火箭推进2012，Vol.38Issue(1)：31-37,7.
液体火箭发动机自引射工作过程传热研究
Investigation on heat transfer characteristics of LRE self-ejecting process
摘要
Abstract
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.关键词
液体火箭发动机/引射器/传热Key words
liquid rocket engine/ejector/heat transfer分类
航空航天引用本文复制引用
张忠利,周立新,张蒙正..液体火箭发动机自引射工作过程传热研究[J].火箭推进,2012,38(1):31-37,7.基金项目
中国航天科技集团公司支撑项目 （）
