常规推进剂火箭发动机膜冷却长度试验与仿真

侯瑞峰; 陈建华; 李龙飞; 杨建文; 张国栋

doi:10.13224/j.cnki.jasp.20230038

常规推进剂火箭发动机膜冷却长度试验与仿真

doi: 10.13224/j.cnki.jasp.20230038

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

基金项目: 173科技基础加强计划重点基础研究项目

详细信息

作者简介:
侯瑞峰（1995-），男，博士生，主要从事液体火箭发动机高压推力室热防护技术研究。E-mail：hrfchina@163.com

中图分类号: V434
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出版历程
- 收稿日期: 2023-01-19
- 网络出版日期: 2023-09-12

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

1.
Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation，Xi’an 710100，China
2.
School of Energy and Power Engineering，Xi’an Jiaotong University，Xi’an 710049，China

摘要

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。
- 液体火箭发动机 /
- 推力室 /
- 膜冷却 /
- 冷却长度 /
- 冷却效率
Abstract:
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.
- liquid propellant rocket engine /
- thrust chamber /
- film cooling /
- cooling length /
- cooling efficiency

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图 1 试验系统的主要组成

Figure 1. Main components of the test system

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图 2 温度传感器的位置

Figure 2. Position of temperature sensor

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图 3 推力室外形及冷却剂流路

Figure 3. Thrust chamber profile and coolant flow path

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图 4 起动和关机的时序

Figure 4. Time sequence of start-up and shutdown

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图 5 从后方尾部观察的推力室情况

Figure 5. Thrust chamber condition observed from the rear

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图 6 推力室剖切结果及理化检验情况

Figure 6. Thrust chamber cutting observation and metallographic examination

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图 7 辐射传热当量的处理方法

Figure 7. Equivalent treatment of radiation heat transfer

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图 8 仿真计算程序逻辑

Figure 8. Computational logic of simulation program

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图 9 推力室头部局部的壁温不均现象

Figure 9. Non-uniformity of wall temperature at the head of thrust chamber

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图 10 异向非等温流体交汇处的温度

Figure 10. Temperature of opposite non-isothermal fluid intersection

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图 11 三维仿真计算模型

Figure 11. Three-dimensional simulation model

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图 12 三维传热计算结果

Figure 12. Results of three-dimensional heat transfer simulation

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图 13 喷注器处的氧化剂温度的实测值

Figure 13. Temperature test result of oxidizer in the injector

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图 14 推力室圆柱段尾部的外壁面温度的实测值

Figure 14. Temperature test result of the external wall of cylinder rear of thrust chamber

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图 15 液膜温度和流量的仿真结果

Figure 15. Simulation of temperature and flow of liquid film

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表 1 推力室尺寸及工作参数

Table 1. Thrust chamber size and working parameters

类别	参数	数值
尺寸	推力室长度/mm	525
	圆柱段直径/mm	150
	喷管喉部直径/mm	90
压强	燃烧室压强/MPa	4.4
压强	冷却通道压强/MPa	6.0
推进剂	氧化剂总流量/（kg/s）	11.3
	燃料总流量/（kg/s）	4.9
	燃料液膜流量/（kg/s）	0.7
	燃料入口温度/K	300
	氧化剂入口温度/K	278

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表 2 液/气膜有效长度的测量结果

Table 2. Measurement of the effective length of liquid film and gas film

试件序号	工作时间/s	液膜长度/mm	气膜长度/mm
1	1350	76	122
2	711	77	125
3	136	74	125
4	803	72	122
5	650	75	126
6	650	74	125
平均值		74.67	124.17

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表 3 燃气流物性参数计算结果

Table 3. Results of physical property of gas flow

参数	数值
总温/K	3337.4
密度/（kg/m³）	3.6
比定压热容/（J/（kg·K））	2059.9
比热比	1.2
动力黏度/10⁻⁷ （N·s/m²）	1031.9
热导率/10⁻³ （W/（m·K））	321.7

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表 4 燃气流化学组成成分

Table 4. Chemical composition of gas flow

成分	摩尔分数/%	成分	摩尔分数/%
H₂O	33.803	CO₂	7.191
N₂	28.168	H₂	9.054
CO	15.456	NO	0.627

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表 5 异向非等温流体交汇处的热流方向

Table 5. Heat flux direction of opposite non-isothermal fluid intersection

热流类别	头部处	平衡处	身部处
辐射传热（燃气发出）	朝外↑	朝外↑	朝外↑
表面传热（燃气-液膜）	朝外↑	朝外↑	朝外↑
表面传热（液膜-气壁面）	朝内↓	朝内↓	朝内↓
表面传热（液壁面-再生冷却剂）	朝内↓	平衡→	朝外↑

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表 6 液膜流量对有效长度的影响

Table 6. Influence of liquid film flow on effective length

液膜流量/（kg/s）	液膜长度/mm
0.6	43.5（−42%）
0.7	75.0（0%）
0.8	131.0（75%）

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表 7 气膜有效长度的校验情况

Table 7. Verification of effective lengths of gas film

气膜长度/mm	气膜冷却效率
120	0.704
122	0.695
124	0.687
126	0.679
128	0.671

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参考文献(21)

[1]	侯瑞峰,李龙飞,陈建华,等. 冷却环带结构形态及离心角度对流场的影响[J]. 推进技术,2023,44(7): 215-225. doi: 10.13675/j.cnki.tjjs.2209084 HOU Ruifeng,LI Longfei,CHEN Jianhua,et al. Effects of structure shape and centrifugal angle on flow characteristics of coolant from cooling film injection slot[J]. Journal of Propulsion Technology,2023,44(7): 215-225. (in Chinese) doi: 10.13675/j.cnki.tjjs.2209084
[2]	侯瑞峰, 陈建华, 曹晨. 高室压液氧烃发动机冷却结构适应性分析[R]. 昆明: 中国航天第三专业信息网第四十届技术交流会, 2019.
[3]	陈建华,张贵田,夏开红,等. 液氧煤油发动机高压推力室冷却技术[J]. 宇航学报,2008,29(1): 242-245, 259. doi: 10.3873/j.issn.1000-1328.2008.01.043 CHEN Jianhua,ZHANG Guitian,XIA Kaihong,et al. Cooling techniques for high pressure chamber of LOX/kerosene engine[J]. Journal of Astronautics,2008,29(1): 242-245, 259. (in Chinese) doi: 10.3873/j.issn.1000-1328.2008.01.043
[4]	韩兆鹏,张强,张建伟,等. 基于Lagrange液膜方法的小推力液体火箭发动机耦合传热策略研究[J]. 推进技术,2018,39(9): 2035-2042. doi: 10.13675/j.cnki.tjjs.2018.09.014 HAN Zhaopeng,ZHANG Qiang,ZHANG Jianwei,et al. Coupling heat transfer strategy for small thrust liquid rocket engine based on Lagrange film method[J]. Journal of Propulsion Technology,2018,39(9): 2035-2042. (in Chinese) doi: 10.13675/j.cnki.tjjs.2018.09.014
[5]	MUNK D J,SELZER M,STEVEN G P,et al. Topology optimization applied to transpiration cooling[J]. AIAA Journal,2019,57(1): 297-312. doi: 10.2514/1.J057411
[6]	FU Pengfei,HOU Lingyun,REN Zhuyin,et al. A droplet/wall impact model and simulation of a bipropellant rocket engine[J]. Aerospace Science and Technology,2019,88: 32-39. doi: 10.1016/j.ast.2019.03.018
[7]	王慧洁,许坤梅. 液体火箭发动机燃烧室壁液膜冷却的数值模拟[J]. 航空动力学报,2018,33(11): 2660-2668. doi: 10.13224/j.cnki.jasp.2018.11.012 WANG Huijie,XU Kunmei. Numerical simulation of liquid film cooling for combustion chamber wall of liquid rocket engine[J]. Journal of Aerospace Power,2018,33(11): 2660-2668. (in Chinese) doi: 10.13224/j.cnki.jasp.2018.11.012
[8]	向纪鑫,张萌,李志强,等. 液氧/甲烷液体火箭发动机推力室跨临界液膜冷却数值模拟[J]. 推进技术,2022,43(11): 291-302. doi: 10.13675/j.cnki.tjjs.210633 XIANG Jixin,ZHANG Meng,LI Zhiqiang,et al. Numerical simulation of transcritical liquid film cooling in LOX/methane liquid rocket engine thrust chambers[J]. Journal of Propulsion Technology,2022,43(11): 291-302. (in Chinese) doi: 10.13675/j.cnki.tjjs.210633
[9]	STROKACH E A,BOROVIK I N,BAZAROV V G,et al. Numerical study of operational processes in a GO_x-kerosene rocket engine with liquid film cooling[J]. Propulsion and Power Research,2020,9(2): 132-141. doi: 10.1016/j.jppr.2020.04.004
[10]	LI X Y, REN J, JIANG H D. Full field algebraic anisotropic eddy viscosity model for the film cooling flows[R]. ASME Paper GT2012-68667, 2012.
[11]	LEE H,JEONG G,LEE H,et al. Hydraulic characteristics of liquid film generated by slit injector[J]. International Journal of Aeronautical and Space Sciences,2019,20(2): 433-441. doi: 10.1007/s42405-019-00167-4
[12]	SAKO N,HAYASHI J,DAIMON Y,et al. Experimental analysis of the spreading of a liquid film on a bipropellant thruster chamber wall[J]. Journal of Thermal Science and Technology,2021,16(1): 1-11.
[13]	LUDESCHER S,OLIVIER H. Experimental investigations of film cooling in a conical nozzle under rocket-engine-like flow conditions[J]. AIAA Journal,2019,57(3): 1172-1183. doi: 10.2514/1.J057486
[14]	PONOMARENKO A. RPA: tool for rocket propulsion analysis thermal analysis of thrust chambers[EB/OL]. [2013-01-01]. http: //www.propulsion-analysis.com/.
[15]	侯瑞峰,李龙飞,陈建华,等. 液体火箭发动机不同室压下冷却方案适用范围[J]. 航空动力学报,2022,37(12): 2797-2806. doi: 10.13224/j.cnki.jasp.20220378 HOU Ruifeng,LI Longfei,CHEN Jianhua,et al. Adaptability of cooling structure schemes of liquid propellant rocket engine thrust chamber under different pressures[J]. Journal of Aerospace Power,2022,37(12): 2797-2806. (in Chinese) doi: 10.13224/j.cnki.jasp.20220378
[16]	吴有亮. 基于Modelica的液体火箭发动机系统建模与仿真研究[D]. 北京: 中国航天科技集团公司第一研究院, 2018. WU Youliang. Study on modeling and simulation of liquid rocket engine built with modelica language[D]. Beijing: The First Academy of China Aerospace Science and Technology Corporation, 2018. (in Chinese)
[17]	PAVLI A J, CURLEY J K, MASTERS P A, et al. Design and cooling performance of a dump- cooled rocket engine[R]. NASA TN D-3532, 1966.
[18]	BARTZ D R. A simple equation for rapid estimation of rocket nozzle convective heat transfer coefficients[J]. Jet Propulsion,1957,27(1): 49-51. doi: 10.2514/8.12572
[19]	HOWELL J. Film cooling design criteria for small rocket engines[R]. AIAA-1968-617, 1968.
[20]	GRISSON W M. Liquid film cooling in rocket engines[R]. AD-A234 288, 1991.
[21]	王治军, 常新龙, 田干. 液体火箭发动机推力室设计[M]. 北京: 国防工业出版社, 2014.