Abstract
Abstract The hydrogen powered precooled aeroengine is highly expected to drive future advanced hypersonic vehicle. The paralleled heat release and compression system has shown its crucial role of guaranteeing the favorable performance of the engine. However, the superior performance of the paralleled system is based on complicated structure with separated flow paths, large scale heat exchangers and unique design of turbomachinery. A trade-off analysis in this paper shows that the paralleled design causes the increase in heat exchanger weight and size, and the high demands of component reliability. Besides, the working conditions, such as corrected rotate speed and flow path size of the compressors inside a system are considerably different from each other. It is proved that a comprehensive evaluation, including considerations on performance, negative effects, and technological challenges, is fundamental to the development of the paralleled heat release and compression system of hypersonic aeroengine.
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