A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.

A hybrid combustion system, and method of operation, for a propulsion system is provided. The hybrid combustion system defines a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The hybrid combustion system includes a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall. The nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, and the nozzle inlet is configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle. The hybrid combustion system further includes an inner liner extended generally along the longitudinal direction; an outer liner extended generally along the longitudinal direction and disposed outward of the inner liner along the radial direction; a bulkhead wall disposed at the upstream end of the inner and outer liners, in which the bulkhead wall extends generally in the radial direction and couples the inner liner and the outer liner, and wherein the inner liner, the outer liner, and the bulkhead wall together define a primary combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the primary combustion chamber; and a fuel manifold assembly extended at least partially through the bulkhead wall, in which the fuel manifold assembly defines a fuel manifold assembly exit disposed adjacent to the primary combustion chamber.

An engine without a compressor or a turbine comprises a combustion chamber for burning a fuel-air mixture formed by mixing a fuel with outside air; and an outside air introduction part for introducing outside air into the combustion chamber. The outside air introduction part comprises an intake main port for introducing outside air into the combustion chamber from the direction along the central axis of the combustion chamber and a plurality of intake sub-ports for introducing outside air into the combustion chamber from the direction toward the central axis. The intake sub-ports comprise ejection openings capable of ejecting outside air toward a collision point inside the combustion chamber. Streams of outside air ejected from the ejection openings of the intake sub-ports mutually collide at the collision point and are thereby compressed.

An engine without a compressor or a turbine comprises a combustion chamber for burning a fuel-air mixture formed by mixing a fuel with outside air; and an outside air introduction part for introducing outside air into the combustion chamber. The outside air introduction part comprises an intake main port for introducing outside air into the combustion chamber from the direction along the central axis of the combustion chamber and a plurality of intake sub-ports for introducing outside air into the combustion chamber from the direction toward the central axis. The intake sub-ports comprise ejection openings capable of ejecting outside air toward a collision point inside the combustion chamber. Streams of outside air ejected from the ejection openings of the intake sub-ports mutually collide at the collision point and are thereby compressed.

An engine in which thrust is achieved by converting electrical energy into high temperature plasma discharges that, in turn, apply thermal, pressure, and/or kinetic energy to a stream of passing air. The engine comprises a plasma region that includes a pair of gapped electrodes, such that the plasma discharges occur in the electrode gap. An energy storage device generates voltage pulses between the electrodes that electrically break down the air as the operating medium within the electrode gap and create plasma discharges.

An engine in which thrust is achieved by converting electrical energy into high temperature plasma discharges that, in turn, apply thermal, pressure, and/or kinetic energy to a stream of passing air. The engine comprises a plasma region that includes a pair of gapped electrodes, such that the plasma discharges occur in the electrode gap. An energy storage device generates voltage pulses between the electrodes that electrically break down the air as the operating medium within the electrode gap and create plasma discharges.

The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.

The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.

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.