常规推进剂火箭发动机膜冷却长度试验与仿真  

Test and simulation of film cooling length in conventional propellant rocket engine

作　　者：侯瑞峰 陈建华 李龙飞 杨建文 张国栋 HOU Ruifeng;CHEN Jianhua;LI Longfei;YANG Jianwen;ZHANG Guodong(Science and Technology on Liquid Rocket Engine Laboratory,Xi’an Aerospace Propulsion Institute,China Aerospace Science and Technology Corporation,Xi’an 710100,China;School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China)

机构地区：[1]中国航天科技集团有限公司西安航天动力研究所液体火箭发动机技术重点实验室,西安710100 [2]西安交通大学能源与动力工程学院,西安710049

出　　处：《航空动力学报》2023年第11期2799-2808,共10页Journal of Aerospace Power

基　　金：173科技基础加强计划重点基础研究项目。

摘　　要：针对液体火箭发动机推力室中膜冷却技术的有效作用范围,基于型号样机采用试验方法获得了液膜和气膜的有效长度数据、再生冷却剂的温升数据、外壁面测点温度,采用仿真方法获得了液膜的升温/蒸发长度、气膜冷却效率的分布、温升结果和外壁温结果。试验获得的再生冷却剂温升差值为90.1 K,测点外壁温约340 K。仿真计算的温升差值为89.7 K,测点外壁温约330 K。试验获得的液膜有效长度为74.67 mm,气膜有效长度为124.2 mm。仿真得到的液膜有效长度为75.0 mm,其中升温长度为66.0 mm,蒸发长度为9.0 mm。校验后得到气膜有效的冷却效率判断标准为≮0.687。通过比对试验结果和仿真结果,验证了仿真程序的适用性和准确性,得到了判断气膜是否有效的冷却效率临界值,可为推力室热防护设计提供参考。In view of the effective range of film cooling in the thrust chamber of liquid propellant rocket engine,based on the model thrust chamber,the effective length data of liquid and gas films,the temperature rise of regenerative coolant and the temperature of outside wall were obtained by test.Heating length and evaporation length of liquid film,distribution of gas film cooling efficiency,regenerative coolant temperature rise and outside wall temperature were obtained by simulation.The temperature rise of the regenerative coolant was 90.1 K,and the outside wall temperature was about 340 K by test.The regenerative coolant temperature rise and outside wall temperature were 89.7 K and about 330 K separately calculated by simulation.The effective length of liquid film was 74.67 mm and that of gas film was 124.2 mm by test.The effective length of the liquid film was 75.0 mm by simulation,in which the heating length was 66.0 mm and the evaporation length was 9.0 mm.The standard for judging effective cooling efficiency of gas film obtained after calibration was 0.687.By comparing the test results and simulation results,the applicability and accuracy of the simulation program were verified,and the critical value of gas film cooling efficiency was obtained,which can be used as a reference for thermal protection design of thrust chamber.

关 键 词：液体火箭发动机 推力室 膜冷却 冷却长度 冷却效率 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]