Provided is an apparatus for generating electricity comprising a gas propellant chamber and one or more generators. The gas propellant chamber comprises a compressor, a nuclear fuel chamber, and a turbine assembly, wherein a drive shaft extending axially through the gas propellant chamber couples the compressor to the turbine assembly and wherein the nuclear fuel chamber is a rotating nuclear fuel chamber configured to rotate axially along the drive shaft to which the compressor and the turbine assembly are coupled.

An electricity generating system is disclosed. The system includes one or more rotary arms extending from a central hub, a tube or blade with an air passage therein extending from each of the one or more rotary arms, a set of rotary blades operably connected to the tube or blade, an axle or shaft joined or fixed to the central hub, and a generator operably connected to the axle or shaft. The air passage has one or more air inlets at or near an end of the tube or blade connected or joined to a corresponding rotary arm. The set of rotary blades is configured to provide a force that rotates the tube or blade. The axle or shaft is configured to rotate with the central hub. The generator is configured to convert a torque from the axle or shaft to electricity.

An Ericsson cycle turbine engine. The Ericsson cycle turbine may comprise: a centrifugal gas compressor, shaft, at least one heat exchanger, and a reaction turbine. The centrifugal gas compressor may function as a spinning wheel trompe and may be fed with a gas-liquid mixture. The centrifugal gas compressor may separate a gas from the gas-liquid mixture and compress that gas via centrifugal acceleration. The shaft may couple to the downstream end of the centrifugal gas compressor and may have an annular space to permit the compressed gas to travel therein. The heat exchanger may introduce heat to the compressed gas, such that isothermal expansion is approached. The reaction turbine may couple to the downstream end of the shaft and may rotate the shaft when releasing the compressed gas against a plurality of vanes. The liquid may be mercury, oil, or water. The gas may be helium, air, argon, or ammonia.

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. A rotating detonation engine can include a cylindrical inner shell within an outer housing, a cylindrical outer shell positioned between the inner shell and the outer housing, an annular gap between the outer shell and the outer housing functioning as a detonation chamber.

A rotary manifold for a rotor assembly of a cohesion-type drive includes a manifold body extending along a drive axis for rotation thereabout, a first ductwork internal the body for fluid communication with a plurality of first chambers of the drive, and a second ductwork internal the body for fluid communication with a plurality of second chambers of the drive. The second ductwork is in fluid isolation of the first ductwork.

The present invention is a turbofan propulsion system, based on a tangential gas turbine that is structurally a part of the propulsion system's centrifugal compressor, wherein the gas turbine's combustion chambers with nozzles are placed to rotate around a larger radius circle at a supersonic circumferential speed, and the fan blades are placed to rotate around a smaller radius circle at a subsonic circumferential speed, therefore increasing the efficiency of the propulsion system.

A dynamic pressure exchanger configured for a combustion process includes a seal plate and a rotor assembly. The rotor assembly is mounted for rotation relative to the seal plate about a central axis of the dynamic pressure exchanger.

A helical cross flow pulse detonation engine.

A rotary device (e.g., a rotary jet), power generation system, and methods of manufacturing and using the same are disclosed. The rotary jet includes a central axle or shaft, an inlet configured to receive at least one fluid, and a plurality of radial arms in fluid communication with the inlet, configured to rotate around the central axle or shaft. Each radial arm has a nozzle at a distal end thereof and an arc between the inlet and the nozzle. The radial arms extend radially from the central axle or shaft at least in part, and are configured to rotate when the fluid enters the inlet and passes through the radial arms, or when a rotational force is applied to the central axle or shaft. Each nozzle may have an opening facing away from a direction of rotation of the radial arms or facing in a direction parallel with the central axle or shaft.

A screw rocket nozzle may include a disc shaped nozzle body and a spiral flow path having an inlet and an outlet. In some examples the flow path is radial with the inlet positioned at a higher pressure region than the outlet.