CPC F02C 6/08 (2013.01) [B64D 15/04 (2013.01); F05D 2220/323 (2013.01); F05D 2260/601 (2013.01); F05D 2260/606 (2013.01)] | 20 Claims |
1. A method for thermal management for an aircraft, the method comprising:
extracting a flow of compressed fluid from a compressor section of a propulsion system;
passing the flow of compressed fluid through an anti-ice system;
flowing the flow of compressed fluid from the anti-ice system to a turbine;
expanding the flow of compressed fluid across the turbine; and
flowing the expanded flow of compressed fluid to thermal communication with a thermal load.
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