A rotating detonation engine includes an annulus that defines a volume having a detonation region which is configured for a mixture of an oxidizer and a fuel to detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows. The rotating detonation engine further includes an oxidizer outlet configured to output the oxidizer into the volume. The rotating detonation engine further includes a fuel outlet configured to output the fuel into the volume such that the oxidizer and the fuel are initially insufficiently mixed to facilitate combustion. The rotating detonation engine further includes an obstacle positioned upstream from the detonation region and configured to mix the fuel and the oxidizer that are directed upstream in response to a passing detonation.

A rotating detonation engine includes an annulus having a first wall, a second wall, and a volume having a detonation region in which a mixture of an oxidizer and a fuel detonate in a rotating fashion to create a pressure wave and detonation exhaust, the volume defining a downstream outlet through which detonation exhaust flows. The engine further includes an oxidizer outlet to output oxidizer and a fuel outlet to output fuel into the volume. The engine further includes an obstacle positioned in the volume and extending for an obstacle distance between the first wall and the second wall that is at least twenty five percent of an annulus distance from the first wall to the second wall, the obstacle designed to reflect the pressure wave such that a reflection of the pressure wave travels downstream and reduces an amount of the detonation exhaust that travels upstream.

A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.

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 turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel including methane. The assembly also includes a fuel reformer configured to produce a secondary fuel, wherein the fuel reformer is further configured to channel a flow of secondary fuel towards the rotating detonation combustor such that the fuel-air mixture further includes the secondary fuel.

A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel including methane. The assembly also includes a fuel reformer configured to produce a secondary fuel, wherein the fuel reformer is further configured to channel a flow of secondary fuel towards the rotating detonation combustor such that the fuel-air mixture further includes the secondary fuel.

This is an engine that uses combustion pressures and shock waves to provide moment about an axis on a rotor producing a torque. This engine is a torque driven power plant which can be used for a variety of energy applications. At the core of this engine is a large diameter right cylinder that uses internal vectored combustion to rotate a shaft that can be attached to various mechanisms for use in diverse applications. This engine can be scaled to be various sizes with the functionality of the engine unaffected. This engine has a unique internal rotational-recoil disk (piston head type) that rotates in a circle making it extremely efficient. This engine has directional intake valves and removes the exhaust through the center of the rotation-recoil disk.

This is an engine that uses combustion pressures and shock waves to provide moment about an axis on a rotor producing a torque. This engine is a torque driven power plant which can be used for a variety of energy applications. At the core of this engine is a large diameter right cylinder that uses internal vectored combustion to rotate a shaft that can be attached to various mechanisms for use in diverse applications. This engine can be scaled to be various sizes with the functionality of the engine unaffected. This engine has a unique internal rotational-recoil disk (piston head type) that rotates in a circle making it extremely efficient. This engine has directional intake valves and removes the exhaust through the center of the rotation-recoil disk.

The invention relates to a turbine, in particular a combustion gas turbine, which drives a high-speed generator for generating electricity, said turbine having a high efficiency. The turbine has at least one combustion chamber (6), which is provided with a fuel injection means (7) and an ignition device (8) and which supplies the turbine with a combustion gas. An external compressor (3) is associated with the turbine. Said compressor has a separate electric drive and is not connected to the turbine by means of a drive shaft. Furthermore, at least two combustion chambers (5) are provided for discontinuous, pulsed combustion and supply of the turbine.

A compound cycle engine having at least one rotary unit defining an internal combustion engine, a first stage turbine in proximity of each unit, and a turbocharger is discussed. The exhaust port of each rotary unit is in fluid communication with the flowpath of the first stage turbine upstream of its rotor. The rotors of the first stage turbine and of each rotary unit drive a common load. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit, and the inlet of the second stage turbine of the turbocharger is in fluid communication with the flowpath of the first stage turbine downstream of its rotor. The first stage turbine has a lower reaction ratio than that of the second stage turbine. A method of compounding at least one rotary engine is also discussed.