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

FIELD: engines and pumps.

SUBSTANCE: hypersonic aircraft engine comprises engine nacelle, air intake, casing, compressor with rotor compressor, combustion chamber installed after compressor and connected therewith an air duct, gas turbine, jet nozzle and fuel system connected with combustion chamber. Engine unit is made two-shaft. Compressor is made two-staged in form of in-series installed low and high pressure compressors, between which is air path, in which heat exchanger is installed. Inside air path coaxially with first shaft there is steam turbine with inlet and outlet headers. Input header is connected to output of heat exchanger, which input is connected to fuel system operating on water. Output header is connected with electrolytic cell, which first and second outputs are connected to combustion chamber. Downstream of combustion chamber there is gas turbine. Low-pressure compressor rotor is connected by first shaft to the steam turbine and compressor rotor is connected by second shaft with gas turbine.

EFFECT: invention is aimed at improving power performance of engine by increasing compression ratio of compressor, increased thrust and improved specific characteristics of propulsion system.

7 cl, 15 dwg