An inlet guide assembly for a turbine receiving a pulsed flow, including a duct having an internal volume, and an inlet port, first outlet nozzle and second outlet nozzle each communicating with the internal volume. The inlet port is configured to receive at least part of the pulsed flow. The first and second outlet nozzles each define a respective nozzle area communicating between the internal volume and a flow path of the turbine. The first and second outlet nozzles are spaced from one another with the first outlet nozzle located closer to the inlet port than the second outlet nozzle relative to a flow direction through the duct, the nozzle area of the first outlet nozzle being smaller than the nozzle area of the second outlet nozzle. A compound engine assembly and method of introducing a pulsed flow into a flow path of a turbine are also discussed.

A rotary engine includes a housing having a working cavity, a shaft, the shaft having an eccentric portion, a rotor having a first axial face, and a second axial face opposite the first axial face, the rotor disposed on the eccentric portion and within the working cavity, the rotor comprising a first cam on the first axial face, the first came having an eccentricity corresponding to the eccentricity of the eccentric portion of the shaft, and a cover integral with, or fixedly attached to, the housing, the cover comprising a plurality or rollers, each roller engaged with the cam, wherein the cam guides the rotation of the rotor as the rotor rotates within the working cavity and orbits around the shaft.

The present invention provides a rotary engine comprising: a housing provided with three lobe accommodation parts; a rotor which is provided with two lobes continuously accommodated in the lobe accommodation parts, has an intake storage part communicating with an intake port provided on the front surface-side, and has an exhaust storage part communicating with an exhaust port provided on the rear surface-side; an intake-side housing cover provided with an intake hole communicating with the intake storage part; an exhaust-side housing cover provided with an exhaust hole communicating with the exhaust storage part; and a crankshaft, wherein the flow of an exhaust gas into a stroke chamber during an intake stroke is reduced by preventing the exhaust storage part, at a portion of a section in which the exhaust port is open, from communicating with the exhaust hole during the intake stroke.

A reciprocating, internal combustion engine comprises a turbine connected to the exhaust port of a cylinder. The turbine receives exhaust gas from the cylinder and a power capture means transfers the power generated by the turbine to at least one of power storage device, a turbocharger, a compressor, and vehicle locomotion.

A rotary engine that starts and operates on compression-ignition of a heavy fuel without a secondary ignition source. The rotary engine includes a rotor housing that forms an epitrochoidal-shaped chamber having linear side portions extending between rounded end portions. A three-flanked rotor is disposed in the chamber to rotate and operate in a manner similar to that of a common Wankel-style rotary engine. The rotor and chamber are configured to provide a compression ratio sufficient to produce compression-ignition of a heavy fuel. The rotor includes apex seal and side seal mounting blocks formed from hardened materials and that are simply removable from the rotor for replacing apex and side seals. The apex seals may include multiple non-parallel seal members at each apex and the apex seals and the side seals may overlap or intersect a corner seal to increase sealing under high compression loads produced by the rotor/chamber configuration.

A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.

A housing for a rotary engine has: a peripheral wall defining two end faces and an inner face transverse to the two end faces; two side walls sealingly engaged to the two end faces of the peripheral wall, a core of a side wall of the two side walls having a core face, the core face having a cavity section facing the rotor cavity and an abutment section annularly extending around the cavity section, the abutment section facing an end face of the two end faces, the abutment section having a flared portion flaring away from the end face; and a coating on the core face, the coating made of a material harder than a material of the core of the side wall, the coating covering the cavity section and ending at a coating edge located on the flared portion, the coating edge free of contact with the end face.

A rotary engine comprised of a pair of counterrotating rotors within a non-rotating outer housing. Each of the rotors is coupled to a common power shaft, one directly and the other through a reversing gear arrangement. Both are driven by the hyper-expansion of combustion gases in a repeating combustion cycle. Each has a generally circular, nearly frictionless working surface perpendicular to the power shaft axis. Each rotor surface defines chambers which rotate past each other. Within such chambers, compressed air and fuel are introduced, mixed, ignited, allowed to hyper-expand (and thus cause the rotation) and exhausted. The power shaft may be connected to a conventional clutch, torque converter, gearbox, differential, alternator or a similar system.

The present invention provides a fluid transfer apparatus comprising: a rotating shaft comprising a rotation unit extending along an axial direction and a first eccentric unit and a second eccentric unit disposed to be spaced apart from each other along the axial direction; a first rotor housing forming a first fluid compression space in the shape of an epitrochoid curved surface; a second rotor housing forming a second fluid compression space in the shape of an epitrochoid curved surface, and positioned to be spaced apart from the first rotor housing along the axial direction; a first rotor disposed in the first fluid compression space so as to delimit the first fluid compression space into multiple variable-displacement spaces, and coupled to the first eccentric unit while surrounding the first eccentric unit in the radial direction of the first eccentric unit; and a second rotor disposed in the second fluid compression space so as to delimit the second fluid compression space into multiple variable-displacement spaces, and coupled to the second eccentric unit while surrounding the second eccentric unit in the radial direction of the second eccentric unit.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.