Abstract: The vane assembly has mating vane support and vane ring, the vane ring having a plurality of annularly interspaced radial loading elements which, when the vane ring is assembled to the vane support, are in a resiliently flexed state and exert corresponding annularly interspaced and outward-oriented radial loads against the vane support, thereby restraining relative radial movement between the vane ring and the vane support during operation of the gas turbine engine. The method includes flexing each of the radial loading elements into the resiliently flexed state simultaneously by sliding the radial loading elements against corresponding lead-in tapers. This can be achieved using a guide tool which includes a plurality of segments bearing the lead-in tapers and which is previously assembled to the vane support.

Abstract: Fans and methods of making and using the fans are disclosed. The fans can include a propeller positioned with in a housing, an air straightener, and a housing which is narrower at the outlet than at the propeller.

Abstract: An exemplary locating mechanism for locating a turbine bearing in a bore of a housing includes a conical pin having a pin axis where the conical pin includes a conical wall portion and a pin portion to locate a turbine bearing; a ball; and a socket disposed in a housing and extending between an opening of the housing and a bore of the housing, the socket having a socket axis where the socket includes a cylindrical surface and a conical surface. According to such a mechanism, disposition of the conical pin in the socket seats the conical pin along the socket axis and against the conical surface and disposition of the ball in the socket seats the ball along the socket axis and against the cylindrical surface. Accordingly, alignment of the ball with respect to the conical pin allows for transmission of force from the ball to the conical pin along the pin axis. Various other exemplary technologies are also disclosed.

Abstract: A method for assembling a gas turbine engine includes coupling a transition piece between a combustor liner and a nozzle assembly. The method also includes extending a first portion of a flow sleeve from the transition piece about at least a portion of the combustor liner. The method further includes coupling a second portion of the flow sleeve to the first portion of the flow sleeve such that the flow sleeve second portion extends from the flow sleeve first portion and at least partially about at least a portion of the transition piece. The flow sleeve second portion includes a scoop that cooperates with the transition piece to at least partially define a unitary cooling air passage that includes a unitary scoop-shaped opening. The scoop is oriented to introduce a substantially uniform cooling air flow to the transition piece.

Abstract: An axial fan assembly including a casing wall with a forward facing step formed therein. Formed on the surface of the step is a plurality of circumferentially spaced wedges which are formed and positioned so as to reduce the swirl flow within the clearance gap between the fan rotor and casing. The wedges are formed so the swirling backflow first encounters a circumferentially tapered face and then an abrupt axially oriented face, thereby substantially removing the swirl component. The wedges have a favorable effect on the flow stability of the fan, thereby extending its operating range. Variations include a fan rotor with a rotating shroud with an outwardly extending portion overlapping the step, and a bellmouth piece at the casing inlet.

Abstract: A technique is provided to facilitate pumping of fluids in a well environment. A submersible pumping system having a submersible pump incorporates features that manage thrust loads resulting from rotating impellers. The thrust reducing features cooperate with the action of the impellers in one or more pump stages to reduce forces otherwise acting on certain pump related components.

Abstract: A dual-powered airflow generator comprising: a primary fan motor powered from a primary power source and an auxiliary fan motor powered from a secondary power source. In one embodiment, the primary fan motor has a first drive shaft wherein operation of the primary fan motor causes a desired airflow at a design power of the primary power source. In a preferred embodiment, the auxiliary fan motor is powered from a secondary power source and has a second drive shaft mechanically coupled to the primary fan motor, wherein the auxiliary fan motor is configured to assist the primary fan motor in causing the desired airflow while the primary fan motor operates from the primary power source at a reduced power. In a preferred embodiment, the auxiliary fan motor is powered by a solar power generating device or other alternative energy source.

Abstract: The present disclosure relates to a vehicle transmission with fluid pump having a recirculation circuit. The recirculation circuit is configured to direct fluid from an outlet of the pump to an inlet during pump cycling. A method of manufacturing a fluid pump for use in a vehicle transmission is also disclosed.

Abstract: A method of machining a curved blade retention slot with electron discharge machining.

Abstract: A gas turbine engine assembly includes an inlet lip assembly, a fan containment case, and a front flange. The fan containment case surrounds a fan section and is positioned downstream from the inlet lip assembly. The front flange is mounted between the inlet lip assembly and the fan containment case and is positioned upstream from the fan section.

Abstract: Starter arrangement for high power rotating equipment strings with multiple compressors driven by a single turbine or motor includes multiple variable fluid drive torque converters (CSTCs) to start the compressors in a pressurized start. The string can use a single CSTC for each compressor or a single CSTC for more than one compressor with at least two CSTCs for a given string. The starting procedure is sequential. After the turbine or motor is started and brought up to speed, successive CSTCs are operated from zero to lock-up speed sequentially to start each compressor or group of compressors in turn. In order to cool the working fluid of the CSTCs, a single heat exchanger is provided and the working fluid of each CSTC in turn is circulated through the heat exchanger as they are sequentially started.

Abstract: A positioning and retaining element has a cylindrical rotary belt of substantially constant thickness, having an inner diameter substantially equal to the outer diameter of the stator to be capable of being mounted substantially coaxial clamped about the stator. The positioning and retaining element also has a number of support members projecting radially from the belt outwards and having each a support surface on the housing of the compressor, the support surfaces being located on the lateral surface of a fictitious rotary cylinder of same axis as the other belt and of diameter substantially equal to the inner diameter of the housing, such that the positioning and retaining element can be mounted clamped inside the housing.

Abstract: The invention relates to a fluid pump, in particular a liquid pump for a cooling and/or heating circuit of a motor vehicle, having a pump housing and having a rotationally fixed shaft, which is arranged in the pump housing, for an inner rotor which has an impeller wheel. According to the invention, it is proposed that the shaft is mounted at one side and, at its end remote from the bearing point, supports a bearing cap which engages at least partially around the shaft. The invention also relates to a method for producing a fluid pump of said type, in which method the shaft is fixed with its first end in a housing, in particular in a plastic housing, of the pump, the inner rotor of the pump is pushed onto the shaft and is secured axially by means of a bearing cap which is placed onto the shaft and is supported by the shaft.

Abstract: A rotary fluid device having a housing that defines a pumping chamber, a shaft disposed in the housing, and a rotor disposed in the pumping chamber and engaged with the shaft. The rotor includes a body which defines a bore that includes an oblique tapered surface. A pivot line is disposed along the tapered surface. The pivot line is a circumferential line at which the rotor pivots. A method for manufacturing a rotor includes turning an outer peripheral surface of the rotor. A bore is formed in the rotor. The bore includes an oblique tapered surface that has a pivot line disposed along the tapered surface, wherein the pivot line is a circumferential line at which the rotor pivots.

Abstract: A magnetic rotary vane pump is disclosed which includes a rotor disposed within a casing that comprises a cavity having an inlet and an outlet. The rotor includes at least one radial slot and at least one vane carried by the radial slot. The vane includes an inner edge directed towards a central axis of the rotor and an outer edge directed towards the casing. The inner edge of the vane is connected to a first magnet. The slot in the rotor includes an inner wall that abuttingly engages or faces the inner edge of the vane when the vane is fully received within the slot. The inner wall of the slot is connected to a second magnet. The two magnets are arranged so that like pole of the magnets face each other thereby biasing the vane out of the slot and against the inner wall of the casing as the rotor rotates. Accordingly, no spring or pin is required to bias the vane outward against the casing or into recesses or slots disposed in the casing wall.

Abstract: The invention relates to a method of producing a mini-fan that has a fan wheel equipped with fan blades (80) and an electric drive motor (61). The latter has an internal stator (90) and an external rotor (62). The rotor has a supporting part (64) made of plastic and is connected to a shaft (60), which part is implemented integrally with the fan blades (80). The external rotor (62) has at least one permanent magnet (72; 72?) having hard ferromagnetic particles (74). The plastic supporting part (64) is connected by plastic injection molding to the shaft (60), and by two-component injection molding to a plastic in which the hard ferromagnetic particles (74) of the rotor permanent magnet (72; 72?) are arranged, so that at least a portion of a transition zone (76) between the supporting part (64) and rotor permanent magnet (72; 72?) forms a materially engaging connection.

Abstract: A structure of a wind turbine selected from the group consisting of: a nacelle of a wind turbine, a hub of a wind turbine, and fairings of a wind turbine is described. The structure includes a structure housing comprising a concrete material.

Abstract: A steam turbine rotor is provided. The rotor includes at least one bearing section coupled axially to a steampath section comprising at least one end, said at least one end further comprising a flange and a bore, said flange and said bore configured to be coupled to the at least bearing section.

Abstract: A method is provided which manufactures a vane used for an oil-sealed rotary vacuum pump and having at least a part formed of a resin material, the method including: an oil impregnating process of immersing the vane into oil used for the oil-sealed rotary vacuum pump under a depressurized condition, the oil impregnating process being carried out before a finishing process of finishing the vane into a final shape.

Abstract: A support structure for a baseframe of a nacelle or the nacelle of a wind turbine is described. The wind turbine has a tower with at least one lower tower section, wherein the at least one lower tower section defines a vertical axis of the tower, a yaw bearing, the nacelle and a hub. The supports structure includes a lower side; an upper side; wherein the support structure has a support structure axis being defined as extending through the center of the lower side and the center of the upper side, and wherein the support structure is adapted to be mounted to a wind turbine such that the support structure axis is inclined relative to the vertical axis of the tower.

Abstract: A resinous shroud includes a resinous wall portion formed between a portion corresponding to a casing and a portion corresponding to a retaining member in a shroud portion when a resin material is filled from a gate portion. Thereby, a flow of the resin material to the portion corresponding to the casing from a portion corresponding to the gate portion can be dispersed by the resinous wall portion. Alternatively, an extended resinous wall portion may be formed in place of the resinous wall portion. Therefore, welds generated at the casing can be made small, and cambers generated at the casing can be suppressed.

Abstract: The described embodiments relate to fans units. One exemplary fan unit includes a housing supporting a motor. The fan unit also includes an impeller coupled to the motor and configured to be rotated by the motor.

Abstract: The hydraulic chamber (2) of a hydraulic swivel motor comprises a lateral opening which is closed by means of a cover (8). The seal of the hydraulic chamber with respect to the surroundings is achieved by a circumferential cover seal (12) which is produced by friction stir welding. The weld root (12?) extends to the vicinity of the faces of a sealing strip (10) which is provided between a shaft (4) and the cover (8) for separating two working chambers (A, B). This measure prevents leakage to the surroundings, on the one hand, and minimizes leakage between the working chambers (A, B), on the other hand.

Abstract: A pressure relief arrangement for a pump, which includes a pump housing assembly with a pumping chamber therein, is provided in the pump housing assembly of the pump and includes a section mounted for movement between a normal operating position and a venting position, further includes a shearing element adapted to retain the section in the normal operating position, the section being mounted such that upon pressure within the pumping chamber increasing to a specified level, the pressure acts on the section and the shearing element will fail thereby permitting movement of the section from the normal operating to the venting position.

Abstract: A power take-off system for a gas turbine engine includes a starter coupled to a second spool, and a clutch assembly coupled between the starter and a first spool, the clutch assembly configured to couple the first spool to the starter when starting the gas turbine engine assembly. A method of assembling a gas turbine engine assembly that includes the power take-off system, and a gas turbine engine assembly including the power take-off system are also described.

Abstract: Various methods are disclosed for manufacturing pump-heads having a housing enclosing at least one rotary member. In an exemplary method first and second housing portions are provided that collectively, when assembled, define a pump-cavity that accommodates the rotary member(s). The rotary member(s) is assembled into the pump-cavity, along with at least one soluble spacer of a defined thickness that corresponds to a desired clearance of the rotary member relative to the pump-cavity. The spacer contacts a surface of the rotary member facing a corresponding surface of the housing portion. The first and second housing portions are attached together to form the pump-cavity containing the rotary member(s). The soluble spacer is dissolved to provide the desired clearance of the rotary member in the pump-cavity. As the housing portions are attached together, e.g. by adhesive bonding, the spacer establishes the desired clearance of the rotary member(s) in the pump-cavity.

Abstract: The aim of the invention is to provide a superheated component of a steam turbine installation with high thermal and mechanical resistance. To this end, the component comprises a lining applied to a body of the component, on a hot side facing a steam chamber, said lining being adapted to the contour of the component body. According to the invention, the lining comprises a number of moulded parts, each moulded part comprising a metallic and ceramic composite layer formed from at least one metallic layer and at least one ceramic layer. The ceramic layer is used especially as a insulating layer, and the metallic layer is especially used as a support or for protection against abrasion and/or erosion.

Abstract: An exemplary method includes positioning a plurality of seal rings on a shaft operably coupled to a turbine wheel and inserting the shaft into a bore via axial inward movement wherein during insertion, an outer seal ring contracts and then expands along a chamfer to reach an outer seal seat. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: A vane ring assembly which includes a lower vane ring (23), an upper vane ring (31), one or more guide vanes (80) positioned at least partially between the vane rings, and a plurality of spacers (49, 50 or 59) positioned between the lower and upper vane rings (23, 31) for maintaining a distance between the lower and upper vane rings, the vane ring assembly being retained in a turbine housing (102) by a retaining ring (400) which is located in a groove (510) in the turbine housing.

Abstract: Fan system, in particular for a heat exchanger, which fan system has at least one receptacle for a fan drive unit, at least one housing wall, and at least one strut, in particular a number of struts which connect the receptacle to the housing wall, wherein the struts are arranged between at least one heat exchanger and at least one fan wheel, wherein at least one strut has a strut end section which is configured as a flow guiding face and has an angle ? with respect to a fan-wheel axis direction.

Abstract: A vane unit system having a plurality of vane units having at least one airfoil projecting from a base is modified by placing a hole in the base and receiving a pin which extends between adjacent bases of vane units. A series of modified bases form a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slit in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A method of fabricating an exhaust hood is provided for use with a turbine engine. The method includes providing an upper shell casing wherein the upper shell casing is fabricated from a composite material, and coupling the upper shell casing to a lower shell casing such that a turbine is housed within the exhaust hood, the shell casing is fabricated from a composite material. A turbine assembly is also provided.

Abstract: The invention relates to a rotor for a positive displacement rotary pump. The rotor comprises a hub with an aperture and a centre axis through said aperture and at least 2 lobes radially extending from said hub and in a direction essentially perpendicular to the axis of said hub. The rotor comprises a core of a first polymer material and a cover of a second polymer material, which second polymer material has a hardness which is lower than the first polymer material. The first and the second polymer materials are connected to each other. The hub or the major part of the hub is preferably provided by the core, whereas at least a part of the lobes is provided by the cover. The invention also relates to a method of providing the rotor and a pump comprising the rotor. The rotor has a high durability and provides an excellent sealing towards inner surface sections of the pumping house as well as towards an engaged rotor.

Abstract: A heat dissipation device comprises a heat sink, a fan, and a fan holder. The heat sink includes a base and a plurality of fins arranged on the base. The fan includes a frame having an engaging flange at each corner thereof. The fan holder configured for attaching the fan to the heat sink includes a main body having two opposite sidewalls extending upwardly from two opposite sides of the main body, a peg extending through the sidewall and movable in a direction perpendicular to the sidewall, and a handle capable of operating the peg. At least one of the engaging flanges of the fan is depressed by the peg towards the main body, thereby securing the fan on the fan holder.

Abstract: A restraint system (300, 300?, 500) for a vaned diffuser (225) of a turbocharger (100) or other fluid boosting device is provided that can reduce or eliminate losses. The system (300, 300?, 500) uses a structure to provide both a pressure load on the vaned diffuser (225) and a seal for the vaned diffuser (225). The structure can be a fluoroelastomer O-ring (350, 350?, 550). The O-ring (350, 350?, 550) can be positioned at least partially in a channel (325, 325?, 525) formed in at least one of the diffuser ring (206, 206?), the compressor housing (103) and the center housing (102).

Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor disposed downstream from the high-pressure compressor, and a high-pressure turbine coupled to the high-pressure compressor using a shaft, counter-rotating booster compressor coupled to the core gas turbine engine, the counter-rotating booster compressor comprising a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction, a single stage fan assembly coupled to the first rotor section, a drive shaft coupled between the low-pressure turbine and the fan assembly, and a gearbox coupled between the drive shaft and the second rotor section such that the low-pressure turbine drives the gearbox and such that the gearbox drives the second rotor section. A method of assembling the above turbofan engine assembly is also described herein.

Abstract: A gas turbine engine assembly is provided. The gas turbine engine assembly includes a core engine. The gas turbine engine assembly further includes a first rotor spool including a first fan assembly, an intermediate-pressure turbine, and a first shaft. The first fan assembly includes a single stage fan assembly coupled upstream from the core engine. The intermediate-pressure turbine includes a single stage turbine coupled downstream from the core engine. The first shaft extends between the first fan assembly and the intermediate-pressure turbine. The gas turbine engine assembly further includes a second rotor spool including a second fan assembly, a low-pressure turbine, and a second shaft. The second fan assembly includes a single stage fan assembly coupled upstream from the first fan assembly. The low-pressure turbine includes a single stage turbine coupled downstream from the intermediate-pressure turbine. The second shaft extends between the second fan assembly and the low-pressure turbine.

Abstract: A method of assembling a turbine includes positioning a turbine nozzle against a forward inner nozzle support extending from a rotor assembly, and coupling a cover to the forward inner nozzle support. The method also includes inserting a tab that extends from the cover within at least one aperture defined in the turbine nozzle.

Abstract: A method enables rotor assembly for a gas turbine engine to be assembled. The method includes providing a plurality of rotor blades that each include a dovetail, providing a rotor disc that includes a plurality of dovetail slots spaced circumferentially about the disc, partially inserting each rotor blade dovetail into a respective rotor dovetail slot, and seating the plurality of rotor blades in the respective rotor dovetail slot substantially simultaneously using an annular blade installation tool.

Abstract: A method for assembling a compressor for use with a turbine is provided. The method includes coupling at least a first stator ring to a second stator ring via at least one fastener sized to extend through at least one stator ring opening. The method further includes coupling a shield assembly to at least one of the first stator ring and the second stator ring to facilitate reducing convection and aerodynamic bleed losses of the at least one stator ring. The shield assembly includes a downstream surface, a retaining portion, and a contoured upstream surface extending from the downstream surface to the retaining portion.

Abstract: A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.

Abstract: An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.

Abstract: A turbofan integrally formed with a shroud and a method of manufacturing the same. The turbofan includes a rotating plate rotated by a driving motor, a plurality of blades having first ends connected to an outer peripheral portion of a front surface of the rotating plate while being arranged in a radial pattern, a shroud having an annular shape and being integrally formed with second ends of the blades, in which the shroud has an inner diameter equal to or larger than a diameter of the rotating plate, and an auxiliary rotating plate having a diameter larger than the diameter of the rotating plate and being fixed to the rotating plate. Since the inner diameter of the shroud is equal to or larger than the rotating plate, the turbofan is integrally formed with the shroud by a mold.

Abstract: Disclosed is a thermoelectric fan for use with radiant heaters, particularly catalytic heaters. The thermoelectric fan of the present invention comprises a housing sub-assembly coupled to a thermal plate sub-assembly, the housing sub-assembly comprising a shrouded circulating air moving member, such as a fan blade, powered solely by the conversion of heat from a separate heater into electricity via an integrated thermoelectric module. Also disclosed is a self-powered fan that can safely perform in hazardous atmospheres while converting radiant heat to circulate air. The thermoelectric fan of the present invention ensures that the air within the space to be heated is more effectively distributed and temperature gradients are minimized. Also disclosed are methods for assembling, installing and safe operation of the thermoelectric fan.

Abstract: A fan (16) draws air through a core (14) of a radiator (10) to which coolant from coolant passages in an engine (12) rejects heat. A shroud (28) having first and second parts (30, 32) in axial succession channels air that has been drawn through the core toward the fan. The first part (30) is a non-elastomeric ring, and the second part (32) has an elastomeric ring (34) having opposite axial ends, one of which telescopically fits to the non-elastomeric ring of the first part (30) and the other of which joins with a second non-elastomeric ring (36).

Abstract: A method for manufacturing a hardened casing for a vane pump is disclosed. The method includes providing a vane pump casing; hardening the casing by (i) cleaning the casing with a high pressure fluid containing abrasive material, (ii) loading the casing in a furnace, (iii) purging the furnace with an inert gas followed by purging the furnace with ammonia, (iv) conducting a first heating of the casing in the furnace at a first temperature of about 1200° F. for a time period of about 4 hours, (v) conducting a second heating of the casing in the furnace at a second temperature of about 1000° F. for a time period of about 4 hours, and (vi) cooling the casing and purging the furnace with an inert gas before removing the casing.

Abstract: A method for manufacturing a multi-stage compression type rotary compressor which avoids the replacement of parts to be used as much as possible to reduce costs and also which enables easily setting an appropriate displacement volume ratio between first and second rotary compression elements without increasing the size of the compressor outer housing. This is done by altering the inner diameter of the cylinder of one of the rotary compression elements without altering the thickness (or height) of this cylinder to set a displacement volume ratio between the first and second rotary compression elements to an optimum value in accordance with the alteration.

Abstract: A fan guide including a guide body, a central frame positioned at a central portion of the guide body and having an outer circumferential region, a plurality of motor fixtures formed at the outer circumferential region of the central frame for fixing a motor coupled with a fan, and at least three straight connecting frames for connecting the guide body and the central frame to each other, wherein one of intersection points among imaginary lines extending the three straight connecting frames is inside the outer circumferential region and the other intersection points among imaginary lines extending the three straight connecting frames are outside the outer circumferential region. By this arrangement, it is possible to decrease the degree of noise resulting from a blade passing frequency while destroying the regularity of a vortex shedding formed at each frame to reduce the interaction between a vortex flow and fan blades, thereby achieving a reduction in noise and flow loss.

Abstract: A twin cylinder rotary compressor including first and second cylinders; a crankshaft having first and second eccentrics mounted thereon, the first eccentric disposed within the first cylinder, the second eccentric disposed within the second cylinder; and a separator plate disposed between the first and second cylinders and having a first piece and a complementary second piece. Each of the first and second pieces includes an interior surface defining a semi-circular recess. The interior surface and the semi-circular recess of the second piece is complementary to the interior surface and the semicircular recess of the first piece, respectively, such that the semi-circular recesses combine to form a circular bore, which closely captures a portion of the crankshaft located between the first and second eccentrics.

Abstract: A twin cylinder rotary compressor including first and second cylinders; a crankshaft having first and second eccentrics mounted thereon, the first eccentric disposed within the first cylinder, the second eccentric disposed within the second cylinder; and a separator plate disposed between the first and second cylinders and having a first piece and a complementary second piece. Each of the first and second pieces includes an interior surface defining a semi-circular recess. The interior surface and the semi-circular recess of the second piece is complementary to the interior surface and the semicircular recess of the first piece, respectively, such that the semi-circular recesses combine to form a circular bore, which closely captures a portion of the crankshaft located between the first and second eccentrics.