| 摘要 |
A heat exchange system (10) for a supersonic flight vehicle. A first conduit (32) connects the gas (e.g., helium) exit (30) of a compressor (20) of a gas-driven turbocompressor to the gas inlet (24) of a turbine (18) of the turbocompressor, and a second conduit (34) connects the gas outlet (26) of the turbine to the gas entrance (28) of the compressor. The first conduit (32) has a portion positioned near a hotter temperature region (12) (e.g., the combustor wall) and the second conduit (34) has a portion positioned near a colder temperature region (14) (e.g., the fuel region) of the flight vehicle. The temperature difference self powers the turbocompressor which can transfer large amounts of heat and which is hermetically-sealed in a housing (37) against gas leaks. <IMAGE>
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