摘要
建立了液体火箭发动机自引射工作过程传热分析模型。分析了圆柱型和二次喉道型引射器在不同冷却水流量下引射器的壁温和热流的变化,得到了引射器可靠工作的冷却水流量范围,引射器冷却水温升测试值和仿真值的一致性较好。
An analytical model for convective and radiate heat transfer between the hot gas and the ejector structure was established. The variation of wall temperature and heat flow of the cylindri- cal and secondary-throat ejectors in the case of different cooling water flow is analyzed. The range of mass flow rate of the cooling water needed for heat protection of the ejector was determined on the basis of detailed heat transfer analysis. The computational results show that the simulation results are consistent with the experimental measurements obtained in the vacuum cabin.
出处
《火箭推进》
CAS
2012年第1期31-37,共7页
Journal of Rocket Propulsion
基金
中国航天科技集团公司支撑项目
关键词
液体火箭发动机
引射器
传热
liquid rocket engine
ejector
heat transfer
作者简介
张忠利（1970-），男，高级工程师，研究领域为液体火箭发动机过程分析
