A propulsion system defining a longitudinal centerline extended along a longitudinal direction is provided. The propulsion system includes an inlet section configured to provide an oxidizer to a rotating detonation combustion system positioned downstream of the inlet section. The rotating detonation combustion system includes a nozzle assembly positioned to provide a flow mixture of oxidizer and fuel to a combustion chamber, a centerbody forming an inner wall of the combustion chamber, an outer wall at least partially surrounding the centerbody, wherein the inner wall and the outer wall define a volume of the combustion chamber; and an actuation structure coupled to the nozzle assembly. The actuation structure is configured to expand and contract to displace the nozzle assembly along the longitudinal direction to alter the volume of the combustion chamber.

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.

The present invention relates to an assembly for a turbomachine (1) comprising: a compressor (30), an isochoric combustion chamber (7), an isobaric combustion chamber (40), and a turbine (50).

A system and method is disclosed for the start-up and control of pulsejet engines and this system includes an Electronic Fuel Injection (EFI) system that further includes one or more electrically controlled fuel injectors that can be selectively operated for start-up and control of such pulsejet engines. According to the system and method, the rate and/or pattern of fuel delivery to pulsejet engines can be varied not only by controlling the amount of time the fuel injectors are open versus closed to define a duty cycle, but also with the capability to selectively disable one or more fuel injectors in the programmed manner for start-up and control of such pulsejet engines.

A constant volume combustion chamber for a turbine engine, includes an intake port, an exhaust port, and a first rotary shutter facing the intake and exhaust ports and configured to rotate around an axis in a first direction of rotation, the first shutter including an aperture intended to cooperate alternately with the intake and exhaust ports during the rotation of the first shutter. The chamber further includes at least one second rotary shutter facing the intake and exhaust ports and configured to rotate around the axis in a second direction of rotation opposite to the first direction, the second shutter including an aperture intended to cooperate alternately with the intake and exhaust ports during the rotation of the second shutter, the first and second shutters being synchronized and configured so that their respective apertures intersect alternately when both are facing the intake and when both are facing exhaust ports.

An engine (5) with a gas supply unit (10) that supplies combustion gas for driving purposes with linear reciprocal movement of a piston (12) is provided. The gas supply unit (10) includes a first combustion chamber (31) provided on a first side of the piston, a first gas outlet (17) that supplies high pressure combustion gas generated in the first combustion chamber for driving purposes, and a second combustion chamber (32) that is provided on a second side on the other side of the piston and generates a second force that moves the piston toward the first side. The engine (5) further includes a piston control unit (60) that controls the position of the piston against a first force of the piston that moves due to combustion in the first combustion chamber and the second force described above.

A propulsion system includes at least one rotating detonation actuator comprising: a flow path extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the flow path; an outer wall defining a radially outer boundary of the flow path; and at least one aircraft wing. The rotating detonation actuator is disposed in the aircraft wing. At least one rotating detonation wave travels through the flow path from the inlet end to the outlet end.