Embodiments of the invention provide a system or a method for combusting reactants including a fuel and an oxidizer into combustion products in a combustor. A combustor can be configured to contain a flow of the reactants and the combustion products that extends in a first direction. The flow can be subject to acceleration in a second direction at least partly transverse to the first direction. One or more micro-flameholders can be disposed within the combustor at or upstream of a location at which the flow is subject to the acceleration in the second direction. The one or more micro-flameholders can be configured to facilitate or promote Rayleigh-Taylor instability to cause interpenetration of the reactants and the combustion products within the combustor.

Embodiments of the invention provide a system or a method for combusting reactants including a fuel and an oxidizer into combustion products in a combustor. A combustor can be configured to contain a flow of the reactants and the combustion products that extends in a first direction. The flow can be subject to acceleration in a second direction at least partly transverse to the first direction. One or more micro-flameholders can be disposed within the combustor at or upstream of a location at which the flow is subject to the acceleration in the second direction. The one or more micro-flameholders can be configured to facilitate or promote Rayleigh-Taylor instability to cause interpenetration of the reactants and the combustion products within the combustor.

The present disclosure is directed to a rotating detonation combustor that includes a forward wall, a radially inner wall, and a radially outer wall. The forward wall is disposed at an inlet end of the rotating detonation combustor. The radially inner wall surrounds a longitudinal axis and extends downstream from the forward wall to an outlet end of the rotating detonation combustor. The radially outer wall extends downstream from the forward wall to the outlet end and surrounds the radially inner wall to define at least one annular plenum between the radially inner wall and the radially outer wall. At least one partition is proximate to the inlet end and defines at least two mixing zones. A plurality of oxidizer inlets and a plurality of fuel inlets are disposed at the inlet end in fluid communication with the at least two mixing zones.

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 fuel mixer for mixing a fuel and an oxidizer prior to detonation in a rotating detonation engine includes a combustion channel configured to transport a final mixture of the fuel and the oxidizer for combustion. The fuel mixer also includes a mixture channel positioned upstream from the combustion channel and configured to transport a first mixture having at least some of the fuel and at least some of the oxidizer. The fuel mixer also includes a secondary outlet positioned upstream from the combustion channel and configured to output a supplemental mixture of the fuel and the oxidizer that includes at least one of the fuel or the oxidizer such that the first mixture and the supplemental mixture combine in the combustion channel to form the final mixture.

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 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.

An injector for a gas turbine combustion chamber, includes a fluid feed system; an injector body extending along a longitudinal axis; an injection head arranged on the injector body and configured to spray the fluid in a direction that is inclined relative to the longitudinal axis; and an actuator configured to turn the injector selectively about the longitudinal axis so as to vary the direction in which the fluid is sprayed; wherein the actuator is configured to enable the orientation of the injector to be varied by turning about the longitudinal axis through an amplitude less than or equal to 90.

An injector for a gas turbine combustion chamber, includes a fluid feed system; an injector body extending along a longitudinal axis; an injection head arranged on the injector body and configured to spray the fluid in a direction that is inclined relative to the longitudinal axis; and an actuator configured to turn the injector selectively about the longitudinal axis so as to vary the direction in which the fluid is sprayed; wherein the actuator is configured to enable the orientation of the injector to be varied by turning about the longitudinal axis through an amplitude less than or equal to 90.

A dynamic pressure exchanger configured for a combustion process includes a seal plate and a rotor assembly. The rotor assembly is mounted for rotation relative to the seal plate about a central axis of the dynamic pressure exchanger.