ENGINE OF HYPERSONIC AIRCRAFT Russian patent published in 2016 - IPC F02K3/04 

FIELD: engines and pumps.

SUBSTANCE: engine of hypersonic aircraft comprises fuselage, air intake, housing, compressor of low, medium and high pressure with rotors, combustion chamber installed after high pressure compressor, gas turbine, the first shaft connecting the compressor of low pressure and gas turbine, jet nozzle and fuel system, using hydrogen, connected to the combustion chamber. Fuselage manufactured with its cooling system, which is connected to the fuel system. After low pressure compressor is air path, in which a first hydrogen-air heat exchanger is installed. Inside the air channel coaxially with the shaft the hydrogen turbine is installed, it has input and output manifolds. Input manifold is connected to the output of their first hydrogen-air heat exchanger, and output-with combustion chamber. Between the compressor of medium pressure and high pressure compressor the second hydrogen-air heat exchanger is installed. Before the gas turbine the HP gas turbine is installed. Hydrogen turbine and compressor of medium pressure are connected to the second shaft installed coaxially with the first. High pressure compressor is connected with high-pressure turbine by third shaft.

EFFECT: invention is aimed at improving power performance of gas turbine engine and improving its specific characteristics.

3 cl, 6 dwg