Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor, a gear reduction, a first spool including a first compressor, a first turbine and a first shaft, and a second spool including a second compressor, a second turbine and a second shaft. The gear reduction includes a carrier and a plurality of gears. The plurality of gears include a sun gear, a ring gear, and a plurality of intermediate gears that engage the sun gear and the ring gear. At least two of the plurality of gears are double helical gears in meshed engagement.

Abstract: A differential includes a drive rotating body rotatable about a rotation axis, a planetary rotating body that is rotatable and is revolvable about the rotation axis, and a driven rotating body rotatable about the rotation axis. The planetary rotating body is made to mesh with each of the drive rotating body and the driven rotating body, so that a first speed reducer is constituted between the planetary rotating body and the drive rotating body and so that a second speed reducer is constituted between the planetary rotating body and the driven rotating body. The planetary rotating body is driven by an electric motor, and the drive rotating body is driven by a driving force from an engine. The intake camshaft is provided on the driven rotating body, and the exhaust camshaft is provided on the drive rotating body.

Abstract: A system can include an emitter structure connected to a reservoir containing a working material, wherein the working material is in electrical communication with a first electrode, an electrode opposing the emitter structure across a gap; and optionally a frame holding the emitter structure and the electrode.

Abstract: A check valve part includes: a valve seat hole into which hydraulic oil flows; a valve seat formed around the valve seat hole; a lateral hole formed to have an axis intersecting an axis of the valve seat hole; and a valve body provided so as to be separated from the valve seat or abutted against the valve seat. The valve timing adjustment device further includes a back pressure oil passage that communicates a space opposite to the valve seat with respect to the valve body with the lateral hole.

Abstract: The invention relates to a turbocharger which contains a bearing device which is arranged between a compressor and a turbine and which is designed to support a shaft. This bearing device has a bearing housing, in which an oil-lubricated bearing for supporting the shaft is arranged. The shaft has a slinger element extending in the circumferential direction for centrifugally dispersing lubricating oil. The bearing housing has an oil drainage channel for discharging the lubricating oil from the bearing housing. The inner region of the bearing housing forms an oil delimitation chamber, which is sealed off by seals arranged between the shaft and the bearing housing. The oil delimitation chamber has a deflection means which is formed in such a way that, during operation of the turbocharger, lubricating oil that is centrifugally dispersed by the slinger element is deflected by the deflection means and is conducted in the opposite direction to the seals.

Abstract: The present disclosure relates to a hydrogen electric hybrid power plant for a hovercar. The hydrogen electric hybrid power plant comprises a first-stage duct, a transition duct and a second-stage duct. An air outlet end of the first-stage duct is connected to the second-stage duct through the transition duct. A hydrogen reactor is arranged in the first-stage duct, and the hydrogen reactor is fixed with the first-stage duct through a plurality of supporting pieces A. A primary filter screen is arranged at a front end of the first-stage duct and fixed on the first-stage duct through a hoop, so that low-altitude sundries and dust are prevented from entering the reactor. A return pipe is arranged, and the problems of oxygen supply, heat dissipation and cooling and the like of the hydrogen reactor are solved through ducted airflow. A motor power supply requirement of a ducted fan is met.

Abstract: An exhaust energy recovery system (EERS) and associated methods for an engine are disclosed. An embodiment of an EERS, for example, includes an inlet duct that is configured to divert exhaust gas from an exhaust duct of the engine into the recovery system and an outlet duct configured to return the exhaust gas to the exhaust duct downstream of the inlet duct. The recovery system is configured to heat components or fluids associated with engine to operating temperatures. The recovery system may be part of a mobile power system that is mounted to a single trailer and includes an engine and a power unit such as a high pressure pump or generator mounted to the trailer. Methods of operating and purging recovery systems are also disclosed.

Abstract: A gas turbine engine includes a first bearing compartment and a seal assembly within the first bearing compartment that includes a rotatable seal seat, a gutter radially outward of the seal seat and fixed against rotation. The gutter includes a channel on its radially inner face. A second bearing compartment is also included. A scavenge pump is in communication with a first supply line configured to supply the first bearing compartment and a second supply line configured to supply the second bearing compartment. The gutter is in communication with the scavenge pump through a gutter scavenge line.

Abstract: A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

Abstract: The present disclosure describes an improved vehicle wheel rotation apparatus. The apparatus 300 comprises a combustion chamber 301, one or more turbines (302,311) and at least one non-return valve 306. An auxiliary attachment 305 is retrofitted at surface of each bar 304 present in each turbine. The auxiliary attachment 305 comprises 3-tube arrangement, wherein two tubes (305a, 305b) of the attachment 305 enable entry of jet of exhaust gases into the attachment 305 and further facilitate the plurality of bars 304 for initiating rotation of the runner 303. The jet of exhaust gases, exiting the attachment 305 through last tube 305c, comprises reducing cross-section near opening, enabling further increment in velocity of exhaust gas, resulting in thrust to the bar 304 to which the attachment 305 is already fitted, thus providing additional rotations to the runner 303 and eventually to one or more wheels of the vehicle.

Abstract: An oxidizing reactor apparatus having a heat exchange reactor having an input port, an entry channel in fluid communication with the input port, an exit channel in fluid communication with the entry channel via a plurality of pores and an output port in fluid communication with the exit channel, wherein the exit channel is in thermal communication with the entry channel, an engine in fluid communication with the heat exchange reactor and a heater engaged with the heat exchange reactor to initiate and maintain the oxidation of fuel within the heat exchange reactor. The disclosed heat exchange reactor may be configured to receive engine exhaust from the engine and oxidize fuel within the engine exhaust prior to expelling the engine exhaust. The heat exchange reactor may be further configured to utilize heat released by the oxidation of un-combusted fuel to increase the temperature of the engine exhaust leaving the engine.

Abstract: A combustion engine for a vehicle includes a first centrifugal device for varying timing of a first plurality of suction or relief valves with respect to the drive shaft. A driving disc is mounted idle on a first camshaft which controls the valves, and at least one driven disc is integral with the camshaft. Drive elements for transmitting motion from the driving disc to the driven disc are interposed between the two discs causing a relative rotation of the driven disc with respect to the driving disc when the rotation speed of the discs exceeds a predetermined threshold. A distribution system connects the drive shaft with the driving disc so as to cause the rotation thereof. A second gear meshes with a first gear so that rotation of the driving disc mounted on the first camshaft causes the rotation of the second camshaft to control other valves of the engine.

Abstract: A method and system may be used for storing energy in a geothermal system and recovering both the stored energy as well as thermal energy on demand. The geothermal system may include injection and production wells that are hydraulically coupled in a geothermal energy reservoir that behaves as a confined reservoir system with thermal energy transferring to fluid injected into the injection well and removed via the production well. Injection flow rate, injection pressure, production flow rate, production backpressure, or fluid residence time may be managed to control energy consumption or energy generation profiles of the geothermal system. During an energy storage mode, the injection flow rate exceeds the production flow rate thereby storing energy in the geothermal reservoir. During an energy recovery mode, production backpressure is reduced thereby releasing the stored energy and electricity is generated by removing the thermal energy from the fluid in a heat engine.

Abstract: A bi-metal actuator includes a shape memory alloy layer thermally actuated, a superelastic alloy layer fixed along to at least a part of the shape memory alloy layer, and at least one deformation sensor. The shape memory alloy layer has an initial shape at or below a transition start temperature TS and a final shape at or above a transition end temperature TE, has transitional shapes between the initial shape and the final shape which is formed according to the temperature between the transition start temperature TS and the transition end temperature TE of the shape memory alloy layer. The at least one deformation sensor is provided along at least a part of the superelastic alloy layer for measuring strain values of the superelastic alloy layer indicating the current form of the shape memory alloy layer.

Abstract: An air turbine starter that includes a housing with a divider structure dividing the housing into a wet chamber and an air chamber. The air turbine starter further including a bearing assembly, a turbine member, a first drive shaft, and a second drive shaft connecting the turbine member with a rotating assembly. A lubricant supply portion having at least one supply inlet fluidly coupled to the wet chamber and at least one supply outlet fluidly coupled to the bearing assembly whereby lubricant from the wet chamber can be supplied to the bearing assembly.

Abstract: The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (3), and a thermal drive system (1), including a first thermal engine (1A) and a second thermal engine (1B), which is configured to allow the vaned propulsion system (3) to be driven. The powertrain also includes an electric drive system (2) which allows the vaned propulsion system (3) to be driven, an electrical power supply system (4) including a battery (40) which allows the electric drive system (2) to be supplied with power. A clutch system (10) allows any or each of the thermal engines (1A, 1B) to be engaged in order to drive the vaned propulsion system (3), the clutch system (10) also being configured to allow any or each of the thermal engines (1A, 1B) to be disengaged from the vaned propulsion system (3).

Abstract: A gas turbine sealing interface to seal a gap between a transition duct and a turbine section component is provided. The transition duct includes an outlet exit frame including at least one fastener hole. The turbine section component includes a first stage vane structure including an upstream lip. A seal couples the outlet exit frame to the first stage turbine vane structure. An L-shaped rail including a flat portion and a lipped portion disposed perpendicularly to the flat portion. The seal is secured to the outlet exit frame via the L-shaped rail. An upstream portion of the seal includes a U-shaped cross section forming a first groove. A downstream portion of the seal comprises a groove which engages the upstream lip of the first stage turbine vane structure. A gas turbine engine including a radially inner sealing interface and a radially outer sealing interface is also provided.

Abstract: A straddled vehicle having an engine unit. The engine unit includes an engine body having a cylinder axis tilting forward, a radiator including a radiator core, a turbocharger including a turbine wheel and a compressor wheel, and an intercooler including an intercooler core. In a side view, at least a part of the intercooler core, a part of the turbine wheel and a part of the radiator core are within an area enclosed by a first connecting line, a second connecting line, an engine-body front-surface and a wheel rear-surface. In an upward-downward or forward-backward direction of the cylinder axis, the intercooler-core upper end is more upward than the turbine-wheel upper end, the intercooler-core front end is more frontward than the turbine-wheel front end, the intercooler-core lower end is more upward than the radiator-core upper end, and the radiator-core rear end is more frontward than both the turbine-wheel rear end and the intercooler-core rear end.

Abstract: A control system for active stability management of a compressor element of a turbine engine is provided. In one example aspect, the control system includes one or more computing devices configured to receive data indicative of an operating characteristic associated with the compressor element. For instance, the data can be received from a high frequency sensor operable to sense pressure at the compressor element. The computing devices are also configured to determine, by a machine-learned model, a stall margin remaining of the compressor element based at least in part on the received data. The machine-learned model is trained to recognize certain characteristics of the received data and associate the characteristics with a stall margin remaining of the compressor element. The computing devices are also configured to cause adjustment of one or more engine systems based at least in part on the determined stall margin remaining.