㶲分析在协同吸气式火箭发动机中的应用

In order to study the loss distribution and performance characteristics of the Synergistic Air-Breathing Rocket Engine (SABRE) circulatory system, the exergy analysis was carried out for SABRE4 engine system. The representative flight Mach number Ma=4 was chosen as the main operating condition to study the effects of different working parameters on the exergy loss distribution and exergy efficiency. The maximum exergy efficiency could be obtained by adjusting the exergy loss distribution. The results show that the engine exergy loss is mainly concentrated in the combustion process and gas discharge. For a given flight condition, the exergy efficiency of the engine will be greater as the hydrogen consumption is smaller. when the total hydrogen flow remains unchanged, there is a suitable oxygen-fuel ratio which makes the engine exergy efficiency maximum by changing the oxygen-fuel ratio of the preburner. For a given total hydrogen flow, the engine exergy efficiency increases first and then decreases with increasing the flight Mach number. The maximum exergy efficiency occurring in the vicinity of Ma=4 is 64.6%. The corresponding combustion exergy loss is 16.2% and 13.8% for gas exergy loss. Through the exergy analysis of the system, the exergy loss distribution of the engine is clarified.