液体火箭发动机涡轮泵低温空化实验研究进展  

Experimental studies on cavitating flow for liquid rocket engine cryogenic turbopump:Review

作　　者：项乐 许开富[1] 陈晖[1] 李随波 张凯 刘诗鑫[1] XIANG Le;XU Kaifu;CHEN Hui;LI Suibo;ZHANG Kai;LIU Shixin(Xi’an Aerospace Propulsion Institute,Xi’an 710100,China)

机构地区：[1]西安航天动力研究所,西安710100

出　　处：《航空学报》2023年第7期19-37,共19页Acta Aeronautica et Astronautica Sinica

基　　金：国家重大基础研究项目(613321)。

摘　　要：涡轮泵是泵压式低温液体火箭发动机的核心部件,素有发动机的心脏之称,其性能提升受空化条件限制。由于低温介质的空化热力学效应,低温空化过程相较于常温水空化更为复杂。首先介绍了低温涡轮泵空化实验系统的理论基础和设计要点,梳理了表征空化热效应的相似准则发展现状。接着详细介绍了目前国际上具有代表性的低温液体火箭发动机涡轮泵空化流动实验系统和相应的代表性研究成果,结果表明以热敏介质替代低温工质开展实验是当前技术发展趋势,但需要控制好不同介质之间的热效应相似换算关系;以先进光学手段和无线数据传输技术为代表的先进测试手段已逐渐被引入空化流场分析中,是值得进一步发展的研究方向。最后对空化热效应理论建模工作进展进行了总结归纳,发现当前的相关工作主要集中在稳态空化性能,针对非稳态特性的理论建模工作进展缓慢,亟待进一步的深入研究。本文可为进一步提升中国泵压式低温液体火箭发动机性能和可靠性提供有意义的参考。Turbopump,which can be called the heart of engines,is a critical component of the cryogenic Liquid Rocket Engine(LRE).The improvement of its performance is limited by cavitation conditions.Due to cavitation ther⁃modynamic effect of cryogenic fluids,the cryogenic cavitation is far more complicated than room-temperature water cavitation.The theoretical basis and key design points of cryogenic turbopump cavitation experimental systems are in⁃troduced,and the state-of-the-art similarity criterion for the cavitation thermal effect is revealed.Then several typical cryogenic LTR turbopump cavitating flow experimental systems and investigation results are introduced in detail,it is found that the application of thermal sensitive fluids as the substitution cryogen is technology development tendency,but it is important to keep the thermal effect similarity;Developed test technologies such as optics technique and wire⁃less data transform have been introduced into cavitating flow analysis,they are worth to develop further.At last,the theoretical modeling of the cavitation thermal effect is concluded,it is found that most published works focus on the steady cavitation performance,the theoretical modeling of unsteady cavitation characteristics have been rarely re⁃ported.This paper may provide reference for further promoting the performance and reliability of the pump-pressurizing cryogenic liquid rocket engine.

关 键 词：液体火箭发动机 低温空化 涡轮泵 热力学效应 建模 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程] TV131.3[水利工程—水力学及河流动力学]