A pneumatic engine, comprising: a rotating outer ring (1), an intermediate shaft (2), a direct drive power core (3), and left and right baffles (4) and (5) where the rotating outer ring (1), the direct drive power core (3), and the left and right baffles (4) and (5) are coaxially provided on the intermediate shaft (2), the rotating outer ring (1) is integrally connected to the left and right baffles (4) and (5) to engage with the intermediate shaft (2) via a bearing, and a closed space is formed, the intermediate shaft (2) is provided with a master air inlet (21) and a master air outlet (22), the direct drive power core (3) is provided with a logarithmic spiral line runner, multiple drive grooves (11) are provided on an inner ring surface of the rotating outer ring (1). The pneumatic engine has a simple structure, high transmission efficiency and strong endurance.

Disclosed is a system including a turbine having a plurality of blades being spaced circumferentially around a shaft. Each blade of the plurality of blades is a hemispherical-shaped cup with an open surface. A plurality of dispensers are included, and each dispenser of the plurality of dispensers is positioned facing the open surface of the each blade, and directs discharged fluid toward the open surface of the each blade to drive the turbine. A housing encloses the plurality of blades and a portion of each dispenser of the plurality of dispensers, and has an exhaust pipe extending away from the shaft directing the discharged fluid out of the housing. A controller is in communication with the plurality of dispensers, and controls the plurality of dispensers.

Disclosed is a system including a turbine having a plurality of spokes. The first spoke end is coupled to a shaft and the second spoke end is coupled to a blade of a plurality of blades. Each blade is a cup with an open surface. A dispenser includes a combustion chamber. An air injector is configured to inject air into the combustion chamber. A fuel injector is configured to inject fuel into the combustion chamber. An ignitor is configured to supply a spark for combustion in the combustion chamber. A nozzle directs discharged fluid toward the open surface of the blade to drive the turbine. A housing encloses the second nozzle end and the plurality of blades, and has an exhaust pipe. A controller is configured to control the air injector, the fuel injector and the ignitor.

A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine positioned within the housing and positioned so as to be contacted by the fluid expelled from the jet. The fluid causes the turbine to rotate about a center rotational axis within the housing. The turbine comprises a first axial end, a second axial end, and a plurality of vanes extending axially relative to the center rotational axis from the first axial end to the second axial end. The plurality of vanes defines axially-extending channels between each of the plurality of vanes. The first axial end is axially open such that fluid can flow unblocked axially through the first axial end and into the channels. The jet is positioned such that at least a portion of the fluid enters into the turbine through the first axial end.

An engine having a compressor for generating a flow of pressurized oxidizer, a fuel mixing system in fluid communication with the compressor for mixing fuel with the pressurized oxidizer creating a fuel-oxidizer mixture, a combustion chamber adapted to receive the fuel-oxidizer mixture, at least one ignition system connected to the combustion chamber for igniting the fuel-oxidizer mixture inside of the combustion chamber, an exhaust port in fluid communication with the combustion chamber for receiving exhaust generated by combustion of the fuel-oxidizer mixture, and a turbine having a rotating shaft and a plurality of turbine blades connected downstream of the combustion chamber for receiving the exhaust whereby the fluid force of the exhaust through the exhaust port causes the turbine blades to rotate the shaft.

These new thrusters simultaneously use wheels of the CARPYZ THRA Turbo Powered Helicopter Reactor type and wheels of the CARPYZ TaG Bucket Turbines type or wheels of the CARPYZ TaC Scoop Turbines type, representing real global technological breakthroughs for fluid mechanics. They use, upon vertical take-off of the aircraft, propellers driven by electric motors and temporarily use the required additional high vertical axial thrust that is then supplied by the reactors of the THRA wheels, which also use an energetic fluid. The CARPYZ type thrusters, due to the low diameter and weight afforded thereto, are progressively horizontally inclined and the force of the reactors is progressively replaced by that of the propellers, which then supply the flows required in order for the aircraft to travel horizontally using wings that rely on the lift of the fluid, like airplanes. Photovoltaic wings are then deployed that are like butterfly wings and this economical solution will enable voyages over longer distances. It really is the safe mass market vertical take-off car of the future that can be achieved in less than 10 years by virtual of the new CARPYZ type thrusters, the little things change everything!

A turbopump includes: a main shaft rotatably supported; a pump section including an impeller attached to one end of the main shaft; and a turbine section including: a disk attached to the other end of the main shaft, rotor blades provided on an outer periphery of the disk, and nozzles provided inclined to an entrance plane of a blade cascade constituted of the rotor blades, the nozzles having axisymmetric cross sections and arranged in at least two rows along a circumferential direction of the main shaft in a plane orthogonal to the main shaft.

A turbomachine may include a turbine arranged in a housing and configured to be acted on with a hot working medium. The turbomachine may include at least one bypass channel for heating the housing through the working medium. The bypass channel may extend completely within the housing and be configured to bypass the turbine.

This application provides a steam turbine. The steam turbine may include a number of controlled flow runners and a number of controlled flow guides. The controlled flow guides may include an upstream passage ratio (W.sub.up/W) of 0.4 to 0.7.

A system and method is provided for converting wellhead pressure of natural gas wells, or for converting water head pressure of water towers, to rotational power for operating rotated equipment, such as electrical generators, electrical alternators, pumps, air compressors, and other rotated equipment.