Aerobic heat engine, particularly for the propulsion of hypersonic aircraft

摘要

Heat engine essentially characterised in that the turbine T precedes the compressor C and is separated from the latter by a cooling heat exchanger Ech supplied with cryogenic fluid. This engine thus operates according to a thermodynamic cycle which, with respect to conventional heat engines, is reversed. It is advantageous to take liquid hydrogen as the cryogenic fluid. The hydrogen leaving the exchanger Ech may then supply a combustion centre F1 situated upstream of the turbine, and a combustion centre F2 situated downstream of the compressor C. Application to hypersonic aircraft. <IMAGE>