| 摘要 |
A thermal management system for a propulsion engine of a supersonic or hypersonic aircraft is provided that uses a single flow of endothermic fluid as engine fuel and as a heat sink for engine cooling. The system includes a plurality of heat exchangers in flow series arrangement. Each heat exchanger has a reactor portion, containing a catalyst, in heat exchange relation with a heat source portion. The single fluid flow flows through each of the reactor portions and heat source portions. The heat for the reaction in the reactor portions is provided by the fluid in the heat source portion which as a result is cooled. This cooled fluid is then reheated by flowing it past a hot portion of the engine after which the fluid can flow to another reactor portion or to the engine's combustor where it is ignited.
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