| 摘要 |
Aerobic combustion engine with reverse cycle of the type including, for upstream to downstream, an air inlet EA, a combustion chamber for temperature matching or first combustion chamber F1, a main turbine T, a cryogenic exchanger E fed with hydrogen, a main compressor C driven by the turbine T and possibly a reheat chamber F2 upstream of the outlet nozzle TS. This motor furthermore includes, between the air inlet EA and the said first combustion chamber F1, a pressure-matching module C', Th, which is set so as to provide a substantially constant cut-off pressure Pi2 at the entry of the said first combustion chamber F1 for a very different Mach numbers. This module comprises a matching compressor C' and a hydrogen turbine Th driving this compressor and fed by the said cryogenic exchanger E. Applications to hypersonic propulsion. <IMAGE>
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