RBCC发动机火箭及火箭冲压模态热力循环分析  

Thermodynamic cycle analysis of RBCC engine rocket and rocket-scramjet mode

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

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

出　　处：《火箭推进》2023年第5期39-45,共7页Journal of Rocket Propulsion

基　　金：国家重点项目。

摘　　要：为了研究RBCC发动机火箭模态及火箭冲压模态的工作特性,基于发动机地面自由射流试验结果,利用一维气动理论构建了发动机火箭及火箭冲压模态的性能分析模型,对发动机6 Ma来流条件的试验数据进行了处理,获得了发动机轴向的沿程气流参数,分析了发动机的热力循环、工作效率、有效能分布以及部件和排气中的有效能分配比例。结果表明:一维计算得到的推力与试验结果误差在5%以内;火箭冲压模态下火箭燃气的引入可以有效提升发动机的热循环效率(约提升20%),火箭燃气的引入对有效能产生率和有效能的分配比例影响不大,火箭冲压和冲压模态的有效能产生率分别为0.45和0.48;火箭模态推力增益产生的主要原因是火箭燃气的能量添加至冲压流道中,形成了有效的热力循环,产生了机械能增量,最终表现出推力增益,约为29%。Based on the ground free-jet test results,a performance analysis model of rocket and rocket-scramjet mode of RBCC engine was established by using one-dimensional aerodynamics theory.Then the engine test data at Mach 6 was processed and the flow parameters along the engine axis were obtained,wihle the thermodynamic cycle,work efficiency,exergy distribution and exergy components of each part were analyzed.Results proves the high accuracy of the established energy calculation model,and the thrust error between 1-D calculation and test results is less than 5.In rocket-scramjet mode,the introduction of rocket gas can effectively improve the thermal cycle efficiency of the engine by about 20,while it has little effect on the exergy generation rate and effective energy distribution ratio.The main reason for a thrust gain of 29 under rocket mode is that the energy of rocket gas is added to the scramjet flow tube,which forms an effective thermal cycle in the scramjet flow tube and produces a certain mechanical energy increment.

关 键 词：RBCC发动机 火箭模态 热力循环 有效能分析 一维分析 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]