Control of low pressure recoup air in a gas turbine engine disposed in a gas turbine enclosure with low pressure recoup air piping coupled to a gas turbine combustion exhaust and gas turbine engine enclosure is disclosed. A first valve of the piping controls a flow of the recoup air to the gas turbine combustion exhaust. A second valve of the piping diverts the recoup air to the enclosure for eventual flow to the air intake. A controller controls the flow of the recoup air from the piping to the exhaust and/or the enclosure as a function of ambient and air intake temperature measurements, and a predetermined temperature requirement having an ambient temperature constraint and an air intake temperature differential constraint.

A process for waterless standalone power generation is disclosed that generates electricity efficiently using an ORC fluid which reduces emissions and water usage as compared to conventional power generation process. The waterless standalone power generation plant 100 includes a stabilizer 115, a condensing evaporator 120, a preheater 125, a recuperator 135, an integral chilling unit 140, a pair of condensers 145 and 175, an accumulator 160, a turbine 165, a generator 170. The condensing stabilizer 115 and evaporator 120 reduce the temperature of the flue gases to maintain it below working temperature of ORC fluid and trap the latent heat and the sensible heat which increases the efficiency of the waterless standalone power generation plant 100.

A process for waterless standalone power generation is disclosed that generates electricity efficiently using an ORC fluid which reduces emissions and water usage as compared to conventional power generation process. The waterless standalone power generation plant 100 includes a stabilizer 115, a condensing evaporator 120, a preheater 125, a recuperator 135, an integral chilling unit 140, a pair of condensers 145 and 175, an accumulator 160, a turbine 165, a generator 170. The condensing stabilizer 115 and evaporator 120 reduce the temperature of the flue gases to maintain it below working temperature of ORC fluid and trap the latent heat and the sensible heat which increases the efficiency of the waterless standalone power generation plant 100.

A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.

The auxiliary duct can branch radially outwardly from the bypass duct, have a proximal end fluidly connecting the bypass duct and a distal end, a valve can be activatable to selectively open and close the auxiliary passage, and a structure can protrude partially from the auxiliary duct into the auxiliary passage, the structure spaced apart from the proximal end, between the proximal end and the valve, the structure generating lesser pressure losses when flow in the auxiliary passage is directed towards the distal end than when the flow is directed towards the proximal end.

A system and method of increasing efficiency and power output of a gas turbine system using a compressed air storage system including delivering a compressed air charge from the compressed air storage system, the compressed air charge having a pressure greater than ambient pressure and a temperature less than ambient temperature, the compressed air charge being delivered to the gas turbine and the compressed air charge operable to cool at least a portion of the gas turbine.

A system and method of increasing efficiency and power output of a gas turbine system using a compressed air storage system including delivering a compressed air charge from the compressed air storage system, the compressed air charge having a pressure greater than ambient pressure and a temperature less than ambient temperature, the compressed air charge being delivered to the gas turbine and the compressed air charge operable to cool at least a portion of the gas turbine.

A compressed air-driven tool having an electromagnetically operated control element (27) for controlling a pneumatic control circuit in order to maintain a load-independent torque at a constant rotational speed. The tool includes a principal valve (5), which arranged in a drive housing (1) in a manner displaceable by the supplied compressed air against the force of a helical spring (13), and a generator (43), which is mounted on the shaft (49) of a turbine wheel (51). The rotational speed of the shaft (49) is measured with a speed sensor (75) and the supply of compressed air to the principal valve (5) is controlled in the event of a drop in rotational speed as a consequence of a load.

A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.

An aircraft propulsion system comprises a gas turbine engine arranged to provide propulsive thrust and a fuel cell system having an air input port, the aircraft propulsion system being configured such that air from a compressor of the gas turbine engine is provided to the air input port during operation of the aircraft propulsion system. The fuel cell system is able to provide appreciable electrical power at altitude without the need for a dedicated compressor.