A disc turbocharger includes a multi-disc engine in which each disc engine includes a turbine blade, a compressor blade, and a bearing without requiring a shaft between the turbine blade and the compressor blade. The power produced by each turbine blade is consumed by its own joined compressor. The disc turbocharger has a multi-disc engine that works as a multi-stage turbocharger with a smaller size and no piping between the turbochargers. The disc turbocharger uses a waste spool valve for control of the.

A rotating detonation engine includes an annulus that defines a volume in which a mixture of an oxidizer and a fuel detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows. The rotating detonation engine further includes a wave arrestor positioned upstream from a location of detonation and configured to reduce a magnitude of a pressure wave traveling upstream from the location of detonation.

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 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 disc turbine engine includes a multi disc engine in which each disc engine includes a turbine blade, and low-pressure compressor blade, a high-pressure compressor blade and a bearing that runs the disc engine freely around a shaft. Each disc engine has its own cooling system, the compressor's blades act as cooling fins for the turbine blade, and air bleeding from the high-pressure compressor to the lower pressure compressor through a hollow turbine blade. Cooling the nozzle is by attaching the nozzle to the guide fan and by air bleeding through the hollow body. There is no stator in between the disc engine and no large shaft is required because the power produced by each turbine blade is consumed by its own compressor. The weight and cost of this engine will be less than other engines at the same thrust output.

A disc turbine engine includes a multi disc engine in which each disc engine includes a turbine blade, and low-pressure compressor blade, a high-pressure compressor blade and a bearing that runs the disc engine freely around a shaft. Each disc engine has its own cooling system, the compressor's blades act as cooling fins for the turbine blade, and air bleeding from the high-pressure compressor to the lower pressure compressor through a hollow turbine blade. Cooling the nozzle is by attaching the nozzle to the guide fan and by air bleeding through the hollow body. There is no stator in between the disc engine and no large shaft is required because the power produced by each turbine blade is consumed by its own compressor. The weight and cost of this engine will be less than other engines at the same thrust output.

A hybrid propulsion system includes a wave rotor combustion engine operating in parallel with an electrical motor-generator element. The motor-generator element is coupled to the turbine shaft to selectively drive or be driven by the turbine shaft. In one mode of operation, the motor of the motor generator element is powered by a battery to provide rotational energy to the turbine shaft. In another mode of operation, the wave rotor combustion engine drives the generator to recharge the battery. The wave rotor combustion engine may be further directly coupled to auxiliary components without a gearbox to drive the components at substantially the same speed as the turbine shaft. The turbine rotor of the combustion engine includes a plurality of chambers defined by circumferentially spaced curved vanes that improves specific fuel consumption for the engine.

A hybrid propulsion system includes a wave rotor combustion engine operating in parallel with an electrical motor-generator element. The motor-generator element is coupled to the turbine shaft to selectively drive or be driven by the turbine shaft. In one mode of operation, the motor of the motor generator element is powered by a battery to provide rotational energy to the turbine shaft. In another mode of operation, the wave rotor combustion engine drives the generator to recharge the battery. The wave rotor combustion engine may be further directly coupled to auxiliary components without a gearbox to drive the components at substantially the same speed as the turbine shaft. The turbine rotor of the combustion engine includes a plurality of chambers defined by circumferentially spaced curved vanes that improves specific fuel consumption for the engine.

An engine, a rotary device, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation and/or combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the detonation and/or combustion chamber, a fuel supply inlet configured to provide the fuel to the detonation and/or combustion chamber, at least two rotating arms extending radially from the detonation and/or combustion chamber and configured to exhaust detonation gases from detonating the fuel in the detonation and/or combustion chamber and provide a rotational thrust and/or force, the rotating arms having inner and outer walls and a nozzle at a distal end thereof, the nozzle being at or having an angle configured to provide the rotational thrust and/or force, and a plurality of cooling coils between the inner and outer walls. Alternatively, the rotary device may include a rotary disc.

An engine, a rotary device, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation and/or combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the detonation and/or combustion chamber, a fuel supply inlet configured to provide the fuel to the detonation and/or combustion chamber, at least two rotating arms extending radially from the detonation and/or combustion chamber and configured to exhaust detonation gases from detonating the fuel in the detonation and/or combustion chamber and provide a rotational thrust and/or force, the rotating arms having inner and outer walls and a nozzle at a distal end thereof, the nozzle being at or having an angle configured to provide the rotational thrust and/or force, and a plurality of cooling coils between the inner and outer walls. Alternatively, the rotary device may include a rotary disc.