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.

A flow control system includes at least one flow surface; and at least one rotating detonation actuator including: an annulus extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the annulus; and an outer wall defining a radially outer boundary of the annulus. At least one rotating detonation wave travels through the annulus from the inlet end to the outlet end. Combustion gas from the at least one rotating detonation actuator modifies at least one flow characteristic at the flow surface.

A flow control system includes at least one flow surface; and at least one rotating detonation actuator including: an annulus extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the annulus; and an outer wall defining a radially outer boundary of the annulus. At least one rotating detonation wave travels through the annulus from the inlet end to the outlet end. Combustion gas from the at least one rotating detonation actuator modifies at least one flow characteristic at the flow surface.

A constant volume combustion system includes at least one combustion chamber having at least one admission port and an exhaust port. The system also includes at least one elastically deformable tongue made of ceramic matrix composite material forming an air admission valve, the tongue being present inside the chamber and being positioned facing the admission port, the tongue having a first end that is stationary relative to an inside wall of the chamber and a second end, opposite from the first end, the second end being free and movable relative to the inside wall.

A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one annulus inlet disposed in the annular tube proximate the inlet end, the annulus inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; at least one inlet fluid plenum disposed upstream of the annulus inlet; and at least one fluid inlet disposed upstream of the inlet fluid plenum. The fluid inlet is linearly offset from the annulus inlet.

A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one annulus inlet disposed in the annular tube proximate the inlet end, the annulus inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; at least one inlet fluid plenum disposed upstream of the annulus inlet; and at least one fluid inlet disposed upstream of the inlet fluid plenum. The fluid inlet is linearly offset from the annulus inlet.

A combustion method is disclosed, which includes the steps of mixing fuel and an oxidizer into a mixture, wherein fuel originates from a fuel manifold and the oxidizer originates from an oxidizer manifold, and combusting the mixture in a combustion chamber, the fuel manifold, the oxidizer manifold, and the combustion chamber forming parts of an injector assembly wherein each of the fuel and oxidizer manifolds communicates with the combustion chamber via a plurality of dedicated radially disposed Tesla valves around the combustion chamber each via a corresponding port with only one Tesla valve between the fuel manifold and the corresponding port on the combustion chamber and with only one Tesla valve between the oxidizer manifold and the corresponding port on the combustion chamber, wherein the plurality of Tesla valves substantially eliminate reverse flow of exhaust gases from the combustion chamber back to the fuel manifold or the oxidizer manifold.

A combustion method is disclosed, which includes the steps of mixing fuel and an oxidizer into a mixture, wherein fuel originates from a fuel manifold and the oxidizer originates from an oxidizer manifold, and combusting the mixture in a combustion chamber, the fuel manifold, the oxidizer manifold, and the combustion chamber forming parts of an injector assembly wherein each of the fuel and oxidizer manifolds communicates with the combustion chamber via a plurality of dedicated radially disposed Tesla valves around the combustion chamber each via a corresponding port with only one Tesla valve between the fuel manifold and the corresponding port on the combustion chamber and with only one Tesla valve between the oxidizer manifold and the corresponding port on the combustion chamber, wherein the plurality of Tesla valves substantially eliminate reverse flow of exhaust gases from the combustion chamber back to the fuel manifold or the oxidizer manifold.

The invention relates to a turbine, in particular a combustion gas turbine, which drives a high-speed generator for generating electricity, said turbine having a high efficiency. The turbine has at least one combustion chamber (6), which is provided with a fuel injection means (7) and an ignition device (8) and which supplies the turbine with a combustion gas. An external compressor (3) is associated with the turbine. Said compressor has a separate electric drive and is not connected to the turbine by means of a drive shaft. Furthermore, at least two combustion chambers (5) are provided for discontinuous, pulsed combustion and supply of the turbine.

The invention relates to a turbine, in particular a combustion gas turbine, which drives a high-speed generator for generating electricity, said turbine having a high efficiency. The turbine has at least one combustion chamber (6), which is provided with a fuel injection means (7) and an ignition device (8) and which supplies the turbine with a combustion gas. An external compressor (3) is associated with the turbine. Said compressor has a separate electric drive and is not connected to the turbine by means of a drive shaft. Furthermore, at least two combustion chambers (5) are provided for discontinuous, pulsed combustion and supply of the turbine.