A constant-volume combustion system for a turbomachine includes a plurality of combustion chambers distributed in an annular manner about an axis defining an axial direction, each combustion chamber including an intake port and an exhaust port; a selective closure member rotationally movable about the axis with respect to the combustion chambers, the selective closure member including a ferrule facing the intake and exhaust ports of the combustion chambers, the ferrule containing at least one intake aperture intended to cooperate with the exhaust port of each chamber and at least one exhaust aperture intended to cooperate with the exhaust port of each chamber. Each intake aperture and each exhaust aperture are segmented by at least one segment extending in each aperture in the axial direction.

This patent discloses thrust vectoring ignition chamber engine. Thrust vectoring ignition chamber used in this engine is an annular cylinder having nozzles mounted in a way such that during fuel suction phase they are sealed and during ignition of fuel they are unsealed so that hot jets of ignited fuel escaping through nozzles cause coupled rotatory motion on the ignition chamber. Engine uses cam operated suitably modified 3-screw compressor for suction and compression of fuel and therefore do not require piston mechanism. Flywheel mounted on extension of ignition chamber functions as output of the engine. Each half rotation of flywheel completes three phases namely fuel/air suction, compression and combustion. Thus this engine fires for every half revolution and therefore can give improved power boost.

This patent discloses thrust vectoring ignition chamber engine. Thrust vectoring ignition chamber used in this engine is an annular cylinder having nozzles mounted in a way such that during fuel suction phase they are sealed and during ignition of fuel they are unsealed so that hot jets of ignited fuel escaping through nozzles cause coupled rotatory motion on the ignition chamber. Engine uses cam operated suitably modified 3-screw compressor for suction and compression of fuel and therefore do not require piston mechanism. Flywheel mounted on extension of ignition chamber functions as output of the engine. Each half rotation of flywheel completes three phases namely fuel/air suction, compression and combustion. Thus this engine fires for every half revolution and therefore can give improved power boost.

A rotating detonation combustion (RDC) system is provided. The RDC includes a first outer wall and a second outer wall each extended around a centerline axis, and a detonation chamber formed radially inward of the second outer wall. A fuel passage extended between the first outer wall and the second outer wall, the fuel passage including a first inlet opening proximate to the aft end through which a flow of fuel is received into the fuel passage. The flow of fuel is provided through the fuel passage from the aft end to the forward end of the RDC system and to the detonation chamber.

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.

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.

A rotating detonation combustion (RDC) assembly and propulsion system, and method for operation, are provided. The RDC assembly includes a detonation path extended from a detonation zone at which a predetonation device is in operative communication with a fuel/oxidizer mixture at a detonation chamber. The method includes generating a first fuel/oxidizer equivalence ratio of detonation gases at a first portion of the detonation path, wherein the first portion of the detonation path is defined along a first direction from the detonation zone along which a detonation wave propagates; generating a second fuel/oxidizer equivalence ratio of detonation gases at the second portion of the detonation path, wherein the second fuel/oxidizer equivalence ratio is different from the first fuel/oxidizer equivalence ratio, and wherein the second portion of the detonation path is defined from the first portion to the predetonation device; and sustaining the detonation wave via the second fuel/oxidizer equivalence ratio of detonation gases at the second portion of the detonation path.

A constant volume combustion chamber for a turbine engine, includes an intake port, an exhaust port, and a first rotary shutter facing the intake and exhaust ports and configured to rotate around an axis in a first direction of rotation, the first shutter including an aperture intended to cooperate alternately with the intake and exhaust ports during the rotation of the first shutter. The chamber further includes at least one second rotary shutter facing the intake and exhaust ports and configured to rotate around the axis in a second direction of rotation opposite to the first direction, the second shutter including an aperture intended to cooperate alternately with the intake and exhaust ports during the rotation of the second shutter, the first and second shutters being synchronized and configured so that their respective apertures intersect alternately when both are facing the intake and when both are facing exhaust ports.

Rotating detonation engines are provided with various improvements pertaining to performance and reliability. Improvements pertain to, for example, a fluidic valve/premixing chamber, injection/swirl, flow control and turning, ignition, and cooling.

An engine having a compressor for generating a flow of pressurized oxidizer, a fuel mixing system in fluid communication with the compressor for mixing fuel with the pressurized oxidizer creating a fuel-oxidizer mixture, a combustion chamber adapted to receive the fuel-oxidizer mixture, at least one ignition system connected to the combustion chamber for igniting the fuel-oxidizer mixture inside of the combustion chamber, an exhaust port in fluid communication with the combustion chamber for receiving exhaust generated by combustion of the fuel-oxidizer mixture, and a turbine having a rotating shaft and a plurality of turbine blades connected downstream of the combustion chamber for receiving the exhaust whereby the fluid force of the exhaust through the exhaust port causes the turbine blades to rotate the shaft.