A combustion engine (10) comprises a radial compressor (16) in flow communication via a flow passage (22) with a compressor-combustor array (20) radially outward of the radial compressor (16), both rotatable around a central axis (12). The compressor-combustor (20) comprises an array of rotor blades (26). The walls of the blades (26) define a plurality of chambers (28, 30). Each chamber (28, 30) has a flow inlet (32) to receive fluid from the radial compressor (16), and a flow outlet to exhaust fluid radially outwards from the compressor-combustor (20). The plurality of chambers (28, 30) comprises a first pilot combustion chamber (28a) and a second pilot combustion chamber (28b). The first pilot combustion chamber (28a) is provided with a first fuel injector (40a), and the second pilot combustion chamber (28b) is provided with a second fuel injector (40a). The first fuel injector (40a) is in flow communication with a first fuel reservoir (70a), and the second fuel injector (40b) is in flow communication with a second fuel reservoir (70b). The first fuel reservoir (70a) and the second fuel reservoir (70b) are each in fluid communication with a flow regulator (100), the flow regulator (100, 200, 300) operable to vary fuel flow delivery rate to the first reservoir (70a) and vary fuel flow delivery rate to the second reservoir (70b). The differential regulation of fuel flow between pilot combustion chambers results in different levels of thrust being generated downstream of the combustion chambers. In this way the engine is operable to produce vectored thrust.

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 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 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 engine is disclosed. The engine includes a rotary hub enclosing a manifold, blades radially distributed around the rotary hub, a combustion chamber at a distal end of each blade, an axle or shaft joined or fixed to the hub, and a generator operably connected to the axle or shaft. Each blade has a passage for air to flow to the combustion chamber and a fuel distribution conduit therein/thereon. The manifold connects a fuel supply conduit to the fuel distribution conduits. Each combustion chamber is configured to receive fuel and air from the corresponding fuel distribution conduit and passage, burn or detonate the fuel, and direct heated or expanded air and combustion gases in a direction that rotates the blades and the hub. The axle or shaft is configured to rotate with the hub. The generator is configured to convert a torque from the axle or shaft to electricity.

A boundary layer turbine (BLT) engine has a housing formed by an outer cylinder a first and a second faceplate, a turbine shaft through the faceplates, a stack of alternating disks and spacers with central holes joined to the turbine shaft leaving an outer combustion zone, an air inlet through the first faceplate, an exhaust port through the second faceplate, a fuel port through the outer cylinder, and an ignition device communicating with the combustion zone. The disks and spacers have openings forming separate intake and exhaust channels parallel to the turbine shaft, one channel channeling air from the air inlet port to spaces between disks, and the other channel channeling exhaust from the combustion zone through the exhaust channel to the exhaust port. Fuel is injected into the combustion zone, the air fuel mixture is ignited, and exhaust products impart torque to the turbine shaft by boundary layer friction.

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.

A boundary layer turbine (BLT) engine has a housing formed by an outer cylinder a first and a second faceplate, a turbine shaft through the faceplates, a stack of alternating disks and spacers with central holes joined to the turbine shaft leaving an outer combustion zone, an air inlet through the first faceplate, an exhaust port through the second faceplate, a fuel port through the outer cylinder, and an ignition device communicating with the combustion zone. The disks and spacers have openings forming separate intake and exhaust channels parallel to the turbine shaft, one channel channeling air from the air inlet port to spaces between disks, and the other channel channeling exhaust from the combustion zone through the exhaust channel to the exhaust port. Fuel is injected into the combustion zone, the air fuel mixture is ignited, and exhaust products impart torque to the turbine shaft by boundary layer friction.

Provided is an apparatus for generating electricity comprising a gas propellant chamber, a containment vessel, and a rotor/stator assembly partially integrated within the containment vessel. The gas propellant chamber is disposed within the containment vessel and 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. The rotor of the rotor/stator assembly is disposed internally of the containment vessel and is in communication with the stator, the stator being disposed externally of the containment vessel. The apparatus thereby provides a simpler and safer design that is both scalable and adaptable. The apparatus is easily and safely transportable and can be designed to be highly nuclear-proliferation-resistant.

An engine is disclosed. The engine includes a rotary hub enclosing a manifold, blades radially distributed around the rotary hub, a combustion chamber at a distal end of each blade, an axle or shaft joined or fixed to the hub, and a generator operably connected to the axle or shaft. Each blade has a passage for air to flow to the combustion chamber and a fuel distribution conduit therein/thereon. The manifold connects a fuel supply conduit to the fuel distribution conduits. Each combustion chamber is configured to receive fuel and air from the corresponding fuel distribution conduit and passage, burn or detonate the fuel, and direct heated or expanded air and combustion gases in a direction that rotates the blades and the hub. The axle or shaft is configured to rotate with the hub. The generator is configured to convert a torque from the axle or shaft to electricity.