Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A viscous damper is provided between the torque frame and the flex support at the location.

Abstract: A coolant pump for a coolant circuit of an internal combustion engine, the coolant pump having a pump housing in which is mounted a drivable shaft, to one end of which is attached an impeller-which has vanes extending into a suction chamber and is connected to a cover plate. Fluid can be drawn into the suction chamber through an intake port of the pump housing by joint rotation of the impeller and the cover plate and can be conveyed by the vanes into the pump housing. A guide plate, which is axially displaceable by an actuation unit, is disposed between the impeller and the cover plate. The guide plate has a contour corresponding to the impeller and a collar oriented toward the impeller. The coolant pump is characterized in that the guide plate has at least one opening.

Abstract: Several embodiments of a wobble plate motor include a disc mounted on a bent shaft. Driving the wobble plate so it revolves on a flat base causes the bent shaft to rotate and drive a generator or other work consumer. The wobble plate may be driven by a fluid stream impinging on the plate or by a blade assembly in a path of fluid movement. In one embodiment of a bladed motor, a shroud may direct the fluid stream so it more efficiently cooperates with the blade assembly.

Abstract: One or more variable pitch airfoils in fluid communication with a rotor of a fluid turbine can control the amount of energy directed to the rotor, and further control the amount of energy generated by the turbine. Varying the pitch of the airfoils may provide a means of controlling the power output of a fluid turbine without the need to control the pitch of the rotor blades, and may further provide a means of mitigating the effects of wind shear on the rotor. Variable pitch airfoils may also include a means of controlling the active power, reactive power and SCADA, of a group of fluid turbines.

Abstract: A method is disclosed for manufacturing a tie shaft for aero or land based gas turbine engine. The method includes flow forming a tie shaft preform to produce a tie shaft. In one example, the tie shaft includes a nickel alloy cylindrical wall having a length to diameter ratio of at least 6:1, wherein the diameter is an average outer diameter. The wall includes a minimum effective strain of 0.3 in/in (7.6 mm/mm), and a grain size is in the range of G4 to G16 per ASTM E112. The wall includes a roll formed threaded surface having a thread roughness of less than 1260 ?in (32 microns).

Abstract: A coolant pump for a coolant circuit of an internal combustion engine, the coolant pump having a pump housingin which is mounted a drivable shaft, to one end of which is attached an impeller-which has vanes extending into a suction chamber and is connected to a cover plate. Fluid can be drawn into the suction chamber through an intake port of the pump housing by joint rotation of the impeller and the cover plate and can be conveyed by the vanes into the pump housing. A guide plate, which is axially displaceable by an actuation unit, is disposed between the impeller and the cover plate. The guide plate has a contour corresponding to the impeller and a collar oriented toward the impeller. The coolant pump is characterized in that the guide plate has at least one opening.

Abstract: A bearing support for a turbocharger assembly is provided. The bearing support may include a cylindrical body with a tip end, a base end, and a conical outer surface extending from the tip end to the base end. The bearing support may also include an annular protrusion extending from the base end in a direction away from the tip end, and a stepped bore formed within the cylindrical body and passing from the tip end through the annular protrusion. The bearing support may also include a first conduit disposed within the cylindrical body and extending from an intersection of the annular protrusion and the base end of the cylindrical body toward the tip end.

Abstract: An exemplary fluid supply system for use on a turbomachine includes a turbomachine fluid container having a moveable barrier. A pressurized fluid is delivered to one side of the moveable barrier, and an opposing side of the flexible barrier communicates with a source of lubricant. Pressurized fluid is selectively delivered to the one side to move the moveable barrier between a flow-permitting position that permits flow from the source of lubricant to the turbomachine fluid container and a flow-restricting position that restricts flow from the source of lubricant to the turbomachine fluid container.

Abstract: Disclosed is a turbine for a machine for projecting abrasive for the surface treatment of objects. The turbine includes a first flange and a second flange, at least one blade element provided with a guide surface for receiving, guiding and projecting the abrasive, and a mounting system for releasable mounting of the blade element on the flanges. The mounting system includes a support element arranged between the blade element and the flanges and configured for a releasable mounting on the flanges and for supporting the blade element.

Abstract: A direct drive pump employs an on-off tool to attach the drive rod string to a floating pump drive shaft in both torsion and tension. The downward thrust on the drive shaft, as well as the weight of the drive rod string, is born by a thrust bearing in the drivehead at the surface. A floater pump is used with this direct drive pump to permit the free vertical movement of the drive shaft. When a tandem direct drive pump is employed a housing containing a tandem pump drive shaft connector connects the shafts in an upper and lower tandem pump to permit the two to freely move in the tandem direct drive pump.

Abstract: An example turbomachine cooling arrangement includes a pump configured to pressurize a first turbomachine fluid that is then communicated through a heat exchanger assembly to remove thermal energy from a second turbomachine fluid. A portion of the pump is configured to be housed within a gearbox housing of a turbomachine.

Abstract: A fuel pump includes a pump cover on one side of a housing, a cover end portion on the other side of the housing, a stator inside the housing, a rotor inside the stator, a shaft rotatable with the rotor, an impeller rotatable with the shaft to pressurize fuel inside the housing, a bearing portion provided in the cover end portion on its center axis to slidably support an end part of the shaft, and a relief valve capable of reducing a fuel pressure inside the housing. The cover end portion has an end surface located on its side opposite from the pump cover, and the relief valve includes a valve seat located on an opposite side of the end surface of the cover end portion from the pump cover.

Abstract: 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.

Abstract: A method is provided for pulling a bearing body off the rotor of a gas turbine having a casing, while the casing is closed. The method includes fixing a shaft extension on the relevant end of the rotor. In order to free the bearing body of the weight of the rotor, the method involves supporting the rotor and/or holding the rotor. The method further includes fitting sliding elements between the bearing body and the rotor, and moving the bearing body axially along the machine axis onto the shaft extension.

Abstract: A power system includes a gas turbine engine, which may include a gear box. The gear box may include a pipe connection configured to receive a removable pipe. The power system may also include a moveable support configured to fasten to the pipe connection to at least partially support the gear box.

Abstract: A power transmission system for increasing the rotational speed from a rotor of a wind turbine comprises a main shaft configured to be driven by the rotor, a support structure, and a gearbox. The support structure includes at least one bearing supporting the main shaft for rotation about the main axis, with no other degrees of freedom between the main shaft and support structure. The gearbox includes a gearbox housing rigidly coupled to the support structure and a gearbox input member coupled to the main shaft. The gearbox housing supports the gearbox input member for rotation about the main axis without any other degrees of freedom, and the gearbox input member is coupled to the main shaft with translational degrees of freedom in all directions and rotational degrees of freedom about axes perpendicular to the main axis.

Abstract: An assembly for a gas turbine engine, with a gearbox including a first portion having a first input gear coupled to a rotatable turbine shaft, a first output gear, and defining a first transmission path between the first input and output gears, and a second portion having a second input gear coupled to the turbine shaft, a second output gear, and defining a second transmission path between the second input and output gears different from the first transmission path. A fan rotor is coupled to the first output gear and a booster rotor is coupled to the second output gear on a same side of the gearbox than the coupling between the fan rotor and the first output gear. A method of assembling a drive for a fan rotor and a booster rotor in a gas turbine engine is also disclosed.

Abstract: The invention relates to an actuation system (100) for a propulsive unit including a nacelle, a turbojet engine, and an air circulation channel defined between the nacelle and the turbojet engine, the actuation system (100) including: a body and a connection device for attaching the body to the nacelle, the connection device enabling the body to move relative to the nacelle along two axes of rotation; a first member for moving a flap for controlling the airflow in the channel, the first member extending from the body and having a first point for attaching the first member to the lap; a second member for moving a thrust-reversing flap, the second member extending from the body and having a second point for attaching the second member to the flap, the body being arranged between the first and second attachment points; and a transmission device (40) having an input (42), a first output (44) connected to the first member (50), and a second output (43) connected to the second member (70), the transmission device (

Abstract: A back-up featherer for an engine arrangement having a main hydraulic actuator which angularly displaces propellers of a propeller assembly of the engine arrangement, and fluid supply lines for transferring hydraulic fluid between a hydraulic pressure power source located on a static structure of the engine arrangement and the main hydraulic actuator. The back-up featherer has a back-up actuator assembly for angular displacement of the propellers, the back-up actuator assembly rotating with the propeller assembly, a signal detector operatively connected to the back-up actuator assembly and rotates with the propeller assembly, and a back-up rotating coupling. A static side of the back-up rotating coupling is mounted to the static structure of the engine arrangement and communicates with a regulator located on a static structure of the engine arrangement. A rotating side of the back-up hydraulic rotating coupling rotates with the propeller assembly and communicates with the signal detector.

Abstract: A wind energy system comprising a wind turbine comprising a cowling surrounded by a diffuser and a plurality of inner rotor blades located inside of the cowling that rotate about an inner hub, a plurality of outer rotor blades positioned between the diffuser and the cowling that are counter-rotating relative to the plurality of inner rotor blades, a drive mechanism located within the inner rotor hub, a dynamic telescopic tower, and a tower support that connects the wind turbine to the dynamic telescopic tower.

Abstract: An example gear arrangement includes a gearbox shaft and a journal shaft. The journal shaft establishes an opening that receives an end portion of the gearbox shaft. The gearbox shaft is configured to rotate the journal shaft. The journal shaft is configured to selectively rotatably couple with another shaft. The journal shaft is allowed to align to the bearing surface while the gearbox shaft allows for misalignment between the accessory and gearbox drive.

Abstract: A method of assembling a rotor lock assembly for use in a wind turbine. The wind turbine includes a rotor rotatably coupled to a generator by the rotor shaft. The generator and the rotor shaft are supported from a bedplate frame. The rotor shaft includes a rotor lock disk. The method includes coupling a support frame to the bedplate frame. The support frame is positioned adjacent to the rotor lock disk. A plurality of lock pin housings are coupled to the support frame. Each lock pin housing of the plurality of lock pin housings is positioned with respect to the rotor lock disk. A plurality of lock pins is provided. Each lock pin of the plurality of lock pins is configured to engage the rotor lock disk. Each lock pin is coupled between a corresponding lock pin housing of the plurality of lock pin housings and the rotor lock disk to facilitate limiting a rotation of the rotor shaft.

Abstract: A lube pump has a housing with a flange extending radially outwardly from a body of the housing. At least one rotor is received within the housing, and a shaft for powering the rotor extends away from the flange. A retention plate is positioned on an end of the flange closing the housing. A first set of bolts secure the flange to the retention plate. A second set of bolts secure the flange to the gearbox. The two sets of bolts extend in opposed directions. A gearbox including such a lube pump is also disclosed and claimed.

Abstract: A turbomachine includes a tie shaft extending along an axis. Multiple rotors are mounted on the tie shaft. First and second clamping members are secured to the tie shaft and exert a clamping load between the rotors and clamping members at multiple interfaces. The clamping load at one of the interfaces includes a radial clamping load of greater than 5% of a total design clamping load at the one interface. In one example, one of the clamping members is provided by a hub including a first leg extending between first and second opposing ends. The first end provides a flange configured to be supported by the tie shaft. The second end includes first and second hub surfaces respectively extending in radial and axial directions. The first leg is inclined between 15° and 75° relative to the axial direction.

Abstract: A ram air turbine gearbox housing includes a housing body that has a first flange that defines a first plane and a second flange that defines a second plane that is transverse to the first plane. The housing body extends around an axis and has a first axial end and an opposite, second axial end that are each open to an internal cavity of the housing body. The housing body includes a radially-enlarged section at least partially defining an oil sump within the internal cavity of the housing body.

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool.

Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location.

Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan, a first compressor section, and a differential gear train that couples the fan and the first compressor section to the first shaft.

Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan.

Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location.

Abstract: Disclosed is a gas turbine and a gas turbine power facility which flexibly accommodate changes in layout of devices and in user's needs. This invention includes an air compressor 1; a turbine 2 coaxially coupled to the compressor 1; a turbine casing 4 accommodating the compressor 1 and the turbine 2; a compressor output shaft 23 for coupling rotary devices including a power generator 200, the compressor output shaft 22 protruding from the turbine casing 4 towards the compressor 1; and a turbine output shaft 23 for coupling the rotary devices, the turbine output shaft 23 protruding from the turbine casing 4 towards the turbine 2.

Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan.

Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan. A first compressor section is arranged in an axial flow relationship with the second compressor and the first and second turbines. A geared architecture operatively connects the first shaft and the fan. An inducer operative couples to the gear train.

Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.

Abstract: A fan drive gear system for a gas turbine engine includes a carrier that supports circumferentially arranged gears. A torque frame has circumferentially arranged fingers with each finger including a bore having a bore axis. A bushing is arranged in each bore and provides an aperture. At least one bushing has a bushing axis offset from the bore axis. A pin is disposed in the aperture and secures the carrier to the torque frame.

Abstract: The barring gear assembly is designed to drive in rotation a shaft of a turbo-alternator group having an axis of rotation A. The barring gear assembly includes a main wheel fixed on said shaft and defining lateral sides located on either side of the axis of rotation A, a barring gear module having a support piece on which is mounted a clutch system for coupling and uncoupling a secondary shaft to and from the main wheel, the secondary shaft being driven by an auxiliary motor, and the barring gear module being positioned on one of said lateral sides (C1) of the axis of rotation A.

Abstract: A torque converter includes an impeller with a plurality of impeller blades and a shell with a radial wall disposed radially outside of the blades. The converter also includes a cover fixed to the impeller shell to form a housing, and a turbine. The turbine includes a plurality of turbine blades and a shell with a radial wall disposed radially outside of the turbine blades. The turbine radial wall is arranged to frictionally engage the impeller shell radial wall. In some example embodiments, the turbine shell includes indented slots and the turbine blades include tabs disposed in the slots. In an example embodiment, the turbine blades are fixed to the turbine shell by brazing.

Abstract: A model helicopter includes a drive mechanism comprising a battery powered motor comprising a toothed motor shaft; a main rotor comprising a main shaft aligned with the motor shaft and including a main gear; and a reduction gear assembly comprising a lower section including four first gears arranged around the motor shaft, and four second gears smaller than the first gears, each second gear fixed to top of the first gear; an upper section including four third gears and four fourth gears each being smaller than the third gear and fixed to top of the third gear, the fourth gears being meshed with the main gear; and four shafts each axially passing through the fourth gear, the third gear, the second gear, and the first gear so that a revolution of the motor shaft rotates the main shaft via the first gears, the fourth gears, and the main gear.

Abstract: A turbine engine includes a housing supporting compressor, turbine sections, and an epicyclic gear train including a carrier. Sun gear and intermediate gears are arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubrication on the at least one of the sun gear and intermediate gears.

Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An inner rotor directly drives the shaft and includes an inner set of blades. An outer rotor has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system couples the outer rotor to the shaft and is configured to rotate the inner set of blades at a lower speed than the outer set of blades.

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

Abstract: A mechanical wind mill is provided for producing electricity through the power of wind energy. The wind turbine may include a plurality of gears which may be interchanged to control the rotational velocity of the wind turbine to most efficiently produce electricity. Including in the plurality of gears are the set of gears which may be slid along a shaft to best control the rotational velocity, but which may be changed as wind speed changes. The gears are mounted on a shaft, which is connected to a generator that is capable of producing electricity by rotation of said shaft.

Abstract: A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members are removably secured to one of the engine static structure and the flex support and second members are removably secured to the support structure. The first and second members are circumferentially aligned with one another and spaced apart from one another during a normal operating condition. The first and second members are configured to be engageable with one another during an extreme event to limit axial movement of the geared architecture relative to the engine static structure.

Abstract: An epicyclic gear train includes planetary gears rotatably mounted on spindles supported by an annular carrier and including axially spaced apart forward and aft sets of output teeth extending radially outwardly from a planetary gear hub and axially spaced apart forward and aft roller bearings disposed between planetary gears and spindles. The forward and aft roller bearings are axially aligned with or adjacent to spaced apart forward set of output teeth and input gear respectively. A ring gear meshes with forward set of output teeth and an external gear meshes with aft set of output teeth. An input gear fixedly attached to hub aft of aft set of output teeth and engaged with a sun gear. The output teeth, input gear, ring gear, external gear, and sun gear may all be helical. A turbofan gas turbine engine may include counter-rotatable first and second fan stages driven by a low pressure turbine through the gear train.

Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. The engine includes a combination of quantities providing beneficial operation.

Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique variable cycle gas turbine engine. Another embodiment is a unique adaptive fan system for a variable cycle turbofan engine having at least one turbine. Another embodiment is a unique method for operating a variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and related systems.

Abstract: A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed.

Abstract: [Object] To provide a drive device capable of increasing the drive precision of a movable member for generating power and capable of suppressing the generation of abraded particles. [Solving Means] A fluid machine (100) according to this embodiment has a structure in which a connecting rod as a movable member of a pump unit (20) is not connected to a circling shaft (13) of a motor unit (10) via a bearing but fixed to the circling shaft (13). In other words, the connection structure between the circling shaft (13) and the connecting rod is a structure using no bearings, and the integration, that is, the rigidity, of the circling shaft (13) and the connecting rod can be increased, which can increase the drive precision of the connecting rod. Further, since there are no sliding portions between the circling shaft (13) and the connecting rod, the generation of abraded particles can be suppressed and the reliability of the fluid machine (100) can be increased.

Abstract: A mechanical device includes a prime mover, and a number of rotating masses. Each mass is rotated simultaneously around centers of rotation in two or three planes that are at right angles to each other. The device includes one or more timing devices that are synchronized. The timing devices fix the relationship of the two simultaneous input rotations. In this device, internal energy creates an internal differential that is equalized by an external acceleration of the total mass, and internal energy is transferred to the exterior.