PROPULSION ENGINE OF SUPERSONIC AIRCRAFT Russian patent published in 2016 - IPC F02K3/00 F02C3/10 F02C3/107 

FIELD: aircraft engineering.

SUBSTANCE: supersonic propulsion engine comprises engine nacelle, air intake, casing, compressor with compressor rotor, combustion chamber, installed downstream of compressor and connected to it with air channel, gas turbine, jet nozzle, and fuel system connected with combustion chamber. Engine is made two-shaft. Compressor is made three-stage in form of installed in-series low-, medium-, and high-pressure compressors. Between low- and high-pressure compressors there is air channel, wherein heat exchanger is installed. Inside air channel coaxially to first shaft, birotatory steam turbine is installed, which has inlet and outlet manifolds. Input manifold is connected to output of heat exchanger, input thereof is connected to fuel system operating on water. Output manifold is connected with electrolytic cell, first and second outputs thereof are connected to combustion chamber. Downstream of combustion chamber there is gas turbine. Low-pressure compressor rotor is connected by first shaft to steam turbine. Medium-pressure compressor rotor is made integral with external rotor of steam turbine. High-pressure compressor rotor is connected by third shaft with rotor of gas turbine.

EFFECT: invention is aimed at higher compression ratio of compressor, increasing engine thrust force, and improving its specific characteristics.

7 cl, 15 dwg