A pulse combustor system for operating pulse combustors in anti-phase. The pulse combustor system includes two pulse combustors connected at their combustion chambers by a connecting tube. Each of the pulse combustors has a fundamental oscillation mode and one or more additional oscillation modes when operated in isolation. The connecting tube has a length corresponding to ¼ of the fundamental oscillation mode wavelength.

A pulse combustor system for operating pulse combustors in anti-phase. The pulse combustor system includes two pulse combustors connected at their combustion chambers by a connecting tube. Each of the pulse combustors has a fundamental oscillation mode and one or more additional oscillation modes when operated in isolation. The connecting tube has a length corresponding to ¼ of the fundamental oscillation mode wavelength.

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 fuel detonation combustion pulse device includes a semispherical combustion chamber, a fuel supply system, a spark plug, a detonation accelerator, a hemispherical combustion chamber having a conic duct for transition to the detonation tube; a spark plug is mounted at the end wall of the sphere of the combustion chamber along its longitudinal axis, a fuel supply system is formed as a co-axial injector for fuel; an annular oxidant supply nozzle located perpendicular to the longitudinal axis of the device, and a detonation accelerator is shaped as a profiled stepped obstacle and is mounted in the combustion chamber conic duct for transition to the detonation tube being axial with it.

A fuel detonation combustion pulse device includes a semispherical combustion chamber, a fuel supply system, a spark plug, a detonation accelerator, a hemispherical combustion chamber having a conic duct for transition to the detonation tube; a spark plug is mounted at the end wall of the sphere of the combustion chamber along its longitudinal axis, a fuel supply system is formed as a co-axial injector for fuel; an annular oxidant supply nozzle located perpendicular to the longitudinal axis of the device, and a detonation accelerator is shaped as a profiled stepped obstacle and is mounted in the combustion chamber conic duct for transition to the detonation tube being axial with it.

A combustor is configured to operate in a rotating detonation mode and a deflagration mode. The combustor includes a housing and at least one initiator. The housing defines at least one combustion chamber and is configured for a deflagration process to occur within the at least one combustion chamber during operation in the deflagration mode and a rotating detonation process to occur within the at least one combustion chamber during operation in the rotating detonation mode. The at least one initiator is configured to initiate the rotating detonation process within the at least one combustion chamber during operation in the rotating detonation mode and to initiate the deflagration process within the at least one combustion chamber during operation in the deflagration mode.

A combustor is configured to operate in a rotating detonation mode and a deflagration mode. The combustor includes a housing and at least one initiator. The housing defines at least one combustion chamber and is configured for a deflagration process to occur within the at least one combustion chamber during operation in the deflagration mode and a rotating detonation process to occur within the at least one combustion chamber during operation in the rotating detonation mode. The at least one initiator is configured to initiate the rotating detonation process within the at least one combustion chamber during operation in the rotating detonation mode and to initiate the deflagration process within the at least one combustion chamber during operation in the deflagration mode.

An engine includes an elongated pulse detonation combustor tube having an arcuate combustion path over a majority of an entire length of the combustor tube, and an elongated portion of the combustor tube being oriented transverse to a central axis of the engine.