An inlet guide assembly for a turbine receiving a pulsed flow, including a duct having an internal volume, and an inlet port, first outlet nozzle and second outlet nozzle each communicating with the internal volume. The inlet port is configured to receive at least part of the pulsed flow. The first and second outlet nozzles each define a respective nozzle area communicating between the internal volume and a flow path of the turbine. The first and second outlet nozzles are spaced from one another with the first outlet nozzle located closer to the inlet port than the second outlet nozzle relative to a flow direction through the duct, the nozzle area of the first outlet nozzle being smaller than the nozzle area of the second outlet nozzle. A compound engine assembly and method of introducing a pulsed flow into a flow path of a turbine are also discussed.

The present invention relates to an axial flow turbine, comprising: a rotor mounting part; a housing having a fluid supply part surrounding the rotor mounting part; a rotor which is installed at a rotation shaft installed in the housing and has a plurality of blades installed in a circumferential direction; and a plurality of injection nozzles, installed in the fluid supply part surrounding the rotor mounting part, for spraying a high-pressure fluid toward the blades, wherein the fluid collision surface of the blades installed at the rotor is formed to be inclined at an angle in the rotational direction of the rotor with respect to the normal axis of the rotation center axis, and the injection nozzles formed in the fluid supply part are installed at an angle parallel to the normal direction of the fluid collision surface of the blades. Due to the aforementioned configuration, the present invention provides the effect of maximizing the rotation rate of a turbine while smoothing fluid flow by optimizing the angle of the fluid collision surface of the blades.

An air turbine starter device comprises a rotor arranged in a cavity of a housing, a first manifold having a cavity with a port operative to direct compressed air to the rotor, a second manifold having a cavity with a port operative to direct compressed air to the rotor, wherein the first manifold is larger than the second manifold.

An engine assembly including an internal combustion engine, an impulse turbine, and an exhaust pipe providing fluid communication between the exhaust port of the internal combustion engine and the flow path of the turbine. The exhaust pipe terminates in a nozzle. A ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of the exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the internal combustion engine is at least 0.2. A method of compounding at least one internal combustion engine is also discussed.

A negative-emission pressurized air or other compressible gas operated high-efficiency reciprocating or rotary piston engine, as autonomously considered or as part of a complex system, comprises at least a tank, at least a turbo-alternator and one or more optional fluid heaters.

An object is to provide a mixed flow turbine, wherein intermediate blades having an intermediate height are provided between main blades of the mixed flow turbine, thus improving an impulse blade turbine characteristic and reducing the moment of inertia for a rotor blade as a whole, thereby improving the efficiency and transient response. The mixed flow turbine includes: a turbine rotor blade 11; a turbine housing 3; a scroll partition wall 17 dividing a scroll chamber 13; a shroud-side inflow passageway 35 formed on the side of a shroud-side partition wall surface 25; and a hub-side inflow passageway 29 formed on the side of a hub-side partition wall surface 23, wherein the rotor blade 11 includes: main blades 37 formed with a height spanning the entire extent between a hub outer circumferential surface 31 and the inner periphery surface of a shroud portion 15; and intermediate blades 39 arranged in the circumferential direction between the main blades 37 and arranged so as to extend from the inlet portion of the main blades 37 to an intermediate portion and having an intermediate height with respect to the height of the main blades 37, wherein a fluid from the hub-side inflow passageway 29 flows in through front edges of the intermediate blades 39.

A converter of kinetic energy from a jet formed by a heat transfer fluid and a gas at high temperature, includes: at least one injector of the jet from at least one source of heat transfer fluid and of high-temperature gas, an impulse wheel mounted rotating secured to a shaft extending along an axis substantially perpendicularly to the injector and including a plurality of asymmetric blades, a tank surrounding said impulse wheel and at least one deflector extending underneath the blades.

Several embodiments of a wobble plate motor include a disc mounted on a bent shaft. Driving the wobble plate so it revolves on a flat base causes the bent shaft to rotate and drive a generator or other work consumer. The wobble plate may be driven by a fluid stream impinging on the plate or by a blade assembly in a path of fluid movement. In one embodiment of a bladed motor, a shroud may direct the fluid stream so it more efficiently cooperates with the blade assembly.

The turbine nozzle includes a body having first and second sides defining a thickness between the first and second sides. Nozzle holes are formed through the thickness between the first and second sides. Each nozzle hole has an inlet on the first side of the body to receive fluid and an outlet on the second side of the body to direct the fluid to a turbine rotor. The nozzle holes are arranged in a plurality of circular patterns on the first side about a central axis. An inlet area of each nozzle hole is larger than an outlet area. Inlet areas of the nozzle holes arranged in the same circular pattern are the same, but inlet areas of the nozzle holes arranged in a circular pattern having a larger radius are larger than inlet areas of the nozzle holes arranged in a circular pattern having a smaller radius.

Disclosed is a turbine engine including a housing defining an interior cavity. A shaft extends axially through the housing and a turbine rotor coupled to the shaft. The turbine rotor includes a hub configured to couple to the shaft. A plurality of spokes extend radially outward from the hub. A plurality of blades is included, and each blade is disposed at a distal end of a corresponding spoke of the plurality of spokes and shaped as a hollow spherical shell having an opening. The opening is oriented to receive a working fluid and direct the working fluid tangentially to impart rotational motion to the turbine rotor. An inlet is coupled to the housing and configured to direct the working fluid into the interior cavity. An exhaust pipe is coupled to the housing and configured to discharge residual gases from the housing.