RBCC发动机冲压模态热力循环分析  

Analysis on thermodynamic cycle of scramjet mode for RBCC engine

作　　者：南向军[1] 李斌[2] 何国强[3] 张蒙正[1] NAN Xiangjun;LI Bin;HE Guoqiang;ZHANG Mengzheng(Xi'an Aerospace Propulsion Institute,Xi'an 710100,China;Academy of Aerospace Propulsion Technology,Xi'an 710100,China;Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]西安航天动力研究所,陕西西安710100 [2]航天推进技术研究院,陕西西安710100 [3]西北工业大学,陕西西安710072

出　　处：《火箭推进》2022年第6期17-25,共9页Journal of Rocket Propulsion

摘　　要：为了研究RBCC发动机的真实工作情况,基于地面试验数据,建立了一维性能分析模型,对发动机4 Ma、6 Ma冲压模态不同余气系数条件的性能进行了计算,与试验结果进行了对比,获得了发动机沿程气流参数分布。利用计算结果构建了发动机热力循环,分析了余气系数对循环效率、推进效率等性能参数的影响,提出了有效能产生率的概念,研究了余气系数对有效能产生率的影响以及有效能损失的途径。研究表明,建立的一维分析模型可以较好地计算发动机推力性能,与试验测量误差在10%以内;发动机真实热力循环并非严格的等压释热,其有效能产生率在0.5~0.7之间;提高有效能产生率和减少排气中的有效能是发动机性能优化的主要方向。In order to study the real working condition of RBCC engine,based on the ground test data,an one dimensional analysis model was established to calculate the performance of engine scramjet mode at different residual air coefficient of 4 Ma and 6 Ma conditions.Compared with the test results,the distribution of flow parameters along the engine was obtained.The thermodynamic cycle of engine was conducted by using the calculation results,and the influence of residual gas coefficient on the cycle efficiency and propulsion efficiency was analyzed.The concept of exergy generation rate was put forward,and the effect of residual gas coefficient on exergy generation rate and loss paths of exergy were studied.Research shows that the one dimensional performance analysis model can calculate the engine thrust performance well,and the error is less than 10%.The real thermal cycle of the engine is not strict isobaric heat release,and its exergy generation rate is between 0.5-0.7.Improving the exergy generation rate and reducing the exergy of exhaust are the main directions for optimizing the engine performance.

关 键 词：RBCC发动机 冲压模态 热力循环 有效能分析 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]