Entries |
Document | Title | Date |
20080206049 | BLADE ANGLE SETTING FOR A TURBOMACHINE - A straightener blade for a turbomachine, comprising a platform arranged at a radially external end of the blade and adapted to be engaged in a annular groove of a housing, and a threaded rod radially extending outwardly from the platform and adapted to pass through an orifice of the housing in order to receive a fixing nut, the upstream and downstream edges of the platform each comprising a protrusion extending in the plan of the platform in order to limit the rotation of the platform in the groove when the nut screwed on the threaded rod is tightened. | 08-28-2008 |
20080213090 | Thrust Generating Apparatus - There have been past proposals for air vehicles employing the Coanda effect. In these proposals, a jet of fluid, usually air, is made to flow radially outwardly over a dome-shaped canopy to create lift. A cross-section through the canopy is curved to follow a segment of a circle or it may have a radius of curvature that increases in the direction of flow. In the invention, the radius (r) of the canopy curve decreases towards the downstream direction (x) in a way that is related to the decrease in the width of the jet as it flows over the surface. This means that the radius of curvature decreases (instead of increasing) towards the downstream direction with the rate of decrease being progressively less rapid towards the downstream direction. | 09-04-2008 |
20080219841 | Fan with strut-mounted electrical components - A cooling fan comprises a fan housing, a motor which is positioned within the fan housing, a plurality of electronics components which are associated with the motor, and at least one strut which extends radially between the motor and the fan housing, and on which the electrical components are mounted. | 09-11-2008 |
20080232960 | Fluid return in the splitter of turbomachines with bypass-flow configuration - A turbomachine, includes an annular flow duct, which downstream of at least one stage, is divided into an outer annular bypass duct and an inner annular core-flow duct via a concentrically arranged splitter, wherein the splitter is designed as an intermediate casing with at least one inner volume, through which fluid may be returned between core-flow stages. | 09-25-2008 |
20080240913 | FAN FRAME WITH DIVERSION STRUCTURE - The present invention provides an improved fan frame with a diversion structure. A cooling fan includes a rotor, and fan blades spaced around the rotor at intervals. The fan frame positions the rotor and defines a diversion loop, which corresponds to the air outlet direction when fan blades are turning and has an expanding diversion surface. The fan frame has a diversion surface with diversion ribs spaced at intervals, the placement of the diversion ribs being in a vortex pattern without passing through the hypothetical point of the rotor center. The airflow generated by turning fan blades is guided by the diversion ribs and converted to outlet airflow in axial direction corresponding to the rotor, effectively reducing impact and friction of the gyrate airflow generated by fan blades against the frame diversion surface, lowering the noise level, making air exhaustion smoother, and improving the cooling efficiency of fan. | 10-02-2008 |
20080253884 | Out-flow margin protection for a gas turbine engine - A cooled turbine exhaust case assembly includes a plenum defined at least in part by a forward outer diameter flowpath ring and a turbine case, a probe positioned at a probe opening formed in the forward outer diameter flowpath ring, and an inlet opening in the turbine case for introducing cooling air to the plenum. | 10-16-2008 |
20080267775 | Nozzle segments and method of repairing the same - A method of repairing a nozzle segment is provided. The nozzle segment includes at least one airfoil extending between an inner band and an outer band, and the airfoil includes a first sidewall and an opposing second sidewall that are joined together at a leading edge and at an axially-spaced trailing edge. The method includes identifying a damaged portion of the airfoil, repairing the damaged portion of the airfoil by at least one of welding weld filler in the area of the damaged portion of the airfoil, and brazing preform in the area of the damaged portion of the airfoil, and blending at least one of the weld filler and the preform to remove excess material to facilitate finishing an outer surface of the airfoil. | 10-30-2008 |
20080273970 | HP turbine vane airfoil profile - A two-stage high pressure turbine comprises a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 11-06-2008 |
20080273971 | TURBINE NOZZLE SEGMENT AND REPAIR METHOD - A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed. | 11-06-2008 |
20080273972 | TEMPERATURE CONTROLLING APPARATUS - An apparatus for controlling the temperature of a component, which is situated in use in a gas stream, provides a nozzle to create a jet of air at an angle to the gas stream, the jet being directed into the region of the stagnation point of the component so as to control the temperature of the component. The invention is particularly suited to preventing or reducing the formation of ice on vanes of gas turbine engines, but may also be applied to other components, and may equally be used in situations where a component is to be cooled rather than heated. | 11-06-2008 |
20080292456 | Device for Producing Mechanical Energy by Means of a Divergent, Telescopic and Auto Sustained Chimney - A telescopic chimney and methods are disclosed for generation of mechanical energy using air routed through a turbine. Truncated cones stored nested together telescope to interlock when extended end to end to form a conical shape that diverges upwardly. An air output deflector at the exit of the chimney drives the exiting airflow downwards and is optionally divided into six equal radial spans so that airflow can be varied through each by a computer-controlled shutter to compensate for wind forces. An axial cable raises and lowers truncated cones. A method of deploying the chimney includes steps of closing the shutters; filling the truncated cones with heated air; controlling the rise of the truncated with the cable; and, opening the shutters. A method of collapsing the chimney includes the steps of pulling the cable to exert downward force on a truncated cone. | 11-27-2008 |
20080298960 | Micro-Air Motor - A micro-air motor comprises a collector rotatably mounted in a casing for the compressed air supply and discharge to or from the rotor. By twisting the collector as far the end positions a direction of rotation reversal as well as continuous speed regulation is possible. In a neutral position of the collector the rotor can be additionally stopped and locked. | 12-04-2008 |
20080304961 | Noise Reduced Variable Displacement Vane Pump - A novel and useful improvement to vane pumps, both variable displacement vane pumps and fixed displacement vane pumps, provides a supply of pressurized fluid to the region within the diameter of the pump rotor which would otherwise be a region of reduced pressure wherein air could be ingested by the pump. By reducing or preventing the ingestion of air, operating noise and damage to the pump can be reduced and wear in an engine or other system supplied from the pump can be reduced. The supply of pressurized working fluid also can be used to lubricate auxiliary components and/or accessories as well. Further, a portion of the supply of pressurized working fluid to this region can act to supercharge the pump, reducing the occurrence of cavitation at higher operating speeds. | 12-11-2008 |
20080317590 | PRODUCTION METHOD OF STATOR BLADE AND TURBO-MOLECULAR PUMP WITH THE STATOR BLADE - Disclosed is a method of producing a stator blade for use in a turbo-molecular pump. The method includes subjecting a metal plate to a slitting process to form a blade element having an upstream edge surface and a downstream edge surface, wherein a laser beam is emitted onto the metal plate at an incident angle oblique to a principal surface of the metal plate. Thus, the upstream edge surface and/or the downstream edge surface can be formed to extend obliquely relative to the principal surface of the metal plate, in a simple manner, while eliminating a need for a burr removal operation which would otherwise be necessary in a punching-based slitting process. | 12-25-2008 |
20090003999 | Three-Vaned Drag-Type Wind Turbine - A novel three-vaned, drag-type wind turbine, wherein air, when it exits a first vane, is split into two flow paths. A first path is directed to a second vane, while a second path is directed to a third vane. The air, then, impinges on a plurality of vanes wherein the momentum of the air is altered, thus providing the force needed to drive the wind turbine. In a first embodiment, a wind shield is used to deflect a portion of the wind from entering the wind turbine, this portion being in a region where the vanes are rotating into the wind. In second embodiment, the wind shield is not used. | 01-01-2009 |
20090016877 | THRUST VECTORING SHROUD FOR FLUID DYNAMIC DEVICE - A fluid dynamic device including a shroud disposed about a central axis and having an upstream fluid intake region and a downstream fluid exit region, the shroud directing fluid flow between the upstream fluid intake region and the downstream fluid exit region. The shroud is configured so that, at least during some operating conditions of the fluid dynamic device, at least a portion of fluid exiting the fluid exit region is directed towards the central axis. | 01-15-2009 |
20090028698 | Systems and Methods Involving Aerodynamic Struts - Systems and methods involving struts are provided. In this regard, a representative system includes a gas turbine engine defining a gas flow path. The gas turbine engine comprises a strut extending into the gas flow path. The strut has an interior operative to receive pressurized air, an outer surface, and ports communicating between the outer surface and the interior of the strut, the ports are operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that an effective aerodynamic length of the strut along the gas flow path is increased. | 01-29-2009 |
20090047125 | FLOW CHANNEL OF A REGENERATIVE PUMP - The present invention provides an improvement in a new structure of a regenerative pump, including a cross section structure of the flow channel of a pump casing and closed type impeller, whereby to improve a better flow model for pump performance to solve problems of noise, and to increase the outflow capacity and higher efficiency. | 02-19-2009 |
20090053054 | LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS - Disclosed is a leakage reducing venturi for a dry low nitric oxides (NOx) emissions combustor, the venturi including a substantially annular outer liner, a substantially annular inner liner, a venturi channel defined by the annular inner liner and the annular outer liner, the venturi channel including a forward end and an aft end, a forward weld disposed in proximity to the forward end of the venturi channel, the forward weld being configured to connect the annular outer liner with the annular inner liner, and an aft weld disposed in proximity to the aft end of the venturi channel, the aft weld being configured to connect the annular outer liner with the annular inner liner. | 02-26-2009 |
20090060732 | SERIAL FAN MODULE AND FRAME STRUCTURE THEREOF - A serial fan module includes a first fan, a second fan and a plurality of guide elements. The first fan has a first frame body and a first impeller disposed within the first frame body. The second fan has a second frame body and a second impeller disposed within the second frame body. The guide elements are disposed between the first impeller and the second impeller, wherein the guide elements guide airflow from the first fan to the second fan. Each of the guide elements has an axial extended part and an inclined part and the inclined part meets the axial extended part at a camber angle. Each of the inclined part has an inner edge toward the first impeller and each of the axial extended part has an outer edge toward the second impeller. | 03-05-2009 |
20090068005 | Airfoil Shape For A Turbine Nozzle - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth TABLE I. The X and Y values are distances in inches, which when connected by smooth continuing arcs define airfoil profile sections at each distance Z in inches The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +0.130 inch to −0.030 inch. | 03-12-2009 |
20090074571 | VANE STRUCTURE OF AN AIRFLOW GENERATOR - The present invention provides a vane structure of an airflow generator. The plate of predefined thickness and width has a locating portion and a swinging end. The swinging end of the vane is wider than the locating portion. There is an oblique section placed between the swinging end and locating portion for linking purposes. A better wind guide effect can be obtained from the expanded swinging end, and the oblique section is employed to reduce inlet stagnation, thus greatly improving the smoothness of air flow and the operating performance of the vane with better applicability. | 03-19-2009 |
20090081035 | GAS TURBINE ENGINE COMPRESSOR CASE MOUNTING ARRANGEMENT - A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area. | 03-26-2009 |
20090104032 | AIR CONDITIONER - An air conditioner includes a fan and a rear guide which guides air to the fan. A recess is formed in a side surface of the rear guide which faces the fan. | 04-23-2009 |
20090155067 | NACELLE ASSEMBLY WITH TURBULATORS - A nacelle assembly for a turbine engine has a cowl. The cowl extends along an axis and has an exterior surface spaced from an interior surface. The interior surface forms an air inlet for directing airflow to the turbine engine. A turbulator for creating turbulence is disposed on one of the interior surface and the exterior surface. | 06-18-2009 |
20090169375 | DEVICE FOR STIFFENING THE STATOR OF A TURBOMACHINE AND APPLICATION TO AIRCRAFT ENGINES - The invention concerns a novel type of turbomachine. | 07-02-2009 |
20090175719 | METHOD OF MANUFACTURING A TURBOMACHINE ELEMENT AND DEVICE OBTAINED IN THIS WAY - Use of the stator blade platforms for the deposition of a track of adjacent abradable material inside an external turbomachine shell. | 07-09-2009 |
20090196745 | INLET GUIDE VANE, COMPRESSOR AND REFRIGERATOR - An inlet guide vane is turnably installed about an axis line at a suction port into which a fluid is drawn by rotation of an impeller in order to adjust a suction amount and flow direction of the fluid, the inlet guide vane, and includes: a shaft that is turnably supported by inserting a round bar-shaped shaft main body portion thereof in a bearing sleeve; and a plate-shaped vane main body that is joined with the shaft and projects from an inner periphery surface of the suction port to a central portion of the suction port, the shaft including a flange portion that is provided at a distal end side in a direction of the axis line to join with the vane main body and that extends to an outside in a direction perpendicular to the axis line so as to be extended outward in a radial direction of the bearing sleeve. | 08-06-2009 |
20090214335 | METHOD OF REPAIR FOR CANTILEVERED STATORS - A method for repairing a cantilevered stator vane includes removing a damaged portion leaving a remaining vane portion. A supplemental airfoil portion is then selected and is attached to the remaining vane portion to provide a repaired cantilevered stator vane. | 08-27-2009 |
20090246011 | FILM COOLING OF TURBINE COMPONENTS - A turbine component includes a flow path surface and a trench disposed in the flow path surface. At least one cooling through hole is located in the trench and is capable of injecting a cooling flow onto the flow path surface of the turbine component. The cooling flow forms a cooling film on the flow path surface. A method of cooling a turbine component includes injecting a cooling flow onto a flow path surface of the turbine component through at least one cooling through hole disposed in a trench in the turbine component. A cooling film is formed by the cooling flow between the flow path surface and a hot gas flow. | 10-01-2009 |
20090246012 | TURBINE STATOR MOUNT - A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane. | 10-01-2009 |
20090252606 | Workpiece, and Also a Welding Method for the Manufacture of a Workpiece - The invention relates to a workpiece ( | 10-08-2009 |
20090257866 | Stator blade for a turbomachine, especially a steam turbine - The invention relates to a stator blade ( | 10-15-2009 |
20090257867 | TURBINE, IN PARTICULAR FOR AN EXHAUST-GAS TURBOCHARGER, AND EXHAUST-GAS TURBOCHARGER - The invention relates to a turbine, in particular of an exhaust-gas turbocharger, comprising a turbine rotor which is supported rotatable in a housing, and to which at least one guide vane apparatus forming a radial inlet channel for a medium driving the turbine rotor is allocated, wherein the guide vane apparatus comprises a guide vane mounting ring with a plurality of guide vanes which radially surround the turbine rotor and which are located within the inlet channel, as well as a guide vane cover ring, and wherein the inlet channel is axially bounded by the guide vane mounting ring and the guide vane cover ring, and the guide vane cover ring abuts with a front side facing away from the inlet channel against a support area of the housing. The invention provides that the housing ( | 10-15-2009 |
20090280007 | MULTI-FUNCTIONAL AIR CIRCULATION SYSTEM - A multi-functional air circulation system includes a bottom base, a flow-splitting base, a filter and a main engine. The bottom base has a lower flow-guiding surface, a net, and a space used to contain diverse improving agents. The flow-splitting base is fixed on the bottom base, including an inner flow-guiding surface to rush air flow generated by a blade member down to the bottom base. The filter is laid at an exit of the inner flow-guiding surface, composed of two filter bases forming a room between them for containing aromatic powder, etc. The main engine includes a motor having its shaft fixed with a blade member, and a control system. The motor is installed in a rear shell combined with a front shell. Air is sucked in through the rear shell to run through an ornamental shell and the flow-splitting base to enter a room. The main engine and the bottom base can also be assembled to work independently. | 11-12-2009 |
20090297344 | Rotors and manufacturing methods for rotors - A rotor for driving, or being driven by, a fluid has rotor blades that follow a screw thread shape, all portions of all blades having the same screw pitch. This enables the rotor, or a molding pattern for use in making a mold, to be withdrawn from a mold part by a screw motion without damage to the mold part. This helps to make it economically viable to manufacture the rotor by a molding or casting process in which the mold parts are not destroyed to release the rotor, such as injection molding, for example with reinforced plastics. Additionally, in the case of manufacturing methods in which the mold is destroyed to release the rotor, the process of making or assembling the mold may be improved. In some molding processes, the ability to remove the rotor or the pattern by screw motion improves the economic viability of the process by reducing the number of mold parts required. | 12-03-2009 |
20090304501 | POND PUMP - A pond pump comprising an impeller ( | 12-10-2009 |
20100008773 | Turbine blade and gas turbine equipped with a turbine blade - The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis. | 01-14-2010 |
20100021292 | FLUID DEFLECTOR FOR FLUID SEPARATOR DEVICES - A fluid deflector is for a fluid separator including a central axis and an enclosed wall having an open end and an inner circumferential separation surface extending about the axis to define an interior separation chamber. The fluid deflector includes a base disposeable proximal to the wall open end and having a central axis collinear with the separator axis. A plurality of vanes are connected with the base so as to be spaced circumferentially about the central axis. The vanes define a plurality of flow channels each bounded by a separate pair of adjacent vanes and having an inlet and an outlet. Each vane directs flow through a bounded channel generally radially inwardly from the channel inlet toward the channel outlet and generally circumferentially and radially outwardly from the channel outlet. | 01-28-2010 |
20100028145 | Flow control arrangement - Flow restrictors ( | 02-04-2010 |
20100034649 | DEVICE FOR ENHANCING THE EFFECTIVENESS OF POWER CONVERSION FROM WIND AND OTHER FLUIDS - An energy enhancing device for increasing the effectiveness of energy conversion from wind and other fluid flows is presented by improving methods of accelerating the fluid flow passing through a turbine device or energy converter. Their main application is for accelerating the speed of fluid flow for fluid turbines and other devices designed to extract power from winds, induced air currents, river, ocean, tidal and other water currents. | 02-11-2010 |
20100040462 | Separation-resistant inlet duct for mid-turbine frames - A transition duct assembly for a gas turbine engine includes an outer diameter surface and an inner diameter surface. A substantially annular flowpath having a radial offset is defined between the inner diameter surface and the outer diameter surface. A curvature distribution of the inner diameter surface includes a first region of increasing slope in a radial direction and a second region of decreasing slope in the radial direction adjacent to and downstream of the first region. The first and second regions are configured to reduce flow separation along the outer diameter surface of fluid traveling along the substantially annular flowpath. | 02-18-2010 |
20100040463 | Sealing means - A sealing means for sealing between segments of a component assembly. The sealing means comprises a sealing member having a mating surface for mating with the surface of the segment. The sealing means further comprises a location member removably attached to the sealing member along a transition region therebetween, and also a free end distal to the sealing member. The location member is configured to engage a location feature of the segment so as to locate the mating surface of the sealing member in a fixed position on the surface of the segment relative to the location feature. The location member is configured to be detached from the sealing member along the transition region and be removed from the segment after the sealing member has been bonded to the segment. | 02-18-2010 |
20100061850 | AIRFOIL SHAPE FOR A COMPRESSOR VANE - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape. | 03-11-2010 |
20100074743 | Air Diffuser For a HVAC System - A diffuser for carrying air flow to an evaporator in an air conditioning system of an automotive vehicle includes an inlet and an outlet, a wall extending between the inlet and the outlet, and a guide vane, extending at least partially between the inlet and the outlet, spaced from the wall by a containing a control region whose area ratio changes along a length of the guide vane. | 03-25-2010 |
20100074744 | Fabricated Turbine Housing - A turbine housing is provided. The turbine housing includes a tongue diverter to manage the interaction between exhaust gases entering the inlet of the housing and gasses flowing within the housing. The tongue member may also be arranged to produce a constant ratio throughout the turbine housing between the cross-sectional area of fluid passages and the distance between the centroid of that area and the axis of rotation of the turbine. The housing may comprise a pair of half shells that each form a portion of the tongue diverter. | 03-25-2010 |
20100086400 | INTAKE DEVICE AND A PUMP STATION - In a first aspect the invention relates to an intake device ( | 04-08-2010 |
20100098536 | FLUID FLOW MACHINE WITH RUNNING GAP RETRACTION - A fluid flow machine includes a main flow path which is confined by a hub ( | 04-22-2010 |
20100124493 | MULTI-VANE SEGMENT DESIGN AND CASTING METHOD - Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud. | 05-20-2010 |
20100135778 | Vane - A vane for a gas turbine engine comprising a cap arrangement comprising a cap insert and a cap adapted to receive the insert, the cap insert comprising a wall defining a through passage from top to bottom of the cap insert for receiving a cable or the like therethrough, the wall comprising a slot with a convoluted profile. Also a vane for a gas turbine engine comprising a cap and a cap insert as described. | 06-03-2010 |
20100135779 | SEMI-FINISHED PRODUCT FOR PRODUCING A REPAIRED BLADE FOR A GAS TURBINE AND REPAIR METHOD FOR REPAIRING A BLADE FOR A GAS TURBINE - The invention relates to a semi-finished product for producing a repaired blade for a gas turbine. Said semi-finished product comprises a first part ( | 06-03-2010 |
20100135780 | Component with Compressive Residual Stresses, Process for Producing and Apparatus for Generating Compressive Residual Stresses - A turbine blade or vane is provided. The turbine blade or vane includes an airfoil portion, a root portion arranged below the airfoil portion, a dove tail shaped securing portion arranged below the root portion have a surface including subregions that have locally different compressive residual stresses, and a convexly curved sub region arranged on the surface and adjacent to the concavely curved sub region. The concavely curved region has higher compressive residual stresses than the convexly curved region, and the level of the compressive residual stress in the concavely curved region is at least 30% of the component base material yield strength. | 06-03-2010 |
20100143110 | VANE FOR A COMPRESSOR OR A TURBINE OF AN AIRCRAFT ENGINE, AIRCRAFT ENGINE COMPRISING SUCH A VANE AND A METHOD FOR COATING A VANE OF AN AIRCRAFT ENGINE - An aircraft engine comprising a compressor and at least one turbine is disclosed. The compressor and the turbine are each provided with vanes, each of which has a blade that forms a suction side and a pressure side, where at least one first of the blades is coated with a protective layer in order to reduce the erosion or wear. The layer is applied such that at least two areas are formed that adjoin each other at a boundary line. The first area has a protective layer that has a substantially constant first thickness and the second area is free of the protective layer or has the protective layer with a substantially constant second thickness, the second thickness differing from the first thickness. The boundary line has at least two points, of which the connecting line differs from the course of the boundary line between the two points. | 06-10-2010 |
20100143111 | COMPRESSOR STABILIZER - An annular circulation chamber is arranged in an interior of a compressor housing, which circulation chamber radially surrounds a main flow duct and extends from an intake region to an encircling circulation opening in a region of rotor blades of the compressor wheel. Between the circulation openings, the circulation chamber is delimited from the main flow duct by an annular contoured wall. The contoured wall is connected to the inner compressor housing by plural struts which are spaced apart from one another to different extents in the circumferential direction. As a result of the irregular distribution of the struts in the circumferential direction, generation of undesired vibration excitations can be reduced and/or eliminated. | 06-10-2010 |
20100150710 | STATOR VANE FOR A GAS TURBINE ENGINE - A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance. | 06-17-2010 |
20100158684 | VANE ASSEMBLY CONFIGURED FOR TURNING A FLOW IN A GAS TURBINE ENGINE, A STATOR COMPONENT COMPRISING THE VANE ASSEMBLY, A GAS TURBINE AND AN AIRCRAFT JET ENGINE - A vane assembly configured for turning a flow in a gas turbine engine includes a stationary main guide vane and an additional guide vane, wherein a leading edge of the additional guide vane is positioned upstream of a leading edge of the main guide vane and wherein the additional guide vane extends a distance along the main guide vane towards a trailing edge of the main guide vane forming a passageway between the additional guide vane and the main guide vane. | 06-24-2010 |
20100166550 | METHODS, SYSTEMS AND/OR APPARATUS RELATING TO FREQUENCY-TUNED TURBINE BLADES - A method of tuning a compressor stator blade, having a base portion and an airfoil portion, to achieve a desired natural frequency, comprising: a) identifying the natural frequency of the compressor stator blade; b) determining a different target natural frequency for the compressor stator blade; and c) removing material from at least one of the side surfaces of the base portion of the compressor stator blade in an amount and in a configuration that achieves the target natural frequency. | 07-01-2010 |
20100166551 | HYBRID TURBOMACHINERY COMPONENT FOR A GAS TURBINE ENGINE - The present invention provides a hybrid turbomachinery component for use in a gas turbine engine. The hybrid turbomachinery component may be operative to direct the working fluid of the gas turbine engine and/or addi energy to the working fluid and/or extract energy from the working fluid. One or more portions of the hybrid turbomachinery component are made from one material, and other portions of the hybrid turbomachinery component are made from another material. | 07-01-2010 |
20100172752 | AIRFOIL PROFILE FOR A SECOND STAGE TURBINE NOZZLE - Second-stage nozzles have vanes including airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the nozzle. | 07-08-2010 |
20100172753 | COMPRESSOR SIDE INLET WITH IMPROVED AERODYNAMIC PERFORMANCE AND REDUCED MANUFACTURING COMPLEXITY - An air plenum is configured to direct air into a centrifugal compressor impeller in an ACM compressor. The air inlet plenum has a cylindrical outer wall, a forward circular end wall, and a rearward circular end wall. An air inlet radially extends from the cylindrical outer wall and is in flow communication therewith. An aperture in forward circular end wall is configured to seal receive about a rotating shaft. An aperture in rearward circular end wall is configured to receive the rotating shaft and allow air flow therethrough about the rotating shaft. A rectangular baffle extends radially inward from the cylindrical outer wall at a circumference thereof opposite the air inlet. The rectangular baffle may extend between the forward and rearward end walls. | 07-08-2010 |
20100189559 | FIXTURE FOR USE IN A COATING OPERATION - This invention relates to a fixture for use in a physical vapor deposition coating operation which comprises a support structure | 07-29-2010 |
20100196152 | ROTARY PRESSURE TRANSFER DEVICE WITH IMPROVED FLOW - A rotary pressure transfer device utilizes a multi-channel, generally cylindrical rotor ( | 08-05-2010 |
20100196153 | Fluid turbine systems - Various fluid turbine systems and methods are described. The turbine can be a vertical axis wind turbine configured to generate power from wind energy. The turbine system can have a blade assembly. The blade assembly can have a plurality of blades rotatable about an axis. The turbine system can have a concentrator positionable upwind and in front of a return side of the blade assembly. The concentrator can define a convex surface facing the wind. The turbine system can also have a variable concentrator positionable upwind of a push side of the blade assembly. The variable concentrator can be adjustable between a first position and a second position, the variable concentrator being capable of deflecting more wind toward the turbine in the first position than in the second position. | 08-05-2010 |
20100202878 | Turbo Engine and Method for Producing Such a Turbo Engine - A flow machine having a housing, an axial diffuser, a rotor for deflecting a fluid between an axial direction and a radial direction, a spiral, and an axial diffuser insert which is at least partially received in the housing. A spiral contour is formed in the diffuser insert and, together with the housing, defines the spiral. | 08-12-2010 |
20100209236 | IMPULSE TURBINE FOR USE IN BI-DIRECTIONAL FLOWS - A bi-directional flow impulse type turbine arrangement ( | 08-19-2010 |
20100209237 | VANE - A vane for use in a duct, such as an exhaust duct in a gas turbine engine, comprises a shear web arranged to extend substantially across the duct and to be fixedly attached to at least one wall thereof, and one or more vane plates removably mountable on the web. On each side of the web three retaining plates are secured to the web by bolts | 08-19-2010 |
20100215488 | FLUID FLOW ENERGY CONCENTRATOR - An energy conversion system for converting energy of naturally occurring fluid flow into output power. The energy conversion system includes an accelerator plate that has a leading edge and an upper surface that is substantially linearly inclined from the leading edge and transitions into a gradually increasing inclined shape so as to receive a fluid flow and form a vortex at a rear portion of the accelerator plate and a turbine positioned at the rear of the accelerator to rotate in the vortex created by the accelerator plate. The cross-sectional shape of the accelerator plate has a duckbill shape which causes the fluid flow to increase up to five times and before turbulence is created and directs the increased air flow onto the blades of the turbine. | 08-26-2010 |
20100221108 | Turbine nozzle assemblies - A nozzle assembly for a turbine that may include: (1) a nozzle-blade having inner and outer sidewalls and, in part, defining a flowpath upon assembly into the turbine; (2) an outer ring; (3) a flowsplitter having a horizontal extension; (4) an interface between the outer ring and the outer sidewall having at least one of (i) a male/female interface or (ii) a radial interlock; and (5) an interface between the horizontal extension and the inner sidewall having at least one of (i) the male/female interface or (ii) the radial interlock. In some embodiments, one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall comprises a weld and one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall is weld free. | 09-02-2010 |
20100226768 | AXIAL-FLOW TURBINE - The axial-flow turbine includes an extraction chamber | 09-09-2010 |
20100226769 | FAN ASSEMBLY - A bladeless fan assembly includes a nozzle mounted on a base housing a motor and an impeller driven by the motor for creating an air flow. The nozzle includes an interior passage for receiving the air flow, a mouth for emitting the air flow, and a plurality of stationary guide vanes located within the interior passage and each for directing a portion of the air flow towards the mouth. The nozzle defines an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. | 09-09-2010 |
20100232956 | Turbine Singlet Nozzle Assembly with Radial Stop and Narrow Groove - A nozzle assembly for a turbine including an airfoil, inner and outer sidewalls, and inner and outer rings is provided. The sidewalls and rings are coupled together using a weld and mechanical interconnection, including axial and radial mechanical stops to allow for an accurate assembly, to ensure correct radial and axial positions of the parts during welding, to minimize weld shrinkage and to control an axial weld length. The configuration may further include one or more surfaces at an interface between a ring and a sidewall angled away from the interface to form a narrow groove. The configuration further may include a ring with a consumable root portion to facilitate the weld, and to provide a fixturing stop to further ensure that the parts remain in the correct position. | 09-16-2010 |
20100232957 | Blower Fan - A blower fan includes a housing having a compartment. A stator and an impeller are mounted in the compartment. The housing further includes an air inlet and an air outlet both communicated with the compartment. The impeller has a hub and a plurality of vanes coupled to the hub. Each vane includes an upper edge whose end is an air input portion adjacent to the air inlet of the housing, and an air gap is formed between the upper edge of each vane and a top of the housing, with various widths of the air gap ranging from 0.3 mm to 2.0 mm, while a shortest width of the air gap is formed between the air input portion of the upper edge and the top of the housing for providing reduced turbulence and noises. | 09-16-2010 |
20100232958 | NOZZLE BOX OF AXIAL FLOW TURBINE AND AXIAL FLOW TURBINE - A nozzle box | 09-16-2010 |
20100254808 | MULTI-DIRECTIONAL WIND GUIDE APPARATUS FOR VERTICAL SHAFT MINDMILL - The present invention relates to a vertical shaft aero-generator. An aero-generator has the advantage that it is not influenced by the wind direction, but the resistance in the reverse direction of rotation is a disadvantage thereof. For figuring out this disadvantage, a plurality of dimple panel wind guide apparatuses are mounted around the outer surface of a cylindrical vertical shaft windmill as well as on top and bottom thereof in order to maximally guide the wind coming from various directions including above and below to the rotational direction of the windmill, thereby the efficiency of the vertical shaft aero-generator is increased. The dimple panel wind guide apparatus includes a feature that a great number of dimples are formed on both entire lateral surfaces of the dimple panel so that the resistance may be minimized. | 10-07-2010 |
20100266397 | LIGHTWEIGHT BLOWER - Blowing devices ( | 10-21-2010 |
20100266398 | HP TURBINE VANE AIRFOIL PROFILE - A two-stage high pressure turbine includes a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 10-21-2010 |
20100272564 | MULTI STAGE RADIAL COMPRESSOR - A multistage radial compressor ( | 10-28-2010 |
20100296924 | Guide Vane for a Variable Turbine Geometry - A guide vane, particularly for a turbocharger, has a line of curvature with at least one or more sectors having a discontinuous course. | 11-25-2010 |
20110014039 | TURBINE WITH AXIAL DISCONTINUITY - A turbocharger turbine containing a separate insert affixed within the housing. The insert is of a stamped metal configuration, and forms at least a portion of inlet passageway outer wall. An axial discontinuity is machined into the inlet passageway outer wall, the axial discontinuity being characterized by a size and location to direct airflow away from the blade-gap zone over at least part of the range of flow conditions. The inlet passageway may be either larger or smaller upstream of the axial discontinuity. | 01-20-2011 |
20110033288 | OMNIDIRECTIONAL VERTICAL-AXIS WIND TURBINE - A two-stage, omnidirectional vertical axis wind turbine includes a first chamber in which a plurality of angularly spaced horns guide wind from any side of the wind turbine into a chamber to rotate a first rotor. Wind exiting the first rotor passes through a diverter to produce laminar flow. A fan attached to the shaft intercepts this laminar flow to add additional torque to the shaft. | 02-10-2011 |
20110033289 | Bypass-Type Motor Protecting Device for a Vacuum Cleaner - A bypass-type motor protecting device includes: a casing fitted into a bypass opening in a body housing of a vacuum cleaner and having an inner abutment wall; a seat body having a bypass entry port; a valve body unit movable within the casing relative to the bypass entry port and including a valve disc to be engaged with and disengaged from the seat body, a plunger body having an externally accessible operated head and an axially extending threaded shank, and an abutment member threadedly engaged with the shank such that rotation of the operated head results in a change of an axial distance between the abutment member and the inner abutment wall; and a biasing member disposed to bias the abutment member and the inner abutment wall such that a biasing force thereof is varied in strength by the change of the axial distance. | 02-10-2011 |
20110052386 | METHOD OF WELDING SINGLE CRYSTAL TURBINE BLADE TIPS WITH AN OXIDATION-RESISTANT FILLER MATERIAL - A method for depositing material on a turbine airfoil having a tip wall extending past a tip cap, wherein the tip wall includes a first alloy with a single crystal microstructure. The method includes: depositing a second alloy on at least a portion of the tip wall to form a repair structure, wherein a high temperature oxidation resistance of the second alloy is greater than a high temperature oxidation resistance of the first alloy, and wherein the repair structure has a crystallographic orientation that is substantially the same as a crystallographic orientation of the tip wall. | 03-03-2011 |
20110052387 | NON-AXISYMMETRIC AIRFOIL PLATFORM SHAPING - Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine. | 03-03-2011 |
20110058939 | TURBINE EXHAUST DIFFUSER WITH A GAS JET PRODUCING A COANDA EFFECT FLOW CONTROL - An exhaust diffuser system and method for a turbine engine includes an inner boundary and an outer boundary with a flow path defined therebetween. The inner boundary is defined at least in part by a hub structure that has an upstream end and a downstream end. The outer boundary may include a region in which the outer boundary extends radially inward toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. The hub structure includes at least one jet exit located on the hub structure adjacent to the upstream end of the tail cone. The jet exit discharges a flow of gas substantially tangential to an outer surface of the tail cone to produce a Coanda effect and direct a portion of the exhaust flow in the diffuser toward the inner boundary. | 03-10-2011 |
20110070077 | GAS TURBINE - A gas turbine ( | 03-24-2011 |
20110085901 | SHROUDED WIND TURBINE WITH SCALLOPED LOBES - A shrouded wind turbine comprises an impeller and a turbine shroud surrounding the impeller. The shroud includes alternating inward and outward curving elements that form mixing elements on a trailing edge of the turbine shroud. The inward and outward curving elements have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving elements. This allows for both transverse mixing and radial mixing of air flow through the turbine shroud with air flow passing along the exterior of the turbine shroud. | 04-14-2011 |
20110110774 | Blower Fan - A blower fan includes a housing having a lateral wall defining a compartment. The housing includes an air inlet and an air outlet both in communication with the compartment. An impeller mounted in the compartment includes a hub and blades mounted on the hub. A first plane including opposite first and second end edges in the air outlet is parallel to and spaced from a second plane including a center of the hub. The compartment of the housing includes an air outlet section and a pressure accumulating section on opposite sides of the second plane. The air outlet section is located between the first and second planes. The lateral wall of the housing includes at least one air guiding hole located in the pressure accumulating section. At least one air guiding tube includes an outlet end and an inlet end coupled to the at least one air guiding hole. | 05-12-2011 |
20110116917 | Compressor Stator Vane - A compressor component having a non-linear thickness distribution along the span length is disclosed. By altering the thickness distribution to a non-linear arrangement so as to locally increase airfoil thickness proximate a mid-span location, the natural frequency of the airfoil is increased 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. The present invention also includes a carrier segment or disk fabricated from a material so as to eliminate corrosion with the compressor component. | 05-19-2011 |
20110116918 | METHOD AND MACHINERY WITH COMBINED PARTICLE SEPARATION AND FLOW REGULATION DEVICES - A method for assembling turbomachinery having combined particle separation device and flow regulating device is provided. The turbomachinery includes a casing; a compressor attached to an inside of the casing, the compressor having a shaft supported by bearings; and a cooling system mounted inside the casing and configured to cool the bearings of the compressor with a cooling fluid. The cooling system includes a particle separation device configured to separate particles from the cooling fluid, and a flow regulation device that fluidly communicates with the particle separation device without contacting the particle separation device. The flow regulation device is disposed adjacent to the particle separation device within a wall of the casing. | 05-19-2011 |
20110123325 | SEAL PLATES FOR DIRECTING AIRFLOW THROUGH A TURBINE SECTION OF AN ENGINE AND TURBINE SECTIONS - A seal plate for directing an airflow includes a hub, main pumping vanes, and splitter vanes. The hub has a tubular section and an annular flange section flared outwardly relative to the tubular section to define a flow surface. The main pumping vanes are disposed circumferentially on the flow surface around the annular flange section and each has a canted section located radially inward relative to a straight section and aligned with a flow direction of the airflow. The straight section extends along a first plane including a centerline of the seal plate. The splitter vanes are disposed circumferentially on the flow surface around the annular flange section such that at least one splitter vane is disposed between the straight sections of two adjacent main pumping vanes. Each splitter vane has a length that is less than a length of each of the two adjacent main pumping vanes. | 05-26-2011 |
20110135458 | FLUID TURBINE WITH SHROUD HAVING SEGMENTED LOBES - A shrouded fluid turbine comprises an impeller and a turbine shroud surrounding the impeller. The shroud includes alternating inward and outward curving elements that form mixing elements on a trailing edge of the turbine shroud. The inward and outward curving elements have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving elements. This allows for both transverse mixing and radial mixing of fluid flow through the turbine shroud with fluid flow passing along the exterior of the turbine shroud. | 06-09-2011 |
20110135459 | Continuous-Flow Energy Installation, in Particular a Wind Power Installation - Continuous-flow energy installation having at least one rotor ( | 06-09-2011 |
20110164969 | METHOD FOR PRODUCING A VANE, SUCH A VANE AND A STATOR COMPONENT COMPRISING THE VANE - A method for producing a vane for application in a component in a gas turbine engine includes casting at least one of a vane leading edge part and a vane trailing edge part and connecting the leading edge part and the trailing edge part. | 07-07-2011 |
20110164970 | Stator blade for a turbomachine, especially a stream turbine - The invention relates to a stator blade ( | 07-07-2011 |
20110189007 | FLUID TURBINE - A shrouded fluid turbine comprises an impeller and a turbine shroud surrounding the impeller. The inlet of the turbine shroud is flared. The shroud includes alternating inward and outward curving lobe segments along a trailing edge of the turbine shroud. The inward and outward curving lobe segments have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving lobe segments. This allows for both transverse mixing and radial mixing of air flow through the turbine shroud with air flow passing along the exterior of the turbine shroud. | 08-04-2011 |
20110229317 | HP TURBINE VANE AIRFOIL PROFILE - A two-stage high pressure turbine includes a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 09-22-2011 |
20110236199 | NOZZLE SEGMENT WITH REDUCED WEIGHT FLANGE - A nozzle segment for a gas turbine engine includes a flange which extends from a vane platform, the flange includes a hollow cavity. | 09-29-2011 |
20110236200 | GAS TURBINE ENGINE WITH NON-AXISYMMETRIC SURFACE CONTOURED VANE PLATFORM - A vane segment for a gas turbine engine according to an exemplary aspect of the present disclosure includes an inner vane platform relative an axis, the inner vane platform having a non-axisymmetric surface contour. | 09-29-2011 |
20110243722 | ANTI-ROTATION SLOT FOR TURBINE VANE - A fixed vane section for a gas turbine engine includes an anti-rotation slot that receives a pin for maintaining a desired position while providing for movement encountered during operation. The example anti-rotation slot includes a compound radius on inner surfaces to reduce stresses encountered during operation. | 10-06-2011 |
20110243723 | FAN GUARD - A fan guard includes a bracket, a guide sheet and at least two guide ribs. The bracket defines a vent in the center of the bracket. The guide sheet is located in the center of the vent. The at least two guide ribs interconnect the bracket and the guide sheet. Each guide rib includes a first connecting portion and a second connecting portion connecting the first connecting portion. The first connecting portion and the second connecting portion cooperatively define a first angle therebetween. | 10-06-2011 |
20110255961 | SOLID FEED GUIDE APPARATUS FOR A SOLID FEED PUMP - In one embodiment, a system includes a solid feed pump. The solid feed pump includes a housing, a rotor disposed in the housing, a curved passage disposed between the rotor and the housing, an inlet port coupled to the curved passage, an outlet port coupled to the curved passage, a solid feed guide extending across the curved passage, and multiple discrete contacts distributed along an interface between the solid feed guide and the rotor. | 10-20-2011 |
20110255962 | DIFFUSER HAVING BLADES WITH APERTURES - A diffuser for a mixed flow or centrifugal compressor of a gas turbine. The diffuser includes at least one vane presenting a pressure side, a suction side, and a first flank. The vane includes a plurality of orifices opening out into the suction side and/or the pressure side and communicating with at least one cavity formed in the vane, the cavity extending transversely relative to the vane and opening out into its first flank. The cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank. | 10-20-2011 |
20110274540 | TURBOMACHINE CASING - A turbomachine casing forming a continuous annular ring extending over 360° around a bladed wheel and serving as a propagation medium for rotating waves, each rotating wave being generated by two standing waves of the same frequency, and the casing including at least one longitudinal stiffener at its outer periphery that is dimensioned and positioned in such a manner as to separate the frequencies of the two standing waves of at least one given rotating wave. | 11-10-2011 |
20110280719 | Fan And Shroud Assembly - An axial flow fan assembly includes a plurality of fan blades surrounded by a shroud. The shroud includes an annular first wall which extends radially outwardly, an annular second wall which extends axially and radially outwardly, and an annular third wall which joins the first wall to the second wall. The third wall has a curved cross sectional shape, and has a minimum diameter part which is positioned approximately half-way between the upstream and downstream edges of the fan blades. There is a desired relationship between the radius of curvature of the third wall and the diameter of the fan. There is a desired relationship between the height of the first wall and the diameter of the fan. The fan blades have an upstream edge which is upstream with respect to the first wall. The third wall has a minimum diameter part which is positioned approximately half-way between the upstream and downstream ends of the fan. | 11-17-2011 |
20110280720 | Inner Housing for a Turbomachine - A three-shell steam turbine is provided. The three-shell steam turbine includes an outer housing, an outer inner housing and an inner inner housing, wherein the outer inner housing is arranged around the inner inner housing, in such a way that a cooling steam chamber is formed in between and a flow duct is formed between the outer inner housing and the rotor. | 11-17-2011 |
20110293412 | ANTI-ROTATION PIN RETENTION SYSTEM - A turbine engine vane assembly assembled using an anti-retention pin method can include a vane assembly having a vane supported on a shroud ring and a cavity seal coupled to the vane assembly by a securement mechanism. The cavity seal defines a securement receiving portion through which the securement mechanism is inserted. The securement receiving portion also includes a deformation receiver. The securement mechanism has a deformable rim at a first end and a key at a second end. The securement is rotatable between a first configuration and a second configuration where the key matingly engages the shroud ring and the cavity seal to reduce axial movement of the vane assembly. The deformable rim can be deformed into the deformation receiver to prevent rotation of the securement mechanism and disengagement of the securement mechanism from the vane assembly and cavity seal. | 12-01-2011 |
20110299982 | METHOD FOR REPAIRING A GUIDE BLADE SEGMENT FOR A JET ENGINE - A method for repairing a guide blade segment fashioned as a twin guide blade segment within a guide blade composite element, the guide blades being formed from a nose segment and a rear edge segment, the method having identification, within a guide blade segment, of a non-repairable guide blade to be separated from the guide blade composite structure; separation of a non-repairable guide blade from a one repairable guide blade in a first plane of division; division of at least one separated guide blade in a second plane of division between the nose segment and the rear edge segment; reconditioning of the at least one repairable nose segment and/or rear edge segment; joining of a reconditioned and/or new nose segment to a reconditioned and/or new rear edge segment to form at least one guide blade; and joining of at least two guide blades to form a guide blade segment. | 12-08-2011 |
20110305563 | Wind Turbine Funnel - The wind turbine funnel includes a frame rotatably mounted to support about a rotational axis. The frame includes an inlet having a funnel directing incoming wind towards a turbine wheel disposed adjacent the funnel. The funnel includes an angled upper, main deflector and an optional, angled lower deflector disposed between side panels. The turbine wheel includes a plurality of curved wind blades radiating from the axis of the wheel. The blades are configured to maximize conversion of the wind energy into rotational force for the wheel. The center of gravity of the frame and turbine is disposed behind the rotational axis to permit free rotational adjustment of the frame with respect to wind direction with minimal force. The side panels may include raised sections that function as a rudder. | 12-15-2011 |
20110305564 | LOCAL EXHAUST APPARATUS - A local exhaust system includes a motor provided in an exhaust pipe to generate a rotary drive force when power is applied thereto, in which air is taken in through an intake port and exhausted through the exhaust pipe, a rotor structure disposed on the leading end of the intake port and connected to a drive shaft of the motor, the rotor structure rotating about a central portion of the exhaust pipe, and a plurality of turbulence-generating outer blades for generating a turbulent flow when rotated. Each of the turbulence-generating outer blades is assembled to the outer surface of the rotor structure via an angle-adjusting member in such a fashion that the angle of the turbulence-generating outer blade is adjustable with respect to the direction in which air is taken in through the intake port. | 12-15-2011 |
20110318177 | Turbine housing for an exhaust gas turbocharger and method for producing turbine housing - In the turbine housing for an exhaust gas turbocharger of a drive assembly at least one spiral channel, which can be coupled to an exhaust gas line of the drive assembly is provided A receiving chamber for a turbine wheel to which exhaust gas can be supplied is disposed upstream of the at least one spiral channel. The turbine wheel is disposed in the turbine housing so as to be rotatable about a rotational axis. A guide baffle is arranged fixed to the turbine housing in a transition region between the at least one spiral channel, the guide baffle being connected to the turbine housing by a metal-to-metal joint whereby the guide baffle is connected to the turbine housing in a particular tight manner. | 12-29-2011 |
20120020778 | DIAGONAL FAN - A diagonal fan for gaseous media has a diagonal impeller with a plurality of vanes, which are fastened on a carrier plate, and a guide device, adjoining the diagonal impeller in the axial direction on the outflow side, for increasing the pressure of the medium, with a plurality of guide vanes. The vanes of the diagonal impeller and/or the guide vanes of the guide device are three-dimensionally twisted. By means of an intake unit, the gaseous medium can be directed into the diagonal impeller. The intake unit and/or an exhaust unit, by means of which the gaseous medium can be directed out of the guide device, is, or are, provided as an exchangeable module and can be fastened on the diagonal fan by means of a fastening element. | 01-26-2012 |
20120034078 | IMPELLER AND CENTRIFUGAL COMPRESSOR INCLUDING THE SAME - Provided is an impeller of a centrifugal compressor including: a hub fixed to a rotation shaft; and a plurality of blades extending outward from a center portion of the hub on one surface of the hub, wherein a length of the blade is greater than a straight length between an inlet end of the blade and an outlet end thereof. Assuming that an outlet angle formed along a longitudinal direction of the blade at the outlet end of the blade is β and an inclination angle of the blade from the one surface of the hub at the outlet end of the blade is γ, the following equation is satisfied: 102-09-2012 | |
20120070275 | AIRFOIL FOR ENERGY EXTRACTING SHROUDED FLUID TURBINES - Example embodiments described herein relate an integral and/or multi-piece airfoil and a shrouded fluid turbine having the same. The airfoil can have a generally circumferential body extending circumferentially about a central axis, and can be referred to herein as a “ringed airfoil.” The airfoil can have a front portion defining a leading edge of the airfoil and a rear portion defining a trailing edge of the air foil. A cross-sectional thickness of the front portion can be non-uniform and vary along a mean camber line of the airfoil from the leading edge to a transition area. A cross-sectional thickness of the rear portion can be uniform and constant along the mean camber line of the airfoil from the transition area to the trailing edge of the airfoil. | 03-22-2012 |
20120082542 | STEAM TURBINE ROTOR, METHOD OF MANUFACTURING THE SAME, AND STEAM TURBINE - In one embodiment, a steam turbine rotor has a first and a second rotor, a first and a second flange, a bolt, and a cap nut. The first flange is connected to an end portion of a first shaft of the first rotor and has a first through hole. The second flange is connected to an end portion of a second shaft of the second rotor and has a second through hole. The bolt is inserted through the first and second through holes and has a shaft part, a male screw part disposed on one end of the shaft part, and a projection part disposed on an end portion of the male screw part. The cap nut has a female screw part engaged with the male screw part and a projection through hole which the projection part penetrates. | 04-05-2012 |
20120087787 | TURBOFAN JET ENGINE - There is a turbofan jet engine including an engine core. The engine core includes a fan and a compressor. The engine core includes a combustion chamber and a turbine functionally coupled to the compressor. The engine core includes a nozzle in fluid communication with the turbine. The turbofan jet engine includes a nacelle. The nacelle includes a forward extension proximate the fan and extending forward therefrom. The forward extension is funnel shaped to impart radial momentum to intake air during operation. The nacelle includes a vortex device disposed inside the forward extension and shaped to impart angular momentum to intake air. The vortex device includes a fixed blade extending from the interior of the forward extension and set at a rotational angle. The vortex device is shaped and positioned to direct intake air substantially perpendicular to the blades of the fan. | 04-12-2012 |
20120093637 | Axial Compressor - An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length. | 04-19-2012 |
20120099983 | Torque Balanced, Lift Rotor Module, Providing Increased Lift, With Few or No Moving Parts - A device for continuous torque/anti-torque force balance, except for trim adjustments, of the torque requirements of a single lift rotor while lifting varying load weights and with varying power settings, using a relatively short, cylindrical, vertical duct, flared at the top, air entry end, which flare the lift rotor plane of rotation is parallel to and just below, and is closely contained by the relatively short, cylindrical, vertical duct's inside diameter, and just above a fixed pitch, essentially vertical, array of air foil shaped vanes. In this configuration, lateral lift in an anti-torque rotational direction is generated, in direct proportion to the lift rotor torque requirements, by the lift rotor's rotor wash with swirl air flow component forced interaction with the fixed pitch, essentially vertical, array of air foil shaped vanes to continuously balance torque/anti-torque forces. | 04-26-2012 |
20120114475 | AIR TURBINE STARTER ONE-PIECE AIR EXIT PORT BAFFLE - A one-piece air exit port baffle for containment for an air start turbine includes a circular arc section with a circumferentially corrugated circular arc section and a flange section. The circumferentially corrugated circular arc section has a plurality of openings. The flange section is axially adjacent to the circumferentially corrugated circular arc section and configured for attachment adjacent to an air exit port of an air turbine starter. | 05-10-2012 |
20120114476 | VENTILATOR - A ventilator includes a first casing, a second casing, a fan blade and a flow guider. The second casing is connected to the first casing and forms a flow channel between the first casing and the second casing. The fan blade is disposed between the first casing and the second casing. When the fan blade rotates, an air-flow compression zone and an air-flow decompression zone are formed in the flow channel. The flow guider is formed along a boundary line to the air-flow decompression zone, wherein the boundary line is adjacent to the air-flow compression zone and the air-flow decompression zone. With the ventilator, the air pressure of the ventilator is increased and noise can be controlled. | 05-10-2012 |
20120121402 | CENTRIFUGAL COMPRESSOR DIFFUSER - A system, in certain embodiments, includes a centrifugal compressor diffuser vane including a leading edge, a trailing edge, and a constant thickness section extending between the leading edge and the trailing edge. A radius of curvature of the leading edge and a radius of curvature of the trailing edge vary along a span of the vane. A ratio of a length of the constant thickness section to a chord length of the vane is at least approximately 50%, and the ratio is substantially constant along the span of the vane. | 05-17-2012 |
20120121403 | REMOVABLE THROAT MOUNTED INLET GUIDE VANE - In certain embodiments, a system includes an inlet guide vane assembly. The inlet guide vane assembly includes a plurality of inlet guide vanes disposed in a radial pattern around a central axis and configured to rotate about axes orthogonal to the central axis. The inlet guide vane assembly also includes a plurality of vane shafts, each connected to a respective inlet guide vane and configured to rotate with the respective inlet guide vane about the respective orthogonal axis. The inlet guide vane assembly further includes a drive shaft directly connected to one of the vane shafts and configured to directly cause rotation of the vane shaft to which it is directly connected and to indirectly cause rotation of the remaining vane shafts in the plurality of vane shafts. In addition, the inlet guide vane assembly includes a rotary actuator connected to the drive shaft and configured to cause rotation of the drive shaft. | 05-17-2012 |
20120128478 | CENTRIFUGAL PUMP ASSEMBLY - The invention relates to a centrifugal pump assembly with at least one impeller, with a suction union ( | 05-24-2012 |
20120128479 | DIFFUSOR - The guide device for the diffusor at the compressor impeller outlet of a radial compressor has guide blades with stepped inlet edges. The step is implemented by setting back the hub-side inlet edge. This meridional stepping divides the guide blades into two component blades, of which the first component blade is made longer than the second component blade. The set-back of the inlet edge of the hub-side component blade and the associated superposition of the noise fields which are produced on the front and rear inlet edge of the diffusor leads to improvement of the acoustic properties of the compressor. | 05-24-2012 |
20120128480 | BLADE - The present invention relates to a blade of a turbomachine, in particular an adjustable guide blade or vane of a gas turbine, having at least one thickened area ( | 05-24-2012 |
20120134796 | VOLUTE AND DRAINAGE PUMP - A drainage pump has an impeller, a motor for driving the impeller, and a volute housing the impeller. The volute has an end wall, a side wall, an inlet, and an outlet. The side wall extends from the end wall. The side wall and the end wall cooperatively define a pump chamber. The inner surface of the side wall has at least one interfering surface for mixing of fluid flowing through the volute. | 05-31-2012 |
20120148395 | STEAM TURBINE SINGLET NOZZLE DESIGN FOR BREECH LOADED ASSEMBLY - A steam turbine nozzle airfoil with integral inner and outer sidewalls is engaged with an inner ring and an outer ring in a nozzle assembly. Previous designs required large clearances between radial surfaces to permit simultaneous circumferential loading of the inner and outer sidewall into the inner and outer rings. The inventive arrangement provides for breech loading of the inner sidewall into the inner ring which allows near line-to-line radial contact on the hooks between the rings and the integral sidewalls of the Singlet nozzle airfoil. Tighter radial clearance overcome problems with loose assembly such as movement during welding, gaps leading to stress risers and performance issues associated with nozzle throat control. | 06-14-2012 |
20120171027 | STRUCTURAL LOW-DUCTILITY TURBINE SHROUD APPARATUS - A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; and an annular stationary structure surrounding the shroud segment, where the shroud segment is mechanically coupled to the stationary structure. The stationary structure includes at least one axially-facing bearing surface which is in direct contact with the shroud segment, and the shroud segment is disposed so as to absorb at least one axially-aligned force and transfer the axially-aligned force to the bearing surface. | 07-05-2012 |
20120171028 | VANE WITH SPAR MOUNTED COMPOSITE AIRFOIL - A vane includes a composite airfoil having one or more pockets and one or more spars received therein respectively. The spars extending radially away from a bridge of a vane mount supporting airfoil. The spars may be integrally formed with the bridge. The spars may be adhesively bonded to the composite airfoil within the pockets. A passage may extend between an airfoil base and an airfoil tip. A gas turbine engine annular fan frame includes an annular row of the composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame. | 07-05-2012 |
20120183395 | RADIAL COMPRESSOR DIFFUSER - A radial compressor diffuser for a radial compressor stage includes a flow channel which extends radially outwards and which has a cylindrical inlet cross-section on a first radius which extends radially inwards and a cylindrical outlet cross-section which extends radially outwards. A radial diffuser outlet blade is provided in the region of the outlet cross-section in the flow channel. The outlet blade prevents known disadvantages of traditional bladed diffusers. | 07-19-2012 |
20120195748 | VORTEX PREVENTION DEVICE AND DOUBLE SUCTION VERTICAL PUMP HAVING SUCH VORTEX PREVENTION DEVICE - A vortex prevention device is capable of preventing creation of air entrained vortex and also provides a double suction vertical pump having such a vortex prevention device. The vortex prevention device is used in combination with the double suction vertical pump which is installed in an open channel and has an upper suction opening and a lower suction opening. The vortex prevention device includes a plate member as a vortex prevention structure arranged above the upper suction opening. The plate member is arranged away from the upper suction opening such that a passage is formed between the plate member and the upper suction opening. | 08-02-2012 |
20120201665 | AIR FLOW DEFLECTOR - An air flow deflector comprising (a) a deflector body having an outer surface, the deflector body providing an air passage extending through an inlet, a throat and an outlet, the size of the inlet is greater that the size of the throat; (b) a pair of channels provided between the inlet and the outlet and each of the pair of channels having a venturi profile; and (c) an outlet portion of the air flow deflector provided between the throat and the outlet to provide a gradual transition between the throat and the outlet; wherein the air flow deflector increases an air flow velocity of air entering said inlet. | 08-09-2012 |
20120201666 | STAGGERED MULTI-LEVEL VERTICAL AXIS WIND TURBINE - A staggered multi-level vertical axis wind turbine includes a cage structure including wind directing elements arranged circumferentially about outer edges thereof. Within the cage structure is a rotor including a centrally located shaft orientated along an axis and extending at least from one end of the cage structured to another end. The rotor includes a first rotor level of torque generating elements of a first type coupled to the shaft. The rotor includes a second rotor level of torque generating elements of a second type coupled to the shaft. The rotor includes a third rotor level including torque generating elements of the first type coupled to the shaft. The wind directing elements receive and re-direct wind onto the torque generating elements of the various levels, thereby producing torque and causing the rotor to spin. The rotor is coupled to an electrical generator, which generates clean and renewable energy. | 08-09-2012 |
20120201667 | METHOD AND A DEVICE OF TANGENTIALLY BIASING INTERNAL COOLING ON NOZZLE GUIDE VANE - A deflector for guiding a cooling fluid to a blade device of a turbine is provided. The deflector includes a first opening region with a first opening shape and a second opening region with a second opening shape. The deflector is connectable to a first blade device and to a second blade device in such a way that the cooling fluid is streamable through the first opening region into the first blade device and the cooling fluid is streamable through the second opening region into the second blade device. The first opening shape differs from the second opening shape for achieving a predetermined first mass flow of the cooling fluid into the first blade device and a predetermined second mass flow of the cooling fluid into the second blade device at predetermined installation locations of the first blade device and the second blade device. | 08-09-2012 |
20120207594 | GAS TURBINE ENGINE AIR INTAKE IN A NACELLE - An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle. | 08-16-2012 |
20120213631 | UNFLARED COMPRESSOR BLADE - 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. | 08-23-2012 |
20120213632 | Non-Metallic Vertical Turbine Pump - A non-metallic vertical turbine pump and a method of manufacturing same are provided. In accordance with one embodiment, the vertical turbine pump can include a motor, and a drive shaft coupled to the motor for rotation, a casing with a mixed flow diffuser including a diffuser hub and diffuser vanes that project out from the diffuser hub, and a mixed flow impeller configured to rotatably fit inside the casing, having an impeller hub, impeller vanes, extending from the hub, and a front and a back shroud connected to opposing ends of the impeller vanes. At least one of the mixed flow impeller and the mixed flow diffuser can be made of a non-metallic material and is a singular homogenous component. | 08-23-2012 |
20120213633 | GAS TURBINE ENGINE COMPONENT - A gas turbine engine component includes a ring element and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. At least one of the vanes is made of a composite material. The at least one composite vane is fastened to the ring element. The component further includes first and second wall portions that are fixed in relation to the ring element and arranged on opposite sides of the composite vane. At least a first hole extends through the first wall portion, the composite vane and the second wall portion. The first hole is adapted to receive a first insertion member. The component is arranged such as to, with regard to the first hole, provide a tight fit for the first insertion member in the first wall portion as well as in the composite vane and to provide a loose fit with a radial play in the second wall portion. | 08-23-2012 |
20120219410 | AIRFOIL SHAPE FOR A COMPRESSOR BLADE - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. | 08-30-2012 |
20120219411 | TWO-STAGE CENTRIFUGAL PUMP - The invention relates to a centrifugal pump ( | 08-30-2012 |
20120224954 | AIRFOIL CORE SHAPE FOR A TURBOMACHINE COMPONENT - A turbomachine component includes a compressor stator vane having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape. | 09-06-2012 |
20120224955 | DIFFUSER - A diffuser having a flow path including generally annular regions arranged to direct a flow of fluid with both tangential and axial velocity components. | 09-06-2012 |
20120224956 | PUMP APPARATUS - A pump apparatus includes a drive shaft supported rotatably in a pump body; a power transmission member attached to the drive shaft, and configured to transmit power to the drive shaft; a pump element configured to pressurize and discharge working fluid; a discharge passage formed in the pump body, and configured to introduce the pressurized working fluid discharged from the pump element to an external of the pump body; a control valve configured to control an amount of working fluid to be discharged through the discharge passage to the external, by controlling a movement of a valving element of the control valve on the basis of the pressurized working fluid; and an electromagnetic valve provided between the power transmission member and the control valve, and configured to control the control valve or a fluid pressure acting on the valving element of the control valve based on the pressurized working fluid. | 09-06-2012 |
20120230818 | Airfoil and corresponding guide vane, blade, gas turbine and turbomachine - An airfoil suitable for being arranged in a compressor section of the gas turbine includes a platform, a pressure surface and a suction surface, and a tip region. The tip region is located between the pressure and the suction surface opposite to the platform in respect of the pressure and the suction surfaces, being a distant end of the airfoil in direction along the first direction perpendicular to the platform. The tip region includes a first surface with a first distance to the platform along the first direction, and a second surface with a second distance to the platform along the first direction. The first distance is greater than the second distance and the first surface and the second surface together build a profiled surface. The profiled surface is a ribbed surface. The material of the first surface is deformable to bend away from the rotation direction of the airfoil. | 09-13-2012 |
20120251311 | FUEL PUMP - A fuel pump, including at least one driven impeller made of plastic, which rotates in a pump housing and on the sides having guide blades that each delimit at least one ring of blade chambers, and further having partial ring-shaped channels arranged on both sides in the region of the guide blades in the pump housing, said channels forming delivery chambers with the blade chambers for delivering fuel. An inlet channel leads into the one delivery chamber and the other delivery chamber leads into an outlet channel and the impeller contains carbon fibers embedded in the plastic. | 10-04-2012 |
20120263586 | INLET GUIDE VANE FOR A COMPRESSOR - A compressor assembly ( | 10-18-2012 |
20120263587 | TURBOMACHINE WITH AXIAL COMPRESSION OR EXPANSION - The turbomachine has a ring of radial blades which are connected to an annular end wall. Situated on the end wall upstream of each blade is a deflector wedge with two divergent guide surfaces. The deflector wedge generates pressure-side and suction-side vortices of which the vortices caused by the blade cascade are altered such that the transverse flow and backflow areas on the blade are reduced, and therefore the edge zone losses are decreased. | 10-18-2012 |
20120269622 | TURBINE VANE AND GAS TURBINE - A turbine vane of the invention includes: a plurality of outer shrouds ( | 10-25-2012 |
20120269623 | Guide vane with a winglet for an energy converting machine and machine for converting energy comprising the guide vane - An energy converting machine includes a guide vane. The guide vane includes a guide vane body for guiding a streaming fluid. The guide vane body has a pressure surface and a suction surface, a trailing edge and a leading edge, and a winglet for reducing leakage of the streaming fluid from the pressure surface to the suction surface. The winglet is arranged at a longitudinal end of the guide vane body. The winglet extents from the trailing edge to the leading edge and is arranged at the pressure surface. The winglet is free of protrusions beyond the leading edge and beyond the trailing edge. | 10-25-2012 |
20120282087 | DIAPHRAGM FOR TURBOMACHINES AND METHOD OF MANUFACTURE - A turbine diaphragm assembly is described having an annulus of static blades, each static blade including at least an aerofoil and an outer platform; and an outer diaphragm ring or segments of a ring for holding the annulus of static blades; with confronting edges of the outer platforms and the ring are held by an interference fit when pushed in axial direction into contact with the interference fit designed to withstand the forces on the diaphragm during operation of the assembled turbine. | 11-08-2012 |
20120288365 | METHOD OF REDUCING ASYMMETRIC FLUID FLOW EFFECTS IN A PASSAGE - A method of reducing the fluid flow effects of one or more flow modifiers ( | 11-15-2012 |
20120294713 | Advection-Type Fan - An advection-type fan includes a fan frame, a driving module and an impeller. The fan frame has a first cover portion, a second cover portion and a lateral wall portion arranged between the first and second cover portions, wherein the lateral wall portion has an air inlet and an air outlet. The driving module is received in the fan frame and coupled with the first cover portion. The impeller has a hub and a plurality of vanes. The hub is rotatably coupled with the driving module and the vanes are coupled with the hub. The hub has an air-guiding plane facing the second cover portion. Each of the vanes has a top edge facing the second cover portion. The top edge of each of the vanes is higher than the air-guiding plane of the hub in an axial direction of the hub. | 11-22-2012 |
20120301288 | CHARGING DEVICE - An exhaust gas turbocharging device is disclosed. The turbocharging device comprises a turbine comprising at least one flow guide vane for a medium. The flow guide vane is pivotably mounted on a housing component of the charging device by a bearing shaft seated in a recess of the housing component, wherein the bearing shaft and the recess form at least two bearing locations with different diameters spaced from each other in an axial direction. | 11-29-2012 |
20120301289 | FUEL PUMP - A fuel pump, including a driven impeller, which rotates in a pump housing and on the two sides comprises guide blades that each delimit a ring of blade chambers, and further including partial ring-shaped channels, which are arranged on both sides in the region of the guide blades in the pump housing and which form delivery chambers with the blade chambers for delivering fuel, wherein an inlet channel leads into the one delivery chamber and the other delivery chamber leads into an outlet channel, and mutually opposing blade chambers are connected to each other. The cross-sectional surface of the partial ring-shaped channel arranged on the inlet side decreases toward the end of the partial ring-shaped channel to zero. The region in which the cross-sectional surface decreases extends over an angular region of more than 45°. | 11-29-2012 |
20120308373 | AXIAL FAN ASSEMBLY - A fan assembly includes an axial flow fan between an inlet stator and an outlet stator. The inlet stator has inlet stator blades which extend outwardly from an inner ring. Each inlet stator blade has a downstream edge which has a tangent which is oriented at a first variable angle with respect to a plane which is perpendicular to the fan axis. The first angle increases with increasing distance from the inner support ring. The outlet stator has a plurality of outlet stator blades which extend outwardly from a second inner ring. Each outlet stator blade has an upstream edge which has a tangent which is oriented at a second variable angle with respect to a plane which is perpendicular to the fan axis. The second angle decreases with increasing distance from the inner ring. | 12-06-2012 |
20120308374 | DIFFUSER-GUIDE VANE CONNECTION FOR A CENTRIFUGAL COMPRESSOR - An assembly including a diffuser and an airflow rectifier at an outlet of a centrifugal compressor of a turbine engine, the diffuser being substantially in a shape of a radially positioned double annular disc, and the rectifier being a double toroidal part, arranged as an extension of the double disc of the diffuser and curved such as to divert the airflow in the downstream direction of the engine. The rectifier is attached to the diffuser by a connection positioned immediately adjacent to the contact surface of the two parts and is removable using a standard tool, excluding any other supporting mechanism. | 12-06-2012 |
20120308375 | FAN ASSEMBLY - A fan assembly for creating an air current includes a base having an air inlet and an air outlet, the base housing an impeller and a motor for rotating the impeller to create an air flow passing from the air inlet to the air outlet. The fan assembly further includes a vertically oriented, elongate annular nozzle including an interior passage having an air inlet for receiving the air flow from the base and a mouth for emitting the air flow, the nozzle defining an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. | 12-06-2012 |
20120321455 | TURBOCHARGER HOUSING - A turbocharger housing is split lengthwise and has two housing halves, which in the assembled state sectionally form a bearing housing, a turbine housing, and a compressor housing. The turbocharger housing contains at least one fluid chamber, which is arranged in the bearing housing and/or in the turbine housing and/or in the compressor housing of at least one of the two housing halves. The fluid chamber contains a plurality of raised webs, which are disposed to influence the fluid flow. | 12-20-2012 |
20120328429 | Ni-BASED ALLOY, AND TURBINE ROTOR AND STATOR BLADE FOR GAS TURBINE - A Ni-based alloy including chromium, cobalt, aluminum, titanium, tantalum, tungsten, molybdenum, niobium, carbon, and boron, the balance being nickel and incidental impurities, is provided. The alloy has an alloy composition of, on the basis of mass percent, chromium: 13.10% to 16.00%, cobalt: 8.00% to 12.50%, aluminum: 2.30% to 3.50%, titanium: 4.80% to 5.50%, tantalum: 0.40% to less than 1.00%, tungsten: 4.50% to 6.00%, molybdenum: 0.10% to 1.50%, niobium: 0.60% to 1.70%, carbon: 0.01% to 0.20%, boron: 0.005% to 0.02%, and the balance: nickel and incidental impurities. | 12-27-2012 |
20130004308 | FAN ASSEMBLY - A fan assembly includes a rack, a shield, and a fan. The rack defines a first vent opening and a second vent opening aligned with the first vent opening. The shield is mounted in the rack and aligned with the first vent opening. The shield defines a frame opening corresponding to the first vent opening. A plurality of shielding pieces are pivotally mounted in the frame opening and adapted to use gravity to shield the frame opening. The fan is mounted in the rack and aligned with the second vent opening and the shield. The fan generates air flows flowing through air passages between each adjacent two of the plurality of shielding pieces, and that the plurality of shielding pieces are rotated by the air flows. | 01-03-2013 |
20130004309 | PROTECTIVE INTERNAL COATINGS FOR POROUS SUBSTRATES - A material contains open pores in which the channels and pores that are internally coated with at least one layer of phosphorus-containing alumina. Such material is formed by infiltrating a porous material one or more times with a non-colloidal, low-viscosity liquid coating precursor, drying, and curing the coating precursor to form a phosphorus-containing alumina layer within pores of the material. | 01-03-2013 |
20130017080 | FLOW DIRECTING MEMBER FOR GAS TURBINE ENGINE - In a gas turbine engine, a flow directing member includes a platform supported on a rotor, a radially facing endwall, at least one axial surface extending radially inwardly from a junction with the endwall, an airfoil extending radially outwardly from the endwall, and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface and has radially inner and outer groove ends. The outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. The groove further includes a first groove wall extending from the inner groove end to the outer groove end, and a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end. | 01-17-2013 |
20130017081 | SYSTEM FOR ENHANCED RECOVERY OF TANGENTIAL ENERGY FROM AN AXIAL PUMP IN A LOOP REACTOR - A loop reactor axial pump system improves conversion of tangential to axial flow of a flowing slurry by attaching a straight impeller section to the inlet of an elbow section. A pump shaft extends rotatably from the elbow through guide vanes located in the impeller section, so that flow from an impeller mounted on the shaft passes through the guide vanes before entering the elbow. When the impeller section is detached, the guide vanes have “see through” access from both ends, thereby allowing the guide vanes to be longer and/or more curved than in the prior art. Guide vanes can be straight or curved, and can have inlet angles approximating the absolute flow angle of the fluid, and/or outlet angles approximating 0 degrees. Additional guide vanes can be included in the elbow. Additional straight pipe sections containing only guide vanes can be included between the impeller section and the elbow. | 01-17-2013 |
20130028722 | System and Method for Improving Turbine Efficiency using a Frame and Shroud System - A system and method for improving turbine efficiency using a frame and shroud system is described herein. Specifically, a shroud system can comprise a frame comprising a base and a substantially vertical support structure, said substantially support structure having a top portion and a bottom portion, wherein said bottom portions connect to a base. In another embodiment, the shroud system can also comprise an upper wind shroud connected to said top portion of said support structure, wherein said upper wind shroud is angled between thirty degrees and seventy-five degrees, further wherein a front portion of said wind shroud extends higher than a rear portion of said wind shroud. | 01-31-2013 |
20130028723 | System and Method for Generating Electrical Power Using a Shrouded Turbine System - A system and method for generating electrical power using a shrouded wind turbine system. Specifically, a shrouded wind turbine system can comprise a frame, a turbine mounted to said frame, wherein said turbine comprises a hub, a plurality of blade mounts connected to said hub, said hub rotatable, such that during said rotation said blade mounts move toward a turbine rear when above said hub and toward a turbine front when below said hub. In another embodiment, the shrouded wind turbine system can also comprise a plurality of blades, each connected to a unique one of said blade mounts, and an upper wind shroud comprising a front and a rear, said upper wind shroud front mounted above said turbine front and said upper wind shroud rear mounted above said turbine rear, further wherein said upper wind shroud front is mounted higher than said upper wind rear. | 01-31-2013 |
20130028724 | AXIAL-RADIAL TURBOMACHINE - Axial-radial flow machine having an axial portion with at least one axial stage, a radial portion with at least one radial stage, a housing having an interior space with a dividing wall extending in a radial direction dividing the housing in an axial direction into a first partial space in which the axial portion is received and a second partial space in which the radial portion is received, and a shaft that extends in axial direction through the interior space and through the dividing wall and on which impellers of the axial portion and of the radial portion are received. A radial gap is formed between the dividing wall and a fluid guiding element of the radial portion. The fluid guiding element is axially fixed to the housing so as to be adjacent to the dividing wall. A plurality of fixing units which are distributed in circumferential direction are arranged in the radial gap, each of which fixing units axially fixes the dividing wall to the fluid guiding element. | 01-31-2013 |
20130028725 | Resurfaced Wicket Gate and Methods - A method for refurbishing wicket gates by applying a sheet material to at least a portion of the vane surface of the wicket gate, thus forming a new face. This sheet material may be applied by wrapping the sheet material around the vane surface. The method may further include applying sheet material to the end surfaces of the wicket vane. If end material is applied, it may be sealed to the sheet material of the vane surface. | 01-31-2013 |
20130028726 | FLOW STRAIGHTENER DEVICE FOR TURBOMACHINE - A flow straightener device for a turbomachine including an inner shell ring and an outer shell ring surrounding the inner shell ring, at least one out of the inner shell ring and outer shell ring having first orifices; at least two flow straightener vanes each including, at least at one same first end, an attachment platform having second orifices positioned facing the first orifices; the at least two vanes being assembled with at least one of the inner shell ring and outer shell ring by at least one first device of attachment introduced into the first orifices and the second orifices. The flow straightener device includes a covering platform covering the at least one first device of attachment. | 01-31-2013 |
20130028727 | GAS TURBINE AND TURBINE STATIONARY BLADE FOR SAME - A gas turbine engine and a turbine stator assembly which is capable of being cooled effectively with a small amount of air. The stator assembly comprises a stator vane disposed to be exposed to a combustion gas passage. The stator vane comprises a cooling passage defined therein. The cooling passage is disposed on an upstream of the gas turbine engine and extending in a radial direction with respect to a central axis of the gas turbine engine. The stator vane also has an inlet communicated to a radially outward end of the cooling passage. The stator vane further has an adjustment member secured to the stator vane so that it covers the inlet. The adjustment member has two apertures for guiding a cooling air radially inwardly through the inlet into the cooling passage. The two apertures are spaced away from each other along a camber line of the stator vane. | 01-31-2013 |
20130034434 | VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A vane assembly for a gas turbine engine includes a first vane and a second vane. The first vane and the second vane include an inner platform, an outer platform and an airfoil that extends between the inner platform and the outer platform. The first vane and the second vane are attached at least at one of their inner platforms or their outer platforms with a first attachment mechanism and a second attachment mechanism. | 02-07-2013 |
20130034435 | VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A vane assembly for a gas turbine engine includes a first platform, a second platform, and an airfoil that extends radially across an annulus between the first platform and the second platform. The airfoil is centered relative to a centerline axis of the second platform and is offset relative to a centerline axis of the first platform. | 02-07-2013 |
20130039754 | VERTICAL DOUBLE-SUCTION PUMP HAVING BENEFICIAL AXIAL THRUST - Apparatus, including a vertical double-suction pump, is provided featuring a pump casing and a double suction impeller arranged therein on a shaft. The pump casing has a pump casing wall. The double suction impeller has upper and lower shrouds with metal rims configured to form upper and lower isolating annuli between the double suction impeller and the wall of the pump casing in order to impede a recirculation flow from an impeller discharge to be able to act of the upper and lower shrouds and create a controlled axial thrust load from differentiated hydraulic pressure on the upper and lower shrouds. The upper and lower isolating annuli may also be geometrically varied between the upper and lower shrouds of the double suction impeller to create a pressure differential in a direction parallel to an axis of rotation of the double suction impeller. | 02-14-2013 |
20130045096 | REMOVABLE MASK FOR A TURBOMACHINE BLADE OR DISTRIBUTOR SECTOR PLATFORM - A removable mask for a platform or a nozzle sector of a turbine engine blade, the blade or sector configured to be covered in an electrolytic deposit, the mask including a mechanism to engage on the platform and a mechanism to cover outer surfaces of the platform that are not to be covered by the electrolytic deposit. | 02-21-2013 |
20130058775 | CATCHER RING ASSEMBLY - A catcher ring assembly ( | 03-07-2013 |
20130064661 | AEROFOIL ASSEMBLY - This invention relates to a stator aerofoil for a gas turbine engine, comprising: a body portion; at least one panel which forms at least part of one of either the pressure or section surface of the aerofoil; at least one internal chamber which is bounded by the body portion and panel; and, at least one elastomeric component within the at least one internal chamber, wherein the elastomeric component at least partially defines a cell within the internal chamber, wherein the cell is in fluid communication with the exterior of the aerofoil. | 03-14-2013 |
20130071239 | TURBINE NOZZLE FOR AIR CYCLE MACHINE - A turbine nozzle for an air cycle machine includes a base with a multiple turbine vanes which each extend for a vane height H, a throat width W defined between each of the multiple of turbine vanes, wherein a ratio W/H is 0.101-0.112. | 03-21-2013 |
20130084174 | STRUT RODS FOR STRUCTURAL GUIDE VANES - A reinforced structural guide vane system includes an outer casing; a center body within the outer casing; a plurality of structural guide vanes extending between and connected to the center body and the outer casing; and a plurality of strut rods extended between and connected to the outer casing and to the center body. | 04-04-2013 |
20130084175 | Stator for Progressive Cavity Pump/Motor - A stator for a progressive cavity pump or motor includes a stator housing and a stator thread made of a material moulded within the housing. The stator housing includes an outer tube and an inner anchor element within. The anchor element has radially disposed apertures and is spaced from outer tube. To fix the anchor element in the outer tube, the axial end faces of the anchor element each have a first set of protrusions and indentations around the circumference thereof. Two end caps of the housing are fixed at the end faces of the outer tube. Each end cap is provided with an interconnecting part having a second set of protrusions and indentations. The first and second sets of protrusions and indentations interengage to mechanically fix the anchor element axially and radially within the outer tube. | 04-04-2013 |
20130108430 | FEATHER SEAL SLOT | 05-02-2013 |
20130108431 | FAN ASSEMBLY | 05-02-2013 |
20130108432 | AIRFLOW-STRAIGHTENING STRUCTURE FOR THE NACELLE OF AN AIRCRAFT ENGINE | 05-02-2013 |
20130115072 | ALLOYS FOR BOND COATINGS AND ARTICLES INCORPORATING THE SAME - In an exemplary embodiment, a high temperature oxidation and hot corrosion resistant MCrAlX alloy is disclosed, wherein M comprises cobalt and X comprises, by weight of the alloy, from about 0.001 percent to less than 0.19 percent yttrium. In these alloys, X may also optionally include silicon, including, by weight of the alloy, up to about 1.5 percent. In another exemplary embodiment, a coated article is disclosed. The coated article includes a substrate having a surface. The article also includes a bond coat disposed on the surface. The bond coat comprises a high temperature oxidation and hot corrosion resistant MCrAlX alloy, wherein M comprises cobalt and X comprises, by weight of the alloy, from about 0.001 percent to less than 0.19 percent yttrium. | 05-09-2013 |
20130115073 | NACELLE COVER - For a wind turbine, an electromagnetically shielding nacelle cover is formed of a composite material which can comprise, for example, an outer layer made of a fiber material or fiber mats such as glass fiber mats and an interposed foam layer. A conductor layer, for example a mesh, a woven fabric or a coating made of conductive material is integrated between the fiber layers of the composite material to provide electromagnetic shielding of the nacelle. The conductor layer is also connected, or can be connected, directly or indirectly, to at least one conductive structure that is applied to the outside of the nacelle cover. | 05-09-2013 |
20130121822 | ANTI-RELIEF FAN FRAME BODY STRUCTURE - An anti-relief fan frame body structure includes a frame body and multiple anti-relief sections. The frame body has a receiving space and a shaft seat received in the receiving space. The frame body further has multiple flow guide members extending from a circumference of shaft seat to an inner circumference of the frame body to connect with the inner circumference of the frame body. The anti-relief sections are disposed on the inner circumference of the frame body between the flow guide members to increase the performance of the fan. | 05-16-2013 |
20130121823 | CHROMIUM ALLOY - A hypereutectic chromium alloy consisting of 9 to 12 at % tantalum, 4 to 15 at % silicon, 0 to 7 at % molybdenum, 0 to 7 at % aluminium, 0 to 7 at % titanium, 0 to 5 at % rhenium, 0 to 2 at % silver, 0 to 2 at % hafnium, 0 to 2 at % lanthanum, 0 to 2 at % cerium, 0 to 2 at % yttrium and the balance chromium and incidental impurities. The hypereutectic chromium alloy has good oxidation resistance and good fracture toughness. The chromium alloy may be used to make gas turbine engine turbine blades, turbine vanes, turbine seals, combustion chamber tiles, exhaust nozzle segments or steam turbine components. | 05-16-2013 |
20130129497 | EXHAUST-GAS TURBOCHARGER - The invention relates to an exhaust-gas turbocharger ( | 05-23-2013 |
20130136592 | TURBINE NOZZLE AIRFOIL PROFILE - A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
20130142639 | APPARATUS AND METHOD FOR THE FORMING OF TURBINE VANE COVER PLATES - A method is provided for reconditioning a turbomachine vane cover plate, by a forming apparatus. The vane having a mounting portion, an airfoil extending radially outward therefrom and a vane head connected to the airfoil. The vane also having a cover plate connected to the vane head, bulged in a direction opposite to the root. In a first analysis step, dimensions of the vane in relation to the cover plate are determined in respect of predefined reference points. If, thereafter, forming of the cover plate seems necessary and possible based on comparison of measurement values from the analysis step with predefined dimension values, the bulged cover plate is formed, at least essentially pressed smooth, by pressing by the forming apparatus in a forming step. After the forming step, the cover plate is re-treated in one or more follow-up steps. An apparatus is also provided for carrying out the method. | 06-06-2013 |
20130149129 | VARIABLE GEOMETRY TURBOCHARGER - An exhaust nozzle | 06-13-2013 |
20130149130 | Fan Hub Frame for Double Outlet Guide Vane - A fan hub frame comprises a circular hub having an opening extending axially wherein an engine core is capable of being positioned, the circular hub having a radially outer surface, the radial outer surface having a plurality of cradles, each of the cradles having a lower surface and fillets disposed between the lower surface and upwardly extending sidewalls, the cradles capable of receiving a double outlet guide vane. | 06-13-2013 |
20130149131 | SURROUND FOR A VERTICAL AXIS WIND TURBINE - A surround for housing a wind turbine directs and concentrates wind from any direction toward the wind turbine. The surround can be formed from an upper apron and a lower apron, each having three or more sides, typically four sides. A fin can be disposed between the upper and lower aprons and extend from a corner thereof toward a central region. The wind turbine can be disposed in the central region. Openings formed on each side of the surround are defined by the upper and lower aprons and the two fins extending from each corner on that side. The openings can deliver wind, from any direction, toward the wind turbine. The upper and lower aprons may angle inward to further concentrate and direct wind toward the wind turbine. | 06-13-2013 |
20130149132 | TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly including a casing adapted to encase an aerofoil structure, the aerofoil structure having a tip, a leading edge and a trailing edge, the casing substantially surrounding the tip of the aerofoil structure, wherein the casing has a set-back portion extending from a position in the region of the leading edge or the trailing edge of the aerofoil structure part way towards a position in the region of the respective other edge and set back from the remainder of the casing away from the aerofoil structure, such that the set-back portion permits a flow over a corresponding portion of the tip of the aerofoil structure. | 06-13-2013 |
20130156570 | WIND COLLECTION APPARATUS - A wind collection apparatus includes an outer tube and an inner tube assembly. The outer tube has a front end and a rear end. The inner tube assembly is installed in the outer tube and has an inner channel and an outer channel. An air-guiding channel is formed between an outer circumferential wall of the inner tube assembly and an inner circumferential wall of the outer tube. The inner channel has two openings. One of the openings is located at the front end and the other one of the openings is located at the rear end. The outer channel is in communication with the inner channel and the air-guiding channel at two ends of the outer channel. | 06-20-2013 |
20130170973 | MIXING SYSTEM FOR AN EXHAUST GASES AFTER-TREATMENT ARRANGEMENT - A mixing system includes a pipe having a longitudinal axis, in which exhaust gases can flow in a flow direction, a nozzle designed to inject a fluid inside the pipe from an injection inlet arranged in the pipe wall, according to an injection direction, a first mixing device positioned inside the pipe upstream from the injection inlet, the first mixing device including a peripheral portion including blades capable of creating a peripheral swirl along the pipe wall, and a central portion designed to create substantially no turbulence, and a second mixing device positioned inside the pipe downstream from the injection inlet, the second mixing device including a central portion including blades capable of creating a swirl inside the pipe. | 07-04-2013 |
20130170974 | PUMPING ELEMENT DESIGN - A pumping element includes a blade ( | 07-04-2013 |
20130170975 | FIXED VANE-TYPE TURBOCHARGER - The present invention relates to a fixed vane-type turbocharger provided with a fixed vane ( | 07-04-2013 |
20130170976 | VTG CARTRIDGE OF AN EXHAUST-GAS TURBOCHARGER - A VTG cartridge ( | 07-04-2013 |
20130177409 | ROTOR FOR A PUMP, PRODUCED WITH A FIRST ELASTIC MATERIAL - The invention relates to a rotor for a pump, having at least one blade, the rotor being able to be actuated to rotate about an axis of rotation in order to convey a fluid in the axial or radial direction, the rotor being able to be deformed reversibly elastically in the radial direction between a first, radially compressed state and a second, radially expanded state which the rotor adopts without the effect of external forces, and a third state of the rotor being provided in which, in pumping operation under fluid loading, the rotor is deformed from the first state to beyond the second state. | 07-11-2013 |
20130177410 | CASING FOR AN AIRCRAFT TURBOFAN BYPASS ENGINE - A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts. | 07-11-2013 |
20130183149 | HOUSING-SIDE STRUCTURE OF A TURBOMACHINE - A housing-side structure of a turbomachine, in particular of a gas turbine, including an in particular segmented jacket ring ( | 07-18-2013 |
20130189095 | TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly includes a first casing element, located radially outward of one or more rotating aerofoil elements of a turbomachine, and a second casing element, located radially distal to the first element. A void is provided at a first end of the first element, between radially proximal faces of the first and second elements. The first end of the first element is located against a corresponding first end of the second element by an energy absorbing element. The first element includes a cantilever, arranged in a region extending along the first element from the first end with a pivot axis at its mid-portion. Release of one of the rotating aerofoil elements, resulting in impact with the first element, further results in the cantilever bending into the void between the first and second elements, enabling the rotating aerofoil element to be trapped within the casing assembly. | 07-25-2013 |
20130189096 | Pollutants Collecting Pump for Water Surface - A pollutant collecting pump for water surface comprises a power device ( | 07-25-2013 |
20130195640 | DUAL-FLOW TURBOMACHINE FOR AIRCRAFT, INCLUDING STRUCTURAL MEANS OF RIGIDIFYING THE CENTRAL CASING - A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled. | 08-01-2013 |
20130202427 | METHODS FOR THE CONTROLLED REDUCTION OF TURBINE NOZZLE FLOW AREAS AND TURBINE NOZZLE COMPONENTS HAVING REDUCED FLOW AREAS - Embodiments of a method for controllably reducing of the flow area of a turbine nozzle component are provided, as are embodiments of turbine nozzle components having reduced flow areas. In one embodiment, the method includes the steps of obtaining a turbine nozzle component having a plurality of turbine nozzle flow paths therethrough, positioning braze preforms in the plurality of turbine nozzle flow paths and against a surface of the turbine nozzle component, and bonding the braze preforms to the turbine nozzle component to achieve a controlled reduction in the flow area of the turbine nozzle flow paths. | 08-08-2013 |
20130202428 | METHOD FOR ATTACHING THE COVER OF A CENTRIFUGAL COMPRESSOR OF A TURBINE ENGINE, COMPRESSOR COVER IMPLEMENTING SAME AND COMPRESSOR ASSEMBLY PROVIDED WITH SUCH A COVER - An attachment arrangement at a middle of a cover having an elastically deformable portion. The cover includes a concave shell including an inner surface spaced apart from the compressor including an impeller including blades by an attachment. The attachment includes one connection end at the middle of the shell, another end attached to a casing of the turbine engine, and an axisymmetric diaphragm having a generally frusto-conical configuration having an arm profile coupled to the end for attachment to the casing by a double-elbow joint having right and obtuse angles when in a rest position. The distance between the inner surface of the shell and upper edges of the blades can be held constant during operation with minimum clearance adjustment. The cover can be moved such that clearance between the cover and blades of the compressor impeller remains substantially constant and as low as possible. | 08-08-2013 |
20130209247 | SIDE CHANNEL BLOWER, IN PARTICULAR A SECONDARY AIR BLOWER FOR AN INTERNAL COMBUSTION MACHINE - A side channel blower includes a housing comprising a substantially tangential outlet. A housing cover comprises an axial inlet. At least one conveying duct is configured so that the axial inlet fluidly communicates with the outlet. An impeller is driven by a drive unit. The impeller is rotatably supported in the housing and comprises conveying blades which cooperate with the at least one conveying duct. An interruption region is arranged between the outlet and the axial inlet. The interruption region comprises a radially limiting wall and interrupts the at least one conveying duct in a circumferential direction. A first recess is arranged in the radially limiting wall of the interruption region downstream of the outlet. Further recesses are arranged in the interruption region before the axial inlet and after the outlet. A smallest distance between the further recesses is 0.5 to 3 times a distance between two conveying blades. | 08-15-2013 |
20130224007 | MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE TO INTRODUCE A RADIAL VELOCITY COMPONENT INTO AN AIR FLOW DISCHARGED FROM A COMPRESSOR OF THE MID-SECTION - A midframe portion ( | 08-29-2013 |
20130224008 | NANO-METAL COATED VANE COMPONENT FOR GAS TURBINE ENGINES AND METHOD OF MANUFACTURING SAME - A method of manufacturing a vane component of a gas turbine engine is described, and includes forming a core of the vane component using a rapid manufacturing process, and applying a coating of nanocrystalline metal onto the core, the nanocrystalline metal fully encapsulating the core and defining an outer structural surface of the vane component. | 08-29-2013 |
20130224009 | MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH A RADIAL AIR FLOW DISCHARGED FROM THE COMPRESSOR SECTION - A midframe portion ( | 08-29-2013 |
20130243586 | COMPRESSOR INLET MANIFOLD FOR A GAS TURBINE ENGINE - A compressor inlet manifold for directing air from a radial airflow inlet into an axial compressor inlet of a compressor of a gas turbine engine is disclosed. The compressor inlet manifold provides air flow to the compressor with reduced distortion to the compressor which enables the required design surge margin to be reduced, thereby increasing gas turbine engine efficiency. The improved air flow has reduced distortion, turbulence and unsteadiness. The compressor inlet manifold body may have at least one annular opening extending axially downstream from an upstream wall. Air flow into the compressor inlet manifold may be conditioned with one or more of a flow improvement projection extending radially inward relative to other aspects of a compressor inlet outer wall, a conically shaped inner sidewall, and a baffle positioned at an acute angle relative to an axis aligned with a radially inward air flow. | 09-19-2013 |
20130243587 | TURBINE VANE OF STEAM TURBINE AND STEAM TURBINE - The invention includes vane members that have a space formed therein and a plate spring member that is disposed inside the space of the vane members and elastically contacts inner surfaces of the vane members. The plate spring member includes a positioning portion, an elastic contact portion, and a connection portion. The elastic contact portion is divided into plural numbers in the length direction of the vane members. As a result, in the invention, the elastic contact portion elastically contacts the inner surfaces of the vane members without any partial contact throughout the entire surface thereof. Accordingly, the elastic contact area between the elastic contact portion and the inner surfaces of the vane members is widened, so that self-excited vibration generated in a turbine vane may be reliably suppressed. | 09-19-2013 |
20130251517 | GROMMET FOR GAS TURBINE VANE - A vane assembly for a gas turbine engine includes an annular shroud having openings therein and a plurality of vanes extending radially from the shroud and each having an extremity received within one of the openings. A grommet is positioned within each opening for shielding the vane extremity from the annular shroud. The grommet includes an annular protrusion for providing sealing between the opening and the vane extremity, and an annular restraint element adjacent the protrusion for retaining the vane in place relative to the shroud. | 09-26-2013 |
20130251518 | CONNECTOR ASSEMBLY FOR VARIABLE INLET GUIDE VANES AND METHOD - A connector assembly for variable inlet guide vanes in a compressor case of a gas turbine engine comprises an annular case insert having a plurality of circumferentially distributed open-ended receptacles. The annular case insert is sized so as to be received inside a compressor case, with the plurality of circumferentially distributed open-ended receptacles being in register with holes in the compressor case. Bushings have an outer diameter sized to be received in a respective one of the receptacles of the annular case insert, and an inner diameter adapted to receive a connector portion of a vane. Sets of the bushing and the connector portion of a vane in one of the receptacles forming a rotational joint. A method for installing vanes in a compressor case is also provided. | 09-26-2013 |
20130251519 | TURBOJET CASING AND TURBOJET RECEIVING SUCH CASINGS - A turbojet casing adapted to receive a plurality of vanes, the casing including attachment means ( | 09-26-2013 |
20130259671 | SYSTEM FOR DRAWING SOLID FEED INTO AND/OR OUT OF A SOLID FEED PUMP - A system includes a solid feed pump. The solid feed pump includes a housing, a rotor disposed in the housing, a curved passage disposed between the rotor and the housing, a solid feed inlet coupled to the curved passage, a solid feed outlet coupled to the curved passage, and a rotatable sleeve configured to rotate to actively draw solid feed into the solid feed inlet or out of the solid feed outlet. | 10-03-2013 |
20130259672 | INTEGRATED INLET VANE AND STRUT - A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length. | 10-03-2013 |
20130259673 | VANE SEGMENT AND AXIAL-FLOW FLUID MACHINE INCLUDING THE SAME - A vane segment according to the present invention includes: an outer connection member connecting a plurality of vanes; positioning jigs for positioning end vanes located at both ends, of the plurality of vanes; and radial restriction sections which restrict the outer connection member so as to be relatively immovable to an outer side in a radial direction of a vane ring, wherein: each of the plurality of vanes has a vane main body and an outer shroud; grooves are formed in the outer shrouds; openings into each of which the positioning jig is inserted are formed in portions of the outer connection member; holes into each of which the positioning jig inserted in the opening is inserted are formed in bottoms of the grooves of the two end vanes; and at least one of the positioning jigs is an eccentric positioning jig. | 10-03-2013 |
20130259674 | INSULATOR FOR STATOR ASSEMBLY OF BRUSHLESS DC MOTOR - An insulator for a stator assembly includes at least a first insulator adapted to be mounted to the stator core and structured to insulate the stator core from the coils. The at least one insulator includes structure to perform at least one additional function. For example, the structure may include a support member to support and/or locate the PCBA on the stator core, a wire guide to guide cross-over wires that form a connection between coils, and/or positioning structure to precisely position the PCBA with respect to the coils. | 10-03-2013 |
20130266434 | Impeller and Regenerative Blower - A regenerative blower is disclosed with a rotating impeller that includes a hub that includes a main body and a tapered outer periphery or volute that extends around the main body of the hub. The volute has a wide base that extends to a tapered volute tip. A plurality of vanes are spaced apart along the main body of the hub and intersect the volute. Each vane has a base coupled to or integral with the main body of the hub and a distal end extending radially away from the hub. Each vane has a downstream side and an upstream side. The downstream sides are concave and the upstream sides are convex. Each vane may also include a pair of side edges that are beveled inwardly towards the volute as the side edges extend from the downstream side of the vane to the upstream side of the vane. | 10-10-2013 |
20130266435 | TURBINE SHROUD ASSEMBLY AND METHOD OF FORMING - A turbine shroud assembly includes an inner shroud portion comprising a body portion having a first circumferential edge, and a discourager extending circumferentially past the first circumferential edge of the body portion, wherein the discourager is integrally formed with the inner shroud portion. | 10-10-2013 |
20130266436 | HOUSING STRUCTURE OF EXHAUST GAS TURBOCHARGER - A casing treatment | 10-10-2013 |
20130266437 | COMPRESSOR GUIDE-VANE STAGE FOR A TURBINE ENGINE - A compressor guide-vane stage for a turbine engine, the stage comprising two coaxial shrouds, respectively an inner shroud ( | 10-10-2013 |
20130266438 | RING AIRFOIL WITH PARALLEL INNER AND OUTER SURFACES - A ring airfoil with a voluminous leading edge region, an intermediate region, a trailing edge region including a flap. The ringed structural leading edge region combined with a rigid trailing edge region having intermediate discrete support portions extending therebetween provides sufficient rigidity to support the flap on the trailing edge region while using a membrane intermediate surface to form a portion of the intermediate region of the airfoil. | 10-10-2013 |
20130266439 | FLUID TURBINE WITH VORTEX GENERATORS - The present disclosure relates to fluid turbines having a turbine shroud assembly formed with mixing elements (e.g., both inwardly and outwardly curving elements) having airfoil cross sections. These airfoils form ringed airfoil shapes that provide a means of controlling the flow of fluid over the rotor assembly or over portions of the rotor assembly. The fluid dynamic performance of the ringed airfoils directly affects the performance of the turbine rotor assembly. The mass and surface area of the shrouds result in load forces on support structures. By delaying or eliminating the separation of the boundary layer over the ringed airfoils, boundary layer energizing members (e.g., vortex generators, flow control ports) on the ringed airfoils increase the power output of the fluid turbine system and allow for relatively shorter chord-length airfoil cross sections and therefore reduced mass and surface area of the shroud assemblies. | 10-10-2013 |
20130280059 | AIRFOIL HAVING TAPERED BUTRESS - An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first sidewall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. At least one of the first side wall and the second side wall includes at least one longitudinally elongated buttress that tapers longitudinally. The at least one longitudinally elongated buttress defines an increased thickness of, respectively, the first side wall or the second sidewall. The at least one longitudinally elongated buttress projects partially across the cavity toward the other of the first side wall or the second sidewall. | 10-24-2013 |
20130287561 | PUMP - A liquid pump has a rotor in a pump housing which has a pump chamber, a pump base, a pump-chamber wall and a cover. The rotor rotates just above the pump base, the pump-chamber wall being provided around the outside of and slightly spaced apart from the rotor and having a heating means thereon. An inlet to the rotor is provided centrally in the axial direction towards the rotor and an outlet from the pump housing is provided externally at the periphery of the pump-chamber wall. Blade-like guiding elements which are integrally injection-moulded thereon are arranged on the pump base, radially outside the impeller. | 10-31-2013 |
20130287562 | GUIDE VANE ATTACHMENT STRUCTURE AND FAN - A guide vane attachment structure including a first fitting portion formed in a vane joint surface of a guide vane, a support member whose constituent material is a metal is integrally connected to a fan frame, and a second fitting portion to be fitted to the first fitting portion formed in a support joint surface of the support member. | 10-31-2013 |
20130294904 | METHOD OF REPAIRING A TURBINE COMPONENT - A method of repairing a turbine component having an array of partitions is provided and includes machining one or more partitions of the array to remove trailing edge sections thereof, fabricating one or more replacement inserts, respectively locating the one or more replacement inserts in the one or more machined partitions and substantially simultaneously brazing the one or more replacement inserts to the one or more machined partitions. | 11-07-2013 |
20130302156 | FAN - A fan casing includes an impeller housing, a mixed-flow impeller located within the impeller housing, and a motor for driving the impeller. The impeller includes a hub connected to the motor, and a plurality of blades connected to the hub, each blade comprising a leading edge located adjacent the air inlet of the impeller housing, an inner side edge connected to and extending partially about the outer surface of the hub, an outer side edge located opposite to the inner side edge, and a blade tip located at the intersection of the leading edge and the outer side edge. The leading edge comprises an inner portion located adjacent the hub, and an outer portion located adjacent the blade tip, and wherein the inner portion is swept rearwardly from the hub to the outer portion, and the outer portion is swept forwardly from the inner portion to the blade tip. | 11-14-2013 |
20130309078 | SHIELD SYSTEM FOR GAS TURBINE ENGINE - A shield system for a gas turbine engine extends between an inner case structure and a vane pack. | 11-21-2013 |
20130309079 | TURBINE NOZZLE OUTER BAND AND AIRFOIL COOLING APPARATUS - A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity. | 11-21-2013 |
20130309080 | FAN - A fan for generating an air current includes a body having an air inlet, and a nozzle connected to the body. The nozzle includes an interior passage for receiving an air flow from the body and an air outlet from which the air flow is emitted from the fan. The interior passage extends about an opening or bore through which air from outside the nozzle is drawn by air emitted from the air outlet. The body includes a duct having an air inlet and an air outlet, an impeller located within the duct for drawing the air flow through the duct, and a motor for driving the impeller. An annular guide member extends about the duct for guiding air from the air inlet of the body to the air inlet of the duct. The guide member defines with the duct an annular noise suppression cavity. | 11-21-2013 |
20130315725 | TURBINE VANE - In a turbine vane and a gas turbine, an outer shroud is fixed to one end of a vane body formed in a hollow shape, an inner shroud is fixed to the other end thereof, and a partition plate is fixed to the inner portions of the vane body, the outer shroud, and the inner shroud, so that a cavity is formed so as to be continuous between the partition plate and the group of the vane body, the outer shroud, and the inner shroud. Then, the vane body, the outer shroud, and the inner shroud are provided with a plurality of cooling holes, and the partition plate is provided with a plurality of penetration holes. Accordingly, since the vane structure or the end wall structure is evenly cooled, a deformation or damage may be suppressed. | 11-28-2013 |
20130323042 | STATOR VANE MISTAKE PROOFING - An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots. The OD shroud is positioned radially outward from the ID shroud. A first stator airfoil extends from the ID shroud to the OD shroud. The first stator airfoil is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A first end of the first stator airfoil has one of a raised tab and an indented notch. | 12-05-2013 |
20130330183 | TURBINE ENGINE AND AERODYNAMIC ELEMENT OF TURBINE ENGINE - A turbine engine is provided and includes an aerodynamic element disposed to aerodynamically interact with a flow of working fluid and contour features disposed on the aerodynamic element in alignment in at least one dimension. The contour features are proximate to one another and configured to encourage counter-rotating vortex flow generation oriented substantially perpendicularly with respect to a main flow direction along the aerodynamic element. | 12-12-2013 |
20130330184 | AERODYNAMIC ELEMENT OF TURBINE ENGINE - An aerodynamic element of a turbine engine is provided and includes leading and trailing edges defined with respect to a predominant direction of a flow of working fluid through a pathway defined through the turbine engine, suction and pressure sides oppositely extending from the leading edge to the trailing edge and at least first and second contour features proximate to the leading edge on the suction side. The first and second contour features are substantially aligned along a spanwise dimension of the aerodynamic element. | 12-12-2013 |
20130330185 | Inducer with Cavitation Instability Controls to Reduce Vibrations and Radial Loads - An inducer includes a hub having an inlet end and an outlet end. At least one full size blade has an inner edge is affixed to the hub and an outer edge. This full size blade extends rearwardly from the inlet end in a helical configuration. A partial shroud encloses a first length of the full size blade outer edge adjacent the inlet end. A second length of the full size blade outer edge that is adjacent to the outlet end is free of the partial shroud. It is within the scope of the disclosure to include short blades symmetrically offset from the two full size blades. These short blades have a short blade inner end affixed to the partial shroud and a short blade outer end extending from the partial shroud towards the hub, but terminating prior to reaching the hub. | 12-12-2013 |
20130336776 | CLOSED IMPELLER WITH A COATED VANE - A closed impeller has a base cover, which has a base interior surface, and a second cover. A vane, which has an inlet distal end and an outlet distal end, is on the base interior surface. The vane has low and high pressure side surfaces wherein they have a low or high pressure midpoint, respectively. A hard coating is on the low and high pressure side surfaces. The hard coating has a minimum low and high pressure coating thickness at their respective midpoints. The minimum low, as well as high, pressure coating thickness ranging between about 0.085 and about 0.8 of either one of the maximum outlet coating thickness at the outlet distal end or the maximum inlet coating thickness at the inlet distal end, respectively. | 12-19-2013 |
20130336777 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape. | 12-19-2013 |
20130336778 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-2, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape. | 12-19-2013 |
20130336779 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape. | 12-19-2013 |
20130336780 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in scalable Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined smoothly with one another to form a complete airfoil shape. | 12-19-2013 |
20130336781 | AIRCRAFT - An aircraft includes a propulsive fan arrangement having an intake and an exhaust. The fan arrangement is mounted adjacent a gas washed surface of the aircraft in the form of a suction surface of a wing. The intake is separated from the suction surface to define a channel therebetween. The aircraft further includes a Venturi device positioned downstream of the fan exhaust to draw boundary layer air through the channel. | 12-19-2013 |
20130336782 | TRIPOD BUCKLE FOR SPLIT FAIRING OF A GAS TURBINE ENGINE - A fairing for a turbine engine strut includes: inner and outer bands; a vane extending between the bands; the fairing is split along a generally transverse plane passing through the bands and the vane, defining nose and tail pieces; wherein the vane is defined by spaced-apart sidewalls extending between a leading edge and a trailing edge, each sidewall split into forward and aft portions by the transverse plane; wherein each sidewall portion carries a radially-inwardly extending post, the posts positioned such that pairs of the posts lie adjacent to each other when the nose piece and tail piece are assembled, wherein each pair of adjacent posts includes at least two non-parallel faces; and a pair of slotted buckles, wherein each slotted buckle surrounds and clamps together a pair of the posts, wherein each pair of adjacent posts contacts a slot of the corresponding buckle in a tripod contact configuration. | 12-19-2013 |
20130343886 | TURBOCHARGER COMPRESSOR NOISE REDUCTION SYSTEM AND METHOD - A turbocharger and a method are disclosed. The turbocharger includes a casing having an inlet end and an outlet end. A flow passage within the casing may have a substantially continuous inner surface and may be configured to pass inlet air from the inlet end to the outlet end. A compressor wheel may be located in the casing and may have at least one main blade and may be configured to rotate within the casing to compress the inlet air. A flow disrupting feature on the casing may be configured to disrupt the continuity of the inner surface and may be located at a leading edge of the at least one main blade. The flow disrupting feature may be closed to upstream communication with the flow passage except via the flow passage. | 12-26-2013 |
20140010643 | METHOD OF FABRICATING A STEAM TURBINE DEFLECTOR - The invention relates to a method for manufacturing a steam turbine low-pressure or medium-pressure module deflector, said deflector comprising an internal ring and an external ring as well as vanes, said method comprising a step of welding said vanes to said rings. The main characteristic of a method according to the invention is that the welding step is preceded by a step of automatically machining the ends of each vane to create a peripheral recess around each of said ends. | 01-09-2014 |
20140030083 | ARTICLE OF MANUFACTURE FOR TURBOMACHINE - An article of manufacture is provided having a first component configured for use with a stator of a turbomachine. The first component is configured for attachment to a second component. The second component is also configured for use with the stator of the turbomachine. The first component is configured to substantially reduce the possibility of installation in an undesired stage of the stator by modification of at least one characteristic of the first component. The second component is configured to substantially reduce the possibility of installation in an undesired stage of the stator by modification of at least one characteristic of the second component. | 01-30-2014 |
20140030084 | ARTICLE OF MANUFACTURE FOR TURBOMACHINE - An article of manufacture is provided having a first component configured for use with a turbomachine. The first component is configured for attachment to a second component. The first component is configured to substantially reduce the possibility of attachment with an undesired third component by modification of at least one characteristic of the first component, so that the modification of the at least one characteristic is matched by a complementary characteristic of the second component. | 01-30-2014 |
20140030085 | COMPLIANT ASSEMBLY - A compliant assembly includes an airfoil and a platform section from which the airfoil extends. The platform section includes a compliant attachment that is configured to secure the platform section to another structure different than the airfoil. The compliant attachment includes a compliant material. | 01-30-2014 |
20140030086 | CENTRIFUGAL PUMP - Embodiments of the disclosure include a centrifugal pump assembly including a pump housing defining a cavity and an impeller disposed within the cavity, the impeller being affixed to a shaft. The pump housing includes an inner surface having a geometric pattern configured in increase a turbulence of a fluid flow over the inner surface. The impeller includes one or more blades and a shroud. The inner surface of the pump housing and the shroud of the impeller define a leakage path. | 01-30-2014 |
20140037442 | ANTI-ROTATION LUG FOR A GAS TURBINE ENGINE STATOR ASSEMBLY - A stator assembly includes a case including an arcuate wall having an aperture with circumferentially spaced first lateral surfaces. A stator vane has an outer platform with a notch. An anti-rotation lug has a base that is received in the notch and a boss extends from the base. The boss is received in the aperture. The boss has second lateral surfaces that engage the first lateral surfaces in an interference fit relationship. | 02-06-2014 |
20140044536 | METHOD FOR REPAIRING A TURBINE DIAPHRAGM AND DIAPHRAGM ASSEMBLY RESULTING THEREFROM - This disclosure describes embodiments of a method of repairing a diaphragm found in a turbine, and a diaphragm assembly resulting from the same, that does not require welds in between the partitions. The method inserts a replacement part in place of certain machine-removed portions of the existing partitions on the diaphragm. The replacement part includes coupons that work in combination with the remaining portions of the partitions to form the aerodynamic shape of the original partitions. | 02-13-2014 |
20140050577 | TURBINE APERTURE CAP SYSTEM - Systems and devices adapted to reduce disturbances and windage effects in a turbine during operation are disclosed. In one embodiment, a cap includes: a body portion having a shape complementary to an aperture in a turbine component, the body portion including an external surface which substantially covers the aperture; and a cap groove formed in a circumferential surface of the body portion, the cap groove configured to substantially align with a component groove formed in the aperture. | 02-20-2014 |
20140050578 | FAN AND FAN FRAME THEREOF - A fan includes a fan frame and a fan wheel. The fan frame includes a frame body and a first waved structure. The frame body has a wind enter side and a wind exhaust side, wherein the wind enter side is opposite to the wind exhaust side. The first waved structure is formed on the wind enter side of the frame body. The first waved structure has a plurality of first peaks and a plurality of first valleys, wherein the first peaks and the first valleys are arranged separately. The fan wheel is rotatably disposed in the fan frame. | 02-20-2014 |
20140064948 | SYSTEM AND METHOD FOR OPERATING A COMPRESSOR DEVICE - Embodiments of a system and method manipulate the position of inlet guide vanes and the drive speed for optimizing performance of a compressor device (e.g., a centrifugal compressor). In one embodiment, the systems and methods can correlate setpoints (e.g., inlet volume flow and discharge pressure) desired for installation and/or implementation of the compressor device with reference data collected as part of in-situ performance testing. This reference data identifies, in one embodiment, a position for the inlet guide vanes and a drive speed for a number of different setpoints at a set of reference conditions (e.g., ambient temperature and ambient pressure). | 03-06-2014 |
20140064949 | TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine and a second casing element located radially distal to the first casing element. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. Release of one of the rotating aerofoil elements results in the element, or part thereof, impacting the first casing element which results in the cantilever bending into the void provided between the first and second casing elements. | 03-06-2014 |
20140064950 | Lateral propulsion unit for aircraft comprising a turbine engine support arch - A propulsion unit for an aircraft, comprising one turbine engine and a mounting device for a turbine engine designed to be added laterally on an aircraft structure and comprising a rigid mounting structure. The rigid mounting structure supports at least one arch which is concave towards the longitudinal axis of the propulsion unit and which has a distal end at an angular distance of between 45 and 120 degrees from a vertical plane passing through the axis, on the other side of the structure, and supporting a distal connecting element connecting the turbine engine to the arch. | 03-06-2014 |
20140072425 | MULTI-CHANNEL FUEL PUMP - A fluid pump includes an outlet for discharging fluid from the fluid pump, a housing, and a motor with a shaft that rotates about an axis. The fluid pump also includes an impeller having a first array of blades radially surrounding the axis and a second array of blades radially surrounding the first array of blades. The fluid pump also includes an inlet plate adjacent to the impeller and has an inlet for introducing fluid into the fluid pump, a first inlet plate flow channel aligned with the first array of blades and having a first inlet plate flow channel cross-sectional area, and a second inlet plate flow channel aligned with the second array of blades and having a second inlet plate flow channel cross-sectional area. The second inlet plate flow channel cross-sectional area is synchronized with the first inlet plate flow channel cross-sectional area. | 03-13-2014 |
20140079542 | CASTING OF THIN WALL HOLLOW AIRFOIL SECTIONS - A casting mold assembly comprises an airfoil defining section and a casting core. The airfoil defining section includes an outer mold wall and a direct-shelled inner mold wall. The direct-shelled inner mold wall is disposed within a forward chordwise portion of the airfoil defining section. The direct-shelled inner mold wall includes an aft end having an external radius measuring more than about 0.075 in. (1.9 mm). The casting core is secured within an aft chordwise portion of the airfoil defining section, and includes an aft end with an external radius measuring less than about 0.075 in. (1.9 mm). A cast component and a method for making the casting mold assembly are also disclosed. | 03-20-2014 |
20140086737 | STRUCTURAL GUIDE VANE INTERNAL TOPOLOGY - A disclosed structural guide vane for a gas turbine engine includes a strut defining a plurality of channels and a cover attached over the plurality of channels. The strut includes a first side defining a first surface of an airfoil and a second side including a plurality of channels. At least one of the plurality of channels defines a wall thickness of a portion of the first side that varies in a chord wise direction. | 03-27-2014 |
20140086738 | NACELLE FOR AN AIRCRFT BYPASS TURBOJET ENGINE - A nacelle for an aircraft bypass turbojet engine includes downstream, an internal stationary structure surrounding part of the bypass turbojet engine, and an external structure surrounding the internal stationary structure, defining an annular flow path along which an air flow circulates. The external structure includes a mobile flap disposed at the downstream end of the external structure and positioned facing the annular flow path. Each mobile flap can rotate such as to move into a position that increases or reduces the height of the cross-section of the annular flow path in relation to an idle position, in response to the pressure exerted on the mobile flap by the air flow circulating through the facing annular flow path. The mobile flap can return from the cross-section-increasing or -reducing position to another position under the effect of an elastic return means. | 03-27-2014 |
20140093367 | AIRFOIL WITH GALVANIC CORROSION PREVENTIVE SHIM - An airfoil includes an airfoil body made of a first metal with a leading edge, a trailing edge, pressure side and suction side; a sheath with first and second flanks made of a second metal; a first layer of non-conductive material adhesively bonded between a portion of the end of the first flank and the airfoil body and extending beyond the end of the first flank on the pressure side; and a second layer of non-conductive material adhesively between a portion of the end of the second flank and the airfoil body and extending beyond the end of the second flank on the suction side. | 04-03-2014 |
20140119908 | FAN HOUSING FOR RAM AIR FAN - A fan housing has a radially outer surface. A pair of radially intermediate surfaces includes a first surface spaced towards a first axial end, which has an inner bore positioned radially outward of an inner bore of a second surface. Vanes extend between the radially outer surface and an outer periphery of the pair of radially intermediate surfaces. A bearing bore extends radially inwardly of the first surface. A mounting lug nub is formed on an outer periphery of the radially outer surface. A first distance is defined between the first axial one end of the fan housing and an opposed axial end. A second distance is defined between the first axial end and a center of the mounting lug. A ratio of the first distance to the second distance is between 2.13 and 2.11. An intermediate part, a ram air fan and a method are also disclosed. | 05-01-2014 |
20140119909 | FAN MODULE - A fan module, disposed inside a case of an electronic device, includes a case body, a blade assembly, a stopping plate and an adjusting element. The case body, including a first case unit, a sidewall and a second case unit, forms an accommodating space. The first case unit or/and the second case unit has an air inlet. The sidewall has an air outlet and an adjusting opening. The blade assembly is disposed inside the accommodating space. The stopping plate, disposed on the sidewall, is for opening or closing the adjusting opening. The adjusting element is movably disposed on the stopping plate and for pressing against the stopping plate. When the adjusting element moves from a first position toward a second position, the adjusting element pushes against and makes the stopping plate to be offset toward the blade assembly, and produces a gap between the stopping plate and the sidewall. | 05-01-2014 |
20140127010 | NOZZLE WITH GUIDING DEVICES - The present invention relates to a nozzle with a nozzle surface area and a nozzle rim, on which first and second guiding devices are alternatingly provided in the circumferential direction, where the first guiding devices are of the nozzle-type design and the second guiding devices are of the diffuser-type design. The first guiding devices each have a first azimuthal guide wall and two wall elements, with the first azimuthal guide wall forming a first trailing edge and two first edges to the wall elements. The second guiding devices each have a second azimuthal guide wall and two wall elements, with the second azimuthal guide wail forming a second trailing edge and two second edges to the wall elements. A wall element connects a first guiding device and a second guiding device. The wall elements have a curved course in the axial direction. | 05-08-2014 |
20140140837 | FLOW CONDITIONING FEATURE FOR SUCTION DIFFUSER - A suction diffuser or arrangement is provided featuring a main suction diffuser body and a flow conditioning arrangement. The main suction diffuser body is configured with an inlet to receive an incoming fluid flow, an interior cavity to receive the incoming fluid from the inlet, and an outlet to receive the incoming fluid from the interior cavity and provide an outgoing fluid. The flow conditioning arrangement is configured in relation to the inlet and also comprises a flow conditioning portion having at least one inwardly contoured surface, configured to extend into the interior cavity, diffuse the incoming fluid passing from the inlet into the interior cavity, and provide a flow conditioning that produces a uniform flow of the outgoing fluid by directing the incoming fluid towards the outlet, based at least partly on a contoured design corresponding to the at least one inwardly contoured surface. | 05-22-2014 |
20140147263 | TURBINE VANE WITH MISTAKE REDUCTION FEATURE - A turbine vane for a gas turbine engine has an inner platform, an outer platform, at least one airfoil extending between the inner and outer platforms, and a tab radially extending inward from a front side of the inner platform. The tab contains a mounting aperture and an identification aperture that identifies an engine in which the turbine vane may be installed. | 05-29-2014 |
20140154068 | Endwall Controuring - An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages. | 06-05-2014 |
20140154069 | TURBINE WHEEL, A TURBINE AND USE THEREOF - A turbine wheel for low-pressure ratio applications is disclosed. The ratio of the outlet area of the wheel (A | 06-05-2014 |
20140161605 | GAS TURBINE STRUCTURE - A gas turbine structure includes a guide vane. The gas turbine structure (further includes a first housing and a second housing and the guide vane extends from the first housing to the second housing. The guide vane includes a leading edge and a trailing edge and the guide vane extends from the leading edge to the trailing edge along a mean camber line. The guide vane includes a first attachment structure, a first fastening arrangement and a second fastening arrangement. Moreover, the first attachment structure includes a stiffening member extending over at least a portion of a circumference of the first housing. Furthermore, the stiffening member includes a stiffening member center point as measured along the mean camber line. | 06-12-2014 |
20140161606 | VANE PROFILE FOR AXIAL-FLOW COMPRESSOR - A vane for an axial-flow compressor has a pressure surface generating positive pressure and a suction surface generating negative pressure, and both are located on one side of the chord line. The pressure surface includes a bulging portion, having a maximum curvature of 1.5 or more between a chordal position of 70% and 95%, in a central section of the vane's span. This configuration increases the flow velocity around the bulging portion of the pressure surface to locally decrease the static pressure. By flow continuity the flow velocity on the suction surface that faces the pressure surface is decreased, and thus locally the static pressure on the suction surface is increased. Secondary flow from the pressure surface with positive pressure to the suction surface with negative pressure from the hub region, is suppressed due to the locally increased static pressure on the suction surface. | 06-12-2014 |
20140161607 | TURBOMACHINE - The turbomachine includes a mid turbine vane frame, with an annular compartment formed between the mid turbine vane frame and a low-pressure turbine casing being sealed by means of at least two ring seals, wherein one ring seal is in contact with the mid turbine vane frame and the other ring seal is in contact with the low-pressure turbine casing and a radial annular overlap is thereby created with the first-mentioned ring seal. | 06-12-2014 |
20140186171 | GUIDE BLADE ARRANGEMENT FOR AN EXHAUST GAS TURBOCHARGER - A guide blade arrangement for an exhaust gas turbocharger may include guide blades rotatably mounted on a guide blade carrier ring via a respective blade bearing pin. A cover disc may be spaced from the guide blade carrier ring, wherein the guide blades may be arranged between the cover disc and the guide blade carrier ring. The cover disc may include a ceramic material, and the ceramic material may have a higher thermal conductivity in relation to at least one of the guide blade carrier ring, the guide blades, and the respective blade bearing pin. | 07-03-2014 |
20140193250 | DISC BRAKE PISTON CAP AND DISC BRAKE EQUIPPED THEREWITH - A plate closes the main part of a vane in two parts. An internal cavity is closed by the plate. Around a bearing surface of the plate, a groove receives an elastic seal, and the outer edge of the plate extends over the groove to compress the seal and to establish excellent leak proofing. The position of the plate may be guaranteed by centring pins penetrating into holes adjacent to the seal and which it fills when the pins have been removed, which completes the closing of the cavity. The plate has application in particular to stationary gas guide vanes in turbine engines. | 07-10-2014 |
20140199166 | PROPULSION AND DIRECTIONAL CONTROL APPARATUS FOR AN AIR CUSHION VEHICLE - An apparatus for controlling the propulsion and direction of an air cushion vehicle including a housing and a first vane pivotally coupled to the housing and pivotable about a first axis. A second vane assembly including at least one second vane is disposed within the first vane. The second vane assembly is pivotally coupled to the first vane and pivotal about a second axis. The second axis is orthogonal to the first axis. A first actuator is operably coupled to the first vane and a second actuator is operably coupled to the second vane assembly. The first actuator pivots the first vane and the second vane assembly about the first axis. The second actuator pivots the second vane assembly relative to the first vane and about the second axis to control the flow of air through the housing. | 07-17-2014 |
20140205449 | SUPERALLOYS AND COMPONENTS FORMED THEREOF - A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight: 16.0 to 30.0% cobalt; 9.5 to 12.5% chromium; 4.0 to 6.0% tantalum; 2.0 to 4.0% aluminum; 2.0 to 3.4% titanium; 3.0 to 6.0% tungsten; 1.0 to 4.0% molybdenum; 1.5 to 3.5% niobium; up to 1.0% hafnium; 0.02 to 0.20% carbon; 0.01 to 0.05% boron; 0.02 to 0.10% zirconium; the balance essentially nickel and impurities. The superalloy has a W+Nb−Cr value of at least −6, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 1300° F. and 100 ksi of at least 1000 hours. | 07-24-2014 |
20140212282 | METHOD FOR PROFILING A REPLACEMENT BLADE AS A REPLACEMENT PART FOR AN OLD BLADE FOR AN AXIAL-FLOW TURBOMACHINE - A method for profiling a replacement blade for an axial turbomachine is provided. The method includes: measuring hub contour geometry and housing contour geometry of the flow channel of the old blade and the axial position of the centre of gravity of the blade aerofoil of the old blade; laying out geometry of the blade aerofoil of the replacement blade, the blade aerofoil having a rearward sweep on its leading edge; defining a region of the blade aerofoil near the mounting and in which positive influence of the rearward sweep on the degree of stage efficiency is rated as low; and axially displacing the replacement blade aerofoil section arranged outside this region in the upstream direction, until the axial position of the centre of gravity of the blade aerofoil of the replacement blade coincides with the old blade. In the region from the mounting-side section to the displaced blade aerofoil section of the replacement blade, the leading edge is inclined downstream towards the mounting such that the blade aerofoil has a transition sweep in this region. | 07-31-2014 |
20140212283 | Cage Positioned Tilting Pad Bearing - A tilting pad bearing for a high speed rotary machines, such as a turbocharger for an internal combustion engine, comprises a cage and a plurality of tilting pads. The cage is formed by two annular rings separated by spacers machined from a single billet of high-temperature metal. The bearing pads are inserted between the spacers of the cage. One or more O-rings retain the bearing pads within the cage during assembly of the bearing but are not required after installation of the bearing. When retained in the final assembly and installation of the bearing, the O-rings allow tilting movement of the pads within the cage. The outer surfaces of the spacers have a plurality of grooves, and outer surfaces of each of the pads have matching grooves. One of the grooves is an oil groove, wherein the oil groove of the spacers communicating with and oil inlet holes in the spacers. At least one of the other grooves receives an O-ring that hold the pads in place in the cage during installation. When two O-rings are used on either side of the oil groove in the final assembly, the O-rings serve to direct oil to the oil groove and prevent or reduce oil leakage. | 07-31-2014 |
20140219790 | Axial Turbine With Sector-Divided Turbine Housing - A statorless or nozzleless axial turbine for a turbocharger has an axial turbine wheel that receives a swirling flow of exhaust gas substantially in an axial direction. The turbine includes a sector-divided turbine housing defining a plurality of separate exhaust gas inlets each for receiving a separate exhaust gas stream from an internal combustion engine, the sector-divided turbine housing further defining a plurality of separate angular sector passageways each of which occupies a fractional part of a circumference surrounding the turbine wheel, each angular sector passageway being supplied with exhaust gas by a respective one of the plurality of exhaust gas inlets. The turbine housing assembly defines a separate sector outlet for each angular sector passageway. The turbine housing assembly can include a separately formed heat shroud, and the sector outlets can be formed at least in part by the heat shroud. | 08-07-2014 |
20140234097 | HORIZONTAL-TYPE WIND TURBINE WITH AN UPSTREAM DEFLECTOR - Horizontal axis wind turbine (HAWT) systems are described that include a turbine with deflector in front of the turbine in order to change flow encountered by the turbine's blades. Such an arrangement improves turbine efficiency and may be embodied in a range of size scales for numerous wind (or water) power generation applications. | 08-21-2014 |
20140241871 | VANE STRUCTURE AND A METHOD OF MANUFACTURING A VANE STRUCTURE - A fuel injector comprises a swirler and the swirler comprises a plurality of vanes, a first member and a second member. The second member is arranged coaxially around the first member and the vanes extend radially between the first and second members. The vanes have leading edges and the second member has an upstream end. The leading edges of the vanes extend with radial and axial components from the first member to the upstream end of the second member and the radially outer ends of the leading edges of the vanes form arches with the upstream end of the second member. The arrangement of the swirler enables the fuel injector to be built by direct laser deposition. | 08-28-2014 |
20140241872 | Stator Member and Vacuum Pump - To provide a stator member that facilitates thermal radiation from a surface thereof and thermal conduction to an adjacent member, and a vacuum pump that contains the stator member. For the purpose of enhancing heat dissipation of a rotor portion, surface treatment removal processing is performed on a predetermined section of a thread groove spacer in order to efficiently release heat of the thread groove spacer toward a base and a stator blade spacer. More specifically, the surface treatment removal processing removes the surface treatment of the base and a section where the stator blade spacer comes into contact with the thread groove spacer. This surface treatment removal processing is executed simultaneously with finishing processing. | 08-28-2014 |
20140248143 | MONOLITHIC FAN COWL OF AN AIRCRAFT ENGINE AND A MANUFACTURING METHOD THEREOF - The invention provides a fan cowl ( | 09-04-2014 |
20140248144 | TURBOMACHINE CENTRE BLADE COMPRISING A CURVED PORTION - A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion. | 09-04-2014 |
20140255176 | PUMP HOUSING WITH AN INTERIOR FOR ACCOMMODATING A PUMP ROTOR - In a pump housing having an interior for accommodating a pump rotor, which may be transferred from a radially compressed state into a radially expanded state, and comprises a housing skin revolving in circumferential direction, as well as at least one reinforcement element, a stretch-resistant element revolving in circumferential direction is provided, which is stretched less than 5% in the expanded state as opposed to the force-free state in circumferential direction, and which limits any further expansion of the pump housing in radial direction. | 09-11-2014 |
20140255177 | OUTBOARD INSERTION SYSTEM OF VARIABLE GUIDE VANES OR STATIONARY VANES - A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture. The guide vane is secured to the outer surface of the casing such that the guide vane can be serviced from an outer part of the casing. | 09-11-2014 |
20140255178 | AIRCRAFT ENGINE AIR FLOW STRAIGHTENING VANE AND ASSOCIATED FLOW STRAIGHTENING STRUCTURE - A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin. | 09-11-2014 |
20140271169 | NACELLE FOR A HIGH BYPASS RATIO ENGINE WITH MULTIPLE FLOW PATHS - Nacelle air management systems for a high bypass ratio engine are provided. The nacelles air management systems may include an outer cowl and an inner cowl that are configured to provide dual bypass flow channels around an engine core. These systems may be employed to accommodate larger engine fans. The nacelle air management system may also include one or more blocker doors are configured to at least partial obstruct and/or direct air from the dual bypass flow channels to create reverse thrust. | 09-18-2014 |
20140286768 | TURBOMACHINE ELEMENT - A turbomachine element including an airfoil set including a plurality of airfoils that are offset from one another in a lateral direction, and upstream from at least one end of each airfoil, a group of a plurality of vortex generator devices that are mutually offset both laterally and axially. | 09-25-2014 |
20140294578 | DIFFUSER MODULE AND ELECTRIC BLOWER HAVING THE SAME - Disclosed herein is a diffuser module, including: a cover covering an impeller connected to a rotation shaft; a housing coupled with the cover and accommodating a driving module including the rotation shaft; a diffuser directing flow of air drawn by the impeller; and a coupling member coupling the cover and the housing, wherein the cover and the housing have their respective coupling portions in a shaft direction of the rotation shaft, and wherein the diffuser has a groove portion partly corresponding to the coupling portion of the cover at its outer circumferential portion. | 10-02-2014 |
20140294579 | COMPOSITE GUIDE VANE - A composite guide vane for a gas turbine structure is adapted to extend in a guide vane direction from a first housing towards a second housing of the gas turbine structure. The guide vane includes a guide vane length in the guide vane direction and the guide vane includes a first attachment portion with at least one first opening for attachment of the guide vane to the first housing. The first opening extends in a first opening direction which forms an angle with the guide vane direction. The guide vane includes a cover portion including a first material and a core portion which is at least partially enclosed by the cover portion. | 10-02-2014 |
20140294580 | BLOWING DEVICE, AND IMAGE FORMING APPARATUS - Provided is a blowing device including a blower that sends air, a blower pipe having an inlet that takes in the air sent from the blower, an outlet that is formed in an elongated opening shape parallel to the portion of the target structure in the longitudinal direction, and a body portion that connects the inlet and the outlet and to cause the air to flow therethrough, and plural flow dividing plates, each of the flow dividing plates having a distributing portion and a changing portion. | 10-02-2014 |
20140301837 | DOOR FOR A THRUST REVERSER WITH DOORS - A door for a door-type thrust reverser is pivotally mounted on a stationary structure of a thrust reverser. The door includes an inner surface integrated to a flow path of an air flow generated by a turbojet engine, an outer surface providing an outer aerodynamic continuity of a nacelle equipped with the thrust reverser, a spoiler to deflect the air flow disposed at an upstream end of the door, and an actuator actuating the spoiler. The spoiler is movably mounted, in rotation around a rotation axis substantially perpendicular to a front frame of the door, between a retracted and a deployed position. In particular, the actuator includes a first rod connected to the spoiler, a second rod connected to the first rod and the front frame, and a third rod connected to the first and second rods as well as to the spoiler. | 10-09-2014 |
20140314559 | GUIDE VANE & INLINE FAN ASSEMBLY - An improved guide vane for an inline fan is provided, as is an inline fan assembly so characterized. The vane guide includes a first vane segment characterized by first and second end portions, and a second vane segment characterized by first and second end portions. The second end portion of the first vane segment is in a spaced apart and overlapped arrangement in relation to the first end portion of the second vane segment. The first end portion of the first vane segment is an adjacent most vane guide end portion in relation to an impeller of the fan. The first vane segment is of arcuate configuration, with the second vane segment being of linear configuration. | 10-23-2014 |
20140322004 | AXIAL FLOW WATER TURBINE - An axial flow water turbine according to an embodiment includes a discharge ring and a runner vane. When seen in the runner meridional cross section, a straight line that passes a border between a cylindrical surface and a spherical surface of the discharge ring and that is perpendicular to a water turbine rotation axis is denoted as A. A crossing point between the straight line A and the water turbine rotation axis is denoted as B. A straight line inclined by an angle θ of 10 degrees or less is denoted as C. A cross point between the straight line C and the external peripheral end surface of the runner vane is denoted as D. In this case, the external peripheral end of the forward edge of the runner vane is located on the crossing point D. | 10-30-2014 |
20140322005 | EXHAUST GAS TURBOCHARGER - In an exhaust gas turbocharger with a casing part in which a guide apparatus comprising two axially spaced insert elements forming a flow duct is arranged with guide vanes supported on at least one of the insert elements via which exhaust gas flowing through the flow duct is guided into the turbine of the turbocharger and wherein a first of the insert elements comprises a first wall portion which extends at least essentially in the radial direction and an adjoining second wall portion which extends essentially in the axial direction so as to form a corner area of the first insert element, wherein in the first wall portion and/or in the corner area in a side facing the casing part at least one recess is provided. | 10-30-2014 |
20140322006 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 10-30-2014 |
20140334924 | METHOD AND DEVICE FOR THE GENERATIVE PRODUCTION OF A COMPONENT USING A LASER BEAM AND CORRESPONDING TURBO-ENGINE COMPONENT - In a method for the generative production of a component ( | 11-13-2014 |
20140341729 | RADIAL TURBINE - A radial turbine comprises a plurality of nozzle vanes disposed along a circumferential direction inside a spiral scroll and configured to regulate a flow of a working gas from the scroll to a rotor blade, wherein each of the nozzle vane includes a leading edge bulging portion on both end portions in a width direction of an inlet leading edge portion, the leading edge bulging portion being bulged toward a pressure face side of the nozzle vane relative to a central portion, so that a vane angle is configured to correspond with an inflow angle of the working gas to be flown into the nozzle vane, and wherein each of the nozzle vane includes a trailing edge bulging portion on both end portions in a width direction of an outlet trailing edge portion, the trailing edge bulging portion being bulged toward the pressure face side relative to a central portion, so that an outflow angle of the working gas from the outlet trailing edge of the nozzle vane becomes uniform. | 11-20-2014 |
20140348648 | AEROFOIL RECAMBERING - A method of recambering an aerofoil section. A position on one of the surfaces that intersects with a passage shock between adjacent aerofoils is determined and then projected as a shock position onto the camber line. A shock region encompassing the shock position and extending in a chordal direction towards the leading and trailing edges is defined. The camber line is recalculated in an upstream region using semi-inverse design. The camber line is extrapolated across the shock region to match a geometric criterion. The camber line is recalculated in a downstream region using semi-inverse design. | 11-27-2014 |
20140348649 | CEILING FAN WITH MOISTURE PROTECTION FEATURES - A fan may be designed for the strategic diversion of moisture through or around a housing enclosing a controller and/or a motor. The enclosure may include one or more paths for directing moisture away from the controller or the motor. For instance, the housing may include a gap between a support structure and the housing for preventing moisture from entering the housing. The housing may also include a hollow structure for directing fluid through the housing. Additionally, the housing may include one or more channels, raised walls, gutters, and shields for preventing fluid, such as liquid water, from entering an enclosure for the controller or motor. | 11-27-2014 |
20140356154 | Blade With An S-Shaped Profile For An Axial Turbomachine Compressor - The present disclosure provides a subsonic rotor and/or stator blade profile of an axial turbomachine compressor, such as a turbojet. The blade comprises a leading edge with an S-shaped lateral profile in its mid-plane. Specifically, the profile includes, from its inner end to the outer end, a first convex portion including the foremost point of the blade, and a second concave portion including the rearmost area of the blade. This profile enables the fluid flow between 20% and 80% of the blade's length to be redistributed. This so-called “sweep” profile increases the performance of the stage with such blades because it reduces blade tip vortex losses as well as secondary losses. | 12-04-2014 |
20140356155 | Nozzle Insert Rib Cap - The present application provides a nozzle assembly for use in a turbine engine. The nozzle assembly may include a first nozzle cavity, a second nozzle cavity, a rib positioned between the first nozzle cavity and the second nozzle cavity, a first cavity insert with a first cavity insert configuration, a second cavity insert with a second cavity insert configuration, and a rib cap positioned on the rib. The rib cap may include a rib cap configuration such that only the first cavity insert with the first cavity insert configuration fits within the first nozzle cavity and only the second cavity insert with the second cavity insert configuration fits within the second nozzle cavity. | 12-04-2014 |
20140356156 | AIRFOIL GEOMETRY OF BLADE FOR AXIAL COMPRESSOR - A suction surface of a blade forming a blade row of an axial compressor includes a concave region having a negative curvature at a leading edge part, and a flat region having substantially zero curvature continued rearwardly of the concave region, so that multiple compression waves are generated, enabling moderation of magnitude of a 1st passage shock to reduce pressure loss and suppress boundary layer separation on the suction surface. Providing a concave region having a negative curvature in a frontal part on a pressure surface of the blade suppresses an increase in the airflow velocity in the frontal part, thus weakening a 2nd passage shock generated on the pressure surface to enable reduction of pressure loss. The concave region of the pressure surface may be extended from a position having a chord length of no greater than 10% to a position having at least 20%. | 12-04-2014 |
20140363283 | SHROUD ARRANGEMENT FOR A FLUID FLOW MACHINE - A shroud arrangement for a fluid-flow machine includes a blade root connected to at least one blade/vane end of a row of rotor blades or stator vanes, or is connected to at least one such blade/vane end. A shroud is connected to the blade root on the side of the blade root facing away from the blades/vanes. The blade root on the side facing away from the blades/vanes has two blade root fingers extending substantially in the radial direction and axially spaced from one another, the blade root fingers forming between them a recess being continuous in the circumferential direction. An element or area of the shroud for fastening to the blade root is arranged in the recess. The shroud has two webs extending into the recess and enclosed by the blade root fingers, with the two webs forming substantially a V-shaped arrangement. | 12-11-2014 |
20140363284 | STATOR VANE SEGMENT OF A FLUID FLOW MACHINE AND TURBINE - A stator vane segment ( | 12-11-2014 |
20140363285 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 12-11-2014 |
20150016983 | SUBSONIC SHOCK STRUT - A gas turbine engine strut is disclosed as having a will forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body includes a discontinuity in a curvature distribution which provides for a “subsonic shock.” The discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body. In some forms, the aft body can additionally include boundary layer aspiration. The gas turbine engine strut can be symmetrical about a centerline. | 01-15-2015 |
20150016984 | Guide vane arragement and method for mounting a guide vane - The invention relates to a guide vane arrangement and a method for mounting a guide vane. The guide vane arrangement has at least one guide vane having a radially inner journal, which engages in a borehole of a bushing. The bushing is disposed in a borehole of an inner ring segment. The journal is connected to the bushing in a rotation-resistant manner and a slide mounting is provided between the bushing and the inner ring borehole. For mounting the guide vane in an inner ring segment, the journal of the guide vane is introduced into the borehole of the bushing. Further, the journal is fastened to the bushing in a rotation-resistant manner, and the bushing is slide-mounted with the inner ring segment. The slide mounting is conducted prior to or simultaneously with or after the fastening of the journal to the bushing in a rotation-resistant manner. | 01-15-2015 |
20150016985 | GAS TURBINE STAGE - A gas turbine stage including a rotor blade array having a plurality of rotor blades and an adjacent stator vane array having a plurality of stator vanes which have leading edges facing the rotor blade array. In a first radial position of a rear face of the rotor blade array, a minimum axial gap is formed between this rear face and an opposite first contact region a stator vane leading edges, and in a second radial position of the rear face different from the first position, the minimum axial gap is formed between the rear face and an opposite second contact region. Between the first and second contact regions, this stator vane leading edge has an axial offset of no more than 0.6% of a radial height of the stator vane leading edge. | 01-15-2015 |
20150023788 | FLOW THERMAL STRESS TURBOCHARGER TURBINE HOUSING DIVIDER WALL - The propensity for turbocharger turbine divider wall to crack in the turbine housing is minimized by matching the mass of the divider wall more closely to the transient heat transfer between said divider wall and the exhaust gas flowing past it. This is achieved by providing said divider wall having a cross-sectional shape defined substantially by a Log | 01-22-2015 |
20150044040 | AIR BLOWER - Air blower incorporates in housing thereof: suction port; a high pressure air generating portion; a blowout port; first air passage; introduction air suction port; introduction air mixing portion; introduction air blowout port; and second air passage. | 02-12-2015 |
20150044041 | CRACK RESISTANT TURBINE VANE AND METHOD FOR VANE CONTAINMENT CAP ATTACHMENT - A gas turbine vane containment cap is attached to an inboard surface of the vane inner shroud by penetrating flat weld filler, formed in a root gap between the cap and inner shroud. A semi-circular bead weld filler is formed outboard the penetrating weld filler closer to the vane exterior. Vane containment caps so welded are more resistant to in-service cracking along weldments. | 02-12-2015 |
20150063997 | AIRFOIL TRAILING EDGE - An airfoil includes a radially inner edge extending in a radial direction of the airfoil to a radially outer edge. Also included is a leading edge extending in an axial direction of the airfoil to a trailing edge. Further included is a trailing edge geometry comprising at least one wave segment having simultaneous curvature in at least two directions. | 03-05-2015 |
20150063998 | HORIZONTAL AGITATOR - The invention relates to a horizontal agitator for producing a flow in a clarifier, a submersible motor and a propeller drivingly connected thereto forming an assembly unit, wherein a receiving portion for removably attaching the assembly unit is provided and can be supported on the bottom of the clarifier, and wherein a guide for guiding the assembly unit along a substantially vertical movement path between a surfacing position above a maximum nominal sewage level defined for the clarifier and the receiving portion is provided. In order to improve the efficiency of the horizontal agitator and to reduce complexity of manufacture, the guide is formed by at least one first cable extending between the surfacing position and the receiving portion. | 03-05-2015 |
20150063999 | PRESS FIT KEYED OUTER RACE IN STATOR - The invention presented is an outer race for a stator assembly which includes keys that extend radially outward from the outer circumferential edge. The keys include transverse projecting splines. The splines are configured to cut grooves into the body of a stator to form a press fit connection between the outer race and the stator. The connection reduces or eliminates a loosening of the stator-outer race connection when fluid temperatures increase as well as reducing the effects of lash by reducing or eliminating gaps in the stator-outer race connection. | 03-05-2015 |
20150086349 | POWERED VENTILATORS - A number of fan assemblies are shown. Configurations are shown that include one or more diffusers. Diffuser locations and specific diffuser configurations are described that improve one or more fan assembly characteristics, including, but not limited to fan efficiency. | 03-26-2015 |
20150086350 | Divided Stator Casing - A stator for eccentric screw pumps with a stator casing for an elastomer body for accommodating a rotor, the elastomer body being provided with at least one collar, wherein the collar is disposed in a recess between the stator casing and a connection body, wherein the fixing of the elastomer body in the stator casing is to be improved. The stator casing includes for this purpose open cavities, recesses and/or elevations at least at one side on the end face. | 03-26-2015 |
20150104302 | RAM AIR FAN HOUSING - A fan housing of a ram air fan assembly is provided including a flange having at least one tab. The at least one tab includes a first portion extending generally perpendicularly from the flange and a second portion extending generally parallel to the flange. A notch is formed by an inclined surface and a curved surface at an intersection between the first portion and the second portion. The second portion is elongated and extends about 0.020 inches beyond a front surface of the first portion. | 04-16-2015 |
20150110616 | GAS TURBINE NOZZLE TRAILING EDGE FILLET - A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform. The airfoil body includes opposed pressure and suction sidewalls extending between a leading edge and a trailing edge of the airfoil body. The airfoil body includes a first trailing edge fillet blending into the inner platform at a trailing edge of the airfoil body. | 04-23-2015 |
20150110617 | TURBINE AIRFOIL INCLUDING TIP FILLET - A turbine blade can include a root configured to connect to a turbine and supporting an airfoil configured to extend into a flowpath of the turbine. The airfoil can include a tip disposed substantially opposite the root and a first tip fillet disposed proximate the tip that can extend substantially perpendicular to a local flow direction at points along a surface of the turbine blade over the extremity of the first tip fillet. The tip fillet can enhance performance of the turbine by beneficially altering flow through a stage in which the blade is included. | 04-23-2015 |
20150132121 | FAN - A fan includes a frame and an impeller. The frame defines a hole in a middle of the frame. An inner wall of the frame bounding the hole defines a circumferential groove and forms a circumferential protrusion adjoining the groove. The impeller is received in the hole of the frame. When the impeller is rotated, airflow through the hole is pressurized by the groove and the protrusion, and concentrates when the airflow is blown out of the hole. | 05-14-2015 |
20150139789 | Array of flow-directing elements for a gas turbine compressor - An array of flow-directing elements for a compressor of a gas turbine including at least one first flow-directing element and at least one second flow-directing element different from the first flow-directing element; the flow-directing elements each having a leading edge facing the gas turbine inlet, a trailing edge, a pressure side connecting them and located ahead in the direction of rotation, a suction side located opposite thereof, as well as successive chords along a stacking axis; the flow-directing elements each extending between an airfoil root proximate to the rotor and an airfoil tip remote from the rotor. The trailing edge of the first flow-directing element is, at least in a portion thereof, axially offset from the trailing edge of the second flow-directing element in a direction toward the leading edge at least in a half proximate to the airfoil tip. | 05-21-2015 |
20150292509 | FAN - A fan of the present disclosure includes a housing, an air guiding device, and a fan blade, where the an guiding device and the fan blade are arranged in the housing, and the an guiding device is used to guide air. The air guiding device includes a fixed ring. A limiting-position device is arranged in the fan, and is structured and arranged to limit and fix the air guiding device, which makes the air guiding device not shake and firmly fixes the air guiding device in the housing of the fan, further makes the air guiding device maintain a normal working state. | 10-15-2015 |
20150300184 | APPARATUS AND METHOD FOR THE FORMING OF TURBINE VANE COVER PLATES - A method is provided for reconditioning a turbomachine vane cover plate, by a forming apparatus. The vane having a mounting portion, an airfoil extending radially outward therefrom and a vane head connected to the airfoil. The vane also having a cover plate connected to the vane head, bulged in a direction opposite to the root. In a first analysis step, dimensions of the vane in relation to the cover plate are determined in respect of predefined reference points. If, thereafter, forming of the cover plate seems necessary and possible based on comparison of measurement values from the analysis step with predefined dimension values, the bulged cover plate is formed, at least essentially pressed smooth, by pressing by the forming apparatus in a forming step. After the forming step, the cover plate is re-treated in one or more follow-up steps. An apparatus is also provided for carrying out the method. | 10-22-2015 |
20150300206 | AIR EXHAUST TUBE HOLDER IN A TURBOMACHINE - A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins that are inclined relative to the axial direction of the annular portion and relative to the radial plane, the radially outer periphery of each fin being for fastening to an exhaust cone of the turbine engine. | 10-22-2015 |
20150314868 | A DEVICE FOR THE GENERATION OF LIFT - A lift device generating including:
| 11-05-2015 |
20150315919 | LIGHTWEIGHT STRUCTURAL NiAl ALLOY WITH A HIGH HIGH-TEMPERATURE STRENGTH - Disclosed is a material on the basis of intermetallic nickel aluminides for applications which require a high high-temperature strength. The material comprises more than 50 at. % nickel and ternary Laves phases. Also disclosed is a component of a turbomachine produced from the material. | 11-05-2015 |
20150322820 | SHROUDED CONDUIT FOR ARRANGING A FLUID FLOWPATH - A shrouded conduit is provided for arranging, for example, in a gas path of a turbine engine. The shrouded conduit includes a tubular shroud extending longitudinally along a centerline. The shrouded conduit also includes a fluid conduit extending longitudinally in the shroud. A first portion of the fluid conduit is connected laterally to and may be formed integral with a first portion of the shroud. | 11-12-2015 |
20150322958 | MULTI-SEGMENT TURBOCHARGER BEARING HOUSING AND METHODS THEREFOR - A turbocharger ( | 11-12-2015 |
20150337664 | TURBOMACHINE BLADE, CORRESPONDING TURBOMACHINE AND METHOD OF MANUFACTURING A TURBINE BLADE - A blade of a turbomachine comprises an airfoil portion; the airfoil portion extends longitudinally; the airfoil portion is defined laterally by an external surface; the airfoil portion has a 3D and twisted shape and has an internal cavity; the blade is in a single piece. Furthermore, the blade is designed for a rotor or stator array; the rotor or stator defines a radial direction and an axial direction; the external surface of the airfoil portion has a leading edge and a trailing edge; the leading edge and/or the trailing edge shifts backward or forward in the axial direction moving in the radial direction; the internal cavity extends along substantially the whole longitudinal length of the airfoil portion. Additive manufacturing is particularly effective and advantageous for such blade. | 11-26-2015 |
20150337666 | PLATFORM WITH CURVED EDGES ADJACENT SUCTION SIDE OF AIRFOIL - A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge adjacent the suction side and a second curved edge spaced from the pressure side such that more than half of the platform is located to the pressure side. The platform located to the pressure side has a non-axisymmetrical surface contouring. | 11-26-2015 |
20150354385 | FLAPPER SEAL APPARATUS AND SYSTEM - An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element. | 12-10-2015 |
20150369062 | TURBINE ROTOR, TURBINE, AND METHOD FOR REMOVING SEAL PLATE - This turbine rotor ( | 12-24-2015 |
20150369067 | STRUCTURAL GUIDE VANE OUTER DIAMETER K GUSSETS - A guide vane includes an airfoil with a first end and a second end. A platform is disposed at a first end of the airfoil, and a K-gusset is disposed on the platform opposite the airfoil. The K-gusset includes four bosses and ribs extending between the bosses in a “K” configuration. | 12-24-2015 |
20150369254 | TURBOCHARGER COMPRESSOR NOISE REDUCTION SYSTEM AND METHOD - A turbocharger and a method are disclosed. The turbocharger includes a casing having an inlet end and an outlet end. A flow passage within the casing may have a substantially continuous inner surface and may be configured to pass inlet air from the inlet end to the outlet end. A compressor wheel may be located in the casing and may have at least one main blade and may be configured to rotate within the casing to compress the inlet air. A flow disrupting feature on the casing may be configured to disrupt the continuity of the inner surface and may be located at a leading edge of the at least one main blade. The flow disrupting feature may be closed to upstream communication with the flow passage except via the flow passage. | 12-24-2015 |
20150369582 | Datum Transfer Apparatus and Method for Inspecting Coated Components - A method of inspecting components between a pre-coated state and a post-coated state is provided. The method entails providing at least first and second datum points onto the component in the pre-coated state, where each of the at least first and second datum points have a substantially hemi-spherical shape and a center point. The center points of each of the at least first and second datum points are utilized for measurement of a selected portion on the component in the pre-coated state. Then, the component is coated. Next, the center points of each of the at least first and second datum points are utilized for measurement of the selected portion on the component in the post-coated state. The pre-coated state measurements and the post-coated state measurements are then correlated for inspection purposes. | 12-24-2015 |
20150377042 | Leiteinrichtung fur eine Gasturbine sowie Gasturbine mit einer solchen Leiteinrichtung - The invention relates to a guide means ( | 12-31-2015 |
20150377043 | STEAM TURBINE VANE MANUFACTURING METHOD - A steam turbine vane manufacturing method including: a groove processing step for forming a protective part connecting surface ( | 12-31-2015 |
20150377044 | FIXED DIFFUSER VANES ASSEMBLY FOR GUIDING FLOW THROUGH A TURBOMACHINE, COMPRISING AN INTERNAL PLATFORM WITH INBUILT REINFORCEMENTS, AND ASSOCIATED TURBOMACHINE AND PRODUCTION METHOD - The invention relates to a fixed diffuser vanes assembly ( | 12-31-2015 |
20160003051 | ARTICLE WITH SECTIONS HAVING DIFFERENT MICROSTRUCTURES AND METHOD THEREFOR - An article includes a body that has a first section and a second section bonded with the first section. The first section is formed with a first material that has a first microstructure and the second section is formed of a second material that has a second, different microstructure. | 01-07-2016 |
20160008937 | TURBINE DRIVEN POWER UNIT FOR A CUTTING TOOL | 01-14-2016 |
20160010460 | PRETRENCHED ROTOR FOR GAS TURBINE ENGINE | 01-14-2016 |
20160010650 | SUSPENDED FAN GENERATING RANDOM MOVEMENT OF A MAIN BODY | 01-14-2016 |
20160017716 | A TURBOMACHINE COMPONENT WITH A STRESS RELIEF CAVITY - A turbomachine component with a stress relief cavity includes an airfoil and a platform. The airfoil has a trailing edge. The platform has a trailing edge region, a seal strip slot and a stress relief cavity. The trailing edge region supports at least a part of the trailing edge. The stress relief cavity extends inside the platform into the trailing edge region and is an extension of the seal strip slot. | 01-21-2016 |
20160017724 | VARIABLE THICKNESS TRAILING EDGE CAVITY AND METHOD OF MAKING - A method for forming an airfoil includes forming a ceramic core, forming a refractory metal core using additive manufacturing, joining the ceramic core and the refractory metal core to form a hybrid core, and casting the airfoil around the hybrid core. The ceramic core is used to define an internal cavity of the airfoil. The refractory metal core has an upstream end and a downstream end. The upstream end has a lateral thickness greater than a lateral thickness of the downstream end. The refractory metal core is used to define a trailing edge cavity within the airfoil. The trailing edge cavity is in flow communication with the internal cavity of the airfoil and trailing edge slots located on an outer surface of the airfoil near a trailing edge. This method provides for an airfoil having a trailing edge cavity of variably thickness and casting cores used for their manufacture. | 01-21-2016 |
20160017729 | STRUCTURAL GUIDE VANE SONIC SHAPE AND INSPECTION - A method of forming a guide vane is disclosed. The method includes forming a vane blank with sufficient material to fabricate the guide vane in accordance with any one of a plurality of different vane classes. The vane blank is inspected for material inconsistencies, and material is removed from the vane blank to form a desired guide vane in accordance with one of the plurality of vane classes. The inspection process includes disregarding at least one material inconsistency in a region of the vane blank that is re- moved to form the guide vane. | 01-21-2016 |
20160024945 | TURBOMACHINE BLADE - The present invention relates to a turbomachine blade ( | 01-28-2016 |
20160024952 | ASSEMBLY FOR SEALING A GAP BETWEEN COMPONENTS OF A TURBINE ENGINE - An assembly for a turbine engine includes a case, a guide vane arrangement and a flexible seal ring. The case extends circumferentially around an axis, and includes a first seal land. The guide vane arrangement is located radially within the case, and includes a second seal land. The seal ring at least partially seals a gap between the first seal land and the second seal land. The seal ring includes a first leg and a second leg that is connected to the first leg at a corner of the seal ring. The first leg is axially engaged with the first seal land. The second leg is axially engaged with the second seal land. | 01-28-2016 |
20160024971 | VANE ASSEMBLY - An annular support for a vane assembly including a vane having an aerofoil section with a radially inner base and a radially outer tip is provided. The annular support has a gas path surface which, in use, faces an annular gas path. In some aspects, the annular support is locally thickened by a projection extending radially from the gas path surface, the projection at least partly defining the perimeter of an aperture for receiving the base or tip of the aerofoil section. In some aspects, there is a liner lining the aperture and the liner extends from the aperture beyond the gas path surface. | 01-28-2016 |
20160024972 | NOSECONE SUPPORT - A example nosecone support of a gas turbine engine includes, among other things, a spar to extend radially from a nosecone. The spar is configured to attach to a case to support the nosecone. | 01-28-2016 |
20160032741 | SHOT PEENING DEFORMATION PROCESS FOR ASSEMBLING TWO PARTS OF A TURBOMACHINE - The main object of the invention is a process for deforming at least one part ( | 02-04-2016 |
20160059364 | WIDE GAP BRAZE - A method to fill a gap in a component according to one disclosed non-limiting embodiment of the present disclosure includes applying an alloy powder onto the component such that the alloy powder is received into a gap in response to vibrating of the component. | 03-03-2016 |
20160061218 | BLADE AND BLADE DIHEDRAL ANGLE - The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h. | 03-03-2016 |
20160069197 | TURBINE VANE WITH VARIABLE TRAILING EDGE INNER RADIUS - A turbine vane has an airfoil extending between an inner platform and an outer platform. The airfoil is hollow. A hollow within the airfoil extends between an inner leading edge to an inner trailing edge. An inner radius is defined at the inner trailing edge in a circumferential direction measured between walls which extend from the inner leading edge to the inner trailing edge. The inner radius varies along a radial length defined between the inner and outer platforms. A mid-turbine frame and a gas turbine engine are also disclosed. | 03-10-2016 |
20160084106 | ANTI-ICING CORE INLET STATOR ASSEMBLY FOR A GAS TURBINE ENGINE - A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing. | 03-24-2016 |
20160090851 | AIRFOIL ASSEMBLY WITH SPACER AND TIE-SPAR - An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil. | 03-31-2016 |
20160097370 | High-torque wind turbine - A high-torque turbine system receives and converts low to higher speed wind or airflow into mechanical work or electric power; consisting of a number of sail or airfoil blades or blade portions located near the outer periphery having extended moment arms for increased torque, that rotate around an center axis that is parallel to the airflow, wherein the blades receive wind directly, from a center deflector that directs wind received in the center outward to the blades, or from airflow directed externally from man-made, natural or structural sources, wherein the turbine system outputs mechanical work or electrical power. | 04-07-2016 |
20160102559 | ABRASIVE PROCESSING METHOD - The present invention provides an apparatus and method for processing a component surface by abrading the component surface using an abrasive surface. The apparatus comprises an abrasive surface which is rotatable about an axis extending parallel to said component surface. A support is provided for moving the abrasive surface or the component surface along a computer-generated toolpath and for applying a force between the abrasive surface and the component surface. The support increases the force between the abrasive surface and the component surface from a minimum force to a maximum force as the distance along the toolpath increases to maintain constant material removal from the component surface. | 04-14-2016 |
20160108734 | BLADING - A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades. | 04-21-2016 |
20160108887 | Horizontal and Vertical Axis Wind Generator - An embodiment of Horizontal and Vertical Axis Wind Generator (HVAWG) concept with the rotating wings, the gearbox, magnets attached to the wings and the wind tunnel cover with the same pole magnets is described. This feature allows for a number of improvements over the current state of the art including damage protection and the ability to remain operational during high wind conditions. In addition, the invention described here is scalable for cars, boats, motor cycles, camping cars, homes, offices, and power plants. | 04-21-2016 |
20160108930 | GAS GUIDING DEVICE AND FACILITY INCLUDING THE SAME - A gas guiding device includes: a first connection part ( | 04-21-2016 |
20160115800 | STATOR ASSEMBLY WITH PAD INTERFACE FOR A GAS TURBINE ENGINE - An inner platform structure of a stator vane for a gas turbine engine includes a male circumferential side opposite a female circumferential side, the male circumferential side includes a male wall received at least partially within a female wall of a neighboring stator vane at an interface with a pad at the interface. | 04-28-2016 |
20160115868 | TURBO-CHARGING SYSTEM OF AN ENGINE - A turbo-charging system of an engine comprising: a central body on which a turbine and a compressor, both keyed on a same shaft, are mounted, and at least two flange diffusers connected to two Venturi tubes comprised in the central body and ending with nozzles. The turbocharging system is interposed between the engine air filter and the engine throttle unit, the turbine receiving from the nozzles the engine intaking air at the output of the air filter whose flow determines the handling of the turbine and, through the shaft, of the compressor. | 04-28-2016 |
20160123167 | HOLLOW VANE, AND ASSOCIATED PRODUCTION METHOD - A hollow vane, includes a main portion, of which the cavity is closed by a cover, that is produced by expanding the main portion relative to the cover, for example by means of differential thermal expansion, then by placing the cover at the bottom of the opening of the cavity, before allowing the main portion to close again, closing a nesting between a protrusion at the bottom of the cover and a widening at the bottom of the opening. The disadvantages linked to the use of welding, glue or even assembly parts are as such avoided. | 05-05-2016 |
20160123170 | SEALING SYSTEMS - A sealing system for a turbomachine includes an annular seal defining a centerline axis and an inner diameter sealing surface. The sealing system also includes a turbomachine component radially inboard of the annular seal having a surface defined on an outer diameter surface. The sealing surface of the turbomachine component has a radius of curvature configured to be non-concentric with respect to the inner diameter surface of the annular seal in a cold sate. The radius of curvature of the surface is configured to be substantially concentric with respect to the inner diameter surface of the annular seal in a hot state. | 05-05-2016 |
20160123345 | COMPRESSOR IMPELLERS - An impeller includes a hub having a direction of rotation, a plurality of impeller blades extending from the hub, each blade having a downstream end, an upstream end, a leading surface facing the direction of rotation of the hub, and a trailing surface facing opposite to the direction of rotation of the hub. The impeller further includes a secondary flow reducer extending towards the downstream end and the upstream end of the at least one of the plurality of impeller blades, the secondary flow reducer defining first and second surfaces intersecting one of the leading surface and the trailing surface of the at least one of the plurality of impeller blades as well as a third surface between the first and second surfaces. | 05-05-2016 |
20160130946 | METHOD TO REPAIR VARIABLE VANES - A variable vane having an airfoil, an inner trunnion shaft and an outer trunnion shaft, with the outer trunnion shaft having a threaded hole and a groove extending around a circumference of the outer trunnion shaft is repaired by removing a portion of the outer trunnion shaft leaving a shaft stub. A repair detail is prepared having an outer peripheral shaft portion with a nominal outer diameter. The repair detail further has a pilot portion extending forwardly and having a smaller outer diameter than an outer diameter of the nominal outer diameter. The shaft stub has a remaining bore portion, which is a portion of the threaded hole. The pilot portion is sized to be received within the remaining bore portion. The pilot is inserted into the remaining bore portion. The repair detail is welded to the shaft stub. A repaired variable vane is also disclosed. | 05-12-2016 |
20160138409 | SHIELD - The present invention provides a method of making a metallic shield for shielding an edge of a component e.g. an aerofoil component such as a gas turbine blade or vane. The method comprises:
| 05-19-2016 |
20160138419 | COMPOSITE PIEZOELECTRIC APPLICATION FOR ICE SHEDDING - A flow surface comprises a composite material formed of a plurality of layers of the composite, and a piezoelectric actuator located within the layers or on an outer surface of the composite material. The piezoelectric actuator is actuatable to vibrate the composite material and one of inhibit ice build-up or shed ice which has formed. | 05-19-2016 |
20160138565 | WIND TURBINE FOR ELECTRIC VEHICLE - The invention relates to mechanical engineering and can be applied to the modernization of electric vehicles in order to conserve energy while in motion. An electric vehicle wind generator, containing a cylindrical chamber having wind wheels positioned therein. A shaft can be installed vertically, horizontally, or at any angle. The shaft is provided with a disk and the disk is provided with blades; the blades consist of a support beam, which is affixed to the disk, and of wings which are installed onto the beam with the help of arcs; a plurality of arcs is installed on each blade in accordance with the width and length of the blade; the arcs on the support beam can rotate, changing the angle of the wings relative to a base; the arcs are affixed by means of clamping bolts, the height of the arcs depends on the size of the turbine, and the arcs are installed beginning from the end of the blade; the base of the turbine is the component on which the turbine is installed. A small space, an air fairing, exists between the turbine and the base. The wider the blades, the larger the fairing distances between them, wherein without the fairing, an air lock is created, decreasing the efficiency of the turbine. The invention provides for an increase in the operating area of the turbine, and also for the possibility of installing the turbine on any components and assemblies. | 05-19-2016 |
20160138602 | Vacuum Pump - A vacuum pump is provided, which suppresses occurrence of a gas product in an exhaust side outlet of a thread groove and maintains pump performance over a long period. The vacuum pump includes inflow suppressing walls formed by widening greater an exhaust side end portion of ridge portions, extended along a gas exhaust direction on an outer circumferential surface of an inner circumference side stator, forward in a rotor rotating direction than an intake side end portion, the inflow suppressing walls suppressing retention of gas in exhaust side outlets of thread grooves engraved among the ridge portions. | 05-19-2016 |
20160146031 | TURBINE BLADE OR VANE HAVING A STEPPED AND BEVELED PLATFORM EDGE - A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided. | 05-26-2016 |
20160153314 | HUB OF AN INTERMEDIATE CASING FOR AN AIRCRAFT TURBOJET ENGINE COMPRISING DOORS WITH CONTOURED GEOMETRY | 06-02-2016 |
20160160690 | CMC Oxide-Oxide Mixer Design - An exhaust mixing system having an attachment flange configured to couple a lobed Oxide-CMC exhaust mixer to a turbine engine. The attachment flange includes an annulus and a plurality of projections extending from the annulus in a first direction that is substantially parallel to a central axis of the annulus. The annulus is configured to couple to the turbine engine and the plurality of projections is configured to couple to the lobed mixer. | 06-09-2016 |
20160160874 | AIRFOIL FOR INLET GUIDE VANE (IGV) OF MULTISTAGE COMPRESSOR - A vane for an Inlet Guide Vane (IGV) of a multistage compressor includes a root portion, a tip portion, and an airfoil extending therebetween. The vane is configured such that a ratio of the maximum thickness of the airfoil to a chord length (T | 06-09-2016 |
20160169015 | Steam Turbine Stationary Blade | 06-16-2016 |
20160169193 | COMPACT WIND POWER GENERATION SYSTEM | 06-16-2016 |
20160177728 | VANE STRUCTURE FOR AXIAL FLOW TURBOMACHINE AND GAS TURBINE ENGINE | 06-23-2016 |
20160177755 | HARDWARE GEOMETRY FOR INCREASING PART OVERLAP AND MAINTAINING CLEARANCE | 06-23-2016 |
20160177756 | AIRFOIL FILLET | 06-23-2016 |
20160194962 | TURBINE ENGINE GUIDE VANE | 07-07-2016 |
20160194971 | SEAL FOR TURBOFAN ENGINE | 07-07-2016 |
20160201468 | TURBINE AIRFOIL | 07-14-2016 |
20160201512 | GAS TURBINE ENGINE MID-TURBINE FRAME TIE ROD ARRANGEMENT | 07-14-2016 |
20160376898 | STEAM TURBINE NOZZLE SEGMENT FOR PARTIAL ARC APPLICATION, RELATED ASSEMBLY AND STEAM TURBINE - A steam turbine diaphragm nozzle segment, related assembly and steam turbine. Various embodiments include a steam turbine diaphragm nozzle segment having: a pair of opposing sidewalls; an airfoil extending between the pair of opposing sidewalls and integral with each of the pair of sidewalls, the airfoil having a single contact surface for directing a flow of working fluid through a flow channel; and a fill region integral with the airfoil and the pair of opposing sides, the fill region extending between the pair of opposing sides along an entirety of a length of the airfoil, the fill region for completely obstructing the flow of working fluid. | 12-29-2016 |
20160377092 | CANTILEVERED STATOR VANE AND STATOR ASSEMBLY FOR A ROTARY MACHINE - A stator vane assembly is provided. The stator vane assembly may comprise a stator vane, an outer shroud, and a spring. A first end of the stator vane may be fixed to an inner diameter (ID) surface of a vane platform. A slot may be disposed in a surface of the outer shroud, wherein a portion of the stator vane is configured to be located within the slot. In various embodiments, the stator vane may be configured to translate in a radial direction in response to a force between the stator vane and a rotor. In various embodiments, the spring may be configured to be coupled to an outer diameter (OD) surface of the vane platform, wherein the spring is configured to bias the ID surface of the vane platform toward the outer shroud. | 12-29-2016 |
20160377103 | ASSEMBLY WITH GUIDANCE OF AN ELONGATE THIN LIP IN AN ELONGATE NARROW SLOT AND APPLICATION TO THE ASSEMBLING OF AN AIR GUIDE ON A NOZZLE - An assembly of a first element with a second element includes an elongate thin lip belonging to the second element being inserted in an elongate narrow slot formed by three sides of an elongate flat plate fixed in parallel to a flat wall of the first element. At least one element forming a guide is secured to a long side of the elongate flat plate forming an edge of the slot. The element forming a guide includes a sliding surface extending in the continuation of the elongate flat plate and diverging from the flat wall away from the first element. The at least one element forming a guide cooperates with the lip so that the insertion of the lip into the slot begins with the sliding of the lip on the sliding surface and then continues as the lip advances, with progressive insertion of the lip into the slot. | 12-29-2016 |
20170234140 | AIRFOIL FOR A GAS TURBINE ENGINE | 08-17-2017 |
20180023572 | DEVICE FOR CONDITIONING FLOW OF WORKING FLUIDS | 01-25-2018 |
20180023583 | MULTI-SEGMENT TURBOCHARGER BEARING HOUSING AND METHODS THEREFOR | 01-25-2018 |
20180023625 | TIDAL CURRENT ENERGY GENERATING DEVICE | 01-25-2018 |
20220136398 | VANE WITH SEAL - An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed. | 05-05-2022 |