Disclosed herein is an indexing system for a rotor assembly where in one example the indexing system regulates the rotational location of drive rotors. In one example the rotors are configured to rotate about a shaft.

An engine, a biomass powder energy conversion and/or generation system, hybrid turbine engines, and methods of manufacturing and using the same are disclosed. The engine includes a housing having an inner wall and an outer wall, a central rotary shaft extending from the housing, at least one fuel and air supply channel having a first portion extending radially from the rotary shaft and a second portion in fluidic communication with first portion of the fuel and air supply channel, at least two propulsion vessels, each propulsion vessel connected to the at least one of the fuel and air supply channel and configured to burn or detonate the fuel and rotate around the central rotary shaft; and at least one exhaust duct extending from the housing.

A centrifuge type turbine. The turbine has a circular hollow rotor having a centrally located air and fuel inlet and an outer periphery. A stationary exhaust shroud surrounds the outer periphery of the rotor. The rotor has at least two spiral shaped swirl channels located therein extending from the air and fuel inlet to an outlet located at its outer periphery. The swirl channels are formed by stationary spiral walls. The air and fuel inlet has a plurality of stationary curved blades located therein and adapted to rotate with the rotor and to swirl and admix fuel and air introduced thereinto. An ignition source located in the exhaust shroud ignites the air/fuel mixture. A plurality of stationary push point members are located within the exhaust shroud.

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.

A method utilizing a rotating disc gasifies and pressurizes liquid propellants for use in rocket propulsion systems. The method is carried out by: a) increasing the tangential kinetic energy and pressure of liquid propellants by driving them from the center of the rotating disc to the periphery of the disc; b) gasifying the propellants at the periphery of the disc by partial combustion; and c) decreasing the tangential kinetic energy of the gasified propellants by driving them from the periphery to the center of the disc. The single rotating disc gasifies oxidant and fuel simultaneously, without relative movement between the components of the disc which include a structural disc (2), plates (3), compression ducts (4) and (5) and expansion ducts (6) and (10). The various ducts transport the propellants as shown by the arrows in FIG. 1.

Aspects of the present disclosure are directed to apparatuses and methods involving a turbine blade that rotates with a shaft, which may be implemented with a round or toroidal-based engine housing. As may be implemented with some embodiments, an apparatus includes a shaft and turbine blade having a common axis of rotation, with each drive shaft operable to rotate independently of the other drive shaft. A housing extends around the shaft and turbine blade and has sidewall with inlet and exhaust ports. In some implementations, clutch bearings limit rotation of the drive shaft to a common rotational direction. The turbine blade and inner surface of the sidewall define chambers and operable to move circumferentially within the chamber about the axis of rotation, with the shaft to which it is coupled, and to drive the turbine blade using gas supplied via the inlet port(s) and exhausted vie the exhaust port(s).

A method utilizing a rotating disc gasifies and pressurizes liquid propellants for use in rocket propulsion systems. The method is carried out by: a) increasing the tangential kinetic energy and pressure of liquid propellants by driving them from the center of the rotating disc to the periphery of the disc; b) gasifying the propellants at the periphery of the disc by partial combustion; and c) decreasing the tangential kinetic energy of the gasified propellants by driving them from the periphery to the center of the disc. The single rotating disc gasifies oxidant and fuel simultaneously, without relative movement between the components of the disc which include a structural disc (2), plates (3), compression ducts (4) and (5) and expansion ducts (6) and (10). The various ducts transport the propellants as shown by the arrows in FIG. 1.

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 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.

The invention includes engines adapted for using apparatuses and methods for instantiating chemical reactants in a nanoporous carbon powder, and further includes methods of use for such engines.