㶲分析在协同吸气式火箭发动机中的应用

Application of Exergy Analysis in SynergisticAir-Breathing Rocket Engine

关键词:  循环系统  损失分布  㶲分析  㶲损失  㶲效率  协同吸气式火箭发动机

Key words:  Circulatory system  Loss distribution  Exergy analysis  Exergy loss  Exergy efficiency  SABRE

摘要:

为了研究协同吸气式火箭发动机（SABRE）循环系统的损失分布规律以及性能特性，针对SABRE4发动机系统开展了?分析，选择具有代表性的飞行马赫数Ma=4作为主要工况，研究不同工作参数对系统?损失分布和?效率的影响，通过调节?损失分布以获得最大?效率。研究结果表明：发动机?损失主要集中在燃烧过程和燃气排出，对于给定飞行条件，耗氢量越小，发动机?效率越大；当主路氢流量固定，调节预燃室氧燃比，存在合适的氧燃比使得发动机?效率最大；在给定主路氢流量条件下，发动机?效率随着飞行马赫数增大呈先增大后减小，在Ma=4附近达到最大，最大?效率为64.6%，对应的?损失分别为燃烧?损失16.2%，燃气排出?损失13.8%。通过对系统的?分析研究，明确了发动机内部损失分布。

Abstract:

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.