A dynamic pressure exchanger configured for a combustion process includes a seal plate and a rotor assembly. The rotor assembly is mounted for rotation relative to the seal plate about a central axis of the dynamic pressure exchanger.

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.

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.

An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

The present invention discloses an internal combustion engine, comprising a compressor, a combustion chamber, a pipeline, a spray pipe, an oil feeder, a driving device, a first safety device, a second safety device, an electric ignition device, a rack, a first bracket arranged on a top of the rack, a second bracket arranged on an upper part of the rack, a third bracket arranged on a lower part of the rack and a fourth bracket arranged on a left part of the rack. The compressor comprises an inner shell and an outer shell, wherein the inner shell comprises an upper pressing plate and a cylindrical plate; the cylindrical plate can move up and down in the cylindrical plate slot; and an outlet is formed in a non-protruding part at the bottom of the outer shell. The internal combustion engine has simple structure and high efficiency.

A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.

A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.

Provided is a supercharger (11) comprising: a hollow housing (15); a rotating shaft (14) rotatably supported by the housing (15); a turbine (12) provided at one axial end of the rotating shaft (14); and a compressor (13) provided at the other axial end of the rotating shaft (14). A threaded section (41) and a circular column section (42) are axially arranged at the other end of the rotating shaft (14). A threaded hole (43) with which the threaded section (41) is engaged and a fitting hole (44) in which the circular column section (42) is fitted are axially arranged in the compressor (13). The axial length of the circular column section (42) and the fitting hole (44) is set to be greater than the axial length of the threaded section (41) and the threaded hole (43).

Provided is a supercharger (11) comprising: a hollow housing (15); a rotating shaft (14) rotatably supported by the housing (15); a turbine (12) provided at one axial end of the rotating shaft (14); and a compressor (13) provided at the other axial end of the rotating shaft (14). A threaded section (41) and a circular column section (42) are axially arranged at the other end of the rotating shaft (14). A threaded hole (43) with which the threaded section (41) is engaged and a fitting hole (44) in which the circular column section (42) is fitted are axially arranged in the compressor (13). The axial length of the circular column section (42) and the fitting hole (44) is set to be greater than the axial length of the threaded section (41) and the threaded hole (43).

A combustor for a rotating detonation engine includes a radially outer wall extending along an axis (A); a radially inner wall extending along the axis (A), wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a first passage for feeding at least one of the fuel and the oxidant along a first passage axis (a.sub.1) to the inlet; a second passage for feeding at least one of the fuel and the oxidant along a second passage axis (a.sub.2) to the inlet, wherein the second passage axis is arranged at an angle (α) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.