATOR EQUIPPED WITH WIND TURBINE BLADE AND METHOD OF DESIGNING WIND TURBINE BLADE - It is intended to provide a wind turbine blade with superior aerodynamic characteristics and rigidity, a wind turbine generator equipped with the wind turbine blade, and a method of designing the wind turbine blade. The wind turbine blade | 04-18-2013 |
| 20130101423 | AIRFOIL DEVICES, LEADING EDGE COMPONENTS, AND METHODS OF MAKING - In a method of making a leading edge component for an airfoil device a first elongate sheet is provided and has a shape substantially conforming to a surface on one of a suction side or a pressure side of an airfoil. A second elongate sheet is provided and has a shape substantially conforming to a surface on the other of the suction side or the pressure side of the airfoil. The elongate sheet can be welded together at least along respective elongate edges thereof, in such a way as to form a leading edge base structure comprising a weld extending the length of the elongate sheets. Material deposits can be provided onto an outer surface of the leading edge base structure in such a way as to substantially cover the weld, whereby the leading edge component is formed. | 04-25-2013 |
| 20130101424 | OVERFLOW VORTEX TRANSFER SYSTEM - The present invention is directed to a molten metal pump comprising an elongated pumping chamber tube with a base end and an open top end. A shaft extends into the tube and rotates an impeller therein, the impeller rotates proximate the base end. The tube has a diameter at least 1.1 times the diameter of the impeller. The pumping chamber tube preferably has a length at least three times the height of the impeller. The base end includes an inlet and the top end includes a tangential outlet. Rotation of the impeller draws molten metal into the pumping chamber and creates a rotating equilibrium vortex that rises up the walls of the pumping chamber. The rotating vortex adjacent the top end exists the device cia the tangential outlet. | 04-25-2013 |
| 20130115090 | TURBOMACHINE COMPONENT AND METHOD OF CONNECTING COOLING CIRCUITS OF A TURBOMACHINE COMPONENT - A turbomachine component is provided and includes a turbine blade, which is rotatable about a rotor of a turbine for power generation operations and a platform with which the turbine blade is to be assembled. The turbine blade is formed to define a main circuit having an appendage. The platform is formed to define a platform circuit, and a substantially radially extendible pathway configured to be coupled to the appendage and to the platform circuit. | 05-09-2013 |
| 20130115091 | SPLICE INSERT REPAIR FOR SUPERALLOY TURBINE BLADES - A damaged portion of a superalloy material turbine blade body is removed, forming an excavated recess. A repair splice is formed of a same material with similar mechanical structural properties, having a mating outer profile conforming to the corresponding recess profile. The repair splice is inserted and captured within the recess, so that the blade body and repair splice are mechanically interlocked. Given similarities in mechanical properties of both the blade body and the mechanically interlocked splice the repaired blade's overall mechanical structural properties are similar to those of an undamaged blade. The repair splice is affixed to the blade body so that the interlocking respective portions of each do not separate. Localized affixation and subsequent cosmetic blade surface repair can be performed with softer, low temperature application braze and weld alloys. | 05-09-2013 |
| 20130115092 | ISOTHERMAL STRUCTURAL REPAIR OF SUPERALLOY COMPONENTS INCLUDING TURBINE BLADES - Structural repair of cracks and other defects in superalloy components, such as steam or gas turbine blades in stationary or aero gas turbines, are performed by heating the blade substrate to an isothermal hold temperature below the substrate's incipient melting point and filling the crack with molten superalloy filler material. The molten filler solidifies into a casting and bonds with the component substrate at the isothermal hold temperature. Heat treatment processes are completed, so that the former crack is filled with cast superalloy material having identical or similar structural properties as the adjoining substrate superalloy material. The casting repair method may be utilized universally for all types of superalloy component defects, including those previously repaired by cosmetic, lower strength welding or brazing methods. | 05-09-2013 |
| 20130121837 | DEVICE FOR REDUCING THE DRIVE POWER REQUIREMENTS OF A WATERCRAFT - A device is provided for reducing the drive power requirement of a watercraft includes a fore-nozzle, wherein at least one outer fin projects outwards from the fore-nozzle. | 05-16-2013 |
| 20130129514 | PROPELLER ARRANGEMENT, IN PARTICULAR FOR WATERCRAFT - A drive system of a watercraft includes a propeller rotatable about a propeller axis, and at least one rotor fin which is disposed freely rotatably about the propeller axis. The diameter of a circular path described by the rotation of the at least one rotor fin is less than the diameter of the propeller. | 05-23-2013 |
| 20130129515 | CROSS FLOW FAN AND AIR CONDITIONER - A cross flow fan and an air conditioner including the cross flow fan, where the cross flow fan includes a fixing member, and a plurality of blades fixed to an upper surface of the fixing member and spaced apart from each other in a circumferential direction. one or more of the blades include a protrusion protruding in a downward direction from a surface of the blade. | 05-23-2013 |
| 20130136612 | FLUID DRIVEN TURBINE BLADE, AND TURBINE USING SAME - A turbine is described for deriving energy from a fluid flow. The turbine has a plurality of generally arcuate blades that are rotatable about a rotational axis transverse to the direction of fluid flow. Each blade comprises a plurality of separately formed straight sections that are straight when unstressed, and that are joined to form a blade in which at least some adjacent sections are inclined at an angle to one another. | 05-30-2013 |
| 20130142657 | TWO-BLADED VERTICAL AXIS WIND TURBINES - Two-bladed vertical axis wind turbines (VAWT) have many efficiency advantages over turbines with other numbers of blades. Principles for making them in the ideal fashion are presented for both drag and lift configurations. | 06-06-2013 |
| 20130149160 | AIRFOIL FOR ROTOR BLADE WITH REDUCED PITCHING MOMENT - A rotor blade for a rotary wing aircraft includes a root region extending from a rotor head to about 15% to 20% of a blade radius, a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius, and a tip region extending from a radial extent of the main region to a blade tip. At least a portion of one of the root region, the main region and the tip region includes an airfoil profile section defined by a scaled set of coordinates in which a set of y/c coordinates listed in Table I are scaled by a selected factor. | 06-13-2013 |
| 20130149161 | Conical wind turbine - A wind turbine comprising a rotor having a shallow slope cone configuration on a horizontal axis with its apex facing the wind and its base downstream. A plurality of circumaxially-spaced wind engaging vanes are mounted on the surface of the rotor. Each vane has an elongated substantial flat entry surface projecting substantially at right angles from the surface of the rotor for engagement by the wind and the surface of the vane being displaced angularly front to rear from the axis of the rotor so as to be engaged by the wind and drive the rotor. | 06-13-2013 |
| 20130149162 | QUIET WIND TURBINE BLADE - Noise produced by the blades of a wind turbine electric generator is reduced by creating randomly varied serrations on the trailing edge of the blade, thereby creating vortices of varying size, energy, and distance from the trailing edge. This configuration creates vortices that tend to cancel one another while avoiding the creation of adjacent, mutually reinforcing vortices. | 06-13-2013 |
| 20130164141 | BLADE WITH SEMI-RIGID TRAILING EDGE - A blade with an aerodynamic blade body having a leading edge and a trailing edge is provided. The blade includes at least one flexible adaptor component having a first side coupled to the trailing edge. Further, the blade includes at least one rigid acoustic segment attached to an opposing second side of the at least one flexible adapter component for mitigating noise during fluid flow over the blade. | 06-27-2013 |
| 20130170999 | FLUID FLOW MODIFICATION APPARATUS AND METHOD OF MANUFACTURE - A fluid flow modification apparatus ( 10 ) has a surface ( 15 ), the surface having an edge ( 65 ) of length Y over or past which a fluid can flow in use. The edge ( 65 ) has a virtual boundary ( 30 ) of length X where Y is greater than X. At least a first portion of the apparatus ( 10 ) within the virtual boundary ( 30 ) comprises an opening ( 55 ) and at least a second portion of the apparatus ( 10 ) comprises a projection ( 60 ) which extends beyond the virtual boundary ( 30 ) to provide the edge ( 65 ). The edge ( 65 ) is multi-scale. | 07-04-2013 |
| 20130177431 | MULTI-MATERIAL ROTOR, A STEAM TURBINE HAVING A MULTI-MATERIAL ROTOR AND A METHOD FOR PRODUCING A MULTI-MATERIAL ROTOR - A multi-material rotor, a super-critical steam turbine having a multi-material rotor, and a method of producing a multi-material rotor are disclosed. The rotor includes a shaft high temperature section having a first end and a second end. The shaft high temperature section is made up of at least three different materials. | 07-11-2013 |
| 20130183159 | WIND TURBINE BLADE, WIND POWER GENERATION SYSTEM INCLUDING THE SAME, AND METHOD FOR DESIGNING WIND TURBINE BLADE - A wind turbine blade includes a blade body whose chord length increases from a blade tip toward a blade root. The blade body includes a blade tip region located near the blade tip and whose chord length increases gradually toward the blade root, the blade tip region having a substantially constant first design lift coefficient, a maximum-chord-length position located near the blade root and having a maximum chord length, the maximum-chord-length position having a second design lift coefficient higher than the first design lift coefficient, and a transition region located between the blade tip region and the maximum-chord-length position. The transition region has a design lift coefficient increasing gradually from the first design lift coefficient to the second design lift coefficient in a direction from the blade tip toward the blade root. | 07-18-2013 |
| 20130195669 | FAN BLADE ATTACHMENT OF GAS TURBINE ENGINE - A fan blade includes a root including a front surface, a rear surface, a first side surface connected to the front surface and the rear surface, and a second side surface connected to the front surface and the rear surface. The front surface engages the first side surface and the second side surface by one or more blunted surfaces, and the rear surface engages the first side surface and the second side surface by one or more blunted surfaces. A blade extends from the root. | 08-01-2013 |
| 20130195670 | ROTOR FOR A WIND TURBINE - A rotor for a wind turbine, having a diameter of 50 metres or more, has a blade with at least two blade sections in the lengthwise direction of the blade, where at least one blade section has a curvature along the blade and relative to a second blade section, where said curvature results in the tip end of said blade being offset (x) relative to the axis of the blade root. A ratio (x/L) of the offset (x) relative to a distance (L) from the tip end of the blade to the blade root is between 0 and 0.1. | 08-01-2013 |
| 20130202443 | AXIAL FLOW DEVICE - An axial flow device includes a hub having an outer periphery and a plurality of blades each having a root portion, a tip portion and a body portion between the root portion and the tip portion and projecting outward from the outer periphery of the hub. Furthermore, the root portion has a first angle of attack, the tip portion has a second angle of attack, and the second angle of attack is greater than the first angle of attack. Specifically, each blade is integrally formed based on a continuous angle of attack variation from the root portion through the body portion to the tip portion. | 08-08-2013 |
| 20130202444 | BLADE CASCADE AND TURBOMACHINE - A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed. | 08-08-2013 |
| 20130209262 | METHOD OF MANUFACTURING AN AIRFOIL - Disclosed is a method of manufacturing an airfoil. The method includes establishing an Argon (Ar)-free environment, providing a bed within the Argon free environment, providing a set of data instructions for manufacturing the airfoil, and providing a powdered Nickel (Ni)-based alloy on the bed. In one example, the powdered Nickel (Ni)-based alloy consists essentially of about 4.8 wt. % Iron (Fe), about 21 wt. % Chromium (Cr), about 8.6 wt. % Molybdenum (Mo), about 0.07 wt. % Titanium (Ti), about 0.40% Aluminum (Al), about 5.01 wt. % Niobium (Nb), about 0.03 wt. % Carbon (C), about 0.14 wt. % Silicon (Si), and a balance Nickel (Ni). The method further includes fusing the powdered Nickel (Ni)-based alloy with an electron beam with reference to the data instructions to form the airfoil. | 08-15-2013 |
| 20130209263 | Blade for a Wind Turbine - A blade for a wind turbine comprising a blade root portion, the blade root portion defining an annular mounting surface for coupling to a hub or extender of the wind turbine and comprising a plurality of first holes provided with an internal bushing, wherein at least one first internal bushing comprises at least one first securing member, and at least one second internal bushing comprises at least one second securing member, the first and second bushings being located in or near substantially opposite positions of the annular mounting surface, and wherein said first and second securing members are adapted to receive connecting means for connecting the first securing member with the second securing member. | 08-15-2013 |
| 20130224031 | AIRFOILS FOR USE IN ROTARY MACHINES - An airfoil section of a propeller for a propulsion device includes a pressure surface and a suction surface, the pressure surface and suction surface intersecting at a leading edge and a trailing edge. The airfoil section has a meanline defined midway between the pressure surface and the suction surface and a meanline angle is defined as an angle between a tangent to the meanline and a centerline of the propeller. The blade has a meanline curvature defined as the slope of a meanline angle with respect to chord fraction along the meanline, and at least a portion of the meanline has a meanline curvature that increases from between approximately 0.1 chord fraction progressing toward the leading edge and at least a portion of the meanline has a meanline curvature that decreases from between approximately 0.1 chord fraction progressing toward the leading edge. | 08-29-2013 |
| 20130224032 | BLADE INSERT FOR A WIND TURBINE ROTOR BLADE AND RELATED METHODS - A blade insert for coupling a first blade segment to a second blade segment is disclosed. The blade insert may include an aerodynamic body extending between a first end configured to be coupled to the first blade segment and a second end configured to be coupled to the second blade segment. The aerodynamic body may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the aerodynamic body may define a chord, wherein the chord at the first end is substantially equal to the chord at the second end. | 08-29-2013 |
| 20130224033 | Steam Turbine Rotor - There is provided a steam turbine rotor with high reliability and corresponding to increase in length of a high strength steel blade, in which only a low-pressure last stage is highly strengthened. The steam turbine rotor includes a steam turbine low-pressure last stage long blade made of a precipitation hardening type martensitic stainless steel containing, in mass, 0.1% or less of C, 0.1% or less of N, 9.0% to 14.0% inclusive of Cr, 9.0% to 14.0% inclusive of Ni, 0.5% to 2.5% inclusive of Mo, 0.5% or less of Si, 1.0% or less of Mn, 0.25% to 1.75% inclusive of Ti, 0.25% to 1.75% inclusive of Al, and the balance consisting of Fe and inevitable impurities, and a disk having a specific alloy composition is joined to a last stage section of the turbine rotor made of a low-alloy steel. | 08-29-2013 |
| 20130230403 | TURBINE DIAPHRAGM AIRFOIL, DIAPHRAGM ASSEMBLY, AND METHOD OF REPAIR - A turbine diaphragm airfoil, a turbine diaphragm assembly employing such an airfoil, and a method of repair are described. In one embodiment, a turbine diaphragm airfoil includes: a composite airfoil body which includes a pressure side and a suction side, the composite airfoil including: a leading edge section forming a portion of each of the pressure side and the suction side; and a trailing edge section integral with the leading edge section, the trailing edge section including: a prefabricated member affixed to the leading edge section, the prefabricated member forming a remainder of the pressure side of the composite airfoil body; and a weld or braze section contacting the leading edge section and the prefabricated member, the weld or braze section forming a remainder of the suction side of the composite airfoil body. | 09-05-2013 |
| 20130236319 | AIRFOIL FOR GAS TURBINE ENGINE - An airfoil for a rotor blade or a stator vane of a gas turbine engine having a tip extension extending one or both of the suction and pressure side surfaces adjacent the tip. The tip extension defines a thickness at the tip larger than the true thickness of the airfoil. The tip extension includes a side transitional surface substantially defined along a curve extending tangentially from the corresponding side surface. The tip extension defines a gradual increase in the thickness over a portion of the airfoil having a radial dimension corresponding to at least 2 times the true thickness. | 09-12-2013 |
| 20130236320 | BLADE - A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former includes a zone of weakness, which reduces the ability of the root part to withstand an impact force. Thus, in an impact situation in which the fan blade has separated from the fan rotor and the fan blade has itself separated into fragments, the root part will fracture or buckle more easily than would be the case with conventional arrangements. This will lower the impact force of the root part upon the fan casing, thus permitting the fan casing to be designed to withstand lower impact forces. The fan casing can therefore be made lighter, and cheaper, than in conventional arrangements. | 09-12-2013 |
| 20130236321 | REMOVABLE ROTOR BLADE TIP - One or more embodiments are directed to a rotor blade tip for a rotor blade, in particular for a rotor blade of a wind power installation, which is in the form of an independent portion which can be connected to the rotor blade and has a first connecting surface directed in the direction of the rotor blade to be connected. For making the connection to the rotor blade provided at the connecting surface are first guide means with a guide direction when making the connection to the rotor blade and first locking means for fixing the rotor blade tip to the rotor blade as first component parts of a connecting mechanism. | 09-12-2013 |
| 20130243602 | BLADE RING SEGMENT HAVING AN ANNULAR SPACE DELIMITING SURFACE HAVING A WAVY HEIGHT PROFILE AND A METHOD FOR MANUFACTURING SAME - A method for machining a workpiece. An electrode is moved linearly in the direction of the workpiece to cause material to be removed from the workpiece, at least one end of a surface of the workpiece running obliquely to a guide edge of the electrode machining this surface. The electrode is moved at least partially with the electrode surface parallel to the surface, so that during the approach to the workpiece, areas of the workpiece having an irregular edge machined at a different intensity are formed, the difference in intensity of machining on the edge of the surface to be machined being compensated in that the surface to be machined is provided with a height profile adapted to the shape of the end of the surface to be machined. A blade ring segment and blade ring is also disclosed. | 09-19-2013 |
| 20130251533 | COMPRESSOR WHEEL - A compressor wheel for use with turbochargers or superchargers for forced air induction of internal combustion engines includes a base having a hub portion, and a plurality of blades extending from the base, each blade having a length defined by the distance between opposite axial extremities of the blade, the plurality of blades including at least three different types of blades, each having a substantially different length. | 09-26-2013 |
| 20130251534 | TURBINE - A plurality of stepped parts which have step surfaces facing an upstream side in a rotating axial direction of a structural member are provided in a tip portion of a blade, and seal fins which extend toward a circumference surface of each of the stepped parts and form small clearances between the seal fin and the circumference surface corresponding to the each of the stepped parts is provided in the structural member. Also, lengths from the small clearance to the step surface on the upstream side along the rotating axial direction of the structural member are set such that one of the stepped parts on the downstream side is smaller than the other one of the stepped parts on the upstream side. | 09-26-2013 |
| 20130259697 | ENHANCED WIND TURBINE BLADE - A wind turbine blade includes a root portion, a tip and a body extending between the root portion and the tip. The body has a pressure side and a suction side. The body further has at least one winglet. Each winglet has a spanwise extension towards the root portion of the rotor blade and that ends at the tip to form a winglet having a substantially C-shaped or substantially open P-shaped geometry. | 10-03-2013 |
| 20130266449 | Method of Using a Formable Core Block for a Resin Impregnation Process - A use of a core block for an impregnation process as well as a composite structure comprising such a core block is described. The core block has a first surface and a second surface, and a number of first grooves is formed in the first surface of the core. Furthermore, a number of second grooves is formed in the second surface of the core. The first grooves have a first height (h | 10-10-2013 |
| 20130266450 | CENTRIFUGAL COMPRESSOR - Provided is a centrifugal compressor including a first splitter blade | 10-10-2013 |
| 20130266451 | TURBINE ENGINE BLADE HAVING IMPROVED STACKING LAW - A turbine engine blade, including an airfoil which extends radially between a blade root and an airfoil tip, axially between a leading edge and a trailing edge, and tangentially between a pressure side and a suction side, the profile of the blade having a series of basic profiles, in a form of a vane section, stacked on one another along a stacking line connecting the center of gravity of all the vane sections. The projection of the stacking line of the airfoil on at least one plane extending radially from the blade root includes a double tangential inversion of the direction of the curvature thereof, located in the last thirty percent of the height of the airfoil, the projection plane being positioned substantially perpendicular to the chord of the blade. | 10-10-2013 |
| 20130272888 | TURBOMACHINE BLADE TIP SHROUD WITH PARALLEL CASING CONFIGURATION - Embodiments of the present disclosure include a turbomachine having a turbomachine blade and a stationary structural component. The turbomachine blade includes a tip shroud having a leading edge portion where the leading edge portion has a first surface. The stationary structural component is disposed about the turbomachine blade and includes a corresponding portion corresponding to the leading edge portion of the tip shroud, where the corresponding portion has a second surface, where the first surface and the second surface have generally parallel contours. | 10-17-2013 |
| 20130272889 | Method of Extending the Service Life of Used Turbocharger Compressor Wheels - A method is provided for extending the service life of a used metallic compressor wheel having a damaged surface. The method generally comprises the steps of inspecting the used compressor wheel for material discontinuities such as fatigue cracks and, if fatigue cracks exceeding a predetermined length are not present, renewing the used compressor wheel such as by peening. The inspection process comprises conducting a non-destructive examination of the used compressor wheel to detect cracks larger than those which would fall generally within the compressive stress zone that is generated by peening. | 10-17-2013 |
| 20130272890 | WIND TURBINE BLADE, WIND TURBINE GENERATOR INCLUDING WIND TURBINE BLADE, AND METHOD FOR DESIGNING WIND TURBINE BLADE - When a distance from a front edge along a blade chord line is represented by X and a distance from the blade chord line to a blade back side is represented by Y, a blade back shape of a wind turbine blade includes a first region extending from the maximum blade thickness position toward the rear edge with dY/dX as a primary derivative amount of Y to X decreasing by a first amount of change, a second region on a side of the rear edge of the first region and extending toward the rear edge with dY/dX having a second amount of change smaller than the first amount of change, and a third region on the side of the rear edge of the second region and connected to the rear edge with dY/dX decreasing by a third amount of change larger than the second amount of change. | 10-17-2013 |
| 20130280079 | PROPELLER BLADE WITH METALLIC FOAM SPAR CORE - According to one embodiment, a propeller blade includes a metallic foam core and a structural layer that surrounds at least a portion of the metallic foam core. | 10-24-2013 |
| 20130280080 | GAS TURBINE ENGINE AIRFOIL WITH DIRT PURGE FEATURE AND CORE FOR MAKING SAME - An airfoil includes a body. The body includes leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface. First and second cooling passages extend in a radial direction from a root to a tip. The first cooling passage includes a tip flag passage that is radially inboard from the tip and extends in a chord-wise direction to a first end that penetrates the trailing edge. The second cooling passage includes a second end terminates adjacent the tip flag passage and a dirt purge passage interconnects the second end to the tip flag passage. A core for making the airfoil is also disclosed. | 10-24-2013 |
| 20130280081 | GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS - A core for an airfoil includes a refractory metal structure having a variable thickness. An airfoil includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness, and the second thickness is less than 0.060 inch (1.52 mm). A method of manufacturing a refractory metal core includes depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of a refractory metal core, and producing the core having a variable thickness. | 10-24-2013 |
| 20130280082 | AIRFOIL WITH POWDER DAMPER - An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity. | 10-24-2013 |
| 20130280083 | ROTOR BLADE ARRANGEMENT FOR A TURBO MACHINE - In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade ( | 10-24-2013 |
| 20130287580 | STRESS CORROSION CRACKING RESISTANCE IN SUPERALLOYS - A treatment for improving resistance to stress corrosion cracking (SCC) and a treated component are disclosed. A surface of a relatively high tensile strength component that includes a superalloy material is heated to a temperature at which softening occurs. The surface is then cooled in a controlled manner so as to maintain a reduced tensile strength at the surface that improves resistance to SCC while keeping a relatively high tensile strength in the remainder of the component. | 10-31-2013 |
| 20130287581 | FAN COMPRISING FAN BLADES - Disclosed herein is a fan comprising fan blades, especially for a cooler of a motor vehicle, said fan blades being fixed to a fan hub. In spite of being made of only a small amount of material, said fan is highly resistant to the flow conditions in the motor vehicle, each fan blade being bent rearwards at an angle in the direction of a blade root, an angled region of the fan blade being at least partially bent downwards towards the fan hub. | 10-31-2013 |
| 20130287582 | HIGH EFFICIENCY PROPELLER BLADE WITH INCREASED PRESSURE SIDE SURFACE - A propeller used in aircraft/sea vessels, pumping systems, wind and hydraulic turbines is provided. Propeller blades are distributed around the propeller hub and positioned so as to set an angle with the axis (x) of the propeller hub, to a concave curvilinear contact surface formed on the suction side of said blades that push water and to a convex outlet surface which follows this concave surface and is shorter than said concave surface. | 10-31-2013 |
| 20130287583 | Damping means for damping a blade movement of a turbomachine | 10-31-2013 |
| 20130294919 | METHOD OF MACHINING SURFACES OF ROTOR DISC AND GRINDING MACHINE THEREFOR - A method of manufacturing turned surfaces of a rotor disc of a gas turbine engine, including rotating the rotor disc about its central axis, rotating an abrasive grinding wheel having an outer grinding surface with a hardness greater than that of a material of the rotor disc, contacting the rotating wheel with at least one annular surface of the rotating disc, and sliding the rotating wheel along a curved cross-sectional profile of the at least one annular surface of the rotating disc. | 11-07-2013 |
| 20130309094 | COOLING FAN WITH IMPELLER - A cooling fan includes a hub and an impeller. The hub includes a circular wall and an annular wall. The annular wall has a position end opposite to the circular wall. The impeller includes a blade ring and a plurality of blades integrally extending outwards from an outer circumferential surface of the blade ring. The blade ring receives the hub and has a first mounting end and a second mounting end opposite to the first mounting end. When the position end abuts the second mounting end of the blade ring, the blades extend aslant from the blade ring toward a counterclockwise direction relative to the circular wall. When the position end abuts the first mounting end of the blade ring, the blades extend aslant from the blade ring toward a clockwise direction relative to the circular wall. | 11-21-2013 |
| 20130315746 | Wind blades and producing method thereof - A method of producing a pre-bent wind blade, includes: obtaining a pre-bent curve of a straight wind blade; and producing a bent wind blade according to the pre-bent curve, in such a manner that under a rating wind speed, the wind blade extends to be straight, so as to increase energy yield annually. | 11-28-2013 |
| 20130323066 | MASKANT FOR FLUORIDE ION CLEANING - A method of treating a surface includes the steps of providing a plating including at least some nickel over a nickel alloy surface in a thickness less than 0.0005″ (0.001 cm), and exposing the surface to a fluoride ion cleaning to remove impurities on the surface, and leaving at least some of the plating. | 12-05-2013 |
| 20130323067 | TURBINE ROTOR COVER PLATE LOCK - A rotor assembly for a gas turbine engine includes a rotor configured for rotation about an engine axis, the rotor including an aft surface including a rotor slot and a cover plate attached to the aft surface of the rotor, the cover plate including a tab received within the rotor slot and a cover plate slot aligned with the rotor slot. A lock assembly disposed within the rotor slot holds a position of the cover plate relative to the rotor. The lock assembly includes a key portion conforming to the rotor slot, a lock portion engageable with a surface of the rotor slot and a threaded member for holding the lock assembly within the rotor slot. | 12-05-2013 |
| 20130330199 | CONE ANGLE INSERT FOR WIND TURBINE ROTOR - A rotor for a wind turbine is disclosed. The rotor includes a hub, a rotor blade, and a bearing assembly configured to rotate the rotor blade with respect to the hub. The rotor further includes an insert, the insert including a first end, a second end, and a body extending therebetween. The first end is coupled to the hub and the second end is coupled to the bearing assembly. The second end defines a second plane oriented at a cone angle with respect to a first plane defined by the first end. | 12-12-2013 |
| 20130330200 | CELLULAR WHEEL, IN PARTICULAR FOR A PRESSURE WAVE SUPERCHARGER - A cellular wheel ( | 12-12-2013 |
| 20130336798 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape. | 12-19-2013 |
| 20130343897 | Helix Type Vertical Axis Turbine Blades and Method for Continuously Making Same - A sheet metal blank is formed into a helical turbine blade by stretching an outer portion of the blank by creating indents and detents thereon. Then the stretched side is flattened and the stretched structure is formed into a helical shape. | 12-26-2013 |
| 20140003953 | MANUFACTURE OF A ROTOR BLADE FOR A WIND TURBINE | 01-02-2014 |
| 20140017087 | Dynamic Stability and Mid Axial Preload Control for a Tie Shaft Coupled Axial High Pressure Rotor - A middle support member is used to provide axial support and control to the tie shaft. The middle support member includes a high pressure compressor coupling nut that applies a preload that allows the high pressure compressor stack to be installed separately from the high pressure turbine rotor through a kickstand. | 01-16-2014 |
| 20140023509 | BAYONETED ANTI-ROTATION TURBINE SEALS - An assembly for connecting a coverplate and a rotor includes a first rotor for use in a rotating engine; a first cover mounted to the first rotor, wherein the rotor and the cover create a space there between, the space for having cooling air therein; and a lock assembly for preventing the cover from rotating circumferentially or moving axially away from the rotor if mounted to the to the rotor wherein the cover is sealed against the rotor. | 01-23-2014 |
| 20140023510 | DIAGONAL IMPELLER FOR A DIAGONAL FAN, AND DIAGONAL FAN - A diagonal impeller for a diagonal fan ( | 01-23-2014 |
| 20140030101 | TURBINE BUCKET WITH SQUEALER TIP - A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side wall and a suction side wall extending between a leading edge and a trailing edge. In addition, the airfoil may include a base and a tip disposed opposite the base. The tip may include a tip floor and pressure and suction side tip walls extending outwardly from the tip floor. Moreover, the tip may include an intermediate tip wall extending outwardly from the tip floor between the pressure and suction side tip walls. The intermediate tip wall may define a height that is less than a height of the pressure and/or suction side tip walls. | 01-30-2014 |
| 20140030102 | TURBINE BUCKET WITH NOTCHED SQUEALER TIP - A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the airfoil may include a tip. The tip may include a tip floor and a tip wall extending outwardly from the tip floor. The tip wall may include an inner surface defining an inner perimeter of the tip wall. Moreover, a plurality of notches may be defined by the inner surface around at least a portion of the inner perimeter. | 01-30-2014 |
| 20140030103 | LOW DRAG HIGH RESTORING MOMENT AIRFOILS - A rotor hub fairing system for use in a counter-rotating, coaxial rotary wing aircraft is provided including an upper hub fairing defined about an axis. A lower hub fairing is similarly defined about the axis. An airfoil shaped shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The airfoil shaped shaft fairing has a thickness to chord (t/c) ratio in the range of about 20% and about 45%. | 01-30-2014 |
| 20140030104 | FAN DEVICE AND VANE THEREOF - A fan device includes a frame including an axle base and a vane including a hub disposed on the axle base pivotally and blade assemblies disposed circumferentially on the sidewall surface. The hub includes a windward side and a sidewall surface. Each blade assemblies includes a first blade and a second blade protruded from the sidewall surface radially. The second blade is farther away than the first blade from the windward side. The angle of between an extending surface of a second side edge of the second blade extending and the windward side is greater than another angle of between an extending surface of a first side edge of the first blade extending and the windward side. The gap between the partial second side edge and the windward side is less than another gap between the first side edge and the windward side. | 01-30-2014 |
| 20140037455 | WIND TURBINE BLADE COMPRISING METAL FIBRES AND A TRANSITION REGION - A wind turbine blade | 02-06-2014 |
| 20140044551 | BLADE CASCADE WITH SIDE WALL CONTOURS AND CONTINUOUS-FLOW MACHINE - A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one pressure-side elevation and one suction-side depression, whose highest section and lowest section are located over an area 30% to 60% of an extension of the blades in the axial direction, and the axial positions of the outermost sections differ from each other at the maximum by 10% in the axial direction. | 02-13-2014 |
| 20140064978 | Multi-Axis Balancing Propellers and Methods for Balancing Same - Multi-axis balancing propellers and methods of balancing multi-axis balancing propellers along multiple axes are disclosed herein. In some embodiments, a propeller comprises a first blade extending from a hub in a first direction along a first axis, a second blade extending from the hub in a second direction along the first axis, a first balancing ear extending from the hub in a third direction along a second axis, and a second balancing ear extending from the hub in a fourth direction along the second axis. | 03-06-2014 |
| 20140064979 | Multicant Winglets - A multicant winglet has a first blade section having a leading and a trailing edge, a first lowermost edge and a first uppermost edge, and a first central plane defined by the edges, and a second blade section having a leading and a trailing edge, a second lowermost edge and a second uppermost edge, and a second central plane defined by the edges. The first central plane is canted from vertical by a first cant angle, and the second central plane is canted from vertical by a second cant angle, the first cant angle unequal to the second cant angle. | 03-06-2014 |
| 20140072438 | SUPERALLOY LASER CLADDING WITH SURFACE TOPOLOGY ENERGY TRANSFER COMPENSATION - A superalloy substrate, such as a turbine blade or vane, is fabricated or repaired by laser beam welding to clad one or more layers on the substrate. Laser optical energy is transferred to the welding filler material and underlying substrate to assure filler melting and adequate substrate surface wetting for good fusion. Energy transfer is maintained below a level that jeopardizes substrate thermal degradation. Optical energy transfer to the filler and substrate is maintained uniformly as the laser beam and substrate are moved relative to each other along a translation path by varying the energy transfer rate to compensate for localized substrate topology variations. | 03-13-2014 |
| 20140079557 | PLATINUM-COBALT-BORON BLOOD PUMP ELEMENT - A magnetic impeller for a blood pump such as a magnetically driven, rotary ventricular assist device for pumping blood of a patient, the impeller comprising a magnetic alloy including platinum, cobalt, and boron. | 03-20-2014 |
| 20140079558 | IMPELLER FOR A CENTRIFUGAL PUMP - The present invention relates to a centrifugal pump, the impeller of which comprises a shroud (34) with at least one solid and rigid working vane (36), and at least one solid and rigid rear vane (38), the at least one working vane (36) having a leading edge region (46), a trailing edge region (48), a central region (C), a side edge, a pressure face (42) and a suction face (44), the at least one solid and rigid rear vane (38) having a trailing edge region, a side edge, a pressure face and a suction face. The trailing edge region (48) of the at least one working vane (36) is rounded by means of a rounding to have a thickness greater than that in the central region (C). | 03-20-2014 |
| 20140093377 | EXTRUDED ROTOR, A STEAM TURBINE HAVING AN EXTRUDED ROTOR AND A METHOD FOR PRODUCING AN EXTRUDED ROTOR - A steam turbine, a rotor and a method for making an extruded rotor are disclosed as having a rotor bore formed of an extruded high temperature alloy. The method includes providing a high temperature alloy, melting the high temperature alloy, extruding the high temperature alloy to form a bore, and forming the bore into a rotor. | 04-03-2014 |
| 20140105750 | Turbine engine blade - A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3 H to 0.8 H, where H is the height of the blade measured from its root to its tip. | 04-17-2014 |
| 20140105751 | METHOD FOR MANUFACTURING MACHINE COMPONENT, AND ROTARY MACHINE EQUIPPED WITH IMPELLER MANUFACTURED BY MEANS OF THIS METHOD - A method for manufacturing a machine component includes a process of estimating post-heat-treatment strength for the intermediate form of a base material after a certain mechanical working process is performed, and a process of comparing the estimated strength with reference strength required for a final form. According to a result of the comparison, heat treatment of the base material is performed after one of the mechanical working processes is performed. | 04-17-2014 |
| 20140112795 | TURBINE BLADE - A turbine blade has a profile including a blade suction side line, a blade pressure side line, and a blade trailing edge formed by a curve connecting the rear ends of the blade suction side and pressure side lines to each other, wherein the curve forming the blade trailing edge of the profile is formed by connecting a pressure side curve portion which has an arc shape having a constant radius of curvature and extending from the rear end of the blade pressure side line toward the camber line of the profile, and a suction side curve portion which extends from the rear end of the blade suction side line toward the camber line while passing through a region closer to the camber line than a symmetric curve portion which is line-symmetric to the pressure side curve portion with respect to the camber line. | 04-24-2014 |
| 20140119929 | ROTOR BLADE FOR A TURBOMACHINE AND TURBOMACHINE - The invention relates to a blade ( | 05-01-2014 |
| 20140119930 | Method of Repairing, Splicing, Joining, Machining, and Stabilizing Honeycomb Core Using Pourable Structural Foam and a Structure Incorporating the Same - A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein. | 05-01-2014 |
| 20140119931 | ROTOR BLADE MOLD ASSEMBLY AND METHOD FOR FORMING ROTOR BLADE - Methods for forming rotor blades, rotor blade mold assemblies, and cores for rotor blade mold assemblies are disclosed. A method includes providing a first shell substrate on a first mold, providing a generally hollow core on the first shell substrate, providing a second shell substrate on the generally hollow core, and providing a second mold on the second shell substrate. The method further includes flowing a resin into a mold interior defined between the first mold and the second mold. | 05-01-2014 |
| 20140133994 | GAS TURBINE WITH PYROMETER - A gas turbine with at least one stationary stator blade and at least one rotor blade that can be rotated during operation is provided. The gas turbine has at least one optical waveguide embedded into a first rotor blade. The optical waveguide is oriented such that thermal radiation of a region of the first stator blade can be detected by the optical waveguide. An analyzing device is designed to analyze the thermal radiation and to ascertain the temperature of the region of the first stator blade, the temperature being ascertainable along a path from which the radiation is emitted during the rotation of the first rotor blade. | 05-15-2014 |
| 20140154087 | GAS TURBINE ENGINE AIRFOIL - A blade for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a platform and an airfoil that extends from the platform. The airfoil extends in span between a root and a tip region and in chord between a leading edge and a trailing edge. A sweep angle is defined at the leading edge and a dihedral angle is defined relative to the chord of the airfoil. The sweep angle and the dihedral angle are localized at the tip region and extend over a distance of the airfoil equivalent to about 10% to about 40% of the span. | 06-05-2014 |
| 20140154088 | METHOD FOR MANUFACTURING A METALLIC COMPONENT BY ADDITIVE LASER MANUFACTURING - The invention refers to a method for manufacturing a three-dimensional metallic article/component entirely or partly. The method includes a) successively building up said article/component from a metallic base material by means of an additive manufacturing process by scanning with an energy beam, thereby b) establishing a controlled grain orientation in primary and in secondary direction of the article/component, c) wherein the secondary grain orientation is realized by applying a specific scanning pattern of the energy beam, which is aligned to the cross section profile of said article/component, or with characteristic load conditions of the article/component. | 06-05-2014 |
| 20140161619 | SEALING DEVICE - The present invention relates to a sealing device ( | 06-12-2014 |
| 20140178203 | COATING FIXTURES FOR GAS TURBINE ENGINE COMPRESSOR DISKS - A method for coating a gas turbine engine compressor rotor having a compressor disk with axial slots includes inserting masking fixtures into the axial slots. Each masking fixture includes a masking root that matches the shape of a blade root of an axial blade configured to be inserted into the axial slot the masking fixture is inserted into. The method also includes applying a coating to the compressor rotor after inserting the masking fixtures into the axial slots followed by drying the coating on the compressor rotor at a predetermined temperature. The method further includes removing the masking fixtures from the axial slots after drying the coating on the compressor rotor followed by curing the coating on the compressor rotor. | 06-26-2014 |
| 20140193267 | DMZ Fracture Boundary Limit - A method of establishing a boundary for a material improvement process on a workpiece is disclosed. The method may include identifying a maximum allowable damage depth on the workpiece; identifying a maximum constant thickness line on the workpiece at an extent of the maximum allowable damage depth; identifying a peak vibratory stress gradient on the workpiece; identifying a peak combined engine stress on the workpiece; and specifying the boundary for the material improvement process on the workpiece relative to the maximum constant thickness line, peak vibratory stress gradient, and peak combined engine stress. | 07-10-2014 |
| 20140193268 | METHOD OF FORMATION OF IMPELLER WITH SHAPE DEFINED BY PLURALITY OF LINES AND SUCH IMPELLER - An impeller ( | 07-10-2014 |
| 20140205461 | VACUUM DEGASSING LASER-BLOCKING MATERIAL SYSTEM AND PROCSES - A method of injecting laser-blocking material into a workpiece includes communicating molten laser-blocking material through the workpiece as the workpiece is subjected to at least a partial vacuum within an enclosed environment such that the partial vacuum expands any air bubbles in the laser-blocking material and transports the air bubbles out of the workpiece. | 07-24-2014 |
| 20140205462 | HVATA-HYBRID VERTICAL AXIS TURBINE ASSEMBLY OPERABLE UNDER OMNI-DIRECTIONAL FLOW FOR POWER GENERATING SYSTEMS - A hybrid, vertical axis helical turbine assembly capable of providing unidirectional rotation under an omni-directional low speed obverse fluid flow (gas or liquid), respectively gas flow is disclosed. The assembly comprises a minimum (but not limited to) of three hybrid (airfoil enhanced helical vane profile) wings, which are substantially spaced from the vertical axis (Z) and circumferentially spaced from one another. Each hybrid wing is fixed to the center hub in a rigid position by two or more arms, which are symmetrically located from each other in conjunction with the hub's horizontal axis (X). The hybrid, vertical axis helical turbine assembly provides high torque at very low wind speed because of the absolute symmetric airfoil enhanced helical vane profile wing, which design maintain adaptive lift to drag ratio over the one rotational revolution time line in coincidence of the upwind direction. These characteristics make the hybrid, vertical axis helical turbine assembly suitable for urban off grid and grid tie applications in low wind speed areas and areas of reputable wind turbulence. | 07-24-2014 |
| 20140234112 | ROTOR BLADE - A blade at least part of which is arranged in use to rotate outside of a casing of a gas turbine engine. The blade has a main body, a tip fence and a blend region defining a curve between the main body and the fence. The blend region has a radius of curvature below five inches and the fence extends anhedrally from the blend region with respect to the main body. | 08-21-2014 |
| 20140234113 | WIND TURBINE BLADE AND MANUFACTURING METHOD THEREOF - A manufacturing method of a wind turbine generator includes a cutting step of cutting a base blade at m cutting planes into (m+1) sections where m is an even number, the m cutting planes being at different positions in a blade length direction; and joining step of joining (m/2+1) sections of the (m+1) sections together to obtain a wind turbine blade which is shorter than the base blade, the (m/2+1) sections including a blade-root section which is closest to a blade root and a blade-tip section which is closest to a blade tip, the blade-root and blade-tip sections being non-adjacent to each other. | 08-21-2014 |
| 20140241894 | FAN ASSEMBLY AND FAN WHEEL ASSEMBLIES - Fan assemblies, and in particular fan wheels and stator assemblies for fan assemblies, are disclosed. In one embodiment, the fan wheel includes a wheel back having an outer surface forming one of a curved dome-shape and a truncated cone-shape. The fan wheel may also include a plurality of fan blades radially spaced about and mounted to the outer surface of the wheel back. In one embodiment, each of the fan blades is formed from a segment of an airfoil-shaped aluminum extrusion defining at least one internal cavity. The fan blade first ends can be provided with a compound cut profile with at least one curved cut such that the first end of the blade is mounted flush to the wheel back outer surface. The stator assembly can also be provided with a plurality of stator blades formed from airfoil-shaped aluminum extrusion segments and provided with compound cut profiles. | 08-28-2014 |
| 20140248155 | ONE-BLOCK BLADED DISK PROVIDED WITH BLADES WITH ADAPTED FOOT PROFILE - A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade. | 09-04-2014 |
| 20140271212 | FAILSAFE SYSTEM FOR LOAD COMPENSATING DEVICE - An apparatus and system for automatically deploying an air deflector of a load compensating device when there is a loss of communication or power is provided. In some examples, the apparatus and system may include a spring configured to rotate a gear, thereby deploying the air deflector. In some arrangements, the spring may be a torsion spring and may be biased to rotate the gear when released from a hold position maintained by a latch. The latch may be controlled by a release mechanism, such as a solenoid, that may be configured to activate upon occurrence of a communication loss event. The release mechanism may release the latch, thereby releasing the spring and deploying the air deflector. | 09-18-2014 |
| 20140271213 | AIRFOIL MODIFIERS FOR WIND TURBINE ROTOR BLADES - In one aspect, a rotor blade for a wind turbine is disclosed. The rotor blade may include a body extending between a blade root and a blade tip. The body may define a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the body may define a chord line extending between the leading and trailing edges. The rotor blade may also include an airfoil modifier coupled to at least one of the pressure side or the suction side of the body. The airfoil modifier may define an end surface disposed adjacent to the trailing edge. At least a portion of the end surface may extend at a non-perpendicular angle relative to the chord. | 09-18-2014 |
| 20140294590 | COMPACT BLADE FOR RUNNER OF FRANCIS TURBINE AND METHOD FOR CONFIGURING RUNNER - A blade for a runner of a Francis turbine having a throat diameter (Dth), the blade including: a maximum thickness of no less than 0.03 Dth and a leading edge having a maximum lean angle of no less than 45 degrees, wherein the lean angle is defined by a vertical line and the leading edge. | 10-02-2014 |
| 20140301855 | BLADE INSERT FOR A WIND TURBINE ROTOR BLADE - A blade insert for coupling a first blade segment to a second blade segment is disclosed. The blade insert may generally include an aerodynamic body extending between a forward end configured to be coupled to the first blade segment and an aft end configured to be coupled to the second blade segment. The aerodynamic body may include a top side extending between a forward edge and an aft edge. The top side may define a top scarfed section at its forward edge. The aerodynamic body may further include a bottom side extending between a forward edge and an aft edge. The bottom side may define a bottom scarfed section at its forward edge. Additionally, at least a portion of the forward edge of the top side may be configured to be offset relative to the forward edge of the bottom side. | 10-09-2014 |
| 20140314579 | TURBINE - The turbine related to the invention is a turbine including blades and a structure rotating relative to the blades and having a fluid flowing thereto. The turbine includes step portions that are provided in either radial tip portions of the blades or areas of the structure that face the radial tip portions; sealing fins that extend from the other toward the step portions, and form minute gaps between the sealing fins and the step portions; a flow collision surface that is provided upstream of the sealing fins in a flow direction of the fluid and against which the fluid collides; a protrusion that protrudes toward an upstream side from the flow collision surface; and a facing surface that faces the flow collision surface. | 10-23-2014 |
| 20140322022 | PLATINUM-COBALT-BORON BLOOD PUMP ELEMENT - A magnetic impeller for a blood pump such as a magnetically driven, rotary ventricular assist device for pumping blood of a patient, the impeller comprising a magnetic alloy including platinum, cobalt, and boron. | 10-30-2014 |
| 20140322023 | METHOD AND PRODUCTION FACILITY FOR MANUFACTURING A WIND TURBINE BLADE - The present invention relates to a method for manufacturing a wind turbine blade in a production facility. The method comprises the steps of positioning a first overhung gantry to extend transversely over an elongated first mould part for manufacturing one of a first part and a second part of the blade, performing a first working action at the first mould part with a first tool mounted on the first overhung gantry, moving the first overhung gantry from the first mould part to an elongated second mould part for manufacturing the other of the first and the second part of the blade, positioning the first overhung gantry to extend transversely over the second mould part, and performing a second working action at the second mould part by means of the first tool or a second tool mounted on the first overhung gantry. | 10-30-2014 |
| 20140328688 | ROTOR BLADE ASSEMBLY HAVING VORTEX GENERATORS FOR WIND TURBINE - Rotor blade assemblies for wind turbines are provided. In one embodiment, a rotor blade assembly includes a rotor blade, and a plurality of vortex generators configured on at least one of a suction side or a pressure side and disposed within an inboard area of the rotor blade. The plurality of vortex generators include a row of vortex generators extending in a generally span-wise direction, the row comprising a first portion of vortex generators and a second portion of vortex generators, the second portion of vortex generators spaced apart from the first portion of vortex generators in the span-wise direction. Each first portion vortex generator is disposed at a first chord-wise location, and each second portion vortex generator is disposed at a second chord-wise location different from the first chord-wise location. | 11-06-2014 |
| 20140328689 | METHOD FOR MANUFACTURING IMPELLER - An impeller in which a plurality of vanes are provided so as to overlap each other back and forth as viewed in the direction of axis has a first impeller part on a front side and a second impeller part on a rear side. A method for manufacturing impeller includes a step of molding a first impeller part, a step of molding a second impeller part and a step of combining together the first impeller part and the second impeller part. | 11-06-2014 |
| 20140341745 | ROTOR BLADE FOR A COMPRESSOR AND COMPRESSOR HAVING SUCH A ROTOR BLADE - A rotor blade of an axial compressor includes: a blade root; and a blade leaf. The blade leaf has: a flow inlet edge, a flow outlet edge, a pressure side extending between the flow inlet edge and the flow outlet edge and a suction side extending between the flow inlet edge and the flow outlet edge, which together define a blade profile of the blade leaf in Cartesian coordinate values x, y and z such that first and second profile coordinates, or the coordinates x and y when joining via continuous arcs, each describe a smooth profile section on a radial section height along a third profile coordinate, or the coordinate value z, and the joining of the radial profile sections with a smoothing function describe the blade profile of the blade leaf. | 11-20-2014 |
| 20140348658 | Medallion Fan - This invention relates to a ceiling mounted air circulating apparatus comprising, in combination: a motor; an essentially centrally located radial or axial air impeller; air guiding means; optional airflow enhancement by means of air amplification means; an optional centrally located wiring path from an electrical power source to a wiring enclosure suitable for hanging a lighting fixture or chandelier; and decorative embellishments, all of which are arranged to blend with the architectural style of a space in a manner similar to a decorative ceiling medallion, the planform of which, when viewed from below may be circular, rectangular, or polygonal. Optionally, the apparatus of the present invention may embody any of the following; heating, cooling, filtration means, positive ion generation means, and/or air sterilization means. | 11-27-2014 |
| 20140356179 | IMPELLER AND ROTATING MACHINE PROVIDED WITH SAME - The impeller is provided with: a disc section equipped with a tube section, the grip section of which is fixed by thermal deformation to a rotation shaft that is rotated around the axis line, and a main disc body, which is provided on the other end in the axial direction from the grip section and which extends outward in the radial direction of the rotation shaft; and blade sections that protrude from the main disc body in the axial direction. The disc section is provided with a hoop stress-limiting section, the tube section of which extends further towards the other end in the axial direction than the main disc body. | 12-04-2014 |
| 20140363301 | Bell Turbine - Volumetric turbine blades are proposed that have the capacity to efficiently operate at low flow speeds and oriented in any direction to the incoming flow. | 12-11-2014 |
| 20140363302 | AIRFOIL FOR GAS TURBINE, BLADE AND VANE - The invention relates to an airfoil for a gas turbine, which comprises a compound fillet disposed between the airfoil and a platform. The compound fillet consists of a first arc and a second arc. A first end of the first arc tangentially adjoins an outer surface of the airfoil. A second end of the first arc tangentially adjoins a first end of the second arc. A second end of the second arc tangentially adjoins a surface of the platform, wherein the following equation is satisfied: 0.15≦R1/s≦0.45, and 0.09≦a/s≦0.27. | 12-11-2014 |
| 20140369842 | METHOD OF MANUFACTURING A CERAMIC CORE FOR MOBILE BLADE, CERAMIC CORE AND MOBILE BLADE - A method of manufacturing a ceramic core for a blade including a lower part forming a core body, an upper part forming a squealer tip recess and a set of rods for holding the upper part and the lower part together, includes: coating the rods with a material that has a flash point below 1000° C.; positioning the rods in a mould; moulding the upper and lower parts by injecting ceramic; firing the ceramic core, | 12-18-2014 |
| 20140369843 | MIXING ROTOR AND INTERNAL MIXER - A mixing rotor includes: a rotor shaft portion that includes a cooling passageway formed therein, and a mixing blade portion that is formed in an outer circumferential portion of the rotor shaft portion, wherein each of the long blades of the mixing blade portion includes a land portion as an end surface of the long blade facing a radially outside of the mixing rotor, a length of each of the long blades in the axis direction is set to be 0.6 times or more as large as a length of the mixing blade portion in the axis direction, a biting angle of each of the long blades is set to an angle equal to or smaller than 31°, and a center angle with respect to a land width as a width of the land portion in the cross-section of each of the long blades orthogonal to the axis direction is set to an angle equal to or larger than 7°. | 12-18-2014 |
| 20140369844 | OPTIMISATION OF THE BEARING POINTS OF THE STILTS OF VANES IN A METHOD FOR MACHINING SAID VANES - A method of machining a blade in a three-dimensional machining center, the blade including an airfoil, a platform including upstream and downstream supports formed respectively under the upstream and downstream portions thereof for supporting a sealing liner, a blade root, and a stilt interposed between the platform and the blade root, the method including the upstream and downstream supports constituting two bearing points for a six-point positioning system for positioning the blade in the three-dimensional machining center. | 12-18-2014 |
| 20140377075 | METHOD FOR REPAIRING A BLADE - A method for repairing a blade in a gas turbine engine comprises the steps of: isolating the damage on the airfoil of the blade; forming a cut back in the shape of elongated “D” shaped recess with a pair of fillets, a depth and a longitudinal axis of the “D” shaped recess having a length along the leading or trailing edge of the airfoil; and the fillets having a respective radius. | 12-25-2014 |
| 20150017009 | IMPELLER HAVING BLADE HAVING BLADE SURFACE MADE UP OF LINE ELEMENTS AND METHOD OF MACHINING THE IMPELLER - A blade of an impeller has a blade surface made up of line elements. The line elements forming the blade surface are not parallel to each other. A relationship between a twist angle of the line elements and a distance between the origin and an intersection of a central line of the impeller and an extension line of a Z-axis projection line obtained by projecting each of the line elements onto a Z-axis projection plane is represented by a curve. | 01-15-2015 |
| 20150023797 | Aerodynamic Variable Cross-Section Airfoil and Constant Lateral Surface Area Truss - The invention provides a mechanism for an airtight airfoil with variable cross section that can lower its average density below that of the medium in which it is used, providing additional bouyancy and reducing the effective weight of any craft to which it may be affixed. The outside of the airfoil is formed by a sheet of material that is impermeable to the medium in which the foil is used. This sheet is affixed to several points on an internal expandable frame. The cross-sectional perimeter of the frame remains constant throughout the expansion of the frame, minimizing wear on the enclosing sheet of material. Because the length of the sheet remains constant through the expansion process, the sheet need not be elastic, and may even be replaced by rigid plates of material. By providing a variable source of buoyancy, this foil enables lower speed and lower power applications than regular foils. By providing a smoothly variable airfoil cross-section, this foil enables higher performance in a wider variety of aerodynamic conditions. | 01-22-2015 |
| 20150023798 | BLADE MEMBER FOR FLUID PUMP - The object is to obtain reasonably a blade member for a pump having superior fluid transporting performance. A blade member for a fluid pump includes a cylindrical portion formed around a rotational axis, a plurality of base portions protruding radially outwardly of the rotational axis from one end portion of the cylindrical portion along the rotational axis and provided along a circumferential direction, a bent portion bent from each of the respective base portion in one direction along the rotational axis, and a hole portion provided in a border portion between root portions of the adjacent base portions. A rising edge portion extending from the hole portion to a leading end of the bent portion and an overhang edge portion extending from the hole portion to a leading end of the base portion are formed by a common cut portion. | 01-22-2015 |
| 20150037163 | BLADES FOR AXIAL FLOW COMPRESSOR AND METHOD FOR MANUFACTURING SAME - An axial flow compressor blade unit including a platform section and an airfoil section, which are used as arranged on a circumference about an axis of the compressor. The platform section includes an inner diametric surface segment inwardly of the circumference, an outer diametric surface segment outwardly of the circumference, two annular side surface segments extending in a circumferential direction, two axially side surface segments extending in the axial direction, and a coupling portion formed in each of the annular side surface segments so as to extend in the circumferential direction and being of a shape projecting or recessed in the axial direction. The airfoil section is formed to erect from the platform section so as to extend in a radial direction. The platform section and the airfoil section are formed integrally with each other while having a powdered metal sintered structure. | 02-05-2015 |
| 20150037164 | AIRFOIL FOR FAN BLADE - A fan blade comprises an airfoil profile having a lower surface, an upper surface, a trailing edge, and a leading edge. The lower surface comprises a concave portion which is defined by a first ellipse. The upper surface comprises a convex portion which is defined by a second ellipse. The leading edge and the trailing edge are of a substantially convex shape and transition the concave shape of the lower surface to the convex shape of the upper surface. A maximum thickness of the airfoil profile is defined at a point along the airfoil profile proximal to the leading edge of the fan blade. A chord length is defined as a lineal distance between an outermost point of the leading edge and an outermost point of the trailing edge. The dimensions of the airfoil profile, including those of the first ellipse and second ellipse, are functions of the chord length. | 02-05-2015 |
| 20150044055 | Wind turbine having flow-aligned blades - A wind turbine blade is configured such that the lift force from the blade airfoil is always normal, or nearly normal, to the shaft torque. This condition maximizes energy conversion. This objective may be achieved by a) having the airfoil chord always aligned to the actual wind direction (subject only to small angle of attack variations), and b) slowing the turbine rotation rate so that no blade twist is needed. As a result, blade tip speed due to shaft rotation is less than the wind speed, and preferably much less. This low tip speed eliminates any hazard to birds. The lift force from the blade airfoil directly drives the torque on the shaft, so the control problem simplifies to adjusting the blade angle of attack to keep the lift constant across varying wind speeds. For most airfoils, a slightly negative angle of attack results in zero lift, so this simple approach has a ready fail-safe condition. This fail-safe condition is operable up to very high wind speeds, eliminating any need to provide for turbine overspeed control. The same teachings are equally applicable to water turbines and other types of turbines. | 02-12-2015 |
| 20150050155 | IMPELLER FOR FUEL PUMP OF VEHICLE - Provided is an impeller for a fuel pump of a vehicle capable of decreasing a magnitude of high frequency fluid noise due to high speed rotation of the impeller by upper and lower blades of impeller blades positioned between upper and lower casings of the fuel pump and coupled to a shaft of a driving motor to deliver a fuel by rotational force so as to have asymmetrical angles based on the center of a thickness of an impeller body in sucking the fuel from a fuel tank and supplying the fuel to an engine of an internal combustion engine. | 02-19-2015 |
| 20150071786 | PROPELLER FAN, FLUID FEEDER, AND MOLDING DIE - A blade of a propeller fan includes a blade root portion, a front edge portion, a blade tip end portion, a rear edge portion, a blade rear edge portion, and an outer edge portion. A blade surface of the blade has an inner region including the blade root portion, an outer region including the blade rear end portion, and a coupling portion extending from a front end portion located close to the blade tip end portion to a rear end portion located close to the rear edge portion and coupling the inner region and the outer region to each other such that a side of a positive pressure surface of the blade surface is projecting and a side of a negative pressure surface of the blade surface is recessed. | 03-12-2015 |
| 20150071787 | Impeller For Motor Vehicle Fan, Including Segmented Hub Stiffeners - A blower wheel for setting a flow of air in circulation has vanes ( | 03-12-2015 |
| 20150098832 | METHOD AND SYSTEM FOR RELIEVING TURBINE ROTOR BLADE DOVETAIL STRESS - A system for relieving stress on a turbine rotor blade dovetail in a gas turbine is provided. At least one turbine rotor blade includes a dovetail that is axially insertable into a correspondingly-shaped slot defined in a turbine disk. At least one axially-extending tang is defined on the dovetail. At least one stress relief surface is defined in the at least one tang. The at least one stress relief surface extends along a central portion of a length of the tang. Accordingly, contact between the at least one tang and an inner surface of the slot is precluded, along the central portion, such that stresses generated by radially-directed forces along the central portion are reduced. | 04-09-2015 |
| 20150104321 | WIND SPINNER - A wind spinner includes a body, at least one rod attached to the body for rotation about a blade axis, at least two blades disposed at opposing ends of the rod, forming at least one pair of blades, and at least one blade support disposed within each blade. The at least one blade support includes a central portion disposable on the at least one rod. The central portion is attached to at least one wing portion that extends outwardly therefrom to provide internal support to the blade. In addition, the blades are angled at a blade angle and at a position on the at least one rod such that wind passing thereover causes the at least one pair of blades to rotate about the blade axis. | 04-16-2015 |
| 20150104322 | THERMAL MANAGEMENT ARTICLE AND METHOD OF FORMING THE SAME, AND METHOD OF THERMAL MANAGEMENT OF A SUBSTRATE - A thermal management article, a method for forming a thermal management article and a thermal management method are disclosed. Forming a thermal management article includes forming a duct adapted to be inserted into a groove on the surface of a substrate, and attaching the duct to the groove so that the top outer surface of the duct is substantially flush with the surface of the substrate. Thermal management of a substrate includes transporting a fluid through the duct of a thermal management article to alter the temperature of the substrate. | 04-16-2015 |
| 20150104323 | METHOD FOR CREATING A METAL REINFORCEMENT WITH INSERT FOR PROTECTING A LEADING EDGE MADE OF COMPOSITE - A method for producing a metal reinforcement for protecting a leading edge of a compressor blade of composite, including: creating a core that has a shape of an internal cavity of the reinforcement; creating an insert made of an alloy of a hardness greater than that of the reinforcement; shaping sheet metal by stamping with the creation, upstream of the core, a cavity between the metal sheets, which cavity is configured to accept the insert, positioning the sheets around the core with the insert placed in the cavity and securing the assembly together; creating a vacuum and closing the assembly by welding; consolidation by hot isostatic pressing; cutting the assembly to extract the core and separate the reinforcement; creating an external profile of the reinforcement by a final machining operation that reveals a material of the insert. | 04-16-2015 |
| 20150125307 | PROPELLER FAN, FLUID FEEDER, ELECTRIC FAN, AND MOLDING DIE - A propeller fan includes a boss hub portion and a blade including a front edge portion, a rear edge portion, and an outer edge portion. The outer edge portion has a front outer edge portion, a rear outer edge portion, and a connection portion connecting the front outer edge portion and the rear outer edge portion to each other. In a plan view of the blade along a central axis, a maximum radius R1 | 05-07-2015 |
| 20150139812 | Steam Turbine - A stationary blade includes a main unit having a hollow blade structure formed from a metal plate by plastic forming. The stationary blade includes a blade tail section. In a blade tail upper portion, the metal plate has a concave-shaped recess and a rib formed on an inner surface side thereof and the metal plate further has slits formed by slitting on a blade pressure side thereof, so that droplets affixed on a blade surface can be guided into an inside of the hollow blade when the blade tail section is joined to the hollow blade main unit. The recess in the metal plate is covered so as to be lidded by a suction-side protrusion of a suction-side metal plate from a blade suction side to thereby form a hollow blade tail section. The metal plates are welded together to the main unit. | 05-21-2015 |
| 20150292337 | COMPONENTS RESISTANT TO TRAVELING WAVE VIBRATION AND METHODS FOR MANUFACTURING THE SAME - Components resistant to traveling wave vibration and methods for manufacturing the same are provided. The component comprises a component body and a plurality of features disposed thereabout according to an asymmetry pattern that separates a pair of repeated eigenvalues associated with a targeted mode that deflects in excess of a threshold deflection limit in response to traveling wave excitation. The method comprises identifying, in a model of a rotationally periodic component, one or more modes thereof that deflect in excess of a threshold deflection limit in response to a traveling wave excitation. Each of the modes has a pair of repeated eigenvalues associated therewith. An asymmetry pattern is determined that separates each pair of repeated eigenvalues by a desired frequency split. A plurality of features are formed and disposed according to the asymmetry pattern about the component body defining an asymmetrical component comprising the component resistant to traveling wave vibration. | 10-15-2015 |
| 20150292523 | Conical Impeller and Applications Thereof - An conical impeller with a hub that has a conical surface extending into the interior of the impeller. The hub has spiral, slanting arms which are attached or integrally formed with a plurality of curved blades. The blades can be connected at the bottom by a ring. The intersection of the conical surface of the hub with the blade forms an upward path for fluids and their entrained particles or gases which have been brought into the interior of the impeller to effectively completely be ejected. The discharge edges of the blades and/or the conical surface of the hub may have openings for discharging gas into the fluid. The impeller imparts low shear to the fluid and its components, and the shear is independent or only depends slightly on the size of the impeller. The impeller minimizes or eliminates particle agglomeration and fouling of the impeller. The efficiency of and flow pattern produced by the impeller means that containers don't require the use of baffles. The high efficiency and low shear of the impeller is useful for applications such as mixing of biological fluids, decontamination of produced water, chemical mechanical polishing, and flotation cells. | 10-15-2015 |
| 20150300178 | TURBINE ROTOR - A turbine rotor of a turbine includes a hub that serves as an axis of rotation, and a plurality of turbine blades. The turbine blades each have a line extending along a shroud-side edge of the turbine blade from the inlet to the outlet as a shroud line. The shroud line includes an entrance-side shroud line La that makes a small change from the inlet toward the outlet in a blade angle with respect to the axis of rotation, a center shroud line Lb that extends from the outlet side of the entrance-side shroud line La and makes a greater change than that of the entrance-side shroud line La, and an exit-side shroud line Lc that extends from the outlet side of the center shroud line Lb to the outlet and makes a smaller change than that of the center shroud line Lb. | 10-22-2015 |
| 20150300316 | ROTOR BLADE FOR A WIND TURBINE - The present invention relates to a rotor blade and to a corresponding rotor of a wind turbine with a reduced rotor diameter and increased performance. The rotor blade for a wind turbine has a wing root with a defined first diameter as an attachment to a hub, and a rotor blade end which is opposite the wing root, with a second defined diameter. Said rotor blade furthermore has a trailing edge and a leading edge with respect to the slicing direction of the rotor blade during operation. The leading edge and the trailing edge each have a curvature. The first diameter is smaller than the second diameter. | 10-22-2015 |
| 20150322791 | Repair Method for Vortex Generator and a Kit for it - The invention relates to a method for repairing a vortex generator ( | 11-12-2015 |
| 20150328682 | MOLTEN METAL TRANSFER SYSTEM AND ROTOR - The invention relates to systems for transferring molten metal from one structure to another. Aspects of the invention include a transfer chamber constructed inside of or next to a vessel used to retain molten metal. The transfer chamber is in fluid communication with the vessel so molten metal from the vessel can enter the transfer chamber. A powered device, which may be inside of the transfer chamber, moves molten metal upward and out of the transfer chamber and preferably into a structure outside of the vessel, such as another vessel or a launder. | 11-19-2015 |
| 20160016654 | SELF-TIGHTENING ROTOR - Systems, methods, and devices for propelling self-propelled movable objects are provided. In one aspect, a rotor assembly for a self-propelled movable object comprises: a hub comprising a first fastening feature; a drive shaft comprising a second fastening feature and directly coupled to the hub by a mating connection of the first and second fastening features, wherein the drive shaft is configured to cause rotation of the hub such that the mating connection of the first and second fastening features is tightened by the rotation; and a plurality of rotor blades coupled to the hub and configured to rotate therewith to generate a propulsive force. | 01-21-2016 |
| 20160040687 | IMPELLER, ROTATING MACHINE, AND METHOD FOR ASSEMBLING ROTATING MACHINE - An impeller is equipped with: a disk part, having a cylindrical part into which a rotary shaft that rotates around an axis line is inserted, with a portion of the cylindrical part in the axis line direction of the rotary shaft being fixed to the rotary shaft as a grip part, and a disk main body part extending from the cylindrical part outward in the radial direction of the rotary shaft a blade part protruding from the disk main body part toward a side in a first direction in the axis line direction; a reinforcing member attachment part formed on the cylindrical part closer to a side in a second direction in the axis line direction than the disk main body part; and a reinforcing member formed of material having a higher specific strength than the disk part, and attached so as to cover the reinforcing member attachment part from the outside. | 02-11-2016 |
| 20160090963 | ROTOR BLADE TIP - A rotor blade of a wind energy plant having a main component of the blade and a blade tip, whereby the blade tip is releasably attached to the main component by means of a connection device and the connection device has a tip section attached to the blade tip and a base section attached to the main component of the blade to receive the tip section, whereby the tip section has at least one fastener that extends to the base section for attaching the tip section to the base section, and the fastener for performing the attachment can be actuated through an opening in the surface of the blade tip. | 03-31-2016 |
| 20160102674 | Fan Blade - A heating, ventilation, and/or air conditioning (HVAC) system includes an outdoor unit having an outdoor fan configured to generate an airflow. The outdoor fan includes a fan blade assembly having a plurality of fan blades. Each fan blades is formed from a constant and/or uniform thickness material and includes an upwardly curved leading edge that causes a lower surface of the fan blade to contact the air first as the fan blade assembly is rotated and causes air attachment to the lower surface such that an eddy of air is trapped, recirculated, and/or generally passed more slowly through a recirculation zone, defined generally as the angularly trailing space behind the upwardly curved leading edge and between the upwardly curved leading edge and the remainder of an upper surface. | 04-14-2016 |
| 20160108895 | METHOD FOR MACHINING A SHAFT AND APPARATUS MADE THEREBY - A method for machining a shaft includes the step of machining a compound radius into the shaft at a junction between a radial surface of the shaft and an axial facing flange portion of the shaft. The compound radius has a curved surface with at least two different radii. The curved surface extends circumferentially around the shaft. | 04-21-2016 |
| 20160137296 | ROTOR DOME, A ROTOR, AND A ROTORCRAFT - A dome for a rotor comprising a cap extending radially from an axis of rotation in elevation towards a periphery and in azimuth over 360 degrees, the cap extending in thickness from a bottom face towards a top face above the bottom face. The dome includes at least one slot extending between the periphery and the axis of rotation in elevation, each slot passing right through a thickness of the cap by extending in elevation from the bottom face to the top face. | 05-19-2016 |
| 20160138601 | AXIAL FAN - An axial fan comprises a hub and a plurality of blades extending from the hub; wherein each blade comprises a main blade portion and a secondary blade portion and the secondary blade portion has a leading edge adjacent to a leading edge of the main blade portion and forms a flap for the main blade portion; wherein a fluid passage is defined between the leading edge of the main blade portion and the leading edge of the secondary blade portion; wherein the main blade portion has a main chord and the secondary blade portion has a secondary chord; and wherein the main chord and the secondary chord form a relative attack angle comprised between 5° and 35°. | 05-19-2016 |
| 20160168997 | WIND TURBINE BLADE HAVING A BOND LINE ADJACENT A SANDWICH PANEL OF THE BLADE | 06-16-2016 |
| 20160177915 | ROTOR BLADE EXTENSION | 06-23-2016 |
| 20160177916 | A BLADE FOR A WIND TURBINE AND A METHOD FOR MANUFACTURING A BLADE FOR A WIND TURBINE | 06-23-2016 |
| 20160201645 | A WIND TURBINE, A WIND TURBINE BLADE, AND A METHOD OF REINFORCING A WIND TURBINE BLADE | 07-14-2016 |
| 20190145269 | CERAMIC COMPONENT FOR COMBUSTION TURBINE ENGINES | 05-16-2019 |
| 20190145375 | RETROFIT WINGLETS FOR WIND TURBINES | 05-16-2019 |
| 20090208340 | Impeller structure of blower - The impeller structure of blower in the present invention mainly includes a hub and an impeller. The hub has a spindle disposed centrally therein. The impeller has a top connection ring, a bottom connection ring, a pressure-retaining ring and a plurality of blades, in which the blades are vertically arranged around the periphery of the hub, an outer edge on a top side of each blade is connected with a top connection ring, an bottom side of the inner side of the blade is connected with a bottom connection ring, the outer side is connected with the pressure-retaining ring, and a plurality of swirl-like ribs are extended outwards from the bottom edge of the periphery of the hub and connected with the bottom connection ring. At least a pressure relief hole is provided between the pressure-retaining ring and the bottom connection ring so that the bottom surface of the impeller is not fully enclosed. Therefore, the pressure relief hole is located on a space between the pressure-retaining ring and the bottom connection ring. When air passes through the pressure relief hole, a pressure effect is generated so as to increase air pressure and air volume of blower and alleviate the chance of turbulence. The pressure-retaining ring also has the effect of reinforcing the blade strength. | 08-20-2009 |
| 20090280013 | Frustoconical centrifugal wheel - An inline centrifugal wheel has a back plate and a hub extending from the back plate. A front plate has a diameter greater than the back plate and is inclined to extend downwardly from a central aperture to its outer perimeter. Blades extend between the back and front plate and have an outer edge extending between the outer edges of the front and back plate. The blades extend tangentially to the central aperture of the front plate. | 11-12-2009 |
| 20100028156 | IMPELLER AND PUMP INCLUDING THE SAME - An impeller includes an impeller body which rotates about a rotation axis, and a vane which is provided at the impeller body. The impeller body receives force asymmetric with respect to the rotation axis in driving and rotation in a fluid in a manner that radially inward fluid force, which is generated due to arrangement of the vane, acts on a predetermined point in a peripheral direction. In the impeller body, a filled space filled, in a fluid, with the fluid is formed. | 02-04-2010 |
| 20120328444 | IMPELLER OF CENTRIFUGAL COMPRESSOR - Interference of a leakage vortex flow generated at the tip end side of the full blade with the leading edge of the splitter blade is avoided and high pressure ratio and enhanced efficiency can be achieved. A throat of am impeller is formed so that a distance from a leading edge of a rear side full blade on the rear side of the rotation direction of the compressor to a front side full blade adjacent to the rear side full blade is minimized, and the leading edge of the splitter blade is placed in a fluid flow streaming along the flow passage between the mutually adjacent full blades, on the downstream side of a leakage vortex line formed to connect the middle location of the throat to the leading edge of the front side full blade. | 12-27-2012 |
| 20140037454 | BLADE BODY, WIND TURBINE AND WIND POWER - A blade comprises a first blade surface, a second blade surface forming the reverse surface of the first blade surface, a primary wind receptor protruding from the front end of the first blade surface in a direction away from the second blade surface and with the back surface formed in a curved shape concave toward the front side in a forward direction, a front edge connected to the front end of the primary wind receptor and the front end of the second blade surface and formed in a curved shape convex toward the forward direction, and a back edge connected to the back end of the first blade surface and the back end of the second blade surface and formed in an acute angle facing the back side of the forward direction. | 02-06-2014 |
| 20140127029 | CENTRIFUGAL FAN IMPELLER STRUCTURE - A centrifugal fan impeller structure includes a hub having multiple blades. The blades extend from a circumference of the hub in a direction away from the hub. Each two adjacent blades define therebetween a flow way, an air outlet and an air inlet. The air outlet and the air inlet are respectively positioned at two ends of the flow way in communication with the flow way. The air outlets are arranged at unequal intervals so as to greatly reduce noise in operation. | 05-08-2014 |
| 20150017008 | WIND TURBINE BLADE HAVING A SHAPED STALL FENCE OR FLOW DIVERTER - A wind turbine blade is described wherein at least one stall fence is provided on the blade surface, where the stall fence is arranged such that it extends at an angle to the chord of the blade. The stall fence acts to re-direct airflow over the blade, to improve wind turbine performance. The stall fence may be a provided towards the blade root end, acting to divert airflow towards the root end of the blade to prevent separation of attached airflow. Additionally or alternatively, the stall fence may be arranged as a flow diverter provided towards the blade tip end, to increase airflow in the tip region for increased performance and/or to disrupt the formation of tip vortices. | 01-15-2015 |
| 20160061214 | IMPELLER AND BLOWER - An impeller is arranged to rotate about a central axis, and includes a disk-shaped portion arranged to extend radially with respect to the central axis, and a plurality of rotor blades arranged along a circumferential direction on one surface of the disk-shaped portion. Each rotor blade has one end arranged at an outer edge portion of the disk-shaped portion, and an opposite end arranged radially inward of the outer edge portion of the disk-shaped portion. The rotor blades include a plurality of first rotor blades each of which includes a first curvature portion and a plurality of second curvature portions. A center of the radius of curvature of the first curvature portion of each first rotor blade is arranged on a first side of the first rotor blade with respect to the circumferential direction. A center of the radius of curvature of each second curvature portion of each first rotor blade is arranged on a second side of the first rotor blade with respect to the circumferential direction. The first curvature portion is arranged radially inward of each second curvature portion. Regarding adjacent ones of the second curvature portions, the radius of curvature of the second curvature portion arranged radially outward is greater than the radius of curvature of the second curvature portion arranged radially inward. | 03-03-2016 |
| 20080206061 | OPTIMIZED AERODYNAMIC AIRFOIL FOR A TURBINE BLADE - Optimized aerodynamic airfoil for a turbine blade When cold and in the uncoated state, the aerodynamic airfoil is substantially identical to a nominal airfoil determined by the Cartesian coordinates X, Y, Z′ given in Table 1, in which the coordinate Z′ is the ratio D/H where D is the distance from the point in question to a reference plane P0, located at the base of the nominal airfoil, and H is the height of this airfoil, measured from said reference plane up to the tip of the blade. The D and H measurements being taken radially with respect to the axis of the turbine whereas the X coordinate is measured in the axial direction of the turbine. | 08-28-2008 |
| 20080213098 | Free-standing turbine blade - There is described a blade for a turbomachine, such as a steam turbine. The blade has a blade tip, which is curved in relation to the blade airfoil profile. The curvature has the shape of a winglet, which is known from aircraft construction. | 09-04-2008 |
| 20080273983 | TURBOMACHINE BLADE - A turbomachine including securing means that extend between the pressure wall and the suction surface and which includes an energy absorbing portion for absorbing energy after impact to the blade by a foreign object. The energy absorbing portion has a catch that provides the blade with an improved resistance to bursting. | 11-06-2008 |
| 20080286107 | Course of leading edges for turbomachine components - The course of the leading edges of turbomachine components, such as rotor blades and stator vanes is defined mathematically exactly and repeatedly as well as aerodynamically advantageously by the respective axial coordinate in the direction of the machine axis in relation to the blade height in percent, extending from the blade tip as per equation (1): | 11-20-2008 |
| 20090004019 | Axial Flow Fan - An axial flow fan is provided having an airfoil shape that improves efficiency of the axial flow fan and increases the structural strength and workability/formability of the thin trailing edge portion. The axial flow fan includes a blade having a suction surface, a pressure surface, and a trailing edge surface; the suction surface has the same in shape as a predetermined airfoil including an NACA-series airfoil; a trailing edge portion on the pressure surface is different in shape from the predetermined airfoil. A feature is that the blade trailing edge portion including the trailing edge portions on the oppositely facing pressure and suction surfaces and the trailing edge, has a thickness greater than that of a trailing edge portion of the predetermined airfoil and strength equaling or exceeding a predetermined strength. | 01-01-2009 |
| 20090022595 | STEAM TURBINE AND ROTATING BLADE - A blade is mountable to a disc. The blade comprises a blade platform and a blade root extending from the blade platform. The blade root comprises a first hook and a second hook, a first neck between the first hook and the blade platform, and a second neck between the first hook and the second hook. Each hook comprises a contact surface and a non-contact surface. An angle between each contact surface and each non-contact surface is optimized to reduce local stresses. | 01-22-2009 |
| 20090022596 | Steam Turbine Rotating Blade - A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute. | 01-22-2009 |
| 20090035145 | Airfoil shape for a turbine bucket and turbine incorporating same - Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z′ set forth Table I wherein X and Y values are in inches and the Z′ values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z′ values by the height of the airfoil in inches and adding the radius of the airfoil base. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.0.060 inches in directions normal to the surface of the airfoil. | 02-05-2009 |
| 20090074582 | METHOD FOR JOINING METAL COMPONENTS AND DEVICE FOR EXECUTION OF AN INDUCTIVE LOW OR HIGH-FREQUENCY PRESSURE WELDING METHOD - The present technology concerns one or more methods for joining of metal components especially components of a gas turbine, in which joining of the corresponding joining surfaces of the components occurs by means of an inductive low or high-frequency pressure welding and in which, before heating and joining of the components by means of inductive low or high-frequency pressure welding, sputter etching of the joining surfaces is carried out. The present technology also concerns a device for execution of an inductive low or high-frequency pressure welding method for joining the metal components, especially components of a gas turbine, with at least one induction generator and at least one inductor, as well as a component produced with the method according to the present technology. | 03-19-2009 |
| 20090097982 | COMPRESSOR TURBINE BLADE AIRFOIL PROFILE - A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 04-16-2009 |
| 20090136352 | TURBOMACHINE BLADE - The turbomachine blade has ribs formed in the vicinity of the trailing edge. Over the major fraction of the trailing edge ( | 05-28-2009 |
| 20090142195 | Shank shape for a turbine blade and turbine incorporating the same - A turbine includes a turbine wheel having a plurality of buckets, each of the buckets including a bucket airfoil, a bucket dovetail to connect the bucket to a turbine wheel and a shank shape to connect the airfoil to the bucket dovetail, the shank having an uncoated nominal profile including a concave, pressure side, substantially in accordance with Cartesian values of X, Y and Z′ set forth in Table I wherein the Z′ values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z′ values by shank height in inches, and a convex, suction side, substantially in accordance with Cartesian values of X, Y and Z′ set forth in Table II wherein the Z′ values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z′ values by the shank height in inches. The X and Y are distances in inches which, when connected by smooth continuing arcs, define a shank profile section at each distance Z, the profile sections being joined smoothly with one another to form a complete shank shape. | 06-04-2009 |
| 20090148299 | AIRFOIL LEADING EDGE SHAPE TAILORING TO REDUCE HEAT LOAD - An airfoil includes a leading edge surface that includes a non-continuous curvature distribution. A stagnation region of the airfoil includes a curvature larger than adjacent segments to reduce heat transfer into the airfoil. The reduced curvature in the stagnation region is surrounded by the adjacent segments with larger curvatures to tailor the airfoil surface to provide a desired balance between heat transfer properties and aerodynamic performance. | 06-11-2009 |
| 20090155082 | METHOD TO MAXIMIZE RESONANCE-FREE RUNNING RANGE FOR A TURBINE BLADE - An airfoil for a gas turbine engine component such as a turbine blade is tuned to move its natural frequency outside of a frequency which will be excited during expected speed range of an associated gas turbine engine. The airfoil is tuned about locations of the anti-nodes in an original airfoil design. The tuning affects only the interfered frequency. | 06-18-2009 |
| 20090169390 | ADAPTIVE ROTOR BLADE FOR A WIND TURBINE - A rotor blade for a wind turbine is provided, the rotor blade having a first module of a first type and a second module of a second type, each module having a distal end and a proximal end, wherein the distal end of the first module and the proximal end of the second module are adapted to be attached to each other to form at least a part of the rotor blade, wherein at least one of said first and second modules is selected from a set of at least two differently shaped modules of the same type. Further, a kit of parts for adapting a wind turbine to a site constraint is provided, the kit of parts comprising several modules for assembling a modular rotor blade, wherein the several modules comprise at least one root-type module and at least one tip-type module and at least one further module of the root-type or the tip-type, wherein the at least one further module has a different shape compared to the other module of the same type. Finally a method for adapting a rotor of a wind turbine to a site constraint is provided. | 07-02-2009 |
| 20090169391 | Axial-Flow Fluid Machine Blade - An axial-flow fluid machine blade which achieves reduction of the frictional loss of the blade and provision of a high surge-resistant property is provided. An axial-flow fluid machine blade | 07-02-2009 |
| 20090220346 | Radial Compressor Rotor - A radial compressor rotor is provided for stabilizing the flow behavior of a delivery gas, consisting of a wheel disc and blades arranged uniformly in the circumferential direction, wherein the generatrix of the surface of the blades is designed as a curved line at least in a curved section, such that the surface is curved in two directions in this section. | 09-03-2009 |
| 20090257878 | LOW EXHAUST LOSS TURBINE AND METHOD OF MINIMIZING EXHAUST LOSSES - Disclosed herein is a method of minimizing losses in a multiple-last-stage bucket turbine. The method includes, determining an inlet flow available for the multiple-last-stage bucket turbine, and selecting multiple last-stage buckets from a set of pre-designed last-stage buckets. The multiple last-stage buckets having inlet flows different from one another that when combined match the inlet flow available with a lower total exhaust loss than from multiple same sized last-stage buckets from the set of pre-designed last-stage buckets. | 10-15-2009 |
| 20090257879 | RUNNER VANE FOR AXIAL-FLOW HYDRAULIC MACHINERY - A camber line in a radial section of a runner vane has a curved part extending near the tip of the runner vane is convex toward the front surface of the runner vane. The runner vane is formed in a shape meeting a condition expressed by: ρs<ρp, where ρs is the radius of curvature of the back surface of the runner vane and ρp is the radius of curvature of the front surface of the runner vane. The runner vane of this shape suppresses flows toward the tip thereof to moderate the variation of flow velocity in the turning direction. Consequently, loss can be reduced without impeding the recover of pressure in a draft tube. | 10-15-2009 |
| 20090269204 | AIRFOIL SHAPE FOR A TURBINE BUCKET - A turbine bucket including an airfoil, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 as contained herein wherein the Z values are non-dimensional values from approximately 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by substantially smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined substantially smoothly with one another to form a complete airfoil shape. | 10-29-2009 |
| 20090274558 | HP TURBINE BLADE AIRFOIL PROFILE - A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 11-05-2009 |
| 20090304516 | PLATFORM MATE FACE CONTOURS FOR TURBINE AIRFOILS - Gas turbine engine components having an airfoil extending outwardly of a platform are mounted in adjacent relationship, and such that cooling air flows outwardly of a gap between mating faces of the platforms. The location of localized hot spots is identified on the platform, and the mating faces are designed to provide cooling air through the gap to address these hot spots. A suction side edge of the platform has a curved portion extending inwardly into the platform, and the pressure side has a curved portion bulging outwardly away from the airfoil. When these two portions on adjacent components mate, a gap is provided between two platforms that provides leakage cooling air to the hot spot. | 12-10-2009 |
| 20090304517 | Component structure - Within hollow structures, such as blade structures in a gas turbine engine, traditionally rigid girdered reinforcement has been utilised to define structure and shape. Such rigid definition can inhibit utilisation of damping fillers within the hollow structure. By providing a web former comprising spaced bond areas suspended upon angled interconnecting membranes a hollow structure is achieved which is flexible and can be used in conjunction with a damping filler to achieve desired performance. The web former supports skins defining the shape and takes some load such that the damping filler does not separate within the hollow structure. | 12-10-2009 |
| 20090324415 | AIRFOIL CORE SHAPE FOR A TURBINE NOZZLE - An article of manufacture includes an object having an airfoil core shape. The airfoil core shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1 where X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape. | 12-31-2009 |
| 20100021306 | Steam Turbine Rotating Blade - A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute. | 01-28-2010 |
| 20100028155 | Turbine Rotor - An object of the present invention is to provide a turbine rotor with high reliability of strength. The turbine rotor includes two rotors which are connected at the butted portions of the rotors via a weld without forming penetration beads. Specifically, the turbine rotor includes a rotor for low pressure, a rotor for high pressure, and a center hole formed at a center portion of the turbine rotor. The rotors for low pressure and for high pressure are integrated together into a steam turbine rotor by welding respective ends of the rotors to each other. The respective ends of the rotors are in contact with each other via at least two contact faces in a radial direction and an axial direction of the turbine rotor. At least parts of the respective ends are welded together. | 02-04-2010 |
| 20100054945 | Aerofoil - Composite aerofoils for gas turbine engines are commonly provided with a metal protection strip along the leading edge, to prevent erosion of the leading edge in use and to protect against impacts from foreign bodies. A problem with such strips is that they can cause serious damage to other parts of the engine if they become detached from the aerofoil. The invention provides an aerofoil having such a protection strip, characterised in that the protection strip includes one or more weakening features to reduce the ability of the protection member to withstand a compressive force applied along its length. The weakening features encourage the protection member to break up under impact, or if it becomes detached from the aerofoil, so that damage to other parts of the engine is minimised. | 03-04-2010 |
| 20100068063 | METHODS AND APPARATUS FOR ASSEMBLING GAS TURBINE ENGINES - A method of assembling a rotor assembly is provided. The method comprises forming at least one channel in a dovetail portion of at least one rotor blade assembly, wherein the rotor blade assembly includes an airfoil extending outwardly from the dovetail portion, inserting a sealing assembly within the at least one channel of the dovetail portion, and coupling the at least one rotor blade assembly to a rotor disk using the dovetail portion such that at least a portion of the sealing assembly is between the dovetail portion and the rotor disk. | 03-18-2010 |
| 20100068064 | TRANSONIC AIRFOIL AND AXIAL FLOW ROTARY MACHINE - Sectional profiles close to a tip | 03-18-2010 |
| 20100080708 | SCALLOPED SURFACE TURBINE STAGE WITH TRAILING EDGE RIDGES - An engine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Extending from a surface of the platforms is a trailing edge ridge structure which adjoins the pressure sides, suction sides, and trailing edges of the airfoils with their respective platforms. | 04-01-2010 |
| 20100135812 | TURBINE BLADE APPARATUS - A gas turbine airfoil is disclosed. The gas turbine airfoil includes a root section, a separate extension section attached to the root section, and a joint disposed between the root section and the extension section, the joint including at least one of a mechanical interlock and a metallurgical bond. | 06-03-2010 |
| 20100150727 | ROTOR BLADE FOR A GAS TURBINE - A rotor blade ( | 06-17-2010 |
| 20100158691 | Component and Method for Joining Metal Elements - A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements. | 06-24-2010 |
| 20100202889 | METHOD FOR PRODUCING A LIGHTWEIGHT TURBINE BLADE - A method for producing a lightweight turbine blade for a gas turbine is disclosed. In an embodiment, the method includes casting of a blade element with a blade wall and at least one cavity enclosed by the blade wall. The blade wall is at least partially reduced in thickness by machining after the casting. This provides a method for producing a blade element, in which the wall thickness of the blade wall can be adapted to the mechanical load of the blade element, and the weight of the blade element can be reduced at the same time. | 08-12-2010 |
| 20100215503 | TRANSONIC BLADE - A transonic blade is provided that operates in a flow field where flow has a transonic speed or higher in an axial-flow rotating machine and that concurrently achieves a reduction in shock loss and in the local stress of the blade. | 08-26-2010 |
| 20100226778 | METHOD OF MANUFACTURING AN AEROFOIL - A method of manufacturing an aerofoil structure capable of being diffusion bonded and superplastically formed to create a substantially hollow cavity within the aerofoil structure, the method comprising: providing two metallic panels ( | 09-09-2010 |
| 20100232970 | FAN ROTATING BLADE FOR TURBOFAN ENGINE | 09-16-2010 |
| 20100239425 | NICKEL-BASE ALLOY FOR TURBINE ROTOR OF STEAM TURBINE AND TURBINE ROTOR OF STEAM TURBINE USING THE SAME - A nickel (Ni)-base alloy for a turbine rotor of a steam turbine containing, in mass %, carbon (C): 0.01% to 0.15%, chromium (Cr): 18% to 28%, cobalt (Co): 10% to 15%, molybdenum (Mo): 8% to 12%, aluminum (Al): 0.5% to less than 1.5%, titanium (Ti): 0.7% to 3.0%, and boron (B): 0.001% to 0.006%, the balance being nickel (Ni) and unavoidable impurities. | 09-23-2010 |
| 20100247318 | BUCKET FOR THE LAST STAGE OF A STEAM TURBINE - A turbine bucket including a bucket airfoil having an airfoil shape is provided. The airfoil shape has a nominal profile according to the tables set forth in the specification. The X and Y coordinate are smoothly joined by an arc of radius R defining airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. | 09-30-2010 |
| 20100247319 | HIGH EFFICIENCY LAST STAGE BUCKET FOR STEAM TURBINE - A turbine bucket including a bucket airfoil having an airfoil shape is provided. The airfoil shape has a nominal profile according to the tables set forth in the specification. The X and Y coordinate are smoothly joined by an arc of radius R defining airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The airfoil profile results in improved efficiency and airfoil loading capability. | 09-30-2010 |
| 20100254816 | Exhaust Gas Turbocharger - A turbocharger for or in a motor vehicle has a rotor with an intermediate blade disposed between two primary blades. The intermediate blade, at least in some regions, has an angular progression that differs from the primary blades. | 10-07-2010 |
| 20100284815 | COMPOUND VARIABLE ELLIPTICAL AIRFOIL FILLET - A gas turbine engine blade or vane having a first platform, an airfoil, and a compound fillet extending about a region where the airfoil joins the first platform is disclosed. The compound fillet has a first conic surface and a second conic surface, with the first conic surface tangent to the airfoil and to an offset platform surface and the second conic surface tangent to the first conic surface and the first platform. The two conic surfaces are of different sizes, with different radii, and the conic surfaces can vary in size about the periphery of the joint between the airfoil and the first platform. | 11-11-2010 |
| 20100290915 | MULTI-STAGE PUMP ROTOR FOR A TURBOMOLECULAR PUMP - A multi-stage pump rotor ( | 11-18-2010 |
| 20100296938 | ROTOR OF ROTATING MACHINE AND METHOD OF MANUFACTURING THE ROTOR - A turbine rotor which is composed by connecting Ni-based alloy and heat resisting steel such as 12-Cr steel by welding to be able to ensure strength of welded parts and can be used under steam conditions of 700° C. class and method of manufacturing the rotor are also provided. The rotor of the rotating machine into which working fluid of 650° C. or higher is introduced, the rotor being composed of a plurality of members connected by welding such that material of each member is different in accordance with temperature of working fluid which flows contacting the members, wherein the first member(s) is formed from Ni-based alloy having mean linear expansion coefficient of 12.4×10 | 11-25-2010 |
| 20100322774 | Airfoil Having an Improved Trailing Edge - An airfoil ( | 12-23-2010 |
| 20100329874 | HP TURBINE BLADE AIRFOIL PROFILE - A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 12-30-2010 |
| 20110014055 | GAS DYNAMIC COLD SPRAYING OF OXIDE-CONTAINING PROTECTIVE LAYERS - The present invention relates to a method for producing a coating on a gas turbine component, in which particles at least of parts of a material to be applied as coating are accelerated by means of kinetic gas dynamic cold spraying in a spray jet onto the surface ( | 01-20-2011 |
| 20110014056 | BLADE WITH NON-AXISYMMETRIC PLATFORM - A blade for a turbomachine impeller including an airfoil and at least one platform at one end of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring, the platform surface having a suction surface profile and a pressure surface profile respectively along the suction surface and the pressure surface. In the blade, the pressure surface profile including a pressure surface recessed part is located axially in an upstream half of the airfoil. Due to this configuration, efficiency of the blade is improved. | 01-20-2011 |
| 20110020126 | MODULAR ROTOR BLADE FOR A POWER-GENERATING TURBINE AND A METHOD FOR ASSEMBLING A POWER-GENERATING TURBINE WITH MODULAR ROTOR BLADES - A modular rotor blade for a power generating turbine allows simple replacement of individual rotor blade sections in case of damage to or malfunction of a section. The modular rotor blade includes at least two rotor blade sections, wherein each rotor blade section includes at least one connecting part having at least one conical opening. The connecting parts of adjacent rotor blade sections rest against each other such that the conical openings of the connecting parts are aligned with each other and form a continuous conical connecting opening. Receiving elements for receiving tensioning elements are arranged at the smaller diameter end of the conical connecting opening. A conical bolt corresponding to the continuous conical connecting opening is arranged therein, and at least one tensioning element passes through the conical bolt and tensions the conical bolt against the receiving element. | 01-27-2011 |
| 20110020127 | Component Comprising Overlapping Weld Seams and Method for the Production Thereof - A turbine blade or vane with a platform and two overlapping weld seams, each weld seam having a width, is provided. An overlapping region of the two weld seams is 40% to 60% of the width of one weld seam. The weld seams run parallel or perpendicularly to the platform of the turbine blade or vane. Further, a method for welding a turbine blade or vane is provided. | 01-27-2011 |
| 20110020128 | WIND TURBINE BLADE WITH AN AUXILIARY AIRFOIL - A blade for a rotor of a wind turbine having a substantially horizontal rotor shaft, the rotor comprising a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade comprises a main blade part having a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge. The profiled contour generates a lift when being impacted by an incident airflow. The profiled contour is divided in the radial direction into a root region with a substantially circular or elliptical profile closest to the hub, the substantially circular or elliptical profile having a diameter, an airfoil region with a lift generating profile furthest away from the hub, and a transition region between the root region and the airfoil region. The profile of the transition region gradually changes in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region. The blade further comprises a first auxiliary airfoil having a first pressure side and a first suction side as well as a first chord extending between a first leading edge and a first trailing edge. The first chord has a length that is 75% or less of the diameter of the substantially circular or elliptical profile in the root region and the first auxiliary airfoil is arranged so that it extends in the radial direction along at least a part of the root region of the main blade part with a distance there between. | 01-27-2011 |
| 20110033303 | TURBOMACHINE COMPRESSOR ROTOR INCLUDING CENTRIPETAL AIR BLEED MEANS - A turbomachine compressor rotor including at least two blade-carrying disks mounted on a common axis and connected together by a wall forming a substantially cylindrical surface of revolution, and a centripetal air bleed mechanism including air passages passing through the wall and radial fins for deflecting a stream of air leaving the passages in the wall, the fins being carried by one of the disks and being substantially in radial alignment with the passages through the wall. | 02-10-2011 |
| 20110097210 | TURBINE AIRFOIL - An airfoil is provided and includes a pressure surface and a suction surface. Radially corresponding surface characteristics of the pressure and suction surfaces at a spanwise local portion of the airfoil are formed to cooperatively define at least one of a camber line and a thickness distribution plot of the airfoil as having a radius of curvature with at least two sign changes. The number of sign changes decreases along a radial dimension of the airfoil measured from the spanwise local portion. | 04-28-2011 |
| 20110135482 | TIP VORTEX CONTROL - A rotor blade for a gas turbine engine includes an attachment and an airfoil. The airfoil has a stagger angle, a base region, a transition region and a tip region. The stagger angle changes as the airfoil extends between the attachment and a tip. The base region is disposed adjacent to the attachment. The transition region is located between the base and the tip regions. A rate of the change of the stagger angle in the transition region is greater than a rate of the change of the stagger angle in the base region. The rate of the change of the stagger angle in the transition region is greater than a rate of change of the stagger angle in the tip region. | 06-09-2011 |
| 20110150658 | ROTATING HARDWARE AND PROCESS THEREFOR - A process of fabricating rotating hardware and rotating hardware formed thereby. The process includes fabricating at least two members that together define at least two portions of a component. Each member has an interface surface at which the members can be joined to locate a first of the portions in a radially outward direction from a second of the portions. The members are joined together so that the interface surfaces thereof form a joint interface located within a pad region that has a axial thickness that is greater than a contiguous region of the component. The joint interface is not perpendicular to the axial and radial directions of the component. The pad region is defined by embossments that are offset from each other in the radial direction of the component so as to partially but not completely overlap each other in the axial direction of the component. | 06-23-2011 |
| 20110150659 | AIRFOIL FOR A COMPRESSOR BLADE - The present disclosure provides an improved second stage airfoil for a compressor blade having a unique chord length (CD), a stagger angle (γ), and camber angle (Δβ). The stagger angle (γ) and camber angle (Δβ) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight. | 06-23-2011 |
| 20110164984 | BLADE SECTION FOR A WIND TURBINE BLADE - A blade section for a wind turbine blade, the blade section extending along a longitudinal axis and having at least a first end, the blade section comprising a main blade section with a contour having an outer surface. The main blade section at the first end is provided with a number of connection elements, each connection element being pivotally engaged with the main blade section about a rotational axis. Each of the connection elements being provided with a joining means for anchoring each of the connection element to another blade section. The joining means of each of the number of connection elements is arranged in a distance from the rotational axis. | 07-07-2011 |
| 20110200442 | TURBINE BLADE WITH IMPROVED AERODYNAMIC PERFORMANCE - One or more protuberances are provided on a turbine blade on its suction side in a vicinity of its trailing edge. The protuberances serve to reduce a separation zone in a vicinity of a blade surface that is responsible for disturbances that affect efficiency of the turbine. | 08-18-2011 |
| 20110206525 | TURBINE ROTOR AND MANUFACTURING METHOD OF TURBINE ROTOR - There are provided a turbine rotor having suitable strength and toughness without causing soaring manufacturing costs and prolonged manufacturing time, and a manufacturing method of the turbine rotor. In a turbine rotor constructed by welding a rotor member for high temperature made of high Cr steel, and a rotor member for low temperature made of low Cr steel, the high temperature rotor member is formed from high Cr steel of which the nitrogen content is 0.02% or higher by mass %, and a filler material which welds the high temperature rotor member and the low temperature rotor member together is a 9% Cr-based filler material of which the nitrogen content is 0.025% or lower by mass %. | 08-25-2011 |
| 20110236214 | HIGH PRESSURE TURBINE BLADE AIRFOIL PROFILE - A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 09-29-2011 |
| 20110243747 | HIGH PRESSURE TURBINE VANE AIRFOIL PROFILE - A two-stage high pressure turbine includes a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 10-06-2011 |
| 20110243748 | HIGH PRESSURE TURBINE BLADE AIRFOIL PROFILE - A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 10-06-2011 |
| 20110243749 | GAS TURBINE ENGINE WITH NON-AXISYMMETRIC SURFACE CONTOURED ROTOR BLADE PLATFORM - A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour. | 10-06-2011 |
| 20110250072 | REPLACEMENT PART FOR A GAS TURBINE BLADE OF A GAS TURBINE, GAS TURBINE BLADE AND METHOD FOR REPAIRING A GAS TURBINE BLADE - A replacement part for a gas turbine blade is disclosed. The replacement part is designed to replace a removed portion of the blade, the portion including a section of the blade tip and a section of the leading edge and/or the trailing edge, and the replacement part having at least one joining side with which it can be brought to contact with the blade that is reduced by the removed portion and joined therewith. The joining side has at least one section, the cross-section of which is U-shaped. | 10-13-2011 |
| 20110255984 | SYSTEM AND METHOD FOR REDUCING GRAIN BOUNDARIES IN SHROUDED AIRFOILS - A turbine bucket includes an airfoil and a shroud. The shroud includes first and second bearing surfaces, and the first and second bearing surfaces each comprise a single grain structure. A method for forming a turbine bucket includes orienting a mold vertically, wherein the mold includes a first portion that defines a shank, a second portion connected to the first portion that defines an airfoil, and a third portion connected to the second portion that defines a shroud, wherein the third portion includes first and second sides, and wherein the first portion is higher than the second portion and the second portion is higher than the third portion. The method further includes flowing a molten metal into the mold and selectively growing large single grains in at least one of the first or second sides. | 10-20-2011 |
| 20110262279 | COMPRESSOR TURBINE BLADE AIRFOIL PROFILE - A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 10-27-2011 |
| 20110299990 | TURBINE AIRFOIL WITH OUTER WALL THICKNESS INDICATORS - A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip. | 12-08-2011 |
| 20110318188 | AXIAL CENTRIFUGAL COMPRESSOR WITH SCALABLE RAKE ANGLE - A mobile wheel for a centrifugal or axial centrifugal compressor for a turbine engine, that includes a base on which a plurality of vanes are attached at their feet and extend between a leading edge and a trailing edge, the trailing edge being inclined at the base of the vane by a slope angle relative to the middle plane extending through the base thereof in the rotation direction of the compressor. The trailing edge has at the head of the vane a slope angle smaller than the slope angle at the vane base. | 12-29-2011 |
| 20120027606 | ROTOR ASSEMBLY DISK SPACER FOR A GAS TURBINE ENGINE - A disk spacer for a gas turbine engine includes a rim, a bore, a web and a load path spacer. The web extends between the rim and the bore. The load path spacer is positioned between the rim and the bore. | 02-02-2012 |
| 20120045342 | AIR TURBINE STARTER TURBINE BLADE AIRFOIL - A blade profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Y-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, the Y-coordinate is the axial direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip. | 02-23-2012 |
| 20120057981 | TURBINE BLADE AIRFOIL - An airfoil comprises an external surface formed in substantial conformance with a plurality of cross sections. Each of the cross sections has an axial chord and an offset at a corresponding fractional span as set forth in Table 2. Each of the cross sections is described by a set of Cartesian coordinates defined at the corresponding fractional span as set forth in Table 4. | 03-08-2012 |
| 20120057982 | TURBINE VANE AIRFOIL - An airfoil comprises an external surface formed in substantial conformance with a plurality of cross sections. Each of the cross sections has an axial chord and an offset at a corresponding fractional span as set forth in Table 1. Each of the cross sections is described by a set of Cartesian coordinates defined at the corresponding fractional span as set forth in Table 3. | 03-08-2012 |
| 20120063908 | TURBINE VANE NOMINAL AIRFOIL PROFILE - A turbine vane for a turbine machine comprising an intermediate section having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a radial distance along a stacking axis that is normal to a centerline of the turbine machine and contain the X and Y values with Z value beginning at innermost aerodynamic point and the Z values represent a radial height of the vane and the X and Y values define the nominal airfoil profile at each radial height Z. | 03-15-2012 |
| 20120070297 | AFT LOADED AIRFOIL - An example airfoil array includes an airfoil array configured to rotate within a turbomachine at a different rotational speed than a fan within the turbomachine. The airfoil array includes a first airfoil that is circumferentially spaced a distance from an adjacent second airfoil. A ratio of the distance to an axial chord length of the first airfoil is less than 1.3. An uncovered turning angle of the first airfoil is greater than 15 degrees. | 03-22-2012 |
| 20120070298 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE, IN PARTICULAR FOR A ROTARY WHEEL OF THE SECOND STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P | 03-22-2012 |
| 20120082552 | TURBINE ROTOR - A turbine rotor of a turbine includes a hub that serves as an axis of rotation, and a plurality of turbine blades. The turbine blades each have a line extending along a shroud-side edge of the turbine blade from the inlet to the outlet as a shroud line. The shroud line includes an entrance-side shroud line La that makes a small change from the inlet toward the outlet in a blade angle with respect to the axis of rotation, a center shroud line Lb that extends from the outlet side of the entrance-side shroud line La and makes a greater change than that of the entrance-side shroud line La, and an exit-side shroud line Lc that extends from the outlet side of the center shroud line Lb to the outlet and makes a smaller change than that of the center shroud line Lb. | 04-05-2012 |
| 20120087800 | CENTRIFUGAL IMPELLER FOR A COMPRESSOR - A centrifugal impeller for a compressor, through which a fluid is to pass. The impeller includes blades each having a leading edge and a trailing edge, the rotation of the impeller sucking fluid in through the front of the impeller, the fluid leaving the impeller via its outer periphery, the trailing edges of the blades being such that in a radial section plane intersecting the trailing edges of the blades, they are curved in the direction opposite to the direction of rotation of the impeller, and the trailing edge portions of the blades are redirected in the direction of rotation of the impeller to form respective end fins serving to deflect the flow of the fluid by redirecting it radially. | 04-12-2012 |
| 20120107126 | WIND POWER GENERATOR - This wind power generator comprises: a nacelle that houses a generator; a tower, the top end section thereof being connected to the nacelle and the bottom end section being fastened to a base section; and a rotor that is located on the downwind side of the nacelle during normal operation, and that by receiving the force of the wind and rotating, drives the generator. The rotor has a hub that is supported such that it can rotate, and a plurality of blades that are arranged such that they extend radially from the hub. The blades, when not loaded, are pre-bent blades that are formed such that the middle section of each blade is curved outward with respect to a straight line that connects the root end section of the blade that is attached to the hub and the tip end section on the outer diameter side of the rotor, with a specified coning angle being applied to the blade. | 05-03-2012 |
| 20120148412 | FATIGUE RESISTANT CAST TITANIUM ALLOY ARTICLES - Articles that are cast from a particular titanium alloy can achieve a relatively high fatigue strength. The titanium alloy is an (α+β) titanium alloy that has a nominal composition of about 5.5 to about 6.63 mass percent aluminum, about 3.5 to about 4.5 mass percent vanadium, about 1.0 to about 2.5 mass percent chromium, maximum of 0.50 mass percent iron, about 0.15 to about 0.25 mass percent oxygen, about 0.06 to about 0.12 mass percent silicon, and at least 80 mass percent titanium or the balance titanium (Ti) with the exception of some allowable impurities. In one exemplary application, this titanium alloy may be used to cast a turbocharger compressor wheel. | 06-14-2012 |
| 20120156046 | TURBINE ROTOR FOR AIR CYCLE MACHINE - A turbine rotor for an Air Cycle Machine includes a hub with a multiple turbine blades which extend therefrom, each of the multiple of turbine blades defined by a set of coordinates. | 06-21-2012 |
| 20120224972 | METHOD AND DEVICE FOR PRODUCING AN INTEGRALLY BLADED ROTOR AND ROTOR PRODUCED BY MEANS OF THE METHOD - A method for producing an integrally bladed rotor, in particular a gas turbine rotor, by means of joining, comprises the following steps:—Providing a blade ( | 09-06-2012 |
| 20120244005 | HIGH CAMBER COMPRESSOR ROTOR BLADE - A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region (“S | 09-27-2012 |
| 20120263599 | IMPELLER AND TURBOMACHINERY INCLUDING THE IMPELLER - An impeller includes a hub plate and a plurality of blades circumferentially disposed at intervals on one surface side of the hub plate. Each blade has a shape formed by piling up a plurality of blade sections in a blade height-wise direction of each blade in a reference impeller in which the hub plate intersects with the blades and which includes a linear element blade in the blade height-wise direction so as to form a curvilinear element blade. In piling up the blade sections, amounts of tangential lean and sweep to be applied to the blade sections are increased as it goes from an end face of at least one of a hub plate side end and a counter hub plate side end toward a span intermediate part of the blade. | 10-18-2012 |
| 20120275922 | HIGH AREA RATIO TURBINE VANE - A vane for a turbine engine comprises an airfoil section, an inner platform and an outer platform. The airfoil section comprises pressure and suction surfaces extending from a leading edge to a trailing edge. The inner platform is attached to the airfoil section along an inner flow boundary, where the inner flow boundary extends from an upstream inlet region of the vane to a downstream outlet region of the vane. The outer platform is attached to the airfoil section along an outer flow boundary, where the outer flow boundary extends from the inlet region to the outlet region. An area ratio of the outlet region to the inlet region is greater than 2.4. | 11-01-2012 |
| 20120294722 | HYBRID FLOW BLADE DESIGN - Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution (“s/t distribution”) across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions. | 11-22-2012 |
| 20120308392 | Ceramic-Based Tip Cap for a Turbine Bucket - A turbine bucket may generally include an airfoil formed from a metal-based material. The airfoil may include a base and a tip disposed opposite the base. The airfoil may also include a pressure side wall and a suction side wall extending between a leading edge and a trailing edge. Additionally, the turbine bucket may include a tip cap disposed between the pressure side wall and the suction side wall. The tip cap may be formed from a ceramic matrix composite material. | 12-06-2012 |
| 20130011266 | FAN STAGGER ANGLE FOR DIRT REJECTION - A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extend from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge. The chord forms a stagger angle α with the axis, and the stagger angle α is less than 15° at a position along the propulsor blade that is within an inboard 20% of the span. | 01-10-2013 |
| 20130039771 | TURBOMACHINE COMPONENT HAVING AN AIRFOIL CORE SHAPE - A turbomachine component includes a turbine stator nozzle member having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil core shape. | 02-14-2013 |
| 20130064671 | AIRFOIL SHAPE FOR TURBINE BUCKET AND TURBINE INCORPORATING SAME - A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape. | 03-14-2013 |
| 20130071249 | AIRFOIL SHAPE FOR TURBINE BUCKET AND TURBINE INCORPORATING SAME - A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0% to 100% convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches and adding the radius of the airfoil base, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape. | 03-21-2013 |
| 20130108450 | TURBINE BUCKET PLATFORM LEADING EDGE SCALLOPING FOR PERFORMANCE AND SECONDARY FLOW AND RELATED METHOD | 05-02-2013 |
| 20130108451 | TURBINE BUCKET ANGEL WING FEATURES FOR FORWARD CAVITY FLOW CONTROL AND RELATED METHOD | 05-02-2013 |
| 20130108452 | TURBOMACHINE BLADE WITH TIP FLARE | 05-02-2013 |
| 20130136606 | TURBINE BUCKET AIRFOIL PROFILE - A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
| 20130136607 | TURBINE NOZZLE AIRFOIL PROFILE - The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
| 20130136608 | TURBINE BUCKET AIRFOIL PROFILE - The present application provides a turbine bucket including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
| 20130136609 | TURBINE NOZZLE AIRFOIL PROFILE - A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
| 20130136610 | TURBINE BUCKET AIRFOIL PROFILE - A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
| 20130136611 | TURBINE BUCKET AIRFOIL PROFILE - A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
| 20130164140 | AIRFOILS INCLUDING COMPLIANT TIP - An airfoil, a fan assembly and an engine include at least one airfoil including a root portion, a body portion and a tip portion. The body portion is configured extending radially outward from the root portion and the tip portion is configured extending radially outward from the root portion and the body portion. The airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil including a compliant tip at the tip portion. The compliant tip extending along at least a portion of the tip portion in a chord-wise direction and a span-wise direction. The compliant tip is configured to provide wave propagation along the tip portion such that critical strain proximate the tip portion and the trailing edge is reduced during a foreign object impact. | 06-27-2013 |
| 20130170997 | Gas Turbine Nozzle with a Flow Fence - The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow fence extending from the leading edge to the trailing edge. | 07-04-2013 |
| 20130170998 | IMPELLER TUBE ASSEMBLY - An attenuation bracket is provided and includes an annular body having an annular attenuation arm defining first through-holes and an annular base defining second through-holes. A cross-section of the attenuation arm includes a flange, a connector opposite the flange and a curvilinear section extending between the flange and the connector. A cross-section of the base includes a first side corresponding with the flange and a second side opposite the first side and corresponding with the connector. The second side is connectable with the connector such that each of the first through-holes is defined in positional alignment with a corresponding one of the second through-holes. | 07-04-2013 |
| 20130177430 | SYSTEM AND METHOD FOR REDUCING STRESS IN A ROTOR - A system for reducing stress in a rotor includes a rotor body, a bore extending axially through the rotor body, and a plurality of impeller vanes radially disposed on the rotor body. Each impeller vane includes a first end proximate to the bore, and an undercut feature at the first end of each impeller vane removes a portion of each impeller vane proximate to the bore. The present invention may also include a method for reducing stress in a rotor that includes machining an undercut feature at a first end of a plurality of impeller vanes disposed on a rotor body. | 07-11-2013 |
| 20130236318 | FABRICATED TURBINE AIRFOIL - The invention provides an apparatus and method for combining materials having different thermal and mechanical properties into an article, such as a gas turbine bucket, which includes a first section, a second section, and a third section; wherein the first section provides structural support for the remaining sections, the second section is integrally joined with the first section, and the third section connects the first and second sections. | 09-12-2013 |
| 20130259696 | VERTICAL AXIS WIND TURBINE AIRFOIL - A vertical axis wind turbine airfoil is described. The wind turbine airfoil can include a leading edge, a trailing edge, an upper curved surface, a lower curved surface, and a centerline running between the upper surface and the lower surface and from the leading edge to the trailing edge. The airfoil can be configured so that the distance between the centerline and the upper surface is the same as the distance between the centerline and the lower surface at all points along the length of the airfoil. A plurality of such airfoils can be included in a vertical axis wind turbine. These airfoils can be vertically disposed and can rotate about a vertical axis. | 10-03-2013 |
| 20130272887 | HIGH PRESSURE TURBINE VANE AIRFOIL PROFILE - A high pressure turbine includes a vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 10-17-2013 |
| 20130287579 | BLADE OF A TURBOMACHINE, HAVING PASSIVE BOUNDARY LAYER CONTROL - A blade of a turbomachine is disclosed. A contour variation is provided on the suction side of the blade, where the contour variation has a negative step as viewed in a direction of flow. The step has a stepped surface extending perpendicularly to a contour of the suction side and the contour variation has a tangential surface which leads upstream tangentially on the contour of the suction side starting from a step edge. | 10-31-2013 |
| 20130315745 | AIRFOIL MATEFACE SEALING - An airfoil includes an airfoil working portion and an adjoining endwall. The endwall has a leading edge, a trailing edge, a first mateface, and a second mateface that collectively define a perimeter of the endwall, with the first and second matefaces arranged opposite one another. A forward zone is defined by the endwall that extends to the leading edge. The first and second matefaces are each oriented at an angle α | 11-28-2013 |
| 20140003951 | SUPER POLISH MASKING OF INTEGRALLY BLADED ROTOR | 01-02-2014 |
| 20140003952 | PROTECTIVE POLISHING MASK | 01-02-2014 |
| 20140079556 | STEAM TURBINE STATIONARY BLADE AND STEAM TURBINE - A plurality of slots with different widths are provided in a plurality of line on a stationary blade surface. More specifically, the steam turbine stationary blade has a hollow nozzle with a penetrating space, which is connected with a diaphragm outer ring or inner ring, and a plurality of suction slots extending radially which are arranged on the blade surface. At a position where a water film deposited to the blade surface is thick, the width of a slot is smaller and at a position where the water film is thin, the width of a slot is larger. | 03-20-2014 |
| 20140133993 | Apparatus and Method for Tuning a Vibratory Response of a Rotor Blade - A method and apparatus for reducing a vibratory response in a structure using a tuning object. A selected mass may be identified for the tuning object. A plurality of channels may be formed in a workpiece having a mass greater than the selected mass to form the tuning object having the selected mass. The tuning object may be bonded to the structure using an adhesive bond to reduce the vibratory response of the structure. | 05-15-2014 |
| 20140161618 | Metal Joining And Strengthening Methods Utilizing Microstructural Enhancement - A method for joining first and second metal portions includes welding together the portions such that a weld nugget joins them, compressively stressing the weld nugget throughout its volume, and heat treating the compressively stressed weld nugget to recrystallize metal therein. A method for strengthening a metal element includes imparting compressive stress within a region of the metal element, and heat treating it such that metal of the region recrystallizes with a finer grain structure than was present in the region before the step of imparting the compressive stress. A repaired metal part includes a first, original section made of metal alloy, and a second, repair section of metal alloy joined to the original section by a recrystallized metal weld having crystals within +/−3 ASTM-112 grain sizes of the size of the crystals of the original and repair sections. | 06-12-2014 |
| 20140169977 | BLADE CASCADE AND TURBOMACHINE - A blade cascade of a turbomachine having at least one shape variation of a blade situated on the blade side in the proximity of a side wall and extending downstream, and at least one side wall contouring of the side wall or at least one second shape variation of an adjacent blade near the side wall, as well as a turbomachine, are disclosed. | 06-19-2014 |
| 20140248154 | BLADE OF A ROW OF ROTOR BLADES OR STATOR BLADES FOR USE IN A TURBOMACHINE - The present invention relates to a blade of a row of rotor blades or stator blades for use in a turbomachine, with the blade being designed with a substantially convex suction side and a substantially concave pressure side as well as with a leading edge, onto which the flow passes, and a trailing edge, away from which the flow passes. The blade has at least one contour recess provided on at least one of the blade sides including the suction side and the pressure side, wherein the contour recess includes a step edge, a contour corner and a flank face provided between the step edge and the contour corner. The contour recess extends over at least a part of the profile depth and/or the profile height of the blade. | 09-04-2014 |
| 20140286783 | METHOD OF FABRICATING A PART MADE OUT OF TA6ZR4DE TITANIUM ALLOY - A method of fabricating a part made out of TA6Zr4DE titanium alloy including forging a blank in the alpha/beta domain to form a preform, hot die-stamping the preform to form a rough part in the beta domain of the titanium alloy, and heat treatment. During the die-stamping, the rough part is subjected throughout to local deformation c greater than or equal to 1.2, the die-stamping being terminated by immediate cooling at an initial cooling rate faster than 85° C./min. The method can be utilized to make a rotary part of a turbomachine. | 09-25-2014 |
| 20140334935 | FIBROUS REINFORCEMENT STRUCTURE FOR COMPOSITE MATERIAL PART HAVING A REDUCED THICKNESS PORTION - A fiber structure reinforcing a composite material part woven as a single piece by multilayer weaving between plural first and second layers of yarns. The fiber structure includes a portion of decreasing thickness that presents: plural yarn withdrawal parts in surface continuity, with yarns interrupted from the first plural layers of yarns underlying the layer of yarns of the first plural layers of yarns situated in the surface of the structure; and plural yarn withdrawal parts in surface discontinuity, with yarns interrupted from the first plural layers of yams situated at the surface of the structure, each interrupted yarn replaced in the surface of the structure by a yarn of a layer of yarns underlying the first plural layers of yarns. The yarns of the second plural layers of yarns situated in the surface of the fiber structure are continuous over at least the entire portion of decreasing thickness. | 11-13-2014 |
| 20140341743 | MODIFIED TURBINE BUCKETS AND METHODS FOR MODIFYING TURBINE BUCKETS - Methods for modifying a turbine buckets include removing at least an original outer edge for an entire length of the slash face of the turbine bucket and adding a new material to the slash face to build a new outer edge, wherein the new outer edge extends the entire length of the slash face. | 11-20-2014 |
| 20140341744 | CELLULAR ACOUSTIC STRUCTURE FOR A TURBOJET ENGINE AND TURBOJET ENGINE INCORPORATING AT LEAST ONE SUCH STRUCTURE - A cellular acoustic structure for a turbojet engine includes a closed wall. The closed wall includes at least two faces having acoustically transparent areas and acoustic reflective areas. The closed wall is filled with a plurality of cells, and the acoustic reflective areas are disposed within the closed wall so that an acoustic path of aerial sound vibrations travels through the acoustically transparent areas, penetrates inside the cells and reflects on the acoustic reflective areas. In particular, the acoustic path in some of the cells has a depth greater than a half of the thickness of the cellular acoustic structure. | 11-20-2014 |
| 20140369841 | BLADE FOR A WATER CURRENT TURBINE ROTOR, WATER CURRENT TURBINE COMPRISING SUCH A BLADE, ASSOCIATED WATER CURRENT TURBINE AND METHOD FOR PRODUCING SUCH A BLADE - A blade for a water current turbine rotor, which extends along a radial direction and comprises an outer surface, an inner surface, a leading edge, and a trailing edge. The leading edge is the edge of the blade that extends along the radial direction and is disposed upstream in the direction in which the water flows along the blade, while the trailing edge is the edge of the blade opposite the leading edge and is disposed downstream in the direction of flow. At least one portion of the blade has a profile comprising a thick portion and a thin portion, the cross section being perpendicular to the radial direction. The thick portion and the thin portion each have a maximum thickness along a direction perpendicular to the outer surface, the maximum thickness of the thick portion being at least four times greater than the maximum thickness of the thin portion. | 12-18-2014 |
| 20150017005 | INSERT WITH AN EXTERNAL SURFACE WHICH IS PART OF AT LEAST ONE AERODYNAMIC PROFILE OF A TURBOMACHINE TEST BLADE - The invention relates to an insert for a turbine engine test vane including the insert and a vane body. The insert includes at least two external surfaces. The insert is configured to fit into the vane body, such that the external surfaces are vane aerodynamic surfaces each forming part of a vane aerodynamic profile. | 01-15-2015 |
| 20150017006 | Wind Turbine Assembly - A wind turbine assembly comprising a generally cylindrical wind turbine rotor that is supported by a rotor support and operable to rotate about a rotational axis, the rotor comprising a plurality of aerofoil blades with each aerofoil blade having a leading edge, a trailing edge, a suction surface, a pressure surface, and an aerofoil chord having a chord length between the leading edge and the trailing edge, the aerofoil blades being in a generally cylindrical arrangement around the rotational axis with the leading edges at a larger radial separation from the rotational axis than the trailing edges, and the chords being angled relative to radii through the rotational axis such that the suction surfaces and pressure surfaces respectively face generally outwardly and inwardly from and to the rotational axis, wherein the minimum separation (S) between the leading edge of a first aerofoil and the suction surface of an adjacent aerofoil is less than the chord length (L | 01-15-2015 |
| 20150017007 | TURBINE BLADE OR VANE - The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow channel. The platform is designed as a separate component and can be connected to the blade in a form-fit manner. Flexible application is achieved in that the platform is composed of several individual platform elements, which enclose the blade in the assembled state. | 01-15-2015 |
| 20150050154 | AIRFOIL TRAILING EDGE APPARATUS FOR NOISE REDUCTION | 02-19-2015 |
| 20150078908 | GAS TURBINE ENGINE FOR AIRCRAFT ENGINE - A gas turbine stator for aircraft engines has a blade array with a plurality of blades constituted by a series of first blades and a series of second blades with different geometries; the array is formed by a plurality of sectors, each having an inner portion, an outer portion, at least one first blade and a least one second blade, and each defined by a body made in one piece; a single first blade is alternated with a single second blade for the entire circumference of the stator. | 03-19-2015 |
| 20150132138 | ROTOR BLADE FENCE FOR A WIND TURBINE - The present invention is directed to a rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade extending from a blade root to a blade tip. The rotor blade has a pressure side surface and a suction side surface. The pressure side surface and the suction side surface each extend between a leading edge and a trailing edge. The assembly also includes a blade root extension configured to attach to one of the pressure side surface or the suction side surface of the rotor blade adjacent to the blade root. The blade root extension includes at least one blade fence and at least one airflow modifying element. The blade fence extends between a proximal end and a distal end in a chord-wise direction. The proximal end is configured to attach to the rotor blade such that the distal end remains free and spaced apart from the rotor blade. The airflow modifying element is configured at the proximal end of the blade fence. As such, the blade root extension is configured to improve aerodynamic performance of the rotor blade. | 05-14-2015 |
| 20150132139 | FOUNDRY CORE ASSEMBLY FOR MANUFACTURING A TURBOMACHINE BLADE, ASSOCIATED METHOD OF MANUFACTURING A BLADE AND ASSOCIATED BLADE - A foundry core for manufacturing a blade of a turbomachine including a tip section offset, including a core element for forming various internal cavities, the core element including a leading-edge cavity internal core, central cavity internal cores, and a trailing-edge cavity internal core. The internal core for the central cavity adjacent to the internal core for the trailing-edge cavity includes a bulge extending toward the core for the leading-edge cavity. | 05-14-2015 |
| 20150147182 | ADJUSTED ROTATING AIRFOIL - A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased surface area over a portion of the airfoil chord length. The increased surface area allows for a greater amount of air to be taken in by the airfoil, thus increasing the air flow through the gas turbine engine. | 05-28-2015 |
| 20150315915 | PROPELLER BLADE FOR A TURBOMACHINE - The invention relates to a propeller blade ( | 11-05-2015 |
| 20150354364 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. | 12-10-2015 |
| 20150354542 | ROOT BUSHING FOR A BLADE ROOT OF A WIND TURBINE ROTOR BLADE, A BLADE ROOT, A WIND TURBINE ROTOR BLADE AND A WIND TURBINE - A root bushing for a blade root of a wind turbine rotor blade, including a cylindrical bushing body and a flat contact body is provided. The contact body is provided on a face of the bushing body. This has the advantage that due to the provision of the contact body, the contact area between the root bushing and the pitch bearing is increased. In another embodiment, the root bushing includes a central bore which protrudes through the bushing body and the contact body. In another embodiment, an outer wall of the bushing body is provided with a connection structure for connecting the root bushing to a composite material of the wind turbine rotor blade. | 12-10-2015 |
| 20150361952 | ROTOR BLADE OF A WIND TURBINE - A rotor blade ( | 12-17-2015 |
| 20160003049 | Geared Turbofan Engine Having a Reduced Number of Fan Blades and Improved Acoustics - A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile. | 01-07-2016 |
| 20160010183 | METHOD OF MAKING A Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE BLADE INCORPORATING SAME | 01-14-2016 |
| 20160010457 | TURBINE WHEEL OF AN EXHAUST GAS TURBOCHARGER AND ASSOCIATED PRODUCTION METHOD | 01-14-2016 |
| 20160010462 | TURBOMACHINE BLADE | 01-14-2016 |
| 20160024929 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil is a fan blade for a gas turbine engine. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning. | 01-28-2016 |
| 20160045988 | METHOD OF REMOVING WELD FLASH - Method of trimming weld flash from a weld joint formed between a first component and a second component. The method provides a rotary shear tool having a rotary blade and a second blade. The second blade may be a fixed blade. The method further includes shearing the weld flash from the weld joint by passing the weld flash between the rotary blade and second blade of the rotary shear tool. Also provides a rotary shear tool for trimming weld flash from a weld joint formed between a first component and a second component. The rotary shear tool includes: a rotary blade; a second blade; and a mounting portion for mounting the rotary shear tool on a robotic arm. | 02-18-2016 |
| 20160047260 | TURBOMACHINE BLADE ASSEMBLIES - A turbomachine blade can include a blade root defining a plurality of feather seal slots on a lateral portion thereof. The plurality of seal slots includes two leg slots, each leg slot extending radially, and a cross member slot extending axially. An airfoil portion extends radially from the blade root. | 02-18-2016 |
| 20160053616 | TURBINE WHEEL OF AN EXHAUST-GAS TURBOCHARGER - A turbine wheel ( | 02-25-2016 |
| 20160067836 | REPAIR OR REMANUFACTURE OF BLADE PLATFORM FOR A GAS TURBINE ENGINE - A method of remanufacturing a turbine component includes electrical discharge machining a puck via the turbine component to form an electrical discharged machined puck; and brazing the electrical discharged machined puck to the turbine component. | 03-10-2016 |
| 20160076514 | Turbine Blade - An energy producing rotating assembly comprising blade(s) with an airfoil cross-section, wherein said airfoil cross section has an asymmetrical airfoil measurement. | 03-17-2016 |
| 20160102554 | INSPECTION AND QUALIFICATION FOR REMANUFACTURING OF COMPRESSOR WHEELS - A method for remanufacturing a compressor wheel for a turbocharger is disclosed. The method includes scanning one or more surfaces of the compressor wheel using a laser scanning system to measure a depth of defects located in the one or more surfaces. The method further includes forming a compressive residual stress zone in each of the one or more surfaces with an effective depth that is at least equal to the predetermined distance if all of the measured depths are less than a predetermined distance and discarding the compressor wheel if at least one of the measured depths is greater than or equal to the predetermined distance. | 04-14-2016 |
| 20160114539 | MANUFACTURING ARRANGEMENT - A manufacturing arrangement realized for the manufacture of a rotor blade, including a pair of tracks arranged along the longitudinal sides of a blade mold, a first gantry assembly realized to span the track pair and to carry a first tool arrangement, which first tool arrangement includes at least a fiber distributor, a second gantry assembly realized to span the track pair and to carry a second tool arrangement, and a control arrangement realized to effect a coordinated movement of the gantry assemblies along the track pair and to coordinate the operation of the second tool arrangement with the operation of the first tool arrangement, is provided. A manufacturing line, a method of manufacturing a rotor blade, and a wind turbine rotor blade are further provided. | 04-28-2016 |
| 20160115795 | TURBINE BLADE AIRFOIL AND TIP SHROUD - A turbine blade airfoil ( | 04-28-2016 |
| 20160138403 | SINGLE-PIECE BLISK FOR TURBOMACHINE FAN COMPRISING AN UPSTREAM AND/OR DOWNSTREAM RECESS MAKING ITS BLADES MORE FLEXIBLE - The invention relates to a single-piece fan blisk ( | 05-19-2016 |
| 20160138561 | METHOD FOR MOUNTING A WIND TURBINE ROTOR BLADE, AND WIND TURBINE ROTOR BLADE - A method for mounting a wind turbine rotor blade which has at least one release unit is provided. A hoisting rope is fastened on or in the rotor blade. First ends of at least one auxiliary rope are fastened on or in the release unit in the rotor blade. The rotor blade is lifted up by means of the hoisting rope. The rotor blade is mounted on a rotor of the wind turbine. The release unit is activated so that the first ends of the auxiliary ropes are released. The auxiliary ropes can be removed. | 05-19-2016 |
| 20160138563 | ROTOR BLADE OF A WIND TURBINE AND WIND TURBINE - A rotor blade of an aerodynamic rotor of a wind turbine, comprising: at least a first and a second wing fence, with the first wing fence being arranged at the rotor blade in radial direction, in relation to an axis of rotation of the rotor, in a range between 25% and 40%, and the second wing fence being arranged at the rotor blade in radial direction, in relation to an axis of rotation of the rotor, in a range between 45% and 60%. | 05-19-2016 |
| 20160168999 | A BALANCED MIXED FLOW TURBINE WHEEL | 06-16-2016 |
| 20160177780 | BLADE ARRANGEMENT OF A JET ENGINE OR AN AIRCRAFT PROPELLER | 06-23-2016 |
| 20160184930 | METHOD OF WELDING SHAFT AND WHEEL IN TURBINE SHAFT, TURBINE SHAFT, AND WELDING DEVICE - Provided is a method of welding a shaft and a wheel in a turbine shaft. A target surface with a hole is provided to any one of the shaft and the wheel. An opposed surface is provided to the other one of the shaft and the wheel. The opposed surface includes an opposed portion opposed to the target surface, and a non-opposed portion formed continuously from the opposed portion toward a center side while facing onto the hole. The welding method includes: disposing the target surface and the opposed surface such that the they are opposed to each other while establishing a state of surface contact; and welding them by beam irradiation from outside in a radial direction of the shaft toward inside in the radial direction thereof based on a condition to cause a depth of fusion to reach a position on a center side beyond the opposed portion. | 06-30-2016 |
| 20160193752 | MOULD FOR A WIND TURBINE COMPONENT | 07-07-2016 |
| 20160195058 | Turbine System and Method | 07-07-2016 |
| 20160195104 | TURBINE ENGINE ROTOR BLADE | 07-07-2016 |
