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.

A method of operating a compoundable engine that includes a turbine having a turbine shaft and an intermittent internal combustion engine having an engine shaft. The engine shaft is rotated at a first rotational speed. The turbine is driven by exhaust gases of the intermittent internal combustion engine to rotate the turbine shaft while the engine shaft rotates independently from the turbine shaft. A rotatable load is driven with the turbine shaft. A rotational speed of the engine shaft is increased from the first rotational speed until the turbine shaft reaches a predetermined rotational speed. After the turbine shaft has reached the predetermined rotational speed, the rotational speed of the engine shaft is adjusted until the turbine shaft and the engine shaft are drivingly engageable with each other, and the turbine shaft with the engine shaft are engaged such that both are in driving engagement with the rotatable load.

A method of operating a compoundable engine that includes a turbine having a turbine shaft and an intermittent internal combustion engine having an engine shaft. The engine shaft is rotated at a first rotational speed. The turbine is driven by exhaust gases of the intermittent internal combustion engine to rotate the turbine shaft while the engine shaft rotates independently from the turbine shaft. A rotatable load is driven with the turbine shaft. A rotational speed of the engine shaft is increased from the first rotational speed until the turbine shaft reaches a predetermined rotational speed. After the turbine shaft has reached the predetermined rotational speed, the rotational speed of the engine shaft is adjusted until the turbine shaft and the engine shaft are drivingly engageable with each other, and the turbine shaft with the engine shaft are engaged such that both are in driving engagement with the rotatable load.

In order to improve a machine for depressurizing or compressing substantially gaseous media, comprising a machine casing and at least one screw rotor, which is arranged in a screw rotor bore in the machine casing, extends between a low-pressure side and a high-pressure side of the screw rotor bore, cooperates with the substantially gaseous medium and is mounted on both sides in the machine casing by means of a respective bearing set, and a motor/generator unit that is coupled or couplable to the at least one screw rotor, it is proposed that the at least one screw rotor should be provided with at least one axial support bearing that axially supports the at least one screw rotor such that a high-pressure end face of the at least one screw rotor is guided, without making contact, to an end wall, which faces this end face, of the machine casing that receives the at least one screw rotor.

Some implementations of this invention relate to energy systems and more particularly to rotating componentry enabling shaft work, propulsion drive, electric power generation, jet propulsion and/or thermodynamic systems related to aerothermodynamic thrust and shaft power, waste heat recovered shaft power, ventilation, cooling, heat, pressure and/or vacuum generating devices. Some implementations pertain to the art of vane assemblies for eccentrically placed rotating partial admission compressors and expanders that may either be used together or in conjunction with other mechanical, electrical, hydraulic and/or pneumatic machineries. Some implementations further relate to fluid energy recovery mechanical devices, targeting the field of gas turbine engines, internal combustion engines, furnaces, rotary kilns, coolers and refrigeration rotary components and/or expansion nodes. Other implementations are described.

Some implementations of this invention relate to energy systems and more particularly to rotating componentry enabling shaft work, propulsion drive, electric power generation, jet propulsion and/or thermodynamic systems related to aerothermodynamic thrust and shaft power, waste heat recovered shaft power, ventilation, cooling, heat, pressure and/or vacuum generating devices. Some implementations pertain to the art of vane assemblies for eccentrically placed rotating partial admission compressors and expanders that may either be used together or in conjunction with other mechanical, electrical, hydraulic and/or pneumatic machineries. Some implementations further relate to fluid energy recovery mechanical devices, targeting the field of gas turbine engines, internal combustion engines, furnaces, rotary kilns, coolers and refrigeration rotary components and/or expansion nodes. Other implementations are described.

A method of operating a compoundable engine that includes a turbine having a turbine shaft and an intermittent internal combustion engine having an engine shaft. The engine shaft is rotated at a first rotational speed. The turbine is driven by exhaust gases of the intermittent internal combustion engine to rotate the turbine shaft while the engine shaft rotates independently from the turbine shaft. A rotatable load is driven with the turbine shaft. A rotational speed of the engine shaft is increased from the first rotational speed until the turbine shaft reaches a predetermined rotational speed. After the turbine shaft has reached the predetermined rotational speed, the rotational speed of the engine shaft is adjusted until the turbine shaft and the engine shaft are drivingly engageable with each other, and the turbine shaft with the engine shaft are engaged such that both are in driving engagement with the rotatable load.

A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.

A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.

The present invention uses the exhaust gas of an internal combustion reciprocating engine to drive a turbine. The turbine is position around the cylinder. The turbine is connected to systems that will use the energy to improve the total system efficiency. One such system would be connected to a compressor to create the force induction required for two-stroke engines.