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 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.

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.

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.

Disclosed herein are several embodiments for shroud arrangements to be used in rotary engines using a plurality of rotors within the shroud arrangement. At least one of the rotors is not fixed to the shroud.

The present invention relates to the technical field of hydrogen fuel power generation, specifically a hydrogen fuel high-speed rotating magnetohydrodynamic power generation device. The device comprises a shaft portion, a cover plate portion, a thin plate portion and a combustion propelling portion. The device craftily utilizes hydrogen electrochemical reaction and direct combustion of unionized hydrogen to complete the hydrogen catalytic ionization reaction while providing jet thrust for rotation. Advantages are that it is more efficient than hydrogen fuel cells, has high power density, which is suitable for high-power and high-energy power needs, utilizes no key special components and does not require auxiliary systems such as heat dissipation, breaking limitations of proton exchange membrane on hydrogen fuel cells and low efficiency of a Carnot cycle on hydrogen internal combustion engines.

A wave disc engine apparatus is provided. A further aspect employs a constricted nozzle in a wave rotor channel. A further aspect provides a sharp bend between an inlet and an outlet in a fluid pathway of a wave rotor, with the bend being spaced away from a peripheral edge of the wave rotor. A radial wave rotor for generating electricity in an automotive vehicle is disclosed in yet another aspect.

A combustion systems and components for rotary ramjet engines. An injection system, optionally stratified for ease of engine startup, provides an air and fuel mixture to a combustion chamber. An ignition system ignites the mixture. A flameholding system may be positioned for communication with the combustion chamber to force an ignited flow of the air and fuel mixture toward a center of rotation within the ramjet engine. The ramjet engine may have a diverging stator for improved exhaust efficiency. The ignition may take place in the engine air intake. Alternatively, the ignition may take place within the combustion chamber using a dual-hub electrically charged system. An impulse turbine may use recirculation of injected fuel to cool a rim-rotor and/or to reduce windage on the rim-rotor. A sealing system may reduce gas leaks from a fuel conduit into the engine air intake.

The invention relates to a system for emergency starting a turbine engine, characterised in that it comprises a flyer for driving the turbine engine, said flyer comprising a drum (2) rigidly connected to a rotary shaft (3), the axes of symmetry (LL) of the drum (2) and of the shaft being coincident, the flyer further comprising at least one exhaust nozzle (4) for ejecting gas, which is positioned on the periphery of the drum (2) and oriented substantially tangentially to the rotation about said axis (LL), and a pyrotechnic gas generation device which is installed in the flyer and feeds said at least one exhaust nozzle (4), said emergency start system further comprising a support in which the shaft of the flyer rotates, and a volute for recovering the gases, which radially surrounds the flyer and is rigidly connected to said support.