A rotating internal combustion engine is provided. The engine includes a drive shaft and a rotatable cylinder coupled with the drive shaft. Combustion chambers are formed through the rotatable cylinder. The combustion chambers are defined by combustion blades of the rotatable cylinder. The engine is configured to generate power from combustion of the gases and from turbine movement caused from the combustion gases. Also disclosed is a fixed cylinder combustion engine.

The invention relates to a jet engine with a fixed housing in which a primary flow is formed in which incoming air is burned in at least one combustion chamber, in said housing a secondary flow being formed in which incoming air is accelerated by a fan and, said secondary flow being expelled at the outlet cone of the housing together with the exhaust gas from the combustion chamber, said fan being mounted on a main shaft rotatably about an axis and having a plurality of substantially radially-extending fan blades. According to the invention, it is proposed that at least one fan blade or a plurality of the fan blades or all fan blades have at least one air inlet channel for the primary flow which directs the air of the primary flow through the fan blade to the combustion chamber, and that at least one fan blade or a plurality of the fan blades or all fan blades each have an outlet channel with an at least partially axially- and at least partially tangentially-oriented outlet opening in order to supply the exhaust gas of the combustion chambers to the accelerated air of the secondary flow, said air-exhaust gas mixture emerging at the outlet cone of the jet engine housing, producing the thrust.

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.

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.

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.

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. In other examples the flow path is axial with the inlet positioned at a lower pressure region than the outlet. The nozzle may rotate about its center as a turbine in an axial configuration.

A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowing outwards through the compression passage; a combustion chamber supported within the compression passage near the maximum radius of the rotor having a closed outer end and combustion chamber gases inlets through which gases enter the combustion chamber, each combustion chamber having a fuel inlet, and; one or more expansion passages in fluidic connection with and extending radially inwards from the combustion chamber within a compression passage and fluidically connecting at or near the rotor axis to a combustion gas outlet tube that extends along the rotor axis, combustion gases created by combustion of fuel with inlet gases within the combustion chamber expanding as they flow inwards through the expansion passage.

A device comprising a combustion toroid for receiving combustion-induced centrifugal forces therein to continuously combust fluids located therein and an outlet for exhaust from said combustion toroid.

A combustion engine comprising a radial compressor in flow communication via a flow passage with an annular compressor-combustor array radially outward of the radial compressor. Both the radial compressor and compressor-combustor are co-axial with, and rotatable around, a central axis.