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.

A forced-induction device includes a turbine wheel, a turbine housing, and a connection pipe. The connection pipe includes a partition wall that partitions the inside of the connection pipe into a first passage and a second passage. When a cross section orthogonal to a rotation axis of the turbine wheel is viewed, a line segment extending from the distal end of the partition wall toward the upstream side in the flow direction of exhaust gas and defining a boundary between the first passage and the partition wall is a first downstream line segment. A line segment extending from the distal end of the partition wall toward the upstream side in the flow direction of exhaust gas and defining a boundary between the second passage and the partition wall is a second downstream line segment. The first downstream line segment and the second downstream line segment are parallel to each other.

A system and method for ram air intake for pulse combustion systems is disclosed that improves the ability of pulse combustions to ingest air into the inlet pipe when the pulse combustion system is moving in a direction opposite the direction the open end of the inlet pipe is facing and the system and method includes the ability to increase the thrust output from the pulse combustion system.

A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.

A module (4) for an aircraft turbomachine comprises an assembly of constant-volume combustion chambers, and including a first sub-assembly of first chambers succeeding each other along a given sense (76) and forming series of chambers (S1), and within each series (S1), a first ignition chamber (C1.1) located at one of both circumferential ends of the series is defined, the first ignition chamber (C1.1) being connected to the first directly consecutive chamber (C1.2) along the given sense (76) so as to supply the same with exhaust gases, and so forth up to the first chamber (C1.3) located at the other circumferential end of the series. In addition, a control device (46) is configured such that for all the first ignition chambers (C1.1), diametrically opposite two by two, the combustion cycles are simultaneously initiated. Finally, a second sub-assembly comprising second combustion chambers (C2.1-C2.3) is also provided.

The gas turbine comprises a compressor, a combustor, and a turbine. The method comprises: compressing air with the compressor and feeding compressed air continuously to the combustor, feeding fuel to the combustor, continuously firing the mixture of fuel and gas in the combustor, feeding combustion gases from the combustor to the turbine, and supplying at least a portion of the total amount of fuel that is supplied to the combustor intermittently.

The gas turbine comprises a compressor, a combustor, and a turbine. The method comprises: compressing air with the compressor and feeding compressed air continuously to the combustor, feeding fuel to the combustor, continuously firing the mixture of fuel and gas in the combustor, feeding combustion gases from the combustor to the turbine, and supplying at least a portion of the total amount of fuel that is supplied to the combustor intermittently.

A wastegate assembly includes a valve arm moveable between a first position and a second position to control flow of exhaust gas to a turbine housing interior of a turbocharger. The valve arm includes a proximal end, a distal end spaced from the proximal end, and a valve arm orientation projection spaced from the distal end and extending away from the proximal end. The wastegate assembly also includes a valve body coupled to the distal end of the valve arm that is moveable with the valve arm. The valve body includes a valve body orientation component, and the orientation projection of the valve arm extends toward and is orientable with the orientation component of the valve body to orient the valve arm relative to the valve body. The valve body is disposed between the orientation projection of the valve arm and the distal end of the valve arm.

A wastegate assembly includes a valve arm moveable between a first position and a second position to control flow of exhaust gas to a turbine housing interior of a turbocharger. The valve arm includes a proximal end, a distal end spaced from the proximal end, and a valve arm orientation projection spaced from the distal end and extending away from the proximal end. The wastegate assembly also includes a valve body coupled to the distal end of the valve arm that is moveable with the valve arm. The valve body includes a valve body orientation component, and the orientation projection of the valve arm extends toward and is orientable with the orientation component of the valve body to orient the valve arm relative to the valve body. The valve body is disposed between the orientation projection of the valve arm and the distal end of the valve arm.

A method and system of effervescent atomization of liquid fuel for a rotating detonation combustor (RDC) for a propulsion system is provided. The method includes flowing liquid fuel through a fuel injection port of a nozzle assembly of the RDC system; flowing a gas through the fuel injection port of the nozzle assembly volumetrically proportional to the liquid fuel; producing a gas-liquid fuel mixture at the fuel injection port by mixing the flow of gas and the flow of liquid fuel; flowing an oxidizer through a nozzle flowpath of the RDC system; producing an oxidizer-gas-liquid fuel mixture by mixing the gas-liquid fuel mixture and the flow of oxidizer within the nozzle flowpath; and igniting the oxidizer-gas-liquid fuel mixture within a combustion chamber of the RDC system.