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.

A method for operating a rotating detonation engine, having a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet and an outlet, wherein the method includes flowing liquid phase fuel along at least one wall of the radially inner wall and the radially outer wall in a direction from the outlet toward the inlet to cool the at least one wall and heat the liquid fuel to provide a heated liquid fuel; flowing the heated liquid fuel to a mixer at the inlet to reduce pressure of the heated liquid fuel, flash vaporize the heated liquid fuel and mix flash vaporized fuel with oxidant to produce a vaporized fuel-oxidant mixture; and detonating the mixture in the annular detonation chamber.

An engine having a compressor for generating a flow of pressurized oxidizer, a fuel mixing system in fluid communication with the compressor for mixing fuel with the pressurized oxidizer creating a fuel-oxidizer mixture, a combustion chamber adapted to receive the fuel-oxidizer mixture, at least one ignition system connected to the combustion chamber for igniting the fuel-oxidizer mixture inside of the combustion chamber, an exhaust port in fluid communication with the combustion chamber for receiving exhaust generated by combustion of the fuel-oxidizer mixture, and a turbine having a rotating shaft and a plurality of turbine blades connected downstream of the combustion chamber for receiving the exhaust whereby the fluid force of the exhaust through the exhaust port causes the turbine blades to rotate the shaft.

An engine that uses detonation for generating energy includes a housing; an inlet configured to inject a fuel mixture into an ignition region of the housing, the inlet being attached to the housing; an ignitor located in the ignition region and configured to ignite the fuel mixture; a deflagration to detonation, DDT, region in fluid communication and downstream from the ignition region; a pair of electrodes located in the DDT region and configured to apply nanosecond repetitive voltage pulses to the DDT region; and a detonation region, within the housing, in fluid communication and downstream from the DDT region. The nanosecond repetitive voltage pulses generate a non-thermal plasma that transition a combustion front propagation through the housing from a deflagration mode to a detonation mode.

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 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 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 (a) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.

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 (a) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.

A device serves for the repeated generation of explosions, in particular for the drive of an aircraft. It comprises: .square-solid.a combustion chamber (21), .square-solid.at least one feed line for feeding a flowable, explosive material or components which form an explosive material upon mixing to the combustion chamber (21); .square-solid.a discharge device for the targeted discharge of a gas pressure which is generated by way of ignition of the explosive material in the combustion chamber (21), .square-solid.a movable nozzle regulating element (26) for the partial or complete closure of the discharge device, .square-solid.an actuating element (25) which is configured to open the discharge device further after opening of the discharge device and during an outflow of explosion gases by way of the discharge device. Here, the discharge device has a plurality of part nozzles (40) for the discharge of the gas pressure, and a position of the part nozzles (40) can be set by way of the actuating element (25).

A device serves for the repeated generation of explosions, in particular for the drive of an aircraft. It comprises: .square-solid.a combustion chamber (21), .square-solid.at least one feed line for feeding a flowable, explosive material or components which form an explosive material upon mixing to the combustion chamber (21); .square-solid.a discharge device for the targeted discharge of a gas pressure which is generated by way of ignition of the explosive material in the combustion chamber (21), .square-solid.a movable nozzle regulating element (26) for the partial or complete closure of the discharge device, .square-solid.an actuating element (25) which is configured to open the discharge device further after opening of the discharge device and during an outflow of explosion gases by way of the discharge device. Here, the discharge device has a plurality of part nozzles (40) for the discharge of the gas pressure, and a position of the part nozzles (40) can be set by way of the actuating element (25).