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.

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.

This patent discloses thrust vectoring ignition chamber engine. Thrust vectoring ignition chamber used in this engine is an annular cylinder having nozzles mounted in a way such that during fuel suction phase they are sealed and during ignition of fuel they are unsealed so that hot jets of ignited fuel escaping through nozzles cause coupled rotatory motion on the ignition chamber. Engine uses cam operated specially designed bilaterally operated double action scotch-yoke mechanism which facilitates two phase suction and compression of fuel and facilitates separation of fuel valve from ignition chamber. Flywheel mounted on extension of ignition chamber functions as output of the engine. Each half rotation of flywheel completes three phases namely fuel/air suction, compression and combustion. Thus this engine fires for every half revolution and therefore can give improved power boost.

This patent discloses thrust vectoring ignition chamber engine. Thrust vectoring ignition chamber used in this engine is an annular cylinder having nozzles mounted in a way such that during fuel suction phase they are sealed and during ignition of fuel they are unsealed so that hot jets of ignited fuel escaping through nozzles cause coupled rotatory motion on the ignition chamber. Engine uses cam operated suitably modified 3-screw compressor for suction and compression of fuel and therefore do not require piston mechanism. Flywheel mounted on extension of ignition chamber functions as output of the engine. Each half rotation of flywheel completes three phases namely fuel/air suction, compression and combustion. Thus this engine fires for every half revolution and therefore can give improved power boost.

A computer-implemented method for multi-mode operation of a combustion system, a combustion system, and a heat engine are provided. The method includes initializing combustion of a fuel/oxidizer mixture, determining whether conditions at the combustion system meet or exceed a first threshold operating parameter, transitioning to detonation combustion of the fuel/oxidizer mixture if conditions at the combustion system meet or exceed the first threshold operating parameter, and maintaining or increasing fuel flow through a deflagrative fuel circuit if conditions at the combustion system do not meet or exceed the first threshold operating parameter.

A computer-implemented method for multi-mode operation of a combustion system, a combustion system, and a heat engine are provided. The method includes initializing combustion of a fuel/oxidizer mixture, determining whether conditions at the combustion system meet or exceed a first threshold operating parameter, transitioning to detonation combustion of the fuel/oxidizer mixture if conditions at the combustion system meet or exceed the first threshold operating parameter, and maintaining or increasing fuel flow through a deflagrative fuel circuit if conditions at the combustion system do not meet or exceed the first threshold operating parameter.

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.

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.

A turboprop engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system, an air duct in fluid communication with an environment of the aircraft, a heat exchanger received within the air duct having coolant passages in fluid communication with the liquid coolant system and air passages air passages in fluid communication with the air duct, and an exhaust duct in fluid communication with an exhaust of the internal combustion engine. The exhaust duct has an outlet positioned within the air duct downstream of the heat exchanger and upstream of an outlet of the air duct, the outlet of the exhaust duct spaced inwardly from a peripheral wall of the air duct. In use, a flow of cooling air surrounds a flow of exhaust gases. A method of discharging air and exhaust gases in an turboprop engine assembly having an internal combustion engine is also discussed.