| 摘要 |
FIELD: engines.SUBSTANCE: hypersonic engine comprises engine nacelle, air intake, housing, compressor, combustion chamber installed after compressor, gas turbine, jet nozzle and fuel system, using hydrogen, connected to combustion chamber. Engine is made by three-shaft scheme. Nacelle is provided with cooling system, which is connected to fuel system. Compressor is made three staged containing compressors of low, medium and high pressure. After low pressure compressor is installed first hydrogen-air heat exchanger. Between medium and high pressure compressors second hydrogen-air heat exchanger is installed. Inside air channel between compressors of low and medium pressures coaxial to shafts there is hydrogen bi-rotative turbine, which has input and output manifolds. Input manifold is connected to output of hydrogen-air heat exchangers, and output is with combustion chamber. Gas turbine is made of high pressure gas turbine and low pressure gas turbine. Bi-rotative hydrogen turbine and medium pressure compressor are connected to second shaft. High pressure compressor is connected by third shaft with low pressure gas turbine.EFFECT: invention is aimed at improving power performance of gas turbine engine, higher degree of compression of compressor, increasing engine thrust force and improving its specific characteristics.3 cl, 6 dwg |
