A wave rotor assembly includes a wave rotor combustor and an exit duct. The wave rotor combustor includes an aft plate formed to include an exit port and a rotor drum mounted for rotation relative to the aft plate. The rotor drum is formed to include a plurality of rotor passages arranged to align with the exit port during rotation of the rotor drum. The exit duct is coupled to the aft plate and defines a passage arranged to receive exhaust gasses flowing through the exit port.

A rotating detonation engine includes an annulus that defines a volume in which a mixture of an oxidizer and a fuel detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows. The rotating detonation engine further includes a wave arrestor positioned upstream from a location of detonation and configured to reduce a magnitude of a pressure wave traveling upstream from the location of detonation.

A rotating detonation engine includes an annulus that defines a volume in which a mixture of an oxidizer and a fuel detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows. The rotating detonation engine further includes a wave arrestor positioned upstream from a location of detonation and configured to reduce a magnitude of a pressure wave traveling upstream from the location of detonation.

Rotor systems are driven by jet engines arranged at the tip of a rotor that includes a structure that turns on a rotational axis. A jet stream generated by a jet engine produces a thrust force orthogonal to a rotor radius to motivate rotation. Methods presented include those which take advantage of the intrinsic centrifugal forces present in the rotor to convey gaseous fuel to the engine. Liquefied fuel from a source reservoir is evaporated into a gaseous state and made subject to centrifugal force causing it to move radially outward to a detonation type jet engine. These methods further include special process for mixing fuel with oxidizer and treating fuel or/and fuel mixtures to improve their detonation capacity.

A disc turbocharger includes a multi-disc engine in which each disc engine includes a turbine blade, a compressor blade, and a bearing without requiring a shaft between the turbine blade and the compressor blade. The power produced by each turbine blade is consumed by its own joined compressor. The disc turbocharger has a multi-disc engine that works as a multi-stage turbocharger with a smaller size and no piping between the turbochargers. The disc turbocharger uses a waste spool valve for control of the.

A disc turbocharger includes a multi-disc engine in which each disc engine includes a turbine blade, a compressor blade, and a bearing without requiring a shaft between the turbine blade and the compressor blade. The power produced by each turbine blade is consumed by its own joined compressor. The disc turbocharger has a multi-disc engine that works as a multi-stage turbocharger with a smaller size and no piping between the turbochargers. The disc turbocharger uses a waste spool valve for control of the.

A rotating detonation combustion system is generally provided. The rotating detonation combustion system includes an outer wall, an upstream wall, and a radial wall. The outer wall is defined circumferentially around a combustor centerline extended along a lengthwise direction. The outer wall defines a first radius portion generally upstream along the outer wall. A second radius portion is defined generally downstream along the outer wall and a transition portion is defined between the first and second radius portions. The first radius portion defines a first radius greater than a second radius at the second radius portion. The transition portion defines a generally decreasing radius from the first radius portion to the second radius portion. The upstream wall is defined circumferentially around the combustor centerline and is extended along the lengthwise direction and inward radially of the first radius portion of the outer wall. An oxidizer passage is defined within the upstream wall. A combustion chamber is defined downstream of the upstream wall and radially inward of the outer wall. The radial wall is coupled to the outer wall and the upstream wall. A fluid injection opening is defined through at least one of the radial wall or the outer wall adjacent to the combustion chamber.

A cavity stabilized detonation combustor assembly for a rotating detonation engine includes opposing inner and outer walls that are radially spaced apart from each other and that both extend around a center axis of the rotating detonation engine. Detonations in the rotating detonation engine rotate around the center axis of the rotating detonation engine. The assembly also includes opposing leading and trailing cavity walls that are coupled with the inner and outer walls and which radially extend away from the center axis, and an axial wall that is coupled with and connects the leading and trailing cavity walls with each other. The axial wall and the leading and trailing cavity walls define a detonation stabilizing cavity in which detonations of the rotating detonation engine occur and are stabilized.

A cavity stabilized detonation combustor assembly for a rotating detonation engine includes opposing inner and outer walls that are radially spaced apart from each other and that both extend around a center axis of the rotating detonation engine. Detonations in the rotating detonation engine rotate around the center axis of the rotating detonation engine. The assembly also includes opposing leading and trailing cavity walls that are coupled with the inner and outer walls and which radially extend away from the center axis, and an axial wall that is coupled with and connects the leading and trailing cavity walls with each other. The axial wall and the leading and trailing cavity walls define a detonation stabilizing cavity in which detonations of the rotating detonation engine occur and are stabilized.

A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.