COMBINED GAS-TURBINE ENGINE Russian patent published in 1995 - IPC

FIELD: aircraft engine engineering. SUBSTANCE: engine has heat-exchanger- cooler, compressor, steam-hydrogen turbine mounted on the same shaft as the compressor through a reduction gear, combustion chamber, heat-exchanger-evaporator, gas ejector, and jet nozzle mounted inside the housing in series and liquifying loop. The air liquifying loop is mounted outside of the housing and constructed as ring- like pipe coupled through a controlled shutter with the space downstream of the compressor. The heat-exchanger- condenser and separator with collector and tank- accumulator, which are connected with the inlet of the separator through a pipe line, are mounted inside the pipe. The liquifying loop also has a pump for supplying oxidizer to the combustion chamber connected with the nozzle bank via pipe lines. The nozzles are mounted inside the combustion chamber. The pump is mounted on the same shaft as the compressor and steam-hydrogen turbine between them via a reduction gear. The inlet of the combustion chamber is connected with the outlet of the steam-hydrogen turbine. The outlet of the combustion chamber is connected with the primary nozzle of the ejector whose inlet is connected with the inner housing wherein the combustion chamber with heat-exchanger- evaporator is mounted. EFFECT: enhanced efficiency. 1 dwg