Class / Patent application number | Description | Number of patent applications / Date published |
416241000 | Ceramic material | 50 |
20080206064 | ROTORCRAFT BLADE PROVIDED WITH A RADIAL SEGMENT AND WITH AT LEAST ONE FORWARDLY-AND/OR REARWARDLY-SWEPT SEGMENT - The present invention relates to a rotorcraft blade (P) provided in succession with a radial segment ( | 08-28-2008 |
20080213099 | Ni-Fe BASED FORGING SUPERALLOY EXCELLENT IN HIGH-TEMPERATURE STRENGTH AND HIGH-TEMPERATURE DUCTILITY, METHOD OF MANUFACTURING THE SAME, AND STEAM TURBINE ROTOR - An Ni—Fe based superalloy forging material including 30 to 40 wt % of Fe, 14 to 16 wt % of Cr, 1.2 to 1.7 wt % of Ti, 1.1 to 1.5 wt % of Al, 1.9 to 2.7 wt % of Nb, 0.05 wt % or less of C and the remainder of Ni and inevitable impurities is solution-treated and aged, and thereby γ′ phase (Ni | 09-04-2008 |
20080213100 | Fan Blade Structure - A fan blade comprises a first board and a second board, wherein the density of the first board is greater than that of the second board, so that the first board is used to strengthen the structure strength of the second board. Therefore, the fan blade is less likely to deform and can maintain its wind guide structure, and its life span is prolonged. | 09-04-2008 |
20080219853 | Multi-alloy turbine rotors and methods of manufacturing the rotors - A dual alloy turbine rotor is provided and includes an integrally formed blade ring and a disk. The blade ring is made of a first alloy and includes a ring portion and a plurality of airfoils extending therefrom, where the ring portion includes an inner surface, and each airfoil includes an internal cavity formed therein. The disk is made of a second alloy and may have a beveled outer peripheral surface. The disk is disposed within the ring portion such that the disk outer peripheral surface contacts at least a portion of the ring portion inner surface. Methods of manufacturing the turbine rotor are also provided. | 09-11-2008 |
20080226460 | COMPRESSOR ROTOR - A blade as a main body of a rotor blade has a suction side made convex and a pressure side made concave so as to have an aerofoil profile. A squealer tip having a back face continuous to the suction side and a front face matching with a center plane of the blade is formed at a distal end of the blade. The front face is coated with a hard coating. | 09-18-2008 |
20080240926 | Cobalt-Free Ni-Base Superalloy - There is provided a Co-free Ni-base superalloy having a composition containing 1.0 to 10.0 wt % of Cr, 0.1 to 3.5 wt % of Mo, 7.5 to 10.0 wt % of W, 4.0 to 8.0 wt % of Al, 12.0 wt % or less of at least one species of Ta, Nb and Ti, 0 to 2.0 wt % of Hf, 0.1 to 5.0 wt % of Re and the remainder comprised of Ni and unavoidable impurities. The Co-free Ni-base superalloy exhibits high composition stability over a long period of time and is excellent in creep properties at high temperature, and also suitable as a turbine blade or turbine vane of atomic power generation in which maintenance for radioactive contamination and so forth are easy. | 10-02-2008 |
20080279693 | Heat-dissipating fan structure able to dispaly representation - A heat-dissipating fan structure able to display a representation includes a fan body and a plurality of images. The fan body includes a socket and a fan. The fan is pivotally connected to the socket and has a hub and a plurality of blades. Each of the blades is connected to the hub and respectively to a positioning structure. The images are respectively attached onto the blades in a manner to be positioned with the assistance of the positioning structure. | 11-13-2008 |
20080298976 | Blade of a Turbomachine - A blade of a turbomachine, in particular of a gas turbine, is disclosed. The blade includes at least one fastening section for fastening the same in a locating section of a rotor-side or stator-side component of the turbomachine. The, or each, fastening section has a core region which is made of a relatively brittle and relatively light material and is embedded in an encasing region made of a material having relatively high ductility. | 12-04-2008 |
20080304975 | METHOD FOR PRODUCING ABRASIVE TIPS FOR GAS TURBINE BLADES - A method of attaching particles to a substrate, comprising the steps: providing a substrate having a surface providing an interlayer on the surface which conforms to the surface of the substrate, forming a melt pool in the interlayer, depositing a material within the melt pool, allowing the material to solidify, applying a powder containing dispersed particles to the solidified material, and applying heat to attach the dispersed particles to the substrate. | 12-11-2008 |
20080317601 | Turbomachine Blade With Erosion and Corrosion Protective Coating and Method of Manufacturing - A turbomachine blade ( | 12-25-2008 |
20080317602 | ARTICLE HAVING A VIBRATION DAMPING COATING AND A METHOD OF APPLYING A VIBRATION DAMPING COATING TO AN ARTICLE - A compressor blade ( | 12-25-2008 |
20090016893 | Skinning of progressive cavity apparatus - A skinned rotor | 01-15-2009 |
20090016894 | Component with internal damping - A method of manufacturing a component such as a gas turbine fan blade. The method comprises: disposing a plurality of webs between a plurality of panels; and deforming the panels and the webs by applying internal pressure between the panels, thereby forming a series of internal cavities ( | 01-15-2009 |
20090016895 | Impeller - The invention relates to closed impellers ( | 01-15-2009 |
20090022600 | 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 |
20090022601 | 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 |
20090047135 | LAYERED CORROSION RESISTANT COATING FOR TURBINE BLADE ENVIRONMENTAL PROTECTION - The present invention is a gas turbine engine turbine blade comprising an airfoil section having at least an exterior surface, a platform section having an exterior surface, an under platform section having an exterior surface, and a dovetail section having an exterior surface. The blade further comprises a corrosion resistant coating on a surface of a turbine blade section selected from the group consisting of the exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the corrosion resistant coating comprising a particulate corrosion resistant component comprising from about 5 weight percent to about 100 weight percent corrosion resistant non-alumina particulates having a CTE greater than that of alumina particulates and balance alumina particulates, and a binder component. The present invention also includes methods for making such a gas turbine engine blade. | 02-19-2009 |
20090053068 | STRUCTURES FOR DAMPING OF TURBINE COMPONENTS - Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component. | 02-26-2009 |
20090053069 | Layer System for a Component Comprising a Thermal Barrier Coating and Metallic Erosion-Resistant Layer, Production Process and Method for Operating a Steam Turbine - There are described components of a steam turbine, comprising a thermally insulating layer and a metallic anti-erosion layer on said thermally insulating layer. The anti-erosion layer is provided with the same material as the metallic connecting layer. | 02-26-2009 |
20090068019 | ROTOR BLADE FOR A WIND POWER PLANT - The present invention concerns a rotor blade for a wind power plant having an aerodynamic profile comprising a rotor blade leading edge and a rotor blade trailing edge. The invention also concerns a rotor blade tip for a rotor blade having an aerodynamic profile with a pressure and a suction side, wherein the rotor blade tip is curved or angled in its end region in the direction of the pressure side of the rotor blade. In order further to reduce the levels of sound emission of wind power plants the rotor blade is curved or angled in its edge region in the direction of the trailing edge of the rotor blade in the plane of the rotor blade. In that respect the invention is based on the realization that, in the case of a rotor blade which does not go to a point at the tip, the effective rotor blade area is maintained unreduced precisely in the outer region in which the effect is greatest. The curve or angling of the end region of the rotor blade however provides that the trailing edge is displaced rearwardly in the end region of the rotor blade so that the flow at the rotor blade trailing edge is detached with a time delay in the outer region. Alternatively to attain the object of the invention a rotor blade can be developed in such a way that the ‘outer region’ narrows. That configuration of the rotor blade tip is based on the realization that the decreasing blade depth results in a reduced flow around the blade tip as the energy thereof is previously distributed to the trailing edge vortices but at the same time the effective rotor blade area is also reduced. The angling of the rotor blade tip provides that the effective rotor blade depth remains at its optimum as far as the angled rotor blade tip. | 03-12-2009 |
20090092498 | Component to be Arranged in The Flow Channel of a Turbomachine and Spraying Method For Producing The Coating - The invention relates to a component for arrangement in the duct of a turbine engine. The component is provided with a coating, which has a surface structure with scales which overlap each other in the direction of flow of the turbine engine. The invention also relates to a spraying method for generating a coating on a component. | 04-09-2009 |
20090104040 | Nickel Based Alloy for Forging - A nickel (Ni) based alloy for forging includes: 0.001 to 0.1 wt. % of carbon (C); 12 to 23 wt. % of chromium (Cr); 3.5 to 5.0 wt. % of aluminum (Al); 5 to 12 combined wt. % of tungsten (W) and molybdenum (Mo) in which the Mo content is 5 wt. % or less; a negligible small amount of titanium (Ti), tantalate (Ta) and niobium (Nb); and the balance of Ni and inevitable impurities. | 04-23-2009 |
20090104041 | TITANIUM TREATMENT TO MINIMIZE FRETTING - A method for surface treating a titanium gas turbine engine component. The method includes providing a gas turbine engine component having a titanium-containing surface. The component is heated to a temperature sufficient to diffuse carbon into the titanium and below 1000° F. The surface is contacted with a carbon-containing gas to diffuse carbon into the surface to form carbides. Thereafter, the carbide-containing surface is coated with a lubricant comprising a binder and a friction modifier. The binder preferably including titanium oxide and the friction modifier preferably including tungsten disulfide. The coefficient of friction between the surface and another titanium-containing surface is less than about 0.6 in high altitude atmospheres. | 04-23-2009 |
20090110560 | Run-in coating for gas turbines and method for producing same - A run-in coating is for gas turbines. The run-in coating is used for sealing a radial gap between a housing of the gas turbine and rotating rotor blades of same, the run-in coating being applied onto the housing. The run-in coating is made of an intermetallic titanium-aluminum material. | 04-30-2009 |
20090116967 | COMPRESSOR TURBINE VANE AIRFOIL PROFILE - A single stage high pressure turbine vane 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. | 05-07-2009 |
20090116968 | Blade for wind turbines & an improved wind turbine - An improved blade for a wind turbine incorporates a planar member. The planar member has a leading surface, a trailing surface, an inboard side, an outboard side, an inner impulse surface, an outer impulse surface. The inner impulse surface and outer impulse surface are used for the purpose of actuating the wind turbine from a state of rest and for the purpose of imparting turbulence. By producing a breakdown in the laminar flow between the impulse surface and the trailing surface the improved blade will rotate slower thereby decreasing the amount of wear and tear to the wind turbine. | 05-07-2009 |
20090123290 | NI-BASED ALLOY MEMBER, METHOD OF PRODUCING THE ALLOY MEMBER, TURBINE ENGINE PART, WELDING MATERIAL, AND METHOD OF PRODUCING THE WELDING MATERIAL - A Ni-based alloy member has resistance against grain boundary fracture, fatigue strength, and oxidation resistance at temperatures near 1000° C. or higher. The Ni-based alloy member includes a non-repaired region made of a Ni-based alloy base and a region repaired by welding, which is formed on the non-repaired region and which is made of a buildup-welded layer, the buildup-welded layer being made of a Ni-based alloy containing, by weight, 15% or less of Co, 18-22% of Cr, 0.8-2.0% of Al, 5.0% or less of Ta, 0.5% or less of Mo, 0.5% or less of Ti, 13-18% of W, 0.05-0.13% of C, 0.06% or less of Zr, 0.015% or less of B, 0.4-1.2% of Mn, and 0.1-0.3% of Si, the balance of the alloy being preferably essentially made of Ni. | 05-14-2009 |
20090123291 | Coatings for Use in the Field of Power Generation - There is described a method for coating the surfaces of turbomachines that come into contact with fluid media, wherein the outer surface of parts of turbomachines that come into contact with fluid media are contacted by a coating comprising an inorganic-organic hybrid polymer. Furthermore, there is described a turbomachine, wherein the surfaces that come into contact with fluid media have an outer coating which comprises an inorganic-organic hybrid polymer. Such a turbomachine can be used for generating electric power. | 05-14-2009 |
20090129933 | BLOWER WHEEL - The invention relates to a blower wheel, especially a plastic blower wheel for a cylindrical rotor radial fan for the heating and air-conditioning systems of a motor vehicle. Said blower wheel comprises a plurality of blades ( | 05-21-2009 |
20090155087 | COOLING FAN - A cooling fan, includes a hub ( | 06-18-2009 |
20090162209 | TURBINE ENGINE COMPONENTS WITH ENVIRONMENTAL PROTECTION FOR INTERIOR PASSAGES - A gas turbine blade comprises a base metal, a platform, an airfoil extending upwardly from the platform, a shank extending downwardly from the platform. The shank has an exterior wall and an internal passage, and the airfoil has a cooling flow channel inside the airfoil for flowing a cooling flow therethrough. The blade has a first chromide coating contacting the base metal of at least a portion of an interior surface of the shank and interdiffused therewith, wherein the first chromide coating does not have an aluminide coating deposited over it. The blade has a second chromide coating contacting the base metal of at least a portion of an interior surface of the airfoil and interdiffused therewith. A method for preparing a gas turbine blade comprises the steps of applying chromide coatings, sealing the interior passages of the shank and airfoil and applying an aluminide or platinum aluminide coating and an optional ceramic layer on the airfoil. | 06-25-2009 |
20090196760 | Nickel-Base Superalloy Excellent in the Oxidation Resistance - A nickel-base superalloy having excellent oxidation resistance is provided. It is useful as high-temperature members such as turbine blades and turbine vanes for jet engines or gas turbines. The nickel-base superalloy has a composition containing Co: 0.1 to 15% by weight, Cr: 0.1 to 10% by weight, Mo: 0.1 to 4.5% by weight, W: 0.1 to 15% by weight, Al: 2 to 8% by weight, Ta+Nb+Ti: 0 to 16% by weight, Hf: 0 to 5% by weight, Re: 0.1 to 16% by weight, Ru: 0.1 to 16% by weight, Si: 0.2 to 5% by weight and a balance made of Ni and unavoidable impurities. | 08-06-2009 |
20090196761 | METAL INJECTION JOINING - A method of joining a first part together with a second part is disclosed. The method may comprise providing a first part having a first joining portion including a first channel and a second part having a second joining portion including a second channel. The method may further comprise positioning the first part adjacent to the second part such that the first channel and second channel align with one another to define a cavity. The method may still further comprise preparing a mixture comprising at least one of a metal powder and a polymer binder, placing the mixture into the cavity so as to form a preform and solidifying the preform forming a metal element in the cavity. The metal element joins the first part together with the second part | 08-06-2009 |
20090196762 | CASTING ALUMINUM ALLOY, CAST COMPRESSOR IMPELLER COMPRISING THE ALLOY, AND PROCESS FOR PRODUCING THE SAME - A casting aluminum alloy which contains, in terms of mass %, 3.2-5.0% Cu, 0.8-3.0% Ni, 1.0-3.0% Mg, 0.05-0.20% Ti, and up to 1.0% Si, the remainder being aluminum and incidental impurities. This casting aluminum alloy is used to produce a cast compressor impeller comprising a hub part, a hub-disk part extending from the hub part in the radial directions and having a hub surface and a disk surface, and blade parts disposed on the hub surface. Compared to conventional aluminum alloys, the casting aluminum alloy has a moderate elongation and a high strength at ordinary temperature and has high strength even at high temperatures. | 08-06-2009 |
20090208342 | TURBOMACHINE PART HAVING ITS LEADING EDGE CONSTITUTED BY A SUPERELASTIC MATERIAL - The invention relates to a turbomachine part comprising a main portion and a leading edge. Over at least a fraction of the length of said part, the leading edge is constituted by a sheet of material that is fastened to the main portion and that extends from the pressure side to the suction side of the main portion while leaving a space between the sheet and the upstream end of the main portion, said material being capable, below a maximum deformation ε | 08-20-2009 |
20090214352 | SURFACE TREATMENT METHOD AND REPAIR METHOD - A method for forming a dense coating on a limited region of a subject body is disclosed. The method is composed of the steps of: applying one selected from the group of a compressed body of a powder of a metal and a sintered compressed body of a powder of a metal to a working electrode; executing discharge deposition to deposit a first coating from the working electrode on the subject body by applying the subject body as a workpiece of the discharge deposition; executing discharge deposition to deposit a second coating from the working electrode on the first coating by applying the subject body as a workpiece of the discharge deposition; and heating the subject body in one selected from the group of a vacuum, an air and an oxidizing atmosphere so as to densify the second coating or oxidizing the second coating at least in part to generate a solid lubricant substance. | 08-27-2009 |
20090226326 | THERMAL BARRIER COATING WITH THERMOLUMINESCENT INDICATOR MATERIAL EMBEDDED THEREIN - A coating material ( | 09-10-2009 |
20090238693 | Substrate With Applied Coating and Production Method - There is described a substrate with a coating; the coating contains a coating matrix in whose matrix structure multilayered and/or encapsulated nanoparticles are arranged and release a dye when a limit temperature is exceeded the first time and/or trigger a color reaction which causes the color of the coating to change irreversibly. | 09-24-2009 |
20090252613 | REPAIR OF GAS TURBINE BLADE TIP WITHOUT RECOATING THE REPAIRED BLADE TIP - A damaged gas turbine blade which has previously been in service, and which is made of a base metal, is furnished. Any damaged material is removed from the damaged blade tip. The damaged blade tip is weld repaired with a nickel-base superalloy that is more resistant to oxidation resistance than is the base metal in the operating environment of the tip-repaired gas turbine blade. The method does not include any step of coating a lateral surface of the repaired blade tip with a non-ceramic coating after the step of weld repairing. | 10-08-2009 |
20090269207 | COMPONENT, IN PARTICULAR, A GAS TURBINE COMPONENT - A component, specifically a component for a gas turbine, having a main body of a base material and a wear protection coating applied to a surface of the main body, specifically a protective coating against corrosion and/or oxidation and/or erosion, is disclosed. A barrier coat is applied between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component. | 10-29-2009 |
20090269208 | REPAIR METHOD AND REPAIRED ARTICLE - A method of repairing an article includes removing an undesirable section of the article, attaching a repair section to the article at a location from which the undesirable section has been removed, and mechanically working the repair section to achieve a reduction in a cross-sectional area of the repair section. | 10-29-2009 |
20090269209 | Wind Turbine - A vertical-axis wind turbine for use with an electrical generator for producing power by converting the energy of wind currents into mechanical rotational energy which is then used to operate the electrical generator. In an embodiment, a rotor is responsive to wind currents by imparting rotation upon a central vertical shaft. Preferably, the rotor is designed with functional curved surfaces for efficient operation. | 10-29-2009 |
20090274562 | Coated turbine-stage nozzle segments - A method for coating a nozzle segment, the method comprising separating an outer shroud and an inner platform of the nozzle segment along pathways that bisect a first stator vane and a second stator vane of the of the nozzle segment, coating the first stator vane and the second stator vane after separating the outer shroud and the inner platform, and rejoining the separated outer shroud and the separated inner platform after coating the first stator vane and the second stator vane. | 11-05-2009 |
20090285692 | NI-BASE ALLOY FOR TURBINE ROTOR OF STEAM TURBINE AND TURBINE ROTOR OF STEAM TURBINE - An Ni-base alloy for a turbine rotor of a steam turbine contains in percent by weight C: 0.01 to 0.15, Cr: 15 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, Re: 0.5 to 3, and the balance of Ni and unavoidable impurities. | 11-19-2009 |
20090290986 | IMPELLER OF MULTIBLADE BLOWER AND METHOD OF MANUFACUTURING THE SAME - An impeller of a blower is disposed with circular support plates that are made of a resin and rotate about an axis of rotation and a plurality of blades that are made of a resin. The blades are disposed on outer peripheral portions of the circular support plates so as to be parallel to an axis of rotation, and serrated shapes are formed on the blades by cutting out blade tips at plural places. Additionally, a step is formed in a blade face of each of the blades at a position a predetermined distance from the blade tip where the serrated shape is formed. | 11-26-2009 |
20090290987 | COMPRESSOR 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 thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component. | 11-26-2009 |
20090297359 | High Modulus Metallic Component For High Vibratory Operation - A high modulus component, such as an aircraft engine turbine blade, is formed from a base metal that has a high modulus crystallographic orientation that is aligned with the primary, i.e. radial, direction of the turbine blade. The base metal is Ni, Fe, Ti, Co, Al, Nb, or Mo based alloy. Alignment of a high modulus direction of the base metal with the primary direction provides enhanced high cycle fatigue life. | 12-03-2009 |
20090324418 | Structural and acoustical vibration dampener for a rotatable blade - A structural and acoustical vibration dampener for a rotatable blade comprises a layer of structural/acoustic damping material coupled to at least a portion of the blade. A fan blade comprises a structural layer and a layer of damping material coupled to at least a portion of the structural layer. A method of applying a structural and acoustical vibration dampener to a fan blade comprises identifying a region on the fan blade and securing the structural/acoustical vibration dampener to the fan blade over at least a portion of the region. | 12-31-2009 |
20090324419 | HIGHLY CORROSION-RESISTANT MOVABLE BLADE ASSEMBLY FOR A STEAM TURBINE, IN PARTICULAR A GEOTHERMAL IMPULSE TURBINE - A highly corrosion-resistant movable blade assembly ( | 12-31-2009 |
20100008790 | Superalloy compositions, articles, and methods of manufacture - A composition of matter comprises, in combination, in weight percent: a largest content of nickel; at least 16.0 percent cobalt; and at least 3.0 percent tantalum. The composition may be used in power metallurgical processes to form turbine engine turbine disks. | 01-14-2010 |
20100008791 | Acoustical Vibration Dampener for a Rotatable Blade - An acoustical vibration dampening system for a rotatable blade comprises at least one section of a rotatable blade and a layer of acoustic damping material coupled to a portion of the at least one section of a rotatable blade. A fan blade comprises a first structural section of a fan blade, a second structural section of the fan blade, and a layer of acoustic damping material provided between the first structural section and the second structural section of the fan blade. A method of making a fan blade with acoustic damping comprises forming at least two sections of a fan blade, and disposing an acoustical vibration dampener between the at least two sections of the fan blade. | 01-14-2010 |
20100014982 | Turbine Blade for a Steam Turbine - Disclosed is a turbine blade for a steam turbine, comprising an aerofoil section and a root section and is characterized according to the invention in particular in that the aerofoil section is designed for use in a low-pressure stage of the steam turbine and contains fiber composite materials at least in regions. | 01-21-2010 |
20100014983 | TURBINE BLADE - The present invention provides a turbine blade that is exposed to a high temperature atmosphere at relatively high temperatures and to a low temperature atmosphere at relatively low temperatures, including: a concave-curve-like pressure surface that is concaved along a flow direction of fluid; a convex-curve-like suction surface that is convexed along the flow direction of the fluid; and a concave and convex formation device which causes a concave and convex portion along the flow of the fluid to appear on the suction surface when the turbine blade is exposed to the low temperature atmosphere, and which turns the suction surface into a smooth surface along a convex curve surface of the suction surface when the turbine blade is exposed to the high temperature atmosphere. With this construction, it is possible to reduce a pressure loss of the turbine blade at high Reynolds numbers in the low temperature atmosphere without increasing a pressure loss of the turbine blade at low Reynolds numbers in the high temperature atmosphere. | 01-21-2010 |
20100028162 | Rotor blade extension portion having a skin located over a framework - A wind turbine rotor blade extension portion having a permanent framework with one or more chord-wise members and a substantially span-wise member. A membrane is located over the framework to thereby generate a streamlined surface. The extension portion is configured to transmit aerodynamic loads from the membrane, along the chord-wise members to a rotor blade to which the extension portion is connected, in use. | 02-04-2010 |
20100034661 | EROSION RESISTANT PROTECTIVE STRUCTURE AND PROCESS FOR APPLYING SAME TO A SUBSTRATE - A component is provided for use in a turbine comprising: a substrate formed from an alloy, and an erosion resistant protective structure mechanically coupled to a portion of the substrate for protecting the substrate portion from erosion caused by a fluid. The erosion resistant protective structure may be formed from a shape memory alloy. | 02-11-2010 |
20100040476 | CORROSION COATING FOR TURBINE BLADE ENVIRONMENTAL PROTECTION - A gas turbine engine turbine blade comprising an airfoil section, a platform section, an under platform section, and a dovetail section, an exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface. The blade further comprises a silicon-modified diffusion aluminide layer a surface of a turbine blade section selected from the group consisting of an exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the silicon modified diffusion aluminide layer having a concentration of silicon at a surface of the silicon-modified diffusion aluminide layer in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum at the surface of the silicon modified diffusion aluminide layer in the range of about 5 weight percent to about 25 weight percent. | 02-18-2010 |
20100047076 | BETA TITANIUM ALLOY - A beta titanium alloy comprises 25 wt % vanadium, 15 wt % chromium, 2 wt % aluminium, up to 0.15 wt % oxygen, 0.1 to 0.3 wt % carbon and the balance titanium plus incidental impurities. The carbon is present in the form of titanium carbide precipitates distributed throughout the beta titanium alloy matrix, the titanium carbide precipitates refine the grain size of the beta titanium alloy matrix and remove oxygen from the beta titanium alloy matrix to reduce precipitation of alpha titanium in the beta titanium alloy matrix to increase the ductility of the beta titanium alloy. The alloy is useful for gas turbine engine compressor blades ( | 02-25-2010 |
20100061863 | AIRFOIL AND METHODS OF LASER SHOCK PEENING OF AIRFOIL - A blade for rotating equipment. The blade includes a root and an airfoil with a leading edge attached to the root. The blade may include a laser shot peened root patch extending along the leading edge and the root. | 03-11-2010 |
20100061864 | COATING OPTIMIZATIOH PROCESS USING A COUPON AND COMPONENT COMPRISING A COUPON - A method for optimizing the coating of a component using a coupon by introducing the coupon into a depression of the component, in which the geometry of the component is not altered as compared to a component without a coupon, is provided. A component having a depression into which a coupon is fastened is also provided. | 03-11-2010 |
20100068065 | WIND TURBINE BLADE - The invention relates to a blade for a wind turbine, particularly to a blade that may be produced by an advanced manufacturing process for producing a blade with high quality structural components. Particularly, the structural components, which are preferably manufactured from fibre reinforced plastic material, will have a high level of stretched fibres as well as a far better controlled resin distribution and content and also a low void content. | 03-18-2010 |
20100086411 | MODERATE DENSITY, LOW DENSITY, AND EXTREMELY LOW DENSITY SINGLE CRYSTAL ALLOYS FOR HIGH AN2 APPLICATIONS - A single crystal alloy for high AN | 04-08-2010 |
20100092301 | Component for a high-temperature steam turbine , and temperature steam turbine - A component for a high-temperature steam turbine which operates at temperatures above 600° C., especially above 700° C., is formed of a nickel-based alloy. The negative influence of oxidation of the component which is induced by the superheated steam is prevented by the alloy which is used, having the following composition (in % by weight): | 04-15-2010 |
20100092302 | Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE BLADE INCORPORATING THE SAME - A Ni-based single crystal superalloy which has the following composition: Co: 0.0 wt % or more to 15.0 wt % or less, Cr: 4.1 to 8.0 wt %, Mo: 2.1 to 6.5 wt %, W: 0.0 to 3.9 wt %, Ta: 4.0 to 10.0 wt %, Al: 4.5 to 6.5 wt %, Ti: 0.0 to 1.0 wt %, Hf: 0.00 to 0.5 wt %, Nb: 0.0 to 3.0 wt %, Re: 3.0 to 8.0 wt % and Ru: 0.5 to 6.5 wt % with the remainder including Ni and unavoidable impurities, wherein P1≦700 is satisfied in which P1 represents a parameter 1, which is obtained by a formula: P1=137×[W (wt %)]+24×[Cr (wt %)]+46×[Mo (wt %)]−18×[Re (wt %)]. The Ni-based single crystal superalloy has excellent specific creep strength. | 04-15-2010 |
20100098550 | Method for coating of a base body and also a workpiece - A method for the coating of a base body is proposed, in which a layer of a platinum modified aluminide of the kind PtMAl is produced on the base body wherein M designates the metals iron (Fe) or nickel (Ni) or cobalt (Co) or combinations of these metals, wherein the layer is produced by means of a physical deposition out of the gas phase (PVD), wherein at least the two components aluminium (Al) and metal M are physically deposited out of the vapour phase, with the deposition being carried out at a process pressure of at least 0.1 mbar, preferably of at least 0.4 mbar and especially between 0.4 mbar and 0.6 mbar. A workpiece is further proposed, in particular a turbine blade, with a base body on which a layer is applied which is produced using a method of this kind. | 04-22-2010 |
20100098551 | METHOD AND DEVICE FOR COATING COMPONENTS OF A GAS TURBINE - The present invention relates to a method for coating components of a gas turbine, in particular for producing a wear-resistant, temperature, oxidation and/or corrosion-resistant protective coating on the component, wherein the protective coating is made of at least one solder film or slurry coating, which is connected to the corresponding region of the component by means of an inductive high-temperature soldering method. The bonded connection between the component and the solder film or slurry coating disposed on the component is achieved by locally heating the component in the region of the solder film or slurry coating to be applied, and simultaneously heating the solder film or slurry coating by means of thermal energy generated and emitted by at least one induction amplifier, wherein the induction amplifier is disposed between the inductor and the component in the region of the solder film or slurry coating. The invention further relates to a device for coating components of a gas turbine, in particular for producing a wear-resistant, temperature, oxidation and/or corrosion-resistant protective coating on the component, using at least one inductor for carrying out an inductive high-temperature soldering method for heating and bonding at least one component to at least one solder film or slurry coating forming the protective coating, wherein according to the invention at least one induction amplifier is disposed in the region of the solder film or slurry coating between the inductor and the component having the solder film or slurry coating. | 04-22-2010 |
20100104449 | IMPELLER AND COOLING FAN INCORPORATING THE SAME - A cooling fan includes a housing, a cover arranged on the housing, and an impeller received in a space formed between the housing and the cover. The impeller includes a hub and a plurality of blades extending radially and outwardly from the hub. Each of the blades includes a windward surface and a leeward surface opposite to the windward surface. A porous layer is disposed on the leeward surface of each of the blades, adjacent to a free end thereof. The porous layer has one side surface attached to the leeward surface and an opposite side surface facing the windward surface of an adjacent blade. | 04-29-2010 |
20100119375 | Pre-Coating Burnishing of Erosion Coated Parts - A gas turbine engine blade has a platform. A root depends from the platform and an airfoil extends from the platform. The airfoil has leading and trailing edges and pressure and suction sides. The blade has a substrate having a surface. A compressive stress exists below a first region of the surface. The first region extends over a majority of a streamwise perimeter of the airfoil at a location at a spanwise distance from the tip or more than 50% of a tip-to-platform span. A coating is on the surface including at the location. | 05-13-2010 |
20100124506 | VERTICAL AXIS WIND TURBINE BLADE - A blade for a wind turbine, such as vertical axis wind turbine, is disclosed. | 05-20-2010 |
20100135819 | Method of Manufacturing a Wind Turbine Rotor Blade - A method of manufacturing a wind turbine rotor blade is provided. Anticipated primary load paths within the rotor blade are predicted. Fibres of reinforcing material are dispensed onto a mould, having an orientation pattern of the fibres which is selected in dependence on the predicting step. Resin is also dispensed into the mould. | 06-03-2010 |
20100135820 | WIND BLADE SPAR CAP LAMINATE REPAIR - A wind blade spar cap laminate repair for wind turbine rotor blades, a repair kit to repair spar cap laminate damage, and a method of repairing damage on wind turbine rotor blades is provided. The wind blade spar cap laminate repair includes a prepared surface, an adhesive region disposed on the prepared surface, and a repair disposed on the adhesive region, wherein the adhesive region sufficiently bonds the repair to the prepared surface to substantially match the mechanical properties of the bulk of the wind turbine rotor blade. | 06-03-2010 |
20100143147 | SPARCAP FOR WIND TURBINE ROTOR BLADE AND METHOD OF FABRICATING WIND TURBINE ROTOR BLADE - A sparcap for a wind turbine rotor blade. The sparcap includes a first carbon material layer coupled to an inner surface of the wind turbine rotor blade. The first carbon material layer extends along at least a portion of a length of the wind turbine rotor blade. A core material is coupled to the first carbon material layer. The core material is positioned with respect to a buckling prone region of the wind turbine rotor blade. A second carbon material layer covers the core material and is coupled to the first carbon material layer and/or the core material. The second carbon material layer extends along at least a portion of the length of the wind turbine rotor blade. | 06-10-2010 |
20100143148 | TURBINE BLADE AND METHOD OF FABRICATING THE SAME - A turbine blade includes at least two blade segments. Each blade segment includes first and second shells joined together, a base region, at least one joint region including a mating face. Each of the first and second shells includes an outer skin, a base spar cap attached to an inner surface of the outer skin in the base region, a joint spar cap attached to the inner surface of the outer skin in the joint region and adjacent to at least a portion of the base spar cap. The joint spar cap includes holes in the mating face of the joint region. The turbine blade further includes fasteners within the holes for securing the at least two blade segments together. | 06-10-2010 |
20100150730 | COMPONENT HAVING AN ABRASIVE LAYER AND A METHOD OF APPLYING AN ABRASIVE LAYER ON A COMPONENT - The tips of gas turbine engine turbine rotor blades are provided with an abrasive layer and the abrasive layer comprises chromised silicon carbide grit protruding from a layer of material. In particular the abrasive layer comprises a mixture of cubic boron nitride grit and chromised silicon carbide grit and the cubic boron nitride grit and the chromised silicon carbide grit protruding from the layer of material. The cubic boron nitride grit has a greater dimension than the chromised silicon carbide grit. The cubic boron nitride grit cuts the majority of a track in an abradable structure and then the chromised silicon carbide grit provides any additional cutting of the abradable structure. | 06-17-2010 |
20100158695 | Superalloy Compositions, Articles, and Methods of Manufacture - A composition of matter comprises, in combination, in weight percent: a largest content of nickel; at least 16.0 percent cobalt; and at least 3.0 percent tantalum. The composition may be used in power metallurgical processes to form turbine engine turbine disks. | 06-24-2010 |
20100166567 | WIND TURBINE AND METHOD OF MANUFACTURE - A variable voltage and frequency output wind turbine. Variations of the wind turbine include use of a slotless alternator to reduce alternator noise, a high power AC output to facilitate transmission of the output over extended distances, AC to DC converters and DC to AC converters, and sensors for systems and devices to receive the wind turbine output and to allow matching of the output to the receiving devices and system. Other features include a removable hatchcover for dissipating heat from components contained in the turbine or attached to the hatchcover, a swept blade design to reduce blade-produced noise, and power storage components for storing and intermittently using energy stored as a result of wind turbine power generation. | 07-01-2010 |
20100189566 | Manufacturing a composite component - A composite component, such as an aerofoil component for a gas turbine engine, comprises a body and a platform which are formed from respective body and platform preforms. The body preform includes fibres which are directed laterally of the preform, forming a cavity in the end of the preform. The platform preform includes a projection constituting a deltoid filler which is received in the cavity. The projection includes a 3D woven structure of reinforcement fibres so that the cavity is occupied by fibres to give the platform a generally uniform volume fraction. A further platform preform fits over the body preform so that the lateral fibres are sandwiched between the platform preforms. | 07-29-2010 |
20100202891 | LOW-PRESSURE TURBINE ROTOR - The object of the invention is to provide a low-pressure turbine rotor capable of maintaining mechanical strength characteristics, and without problems in terms of quality without increasing manufacturing costs and manufacturing days, even if high temperature steam is introduced into the low-pressure turbine. A low-pressure turbine rotor used in a steam turbine facility including a high-pressure turbine, an intermediate-pressure turbine, and a low-pressure turbine includes a member formed from 1CrMoV steel, 2.25CrMoV steel, or 10CrMoV steel arranged on a steam inlet side, and a member formed from 3.5Ni steel arranged on a steam outlet side, which are joined together by welding. Alternatively, the member arranged on the steam inlet side and the member arranged on the steam outlet side, both of which are formed from 3.5Ni steel, are joined together by welding, and the member arranged on the steam inlet side is made of low-impurity 3.5Ni steel containing, by weight %, Si: 0.1% or less, Mn: 0.1% or less, and inevitable impurities containing, by weight %, P: 0.02% or less, S: 0.02% or less, Sn: 0.02% or less, As: 0.02% or less, Sb: 0.02% or less, Al: 0.02% or less, and Cu: 0.1% or less. | 08-12-2010 |
20100215506 | IMPELLER COATING - An impeller is provided with a back surface that is at least partly coated with a thermal barrier coating. The thermal barrier coating includes an anodized layer, polymer or polymer-based ceramics. | 08-26-2010 |
20100221118 | INTEGRALLY BLADED ROTATING TURBO MACHINERY AND METHOD AND APPARATUS FOR ACHIEVING THE SAME - A method and an apparatus for performing the method of inducing compressive residual stress in blading members integrally formed with a rotor. The method includes using a caliper-type burnishing tool such that the caliper arms of the tool are contoured and oriented for placing the burnishing elements on opposite sides of the blading member to be treated. The blading member is burnished to introduce a pre-determined pattern of residual compressive stresses in a selected area of the blade. | 09-02-2010 |
20100239429 | WEAR PROTECTION COATING - The English-language Abstract from the international application is to be retained and is therefore not duplicated in the specification. | 09-23-2010 |
20100247323 | Erosion barrier for thermal barrier coatings - A workpiece, such as a turbine engine component, comprises a substrate, a thermal barrier coating on the substrate, and a hard erosion barrier deposited over the thermal barrier coating. The erosion barrier preferably has a Vickers hardness in the range of from 1300 to 2750 kg/mm | 09-30-2010 |
20100247324 | WELDING MATERIAL AND WELDING ROTOR - The invention provides a Ni—Fe-based alloy which is preferable for a welding of a joint between different materials such as a steel material and a Ni-based alloy, and a rotor for a steam turbine which is manufactured by using the same. The invention employs a Ni—Fe-based alloy comprising Cr: 14 to 18%, Al: 1.0 to 2.5%, Mo+W: 2.5 to 5.0%, C: 0.01 to 0.10%, B: 0.001 to 0.03%, and Fe: 15 to 20%, in mass, in which the remaining portion is constructed by an unavoidable impurity and Ni, as a welding metal. As a result, it is possible to provide a rotor for a steam turbine which can hold down a reduction of a ductility and a toughness generated in the case of welding the different materials, and is excellent in a strength and the ductility. | 09-30-2010 |
20100254820 | Article with restored or regenerated structure - A restored or regenerated article including a residual substrate comprised of a first material and a restorative or regenerative layer of second material overlying at least a portion of the residual substrate. The second material is substantially similar in composition to the first material to promote an integral bond therebetween. The second material comprises the deposit of a suitable deposition process, i.e., vapor phase deposition, cathodic arc deposition, or sputtering. The restored/regenerated article includes an environmental coating at least partly diffused into the restorative or regenerative layer. The environmental coating comprises a deposit from a deposition process selected from vapor phase deposition, cathodic arc deposition, and combinations thereof. Heat treatments of about 2 hours or longer at temperatures between about 1500 ° F. to about 2300° F. (about 816° C. to about 1260° C.) to enhance the bond between the residual substrate and the restorative/regenerative layer. Surface characteristics of the restored/regenerated component may be enhanced by a suitable surface treatment such as grit blast polishing. | 10-07-2010 |
20100254821 | INTERMEDIATE-MANUFACTURED COMPOSITE AIRFOIL AND METHODS FOR MANUFACTURING - An intermediate-manufactured composite airfoil includes first and second composite skins each having a plurality of fibers in a polymer matrix. A composite core is removably located between the first and second composite skins. The composite core includes a dry, three-dimensional, woven fiber network. The composite core may alternatively include a three-dimensional, woven fiber network in a fully cured polymer matrix. | 10-07-2010 |
20100254822 | Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom - A nickel-base superalloy composition including (measured in % by weight) from about 6.5 to about 7.5% aluminum, from about 4 to about 8% tantalum, from about 3 to about 10% chromium, from about 2 to about 7% tungsten, from 0 to about 4% molybdenum, from 0 to about 6% rhenium, from 0 to less than about 0.001% niobium, from 0 to about 5% cobalt, from 0 to about 0.2% silicon, from 0 to about 0.06% carbon, optionally, from 0 to about 0.5% titanium, from 0 to about 0.005% boron, from about 0.15 to about 0.7% hafnium, from 0 to about 0.03% of a rare earth addition selected from the group consisting of yttrium, lanthanum, cesium, and combinations thereof, balance nickel and incidental impurities. The nickel-base superalloy composition may be used in single-crystal or directionally solidified superalloy articles such as high pressure turbine blades for a gas turbine engine. | 10-07-2010 |
20100260613 | Process for preventing the formation of secondary reaction zone in susceptible articles, and articles manufactured using same - A process for reducing secondary reaction zone formation articles includes the steps of non-selective removing an external surface of an as-cast article free of coating to form an as-cast article having a surface substantially free of residual surface stress; and applying a coating material upon the surface substantially free of residual surface stress to form a coated as-cast article having a coating layer disposed upon the surface substantially free of residual surface stress. | 10-14-2010 |
20100260614 | WIND TURBINE BLADE WITH SUBMERGED BOUNDARY LAYER CONTROL MEANS COMPRISING CROSSING SUB-CHANNELS - A wind turbine blade having a longitudinal direction with a root end and a tip end as well as a chord extending in a transverse direction between a leading edge and a trailing edge is described. The blade comprises a flow control surface with a suction side and a pressure side. A number of boundary layer control means is formed in the flow control surface. The boundary layer control means include a channel submerged in the flow control surface with a first end facing towards the leading edge and a second end facing towards the trailing edge of the blade. The channel further comprises a bottom surface extending from the first end to the second end. The channel at the first end comprises a first channel zone comprising a first sub-channel having a first cross-sectional area and a second sub-channel having a second cross-sectional area, the first sub-channel and the second sub-channel crossing each other at a point of crossing. | 10-14-2010 |
20100266417 | Bond coat with low deposited aluminum level and method therefore - A method for applying a NiAl based bond coat and a diffusion aluminide coating to a metal substrate is disclosed. The method comprises providing a superalloy substrate, the superalloy substrate having an external surface; and optionally cleaning the external surface of the superalloy substrate. The method further comprises coating a portion of the external surface of the superalloy substrate, by physical vapor deposition with a layer of a NiAl based metal alloy, wherein the deposited NiAl based metal alloy includes a controlled amount of about 6 to 25 weight percent aluminum and additionally the deposited aluminum level of the NiAl based metal alloy is controlled to be about 50-100% of its final level after aluminizing to form a coated external portion; and subsequently, simultaneously aluminizing the coated external portion and a different surface of the superalloy substrate. Advantageously, a diffusion aluminide layer is formed on the different surface and the NiAl based metal alloy becomes a NiAl based bond coat, wherein the NiAl based bond coat comprises between about 12 to 25 weight percent aluminum, and the NiAl based bond coat has a uniform distribution of aluminum and other modifying elements selected from at least one of Cr, Zr and Hf throughout the NiAl based bond coat. | 10-21-2010 |
20100266418 | Gas Turbine Blade and Manufacturing Method Thereof - In a gas turbine blade where a part of the γ′ phase precipitation strengthened type Ni-based alloy base material is composed of a weld metal, the weld metal is a Ni-based alloy containing Ta from 4.8 to 5.3 wt. %, Cr from 18 to 23 wt. %, Co from 12 to 17 wt. %, W from 14 to 18 wt. %, C from 0.03 to 0.1 wt. %, Mo from 1 to 2 wt. %, and Al of 1 wt. % or less, in which the oxygen content is 0 to 30 ppm, the Ti content from 0 to 0.1 wt. %, and the Re content from 0 to 0.5 wt. %. A blade base metal is manufactured by the step of stripping, the step of solution heat treatment where the γ′ phase is dissolved again, the step of welding in an inert gas chamber by a TIG method using a welding wire where the weld metal can be obtained, the step of HIP treatment at 1100° C. to 1150° C., and the step of an aging treatment at 835° C. to 855° C. | 10-21-2010 |
20100266419 | ENGINE COMPONENT FOR A GAS TURBINE - The object of the invention is an engine component for arrangement in the gas flow of a gas turbine. According to the invention, at least one part of the surface of said component subjected to the gas flow in operation comprises a modified amorphous carbon layer containing hydrogen that is applied using a vacuum coating technique. | 10-21-2010 |
20100272577 | Jet vane and method for manufacturing a jet vane - A jet vane for use in streams of hot gas, comprising a wing having a core area and a cover skin area surrounding the core area, is proposed. The cover skin area is made of a fiber-reinforced material, and the fibers in the cover skin area are oriented substantially parallel to the wing surface, and/or the cover skin area is made of a fiber-reinforced material that is reinforced with short fibers. | 10-28-2010 |
20100278657 | WIND TURBINE BLADE AND BLADE ELEMENT COMBINATION AND METHOD OF CHANGING THE AERODYNAMIC PROFILE OF A WIND TURBINE BLADE - A blade element ( | 11-04-2010 |
20100284817 | METHOD FOR PRODUCING A BLISK OR A BLING, COMPONENT PRODUCED THEREWITH AND TURBINE BLADE - A method for producing a blisk (bladed disk) or a bling (bladed ring) of a gas turbine is disclosed. The method includes the following steps: a) producing a turbine blade by joining a blade to an adapter element consisting of a metal material that is suitable for fusion welding, the adapter element being used to form a blade root of the turbine blade, and b) joining the turbine blade to a rotor disk consisting of a metal material that is suitable for fusion welding or to a rotor ring consisting of a metal material that is suitable for fusion welding in such a manner that the turbine blade is arranged on the outer periphery of the rotor disk or of the rotor ring. A component of a gas turbine or of a high-pressure or low-pressure compressor, especially a blisk or bling, and a turbine blade are also disclosed. | 11-11-2010 |
20100284818 | TURBINE BLADE CASCADE ENDWALL - Provided is a turbine blade cascade endwall that is capable of reducing crossflow and is capable of reducing secondary-flow loss that occurs in association with the crossflow, therefore being capable of achieving enhanced turbine performance. A convex portion ( | 11-11-2010 |
20100296943 | Thermal barrier coated materilas, method of preparation thereof, and method of coating using them - A sintered material for a thermal barrier coating is provided. The sintered material comprises Gd | 11-25-2010 |
20100322778 | Method and apparatus for improving turbocharger components - In one form, a turbocharger component, such as a compressor wheel or an impeller, formed of a cast material or a material made using a powder metal process, includes a surface having at least a portion thereof treated by a thermo-mechanical treatment process, such as friction stir processing. At the treated portion, the material forming the component includes a microstructure that is different than the microstructure of the material throughout the rest of the component. For example, in one form the material at the treated portion includes a homogenous microstructure while the material throughout the rest of the component includes a cast microstructure. In one or more forms, the treated portion exhibits at least one of increased strength, ductility and fatigue-resistant properties. In another form, a method is directed to providing components for a turbocharger which exhibit enhanced structural properties. However, other embodiments, forms and applications are also envisioned. | 12-23-2010 |
20100322779 | PROPELLER FAN - A propeller fan has a gap between a bellmouth and each blade tip. A leakage flow is thus produced from a positive pressure surface of a blade toward a negative pressure surface of the blade via the gap. The leakage flow develops while flowing from the leading edge of each blade toward the trailing edge, thus forming a blade tip vortex. This increases blowing noise and raises the input of the fan motor. In order to suppress the blade tip vortex caused by the leakage flow, the present invention includes recessed portions and projected portions, which are alternately formed in a portion of a blade surface of each blade corresponding to the blade tip. | 12-23-2010 |
20100322780 | SOLDER COATING, METHOD FOR COATING A COMPONENT, COMPONENT, AND ADHESIVE TAPE HAVING A SOLDER COATING - A solder coating ( | 12-23-2010 |
20100329883 | METHOD OF CONTROLLING AND REFINING FINAL GRAIN SIZE IN SUPERSOLVUS HEAT TREATED NICKEL-BASE SUPERALLOYS - A gamma prime precipitation-strengthened nickel-base superalloy and method of forging an article from the superalloy to promote a low cycle fatigue resistance and high temperature dwell behavior of the article. The superalloy has a composition of, by weight, 16.0-22.4% cobalt, 6.6-14.3% chromium, 2.6-4.8% aluminum, 2.4-4.6% titanium, 1.4-3.5% tantalum, 0.9-3.0% niobium, 1.9-4.0% tungsten, 1.9-3.9% molybdenum, 0.0-2.5% rhenium, greater than 0.05% carbon, at least 0.1% hafnium, 0.02-0.10% boron, 0.03-0.10% zirconium, the balance nickel and incidental impurities. A billet is formed of the superalloy and worked at a temperature below the gamma prime solvus temperature of the superalloy so as to form a worked article, which is then heat treated above the gamma prime solvus temperature of the superalloy to uniformly coarsen the grains of the article, after which the article is cooled to reprecipitate gamma prime. The article has an average grain size of not coarser than ASTM 7 and is substantially free of critical grain growth. | 12-30-2010 |
20100329884 | TURBINE ROTOR BLADE - A turbine rotor blade which is enhanced in erosion resistance and reduced in stress corrosion cracking sensitivity is provided. When a blade tip end of the turbine rotor blade is hardened by heat treatment, hardness at an outer circumferential side in a radial direction is made higher than hardness at an inner circumferential side, and thereby, enhancement in erosion resistance and reduction in stress corrosion cracking sensitivity are made compatible with each other all over in a blade length direction. | 12-30-2010 |
20110014059 | PRODUCTION METHOD OF A COATING LAYER FOR A PIECE OF TURBOMACHINERY COMPONENT, THE COMPONENT ITSELF AND THE CORRESPONDING PIECE OF MACHINERY - A method to produce a turbomachinery impeller, which includes, at least, the following steps: creation of the impeller using a light alloy, and coating of the impeller with a nickel-plating coating. | 01-20-2011 |
20110014060 | Substrate Features for Mitigating Stress - An article may include an array of features formed in a substrate and may be coated with a coating layer. The array of features may mitigate stress experienced by the coated article. In particular, the array of features may reduce or limit crack propagation at the interface between the substrate and the coating layer. In some examples, the article is an airfoil that includes a tip that defines an edge. An array of features is formed on the surface of the tip, where the array of features is proximate to the edge, and the array of features does not intersect the edge. The airfoil includes a coating layer formed on the surface of the tip and the array of features. | 01-20-2011 |
20110020134 | LIGHTNING RECEPTORS COMPRISING CARBON NANOTUBES - The present invention relates to a wind turbine rotor blade comprising a lightning protection system. The lightning protection system comprises a lightning receptor for capturing lightning strikes. The receptors are arranged in the rotor blade. The lightning receptors comprise carbon nanotubes. In embodiments, the nanotubes are at an exterior surface is provided with a layer of carbon nanotubes and/or at least part of the lightning receptor is of a carbon nanotube metal composite material, such as a carbon nanotube metal matrix composite material. Moreover, the exterior surface of the receptor may in embodiments be provided with one or more electric field enhancing protrusions. | 01-27-2011 |
20110027099 | METAL COMPONENT, TURBINE COMPONENT, GAS TURBINE ENGINE, SURFACE PROCESSING METHOD, AND STEAM TURBINE ENGINE - Formation of a protective coating having oxidation resistance on a portion to be processed of a component main body by employing an electrode composed of a molded body molded from mixed powders of one or more of an aluminum powder, an aluminum alloy powder, a chromium powder and a chromium alloy powder, or the molded body processed with a heat treatment, generating a pulsing electric discharge between the portion to be processed of the component main body and the electrode in an electrically insulating liquid or gas so that an electrode material of the electrode is adhered to the portion to be processed of the component main body by energy of the electric discharges, and further keeping the portion to be processed of the component main body and the electrode material adhered thereto in high temperatures so that the electrode material adhered thereto diffuses into a base material of the component main body. | 02-03-2011 |
20110038733 | BLADE FOR A ROTATING THERMAL MACHINE - A blade for a rotating thermal machine, such as a stator blade for a low-pressure turbine of a gas turbine with sequential combustion, includes a blade airfoil which extends essentially in the radial direction, is exposed to circumflow by an operating medium in a flow direction, and is delimited by a leading edge and a trailing edge in the flow direction. The concurring fluidic and constructional demands on the blade with sharp inclination of the flow are met by the blade airfoil being structured in such a way that an angle which the flow lines form with the trailing edge of the blade airfoil deviates from a right angle within a limited range. | 02-17-2011 |
20110044821 | Methods and apparatus for coating gas turbine engines - A method of fabricating a component for a gas turbine engine is provided. The method includes applying a bond coat to at least a portion of the component, applying a dense vertically cracked (DVC) thermal barrier coating to at least a portion of the bond coat using a spray mechanism positioned a first distance from the component, and overlying at least a portion of the DVC thermal barrier coating with a soft coat thermal barrier coating using a spray mechanism that is positioned a second distance away from the component, wherein the second distance is greater than the first distance to facilitate adherence of the soft coating thermal barrier coating to the DVC thermal barrier coating. | 02-24-2011 |
20110052406 | AIRFOIL AND PROCESS FOR DEPOSITING AN EROSION-RESISTANT COATING ON THE AIRFOIL - A process for depositing coatings, and particularly erosion-resistant coatings suitable for protecting surfaces subjected to collisions with particles, such as a compressor blade of a gas turbine engine. The blade has an airfoil comprising oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, and a blade tip. An erosion-resistant coating is present on at least the concave surface, but not on the convex surface within at least 20% of the chord length from the leading edge. | 03-03-2011 |
20110052407 | SWEPT BLADES UTILIZING ASYMMETRIC DOUBLE BIASED FABRICS - A swept turbine blade may include a blade shell formed from a variety of fabric types, including an asymmetric double-biased fabric. This asymmetrical double-biased fabric may include fibers with a crossing angle of less than 80°. The fabric may alternately include fibers of a first type or fraction extending in one direction and fibers of a different type or fraction extending in a second direction. This fabric may be curved in the direction of the blade sweep when used in the swept turbine blade. | 03-03-2011 |
20110052408 | SWEPT BLADES UTILIZING ASYMMETRIC DOUBLE BIASED FABRICS - A swept turbine blade may include a blade shell formed from a variety of fabric types, including an asymmetric double-biased fabric. This asymmetrical double-biased fabric may include fibers with a crossing angle of less than 80°. The fabric may alternately include fibers of a first type or fraction extending in one direction and fibers of a different type or fraction extending in a second direction. This fabric may be curved in the direction of the blade sweep when used in the swept turbine blade. | 03-03-2011 |
20110052409 | PROCESS AND ALLOY FOR TURBINE BLADES AND BLADES FORMED THEREFROM - A process and alloy for producing a turbine blade whose properties enable the blade to operate within a steam turbine at maximum operating temperatures of greater than 1300° F. (about 705° C.). The process includes casting the blade from a gamma prime-strengthened nickel-base superalloy having a composition of, by weight, 14.25-15.75% cobalt, 14.0-15.25% chromium, 4.0-4.6% aluminum, 3.0-3.7% titanium, 3.9-4.5% molybdenum, 0.05-0.09% carbon, 0.012-0.020% boron, maximum 0.5% iron, maximum 0.2% silicon, maximum 0.15% manganese, maximum 0.04% zirconium, maximum 0.015% sulfur, maximum 0.1% copper, balance nickel and incidental impurities, and an electron vacancy number of 2.32 maximum. The casting then undergoes a high temperature solution heat treatment to promote resistance to hold-time cracking. The blade exhibits a combination of yield strength, stress rupture properties, environmental resistance, and cost in steam turbine applications to 1400° F. (about 760° C.). | 03-03-2011 |
20110058950 | PROTECTING FILM FOR BLADE OF WIND POWER GENERATOR - The present invention provides a protection film for blades to be adhered to the blade surface of wind power generators, which has a substrate and a pressure-sensitive adhesive layer on one surface of the substrate. | 03-10-2011 |
20110058951 | TURBINE BLADE OF A GAS TURBINE AND METHOD FOR COATING A TURBINE BLADE OF A GAS TURBINE - A turbine blade of a gas turbine is disclosed. The turbine blade includes a blade pan, a blade root, and a platform positioned between the blade pan and the blade root. The turbine blade is provided with an anti-corrosion coating at least in regions, in particular on a lower side of the platform and/or in the transition region between the lower side of the platform and the blade root. The anti-corrosion coating is a diffusion coating having a chromium content in the surface region of more than 30% by weight. | 03-10-2011 |
20110058952 | HIGH-TEMPERATURE ANTI-CORROSIVE LAYER AND METHOD FOR THE PRODUCTION THEREOF - A method for producing a high-temperature protective layer containing metal on a metallic high-temperature material is disclosed. The metal is deposited on the high-temperature material via the gaseous phase to form the high-temperature protective layer. The high-temperature material is held at a diffusion temperature for a specific length of time so that at least a portion of the deposited metal is diffused into the high temperature material to form a diffusion zone and where the high-temperature material is not in contact with solids or liquids in the region of the surface to be coated, but merely has a solid/gas interface. Also disclosed is a component made of a high-temperature material with a hot-gas anti-corrosive layer containing chromium. There is a coating layer containing chromium applied to the surface of the high-temperature material, a diffusion layer in the high-temperature material, and a build-up zone between the coating layer and the diffusion layer. | 03-10-2011 |
20110058953 | TURBINE BLADE - A turbine blade is provided having an airfoil and a platform manufactured in two separate pieces, which are joined together. The blade includes a seal, which is a mechanically decoupled seal, interposed between the airfoil and platform in a position closer to a hot gases path than a joint. | 03-10-2011 |
20110058954 | Nickel base alloy and use of it, turbine blade or vane and gas turbine - A nickel base alloy is provided which includes the following components by weight: Co: 2.75 to 3.25% Cr: 11.5 to 12.5% Mo: 2.75 to 3.25% Al: 3.75 to 4.25% Ti: 4.1 to 4.9% Ta: 1.75 to 2.25% C: 0.006 to 0.04% B: ≦0.01% Zr: ≦0.01% Hf: ≦1.25% Nb: ≦1.25% balance Ni. | 03-10-2011 |
20110058955 | ROTOR BLADE FOR ROTARY WING AIRCRAFT HAVING DEFORMABLE PROTRUSIONS TO REDUCE BLADE VORTEX INTERACTION NOISE - A rotor blade for a rotary wing aircraft, which rotates about and is combined with a rotation shaft of the rotary wing aircraft. The rotor blade includes a body combined with the rotation shaft and including a leading edge that is a front edge in a direction of rotation; and a plurality of deformable protrusions formed on the leading edge of the body in a radial direction of rotation, and deformable between a first shape protruding forward in the direction of rotation and a second shape not protruding forward in the direction of rotation such that BVI noise generated when a vortex formed near a blade tip collides with the rotor blade is selectively reduced whenever necessary. The deformable protrusions are formed in a region from a point spaced apart from the rotation shaft by 75% of a radius of rotation to a point spaced apart from the rotation shaft by 90% of the radius of rotation. | 03-10-2011 |
20110064584 | APPARATUS AND METHOD FOR A TURBINE BUCKET TIP CAP - A turbine bucket that includes a pressure side, a suction side opposite the pressure side, and a rib extending between the pressure side and the suction side. A tip cap is attached to the pressure side and the suction side and covers the rib. The tip cap includes a precipitation hardened material and a passage aligned with the rib. A method for assembling a turbine bucket having a pressure side and a suction side and a rib extending between the pressure side and suction side. The method includes receiving a tip cap made from a precipitation hardened material and having a passage in the tip cap. The method further includes locating the rib visually through the passage and aligning the passage with the rib. The method also includes welding the tip cap to the turbine bucket and to the rib. | 03-17-2011 |
20110070093 | COATING OF METALLIC ARTICLES TO RESTRICT ICE ACCUMULATION - An anti-icing coated metallic substrate includes molecules of an anti-icing material chemically bonded to the metallic substrate. | 03-24-2011 |
20110076152 | VENTILATOR WHEEL OR FAN WHEEL WITH ANTIBACTERIAL COATING - The present invention relates to a ventilator wheel or fan wheel composed of a hub and blades which are fastened in said hub. The hub and/or the blades are at least partially provided, on the surface thereof, with an antibacterial agent. | 03-31-2011 |
20110081251 | FREE-STANDING, IMMERSIBLE POWER GENERATION PLANT COMPRISING AN AXIAL TURBINE - The invention relates to an immersible power generation plant driven by a water flow, particularly a tidal current, comprising a water turbine in the form of an axial turbine with an associated rotational axis. The water turbine comprises at least one turbine blade that is designed such that the course of the threading line of the profile sections thereof deviates from the radial flow when projected on the rotational plane. | 04-07-2011 |
20110081252 | Vane or blade for an axial flow compressor - A compressor vane or compressor blade is provided. The axial flow compressor includes an axial direction, a radial direction, a compressor hub and a compressor casing. The vane or blade includes an airfoil with airfoil sections having a span, a chamber line and a leading edge at which the chamber line includes a leading edge blade angle with the axial direction of the compressor and a trailing edge at which the chamber line includes a trailing edge blade angle with the axial direction of the compressor. The airfoil sections are stacked at the leading edge on a straight line extending along a radial direction of the compressor from the compressor hub towards a compressor casing and in that the leading edge angles of the airfoil sections vary along the span and are larger for airfoil sections close to the hub and close to the wall than for mid-span airfoil sections. | 04-07-2011 |
20110085912 | PROPELLER FOR A WIND MOTOR - A propeller ( | 04-14-2011 |
20110085913 | Integrally rotating turbo machinery and method and apparatus for achieving the same - A method of inducing compressive residual stress of blading members integrally formed with a rotor. The method includes using a caliper-type burnishing tool such that the caliper arms of the tool are contoured and oriented for placing the burnishing elements on opposite sides of the blading member to be treated. The blading member is burnished to introduce a pre-determined pattern of residual compressive stresses in a selected area of the blade. | 04-14-2011 |
20110103967 | ABRASIVE SINGLE-CRYSTAL TURBINE BLADE - A turbine blade for a turbine rotor, is provided having a single-crystal basic body which has a blade tip and extends in the radial direction. The turbine blade includes at least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on the radially outer blade tip, and in that an at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and consists of oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least certain regions of said epitaxial intermediate coating. | 05-05-2011 |
20110103968 | WEAR-RESISTANT AND OXIDATION-RESISTANT TURBINE BLADE - A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there. | 05-05-2011 |
20110110788 | BLADE WITH 3D PLATFORM COMPRISING AN INTER-BLADE BULB - A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface. | 05-12-2011 |
20110110789 | BLADE TIP FOR A ROTOR BLADE OF A WIND TURBINE AND A METHOD OF INSERTING THE BLADE TIP INTO A ROTOR BLADE - A blade tip for a rotor blade of a wind turbine, and a method of inserting the blade tip into a rotor blade are provided. The blade tip for the rotor blade of a wind turbine simplifies the installation and the replacement of the blade tip as well as a method of inserting such a blade tip. The blade tip can be inserted by means of an adjustable clamping wedge so as to simplify replacement of the tip if necessary. The associated method of inserting the blade tip outside the shell mould removes the likelihood of damage to the shell mould due to sawing. | 05-12-2011 |
20110123347 | WELDING REPAIR METHOD OF AN INTEGRALLY BLADED ROTOR - A method of repairing a rotor blade, for example on an integrally bladed rotor, includes preparing a surface on a damaged area of the blade. The blade has first and second airfoil surfaces adjoining the prepared surface that are spaced apart a distance. An edge of a patch abuts the prepared surface to provide a weld interface defining a welding plane. First and second cover sheets respectively overlap the first and second airfoil surfaces. The first and second cover sheets adjoin the edge and the first and second airfoil surfaces. The blade, patch and first and second cover sheets are welded along the welding plane providing a welded joint at the weld interface. The first and second cover sheets are substantially unsecured to the first and second airfoil surfaces subsequent to the welding operation. | 05-26-2011 |
20110123348 | FAN AND PROPELLER PERFORMANCE ENHANCEMENTS USING OUTSIZED GURNEY FLAPS - The present invention relates to enhancing performance of fans and propellers using outsized Gurney flaps. Specifically, the current invention proposes the application of ‘outsized Gurney flaps’ (OGFs) to the trailing-edges of fan blades. According to an exemplary embodiment of the current invention, the Gurney flaps are larger than 10% of the fan blade chord length. Attaching OGFs is not only non-obvious; it seems counterintuitive, because it is akin to placing a large bluff body onto a flow. Preliminary experimental data acquired at Reynolds numbers typically exist during fan operation on idealized blade profiles showed a 100% increase in the generated lift and 40% to 60% increase in aerodynamic efficiency. This translates to significant improvements in fan performance at a given rpm, and/or significant saving in power and noise reduction for the same aerodynamic performance. The current invention may increase performance, may decrease energy consumption, may decrease size, may decrease cost, and may increase performance of: computer cooling fans, personal upright and ceiling fans, refrigeration fans, air conditioning fans, automotive fans, ventilation, vacuuming, small-scale propellers, etc. | 05-26-2011 |
20110123349 | NOTCHED TORQUE CONVERTER BLADE - A hydraulic torque transferring assembly comprising a shell, at least one blade installed in the shell, the blade having an inlet for receiving a flow of fluid, wherein the blade includes a notch, wherein the notch is operatively arranged to reduce a pressure that the flow of fluid exerts on the inlet, and wherein the assembly is for a turbine or an impeller in a torque converter. | 05-26-2011 |
20110123350 | HOLLOW TURBINE WHEEL VANE COMPRISING A RIB AND ASSOCIATED WHEEL AND TURBOMACHINE - A turbine blade extends radially between a blade root and a blade tip having an open cavity referred to as a bathtub formed therein, which cavity is defined by a closed end wall and a side rim. The side rim of the cavity carries at least one rib extending between a leading edge and a trailing edge of the blade. | 05-26-2011 |
20110129353 | METHODS FOR JOINING A MONOCRYSTALLINE PART TO A POLYCRYSTALLINE PART BY MEANS OF AN ADAPTER PIECE MADE OF POLYCRYSTALLINE MATERIAL - The present invention relates to methods for joining a rotationally asymmetrical part, preferably a turbine blade, which is made of a monocrystalline material, to a part, preferably a rotor core, which is made of polycrystalline material, having the method steps of:—joining the rotationally asymmetrical part to an adapter piece made of polycrystalline material by means of rotational friction welding, and—joining the adapter piece to the part made of polycrystalline material. The present invention also relates to a turbine blisk having a rotor core made of polycrystalline material and turbine blades made of monocrystalline material. | 06-02-2011 |
20110135489 | NICKEL-BASED SUPERALLOYS, TURBINE BLADES, AND METHODS OF IMPROVING OR REPAIRING TURBINE ENGINE COMPONENTS - Nickel-based superalloys, turbine blades, and methods of improving or repairing turbine engine components are included. A nickel-based superalloy includes, by weight, about 5% to about 12% cobalt, about 3% to about 10% chromium, about 5.5% to about 6.3% aluminum, about 5% to about 10% tantalum, about 3% to about 10% rhenium, about 2% to about 5% of one or more of elements selected from a group consisting of platinum, ruthenium, palladium, and iridium, about 0.1% to about 1.0% hafnium, about 0.01% to about 0.4% yttrium, about 0.01% to about 0.15% silicon, and a balance of nickel. | 06-09-2011 |
20110135490 | WIND TURBINE ROTOR BLADE - A rotor blade for a wind turbine is disclosed. The rotor blade includes a flange section configured to connect the rotor blade to a rotor hub; and an airfoil section extending outward from the flange section. The flange section is comprised of a carbon reinforced polymer. | 06-09-2011 |
20110135491 | CNT-TAILORED COMPOSITE LAND-BASED STRUCTURES - An apparatus having a composite land-based structure with a first carbon nanotube infused material and a second carbon nanotube infused material. The first and second carbon nanotube infused materials each having a range of carbon nanotube loading selected to provide different functionalities. | 06-09-2011 |
20110142673 | WIND TURBINE BLADES WITH AERODYNAMIC VORTEX ELEMENTS - A wind turbine blade had a suction side surface and a pressure side surface. A plurality of vortex elements are formed on at least one of the suction side or the pressure side surfaces. The vortex elements have an upwardly inclined wind face and a downwardly inclined slip face, with the wind face and slip face meeting at a generally open-ended U-shaped ridge that defines side horns. The side horns decrease in height from a forward most portion of the ridge to the suction side surface or pressure side surface. | 06-16-2011 |
20110142674 | WIND TURBINE BLADES WITH IMPROVED BOND LINE - A wind turbine blade includes an upper shell member and a lower shell member defining an internal cavity therebetween. The shell members are joined with a bond paste along bond lines at the leading edge and trailing edge of the blade. A seal member is disposed between the upper and lower shell members at a designed width of the bond line along at least one of the trailing or leading edges. The seal member has a configuration such that excess towable bond paste is prevented from migrating past the seal member and into the internal cavity upon mating the upper and lower shell members in assembly of the blade. | 06-16-2011 |
20110142675 | WIND TURBINE ROTOR BLADE JOINT - A blade segment is disclosed for a rotor blade formed from a plurality of blade segments, the blade segment having a span and a chord. The blade segment includes a shell segment having a pressure side and a suction side extending between a leading edge and a trailing edge, the shell segment further having a tip end and a root end. The blade segment further includes at least one joint portion projecting from the shell segment at one of the tip end or the root end and defining a generally span-wise extending joining surface. The joint portion allows the blade segment to be coupled to an adjacent blade segment with a mating joint portion. | 06-16-2011 |
20110142676 | ROTOR BLADE ASSEMBLY HAVING AN AUXILIARY BLADE - A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly may generally include a primary rotor blade and an auxiliary rotor blade disposed on a suction side of the primary rotor blade. The auxiliary blade may generally include an upstream edge and a downstream edge, with the upstream edge being positioned downstream of a leading edge of the primary rotor blade. | 06-16-2011 |
20110142677 | WINGLET FOR WIND TURBINE ROTOR BLADE - A rotor blade for a wind turbine is disclosed. The rotor blade includes a root, a tip, and a body extending from the root, the body including a pressure side and a suction side extending between a leading edge and a trailing edge. The rotor blade further includes a winglet extending between the body and the tip, the winglet including a pressure side and a suction side extending between a leading edge and a trailing edge. The winglet further includes a transition section and defines a height, a sweep angle, an outboard cant angle, and a twist angle. The sweep angle, the outboard cant angle, and the twist angle change continuously throughout the transition section. | 06-16-2011 |
20110142678 | EROSION PROTECTION COATING FOR ROTOR BLADE OF WIND TURBINE - A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes an erosion protection coating configured on a surface of the rotor blade. The erosion protection coating includes a ceramic layer, the ceramic layer having a thickness of less than approximately 10 millimeters. The ceramic layer is configured to reduce erosion of the rotor blade. | 06-16-2011 |
20110142679 | ROTOR BLADE FOR A WIND TURBINE, METHOD AND MANUFACTURING MOLD FOR THE PRODUCTION THEREOF - A rotor blade and a method and a manufacturing mold for the production of a rotor blade for a wind turbine, which extends longitudinally in the operational state from a blade root area to the connection to a rotor hub of the wind turbine and which is divided into at least two segments for its production, wherein at least one subdivision is provided approximately transverse to its longitudinal extension between the blade root area and the blade tip. The method facilitates and shortens the production of the rotor blade, in particular for a series production and to still provide the completed rotor blade as a familiar uniform rotor blade. In the method, the at least two segments, preferably after they have been at least partially produced or partially produced mainly parallel in time, are interconnected in an integration device. | 06-16-2011 |
20110150664 | AEROACOUSTIC ROTOR BLADE FOR A WIND TURBINE, AND WIND TURBINE EQUIPPED THEREWITH - A rotor blade and a wind turbine is provided that has such a rotor blade, wherein the absolute length L of the rotor blade extends from the blade attachment to the blade tip and the relative blade length x/L proceeds from the blade attachment. The rotor blade is divided into an inner longitudinal section L | 06-23-2011 |
20110164988 | TURBOCHARGER AND COMPRESSOR IMPELLER THEREFOR - The invention relates to a compressor impeller for a turbocharger, in particular in a diesel engine, and to an exhaust gas turbocharger containing such a compressor impeller. | 07-07-2011 |
20110182748 | CENTRIFUGAL IMPELLER - A centrifugal impeller includes a body of antistatic plastic and a back plate made of metal, preferably aluminium. The back plate is fixed to the body is such a way that the back plate can not make accidental contact with a volute of a blower in which the impeller is deployed. | 07-28-2011 |
20110182749 | TURBOCHARGER AND ADJUSTABLE BLADE THEREFOR - An adjustable blade for turbocharger applications, particularly in diesel engines, is described, which consists of an iron-based alloy with an austenitic basic structure with dendritic carbide precipitations. | 07-28-2011 |
20110189026 | MATERIAL FOR A GAS TURBINE COMPONENT, METHOD FOR PRODUCING A GAS TURBINE COMPONENT AND GAS TURBINE COMPONENT - A material for a gas turbine component, to be specific a titanium-aluminum-based alloy material, including at least titanium and aluminum. The material has a) in the range of room temperature, the β/B2-Ti phase, the α | 08-04-2011 |
20110206532 | ELECTROLESS METAL COATINGS - The present invention provides a method for preparing an electroless nickel coating composition that includes (a) coating a substrate with an electroless nickel coating to provide a coated substrate; and (b) subjecting the coated substrate to a heating protocol comprising heating to a temperature in a range from about 550° C. to about 700° C. for a period of from about 7 to about 30 hours. An article made from the method is also provided. | 08-25-2011 |
20110206533 | REPAIR OF A COATING ON A TURBINE COMPONENT - A method is provided for repairing an area of damaged coating on a component of a turbine module in a gas turbine engine, the component formed of a base material having a diffusion coating applied to the base material. The repair may be accomplished in place by directly heating the area to which a touch-up coating material has been applied with a hot gas plasma without the need to place the component in an oven for curing and heat treatment of the touch-up coating applied to the damaged area. | 08-25-2011 |
20110206534 | WIND TURBINE BLADE WITH MODULAR LEADING EDGE - A wind turbine blade has a leading edge and a trailing edge and includes an upper shell member and a lower shell member. The shell members include transversely spaced attachment edge that are spaced rearward of the leading edge. A preformed bond cap having opposite legs with rearward edges is mounted to the attachment edges of the upper and lower shell members. The bond cap is preformed into an aerodynamic parabolic shape and size so as to define the leading edge of said blade and lie essentially flush with the upper and lower shell members. The bond cap defines a primary external bonding bridge between the upper and lower shell members and defines at least a portion of the leading edge of the blade. | 08-25-2011 |
20110211971 | ROTOR BLADE FOR A WIND POWER PLANT, WIND POWER PLANT AND METHOD FOR THE PRODUCTION OF A ROTOR BLADE - A rotor blade ( | 09-01-2011 |
20110217178 | TURBINE AIRFOIL HAVING OUTBOARD AND INBOARD SECTIONS - A turbine airfoil usable in a turbine engine and formed from at least an outboard section and an inboard section such that an inner end of the outboard section is attached to an outer end of the inboard section. The outboard section may be configured to provide a tip having adequate thickness and may extend radially inward from the tip with a generally constant cross-sectional area. The inboard section may be configured with a tapered cross-sectional area to support the outboard section. | 09-08-2011 |
20110223034 | WIND TURBINE ROTOR BLADE - A rotor blade for a wind turbine is disclosed. In one embodiment, the rotor blade includes a tip, a root, and a body extending between the tip and the root. The body has surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge. The body further defines an inboard portion, an outboard portion, and a bend therebetween. The bend is defined such that the outboard portion extends outwardly with respect to the inboard portion. The bend is stiffened to reduce opening of the bend during deflection of the rotor blade. | 09-15-2011 |
20110236215 | WIND TURBINE CONTROL SURFACE HINGE - A wind turbine rotor blade has a plurality of trailing edge flaps, the upper surfaces of which are formed as a continuation of the blade skin. The flap deflects about a hinge line in the skin. The hinge line has a plurality of spaced apart slots to prevent the hinge from popping up as the blade deflects in a flapwise direction. The slots are filled with a soft deformable material and the skin around the slots is reinforced during the manufacturing process. | 09-29-2011 |
20110243751 | WIND TURBINE BLADES WITH A HARDENED SUBSTRATE CONSTRUCTION - A wind turbine blade includes an upper shell member and a lower shell member joined at leading and trailing edges of the blade with a bond material. Portions of the bond material are externally exposed. The bond material has surface characteristics of at least one of a Shore D hardness value of greater than about 80 durometer or a Young's modulus stiffness value of greater than about 5 GPa. A protective coating is applied over the upper and lower shell members and exposed portions of the bond material. | 10-06-2011 |
20110243752 | METHOD FOR MANUFACTURING A RECTIFIER - The present invention relates to a method for manufacturing a turbine-engine composite rectifier comprising a ferrule provided with a plurality of stator vanes ( | 10-06-2011 |
20110243753 | WIND TURBINE BLADE HAVING A FLOW GUIDING DEVICE WITH OPTIMISED HEIGHT - A wind turbine blade with a flow guiding device attached to a profiled contour on a pressure side of the blade is described. The flow guiding device extends along at least a longitudinal part of a transition region of the blade and is arranged so as to generate a separation of airflow along at least a central longitudinal portion of the flow guiding device from the pressure side of the blade at a point between the flow guiding device and a trailing edge of the blade, when the blade is impacted by an incident airflow. The flow guiding device is arranged at a relative chordal position, seen from the leading edge of the blade, lying in an interval between 40% and 92%. The relative height of the flow guiding device is at least 10% of a maximum thickness of the profiled contour. | 10-06-2011 |
20110250076 | WIND TURBINE BLADE HAVING A SPOILER WITH EFFECTIVE SEPARATION OF AIRFLOW - A wind turbine blade with a flow guiding device attached to a profiled contour on a pressure side of the blade is described. The flow guiding device extends along at least a longitudinal part of a transition region of the blade and is arranged so as to generate a separation of airflow along at least a central longitudinal portion of the flow guiding device from the pressure side of the blade at a point between the flow guiding device and a trailing edge of the blade, when the blade is impacted by an incident airflow. The inflow surface, in at least the central longitudinal portion, is formed so that, for each transverse cross-section, a end point tangent to the inflow surface at the end point crosses the profiled contour at a crossing point, where the profiled contour has a profile tangent to the profiled contour, and wherein an angle between the profile tangent and the end point tangent is at least 45 degrees. | 10-13-2011 |
20110255988 | PRECIPITATION HARDENABLE MARTENSITIC STAINLESS STEEL AND STEAM TURBINE BLADE USING THE SAME - A precipitation hardenable martensitic stainless steel excellent in the stability of martensite, having the high strength, high toughness and high corrosion resistance is provided. The precipitation hardenable martensitic stainless steel contains at a mass rate, C: 0.05-0.10%, Cr: 12.0-13.0%, Ni: 6.0-7.0%, Mo: 1.0-2.0%, Si: 0.01-0.05%, Mn: 0.06-1.0%, Nb: 0.3-0.5%, V: 0.3-0.5%, Ti: 1.5-2.5%, Al: 1.0-2.3%, and the remainder consisting of Fe and an unavoidable impurity. | 10-20-2011 |
20110268578 | HIGH PITCH-TO-CHORD TURBINE AIRFOILS - A low pressure turbine engine component for use in an engine, for propelling a vehicle such as an aircraft is formed by a disk portion and a plurality of low pressure turbine blades extending outwardly from the disk portion. Each of the low pressure turbine blades has an airfoil portion with an axial chord length and a trailing edge. The low pressure turbine blades are spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein the pitch is a distance between the trailing edges of adjacent ones of the low pressure turbine blades and the chord is the axial chord length of the blades. | 11-03-2011 |
20110274553 | Method for Manufacturing a Wind Turbine Rotor Blade and Wind Turbine Rotor Blade - A method for manufacturing a wind turbine rotor blade is described. Composite material is placed around a moulding core arrangement. The moulding core arrangement includes a first moulding core and a second moulding core. The composite material is set forming a wind turbine rotor blade. The wind turbine rotor blade includes a root portion and a shoulder portion. The first moulding core is removed from the wind turbine rotor blade through an opening at the root portion. The second moulding core is removed from the wind turbine rotor blade through an opening at the shoulder portion. | 11-10-2011 |
20110274554 | DUCTILE EXPANDED POLYESTERS HAVING HIGH IMPACT RESISTANCE - This invention relates to expanded polyester materials comprised of polyester/acrylic elastomer blend having an improved ductility and impact resistance, while the compression strength, shear strength/modulus of polyesters remain almost unchanged or unworsened. Addition of a non-reactive/reactive acrylic mixture serving as the blend partner improves the melt strength in an expanding process and leads to a better impact resistance of expanded aromatic polyester materials. All expanded polyester materials are produced with help of a reactive process. | 11-10-2011 |
20110274555 | PRODUCTION METHOD OF LEADING EDGE REINFORCEMENT OF FAN BLADE - A production method uses ultrasonic forming but does not leave a bonding face exposed to the exterior in a final product. | 11-10-2011 |
20110286854 | AIRFOIL COMPONENT - An airfoil component includes an aluminum alloy body having at least an airfoil portion and a root portion. A metallic layer is located on at least a portion of the aluminum alloy body and an electrochemically insulating layer is located between and adjoining the aluminum alloy body and the metallic layer. | 11-24-2011 |
20110286855 | JACKET IMPELLER WITH FUNCTIONAL GRADED MATERIAL AND METHOD - Devices and methods provide for an impeller for use in a compressor. A method for manufacturing the impeller includes: attaching an intermediate layer to a base metal by placing a first metal powder into a gap between a first insert and the base metal; processing with hot isostatic pressing the base metal, the first metal powder and the first insert such that the intermediate layer is bonded to the base metal; attaching an external layer to the intermediate layer by placing a second powder into a gap between a second insert and the intermediate layer; processing the base metal, the intermediate layer, the second metal powder and the second insert via hot isostatic pressing such that the external layer is bonded to the intermediate layer; and removing the second insert to form the impeller, wherein the external layer is corrosion resistant. | 11-24-2011 |
20110286856 | AIRFOIL FOR A COMPRESSOR BLADE - The present disclosure provides an improved second 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 |
20110293438 | PUMP WITH AXIAL CONDUIT - In one aspect, a pump for moving air includes an inlet, an outlet, an outer housing adapted to couple to an inflatable device, and an inner housing located within the outer housing. An air conduit is defined between the inner housing and the outer housing. A motor is at least partly positioned within the inner housing, and a plurality of vanes are positioned within the air conduit. | 12-01-2011 |
20110299996 | ANTI-EROSION COATING SYSTEM FOR GAS TURBINE COMPONENTS - A gas turbine component and a method for producing an anti-erosion coating system are disclosed. The gas turbine component includes a basic material, on which an anti-erosion coating system is provided that is a multilayer system including at least one ductile metal layer and at least one hard, ceramics-containing layer for forming a partial anti-erosion system. At least one anti-corrosion layer that has a lower electrochemical potential than the basic material is provided between the partial anti-erosion system and the basic material, thus providing cathodic corrosion protection. | 12-08-2011 |
20120003101 | CASTING METHOD FOR MANUFACTURING A WORK PIECE - A method for manufacturing a work piece is provided. The method includes preparing fibreglass in a mould, preparing a closed mould cavity around the fibreglass, flushing the closed mould cavity with an oxygen-free gas, injecting resin in the closed mould cavity, and curing the casted work piece. Furthermore, a work piece manufactured by the above method is provided | 01-05-2012 |
20120003102 | DENSE VERTICALLY CRACKED THERMAL BARRIER COATINGS - This invention relates to dense, vertically cracked thermal barrier coatings made from high purity yttria or ytterbia stabilized zirconia powders. The high purity yttria or ytterbia stabilized zirconia powder consisting essentially of less than about 0.01 weight percent silicon dioxide (silica), less than about 0.002 weight percent aluminum oxide (alumina), less than about 0.005 weight percent calcium oxide, less than about 0.005 weight percent ferric oxide, less than about 0 to about 0.002 weight percent magnesium oxide, less than about 0 to about 0.005 weight percent titanium dioxide, from about 1.5 to about 2 weight percent hafnium oxide (hafnia), from about 6 to about 25 weight percent yttrium oxide (yttria), less than 0.1 weight percent other impurity oxides, and the balance zirconium oxide (zirconia) and the balance zirconium oxide (zirconia). The thermal barrier coatings are intended to be used in cyclic thermal environments such as for gas turbine blades, vanes and seal surfaces exposed in the hot section of gas turbine engines. | 01-05-2012 |
20120020804 | TURBINE NOZZLE SEGMENT HAVING ARCUATE CONCAVE LEADING EDGE - Turbine nozzle segments with trimmed leading edges are disclosed. In one embodiment of the invention, a turbine static nozzle airfoil includes: an arcuate concave leading edge; and a substantially flat trailing edge. | 01-26-2012 |
20120020805 | REVERSE CAVITY BLADE FOR A GAS TURBINE ENGINE - A rotor blade for a turbine engine includes an airfoil section which extends from a platform section opposite a root section, the airfoil section defines a cavity which extends from an airfoil tip section toward a root section. | 01-26-2012 |
20120020806 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE VANE, IN PARTICULAR FOR A NOZZLE OF THE FOURTH 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 PO situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P | 01-26-2012 |
20120027617 | TURBINE NOZZLE SEGMENT AND METHOD OF REPAIRING SAME - A method is provided for repairing a metallic turbine component which includes at least two airfoils interconnected by a mid-span shroud. The method includes: (a) applying a reinforcement plate to the mid-span shroud; (b) applying braze material to at least a portion of a perimeter of the reinforcement plate; (c) heating the component to melt and flow the braze material between the reinforcement plate and the mid-span shroud; and (d) allowing the braze material to cool and solidify so as to bond the reinforcement plate to the mid-span shroud. | 02-02-2012 |
20120027618 | ANGLED BLADE ROOT - A blade root for a wind turbine rotor blade is disclosed. The blade root may generally comprise a substantially cylindrically shaped member extending lengthwise along a longitudinal axis and defining a planar end surface. Additionally, an angle may be defined between the planar end surface and a reference plane extending perpendicular to the longitudinal axis. The angle may be greater than 0 degrees and less than about 10 degrees. | 02-02-2012 |
20120034097 | COMPONENT WITH INSPECTION-FACILITATING FEATURES - A turbine airfoil can be formed with features to facilitate measurement of its wall thickness. An outer wall of the airfoil can include an outer surface and an inner surface. The outer surface of the airfoil can have an outer inspection target surface, and the inner surface of the airfoil can have an inner inspection target surface. The inner and outer target surfaces can define substantially flat regions in surfaces that are otherwise highly contoured. The inner and outer inspection target surfaces can be substantially aligned with each other. The inner and outer target surfaces can be substantially parallel to each other. As a result of these arrangements, a highly accurate measurement of wall thickness can be obtained. In one embodiment, the outer inspection target surface can be defined by an innermost surface of a groove formed in the outer surface of the outer wall of the airfoil. | 02-09-2012 |
20120034098 | Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE BLADE INCORPORATING THE SAME - A Ni-based single crystal superalloy which has the following composition: Co: 0.0 wt % or more to 15.0 wt % or less, Cr: 4.1 to 8.0 wt %, Mo: 2.1 to 4.5 wt %, W: 0.0 to 3.9 wt %, Ta: 4.0 to 10.0 wt %, Al: 4.5 to 6.5 wt %, Ti: 0.0 to 1.0 wt %, Hf: 0.00 to 0.5 wt %, Nb: 0.0 to 3.0 wt %, Re: 8.1 to 9.9 wt % and Ru: 0.5 to 6.5 wt % with the remainder including Ni and unavoidable impurities. As a result, the Ni-based single crystal superalloy which includes more than 8 wt % of Re in the composition ratio and has excellent specific creep strength and the turbine blade incorporating the Ni-based single crystal superalloy may be made. | 02-09-2012 |
20120039721 | IMPELLER FOR MIXING SLURRY IN METALLURGICAL PROCESSES - The invention relates to a turbine-type high-power impeller, to be used for mixing slurry in hydrometallurgical process reactors. The impeller is formed of at least five blades, each of which blades comprises a front edge, trailing edge, root and tip; the roots of the impeller blades are permanently attached by a joint to the hub or axis of the impeller, so that the front edge of the impeller blade is straight, and the trailing edge is chamfered, in which case the blade is narrowed towards the tip, and the blade is provided with two longitudinal folds arranged in parallel with the front edge of the blade. | 02-16-2012 |
20120039722 | Geared Compressor Rotor For Cold Gas Applications - A geared compressor rotor for cold gas applications is provided. The geared compressor rotor includes a pinion shaft having a gear tooth segment having gear teeth. The rotor further includes at least one impeller wheel having an impeller wheel hub and a sealing segment arranged between the gear tooth segment and the impeller wheel hub that bears a seal. The impeller wheel hub and the sealing segment form a common, continuously coherent region composed of a first material. The toothing segment is formed from a second material. The first material is tougher at subzero temperatures than the second material. | 02-16-2012 |
20120057987 | WIND TURBINE BLADE WITH BASE PART HAVING NON-POSITIVE CAMBER - A blade, for a rotor of a wind turbine has a profiled contour in a radial direction is divided into 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 between the root region and the airfoil region has a profile gradually changing in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region, and the airfoil region comprises at least a first longitudinal segment extending at least 20% of a longitudinal extent of the airfoil region. The first longitudinal segment has a first base part with a cross-sectional profile such that, when impacted by an incident airflow at an angle of attack of 0 degrees has a lift coefficient, which is 0 or less. | 03-08-2012 |
20120063913 | METHOD OF MANUFACTURING A WIND TURBINE BLADE HAVING PREDESIGNED SEGMENT - A blade for a rotor of a wind turbine is manufactured with a root region with a substantially circular or elliptical profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub and a transition region having a profile gradually changing the root region to the airfoil region. A first blade design is used for the first base part on a first longitudinal section of an airfoil region of a second blade, so that an induction factor of the first base part on the second blade deviates from a target induction factor. The first longitudinal section of the second blade is provided with flow altering devices so as to adjust the aerodynamic properties of the first longitudinal segment to substantially meet the target induction factor at the design point on the second blade. | 03-15-2012 |
20120070303 | Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE BLADE - The present invention provides a Ni-based single crystal superalloy which has the following composition by weight: 0.1 wt % or more and 9.9 wt % or less of Co, 5.1 wt % or more and 10.0 wt % or less of Cr, 1.0 wt % or more and 4.0 wt % or less of Mo, 8.1 wt % or more and 11.0 wt % or less of W, 4.0 wt % or more and 9.0 wt % or less of Ta, 5.2 wt % or more and 7.0 wt % or less of Al, 0.1 wt % or more and 2.0 wt % or less of Ti, 0.05 wt % or more and 0.3 wt % or less of Hf, 1.0 wt % or less of Nb and less than 3.0 wt % of Re with the remainder including Ni and unavoidable impurities. This Ni-based single crystal superalloy has a low Re content and also has excellent high-temperature strength, mainly creep strength. | 03-22-2012 |
20120076661 | BLADE FOR A GAS TURBINE ENGINE - A rotor blade for a turbine engine includes a first side that defines a first contact face with a hardcoat and a second side that defines a second contact face without a hardcoat. | 03-29-2012 |
20120076662 | TURBINE ENGINE COMPONENT HAVING PROTECTIVE COATING - A turbine engine apparatus includes a structural component made of a superalloy material. A protective coating is disposed on the structural component and has a composition that consists essentially of up to 30 wt % cobalt, 5-40 wt % chromium, 7.5-35 wt % aluminum, up to 6 wt % tantalum, up to 1.7 wt % molybdenum, up to 3 wt % rhenium, up to 5 wt % tungsten, up to 2 wt % yttrium, 0.05-2 wt % hafnium, 0.05-7 wt % silicon, 0.01-0.1 wt % zirconium, and a balance of nickel. | 03-29-2012 |
20120082557 | EFFICIENT WIND TURBINE BLADES, WIND TURBINE BLADE STRUCTURES, AND ASSOCIATED SYSTEMS AND METHODS OF MANUFACTURE, ASSEMBLY AND USE - Wind turbine systems and methods are disclosed herein. A representative system includes a wind turbine blade having an inner region that has an internal load-bearing truss structure, and an outer region that has an internal, non-truss, load-bearing structure. In particular embodiments, the truss structure can include a triangular arrangement of spars, and/or can include truss attachment members that connect components of the truss without the use of holes in the spars. Spars can be produced from a plurality of pultruded composite members laminated together in longitudinally extending portions. The longitudinally extending portions can be connected at joints that interleave projections and recesses of each of the spar portions. The blades can include fan-shaped transitions at a hub attachment portion, formed by laminated layers and/or a combination of laminated layers and transition plates. | 04-05-2012 |
20120082558 | EFFICIENT WIND TURBINE BLADES, WIND TURBINE BLADE STRUCTURES, AND ASSOCIATED SYSTEMS AND METHODS OF MANUFACTURE, ASSEMBLY AND USE - Wind turbine systems and methods are disclosed herein. A representative system includes a wind turbine blade having an inner region that has an internal load-bearing truss structure, and an outer region that has an internal, non-truss, load-bearing structure. In particular embodiments, the truss structure can include a triangular arrangement of spars, and/or can include truss attachment members that connect components of the truss without the use of holes in the spars. Spars can be produced from a plurality of pultruded composite members laminated together in longitudinally extending portions. The longitudinally extending portions can be connected at joints that interleave projections and recesses of each of the spar portions. The blades can include fan-shaped transitions at a hub attachment portion, formed by laminated layers and/or a combination of laminated layers and transition plates. | 04-05-2012 |
20120082559 | AIRFOIL BLADE - A fan blade of a gas turbine engine, and a method of producing same, is disclosed which is composed of a core substrate and a nanocrystalline metal coating provided on at least a portion of the airfoil of the fan blade. The method includes the steps of providing a fan blade core having an airfoil and then applying a nanocrystalline metal coating over at least a portion of the fan blade core. | 04-05-2012 |
20120087802 | METHOD OF COATING A SURFACE - A method is proposed of coating a surface of a body which has at least one throughgoing bore having an inlet and having an outlet, wherein the outlet is provided in the surface to be coated, in which method the coating takes place by means of thermal spraying, wherein, during the thermal spraying, the bore is flowed through by a fluid which flows out through the outlet of the bore and substantially prevents a constriction of the bore caused by the coating. | 04-12-2012 |
20120093658 | COMPOSITE STRUCTURES - A core for a composite structure is described. The core has first and second core layers, and an interlayer region between the first and second core layers. At least one of the first and second core layers has hinge portions that facilitate draping of the core without interrupting the interlayer region. The interlayer region may include functionality such as a radar reflecting layer and/or optical fibres. Alternatively, the core may be a bonded core in which the interlayer region includes an adhesive layer for bonding the first and second core layers together. | 04-19-2012 |
20120093659 | ROTOR BLADE, ROTOR BLADE ELEMENT AND PRODUCTION PROCESS - A rotor blade or rotor blade element for a wind power installation is provided having a surface film and a hardenable resin, wherein the surface film has been reacted with the resin to form an integral portion of the rotor blade or rotor blade element. Production and repair processes for the rotor blade or the rotor blade element are also provided. | 04-19-2012 |
20120100004 | High efficiency impeller - An impeller for a turbine includes a conical body having a wider end, a narrower end and an outside surface, a front end surface connected to the wider end of the conical body, a back end surface connected to the narrower end of the conical body, and a plurality of helical grooves disposed in the outside surface of the conical body wherein the helical grooves decrease in depth from the wider end to zero depth near the narrower end. | 04-26-2012 |
20120100005 | Blade of a Wind Turbine - A blade of a wind turbine is provided. The blade includes at least one vortex-generator, which is positioned at the blade-surface. The vortex-generator is constructed and arranged in a way that it contributes to the aerodynamic characteristics of the blade. The vortex-generator includes a platform and an extension-part. The blade also includes a recess, which is constructed and arranged to receive at least a part of the platform of the vortex-generator. The platform is fixed at least partly within the recess. | 04-26-2012 |
20120107130 | METHOD OF ENHANCING THE OUTPUT EFFICIENCY OF A PROPELLER AND REDUCING THE NOISE THEREOF - A method of enhancing the output efficiency of a propeller and reducing the noise thereof wherein a plurality of small cavities are formed on the whole or at least a portion of a blade skin of the propeller. When the propeller is rotated and a fluid passes through the small cavities, a plurality of small vortexes are created at the blade skin to form a thin turbulent boundary layer that allows an advantageous interference acting on a turbulence of the fluid at the blade skin. In this way, a portion of fluid is not in contact with the blade skin, and a viscous drag acting on the blade skin is reduced to extend a wake and reduce a drag force of the wake. The aforementioned mechanism can enhance the output efficiency of a propeller and reduce the noise thereof. | 05-03-2012 |
20120107131 | CENTRIFUGAL COMPRESSOR IMPELLER - A compressor impeller includes a hub, main blades and splitter blades. The main blades are equally spaced around the circumference of the hub. Each splitter blade is equally spaced between two adjacent main blades. Each main blade and splitter blade has suction and pressure surfaces formed in substantial compliance with normalized Cartesian coordinate values of X, Y, and Z set forth in Tables 1-4. When connected by smooth, continuing arcs, the normalized Cartesian coordinates form complete main blade and splitter blade shapes that are substantially matched by the main blade and splitter blade shapes of the compressor impeller. | 05-03-2012 |
20120107132 | TITANIUM ALLOY WITH IMPROVED PROPERTIES - A titanium alloy having high strength, fine grain size, and low cost and a method of manufacturing the same is disclosed. In particular, the inventive alloy offers a strength increase of about 100 MPa over Ti 6-4, with a comparable density and near equivalent ductility. The inventive alloy is particularly useful for a multitude of applications including components of aircraft engines. The Ti alloy comprises, in weight percent, about 6.0 to about 6.7% aluminum, about 1.4 to about 2.0% vanadium, about 1.4 to about 2.0% molybdenum, about 0.20 to about 0.42% silicon, about 0.17 to about 0.23% oxygen, maximum about 0.24% iron, maximum about 0.08% carbon and balance titanium with incidental impurities. | 05-03-2012 |
20120114496 | Precipitation Hardening Martensitic Stainless Steel and Steam Turbine Component Made Thereof - It is an objective of the present invention to provide a precipitation-hardening martensitic stainless steel having well-balanced properties of high mechanical strength, high toughness and good corrosion resistance properties. There is provided a precipitation-hardening martensitic stainless steel comprising: 0.10 mass % or less of C; 13.0 to 15.0 mass % of Cr; 7.0 to 10.0 mass % of Ni; 2.0 to 3.0 mass % of Mo; 0.5 to 2.5 mass % of Ti; 0.5 to 2.5 mass % of Al; 0.5 mass % or less of Si; 0.1 to 1.0 mass % of Mn; and the balance including Fe and incidental impurities, in which the mass % content of the Ti (represented by [Ti content]), the mass % content of the Al (represented by [Al content]) and the mass % content of the C (represented by [C content]) satisfy relationships of “0.5≦[Ti content]≦2.5” and “0.5≦[Al content]+2[C content]≦2.7”. | 05-10-2012 |
20120114497 | METHOD OF MANUFACTURING A WIND TURBINE BLADE COMPRISING TWO MEMBERS BEING JOINED BY ADHESION - The present invention relates to a method of manufacturing a wind turbine blade | 05-10-2012 |
20120121430 | Arrangement and method to retrofit a wind turbine - An arrangement and a method to retrofit a wind turbine is provided. The wind turbine is retrofitted by at least one of its blades. The blade is prepared for a connection with the hub of the wind turbine. An extension unit is designed and prepared to increase the surface-area of the blade. The extension unit and the blade are designed and arranged to interact with each other by an opening. Thus the opening might be arranged inside the blade and/or inside the extension unit. The extension unit is connected with the blade by an adhesive, which is applied at least partly within the opening. | 05-17-2012 |
20120121431 | BLADE TIP COATING THAT CAN BE RUBBED OFF - The present invention relates to a method for producing a component, in particular a blade for a gas turbine, wherein a main body ( | 05-17-2012 |
20120128501 | FAN BLADE TIPS - Fans having blade tips with downwardly extending airfoil surfaces are disclosed herein. In one embodiment, for example, a high volume low speed ceiling fan includes a plurality of blades, each having an anhedral or downward sloping tip portion. The blade tips can also include an aft swept portion that extends between the main airfoil portion of the fan blade and the anhedral tip portion. | 05-24-2012 |
20120128502 | EROSION RESISTANT MACHINE COMPONENT, METHOD FOR FORMING SURFACE LAYER OF MACHINE COMPONENT, AND METHOD FOR MANUFACTURING STEAM TURBINE - A method for forming a surface layer, the purpose thereof is to form a high erosion resistant film. The method for forming a surface layer includes: arranging a member ( | 05-24-2012 |
20120141288 | FABRICATING PARTS WITH COMPOSITE MATERIAL REINFORCEMENT HAVING A SINGLE CROSSING LINE - Method for fabricating a reinforcing coating for a part made of composite material. Pre-impregnated reinforcing fibers are used in the form of slivers and said slivers are laid on the part in two layers of longitudinal slivers by being placed thereon. This fabrication makes provision for using an angular orientation for the slivers of each layer respectively of 0° and of some other angle relative to said determined direction of the solid body for covering using an interlaced pattern type that gives layer crossing lines parallel to a longitudinal axis of the solid body for covering, which pattern type is selected to form interlacing patterns that limit the number of layer crossing lines along the longitudinal axis of the solid body for covering to a single line. | 06-07-2012 |
20120141289 | AIRFOIL WITH WRAPPED LEADING EDGE COOLING PASSAGE - A turbine engine airfoil includes an airfoil structure having an exterior surface providing a leading edge. A radially extending first cooling passage is arranged near the leading edge and includes first and second portions. The first portion extends to the exterior surface and forms a radially extending trench in the leading edge. The second portion is in fluid communication with a second cooling passage. In one example, the second cooling passage extends radially, and the first cooling passage wraps around a portion of the second cooling passage from a pressure side to a suction side between the second cooling passage and the exterior surface. In the example, the first portion is arranged between the pressure and suction sides. In one example, the first cooling passage is formed by arranging a core in an airfoil mold. The trench is formed by the core in one example. | 06-07-2012 |
20120141290 | COMPONENTS, TURBOCHARGERS, AND METHODS OF FORMING THE COMPONENTS - Components, turbochargers, and methods of forming components are provided. In an embodiment, by way of example only, a method of forming a component is provided. The method includes applying a plurality of coated particles to a substrate, wherein each coated particle comprises a solid film lubricant particle and a layer surrounding an entire surface of the solid film lubricant particle, each solid film lubricant particle comprises at least one compound, and the layer comprises a coating material having a greater resistance to oxidation than the compound when subjected to a predetermined processing temperature and heating the substrate to the predetermined processing temperature to form a portion of a coating over the substrate. | 06-07-2012 |
20120141291 | WIND TURBINE COMPOSITE STRUCTURES - A wind turbine composite structure for absorbing radio frequency energy, the wind turbine composite structure comprising: a sandwich panel construction comprising a core having an inner surface and an outer surface, disposed between an inner skin and an outer skin; the outer surface and the outer skin facing towards an exterior surface of the wind turbine composite structure and the inner surface and the inner skin facing towards an interior of the wind turbine composite structure; a reflector layer disposed adjacent to the inner skin; and a functional layer comprising printed or deposited circuitry, the functional layer forming a radar absorbing circuit in combination with the reflector layer, wherein the functional layer is printed or deposited directly on to the outer surface of the core. | 06-07-2012 |
20120156052 | ICE RELEASE SYSTEMS - An article with ice phobic surface along with method of making and using the article are disclosed. The article includes a silicone composition disposed on a surface of the article and a grease applied to the silicone composition. The grease includes a fluid lubricant component and a thickener component. The method of making the article includes the steps of disposing a silicone composition on a surface, curing the silicone composition, and applying a grease on the cured silicone composition to form a greased silicone. | 06-21-2012 |
20120163987 | HIGH STRENGTH GLASS COMPOSITION AND FIBERS - Glass compositions and high-modulus, and high-strength glass fibers made therefrom, being capable of economical, continuous processing and suitable for the production of high-strength and/or high stiffness, low-weight composites, such as windturbine blades, the glass composition comprises the following constituents in the limits defined below, expressed as weight percentages: between about 56 to about 61 weight percent SiO | 06-28-2012 |
20120171045 | TURBINE COMPONENT FIXTURE AND COATING SYSTEM - A system comprises a turbine component and a fixture. The turbine component comprises a first end, a second end, a first region with a first feature and a second region with a second feature. The fixture comprises first and second end blocks adjacent the first and second ends of the turbine component, and a load beam coupling the first and second end blocks to retain the turbine component therebetween. A compliant mask is positioned against the turbine component, covering the first region and leaving the second region uncovered. A removable coating is applied to the turbine component, coating the second feature and leaving the first feature uncoated. | 07-05-2012 |
20120183410 | TITANIUM ALLOY TURBINE BLADE - It is an objective of the present invention to provide an effective use of the friction stir processing (FSP) technology for Ti-alloy turbine blades with a long radial length, and provide a Ti-alloy turbine blade having both high erosion resistance and high long term reliability. There is provided a turbine blade made of an α-β titanium alloy having an average Vickers hardness of 320 Hv or less, the turbine blade having a leading edge, in which: the turbine blade includes, at the leading edge thereof, a first hardened surface region having a thickness of from 0.5 to 3.0 mm and having an average Vickers hardness of 340 Hv or more; and the first hardened surface region is formed by friction stir processing a surface region of the leading edge of the turbine blade. | 07-19-2012 |
20120189459 | Welded Rotor, a Steam Turbine having a Welded Rotor and a Method for Producing a Welded Rotor - A welded rotor, a steam turbine having a welded rotor, and a method of producing a welded rotor are disclosed. The welded rotor includes a high pressure section and an intermediate pressure section. Either or both the high pressure section and/or the intermediate pressure section includes a high temperature material section joined to a low temperature material section. | 07-26-2012 |
20120189460 | Welded Rotor, a Steam Turbine having a Welded Rotor and a Method for Producing a Welded Rotor - A welded rotor, a steam turbine having a welded rotor, and a method of producing a welded rotor are disclosed. The welded rotor includes a high pressure section and an intermediate pressure section. The welded rotor includes a shaft having a high temperature material section joined to a first and second low temperature material sections. | 07-26-2012 |
20120201691 | METHOD FOR PRODUCING A ROTOR OR STATOR BLADE AND SUCH A BLADE - The invention relates to a method for producing a rotor or stator blade ( | 08-09-2012 |
20120207613 | COMPONENT OF A TURBINE BUCKET PLATFORM - A component is provided and includes a first surface, a second surface adjacent to and oriented transversely with respect to the first surface and having a pocket formed therein defining a rib along a periphery thereof and a thermal barrier coating (TBC) respectively applied to the first surface and to the second surface at the pocket such that the rib is interposed between the TBC of the first and second surfaces. | 08-16-2012 |
20120269645 | WIND TURBINE COMPONENT HAVING AN EXPOSED SURFACE MADE OF A HYDROPHOBIC MATERIAL - The invention provides a wind turbine component having an exposed surface made of a hydrophobic material and having a surface texture providing a Water Contact Angle (CA) of at least 150. Due to the combination between a CA over 150 and the hydrophobic material, the component becomes less vulnerable to ice formation etc. The invention further provides a method of preventing ice formation, a method of reducing noise and a blade for reducing noise from a wind turbine. | 10-25-2012 |
20120269646 | NICKEL BASE SUPERALLOY - A nickel base superalloy consisting of 20 to 40 wt % cobalt, 10 to 15 wt % chromium, 3 to 6 wt % molybdenum, 0 to 5 wt % tungsten, 2.5 to 4 wt % aluminium, 3.4 to 5 wt % titanium, 1.35 to 2.5 wt % tantalum, 0 to 2 wt % niobium, 0.5 to 1 wt % hafnium, 0 to 0.1 wt % zirconium, 0.01 to 0.05 wt % carbon, 0.01 to 0.05 wt % boron, 0 to 2 wt % silicon and the balance nickel plus incidental impurities. The gamma prime phase comprises (Ni/Co) | 10-25-2012 |
20120294729 | COLD METAL TRANSFER HARDFACING OF BUCKETS - In one embodiment, the invention provides a method of hardfacing a portion of a bucket subject to mechanical stress, the method comprising: contacting a surface of a bucket with a hardfacing filler metal connected to a welding nozzle to establish an arc between the surface and the filler metal and form a molten weld pool comprising the filler metal and a material of the surface; extending the filler metal into the molten weld pool to short circuit the arc; withdrawing the filler metal from the molten weld pool to re-establish the arc; moving the welding nozzle along the surface; and re-extending the filler metal into the molten weld pool to short circuit the arc, deposit additional filler metal into the molten weld pool, and liquify additional material of the surface into the molten weld pool. | 11-22-2012 |
20120301318 | CONVEYING BLADES FOR A COMPRESSIBLE ROTOR - To provide a simple embodiment of a rotor for a fluid pump which is nevertheless very flexible in handling and compressible, in accordance with the invention a conveying blade is provided having at least two struts and a membrane spanned between them in the expanded state, wherein the struts each have at least one joint, in particular more than one joint, which enables an angling in a first direction in a first movement plane and bounds an overelongation beyond an elongation angle of in particular 180° in the opposite second direction. In particular when a plurality of joints are provided at the struts, they, and with them the conveying blades, are particularly flexible for simple compressibility. | 11-29-2012 |
20120308395 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture is disclosed. The article may have a nominal profile generally in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y may correspond to distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the airfoil profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape. | 12-06-2012 |
20120308396 | SECTIONAL BLADE - A sectional blade for a wind turbine, the blade extending lengthwise between a tip and a root where the blade is attachable to a hub of a wind turbine, crosswise between a leading edge and a trailing edge, and thickness wise between a windward and a leeward outer surface. The sectional blade comprises a first blade portion and a second blade portion. The blade portions are formed as separate components and arranged to extend lengthwise in opposite directions from a junction where the blade portions join. The blade forms, in a cross section perpendicular to the lengthwise direction and through the junction, a maximum thickness location between the leading and trailing edges, the maximum thickness location being where the distance between the windward and leeward outer surfaces is larger than at any other location in this cross section. The sectional blade comprises an assembly board which is adhesively joined to an outer surface of both blade portions between the trailing edge and the maximum thickness location. | 12-06-2012 |
20120321481 | Spinnable Bladed Device For Operation In Air, Water Or Other Fluid Medium - A device having a pair of blades spinnable about a spin axis. The pair of blades includes a first blade and a second blade, with the first blade canted about a first-blade canting axis at a first-blade canting angle and the second blade canted about a second-blade canting axis at a second-blade canting angle. The first-blade canting axis is oriented at a first-blade canting axis angle relative to a first-blade radial and the second-blade canting axis is oriented at a second-blade canting axis angle relative to a second-blade radial, each canting axis angle being other than 90 degrees. The first-blade radial is oriented perpendicular to a first chord plane that passes through the first blade and contains a first-blade chord, and the second-blade radial is oriented perpendicular to a second chord plane that passes through the second blade and contains a second-blade chord. The first-blade chord is oriented at a first-blade chord pitch angle determined at least in part by the first-blade canting axis angle and the first-blade canting angle. The second-blade chord is oriented at a second-blade chord pitch angle determined at least in part by the second-blade canting axis angle and the second-blade canting angle. | 12-20-2012 |
20120321482 | WIND TURBINE BLADE - A blade for a partial pitch wind turbine is described, wherein the blade has a truncated aerodynamic profile provided at the pitch junction of the blade. The truncated trailing edge acts to prevent the formation of a trailing edge gap during pitching between the trailing edges of the inner and outer blade sections of a partial pitch blade, thereby reducing the negative impact of air leakage, etc., when pitching a partial pitch blade. | 12-20-2012 |
20120328448 | COMPONENTS WITH COOLING CHANNELS AND METHODS OF MANUFACTURE - A manufacturing method is provided. The manufacturing method includes forming one or more grooves in a component comprising a substrate. Each groove extends at least partially along the substrate and has a base, a top and at least one discharge end. The manufacturing method further includes forming a crater, such that the crater is in fluid connection with the respective discharge end for each groove, and disposing a coating over at least a portion of an outer surface of the substrate. The groove(s) and the coating together define one or more channels for cooling the component. The coating does not completely bridge each of the one or more craters, such that each crater defines a film exit. A component with cratered film exits is also provided. | 12-27-2012 |
20130004327 | ALUMINUM FAN BLADE ROOT - A method of improving fatigue strength in a fan blade includes fabricating a metal fan blade with an airfoil and a root and deep peening the root. | 01-03-2013 |
20130004328 | ABRASIVE AIRFOIL TIP - An airfoil comprises a substrate, a residual abrasive coating and a supplemental abrasive coating. The substrate extends along a tip section of the airfoil, from a leading edge to a trailing edge. The residual abrasive coating comprises a two-phase abrasive and metal matrix material bonded to the substrate, on the tip section of the airfoil. The supplemental abrasive coating comprises a two-phase abrasive and metal matrix material bonded to the residual abrasive coating and to the substrate adjacent the residual abrasive coating, on the tip section of the airfoil. The supplemental abrasive coating restores the airfoil to a nominal tip height in the tip section. | 01-03-2013 |
20130028745 | System and Method for Generating Electrical Power Using an Improved Wind Turbine Blade - A system and method for generating electrical power using an improved wind turbine blade is described herein. Specifically, a wind turbine blade assembly can include a one or more curved blade mount, each parallel to the other, having a ratio of a linear blade length to a curve depth between 15/99 and 17/99, and a blade, wherein blade is mounted to said one or more blade mounts, wherein said blade comprises a thin flexible material capable of conforming to one or more curved blade mount. | 01-31-2013 |
20130028746 | TURBINE ENGINE TURBINE BLADE MADE OF A CERAMIC-MATRIX COMPOSITE WITH RECESSES MADE BY MACHINING - A turbine engine turbine blade of ceramic matrix composite. The root of the blade includes a single densified fiber preform including at least one recess made by machining, each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, and the distal portion of the root of the blade includes a distal wall that is continuous and in a single piece. | 01-31-2013 |
20130034448 | Integrally Rotating Machinery and Method and Apparatus for Achieving the Same - An article formed with blading members comprising a rotor a a plurality of blading members integrally formed with the rotor wherein each blading member having continuous zones of compressive residual stress on the pressure side and the suction side and extending substantially along the perimeter and extending inwards, towards the center of each blading member, and wherein the continuous zones of compressive residual stress have an improved surface finish. | 02-07-2013 |
20130052033 | WIND TURBINE PROVIDED WITH A SLAT ASSEMBLY - The present invention relates to a wind turbine blade for a rotor of a wind turbine having a substantially horizontal rotor shaft, the rotor comprising a hub from which the blade extends in a substantially radial direction when mounted to the hub. The wind turbine blade comprises a profiled contour defining a leading edge and a trailing edge, a pressure side and a suction side connecting the leading edge and the trailing edge, the profiled contour generating a lift when being impacted by an incident air-flow, and a slat assembly located on the blade, the slat assembly comprising a slat device being supported by a support device positioning the slat device in a distance from the surface of the blade. | 02-28-2013 |
20130058791 | PROTECTIVE COATING FOR TITANIUM LAST STAGE BUCKETS - Described herein a bucket for use in the last stage of a steam turbine engine. The bucket includes a titanium-based alloy having a leading edge wherein the leading edge includes titania having a plurality of pores and a top sealing layer filling the plurality of pores, the sealing layer selected from the group consisting of: chromium, cobalt, nickel, polyimide, polytetrafluoroethylene and polyester. | 03-07-2013 |
20130064677 | ROTOR BLADE ASSEMBLY FOR WIND TURBINE - A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The surfaces further define an interior, and the rotor blade further defines a span and a chord. The rotor blade assembly further includes a strut disposed in the interior and extending between the pressure side and the suction side. A length of the strut extends in a generally spanwise direction, and a width of the strut extends diagonally to the chord. | 03-14-2013 |
20130084190 | TITANIUM ALUMINIDE ARTICLES WITH IMPROVED SURFACE FINISH AND METHODS FOR THEIR MANUFACTURE - Titanium-containing articles having improved surface finishes and methods for improving surface finishes on titanium containing articles are provided. One method includes passing an abrasive medium across a surface of an titanium aluminide alloy-containing article, for example, a turbine blade, at high linear speed; deforming the surface of the titanium aluminide alloy-containing article with the abrasive medium and reducing a surface roughness of the surface of the titanium aluminide alloy-containing article and improving the surface finish of the surface. Surface finishes of 20 microinches Ra or less can be obtained. Though aspects of the invention can be used in fabricating high performance turbine blades, the methods disclosed can be applied to the treatment of any titanium-containing article for which it is difficult to obtain an improved surface finish. | 04-04-2013 |
20130101431 | ROTOR, A STEAM TURBINE AND A METHOD FOR PRODUCING A ROTOR - A rotor having a first low temperature material section, a second low temperature material section attached to a first end of the first low temperature material section and a third low temperature material section joined to a first end of the second low temperature material section. The first, second and third temperature material sections are exposed to steam at a pressure less than about 180 bar. A steam turbine and a method for producing a rotor are also disclosed. | 04-25-2013 |
20130101432 | Erosion Resistant Helicopter Blade - A rotor blade including a main portion having a main portion leading edge shield; a main portion impact-resistant layer formed on a nose of the leading edge shield; a main portion erosion-resistant layer formed on a top and bottom of the main portion, rearward of the main portion impact-resistant layer; a main portion foil formed on the top and the bottom of the main portion rearward of the main portion erosion-resistant layer; a tip cap having a tip cap leading edge shield; a tip cap impact-resistant layer formed on a surface of the tip cap leading edge shield; and a tip cap foil formed on the top and the bottom of the tip cap rearward of the tip cap erosion-resistant layer. | 04-25-2013 |
20130108459 | MOLD COMPOSITIONS AND METHODS FOR CASTING TITANIUM AND TITANIUM ALUMINIDE ALLOYS | 05-02-2013 |
20130108460 | COMPONENT OR COUPON FOR BEING USED UNDER HIGH THERMAL AND STRESS LOAD AND METHOD FOR MANUFACTURING SUCH COMPONENT OR COUPON | 05-02-2013 |
20130108461 | PROPELLER FAN AND MANUFACTURING METHOD THEREOF | 05-02-2013 |
20130115097 | CORROSION-RESISTANT DIFFUSION COATINGS - A metal article such as a gas turbine component may include a super-diffusion coating with unusually high content of the desired constituent. The coating may be provided by combining two or more diffusion coating processes, each process interdiffusing the desired constituent with the metal article from a different metal source. The metal article can be placed in physical contact with a metal source in powder form as a first source, and the article can also be exposed an additional metal vapor source. Super-chromide coatings can be produced with alpha-chrome content in a manner that also provides the coating with sufficient ductility for long-term durability. For example, a shank portion of a gas turbine blade may be provided with a chromide coating with at least a portion of the coating having from 60-90% chromium content. | 05-09-2013 |
20130115098 | Wind Turbine Blade with Narrow Shoulder and Relatively Thick Airfoil Profiles | 05-09-2013 |
20130121838 | Runner for Direct-connected Low-speed Small Mixed Flow Type Water Turbine Applied in Hydrodynamic Energy-saving Cooling Tower - The invention relates to a runner for a direct-connected low-speed small mixed flow type water turbine applied in a hydrodynamic energy-saving cooling tower, which comprises an upper crown ( | 05-16-2013 |
20130121839 | TURBINE AIRFOIL AND METHOD FOR THERMAL BARRIER COATING - A turbine airfoil including an airfoil body is disclosed. The airfoil includes a leading edge, a trailing edge, an exterior surface including a suction side extending from the leading edge to the trailing edge and a pressure side extending from the leading edge to a trailing end. The pressure side is located opposite to the suction side on the airfoil body. The complete pressure side of the exterior surface is coated by a thermal barrier coating with a thickness decreasing towards the trailing end. | 05-16-2013 |
20130129522 | RHENIUM-FREE SINGLE CRYSTAL SUPERALLOY FOR TURBINE BLADES AND VANE APPLICATIONS - A rhenium-free nickel-base superalloy for single crystal casting that exhibits excellent high temperature creep resistance, while also exhibiting other desirable properties for such alloys, comprises 5.60% to 5.85% aluminum, 9.4% to 9.9% cobalt, 5.0% to 6.0% chromium, 0.08% 0.35% hafnium, 0.50% to 0.70% molybdenum, 8.0% to 9.0% tantalum, 0.60% to 0.90% titanium, 8.5% to 9.8% tungsten, the balance comprising nickel and minor amounts of incidental elements. | 05-23-2013 |
20130129523 | Bimetallic Compressor Wheel and a Method of Manufacture Thereof - The performance and durability of compressor wheels coupled to turbocharger shafts are at odds with each other in that a higher rotational speed can be accommodated by an aluminum compressor wheel. But, aluminum has a low yield strength which causes the compressor wheel to expand outwardly at high rotational speeds such that the slip fit on the shaft no longer prevents wobble at high rotational speeds. To at least partially address this issue, the compressor wheel has two portions: an inner portion made of steel or titanium that has a relatively higher yield strength and a blade portion made of a lightweight, castable material. The inner portion is manufactured with grabbing features on its periphery, placed in a die, and the blade portion is cast over the grabbing features to yield a compressor wheel of two materials that provides sufficient shaft stiffening without high rotational inertia. | 05-23-2013 |
20130136620 | Water Impeller - The invention is a magnetically driven pump with a floating impeller and driven magnet, and the invention includes an impeller surface having geometric figures acting as the pumping bodies. | 05-30-2013 |
20130142661 | NICKEL-BASED ALLOY - Adding silicon, in a defined range of weight percentage, to the composition of a known nickel-based alloy improves oxidation, hot corrosion and dwell crack growth resistance without the detrimental effects on the thermal stability of the microstructure and on other material properties that have been found with known alloys. In a particular preferred embodiment the alloy has the following composition (in weight percent): chromium 14.6-15.4%; cobalt 18-19%; molybdenum 4.75-5.25%; aluminium 2.8-3.2 titanium 3.4-3.8%; tantalum 1.8-2.2%; hafnium 0.4-0.6%; carbon 0.020-0.034%; boron 0.005-0.025%; silicon 0.2-0.6%; the remainder being nickel and incidental impurities. | 06-06-2013 |
20130142662 | EXHAUST-GAS TURBOCHARGER COMPONENT - An exhaust-gas turbocharger component ( | 06-06-2013 |
20130156595 | RIBLET STRUCTURE ON A FLOW SURFACE AND METHOD - A riblet structure for a flow surface is provided. The riblet structure has a multitude of riblets that comprise a matrix material which includes reinforcement elements. The reinforcement elements can be designed as reinforcement fibers that extend in the longitudinal direction or as particles. In this manner the abrasion resistance can be improved and erosion can be retarded. | 06-20-2013 |
20130177437 | PROCESSES FOR COATING A TURBINE ROTOR AND ARTICLES THEREOF - A process for applying a hard coating to a turbine rotor comprising providing a turbine rotor having at least one surface; applying a first coating to the at least one surface, the first coating being cold sprayed onto the at least one surface; applying a second coating onto the first coating to form the hard coating, wherein the hard coating is configured to substantially resist wear of a brush seal in physical communication with the turbine rotor. | 07-11-2013 |
20130177438 | SECTIONED ROTOR, A STEAM TURBINE HAVING A SECTIONED ROTOR AND A METHOD FOR PRODUCING A SECTIONED ROTOR - A sectioned rotor is disclosed that includes a high temperature section. The high temperature section includes a first high temperature material section, a second high temperature material section; and a sectioned high temperature material section formed of a plurality of high temperature material subsection components. The sectioned high temperature material section is joined to the first high temperature material section and the second high temperature section. The plurality of the high temperature subsection components are independently formed of a nickel-based superalloy. A steam turbine having a sectioned rotor and a method for manufacturing a sectioned rotor are also disclosed. | 07-11-2013 |
20130177439 | CREEP RESISTANT COATING FOR CERAMIC TURBINE BLADES - A gas turbine blade having a surface may have a bond layer applied to a first section of the surface, wherein the bond layer is not applied to a second section of the surface. One or more protective layers may be applied such that the protective layers cover and overlap the bond layer making direct contact with an area of the surface immediately outside the first section of the surface and forming a mechanical constraint geometry about the edge of the bond layer. | 07-11-2013 |
20130177440 | Continuous Fiber Reinforced Mesh Bond Coat for Environmental Barrier Coating System - A gas turbine blade may have a bond coat applied to its surface. A porous substrate may be applied to the bond layer and one or more protective layers may be applied to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer to prevent creep. | 07-11-2013 |
20130177441 | Compositional Bond Coat for Hindering/Reversing Creep Degradation in Environmental Barrier Coatings - A gas turbine blade may have a bond coat applied to its surface. The bond coat may include silicon and a reactive material. The reactive material may react with thermally grown oxide generated at the bond layer to prevent and reverse creep. One or more protective layers may be applied to the bond layer. | 07-11-2013 |
20130177442 | NICKEL-BASE SUPERALLOY - A nickel-base superalloy for turbine vanes or turbine blades is provided. The nickel-base superalloy has in wt %: C: equal to or greater 0.1; Si: =0.2; Mn: =0.2; P: =0.005; S:=0.0015; Al: 4.0 to 5.5; B: =0.03; Co: 5.0 to 9.0; Cr: 18.0 to 22.0; Cu: =0.1; Fe: =0.5; Hf: 0.9 to 1.3; Mg:=0.002; Mo: =0.5; N: =0.0015; Nb: =0.01; 0: =0.0015; Ta: 4.8 to 5.2; Ti: 0.8 to 2.0; W: 1.8 to 2.5; Zr: =0.01; Ni: balance; and inevitable impurities. | 07-11-2013 |
20130189115 | TURBINE AIRFOIL MASK - A masking system for an airfoil comprises a locator for positioning along the trailing edge of the airfoil, and first and second mask sections. The first mask section has a trailing edge portion with locator pins for cooperating with a positioning tab on the locator to position the first mask section along the trailing edge of the airfoil, and a leading edge portion for extending around the leading edge of the airfoil to locate the first mask section along the convex surface. The second mask section has a retainer portion for cooperating with a retainer process on the first mask section to retain the second mask along the leading edge of the airfoil, and a flange portion for extending between the locator pins to locate the second mask along the concave surface. | 07-25-2013 |
20130195673 | MULTI-MATERIAL TURBINE COMPONENTS - A turbine component for a turbine of an engine is provided. The turbine component includes a blade portion of a first material; and an attachment portion coupled to the blade portion, the attachment portion being a second material. | 08-01-2013 |
20130195674 | ALUMINUM AIRFOIL - A method of making an aluminum airfoil includes brazing a first airfoil piece and a second airfoil piece together using a braze material that includes an element selected from magnesium and zinc, to form a braze joint between the first airfoil piece and the second airfoil piece. At least one of the first airfoil piece or the second airfoil piece has an aluminum alloy composition that includes greater than 0.8% by weight of zinc. | 08-01-2013 |
20130202445 | TURBINE BLADE HAVING IMPROVED FLUTTER CAPABILITY AND INCREASED TURBINE STAGE OUTPUT - A turbine blade, airfoil configuration, and rotor stage are disclosed in which through the airfoil profile disclosed in Table 1, a modification in airfoil flutter and swirl are achieved. Through the airfoil configuration, the swirl and improved platform sealing configuration, result in the turbine blades having the airfoil profile with an increased performance output from the turbine. | 08-08-2013 |
20130209264 | WIND TURBINE ROTOR BLADE ASSEMBLY WITH ROOT EXTENSION PANEL AND METHOD OF ASSEMBLY - A wind turbine rotor blade assembly and associated method include a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension panel is attached along either of the leading edge or trailing edge (or along both edges) in a generally span-wise direction from adjacent the root towards the tip. The edge extension panels include a cured and hardened viscous material continuous core formed onto the leading or trailing edge with a contoured generally aerodynamic outer surface. | 08-15-2013 |
20130209265 | Superalloy Compositions, Articles, and Methods of Manufacture - A composition of matter comprises, in combination, in weight percent: a content of nickel as a largest content; 3.10-3.75 aluminum; 0.02-0.09 boron; 0.02-0.09 carbon; 9.5-11.25 chromium; 20.0-22.0 cobalt; 2.8-4.2 molybdenum; 1.6-2.4 niobium; 4.2-6.1 tantalum; 2.6-3.5 titanium; 1.8-2.5 tungsten; and 0.04-0.09 zirconium. | 08-15-2013 |
20130209266 | Superalloy Compositions, Articles, and Methods of Manufacture - A composition of matter, comprising in combination, in atomic percent contents: a content of nickel as a largest content; 19.0-21.0 percent cobalt; 9.0-13.0 percent chromium; 1.0-3.0 percent tantalum; 0.9-1.5 percent tungsten; 7.0-9.5 percent aluminum; 0.10-0.25 percent boron; 0.09-0.20 percent carbon; 1.5-2.0 percent molybdenum; 1.1-1.5 percent niobium; 3.0-3.6 percent titanium; and 0.02-0.09 percent zirconium. | 08-15-2013 |
20130216390 | REINFORCED COMPOSITES PRODUCED BY A VACUUM INFUSION OR PULTRUSION PROCESS - Carbon nanotube-reinforced composites are produced by incorporating up to 0.7% by weight of carbon nanotubes into a liquid polymeric material a polymeric material. The viscosity of the carbon nanotube-containing liquid polymeric is sufficiently low that it can be used in vacuum infusion and pultrusion processes to produce large articles such as wind turbine blades. | 08-22-2013 |
20130216391 | METHOD FOR THE PRODUCTION OF A ONE-PIECE ROTOR AREA AND ONE-PIECE ROTOR AREA - The present invention describes a method for the production of a one-piece rotor area, preferably of a jet engine. The rotor area includes an annular base body and several, circumferentially distributed blade elements extending essentially radially from the base body. Residual stresses are imparted to the blade elements in surface-near areas by way of roller compression using a rolling tool introduced between the blade elements. During roller compression, one each area of a blade element is arranged between areas of the rolling tool, with longitudinal sides of the blade element being simultaneously roller-compressed. According to the present invention, the rolling tool is radially introduced between the blade elements and the surfaces of the blade elements are roller-compressed, thus at least the blade elements having a roller-compressed surface. | 08-22-2013 |
20130216392 | WIND TURBINE, ROTOR BLADE, AND OBSTRUCTION REMOVAL SYSTEM FOR ROTOR BLADE - A wind turbine blade ( | 08-22-2013 |
20130224038 | MOLTEN METAL IMPELLER - According to another embodiment, a molten metal impeller comprised of a generally cylindrical body including a plurality of passages extending from a top surface to a side wall and a cap member secured to a top surface of the body. The cap member is shaped cooperatively to overlay the cylindrical body. The cap member includes a first side seated on the top surface and a second opposed side. The top surface includes one of a notch or a protrusion and the first side of the cap member includes one of a notch or a protrusion oriented to mate with the notch or protrusion of the body. | 08-29-2013 |
20130230405 | NICKEL BASE SUPERALLOY COMPOSITIONS BEING SUBSTANTIALLY FREE OF RHENIUM AND SUPERALLOY ARTICLES - A nickel base superalloy composition substantially free of rhenium includes, in percentages by weight: about 5-8 Cr; about 7-8 Co; about 1.3-2.2 Mo; about 4.75-6.75 W; about 6.0-7.0 Ta; if present, up to about 0.5 Ti; about 6.0-6.4 Al; about 0.15-0.6 Hf; if present, from about 0.03-0.06 C; if present, up to about 0.004 B; if present, one or more rare earths selected from Y, La, and Ce up to about 0.03 total, the balance including nickel and incidental impurities. The superalloy composition is able to provide sustained-peak low cycle fatigue and/or oxidation resistance properties comparable to second generation superalloy compositions including at least about 3 wt % rhenium. Superalloy articles incorporating the compositions include nozzles, shrouds, and splash plates for gas turbine engines. | 09-05-2013 |
20130230406 | Corrosion Resistant Articles - Gas turbine engine turbine blade includes a silicon-modified aluminide coating on at least an under platform region formed from a slurry composition being substantially free of hexavalent chromium. The silicon-modified aluminide coating provides oxidation resistance comparable to PtAl coatings without adding a weight penalty. | 09-05-2013 |
20130236328 | AXIAL FLOW IMPELLER - An axial flow impeller includes a hub, at least three base blades, and a cover blade detachably mounted to each base blade. When the impeller is applied in a medium environment having a high density and viscosity, the impeller will meet the requirement only by virtue of the base blade with the cover blade being removed. When the impeller is applied in a medium environment having low density and viscosity, the cover blade can be mounted in the front and/or rear of the base blade in order to improve the efficiency of the impeller. In this case, the consumption of electrical power can be reduced significantly while producing an equivalent propulsive force, thereby being advantageous for energy conservation. Therefore, the impeller can be adaptable to different medium environments and efficiency requirements, and thus can have good adaptability, need minimal investment cost and can be convenient to use. | 09-12-2013 |
20130243605 | PROTECTING FILM FOR BLADE OF WIND POWER GENERATOR - The present invention provides a protection film for blades to be adhered to the blade surface of wind power generators, which has a substrate and a pressure-sensitive adhesive layer on one surface of the substrate. | 09-19-2013 |
20130251537 | TITANIUM ALUMINIDE INTERMETALLIC COMPOSITIONS - Gamma titanium aluminide intermetallic compositions (gamma TiAl intermetallics) based on the TiAl (gamma) intermetallic compound. The gamma TiAl intermetallics contain chromium and niobium, as well as controlled amounts of carbon that achieve a desirable balance in room temperature mechanical properties and high temperature creep capabilities at temperatures approaching and possibly exceeding 1600° F. (about 870° C.). | 09-26-2013 |
20130272894 | Archimedean Modular / Multi-Axis Rotor (AMR) - An Archimedean Modular/Multi-Axis Rotor (AMR) is a wind/fluid driven electrical generating device as described which utilizes a single foil rotor and appears in an elongated Archimedean curve tapering at its ends. A plurality of AMR's can be assembled in a multiplicity of tetrahedral or other 3-dimensional type structures that generate electric power. | 10-17-2013 |
20130272895 | IMPELLER, ROTOR COMPRISING SAME, AND IMPELLER MANUFACTURING METHOD - An impeller is formed of two parts, i.e., an inner peripheral side part and an outer peripheral side part. The inner peripheral side part is molded in a cylindrical shape. The outer peripheral side part is formed by integrally molding an annular disc externally fitted to an outer peripheral surface of the inner peripheral side part, a plurality of blades provided at an interval in a circumferential direction on a surface that faces the other side in the axis line direction of the annular disc and forming al flow path extending in a radial direction, and a cover covering the plurality of blades from the other side in the axis line direction and having an insertion hole to which the inner peripheral side part is inserted in the axis line direction at an interval in a radial direction. | 10-17-2013 |
20130280088 | WIND TURBINE COMPONENT COMPRISING RADAR-ABSORBING MATERIAL - A method of making a wind turbine component of composite construction with enhanced radar absorbing properties is described. The method comprises making the component and then modifying the component by applying circuit analogue elements to a surface of the component. | 10-24-2013 |
20130287590 | GENERATIVELY PRODUCED TURBINE BLADE AND DEVICE AND METHOD FOR PRODUCING SAME - The present invention relates to a method for producing gas turbine components, in particular aircraft turbine components, preferably low-pressure turbine blades, from a powder which is sintered selectively in layers by locally limited introduction of radiant energy, wherein the sintering is carried out in a closed first housing ( | 10-31-2013 |
20130294925 | CORE FOR A COMPOSITE STRUCTURE AND METHOD OF FABRICATION THEREOF - A flexible core ( | 11-07-2013 |
20130294926 | ANTIFOULING FILM, AIR BLOWER BLADE PROVIDED WITH SAME, AIR BLOWER, AND ANTIFOULING COATING MATERIAL - An antifouling film is coated on a base, and contains a binder component, conductive particles, and a fluororesin. The conductive particles are bound together by the binder component; the binder component is closely bound to the base; and the antifouling film has a comprising the conductive particles of which surfaces are covered with the fluororesin. | 11-07-2013 |
20130309098 | TURBOCOMPRESSOR ROTOR AND METHOD FOR PRODUCING THE SAME - A turbocompressor rotor for a turbocompressor for compressing process gas has a rotor body which makes contact with the process gas and which is produced entirely from a stainless steel material including 0.3 to 1.2% carbon and 12 to 19% chromium, wherein the steel material includes the alloy X39CrMo17-1.9. A process for producing such a turbocompressor rotor by casting includes manufacturing a casting model corresponding to the geometry of the rotor body by rapid technology and producing a casting mold using the casting model, or manufacturing a casting mold corresponding to the negative geometry of the rotor body by rapid technology, introducing the liquid steel material into the casting mold to form a cast workpiece as the rotor body, and finishing the turbocompressor rotor with the rotor body. | 11-21-2013 |
20130323074 | FRICTION WELDED TURBINE DISK AND SHAFT - An assembly for use in a turbine of a gas turbine engine includes a turbine disk and a shaft. The turbine disk comprises a superalloy. The shaft is friction welded to the turbine disk at a shaft interface substantially adjacent the turbine disk. | 12-05-2013 |
20130323075 | NICKEL-CHROMIUM-MOLYBDENUM-VANADIUM ALLOY AND TURBINE COMPONENT - A NiCrMoV alloy and a turbine component are disclosed. The NiCrMoV alloy includes at least about 0.06%, at least about 3.40% nickel, between about 0.22% and about 0.30% carbon, up to about 0.60% molybdenum, up to about 0.15% vanadium, up to about 2.00% chromium, up to about 0.012% phosphorus, up to about 0.007% sulfur, up to about 0.10% silicon, up to about 0.002% antimony, up to about 0.008% arsenic, up to about 0.012% tin, and up to about 0.015% aluminum and/or is resistant to embrittlement at temperatures above 700° F. | 12-05-2013 |
20130330203 | METHOD FOR PRODUCING A PROTECTIVE LAYER FOR A ROTOR BLADE - A method for producing a protective layer for a rotor blade of a turbomachine is proposed. The rotor blade has a wear cap wall that in relation to the axis of the turbomachine protrudes radially towards the exterior of the turbomachine beyond a body of the rotor blade. The method enables the entire rotor blade to have a comparatively long service life and at the same time allows the wear cap wall to be thermally insulated in an especially simple manner. For the purpose, a profile producing a positive fit effective in the radial direction is inserted in a radially located region of the wear cap wall, a slip containing metal powder and/or a ceramic slip is applied to the region and the slip in sintered. | 12-12-2013 |
20130336799 | COMPRESSOR BLADE - A compressor component having an improved airfoil profile so as to eliminate previously known vibratory issues in the blade tip is disclosed. By altering the airfoil profile throughout its span, the natural frequency of the airfoil is altered so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1. | 12-19-2013 |
20130336800 | CHANNEL MARKER AND RELATED METHODS - Various embodiments of the disclosure include a component, methods of forming components, and methods of cooling components. In some embodiments, a component is disclosed including: a body; a microchannel extending through a portion of the body; a thermal barrier coating (TBC) covering a portion of the microchannel; and a marker member extending from the microchannel through the TBC or from an end of the microchannel, the marker member indicating a location of the microchannel in the body. | 12-19-2013 |
20130343900 | PROCESS FOR PRODUCING A RUN-IN COATING - Disclosed is a process for producing a run-in coating ( | 12-26-2013 |
20130343901 | REPAIR METHOD AND REPAIRED ARTICLE - A repaired article includes a body extending between a first side and a second side. The body has a repair section with an associated thickness between the first side and the second side. The repair section includes regions of plastic deformation distributed through the thickness. A gas turbine engine including the body is also disclosed. | 12-26-2013 |
20140030108 | METHOD OF STICKING TOGETHER AND UN-STICKING TWO PARTS BY MEANS OF A FILLED ADHESIVE - The invention provides a method of bonding a first part on a second part made of composite material by means of an adhesive, wherein said adhesive is filled with elements of shape memory alloy. The invention also provides a method of un-sticking the first part adhesively bonded on the composite material second part, said un-sticking method comprising a step of weakening the adhesive interface that consists in subjecting the adhesively bonded parts to heat treatment performed at a temperature that is lower or higher than the martensitic transformation temperature of the shape memory alloy elements. | 01-30-2014 |
20140030109 | low-Modulus Gas-Turbine Compressor Blade - The present invention relates to an aircraft gas-turbine compressor blade having an airfoil with a leading edge, with at least the area of the leading edge being made from a low-modulus titanium alloy. | 01-30-2014 |
20140050590 | INTENTIONALLY FREQUENCY MISTUNED TURBINE BLADES - A new, more economical design for intentionally frequency mistuned turbine blades for more efficient turbine engines is disclosed. A rotating disk of a turbine engine includes first turbine blades that alternate between second turbine blades. The second turbine blades are thicker than the first turbine blades, within manufacturing tolerances, in sections from about their mean line to their airfoil tip. The first and second turbine blades can be cast using two different molds, resulting in an economical manufacturing method. As such, the natural frequency of the second turbine blades is about 3% less than the natural frequency of the first turbine blades. As a result of the intentional difference in natural frequencies of the two different turbine blades, the rotating disk does not experience flutter instability. | 02-20-2014 |
20140056715 | VARIABLE LENGTH BLADE TIP MOLDS, TIP ASSEMBLIES AND METHODS FOR MANUFACTURING THE SAME - Variable length blade tip molds include standard tip mold sections having a tapered profile and variable length joint mold sections having first ends and second ends with a constant cross section, wherein the variable length blade tip molds can each produce a plurality of tip assemblies of various lengths. | 02-27-2014 |
20140064981 | Ni Base Forged Alloy and Gas Turbine Utilizing the Same - An Ni base forged alloy is easy to make hot forging and miniaturization of crystal grains while excellent high-temperature strength and segregation property are compatible. The Ni base forged alloy has solid solution temperature of a precipitation strengthening phase lower than or equal to 970° C., difference in the solid solution temperature between a δ-phase and the precipitation strength phase larger than or equal to 50° C., Al of 0.5 to 1.0%, Cr of 17 to 21%, Fe of 17 to 19%, Nb of 4.5 to 5.5%, Ti of 0.8 to 1.3%, W of 3.0 to 6.0%, B of 0.001 to 0.03%, C of 0.001 to 0.1% and Mo of 1.0% or less in mass percentage [%] and remainder made of Ni and inevitable impurities. | 03-06-2014 |
20140064982 | Ni Base Alloy and Gas Turbine Blade and Gas Turbine Utilizing the Same - An Ni base alloy uses GTD-111 as a base to improve high-temperature strength while maintaining the weldability and corrosion resistance and a gas turbine blade utilizes the Ni base alloy. The Ni base alloy contains Al of 2.5 to 3.5%, Co of 1.5 to 5.5%, Cr of 11.8 to 13.8%, Mo of 0.4 to 1.4%, Ta of 3.0 to 5.0%, Ti of 5.1 to 6.1%, W of 3.3 to 4.3%, B of 0.01 to 0.02%, C of 0.08 to 0.12% in mass % and remainder containing Ni and inevitable impurities and does not substantially contain Nb. | 03-06-2014 |
20140072440 | ATTACHMENT SYSTEM FOR A WIND TURBINE ROTOR BLADE ACCESSORY - A rotor blade assembly for a wind turbine has a rotor blade. A strip-member blade accessory is mounted to one of the rotor blade surfaces that stretches under normal operating conditions of the wind turbine. The blade accessory has a base portion. An attachment layer connects the base portion to the rotor blade surface and has a lower shear modulus than the base portion to allow for shear slippage between the base portion and the underlying rotor blade surface. | 03-13-2014 |
20140072441 | LOAD AND NOISE MITIGATION SYSTEM FOR WIND TURBINE BLADES - A load and noise mitigation system ( | 03-13-2014 |
20140072442 | NEAR-INFRARED RADIATION CURABLE MULTILAYER COATING SYSTEMS AND METHODS FOR APPLYING SAME - Multilayer coating systems, methods of applying and related substrates are disclosed. The coating system may comprise a first coating comprising a near-IR absorber, and a second coating deposited on a least a portion of the first coating. Methods of applying a multilayer coating composition to a substrate may comprise applying a first coating comprising a near-IR absorber, applying a second coating over at least a portion of the first coating and curing the coating with near infrared radiation. | 03-13-2014 |
20140072443 | Composite Turbomachine Blade with In-Built Root - A turbine engine blade of composite material comprising fiber reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade has a first portion constituting an airfoil forming a single piece with at least one second portion constituting a blade root. The fiber reinforcement portions corresponding to the first and second portions of the blade are mutually interleaved, at least in part, with yarns of the second fiber reinforcement portion penetrating into the first fiber reinforcement portion. | 03-13-2014 |
20140086755 | TURBOCHARGER AND COMPONENT THEREFOR - A component for turbocharger applications, in particular in diesel engines, which has an iron-based alloy having a ferritic base structure which has a carbide and nitride structure. | 03-27-2014 |
20140093384 | Method of Manufacturing Complex Shaped Component - A method of forming a complex shaped part includes the steps of forming a polymer core by an additive manufacturing process. A metal is plated about surfaces of the polymer core, and the polymer core is removed, leaving hollows within a plate core. Metal powder is deposited within the hollows. An integral blade rotor is also disclosed. | 04-03-2014 |
20140099209 | GAS TURBINE COMPONENT, METHOD FOR ITS PRODUCTION AND CASTING MOLD FOR USE OF THIS METHOD - A method is provided for casting a gas turbine component having at least a first section and a second section. As per the method, a liquid metal is cast into a casting mold and solidification of the metal is induced by means of controlled cooling. The cooling of the liquid metal in the first section is controlled in such a way that the metal solidifies in a directionally solidified crystal structure or a single-crystal structure. In the second section the cooling is carried out in such a way that it solidifies in a multidirectional crystal structure. | 04-10-2014 |
20140105752 | DRUM POUCH WIND TURBINE - The Drum Pouch Wind Turbine consists of drum shaped cage structures wrapped with fabric pouches all around the perimeter which catch the wind on one side. The pouches may be stretched between two rings, one ring on each end. The system may consist of at least two drum impellers, one drum rotating clockwise and the other counter clockwise, doubling the relative rotational velocity between each pair of drums and having double the torque (because of the counter rotation), thereby increasing power output with the same wind speed. In essence, the system is composed of two counter rotating impellers and one generator, one portion of the generator on each drum. | 04-17-2014 |
20140105753 | Precipitation Hardening Martensitic Stainless Steel and Long Blade for Steam Turbine Using the Same - A precipitation hardening martensitic stainless steel is provided with excellent mechanical property and corrosion resistance and contains, by mass, 0.1% or less of C; 0.1% or less of N; 10.0%˜15.0% of Cr; 10.0%˜15.0% of Ni; 0.5%˜2.5% of Mo; 1.0%˜3.0% of Al; 1.0% or less of Si; 1.0% or less of Mn, and the rest is Fe and inevitable impurities. A steam turbine long blade is made of the precipitation hardening martensitic stainless steel. | 04-17-2014 |
20140119940 | WIND TURBINE BLADES WITH TENSION FABRIC SKIN STRUCTURE - A wind blade with a self-supporting structural framework, having multiple chord-wise members and one or more span-wise members is provided. Each of the multiple chord-wise members and the one or more span-wise members have an aerodynamic contour. The wind blade also comprises a fabric skin located over the self-supporting structural framework in a tensioned state to generate an aerodynamic surface, wherein the fabric skin is attached via multiple tensioning members to both the chord wise members and span wise members. | 05-01-2014 |
20140119941 | CREEP-RESISTANT, RHENIUM-FREE NICKEL BASE SUPERALLOY - Disclosed is a nickel base alloy which is substantially free of rhenium and has a solidus temperature of more than 1320° C. Precipitates of a γ′-phase are present in a γ-matrix with a fraction of 40 to 50 vol % at 1050° C. to 1100° C., and a γ/γ′ mismatch at 1050° C. to 1100° C. is from −0.15% to −0.25%. The alloy comprises 11 to 13 at % aluminum, 4 to 14 at % cobalt, 6 to 12 at % chromium, 0.1 to 2 at % molybdenum, 0.1 to 3.5 at % tantalum, 0.1 to 3.5 at % titanium, 0.1 to 3 at % tungsten. The tungsten content of the γ-matrix is greater than that in the precipitated γ′-phases. | 05-01-2014 |
20140119942 | TURBINE ROTOR BLADE OF A GAS TURBINE - The present invention relates to a turbine rotor blade of a gas turbine with a blade tip, said blade tip having at least on its suction side, extending from a stagnation point on the blade leading edge to an intersection point of the suction-side profile line of the blade with a trailing-edge circle, an overhang which is substantially zero at the stagnation point and at the intersection point and which has a maximum value at around 40% of the running length of the suction-side overhang. | 05-01-2014 |
20140127032 | Casting method, apparatus, and product - A casting method and apparatus are provided for casting a near-net shape article, such as for example a gas turbine engine blade or vane having a variable cross-section along its length. A molten metallic melt is provided in a heated mold having an article-shaped mold cavity with a shape corresponding to that of the article to be cast. The melt-containing mold and mold heating furnace are relatively moved to withdraw the melt-containing mold from the furnace through an active cooling zone where cooling gas is directed against the exterior of the mold to actively extract heat. At least one of the mold withdrawal rate, the cooling gas mass flow rate, and mold temperature are adjusted at the active cooling zone as the melt-containing mold is withdrawn through the active cooling zone to produce an equiaxed grain microstructure along at least a part of the length of the article. | 05-08-2014 |
20140133996 | WEAR RESISTANT SLURRY PUMP PARTS PRODUCED USING HOT ISOSTATIC PRESSING - In one aspect, a method for manufacturing a part for a centrifugal slurry pump is provided, comprising: forming a skeleton of the part having an outer dimension smaller than the part; placing the skeleton of the part in a metal enclosure having an interior dimension larger than the outer dimension of the skeleton of the part and thereby forming a space; adding a metal matrix composite powder into the metal enclosure to fill the space; and subjecting the metal enclosure to hot isostatic pressing, thereby allowing bonding of the metal matrix composite to the skeleton of the part to form the part. | 05-15-2014 |
20140154093 | METHOD OF HEAT TREATING A SUPERALLOY ARTICLE AND ARTICLE MADE THEREBY - A method of heat treating a superalloy article is disclosed. The method includes hot-working an article comprising an superalloy to produce a hot-worked microstructure throughout the article; solution treating the article at a temperature and for a time sufficient to form a partially recrystallized warm-worked microstructure throughout the article; and cooling the article. The method also includes precipitation aging the article at a first precipitation aging temperature of about 1300° F. to about 1400° F. for a first duration of about 4 hours to about 12 hours; cooling the article to a second precipitation aging temperature; precipitation aging the article at a second precipitation aging temperature of about 1150° F. to about 1200° F. for a second duration of about 4 hours to about 12 hours; and cooling the article from the second precipitation aging temperature to an ambient temperature. | 06-05-2014 |
20140154094 | 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. | 06-05-2014 |
20140161623 | TURBINE ENGINES WITH CERAMIC VANES AND METHODS FOR MANUFACTURING THE SAME - A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring. | 06-12-2014 |
20140161624 | METHOD FOR PRODUCING A RUN-IN COATING, A RUN-IN SYSTEM, A TURBOMACHINE, AS WELL AS A GUIDE VANE - A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating. | 06-12-2014 |
20140169979 | GAS TURBINE ENGINE FAN BLADE PLATFORM SEAL - A fan section for a gas turbine engine includes a fan blade having an airfoil with an exterior surface. A platform seal is adhered to the airfoil. A fan section for a gas turbine engine includes a fan hub having a slot. A fan blade includes an airfoil extending from a root to a tip. The root is received in the slot. A platform is secured to the fan hub and is arranged between adjacent fan blades. A seal has a base secured to opposing sides of the fan blade and a flap integral with and extending from the base portion and canted toward the root and engaging the platform to provide a sealed inner flow path. | 06-19-2014 |
20140169980 | ROOT ASSEMBLIES WITH EXTERNAL STRUCTURAL CONNECTION SUPPORTS FOR ROTOR BLADES - Root assemblies for rotor blades include a root portion having an inner surface and an outer surface, wherein the root portion is configured to extend from an airfoil portion of the rotor blade. The root assemblies further include at least one external structural connection support connected to at least the inner surface or the outer surface of the root portion, wherein the at least one external structural connection support connects to a hub of a wind turbine to facilitate the connection of the rotor blade. | 06-19-2014 |
20140178205 | JOINTS FOR CONNECTING BLADE SEGMENTS OF A WIND TURBINE ROTOR BLADE - Joints for connecting a first blade segment to a second blade segment of a wind turbine rotor blade include a first bolt comprising a first proximal end connected to the first blade segment and a first distal end connected to the second blade segment, a second bolt comprising a second proximal end connected to the first blade segment and a second distal end connected to the second blade segment, and a third bolt comprising a third proximal end connected to the first blade segment and a third distal end connected to the third blade segment. At least two of the first bolt, the second bolt and the third bolt differ in size, and a first distance between the first bolt and the second bolt is different than a second distance between the second bolt and the third bolt. | 06-26-2014 |
20140178206 | METHOD FOR CREATING A BLADE FOR A FLOW ENGINE AND BLADE FOR A FLOW FORCE ENGINE - A method for creating a blade ( | 06-26-2014 |
20140193270 | CERAMIC COMPOSITE MATRIX MATERIAL BONDED ASSEMBLY AND PROCESSES THEREOF - A method of making multipart assemblies by producing single parts from ceramic composite materials that are machined and bonded together to form the multipart assembly. The method is used to make turbine engine vanes. | 07-10-2014 |
20140193271 | METHOD OF MAKING PROTECTIVE REINFORCEMENT FOR THE LEADING EDGE OF A BLADE - A method of making a reinforcement for reinforcing a leading edge of a blade, the method including depositing a metal coating on the leading edge by thermal spraying in compression. A blade, for example a blade for a turbine engine, a helicopter, or a propeller, can have the leading edge protected by such a reinforcement. | 07-10-2014 |
20140199175 | GAS TURBINE ENGINE COMPONENTS AND METHODS FOR THEIR MANUFACTURE USING ADDITIVE MANUFACTURING TECHNIQUES - In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3D design model for the component, adding one or more crack resistant features to the 3D design model of the component to produce an enhanced design model, and manufacturing the component using an additive manufacturing technique in accordance with the enhanced design model. The one or more crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured component. | 07-17-2014 |
20140212296 | METHOD OF COATING OF AND/OR APPLYING LACQUER ON MAGNETIC RINGS OF A ROTOR MAGNETIC BEARING, ROTOR MAGNETIC BEARING, AND VACUUM PUMP - A method of at least one of coating of and applying lacquer on magnetic rings of a rotor magnetic bearing mounted on the rotor, includes arranging of the magnetic rings ( | 07-31-2014 |
20140234117 | APPARATUS AND METHOD TO REDUCE WEAR AND FRICTION BETWEEN CMC-TO-METAL ATTACHMENT AND INTERFACE - An apparatus to reduce wear and friction between CMC-to-metal attachment and interface, including a metal layer configured for insertion between a surface interface between a CMC component and a metal component. The surface interface of the metal layer is compliant relative to asperities of the surface interface of the CMC component. A coefficient of friction between the surface interface of the CMC component and the metal component is about 1.0 or less at an operating temperature between about 300° C. to about 325° C. and a limiting temperature of the metal component. | 08-21-2014 |
20140234118 | TURBINE ENGINE COMPRISING A METAL PROTECTION FOR A COMPOSITE PART - A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface. | 08-21-2014 |
20140234119 | BLADE FOR WIND TURBINE AND METHOD OF ASSEMBLY OF THE BLADE - It is described a blade ( | 08-21-2014 |
20140248157 | BLADE OR VANE OF DIFFERING ROUGHNESS AND PRODUCTION PROCESS - A blade or vane of different roughness and a process for producing such a blade or vane are presented. The performance of the blade or vane of a compressor or of a turbine can be improved because of the different configuration of the roughness of the surfaces on the suction side and the pressure side of the blade or vane. | 09-04-2014 |
20140255201 | Removable Rotor Blade Tip - A rotor blade has a spanwise axis, a root comprising an anchor having an anchor surface configured to form at least one of a normal angle relative to the spanwise axis and an acute angle relative to the spanwise axis, and a selectively removable tip comprising a connector having a connector surface configured to complement the anchor surface. | 09-11-2014 |
20140271219 | MOLTEN METAL ROTOR WITH HARDENED TOP - Embodiments of the invention are directed to a rotor for a molten metal pump and a molten metal pump including the rotor. The rotor has a main body and a top comprised of a material that is at least twice as hard as the main body. The top, among other things, may form a first portion of each rotor blade wherein the first portion directs molten metal into a pump chamber or other structure in which the rotor is mounted. | 09-18-2014 |
20140271220 | EROSION RESISTANT COATING - A platinum plus chromium coating applied to the roots and firtrees of turbine blades where the inclusion of chromium creates a single phase outer zone which minimises diffusion paths for sulphur which can preferentially diffuse down phase boundaries and enables a chromium rich outer oxide scale to form on top of the coating. | 09-18-2014 |
20140271221 | USAGE OF A WITNESS MARK TO DISTINGUISH SUPPORT STRUCTURE FROM PART - A component includes a support structure made with an additive manufacturing process with a first end and a second end, and an object made with an additive manufacturing process with a first end and a second end, where the first end of the object is attached to the second end of the support structure. A cross-sectional area of the first end of the object is larger than a cross-sectional area of the second end of the support structure. A method of making an object, the method includes manufacturing a support structure with an additive manufacturing process. An object is manufactured on top of and connected to the support structure with an additive manufacturing process, wherein there is a witness mark created between the support structure and the object. The witness mark is identified. The object is separated from the support structure along the witness mark. | 09-18-2014 |
20140301861 | AIRFOIL HAVING AN EROSION-RESISTANT COATING THEREON - A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, a forward-most nose of the airfoil located at the leading edge and having a profile, a blade tip, and an erosion-resistant coating. The coating is present on the concave surface near the trailing edge, optionally present on the nose, optionally present on the convex surface, wherein the convex surface is free of the erosion resistant coating within at least 20% of the chord length from the nose. The thickness of the coating on the concave surface, the convex surface, and the nose is such that, if the gas turbine engine is exposed to an erosive environment, deterioration of the concave surface, the convex surface and the leading edge does not form a pronounced cusp at an intersection of the convex surface and leading edge. | 10-09-2014 |
20140322025 | Structural Member with X-Web - Disclosed is a structure that may include a first flange, a second flange, and a web connecting the first flange to the second flange. In example embodiments, the web may include at least one end with at least two angled members attaching to one of the first flange and the second flange and another end connecting to the other of the first flange and the second flange. Disclosed also is a wind turbine blade that includes the structure. | 10-30-2014 |
20140328694 | Protective Finish for Wing Tip Devices - The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying the sheath to the surface of the airfoil. In one or more embodiments, the sheath wraps around the surface of the airfoil from the leading edge of the airfoil towards the trailing edge of the airfoil. In at least one embodiment, the sheath covers approximately 50 percent to approximately 70 percent of the chord length of the airfoil. In some embodiments, the sheath is manufactured from at least one polymer, such as a polyurethane and/or a floropolymer. In one or more embodiments, the airfoil is a winglet, a raked wing tip, and/or a wing. | 11-06-2014 |
20140334939 | HIGH PURITY POWDERS - This invention relates to high purity yttria or ytterbia stabilized zirconia powders comprising from about 0 to about 0.15 weight percent impurity oxides, from about 0 to about 2 weight percent hafnium oxide (hafnia), from about 6 to about 25 weight percent yttrium oxide (yttria) or from about 10 to about 36 weight percent ytterbium oxide (ytterbia), and the balance zirconium oxide (zirconia). Thermal barrier coatings for protecting a component such as blades, vanes and seal surfaces of gas turbine engines, made from the high purity yttria or ytterbia stabilized zirconia powders, have a density greater than 88% of the theoretical density with a plurality of verticalzA macrocracks homogeneously dispersed throughout the coating to improve its thermal fatigue resistance. | 11-13-2014 |
20140356183 | RHENIUM-FREE OR RHENIUM-REDUCED NICKEL-BASE SUPERALLOY - A nickel-base superalloy is disclosed. The superally includes aluminium, cobalt, chromium, molybdenum, tantalum, titanium and tungsten, in addition to nickel, as alloy constituents, wherein rhenium can additionally be contained and the rhenium content is less than or equal to 2 wt. % and wherein the titanium content is greater than or equal to 1.5 wt. %. Further disclosed is a component made of the nickel-base superalloy. | 12-04-2014 |
20140363305 | Hybrid Turbine Blade for Improved Engine Performance or Architecture - A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method comprises introducing a molten alloy into a mold; and varying a composition of the introduced alloy during the introduction so as to produce a compositional variation. | 12-11-2014 |
20140369851 | METHOD OF FABRICATING A SURFACE FOR REDUCING ICE ADHESION STRENGTH - A method of fabricating a surface for reducing ice adhesion surface which includes providing a surface of a cured material and impacting the surface of the cured material with a pressurized jet of a fluid material to plastically deform the cured material to enable the surface to reduce ice adhesion strength on the surface. | 12-18-2014 |
20140377078 | ROOT STIFFENER FOR A WIND TURBINE ROTOR BLADE - A rotor blade for a wind turbine may include a body extending between a root end and a tip end. The body may include a root portion extending from the root end. The root portion may include an inner surface defining an inner circumference. The rotor blade may also include a root stiffener disposed within the root portion of the body. The root stiffener may be substantially ring-shaped and may extend around the inner circumference of the root portion. The root stiffener may define a plurality of radially oriented openings configured to receive fasteners for coupling the root stiffener to the root portion. | 12-25-2014 |
20150017015 | Nickel Based Alloy for Forging - A nickel (Ni) based alloy for forging includes: 0.001 to 0.1 wt. % of carbon (C); 12 to 23 wt. % of chromium (Cr); 3.5 to 5.0 wt. % of aluminum (Al); 5 to 12 combined wt. % of tungsten (W) and molybdenum (Mo) in which the Mo content is 5 wt. % or less; a negligible small amount of titanium (Ti), tantalate (Ta) and niobium (Nb); and the balance of Ni and inevitable impurities. | 01-15-2015 |
20150030459 | TURBOMACHINE COMPONENT WITH A PARTING JOINT, AND A STEAM TURBINE COMPRISING SAID TURBOMACHINE COMPONENT - A turbomachine component is provided having at least two sub-components that are separated by a parting joint and each have a sealing surface at the parting joint, at least one of the two sealing surfaces being convex in order to form a linear contact of the two sealing surfaces. At least one of the sealing surfaces has a coating on it which includes a hard material, is a maximum of 30 μm thick and is applied using a vapour deposition method, or a coating which includes a chrome-containing alloy, is a maximum of 30 μm thick and is applied by a vapour deposition method, or is a maximum of 300 μm thick and applied using a thermal spraying method. | 01-29-2015 |
20150050157 | HOLD AND COOL PROCESS FOR SUPERALLOY JOINING - Ni base superalloys containing relatively large amounts of Al and/or Ti are known to be difficult to weld satisfactorily. As the Al and Ti content of the superalloy is increased to improve the strength, the weldability of the component is drastically reduced. It is concluded herein that reducing the γ′ phase improves weldability. A stepwise, controlled heating and cooling process is described to be used in cooperation with a welding process to reduce the γ′ present and thereby improve weldability. | 02-19-2015 |
20150050158 | GAS TURBINE ENGINE COMPONENT INCLUDING A COMPLIANT LAYER - A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel. | 02-19-2015 |
20150056081 | A Post-Moulding Station and an Associated Method of Manufacture of a Wind Turbine Blade - A post-moulding station is described which is used in the manufacturing of a wind turbine blade. A blade shell forming part of a wind turbine blade is initially moulded in a blade mould, the blade shell subsequently transferred to a post-moulding station which allows for various post-moulding operations to be carried out on the blade shell away from the mould, thereby increasing the productivity of the blade mould in the manufacturing process. The post-moulding station may be operable to perform the closing of first and second blade shells to form a wind turbine blade, and may be formed from an adjustable structure which can provide relatively easy access to the contained blade shell for working thereon. Accordingly, the manufacturing equipment may be of reduced cost, combined with an increase in the overall productivity of the manufacturing system. | 02-26-2015 |
20150064017 | ROTOR BLADE FOR A WIND POWER PLANT - The invention concerns a rotor blade of a wind power installation, comprising a rotor blade root for attachment of the rotor blade to a rotor hub and a rotor blade tip arranged at a side remote from the rotor blade root, as well as a wind power installation having such rotor blades. In that arrangement a relative profile thickness which is defined as the ratio of profile thickness to profile depth has a local maximum in a central region between rotor blade root and rotor blade tip. | 03-05-2015 |
20150078913 | ARRANGEMENT TO REDUCE NOISE EMISSION - An arrangement to reduce noise emission generated by a wind turbine rotor blade is provided. The arrangement includes the rotor blade and a noise reduction device attached thereto. The rotor blade has a suction side and pressure side, leading and trailing edge sections with a trailing edge. The noise reduction device has an inner surface facing the rotor blade trailing edge section, and an outer surface opposite to the inner surface. The noise reduction device has a leading and trailing edge, both connecting the inner and outer surface. The noise reduction device is connected at the rotor blade trailing edge section by a connector. The inner surface has a pre-defined distance to at least one side of the rotor blade chosen so acoustic waves generated at the rotor blade trailing edge section are reflected by the inner surface to reduce noise emission generated by the wind turbine rotor blade. | 03-19-2015 |
20150093250 | ROOT STIFFENER ASSEMBLY FOR A WIND TURBINE ROTOR BLADE - In one aspect, a rotor blade for a wind turbine may include a body extending between a root end and a tip end. The body may include a root portion extending from the root end. The root portion may include an inner surface defining an inner circumference. In addition, the rotor blade may include a root stiffener assembly disposed within the root portion of the body. The root stiffener assembly may include a plurality of stiffening ribs coupled to the root portion so as to extend along the inner surface. The stiffening ribs may be spaced apart from one another circumferentially around the inner circumference of the root portion | 04-02-2015 |
20150118060 | TURBINE ENGINE BLADES, RELATED ARTICLES, AND METHODS - A compressor blade generally used in turbine engines is presented. The compressor blade includes a protective covering bonded to a tip portion of the blade with a braze material. The braze material includes from about 1 weight percent to about 10 weight percent of an active metal element, based on the total amount of the braze material. A compressor rotor is also provided that includes a plurality of the compressor blades. A method for joining a protective covering to a tip portion of a compressor blade, and a method for repair of a compressor blade, are also provided. | 04-30-2015 |
20150132143 | WELDING PROCESS AND REDUCED RESTRAINT WELD JOINT - A weld joint ( | 05-14-2015 |
20150132144 | PRECIPITATION HARDENING MARTENSITIC STAINLESS STEEL, TURBINE COMPONENT FORMED OF SAID MARTENSITIC STAINLESS STEEL, AND TURBINE INCLUDING SAID TURBINE COMPONENT - It is an objective of the invention to provide a precipitation-hardening martensitic stainless steel having a far better balance between a high mechanical strength and a high toughness than conventional ones as well as having good corrosion resistance properties. There is provided a precipitation-hardening martensitic stainless steel throughout which precipitates of intermetallic compounds are dispersed, the martensitic stainless steel including: 0.1 mass % or less of C; 11 to 13 mass % of Cr; 7.5 to 11 mass % of Ni; 0.9 to 1.7 mass % of Al; 0.85 to 1.35 mass % of Mo; 1.75 to 2.75 mass % of W; and the balance including Fe and inevitable impurities, in which “[Mo content]+0.5×[W content]” is from 1.9 mass % to 2.5 mass %, and “[Mo content]/[W content]” is from 0.4 to 0.6. | 05-14-2015 |
20150147185 | TURBINE BUCKETS WTIH HIGH HOT HARDNESS SHROUD-CUTTING DEPOSITS - Turbine buckets include a pressure side, a suction side opposite the pressure side, and a bucket squealer tip attached to the pressure side and the suction side. The bucket squealer tip includes a plurality of high hot hardness shroud-cutting deposits deposited on its exterior surface that have a hardness of at least about 1100 kg mm | 05-28-2015 |
20150147186 | SILICON CARBIDE-CONTAINING MOLD AND FACECOAT COMPOSITIONS AND METHODS FOR CASTING TITANIUM AND TITANIUM ALUMINIDE ALLOYS - The disclosure relates generally to mold compositions and methods of molding and the articles so molded. More specifically, the disclosure relates to silicon carbide-containing mold compositions, silicon carbide-containing intrinsic facecoat compositions, and methods for casting titanium-containing articles, and the titanium-containing articles so molded. | 05-28-2015 |
20150292063 | Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE BLADE INCORPORATING THE SAME - A Ni-based single crystal superalloy which has the following composition: Co: 4.0 to 9.5 wt %, Cr: 5.1 to 8.0 wt %, Mo: 2.1 to 3.5 wt %, W: 0.0 to 2.9 wt %, Ta: 4.0 to 10.0 wt %, Al: 4.5 to 6.5 wt %, Ti: 0.0 to 1.0 wt %, Hf: 0.08 to 0.5 wt %, Nb: 0.0 to 3.0 wt %, Re: 4.5 to 8.0 wt % and Ru: 0.5 to 6.5 wt % with the remainder including Ni and unavoidable impurities, wherein P1≦700 is satisfied in which P1 represents a parameter 1, which is obtained by a formula: P1=137×[W(wt %)]+24×[Cr(wt %)]+46×[Mo(wt %)]−18×[Re(wt %)]. | 10-15-2015 |
20150292339 | Method and Device for Manufacturing Turbine Blades - The present invention relates to a method and device for manufacturing turbine blades ( | 10-15-2015 |
20150315921 | PRECIPITATION HARDENED MARTENSITIC STAINLESS STEEL, MANUFACTURING METHOD THEREFOR, AND TURBINE MOVING BLADE AND STEAM TURBINE USING THE SAME - The precipitation hardened martensitic stainless steel is characterized by containing, in percent by weight, 12.25 to 14.25% Cr, 7.5 to 8.5% Ni, 1.0 to 2.5% Mo, 0.05% or less C, 0.2% or less Si, 0.4% or less Mn, 0.03% or less P, 0.005% or less S, 0.008% or less N, 0.90 to 2.25% Al, the balance substantially being Fe, and the total content of Cr and Mo being 14.25 to 16.75%. A turbine moving blade and a steam turbine are manufactured by using this martensitic stainless steel. | 11-05-2015 |
20150330232 | TURBOMACHINE COMPONENT HAVING A FUNCTIONAL COATING - A turbomachine component having a main body and a multilayer coating, which is applied directly to the main body is provided. The multilayer coating is at least 5 μm and at most 35 μm thick and has a plurality of layers applied directly one on top of the other, wherein the layer applied directly to the main body is an adhesion promoting layer, which comprises chromium nitride, and at least one of the remaining layers comprises a hard material. | 11-19-2015 |
20150337670 | COMPOSITE AEROFOIL STRUCTURE WITH A CUTTING EDGE TIP PORTION - An aerofoil structure ( | 11-26-2015 |
20150337671 | ABRASIVE BLADE TIP TREATMENT - An abrasive coating for a metal airfoil tip in a gas turbine engine may include a plurality of grit particles coated with a braze alloy material and configured for attachment to the airfoil tip. The braze alloy may be a nickel base, cobalt base or iron base braze alloy or mixtures thereof, or a titanium base braze alloy. | 11-26-2015 |
20150344753 | POLYURETHANE-BASED ADHESIVES - The present disclosure generally relates to curable precursor compositions for a polyurethane adhesive. In one exemplary embodiment, the composition includes (a) an isocyanate component comprising one or more isocyanates and (b) an isocyanate-reactive component comprising
| 12-03-2015 |
20150354358 | Post-Peen Grinding of Disk Alloys - A process for forming a metallic article comprises: peening a precursor to create a residual stress distribution and a region of slip bands; and surface machining the precursor to substantially remove the slip band region while leaving a substantial amount of the residual stress distribution. | 12-10-2015 |
20150354540 | ROOT BUSHING FOR A BLADE ROOT OF A WIND TURBINE ROTOR BLADE, A BLADE ROOT, A WIND TURBINE ROTOR BLADE, A WIND TURBINE AND A METHOD FOR MANUFACTURING A ROOT BUSHING - A root bushing for a blade root of a wind turbine rotor blade, a blade root, a wind turbine rotor blade, a wind turbine and a method for manufacturing a root bushing are provided herein. A root bushing for a blade root of a wind turbine rotor blade, having a bushing body and a corrosion protective layer, wherein the corrosion protective layer is provided on a face of the bushing body and wherein the corrosion protective layer is applied to the face in a cold-deforming process is provided herein. This has the advantage that due to the fact that the corrosion protective layer is applied in a cold-deforming process, the application of the corrosion protective layer does not influence the mechanical properties of the material of the bushing body. | 12-10-2015 |
20150369058 | TURBOMACHINE ROTOR BLADE - A turbomachine rotor blade, said blade having, at the distal end thereof, a heel comprising: a platform ( | 12-24-2015 |
20150376473 | METHACRYLATE STRUCTURAL ADHESIVE FORMULATION AND PROCESS FOR THE USE THEREOF - A two part adhesive formulation is provided that has an adhesive part including methylmethacrylate monomer, an antioxidant, a cure inhibitor, and a polyfunctional monomer amount of dimethacrylate monomer, trimethacrylate monomer, or a combination thereof. An activator part includes methylmethacrylate monomer, and a cure accelerator. A toughening agent and an impact modifier in at least one of the adhesive part or the activator part. The adhesive formulation is well suited for forming a wind turbine blade from two or more substrates. | 12-31-2015 |
20150377037 | BRAZE METHODS AND COMPONENTS FOR TURBINE BUCKETS - Braze methods for turbine buckets include providing the turbine bucket comprising a modification surface, wherein the modification surface comprises a non-z-notch contact surface, disposing a pre-sintered preform on the modification surface and, heating the pre-sintered preform on the modification surface to bond the pre-sintered preform to the turbine bucket at the modification surface. | 12-31-2015 |
20160003059 | TURBINE ROTOR AND TURBOCHARGER HAVING THE TURBINE ROTOR - A turbine rotor comprising: a turbine wheel | 01-07-2016 |
20160003064 | Abrasive Coating and Manufacture and Use Methods - A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; an abrasive; and a matrix in which the abrasive is at least partially embedded; and heating to cause the self-braze material to braze to the substrate. The heating leaves at least a portion of the self-braze material with a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel. | 01-07-2016 |
20160003065 | Abrasive Coating and Manufacture and Use Methods - A method for applying an abrasive comprises: applying, to a substrate, the integral combination of a self-braze material, an abrasive, a matrix in which the abrasive is at least partially embedded, and an intermediate layer between the self-braze material and the matrix; and heating to cause the self-braze material to braze to the substrate. | 01-07-2016 |
20160003066 | Abrasive Preforms and Manufacture and Use Methods - A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate. | 01-07-2016 |
20160010472 | Coating and coating method for gas turbine engine component | 01-14-2016 |
20160017722 | PROTECTIVE COATING FOR TITANIUM LAST STAGE BUCKETS - Described herein a bucket for use in the last stage of a steam turbine engine. The bucket includes a titanium-based alloy having a leading edge wherein the leading edge includes titania having a plurality of pores and a top sealing layer filling the plurality of pores, the sealing layer selected from the group consisting of: chromium, cobalt, nickel, polyimide, polytetrafluoroethylene and polyester. | 01-21-2016 |
20160017725 | Blades and Manufacture Methods | 01-21-2016 |
20160024942 | Abrasive Tipped Blades and Manufacture Methods - An article ( | 01-28-2016 |
20160032426 | OPTIMIZED NICKEL ALLOY AND TURBINE BLADE MADE THEREOF - A nickel alloy includes a proportion by weight of Cr of 12.3% to 13.7%, a proportion by weight of Al of 4.3% to 4.7% and a proportion by weight of Co of 4% to 6%. The components are preferably Cr, Mo, Re and/or W, Al, Ti, Ta, Hf, Si, reactive elements including actinides and lanthanides, C, optionally the components Zr and/or B. The proportions by weight are selected such that both a desired high creep resistance and also a desired high hot corrosion resistance are achieved. A turbine blade is made of the nickel alloy. | 02-04-2016 |
20160040272 | DIE-CASTABLE NICKEL BASED SUPERALLOY COMPOSITION - A die-cast nickel based superalloy includes 4.5-5.5 wt % Tungsten (W), 1.5-2.5 wt % Columbium (Cb), 4.5-5.5 wt % Tantalum (Ta), 0.5-5.0 wt % Titanium (Ti), and 0.5-3.0 wt % Aluminum (Al), | 02-11-2016 |
20160102564 | ROTATING BODY PROVIDED WITH BLADES - A rotating body includes a rotating body core, and a plurality of blades provided at an outer or inner circumference of the rotating body core at equal intervals in a circumferential direction, and connected circumferentially via an annular connection portion provided separately from the rotating body core. A resonance frequency under a two nodal diameter number mode of the rotating body is lower than or equal to a rotational secondary harmonic frequency with respect to a rated rotation speed. Where N | 04-14-2016 |
20160115798 | ROTOR BLADE WITH REDUCED ACOUSTIC RESPONSE - A turbine engine rotor blade having a trailing edge ( | 04-28-2016 |
20160130954 | WELDING MATERIAL AND WELDING ROTOR - The invention provides a Ni—Fe-based alloy which is preferable for a welding of a joint between different materials such as a steel material and a Ni-based alloy, and a rotor for a steam turbine which is manufactured by using the same. The invention employs a Ni—Fe-based alloy including Cr: 14 to 18%, Al: 1.0 to 2.5%, Mo+W: 2.5 to 5.0%, C: 0.01 to 0.10%, B: 0.001 to 0.03%, and Fe: 15 to 20%, in mass, in which the remaining portion is constructed by an unavoidable impurity and Ni, as a welding metal. As a result, it is possible to provide a rotor for a steam turbine which can hold down a reduction of a ductility and a toughness generated in the case of welding the different materials, and is excellent in a strength and the ductility. | 05-12-2016 |
20160130955 | COMPOSITE COMPRESSOR BLADE AND METHOD OF ASSEMBLING - Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein. | 05-12-2016 |
20160138569 | SPAR CAP FOR A WIND TURBINE ROTOR BLADE - A spar cap for a rotor blade of a wind turbine is disclosed. The rotor blade includes a blade root and a blade tip, leading and trailing edges, pressure and suction sides, and at least one spar cap configured on an internal surface of either or both the pressure or suction sides. The spar cap includes one or more layers of a first material and a second conductive material contacting at least one of the layers of the first material. Further, the conductive material is different than the first material. Thus, the conductive material is configured with the first material so as to create an equipotential spar cap. | 05-19-2016 |
20160145703 | HOT-FORGED TiAl-BASED ALLOY AND METHOD FOR PRODUCING THE SAME - Provided is a hot-forged TiAl-based alloy of the present invention containing 40 to 45 atom % of Al and additive elements in the following composition ratio (A) or (B), and the balance Ti with inevitable impurities: (A) Nb: 7 to 9 atom %, Cr: 0.4 to 4.0 atom %, Si: 0.3 to 1.0 atom %, and C: 0.3 to 1.0 atom %; and (B) at least one of Cr: 0.1 to 2.0 atom %, Mo: 0.1 to 2.0 atom %, Mn: 0.1 to 4.0 atom %, Nb: 0.1 to 8.0 atom %, and V: 0.1 to 8.0 atom %. The TiAl-based alloy is characterized by having a fine structure of densely arranged lamella grains that are laminated alternately with a Ti | 05-26-2016 |
20160153289 | GAS TURBINE ENGINE CERAMIC COMPONENT ASSEMBLY ATTACHMENT | 06-02-2016 |
20160160661 | ABRASIVE COATED SUBSTRATE AND METHOD FOR MANUFACTURING THEREOF - A coated substrate is described including a substrate material, which is coated at least in part with an oxidation-resistant coating, wherein the coating consists of a wear-resistant abrasive coating layer, which contains or consists of coated abrasive particles embedded in an oxidation-resistant matrix material, wherein at least some of the abrasive particles consist of α-Al | 06-09-2016 |
20160169012 | PLATED POLYMER COMPONENTS FOR A GAS TURBINE ENGINE | 06-16-2016 |
20160177742 | Steam Turbine Rotor, Steam Turbine Including Same, and Thermal Power Plant Using Same | 06-23-2016 |
20160177744 | BLADE | 06-23-2016 |
20160177746 | ARTICLES FOR HIGH TEMPERATURE SERVICE AND METHOD FOR MAKING | 06-23-2016 |
20160186578 | ADVANCED GAMMA TiAl COMPONENTS - Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180° F. (638° C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies. | 06-30-2016 |
20160186603 | ROTOR CONSTRUCTION FOR HIGH SPEED MOTORS - A rotor shaft for a high speed motor that has a coating that is secured to a shaft body. The coating and the shaft body are formed from dissimilar materials. More specifically, the coating may be an alloy material, such as, for example, a copper alloy, while the shaft body may be a steel material. According to certain embodiments, the alloy material of the coating may be secured to at least a portion of a rotor body blank in a solution treated condition via a low temperature welding procedure. Additionally, the coating may be hardened, such as for example, through the use of an age hardening process. The coating and the rotor body blank may be machined together to form the rotor shaft. According to certain embodiments, such machining may configure the rotor shaft for use with a turbo-compressor that is configured for air compression. | 06-30-2016 |
20220134428 | METHOD FOR MANUFACTURING COBALT-BASED ALLOY STRUCTURE, AND COBALT-BASED ALLOY STRUCTURE OBTAINED THEREBY - In order to stably produce a structured article made of a metal with a complex shape, such as a turbine stator blade, while securing a sufficient mechanical strength, there is provided a method for manufacturing a cobalt-based alloy structure, the cobalt-based alloy structure including a first structure region comprising a hollow space and a second structure region filled in the hollow space. The method includes the steps of: forming the first structure region by additive manufacturing from a first cobalt-based alloy powder having a particle size distribution within a range of 5-85 μm and in D90 within a range of 40-80 μm; and forming the second structure region in the hollow space by hot isostatic pressing, the hollow space being filled with a second cobalt-based alloy powder with a particle size distribution within a range of 5-85 μm and in D90 within a range of 40-80 μm. | 05-05-2022 |
20080273985 | Roughened Coatings for Gas Turbine Engine Components - A gas turbine engine component ( | 11-06-2008 |
20090060747 | ORIENTED FIBER CERAMIC MATRIX COMPOSITE ABRADABLE THERMAL BARRIER COATING - A method of manufacturing a gas turbine engine component includes the steps of forming a ceramic workpiece having oriented ceramic reinforcement, and severing the ceramic workpiece to produce a ceramic member having a desired orientation of the ceramic reinforcement. The ceramic member is then attached to a turbine engine component as a thermal barrier layer for the turbine engine component. | 03-05-2009 |
20090185912 | Method of Protecting a Component Against Hot Corrosion and a Component Protected by Said Method - A method of protecting a component, in particular a turbine blade, from the effects of hot corrosion includes the steps of applying a chromium diffusion coating to the component and applying a coating of a ceramic material to one or more selected regions of the chromium diffusion coating. The selected regions are regions which, in subsequent use of the component, are subjected to temperatures lower than a predetermined temperature. The ceramic material preferably includes a binder combined with a metal oxide. In a preferred embodiment, a turbine blade is coated over the whole of its internal and external surfaces with the chromium diffusion coating; an aluminium diffusion coating is then applied, through a mask, to the aerofoil surfaces and the internal surfaces of the blade; the mask is removed and the ceramic material is applied as an overlay to the chromium diffusion coating in a region between the platform and the root of the blade. | 07-23-2009 |
20090257882 | WIND TURBINE BLADE WITH LIGHTNING RECEPTOR AND METHOD FOR PROTECTING THE SURFACE OF A WIND TURBINE BLADE - A wind turbine blade has at least one lightning receptor, wherein at least part of a surface of the wind turbine blade close to the lightning receptor is covered by a protective layer having electrical and thermal insulating material. Moreover, a method for protecting the surface of a wind turbine blade close to a lightning protector against temperature increase resulting from lightning impact is disclosed. At least part of the surface of the wind turbine blade is covered with a protective layer having electrical and thermal insulating material. | 10-15-2009 |
20100034660 | Part for rotary machine, and manufacturing method therefor - In a part for a rotary machine, a ceramic hard film is formed on a surface of a base material, the density of droplets which exist in a surface of the ceramic hard film is set to be within 1000 pieces/mm | 02-11-2010 |
20100047075 | Thermal Barrier Coating Compositions, Processes for Applying Same and Articles Coated with Same - A process of coating an article includes the steps of (1) applying a ceramic compound to at least one surface of an article to form a layer of ceramic compound; (2) applying at least one inert compound upon the ceramic compound layer to form a protective layer, wherein the at least one inert compound is composed of a first inert compound having a cubic crystalline structure of formula (I) A | 02-25-2010 |
20100074759 | GAS TURBINE ENGINE AIRFOIL - A gas turbine engine airfoil including at least one outer tile coupled to a supporting member. The outer tile is coupled to the supporting member by a pin passing though the supporting member and the outer tile. | 03-25-2010 |
20100166566 | TURBINE ROTOR BLADE TIPS THAT DISCOURAGE CROSS-FLOW - A turbine rotor blade for a gas turbine engine including an airfoil and dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, the airfoil comprising: a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from a root to a tip plate; a pressure tip wall that extends radially outwardly from the tip plate, traversing from the leading edge to the trailing edge such that the pressure tip wall resides approximately adjacent to the termination of the pressure sidewall; a suction tip wall that extends radially outwardly from the tip plate, traversing from the leading edge to the trailing edge such that the suction tip wall resides approximately adjacent to the termination of the suction sidewall; and one or more tip ribs that extend substantially between the pressure tip wall and the suction tip wall. | 07-01-2010 |
20100226782 | Turbomachine blade with a blade tip armor cladding - A blade of a turbomachine such as a gas turbine includes a blade vane with a blade tip and a blade base. A blade tip armor cladding is applied on the blade tip. A coating covers at least the armor cladding and includes at least one multilayer coating system, and preferably plural such coating systems stacked repetitively on one another. Each coating system includes at least two different layers stacked successively on one another, with one layer of a metal material closer to the blade tip and one layer of a ceramic material farther from the blade tip. | 09-09-2010 |
20100226783 | Erosion and Corrosion Resistant Turbine Compressor Airfoil and Method of Making the Same - A sacrificial and erosion-resistant turbine compressor airfoil includes a turbine compressor airfoil having a modified airfoil surface. The airfoil surface has an airfoil coating that includes a sacrificial coating comprising a layer of Al, Cr, Zn, an Ni—Al alloy, an Al—Si alloy, an Al-based alloy, a Cr-based alloy or a Zn-based alloy, an Al polymer composite, or a combination thereof, or a layer of a conductive undercoat and an overcoat of an inorganic matrix binder having a plurality of ceramic particles and conductive particles embedded therein disposed on the undercoat. The airfoil coating also includes an sacrificial coating, wherein one of the sacrificial coating or the erosion-resistant coating is disposed on the airfoil surface and the other of the corrosion-resistant coating or the erosion-resistant coating is disposed on the respective one, and wherein the sacrificial coating is more anodic than the airfoil surface or the erosion-resistant coating. | 09-09-2010 |
20100284816 | AIRFOIL ATTACHMENT - A rotor blade for a gas turbine engine includes an airfoil that extends in span between a tip and a root opposite from the tip. The root includes a plug, a looped portion that surrounds the plug and a clamp. The clamp contacts only a portion of the looped portion on an opposite side of the looped portion from the plug. | 11-11-2010 |
20100329882 | Ceramic Heat-Insulating Layers Having Increased Corrosion Resistance to Contaminated Fuels - Ceramic coatings for a component that is subjected to high temperatures, especially for a turbine blade are provided. The ceramic coatings contain one or more compounds that are selected from alkaline earth silicates, ZrV | 12-30-2010 |
20110027098 | CERAMIC MATRIX COMPOSITE BLADE HAVING INTEGRAL PLATFORM STRUCTURES AND METHODS OF FABRICATION - A method of making a ceramic matrix composite blade includes laying up at least one ply of the plurality of fibrous ceramic plies in a preselected arrangement to form an airfoil and dovetail preform, laying up at least one additional ply of the plurality of fibrous ceramic plies on the airfoil and dovetail preform in a second preselected arrangement to form an integral platform as part of the non-rigidized blade preform, rigidizing the blade preform to form a rigidized blade preform, and densifying the rigidized blade preform to form a ceramic matrix composite blade having an integral platform structure. A tool for making the ceramic matrix composite blade and a ceramic matrix composite blade are also disclosed. | 02-03-2011 |
20110150663 | Process For Producing A Ceramic Matrix Composite Article And Article formed Thereby - Process for producing a ceramic composite structure includes impregnating a reinforcing material with a suitable precursor slurry composition including thermosetting resin, a suitable curing agent, a ceramic component, a carbonaceous solids component, and optionally, a suitable solvent. Exemplary thermosetting resins include polyesters, vinyl esters, epoxy resins, bismaleimide resins, and polyimide resins. The carbonaceous solids component provides a suitable amount of carbon char upon pyrolization. The preform may be dried prior to curing to remove solvents and thereby provide a working material comprising up to 70 volume % solids. The preform is cured, pyrolized, and infiltrated with molten silicon to form a composite article. The thermosetting resin is selected for processability, green strength, and relatively fast cure cycle. | 06-23-2011 |
20110171039 | BLADE ARRANGEMENT OF A GAS TURBINE - A blade arrangement of a gas turbine, with at least one blade which in the radial direction projects into a hot gas passage arranged concentrically to an axis, and terminates in a blade tip which with a clearance lies opposite a heat shield which delimits the hot gas passage. The blade and the heat shield are movable in relation to each other in the circumferential direction, and the blade tip and the heat shield are covered with coatings, which enable a directed cutting of the blade tip into the heat shield. By such a blade arrangement, a reduction of the clearance as a result of cutting in is simply achieved by the heat shield having a porous thermal barrier coating as an outer, abradable coating, and by the blade tip being provided with a homogenous, metallic cover coating. | 07-14-2011 |
20110229337 | HYBRID CERAMIC MATRIX COMPOSITE TURBINE BLADES FOR IMPROVED PROCESSIBILITY AND PERFORMANCE AND PROCESS FOR PRODUCING HYBRID TURBINE BLADES - The present invention is a hybrid ceramic matrix composite turbine engine component comprising an outer shell section(s) and an inner core section(s), wherein the outer shell section(s) and the inner core section(s) were bonded together using a melt infiltration (MI) process. The outer shell section(s) comprises a SiC/SiC material that has been manufactured using a process selected from the group consisting of a slurry cast MI process and a prepreg MI process. The inner core section(s) comprises a material selected from the group consisting an Si/SiC composite material and a monolithic ceramic material. The Si/SiC composite material may be manufactured using the Silcomp process. The present invention may be a high pressure turbine blade, a high pressure turbine vane, a low pressure turbine blade, or a low pressure turbine vane. The present invention is also a method of manufacturing a hybrid ceramic matrix composite turbine engine component. | 09-22-2011 |
20110229338 | COMPRESSOR WHEEL - A compressor wheel for a turbocharger comprising a central hub and a plurality of impeller blades extending outwardly from the hub. Each of the blades defines a leading edge, a trailing edge and a root portion which connects the blade to the hub. At least one of the blades has a surface provided with a variable thickness surface layer of a ceramic material. The leading edge of the blade is provided with a thicker surface layer of the ceramic material than the trailing edge of the blade, the root portion of the blade, or both the trailing edge and root portion of the blade. | 09-22-2011 |
20110268577 | METHOD FOR SMOOTHING THE SURFACE OF A PART MADE FROM A CMC MATERIAL - A method of smoothing the surface of a ceramic matrix composite part presenting a surface that is undulating and rough. The method includes forming a ceramic coating on the surface of the part, the coating being made by applying a liquid composition on the surface of the part, the composition containing a ceramic-precursor polymer and a factory solid filler, curing the polymer, and transforming the cured polymer into ceramic by heat treatment. The method further includes impregnating the ceramic coating with a liquid metallic composition. | 11-03-2011 |
20120009071 | CMC TURBINE STATOR BLADE - A CMC turbine stator blade | 01-12-2012 |
20120027616 | GAS TURBINE BLADE WITH INTRA-SPAN SNUBBER AND MANUFACTURING METHOD FOR PRODUCING THE SAME - A gas turbine blade ( | 02-02-2012 |
20120057985 | CMC TURBINE STATOR BLADE - A CMC turbine stator blade | 03-08-2012 |
20120057986 | PRODUCTION METHOD OF IMPELLER APPLIED TO SUPERCHARGER - An impeller comprising a wheel portion extending in an axial direction and a plurality of blades arranged around the wheel portion is produced by assembling a mold divisible into a plurality of parts having a cavity adapted for forming an outer profile of the impeller, injecting a kneaded matter including powder of a metal or a ceramic and binder to mold a green body, degreasing and sintering the green body to obtain a sintered body, embedding the sintered body into a die having a cavity adapted for modifying the outer profile of the impeller, and pressurizing the die to modify the outer profile of the impeller. | 03-08-2012 |
20120063911 | DUAL BRAZING ALLOY ELEMENT, PROCESS FOR PRODUCING IT AND USES THEREOF - A dual brazing alloy element for a materially integral connection of a ceramic surface to a metallic surface includes a first layer having a Ni-based brazing alloy with a Ni content of at least 50% by weight and having at least one component configured to lower a melting point of the Ni-based brazing alloy selected from the group consisting of Si, B, Mn, Sn and Ge. A second layer includes an active brazing alloy material having a total content of 1-15% by weight of at least one active element selected from the group consisting of Ti, Hf, Zr and V. | 03-15-2012 |
20120063912 | PROCESS FOR SMOOTHING THE SURFACE OF A PART MADE OF CMC MATERIAL - A method of smoothing the surface of a ceramic matrix composite material part that presents a surface that is undulating and rough. The method includes depositing a refractory vitreous coating on the surface of the part, the vitreous coating essentially containing silica, alumina, baryte, and lime. | 03-15-2012 |
20120163984 | COOLING CHANNEL SYSTEMS FOR HIGH-TEMPERATURE COMPONENTS COVERED BY COATINGS, AND RELATED PROCESSES - A method for providing a fluid cooling system within a high temperature component is described. At least one microchannel is formed in an external surface of the component; and one or more coolant passage holes are then formed, extending from at least one of the microchannels to an interior region of the component. A layer of a metallic structural coating is then applied over the external surface. At least one slot, or a set of relatively small passive cooling holes, are then formed through the metallic structural coating; extending into at least a portion of the microchannels. A second coating layer is then applied over the first layer. In some embodiments, a sacrificial material is deposited into the microchannels before the first coating layer is applied. Related articles are also described. | 06-28-2012 |
20120163985 | COMPONENTS CONTAINING CERAMIC-BASED MATERIALS AND COATINGS THEREFOR - Hybrid components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the components. The components includes a first subcomponent formed of a ceramic-based material and a second subcomponent formed of a metallic material. The first subcomponent has a nub and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent is attached to the first subcomponent by a compression fit and encapsulation of the second subcomponent on the nub of the first subcomponent. The nub has a compliant coating system that provides thermal expansion compliance between the metallic material of the second subcomponent and the ceramic-based material of the first subcomponent. | 06-28-2012 |
20120163986 | TURBINE AIRFOIL COMPONENTS CONTAINING CERAMIC-BASED MATERIALS AND PROCESSES THEREFOR - A hybrid turbine airfoil component containing a ceramic material, in which detailed features of the component are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the component. The component includes a first subcomponent formed of a ceramic-based material, and a second subcomponent formed of a metallic material. The first subcomponent has an airfoil portion and a nub, and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent includes a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent. | 06-28-2012 |
20120301317 | HYBRID ROTOR DISK ASSEMBLY WITH CERAMIC MATRIX COMPOSITES PLATFORM FOR A GAS TURBINE ENGINE - A Ceramic Matrix Composite (CMC) platform for an airfoil of a gas turbine engine includes a CMC platform segment which at least partially defines an airfoil profile. | 11-29-2012 |
20130004325 | HYBRID PART MADE FROM MONOLITHIC CERAMIC SKIN AND CMC CORE - A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material. A ceramic matrix composite material is located adjacent interior portions of the platform and the attachment feature and is bonded to the monolithic ceramic material. | 01-03-2013 |
20130004326 | CMC BLADE WITH INTEGRAL 3D WOVEN PLATFORM - A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component. | 01-03-2013 |
20130052030 | CERAMIC MATRIX COMPOSITE VANE STRUCTURE WITH OVERWRAP FOR A GAS TURBINE ENGINE - A vane structure for a gas turbine engine includes an airfoil section with a platform segment adjacent to a ring. An insert is adjacent to the platform segment and an overwrap is wound around the ring and the insert. | 02-28-2013 |
20130084189 | CMC COMPONENT, POWER GENERATION SYSTEM AND METHOD OF FORMING A CMC COMPONENT - A ceramic matrix composite component for a power generation system includes a ceramic foam core and a ceramic matrix composite material surrounding at least a portion of the ceramic foam core. The ceramic foam core remains in place during operation of the component in the power generation system. Additionally, a method of forming the ceramic matrix composite component is provided. | 04-04-2013 |
20130089431 | AIRFOIL FOR TURBINE SYSTEM - An airfoil for a turbine system is disclosed. The airfoil includes a first body having exterior surfaces defining a first portion of an aerodynamic contour of the airfoil and formed from a first material. The airfoil further includes a second body having exterior surfaces defining a second portion of an aerodynamic contour of the airfoil, the second body coupled to the first body and formed from a second material having a different temperature capability than the first material. | 04-11-2013 |
20130115096 | ROTATING AIRFOIL COMPONENT OF A TURBOMACHINE - A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing. | 05-09-2013 |
20130142660 | CERAMIC MATRIX COMPOSITE AIRFOIL STRUCTURE WITH TRAILING EDGE SUPPORT FOR A GAS TURBINE ENGINE - An airfoil for a gas turbine engine includes an aft trailing edge support between a pressure side and a suction side. | 06-06-2013 |
20130171001 | COMPOSITE AIRFOIL ASSEMBLY - A composite blade assembly for mounting on a turbine wheel includes a ceramic airfoil and an airfoil platform. The ceramic airfoil is formed with an airfoil portion, a blade shank portion and a blade dovetail tang. The metal platform includes a platform shank and a radially inner platform dovetail. The ceramic airfoil is captured within the metal platform, such that in use, the ceramic airfoil is held within the turbine wheel independent of the metal platform. | 07-04-2013 |
20130323073 | ASSEMBLED BLADE PLATFORM - A method of making a platform of a blade includes the steps of creating two platform sections by solidifying a material with a fabric in a mold and positioning a band of fabric around the two platform sections to retain an airfoil and define a blade. The method further includes the step of bonding the two platform sections together by solidifying the material to define a platform of a solid material. The platform is not bonded to the airfoil. | 12-05-2013 |
20140119939 | HIGH-PRESSURE TURBINE BLADES MADE OF CERAMIC MATRIX COMPOSITES - Turbine blade for a turbojet engine, made of a ceramic matrix composite material and comprising a vane that extends above a platform and a root that extends below said platform, the pressure face and suction face of said vane being formed by sheets of a composite material, said sheets meeting at the leading edge and trailing edge of said vane, characterised in that the pressure face and suction face are formed by the same sheet bent back on itself, in a radial direction, at the leading edge or trailing edge. | 05-01-2014 |
20140241900 | METHODS FOR REPAIRING A TURBINE AIRFOIL CONSTRUCTED FROM CMC MATERIAL - Methods for repairing a turbine airfoil constructed from a CMC material are provided via filling a cavity located in the turbine airfoil with a ceramic paste (e.g., including a ceramic powder and a binder), heating the ceramic paste in the cavity to remove the binder, thereby forming a porous ceramic material, and adding a molten ceramic material to the porous ceramic material. The cavity can be defined in an airfoil of the turbine airfoil (e.g., on a tip or cap of the airfoil). Intermediates formed during the repair of a turbine airfoil are also provided. The intermediate can generally include an airfoil comprising a CMC material, a cavity defined in the airfoil, and a porous ceramic material filling the cavity. | 08-28-2014 |
20140271218 | LOW CONDUCTIVITY THERMAL BARRIER COATING - A ceramic composition of matter includes a solvent material and a solute material. The solvent material comprises zirconia or hafnia, or a mixture thereof, which is stabilized with a stabilizing oxide. The solute material comprises a metal oxide of the formula, X | 09-18-2014 |
20140308137 | FLOW ROTOR, IN PARTICULAR TURBINE WHEEL - A flow rotor ( | 10-16-2014 |
20140341750 | PROCESS FOR SELECTIVELY PRODUCING THERMAL BARRIER COATINGS ON TURBINE HARDWARE - A process of depositing a ceramic coating on an airfoil component and the component formed thereby is provided. The process includes depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes. A ceramic coating is then deposited on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes. The ceramic coating within the holes is selectively removed without completely removing the ceramic coating on the trailing edge region and the lands between the holes. | 11-20-2014 |
20150030458 | ROTOR BLADE EROSION PROTECTION SYSTEM - The present application includes a rotor blade having an erosion protective coating, the coating being a cermet material configured to protect against erosion during the operation of the rotor blade. Further, the present application includes a method of selectively applying the erosion protective coating, a method of selectively repairing/reapplying the erosion protective coating, and a process of developing an erosion surface model map of an optimized erosion protective coating pattern and thickness. | 01-29-2015 |
20150093249 | BLADE FOR A GAS TURBINE - Disclosed is a blade for a gas turbine, in particular for an aircraft engine, wherein the blade comprises at least one internal and/or external supporting structure of a metallic and/or intermetallic material. Also disclosed are a blade cluster having at least one such blade for a gas turbine, a method for producing such a blade cluster and a gas turbine. | 04-02-2015 |
20150322804 | AIRFOIL ARRANGEMENT WITH PTAL BOND COATING AND THERMAL BARRIER COATING, AND CORRESPONDING MANUFACTURING METHOD - An airfoil with a coated surface section which having a platinum aluminide and a TBC coating is provided herein. Furthermore, an airfoil arrangement for a gas turbine including an airfoil, an inner shroud, and an outer shroud, wherein the airfoil is arranged between the inner shroud and the outer shroud, wherein the airfoil comprises a coated surface section which is coated with a platinum-aluminide coating and a thermal barrier coating and which represents at least a part of the total surface of the airfoil, wherein the thermal barrier coating of the coated surface section is spaced from the inner shroud and/or the outer shroud with a distance (x) and wherein the distance (x) is between 5% and 25% of a total length of the airfoil between the inner shroud and the outer shroud is provided herein. | 11-12-2015 |
20160009927 | ANTIFOULING LAYER FOR COMPRESSOR BLADES | 01-14-2016 |
20160032735 | TRANSIENT LIQUID PHASE BONDED TIP SHROUD - A composite ceramic turbine blade includes a ceramic airfoil portion and a ceramic outer tip shroud portion. The ceramic outer tip shroud portion is joined to the ceramic airfoil portion by a bonding means. In an embodiment, the bonding means comprises partial transient liquid phase bonding. In another embodiment, the airfoil portion is a fiber reinforced ceramic. | 02-04-2016 |
20160032738 | GAS TURBINE ENGINE BLADE TIP TREATMENT - A fan blade and method of manufacturing a fan blade includes a metallic fan blade body with a crystalline oxidation layer and immersing the crystalline oxidation layer in a solution of ceramic nanosheets in suspension. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer, wherein the crystalline oxidation layer includes pores containing ceramic nanosheets. | 02-04-2016 |
20160069189 | SPLAYED TIP FEATURES FOR GAS TURBINE ENGINE AIRFOIL - A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner. | 03-10-2016 |
20160069195 | ROTARY BLADE TIP - The present invention provides a blade tip for a rotary blade, the blade tip comprising a first portion and a radially-recessed second portion. A radially outermost surface of the first portion comprises a first abrasive coating e.g. a composite material comprising cubic boron nitride embedded in a matrix of nickel alloy. A radially outermost surface of the second portion comprises a second abrasive coating which has a greater resistance to oxidation than the first abrasive coating. The increased oxidation resistance of the second abrasive coating is achieved by providing a radially outer protective layer and/or using a material having a greater inherent oxidation resistance. | 03-10-2016 |
20080286110 | Wind-turbine blade and method for reducing noise in wind turbine - Low-noise wind turbine blades are provided wherein metallic and/or polymeric cellular materials that are capable of bearing directional loads are used in the construction of wind turbine blade parts or entire sections. The use of such materials influences the air flow over them in such a way that the resulting boundary-layer turbulence is damped in a controlled way, thus weakening the noise scattering mechanism at the trailing edge, and the scattered acoustic waves are absorbed and attenuated by the material acting as an acoustic liner. | 11-20-2008 |
20090169392 | Wind turbine blade with sufficiently high strength and light weight - A wind turbine blade is provided with an outer skin layer formed of fiber-reinforced plastic, and a plurality of main structural members formed of fiber-reinforced plastic integrally with the outer skin layer to extend in a blade length direction. The main structural members include a plurality of main dorsal structural members positioned on a dorsal side of the wind turbine blade, and a plurality of main ventral structural members positioned on a ventral side of the wind turbine blade. | 07-02-2009 |
20090196759 | Polymer Nanocomposites for Air Movement Devices - In one embodiment, the invention provides an air movement device having a matrix polymer and nanoparticles. In another embodiment, the invention provides a method of manufacturing an air movement device having dry-mixing about 30% to about 80% by weight matrix polymer and about 2% to about 15% by weight layered clay to form a dry mixture, extruding the mixture to form a polymer nanocomposite, and molding the polymer nanocomposite into an air movement device. In yet another embodiment, the invention provides an air movement device having about 30% to about 80% by weight polypropylene, about 3% to about 10% by weight layered clay, and about 1% to about 10% by weight maleic anhydride grafted polystyrene, wherein the air movement device has a UL 94 5VA flame retardant rating. | 08-06-2009 |
20090246033 | WIND TURBINE BLADE - There is provided a wind turbine blade at least 50% of the surface of which is covered with a self-adhesive thermoplastic film. By applying a self-adhesive thermoplastic film to the blade, the need for a gelcoat or the paint is eliminated. It is estimated that the thermoplastic film will take a similar time to apply as the gelcoat and/or paint. However, it does not require any further treatment once it has been applied thereby reducing significantly the work involved in finishing the blade. Also, the thickness of the film is precisely controlled in advance of its application to the blade ensuring that a surface with a uniform thickness is produced. | 10-01-2009 |
20090252612 | Blade and gas turbine - The invention relates to a turbomachine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbomachine. The aim of said invention is to develop a device and a method for the turbomachine making it possible to reduce the size of a radial split of the turbomachine in order to obtain greater degree of efficiency. The inventive turbomachine comprises a rotor rotationally mounted in the case of the turbomachine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and means influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbomachine rotor by heating fluid flowing therethrough are also disclosed. | 10-08-2009 |
20090297358 | MODIFIED BLADE STIFFENER AND FABRICATION METHOD THEREFOR - The disclosure is generally directed to a modified blade stiffener having enhanced mechanical properties. An illustrative embodiment of the modified blade stiffener includes a stiffener-forming material shaped into a pair of coupled blades having first and second ends, a filler cavity provided at the first end of the blades, a blade filler provided in the filler cavity and a pair of blade flanges provided at the second end of the blades. | 12-03-2009 |
20090311106 | ROTOR BLADE FOR A WIND ENERGY INSTALLATION - A rotor blade for a wind power installation, has at least a first component and a second component. The first component has a rotor blade tip and the second component has a rotor blade root. The first and second components are in the form of separate parts for jointly forming the rotor blade. The first component is of at least a first material and the second component is of at least a second material. | 12-17-2009 |
20100254819 | FOAMED PLASTIC SHEET - An unmixed plastic sheet, which is made of a thermoplastic material and which is composed of a number of body segments that are adjacent to one another in a plane, interconnected and made of a closed-cell foam material. The body segments are thermoplastically welded to one another at their abutting lateral faces while forming flat weld seams. The flat weld seams form a plastic intermediate layer, which has few pores, and which is provided in the form of a web structure that, when viewed from above, is reticular and reinforces the plastic sheet. The inventive plastic sheet is preferably used as a core layer in sandwich composites. | 10-07-2010 |
20100272576 | High performance outboard section for rotor blades - Blades for rotorcraft are designed and/or implemented with rotor blades having a swept portion that occupies at least 20-40% of a length of the blade. Forward and aft sweeps are contemplated, with up to 20° or more of sweep. The swept portion preferably has a thickness ration of at least 10-20% at R80, and can have a tapered planform with a relatively outboard section having a smaller chord than a relatively inboard section. Contemplated design methods include optimizing or otherwise designing the rotor blade planform and lift distribution along the blade for efficiency in various flight conditions without taking into account the detrimental effects of high Mach numbers, and then using sweep angle, airfoil thickness and transonic airfoil shaping to maintain the lift distribution, low drag and low noise level at real Mach numbers at the various blade stations at the various flight conditions. | 10-28-2010 |
20100278656 | Structure an aircraft rotor blade - An aircraft rotor blade structure is disclosed. The rotor blade includes a read blade part made of a pearl board and a front blade part made of a plastic material. The front blade part is connected to the front edge of the read blade part. This read blade part helps reducing the weight of the blade. The front blade part enhances the transverse strength of the read blade part and renders a center of gravity on the front edge of the blade. | 11-04-2010 |
20110097213 | COMPOSITE AIRFOILS HAVING LEADING EDGE PROTECTION MADE USING HIGH TEMPERATURE ADDITIVE MANUFACTURING METHODS - Composite airfoils including a leading edge, and a near net shape metal leading edge protective strip operably connected to the leading edge, the protective strip made by providing a high temperature additive manufacturing device; providing a tooling system including a mandrel; a metallic cladding; and at least one cooling channel applying a metallic deposit to the mandrel having the metallic cladding using the high temperature additive manufacturing device; and concurrently removing heat from the mandrel using the at least one cooling channel. | 04-28-2011 |
20110123346 | WIND TURBINE BLADE - The invention relates to a wind turbine blade having at least one component formed of a fibrous composite material including two or more different types of carbon fibres having a different elastic modulus to each other. The proportions of the different types of fibres vary in the longitudinal direction of the blade such that the elastic modulus of the fibrous composite material increases towards the tip end of the blade. The two or more different types of carbon fibres may be incorporated in an inner beam and/or in the outer shell portions of the blade. | 05-26-2011 |
20110129351 | NEAR NET SHAPE COMPOSITE AIRFOIL LEADING EDGE PROTECTIVE STRIPS MADE USING COLD SPRAY DEPOSITION - Composite airfoil having a leading edge protective strip made by the method of utilizing a cold spray deposition system to deposit the protective strip onto a leading edge of the composite airfoil. | 06-02-2011 |
20110129352 | Rotor Blade with an Integrated Radar Absorber for a Wind Power Plant - A rotor blade comprising fiber-reinforced plastic for a wind power plant is provided with a radar absorber embedded into the fiber-reinforced plastic. The rotor blade includes a layer close to the surface with a defined electrical sheet resistivity of 100 to 800 ohm/square, which is located at a depth of 2 to 5 mm below the surface. The rotor blade also includes a layer far removed from the surface with a defined electrical sheet resistivity of at a maximum 50 ohm/square at a distance to the layer close to the surface of 5 to 16 mm. The integrated radar absorber covers one or several discrete surface sections of the rotor blade, without covering the entire surface of the rotor blade. | 06-02-2011 |
20110135488 | Fibre-Reinforced Plastic Material - A fibre-reinforced plastic material with a matrix material and first fibres is provided. The first fibres are embedded in the matrix material. Further, filling pieces are embedded in the matrix material. The filling pieces are arranged between the first fibres to prevent crack propagation in the fibre-reinforced plastic material. | 06-09-2011 |
20110293437 | WIND TURBINE BLADE WITH A CONDUCTIVELY DOPED COATING FOR LIGHTNING PROTECTION OF THE WIND TURBINE BLADE AND METHOD FOR MANUFACTURING THE WIND TURBINE BLADE - A wind turbine blade is provided having a base body with a base material and at least one coating of the base body with a coating material, wherein the coating material includes a composite material with conductive particles. The composite material includes fiber glass. In one embodiment, the fiber glass forms a glass fiber mat. Additionally a method for manufacturing such a wind turbine blade is provided. The method includes: a) providing the base body of the wind turbine blade; and b) applying the coating on a surface of the base body. | 12-01-2011 |
20110311368 | COMPOSITE MATERIAL TURBINE ENGINE VANE, AND METHOD FOR MANUFACTURING SAME - A method of fabricating a turbomachine blade out of a composite material including fiber reinforcement densified by a matrix, the method including making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a preform for an inner or outer blade platform; and densifying the preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, fowling a single part with incorporated inner and/or outer platform. | 12-22-2011 |
20120014804 | WIND TURBINE BLADE WITH SUFFICIENTLY HIGH STRENGTH AND LIGHT WEIGHT - A wind turbine blade is provided with an outer skin layer formed of fiber-reinforced plastic, and a plurality of main structural members formed of fiber-reinforced plastic integrally with the outer skin layer to extend in a blade length direction. The main structural members include a plurality of main dorsal structural members positioned on a dorsal side of the wind turbine blade, and a plurality of main ventral structural members positioned on a ventral side of the wind turbine blade. | 01-19-2012 |
20120034095 | PROPELLERS FOR AIRCRAFT - One aspect of the present invention provides a propeller for an aircraft. The propeller comprises a propeller hub, a spinner for streamlining the propeller and a plurality of composite propeller blades mounted to the propeller hub. The propeller blades are arranged to rotate together in the same rotational direction in at least two parallel planes substantially perpendicular to an axis of rotation of the propeller. The propeller has a reduced sized spinner with an improved aerodynamic profile that can be better matched to an engine nacelle and also has reduced drag. | 02-09-2012 |
20120034096 | INCORPORATION OF FUNCTIONAL CLOTH INTO PREPREG COMPOSITES - Incorporation of functional cloth into prepreg composites A combined prepreg material ( | 02-09-2012 |
20120082556 | NANOCRYSTALLINE METAL COATED COMPOSITE AIRFOIL - An airfoil for a gas turbine engine comprising a root, a tip, and leading and trailing edges extending between the root and the tip. The airfoil has a non-metallic core which is composed of a composite material, and a metallic coating disposed on at least a portion of the composite core, such as along the leading edge of the airfoil for example. The metallic coating is composed of a nanocrystalline metal, and forms an outer surface of the portion of the airfoil onto which the coating is applied. | 04-05-2012 |
20120093657 | IMPROVED COATING COMPOSITION FOR WIND TURBINE BLADES - The present application discloses a wind turbine blade having on the outer surface thereof a polyurethane-based coating including a polyurethane binder prepared from polyol(s) having an average functionality of ≧2.0 and <8.0; at least 50% (w/w) of the polyols have aliphatic polyester segments included therein and have a Mw of 300-3,000 g/mol; and polyisocyanate(s) having an average functionality of <3.0; at least 50% (w/w) of the polyisocyanate(s) are selected from: (i) polyisocyanates having aliphatic polyester segments included therein, and having a molecular weight of 500-3,000 g/mol and a functionality of ≧2.0 and <3.0; (ii) polyisocyanates of the allophanate type having a Mw of 250-2,000 g/mol and a functionality of ≧2.0 and <3.0; and (iii) polyisocyanates of the uretdion type having a Mw of 250-2,000 g/mol and a functionality of ≧2.0 and <3.0. The application also discloses corresponding coating compositions and a method for coating a substrate. | 04-19-2012 |
20120171044 | COMPOSITE-MATERIAL VANE - The present invention relates to a composite-material turbomachine vane ( | 07-05-2012 |
20120195766 | CMC TURBINE ENGINE BLADES AND A ROTOR WHEEL FOR A TURBINE ENGINE AND A TURBINE ENGINE INTEGRATING THEM - A rotor wheel of a turbine engine includes a plurality of CMC blades each having a first portion constituting a blade airfoil and root and made as a single piece with a second portion forming an outer platform. The blades are held under twisting prestress by mutual engagement via contact zones between the outer platforms of adjacent blades, and the contact zones that are situated on opposite sides of the outer platform of a blade are defined by at least one insert that is integrated in the outer platform and that is, for example, made of a carbon-based material. | 08-02-2012 |
20130017096 | REDUCING RADAR INTERFERENCE FROM WIND TURBINESAANM Holley; CharlesAACI Corpus ChristiAAST TXAACO USAAGP Holley; Charles Corpus Christi TX US - A wind turbine including components formed from or coated in a radar absorptive material. A method for scanning an area having one wind turbines and ignoring the radar interference therefrom is also provided. | 01-17-2013 |
20130039775 | METHOD FOR PRODUCING WIND POWER PLANT ROTOR BLADES AND A WIND POWER PLANT ROTOR BLADE - The present invention concerns a process for the production of a wind power installation rotor blade. To permit more economical manufacture at high quality the following steps are provided: providing at least one mold, placing a layered fiber composite having at least one core in the mold, wherein the core has a top side with first channel portions and an underside with second channel portions, and connecting portions between the first and second channel portions, and feeding resin, in particular through the first and/or second channel portions, until the layered fiber composite is adequately saturated. | 02-14-2013 |
20130142659 | DETUNED VANE AIRFOIL ASSEMBLY - A vane assembly comprises circumferentially adjacent airfoils formed of composite materials. The airfoils have matching exterior geometries defined by pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section. An inner platform is attached to each of the circumferentially adjacent airfoils at the root section, and an outer platform is attached at the tip section. The composite materials are selected to define a vibration mode with different vibration frequencies in the circumferentially adjacent airfoils, where the different vibration frequencies are separated by more than a full width of the vibration mode at half maximum. | 06-06-2013 |
20130149166 | FORMATION OF A CORE STRUCTURE OF A WIND TURBINE ROTOR BLADE BY USING A PLURALITY OF BASIC CORE COMPONENTS - A basic core component is provided for forming, together with at least one another basic core component, a core structure of a rotor blade of a wind turbine. The basic core component includes a precasted base element being made from a foam material, and a resin receiving layer, which is adhered to at least one surface of the precasted base element. When, during a casting procedure, the resin receiving layer adjoins the surface of another basic core component, the resin receiving layer is adapted to receive resin such that, after hardening the received resin, the basic core element and the another basic core element are mechanically connected with each other. | 06-13-2013 |
20130156594 | COMPOSITE ROTOR AND VANE ASSEMBLIES WITH INTEGRAL AIRFOILS - A composite gas turbine engine structure includes a retention ring with airfoils mounted on, integral with, and extending radially away from retention ring. Retention ring includes annular composite plies, a circumferentially segmented airfoil ring including airfoil ring segments disposed around one of outer and inner circumferences of retention ring. Airfoil ring segments include annular bases and radially extending clockwise and counter-clockwise airfoil segments at clockwise and counter-clockwise ends of annular base. Composite airfoils include circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments. A flowpath shell circumferentially disposed around segmented airfoil ring traps annular bases between flowpath shell and retention ring. Composite airfoils airfoils extend through slots in flowpath shell. Plies may be wrapped in a single spiral made from a continuous composite tape. Slots may be circumferentially angled. Circumferentially adjacent ones of clockwise and counter-clockwise airfoil segments may be stitched together. | 06-20-2013 |
20130230404 | METHOD OF OPTIMIZING THE PROFILE OF A COMPOSITE MATERIAL BLADE FOR ROTOR WHEEL OF A TURBINE ENGINE, AND A BLADE HAVING A COMPENSATED TANG - A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment. | 09-05-2013 |
20130243604 | TURBOMACHINE BLADES OR VANES HAVING COMPLEMENTARY EVEN/ODD GEOMETRY - A turbomachine blade made of composite material including a fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, comprises a first portion constituting an airfoil and a blade root. The first portion constitutes a single part with at least one second portion constituting a blade inner platform, said blade then lacking a blade anti-tilting wall, or a blade anti-tilting wall, said blade then lacking a blade inner platform. The first portion also constitutes a single part with at least one third portion constituting a blade outer platform spoiler plate, said blade then lacking a blade outer platform wiper plate, or a blade outer platform wiper plate, said blade then lacking a blade outer platform spoiler plate. | 09-19-2013 |
20130280086 | FAN IMPELLER STRUCTURE AND MANUFACTURING METHOD THEREOF - A fan impeller structure and a manufacturing method thereof. The fan impeller structure includes a base seat, multiple blades and a ring member. Each blade has a main body made of plastic material and at least one fixing member made of metal material. The base seat and the ring member are made of metal material. The base seat and the ring member are respectively disposed on two sides of the blades. By means of the manufacturing method, the blades can be diversified and the universality of the blades is greatly increased to lower the manufacturing cost. | 10-24-2013 |
20130280087 | COMPOSITE STRUCTURES - A foam core for a composite structure is described. The core includes a first core layer ( | 10-24-2013 |
20130287589 | FIBRE REINFORCED COMPOSITE MOULDING - The present invention regards a fibre-reinforced composite moulding with an outer ( | 10-31-2013 |
20130294923 | WIND TURBINE ROTOR BLADE AND WIND TURBINE FOR WIND POWER GENERATION - To provide a wind turbine rotor blade capable of protecting a base material in the blade tip portion of the wind turbine blade from liquid droplet erosion due to raindrops to improve durability of the wind turbine rotor blade, thereby lengthening the interval of maintenance of the wind turbine rotor blade. It is provided with a base material provided with an outer skin material formed of fiber-reinforced plastic, a protective coating having wear resistance that is applied over the entire surface of the base material, and a protective tape having wear resistance that is affixed to the leading edge portion of the protective coating in the blade tip portion. | 11-07-2013 |
20130294924 | METHOD FOR MANUFACTURING A TURBINE ENGINE PART BY INJECTION OF RESIN UNDER PRESSURE - A method for manufacturing a thick turbine engine part in a composite material by injection of resin under pressure. A fiber preform is positioned in a mold, a resin composition is injected into the mold, the resin composition is polymerized in the mold so as to obtain the part, and the part is removed from the mold. Prior to the injection of the resin composition, a mold release shim is inserted between the fibrous preform and a wall of the mold, and between the polymerization of the resin composition and the removal of the part from the mold, the mold release shim is extracted. | 11-07-2013 |
20140030106 | Compressor blade of a gas turbine as well as method for manufacturing said blade - The present invention relates to a compressor blade of a gas turbine having an airfoil made of a fiber-reinforced plastic and a leading-edge element connected to said airfoil, characterized in that the leading-edge element includes two partial elements, which are fabricated as separate elements and connected to one another, with the leading-edge element being connected to the airfoil essentially using the clamping effect of the two partial elements, as well as to a manufacturing method. | 01-30-2014 |
20140030107 | DECOUPLED COMPRESSOR BLADE OF A GAS TURBINE - The present invention relates to a compressor blade of a gas turbine having an airfoil made of a fiber-reinforced plastic, which is fastened by means of a blade root to a disk, as well as a metallic leading-edge element, which is arranged on the leading-edge side of the airfoil and partially encompasses the latter, with the leading-edge element itself being fastened to the disk. | 01-30-2014 |
20140072439 | TRI-LOBE FLOWMETER ROTOR WITH PARTIALLY OPEN CORE STRUCTURE - There is a gear rotor for use in a positive displacement flowmeter of the type described. The rotor has an external wall profile | 03-13-2014 |
20140127031 | SCREW ROTOR FOR EXHAUST PUMP, METHOD FOR MANUFACTURING THE SAME, GAS EXHAUST PUMP HAVING SCREW ROTOR, AND MANUFACTURING METHOD AND ASSEMBLY METHOD OF THE SAME - There is provided a screw rotor that can ensure safe rotation and can greatly increase a pumping performance of a pump. The screw rotor is placed with a gap between a top end surface of a tooth of a screw portion and an inner wall surface of a stator. A PFA film is provided on the top end surface. If the PFA film of the present invention is provided in a predetermined manner, the width of a gap between a free surface of the PFA film and the inner wall surface of the stator can be made significantly smaller than that of a conventional one, so that the pumping performance is greatly improved. After coating at least the top end surface of the screw rotor with PFA, followed by melting and remelting processes, the PFA film is formed to have a high smoothness on its free surface. | 05-08-2014 |
20140308136 | METHOD OF MANUFACTURING A COMPOSITE MATERIAL INCLUDING A THERMOPLASTIC COATED REINFORCING ELEMENT - A method of through-thickness reinforcing a laminated material is disclosed, in which a reinforcing element is coated with a thermoplastic layer. The reinforcing element is inserted into a base material, and a matrix material, such as a polymeric, is included in the base material. The combination is then cured, or heated, such that the thermoplastic layer and the matrix material diffuse into each other, thereby forming an interphase region around the reinforcing element. This interphase region helps to prevent cracks from propagating from the reinforcing element. | 10-16-2014 |
20140369850 | CROSS-LINKABLE COATING COMPOSITION AND METHOD OF PRODUCING THE SAME - The instant invention provides cross-linkable coating compositions, process for producing the same, and substrates coated therewith. The cross-linkable coating composition comprises: (a) polyaldehyde, or acetal or hemiacetal thereof; (b) an acid catalyst having pKa of less than 6; (c) a liquid media; (d) an acrylic polycarbamate comprising at least an average of 2.0 carbamate functional groups, wherein said polycarbamate has a glass transition (Tg) of less than 25° C.; and (e) one or more fillers having a pH in the range of equal to or less than 9 and/or one or more pigments having a pH in the range of equal to or less than 9, and/or one or more additives having a pH in the range of equal to or less than 9, wherein said composition has a curing temperature in the range of less than 70° C. | 12-18-2014 |
20160083621 | COMPOSITE ARTICLE HAVING PROTECTIVE COATING - A composite article includes a substrate and a protective coating on at least a portion of the substrate. The protective coating includes reinforcement particles dispersed within an elastomeric matrix that is modified with a silicon-containing modifier selected from polysilsesquioxane, polyhedral oligomeric silicate, polyhedral oligomeric silsesquioxane (POSS), and combinations thereof. The reinforcement particles are selected from carbon, nickel metal, and combinations thereof. The protective coating is multi-layered and includes a distinct first layer and a distinct second layer that is contiguous with the distinct first layer such that each of the distinct first layer and the distinct second layer have an exposed outer surface. | 03-24-2016 |
20160195062 | INDUCTION CONSOLIDATION FOR WIND BLADE FABRICATION | 07-07-2016 |
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