采用渐变微小通道的RBCC引射火箭复合冷却数值模拟研究  

Numerical Simulation of Composite Cooling of RBCC Ejector Rocket Using Gradient Micro-channels

作　　者：万昊 袁彪 秦飞[1] 李文强 张铎[1] 何国强[1] WAN Hao;YUAN Biao;QIN Fei;LI Wen-Qiang;ZHANG Duo;HE Guo-Qiang(Science and Technology on Combustion,Internal Flow and Thermo-structure Laboratory,School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,PR China;China Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]燃烧流动与热结构国家重点实验室西北工业大学航天学院,西安710072 [2]中国航发四川燃气涡轮研究院,成都610500

出　　处：《工程热物理学报》2020年第5期1179-1185,共7页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.51506180)。

摘　　要：引射火箭是火箭基组合循环(RBCC)发动机重要组成部分,为RBCC发动机提供大推力的同时承载极高的热载荷。本文设计了火箭推力室复合冷却结构,采用再生和液膜冷却相结合的方式对火箭喉部进行冷却,再生冷却通道在收敛段和扩张段的宽度从微尺度到小尺度渐变分布。采用数值模拟的方法研究了该复合冷却结构耦合传热特性。结果表明:渐变微小通道的设计能够强化喉部换热,液膜冷却能够大幅降低入口及下游热流密度,有效控制壁温。Ejector rocket is an important part of rocket-based combined cycle(RBCC)engine,which provides large thrust for RBCC engine while carrying a high thermal load.In this paper,the composite cooling structure of rocket thrust chamber is designed.The rocket throat is cooled by means of combination of regeneration and liquid film cooling.The width of regeneration cooling passage is gradually distributed from micro scale to small scale in the convergence and expansion sections.The coupled heat transfer characteristics of the composite cooling structure were studied by numerical simulation.The results show that the design of the micro-channel with gradual change can strengthen the throat heat transfer,the liquid film cooling can greatly reduce the inlet and downstream heat flux density,and effectively control the wall temperature.

关 键 词：RBCC 引射火箭 复合冷却 数值模拟 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]