An aircraft turbine engine having a primary air flow path with low-pressure and high-pressure compressors, a secondary air flow path which is located around the primary path and runs coaxially thereto, the turbine engine including vanes distributed about a main axis of the turbine engine. A pressurized air circuit draws air between the low-pressure compressor and the high-pressure compressor or in the high-pressure compressor and supplies at least one component located close to a main axis of the turbine engine. The pressurized air circuit includes a heat exchanger between the stream of pressurized air and the stream of air flowing in the secondary path, the heat exchanger being arranged in at least one of the straightening vanes, where a heat exchanger pipe is arranged, the pipe having a pressurized-air inlet and a pressurized-air outlet that are located at the same radial end of the vane.

An air-breathing turbojet engine for a hypersonic vehicle is shown. The engine comprises a pump for pumping a cryogenic fuel, an inlet configured to compress inlet air by one or more shocks, a cooler to cool the compressed inlet air using the cryogenic fuel, and a turbo-compressor to compress the air further. A precooler cools the compressed inlet air using compressed cooled air from the turbo-compressor. A combustor receives compressed cooled air from the turbo-compressor and a first portion of the cryogenic fuel for combustion. A first turbine expands and is driven by combustion products, and a second turbine expands and is driven by a second portion of the cryogenic fuel. The first turbine and the second turbine drive the turbo-compressor via a shaft. An afterburner receives combustion products from the first turbine and the second portion of the cryogenic fuel from the second turbine for combustion therein.

A system for a gas turbine includes a control system comprising a processor. The processor is configured to receive a signal indicating spray intercooling fluid demand of the gas turbine. The processor is configured to determine a rate of change of the spray intercooling fluid demand. The processor is configured to control flow of a nitrogen oxide (NO.sub.X) minimization fluid that reduces NO.sub.X emissions from the gas turbine based at least in part on the rate of change of the spray intercooling fluid demand.

A system for liquefying natural gas that includes a process and apparatus for enhancing the performance of one or more gas turbines. Gas turbine power output can be stabilized or even enhanced using the interstage cooling system configured according to one or more embodiments of the present invention. In one embodiment, partially compressed air from a lower compression stage of a gas turbine is cooled via indirect heat exchange with a primary coolant before being returned to a higher compression stage of the same gas turbine. Optionally, the interstage cooling system can employ one or more secondary coolants to remove the rejected heat from the primary coolant system.

A system for liquefying natural gas that includes a process and apparatus for enhancing the performance of one or more gas turbines. Gas turbine power output can be stabilized or even enhanced using the interstage cooling system configured according to one or more embodiments of the present invention. In one embodiment, partially compressed air from a lower compression stage of a gas turbine is cooled via indirect heat exchange with a primary coolant before being returned to a higher compression stage of the same gas turbine. Optionally, the interstage cooling system can employ one or more secondary coolants to remove the rejected heat from the primary coolant system.

An internal combustion engine includes an exhaust conduit having an exhaust port fluidically coupled to ambient fluid and having an internal cross-sectional area and an engine cylinder fluidically coupled to the exhaust conduit. A fluidic amplifier is disposed within the exhaust conduit and is fluidically coupled to the engine cylinder. The amplifier is further fluidically coupled to a source of primary fluid and is configured to introduce the primary fluid and at least a portion of fluid from the engine cylinder to the exhaust port.

A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°.

A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°.

A method of regulating a temperature associated with a heat exchanger assembly of a turbine engine, the method includes, in a single cycle: measuring the temperature of an air stream at the outlet from a heat exchanger; receiving a setpoint temperature for the air stream at the outlet from the heat exchanger; estimating a theoretical temperature for the air stream at the outlet from the heat exchanger as a function of an estimate of the shutter position of a controlled valve bleeding off a cooling air stream for the heat exchanger; determining a correction current from the difference between the measured temperature and the theoretical temperature; and determining a control current for the shutter from the difference between the measured temperature and the setpoint temperature and the correction current determined during the preceding cycle, the shutter position being determined from the control and correction currents determined during the preceding cycle.

Methods and apparatus for controlling liquid flow to a turbine fogging array. Some implementations are generally directed toward adjusting the output of a variable output pump that supplies water to the turbine fogging array. In some of those implementations, the output is adjusted based on a determined target pump output value that is indicative of a pump output required to change the moisture content of intake air of a combustion turbine to meet a target humidity value. Some implementations are generally directed toward actuating at least one control valve of a plurality of control valves that control liquid throughput to one or more fogging nozzles of a fogging array.