Abstract: A method of operating a rotating detonation combustor includes providing a flow of air through an air inlet into a detonation chamber, providing fuel from a fuel injector into one of the air inlet or the detonation chamber, mixing the fuel and air to generate a fuel-air mixture, detonating the fuel-air mixture to generate rotating detonation waves, and controlling, during operation of the rotating detonation combustor from a first power operating state to a second power operating state, different from the first power operating state, a flow of an auxiliary gas through an auxiliary gas injection port into one of the air inlet to mix with the flow of the air within the air inlet to control a discharge coefficient of the air inlet, or into the detonation chamber to control a discharge coefficient of the detonation chamber, and to control an operating mode of the rotating detonation combustor.

Abstract: A method of operating a rotating detonation combustor includes providing a flow of air through an air inlet to flow into a detonation chamber, providing a flow of fuel from at least one fuel injector into the detonation chamber, mixing the flow of the fuel and the flow of the air in the detonation chamber to generate a fuel-air mixture, detonating the fuel-air mixture in the detonation chamber to generate rotating detonation waves within the detonation chamber, and controlling, during operation of the rotating detonation combustor from a first power operating state to a second power operating state, different from the first power operating state, the air inlet wall to control the flow of the air through the air inlet into the detonation chamber to control a discharge coefficient and an operating mode within the detonation chamber.

Abstract: Combustor systems are provided that include rotating detonation combustors (RDCs) arranged in series. In some embodiments, a combustor system includes a volume that receives a core oxidizer-fuel mixture. The combustor system includes a first RDC having a first detonation chamber. The first detonation chamber receives a first pilot oxidizer-fuel mixture and is bounded by a first channel formed in a peripheral wall. The combustor system further includes at least one additional RDC having a second detonation chamber. The second detonation chamber receives a second pilot oxidizer-fuel mixture and is bounded by a second channel formed in the peripheral wall. The first pilot oxidizer-fuel mixture reacts in the first detonation chamber and the second pilot oxidizer-fuel mixture reacts in the second detonation chamber to generate rotating detonation combustion waves that are guided by the first channel and the second channel to support a reaction that consumes the core oxidizer-fuel mixture.

Abstract: Combustor systems are provided that include rotating detonation combustors (RDCs) arranged in series. In some embodiments, a combustor system includes a volume that receives a core oxidizer-fuel mixture. The combustor system includes a first RDC having a first detonation chamber. The first detonation chamber receives a first pilot oxidizer-fuel mixture and is bounded by a first channel formed in a peripheral wall. The combustor system further includes at least one additional RDC having a second detonation chamber. The second detonation chamber receives a second pilot oxidizer-fuel mixture and is bounded by a second channel formed in the peripheral wall. The first pilot oxidizer-fuel mixture reacts in the first detonation chamber and the second pilot oxidizer-fuel mixture reacts in the second detonation chamber to generate rotating detonation combustion waves that are guided by the first channel and the second channel to support a reaction that consumes the core oxidizer-fuel mixture.

Abstract: A high-speed, air-breathing propulsion engine includes an inlet configured to compress incoming air, a fuel injector configured to supply a fuel for mixing with the compressed incoming air to form a fuel-air mixture, and a combustor configured to burn the fuel-air mixture. The combustor includes a rotation detonation combustor system and a bluff body system that cooperate to generate thrust.