Abstract: Examples of the present disclosure are related to systems and methods for utilizing effluent pipeline to generate energy. More particularly, embodiments disclose positioning a turbine within a bypass pipeline, wherein the bypass pipeline has a greater diameter than the effluent pipeline.

Abstract: In hydraulic systems having rotating-stationary component interfaces, a bore pressure regulating mechanism is provided to interact with the hydraulic fluid in a control volume to maintain a hydraulic fluid pressure in a longitudinal shaft bore at or approximately equal to a supply pressure when a gear shaft rotates within the control volume. In one aspect, the bore pressure regulating mechanism minimizes vortex flow of the hydraulic fluid induced by the rotation of the gear shaft. In another aspect, the bore pressure regulating mechanism provides a direct feed of pressurized hydraulic fluid proximate an opening of the longitudinal shaft bore through an end surface of the gear shaft, and thereby minimizes the opportunity for the hydraulic fluid to be forced into vortex flow by the gear shaft in the area of the longitudinal shaft bore.

Abstract: A system for adjusting and/or restraining a gearbox of a wind turbine includes a base component fixed to the gearbox and a vertical displacement device configured atop the base component. As such, the vertical displacement device is configured to apply a force to the base component. Accordingly, by lifting the vertical displacement device, a downward vertical force is applied to the base component so as to adjust (i.e. lower) the gearbox.

Abstract: A compressor arrangement has a common shaft, an axial compressor having at least a single-stage, and a radial compressor having at least single-stage. Assemblies of the, or each, axial compressor stage on the rotor side and assemblies of the, or each, radial compressor stage on the rotor side are attached to a common shaft (4). A ratio between a maximum diameter of the shaft (4) in the region of the axial compressor (2) and a minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.5 and 3.0.

Abstract: A pump including an outer housing having an outlet chamber with an outlet connector, and including a first part pump and a second part pump connected thereafter, with the first and second part pumps being arranged in the outer housing, a separating element which can be arranged between the first and second part pumps and a rotor shaft which is rotatably arranged in the first and second part pumps. In accordance with the invention, the outer housing, the first part pump and the separating element bound a first pressure chamber and the outer housing, the second part pump and the separating element bound a second pressure chamber and the first and second pressure chambers are designed and arranged such that the outlet chamber is formed as a single high-pressure region of the pump.

Abstract: An electrical power generating system is connected to a sewer for conveying waste water to a sanitary treatment station. Waste water is propelled through the sewer line by pumping equipment which simultaneously pulverizes most large objects carried by the waste water. The waste water drives one or more water-operated turbines. The turbines are operatively connected to electrical power generators for producing electrical power and dispersing the power through an electrical power transmission system.

Abstract: A geared architecture for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan shaft and a frame which supports the fan shaft, the frame defines a frame stiffness. A plurality of gears drives the fan shaft. A flexible support at least partially supports the plurality of gears, the flexible support defines a flexible support stiffness that is less than the frame stiffness. An input coupling to the plurality of gears, the input coupling defines an input coupling stiffness with respect to the frame stiffness.

Abstract: A multi-stage integrally geared compressor includes a first process stage, a second process stage and a gearbox for coupling the two process stages to each other at different rotational speeds. The gearbox further couples a compressor drive shaft to the two process stages at a further rotational speed, which is different from the rotational speeds of the process stages.

Abstract: A ventilation system (1) for air ventilation is disclosed, comprising a continuous duct (5) having openings at both ends, an air flow generator (2) arranged inside the duct to be rotatable around an axis of rotation so that, positioned in different rotational positions, the air flow generator is capable of producing a substantially axial air flow in each of the two directions through the duct, respectively, one or more registers arranged to be moveable between different positions, in at least one of which positions the one or more registers (6) leave the duct (5) open for air passage, whereas in another of the positions the one or more registers (6) substantially block the air passage through the duct (5), means for rotating the air flow generator (2), and means for moving the one or more registers. Furthermore, methods for controlled active and passive ventilation, respectively, through the duct of such a ventilation system (1) are disclosed.

Abstract: The inner wall surfaces on the discharge sides of a cooling area have arc-like curved surfaces. The curvature of upper-side inner wall surfaces above a boundary part and the curvature of lower-side inner wall surfaces below the boundary part are set to be different from one another, the boundary part being located above the center line of cooling devices.

Abstract: A torque converter, including: a cover; an impeller shell; a turbine shell; a turbine clutch formed by the turbine and impeller shells; and a stator formed of a single piece of material and including a protrusion extending in an axial direction and having a radial surface. In a drive mode: the cover transmits torque to the impeller shell; the turbine clutch is open; the radial surface forms an entirety of a portion of the stator closest, in the axial direction from the stator toward the turbine shell, to the turbine shell; and the radial surface is free of contact with the turbine shell. In a coast mode for the torque converter, at least a portion of the radial surface is in contact with the turbine shell or is separated from the turbine shell by a layer of fluid in contact with the radial surface and the turbine shell.

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The fan drive turbine includes a plurality of turbine rotors. A fan includes a plurality of blades rotatable about an axis and a ratio between the number of fan blades and the number of fan drive turbine rotors is between about 2.5 and about 8.5. A speed change system is driven by the fan drive turbine for rotating the fan about the axis. The fan drive turbine has a first exit area at a first exit point and rotates at a first speed. The second turbine section has a second exit area at a second exit point and rotates at a second speed, which is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

Abstract: A gas turbine engine includes a flex mount for a Fan Drive Gear System defined by a lateral and transverse stiffness relatonship.

Abstract: A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.

Abstract: An off axis hydraulic pump for an automatic motor vehicle transmission includes an integrated chain and sprocket assembly. A first, chain drive sprocket is mounted on a shaft driven by an input to a torque converter and a second, driven chain sprocket is attached to a stub shaft which drives the pump. A multi-link chain encircles the sprockets and transfers drive torque from the torque converter input to the stub shaft. The first, chain drive sprocket is retained on the input shaft by a retainer cap which includes seals between both the shaft and a torque converter housing. The second, driven chain sprocket is retained on the stub shaft by a snap ring or similar component.

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine 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 device for coupling two shafts by a gear mechanism includes a coupling part ending one of the two shafts. The coupling part is fitted concentrically into a complementary coupling part ending the other shaft. Splines of the coupling part have a constant profile along a median zone of the coupling part and which, in a first zone in continuation of the median zone, has a smaller thickness, between flanks of a spline, than a maximum thickness of the same spline in the median zone. Splines of the coupling part continue, beyond the first zone, as far as a centering zone on the same side as the first zone. The splines and the spline bottoms have, in the coupling zone between the centering zone and the first zone, a profile that continuously couples the splines and the spline bottoms to the surface of the centering zone.

Abstract: An impeller for pressurizing an intake air of an engine is provided on a left side end portion in a supercharger rotary shaft of the supercharger. The power from the engine is transmitted to a second sprocket, which is provided on a right side end portion of an input shaft of a speed increaser, through a chain to thereby allow the supercharger to drive. The second sprocket is removably fitted to the input shaft by means of a bolt. The supercharger rotary shaft, the input shaft, the second sprocket and the bolt are all accommodated in a supercharger casing. The supercharger casing has a right side end face formed with an access opening through which access can be made to the second sprocket and the bolt from an axial direction.

Abstract: Embodiments of the present application include a gas turbine assembly. The gas turbine assembly may include a solid wheel, a turbine aft shaft, and an aft joint connecting the solid wheel to the turbine aft shaft. The turbine assembly also may include a cover plate positioned between the solid wheel and the turbine aft shaft. The cover plate may be configured to direct a flow of compressor extraction fluid inboard through the aft joint and out the turbine aft shaft.

Abstract: An assembly for use in a turbine engine is provided. The assembly includes a first bucket, a second bucket circumferentially adjacent to the first bucket, a shroud extending between the first and second buckets, and an aerodynamic shell substantially encircling the shroud such that a cavity is formed between the aerodynamic shell and the shroud.

Abstract: In one embodiment, a marine current power generation device has rotary blades, rotating shaft, power generator, guide bearings, thrust collars and thrust bearings. The guide bearing has a second slide surface being slidable relative to the first slide surface of the rotating shaft. The thrust bearing has a fourth slide surface being slidable relative to the third slide surface of the rotary plate of the thrust collar. The materials of the first and third slide surfaces include ferrous materials, stainless materials, Ti, Ti alloy, Co, or Co alloy. The materials of the second and fourth slide surfaces include a resin material filled with a first fibrous member and a second fibrous member. The second fibrous member is smaller than the first fibrous member.

Abstract: A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.

Abstract: Shrouded turbine blisks and methods of manufacturing same are provided. A shrouded turbine blisk includes a central disk portion including an axis of rotation, an inner rim, a plurality of airfoils that extends radially outwardly from the inner rim; and a shroud integrally coupled to each of the plurality of airfoils. The shroud includes a plurality of circumferentially-arranged arcuate shroud segments defined at least in part by gaps positioned between adjacent shroud segments. The central disk portion, the inner rim, the plurality of airfoils, and the shroud are defined from a single billet of blisk material.

Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.

Abstract: A turbine system is provided having a first turbine casing and a second turbine casing, the first and second turbine casings together defining an inner wall. The turbine system further includes a first attachment flange extending from a surface of the first turbine casing within the inner wall and a second attachment flange extending from a surface of the second turbine casing within the inner wall. The first attachment flange defines a first aperture and the second attachment flange defines a second aperture. A pin extends through the first aperture and into the second aperture.

Abstract: A turbine driving a planet gear and an epicyclic gear train and including a planet pinion cage and a ring driving two propellers in rotation, is connected to the planet gear through a flexible sleeve surrounding a turbine support shaft rather than through a support shaft itself to achieve a flexible assembly with a limit stop position in contact with the shaft to limit parasite internal forces applied to the epicyclic gear train without tolerating a loose assembly or breakage of the sleeve due to a condition of the limit stop after a clearance has been eliminated.

Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.

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: A waste heat utilization apparatus is provided with a Rankine cycle and a power transmission mechanism that transmits power regenerated by an expander to an engine. The power transmission mechanism includes an expander clutch that interrupts or permits The transmission of the power from to expander to the engine. The expander includes a rotational speed sensor that detects a rotational speed of the expander. An increase in friction of the expander is detected on the basis of an increase in the rotational speed of the expander detected by the rotational speed sensor when the expander clutch is disconnected.

Abstract: An exhaust-gas turbocharger (1) having a shaft (2), which has a first centric bore (4) on an end face (3), a turbine wheel (5), which has a second centric bore (7) in the wheel rear side (6) thereof, a connection piece (8), which engages into the first and second bores (4, 7); and an integral connection device (9) for connecting the shaft (2) to the turbine wheel (5), wherein the connection piece (8) is hollow in form.

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: A fan device and an electronic device thereof are disclosed. The fan device is disposed in a casing of the electronic device and adjacent to a board of the casing, wherein the board has a first state and a second state. The fan device includes a plurality of fan blades, a shaft, and a ball. The shaft is connected to the plurality of fan blades and allows the plurality of fan blades rotating with the shaft, wherein at least one end of the shaft has a ball accommodating portion and an opening. The ball is disposed in the ball accommodating portion and limited by the opening for not separate from the ball accommodating portion. When the board is in the first state, a gap is between the ball and the casing. When the board is in the second state, the board and the ball touch each other.

Abstract: A method of mounting a gear train to a torque frame includes providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining mounts for interconnecting the walls. Spaced apart apertures are provided between the mounts at an outer circumference of the carrier. Gear pockets are provided between the walls and mounts extending to the apertures, and a central opening in at least one of the walls. A plurality of intermediate gears and a sun gear are inserted in the carrier. A first ring gear half is placed about the outer periphery of the intermediate gears, and attach a torque frame to the carrier.

Abstract: Provided is a rotation drive device including a shaft member extending in a first direction, and a rotating object configured to allow the shaft member to be inserted in the rotating object, and configured to rotate around an axis of rotation extending in the first direction relative to the shaft member. Opposite ends of the shaft member are fixedly joined to respective inner surfaces of a first partition wall and a second partition wall located on the opposite sides in the first direction of the rotating object.

Abstract: A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes a second mount feature that cooperates with the first mount feature for transferring torque there between. A method of disassembling a front architecture of a gas turbine engine includes the steps of accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon, removing the fasteners, and decoupling first and second mount features respectively provided on the central body support and the flex support.

Abstract: A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Abstract: A method for servicing a gas turbine engine includes disassembling a bearing compartment, providing access from a forward side of the gas turbine engine to a gearbox contained within said bearing compartment. The gas turbine engine provides a core flow path that extends from the forward side aftward in a core flow direction. The method includes servicing a component located within the bearing compartment. A method for servicing a gas turbine engine includes providing access from a forward side of a front center body assembly, and servicing a component located within a bearing compartment aft of the front center body assembly. The gas turbine engine includes a seal package located aft of a bearing package. A front wall is mounted to the front center body support and is removable from a front center body support to access at least one of the gearbox, the bearing package and the seal package.

Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend aftward and outward from the engine case to the fan case. A forward frame comprises a plurality of vanes radially across the gaspath. A torque box couples the fan case vanes to the forward frame. A transmission couples a shaft to a fan shaft to drive the fan. A fan bearing assembly couples a stationary forward hub structure to the fan shaft.

Abstract: A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.

Abstract: A turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air. A power turbine converts the gas stream flow into shaft power. The power turbine rotates at a first rotational speed. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The fan includes a tip diameter greater than about fifty (50) inches and an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.30 at a take-off condition.

Abstract: A cryogenic liquid turbine is provided, wherein, an impeller end of the rotor and a nozzle assembly are received into a cavity of a volute (1), and a main part of the volute (1) is put into a perlite cold box (3); an insulation pad (2) is used between the volute (1) and a machine housing (9) to insulate heat; an impeller outlet is connected to a diffuser pipe (20). A nozzle assembly is connected to the machine housing (9) by a nozzle compression flange (27); a nozzle compression plate adjusts a compactness of nozzle vanes (18) by a disc spring (25); a nozzle turntable (14) is axially and rotatably connected on a nozzle chassis (17), and adjusts the nozzle vane stagger angle by a adjusting mechanism passing through the volute (1); impeller shroud side seal is axially fixed on the nozzle compression flange (27), and a shaft seal (5) is axially fixed on a seal gas part (4); the seal gas part (4) and an oil seal (6) are axially fixed on the machine housing (9) by a bolt (15).

Abstract: A rotary machine includes a machine stator and a machine rotor rotatable relative to the machine stator and having a metal shaft portion, a composite impeller portion, and at least a first metal ring portion securing the composite impeller portion to the metal shaft portion, the metal ring portion having a first interface with the composite impeller portion and a second interface with the metal shaft portion.

Abstract: A fan system comprises a hub, a plurality of fan blades, a drive system, and a stationary tube. The hub is configured to rotate. The fan blades are mounted to the hub. The drive system comprises a rotatable hollow output shaft. The hollow output shaft is in communication with the hub, such that the drive system is operable to rotate the hub via the hollow output shaft. The stationary tube is inserted through the hollow output shaft. The stationary tube is configured to remain stationary as the hollow output shaft rotates. Wires and the like may be passed through the stationary tube, to reach an accessory mounted at the bottom of the stationary tube. The fan system may also include a detector, such as a heat detector, a smoke detector, or an accelerometer. The detector may power down the fan system in response to detecting certain conditions.

Abstract: The invention relates to a mobile rotary drive for a wind rotor of a wind power plant having a frame comprising a drive wheel for driving a segment of a rotor shaft of the wind power plant and a drive set which drives the drive wheel in rotation as a drive pinion, wherein the drive wheel is a friction wheel and interacts with a pressing device in such a way that the pressing device generates a force which presses the friction wheel onto the segment with the result that the friction wheel can apply a drive torque to the segment through friction, wherein a torque support for supporting an opposing torque to the drive torque generated by the friction wheel is also provided. Thanks to the friction wheel drive, there is no need for specific pre-equipping of the wind power plant. The invention makes available a mobile rotary drive which can be transported from one wind power plant to another.

Abstract: A ram air turbine system for generating electrical power in an aircraft when the system is exposed to an airstream exterior of the aircraft. The ram air turbine system includes a turbine, a housing defining an interior, a gearbox having a speed-increasing gear train, and a generator.

Abstract: The described embodiments relate generally to improving performance characteristics of a low profile fan. More specifically configurations having sloped fan blade edges are disclosed. By applying a gradual slope to each of the fan blades, performance of the fan can be increased without risking contact or rubbing between the fan blades and a fan housing. In some embodiments, the sloped fan blades can be configured to prevent contact when bearings of the fan include a certain amount of tilt play.

Abstract: Disclosed herein is a cover module, including: a cover covering an impeller connected to a rotating shaft; a housing receiving a driving module coupled with the cover and including the rotating shaft; and a coupling member coupling the cover with the housing, wherein the cover is provided with a coupling part in an axial direction of the rotating shaft, the housing is provided with a coupling part corresponding to the coupling part of the cover in the axial direction of the rotating shaft, and the coupling member is fixed to the coupling part of the cover and the coupling part of the housing.

Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.

Abstract: A rotor assembly, including at least one driven member, e.g., a compressor rotor, and at least one driving member, e.g., a turbine. At least one rotating thermal insulator rigidly attached to either the driven member or the driving member. A coupling feature that includes mating geometric surfaces on the driven member and the driving member, wherein the geometric surfaces are configured to allow radial sliding, relative centering, torque transmission, and axial constraint between the driven member and the driving member.

Abstract: A turbine drive may include a rotor that includes multiple turbine blades arranged in one or more turbine stages, as well as a stator cooperating with the rotor to direct fluid against the turbine blades and convert hydraulic, kinetic energy into rotational energy. The rotor may be fixed to the shaft to rotate synchronously therewith. The stator may be formed of multiple components that can be coupled together to define the stator and encompass the turbine blades of the turbine stages of the rotor. Two stator halves may each include vanes for positioning above and below a corresponding turbine stage, to direct fluid against the turbine blades. The stator may also be connected to a housing that encompasses the stator. Longitudinal slots and tabs on the stator and housing may hold the stator stationary relative to the housing.