大推力液氧煤油发动机半系统装置降水击关机方案研究  

Study on Shutdown Scheme for Reducing Water Hammer Effect in Half System Engine of High Thrust LOX/kerosene Rocket

作　　者：高远皓 张晓光[1] 马冬英[1] 邢理想[1] 陈晖[1] GAO Yuanhao;ZHANG Xiaoguang;MA Dongying;XING Lixiang;CHEN Hui(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：《载人航天》2022年第5期683-689,共7页Manned Spaceflight

基　　金：载人航天领域预先研究项目(050301)。

摘　　要：针对大推力高压补燃循环液氧煤油发动机半系统装置试车中出现的燃料系统关机水击方面的问题,利用AMESim仿真平台建立发动机燃料系统仿真模型,对发动机关机过程进行了仿真分析。对比了关机速率、系统流阻分布及起动贮箱对水击压力峰值与水击波衰减的影响,结合发动机系统及试车台状态提出了降低关机工况点、增大燃料泵出口流阻以及利用起动贮箱降低水击压力等控制措施,并在试车中得到验证,基本消除了由燃料泵停泵带来的水击冲击,推力室燃料主阀关闭时刻水击压力降低了25%。There was a large water hammer in fuel system during the shutdown process of high thrust and high pressure staged combustion LOX/kerosene rocket engine half-system test.To solve this problem,an engine fuel system simulation model was established with the AMESim simulation plat-form,and the engine shutdown process was simulated and analyzed.Using the simulation model,the effects of shutdown rate,flow resistance distribution and starting tank on water hammer pressure were compared.Then,considering the engine and test bench system status,the following sugges-tions were put forward:lower the shutdown condition of the engine,increasing the flow resistance in pump outlet,using the starting tank during shutdown process to control water hammer pressure peak.The proposed measures were verified by the test.The results showed that the water hammer impact caused by shutdown of the pump was eliminated and the water hammer pressure decreased by 25%when the main fuel valve of the thrust chamber was closed.

关 键 词：液氧煤油发动机 关机方案 燃料系统水击 AMESIM仿真 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]