A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.

A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.

A Brayton cycle engine including an inner wall assembly defining a detonation combustion region upstream thereof extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath. A method for operating the engine includes flowing an oxidizer through the gas flowpath; capturing a portion of the flow of oxidizer via the inner wall; flowing a first flow of fuel to the captured flow of oxidizer; producing a rotating detonation gases via a mixture of the first flow of fuel and the captured flow of oxidizer; flowing at least a portion of the detonation gases downstream to mix with the flow of oxidizer; flowing a second flow of fuel to the mixture of detonation gases and oxidizer; and burning the mixture of the second flow of fuel and the detonation gases/oxidizer mixture.

A Brayton cycle engine including an inner wall assembly defining a detonation combustion region upstream thereof extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath. A method for operating the engine includes flowing an oxidizer through the gas flowpath; capturing a portion of the flow of oxidizer via the inner wall; flowing a first flow of fuel to the captured flow of oxidizer; producing a rotating detonation gases via a mixture of the first flow of fuel and the captured flow of oxidizer; flowing at least a portion of the detonation gases downstream to mix with the flow of oxidizer; flowing a second flow of fuel to the mixture of detonation gases and oxidizer; and burning the mixture of the second flow of fuel and the detonation gases/oxidizer mixture.

A flow control actuator includes a first side wall, a second side wall opposite and substantially parallel to the first side wall, an upstream wall mechanically coupled to upstream ends of the first and second side walls, and a downstream cap mechanically coupled to downstream ends of the first and second side walls. The first side wall, the second side wall, the upstream wall and the downstream cap collectively define an interior of the flow control actuator. An energy source is disposed in at least one of the first sidewall and the second sidewall. At least one fuel injector is disposed in the upstream wall, the first sidewall and/or the second sidewall for dispersing fuel into the flow control actuator. At least one air inlet is disposed in the upstream wall, the first sidewall and/or the second sidewall for introducing air into the flow control actuator. Fuel from fuel injector and air from the air inlet are ignited in the flow control actuator.

A combustion system may include a detonation combustor comprising one or more detonation chamber walls defining a detonation chamber, a deflagration combustor comprising one or more deflagration chamber walls defining a deflagration chamber, and one or more conjugate chamber walls defining a conjugate chamber, with the conjugate chamber in fluid communication with the detonation chamber and the deflagration chamber. The detonation chamber includes a detonation region and a nozzle region, with the nozzle region providing fluid communication between the detonation region and the conjugate chamber.

A combustion system may include a detonation combustor comprising one or more detonation chamber walls defining a detonation chamber, a deflagration combustor comprising one or more deflagration chamber walls defining a deflagration chamber, and one or more conjugate chamber walls defining a conjugate chamber, with the conjugate chamber in fluid communication with the detonation chamber and the deflagration chamber. The detonation chamber includes a detonation region and a nozzle region, with the nozzle region providing fluid communication between the detonation region and the conjugate chamber.

A detonation combustion system includes a detonation combustor. The detonation combustor includes a detonation manifold and one or more detonation chamber walls defining a detonation chamber. The detonation manifold includes a plurality of detonation fluid pathways defined by a monolithic structure of the detonation manifold, and a plurality of detonation orifice groups respectively including a plurality of detonation orifices disposed about a surface of the detonation manifold. Respective ones of the plurality of detonation orifice groups provide fluid communication from a corresponding one of the plurality of detonation fluid pathways to the detonation chamber through the plurality of detonation orifices corresponding to the respective one of the plurality of detonation orifice groups. The plurality of detonation orifices may be symmetrically oriented about a reference element of the detonation combustor.

A rotating detonation engine including an annular main chamber configured to sustain a main shockwave that moves along a perimeter of the main chamber and an annular pilot chamber configured to sustain a pilot shockwave that moves along a perimeter of the pilot chamber. The main shockwave may be generated in response to the pilot shockwave extending into the main chamber.

A rotating detonation engine including an annular main chamber configured to sustain a main shockwave that moves along a perimeter of the main chamber and an annular pilot chamber configured to sustain a pilot shockwave that moves along a perimeter of the pilot chamber. The main shockwave may be generated in response to the pilot shockwave extending into the main chamber.