有气体吹入的燃气发生器头腔充填过程仿真

韩佳宁; 周晨初; 陆嘉伟; 于锐渤; 张黎辉

doi:10.13224/j.cnki.jasp.20220772

有气体吹入的燃气发生器头腔充填过程仿真

doi: 10.13224/j.cnki.jasp.20220772

1.
北京航空航天大学宇航学院，北京 102206
2.
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

详细信息

作者简介:
韩佳宁（1999−），男，硕士生，主要从事液体火箭发动机系统仿真研究

通讯作者:
张黎辉（1966−），女，副教授，博士，主要从事液体火箭发动机系统设计、仿真和优化研究。E-mail：zhanglihui@buaa.edu.cn

中图分类号: V434
计量
- 文章访问数: 126
- HTML浏览量: 52
- PDF量: 23
- 被引次数: 0
出版历程
- 收稿日期: 2022-10-08
- 网络出版日期: 2024-03-27

Simulation on filling process of gas generator head with gas injecting

1.
School of Astronautics，Beihang University，Beijing 102206，China
2.
Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute，Xi’an 710100，China

摘要

摘要:
以高压补燃液氧煤油火箭发动机起动过程为背景，研究有气体吹入的燃气发生器头腔充填过程。首先通过实验，确定马尔基涅利经验关系式所需系数$ n $为2.29，验证了经验关系式的准确性；其次利用有限元分割建立有气体吹入的燃气发生器头腔的一维分布参数模型，并将实验数据与经验关系式、一维分布模型仿真结果进行对比分析，证明了该模型的准确性。结果表明：一维分布参数模型稳态压强与实验数据平均值误差为0.429%，经验关系式（集中参数模型）误差为1.464%；喷嘴喷注面积增加，头腔内建压速度减慢，且稳定压强值降低；头腔体积增加，建压速度减慢，但压强稳定值不变；头腔摩擦因数增加，压强稳定值与充填速度降低。
- 液氧煤油发动机 /
- 燃气发生器 /
- 头腔充填 /
- 有限元分割 /
- Amesim仿真
Abstract:
Based on the starting process of high-pressure combustion liquid oxygen kerosene rocket engine, the filling process of the head cavity of the gas generator with gas injecting was studied. Firstly, experiments indicated that the coefficient n required for the Marquinelli empirical relation was determined to be 2.29, which verified the accuracy of the empirical relationship. Secondly, the finite element segmentation was used to establish a one-dimensional distribution parameter model of the head cavity of the gas generator with gas injecting, and the experimental data were compared and analyzed with the empirical relationship and the simulation results of the one-dimensional distribution model, which proved the accuracy of the model. The results showed that the error between steady-state pressure and the mean value of experimental data of the one-dimensional distribution parameter model was 0.429%, and the error of the empirical relationship (centralized parameter model) was 1.464%; the flow area of the injecting increased, the pressure built into the head cavity slowed down, and the stable pressure value decreased; the volume of the head cavity increased, and the pressure building speed slowed down, but the pressure stability value was kept unchanged; the resistance coefficient of the head cavity increased, and the pressure stability value and filling speed decreased.
- LOX/kerosene engine /
- gas generator /
- head cavity filling /
- finite element segmentate /
- Amesim simulation

HTML

图 1 实验系统

Figure 1. Experimental system

下载: 全尺寸图片幻灯片

图 2 实验头腔结构图

1 螺栓；2 螺母；3 平垫圈；4 喷注面板；5 密封圈； 6 顶盖；7、8 接头；9 喷嘴盖；10 喷嘴；11 密封圈。

Figure 2. Structure diagram of experimental head cavity

下载: 全尺寸图片幻灯片

图 3 压强计算值与实验值对比

Figure 3. Comparison of calculated and experimental pressure

下载: 全尺寸图片幻灯片

图 4 单元划分示意图

Figure 4. Schematic diagram of unit division

下载: 全尺寸图片幻灯片

图 5 集中参数模型仿真结果与实验数据对比

Figure 5. Comparison of simulation results and experimental data of centralized parameter model

下载: 全尺寸图片幻灯片

图 6 一维分布参数模型仿真结果与实验数据对比

Figure 6. Comparison of simulation results and experimental data of one-dimensional distributed parameter model

下载: 全尺寸图片幻灯片

图 7 两种模型间压强的对比

Figure 7. Comparison of pressure between two models

下载: 全尺寸图片幻灯片

图 8 各分段压强变化

Figure 8. Pressure change in each segment

下载: 全尺寸图片幻灯片

图 9 头腔各单元内喷嘴流出流量

Figure 9. Flow rate of nozzle in each unit of head cavity

下载: 全尺寸图片幻灯片

图 10 头腔结构参数的影响

Figure 10. Influence of structural parameters of head cavity

下载: 全尺寸图片幻灯片

图 11 摩擦因数对压强的影响

Figure 11. Effect of drag coefficient on pressure

下载: 全尺寸图片幻灯片

表 1 各工况下系数n

Table 1. Coefficient n under different working conditions

实验序号	仅有气体压降$ /\mathrm{M}\mathrm{P}\mathrm{a} $	仅有液体压降$ /\mathrm{M}\mathrm{P}\mathrm{a} $	两相时压降$ /\mathrm{M}\mathrm{P}\mathrm{a} $	系数$ n $
9	0.1103	0.0535	0.3891	2.29974
10	0.1908	0.0535	0.5351	2.27864
11	0.2876	0.0535	0.707	2.29336
12	0.3552	0.0535	0.8204	2.29981
13	0.1103	0.0663	0.4493	2.37378
14	0.1908	0.0663	0.5891	2.30218
15	0.2876	0.0663	0.7573	2.28856
16	0.3552	0.0663	0.8627	2.27232

下载: 导出CSV

参考文献(18)

[1]	谭永华. 大推力液体火箭发动机研究[J]. 宇航学报,2013,34(10): 1303-1308. TAN Yonghua. Research on large thrust liquid rocket engine[J]. Journal of Astronautics,2013,34(10): 1303-1308. (in Chinese doi: 10.3873/j.issn.1000-1328.2013.10.002 TAN Yonghua. Research on large thrust liquid rocket engine[J]. Journal of Astronautics, 2013, 34(10): 1303-1308. (in Chinese) doi: 10.3873/j.issn.1000-1328.2013.10.002
[2]	张贵田高压补燃液氧煤油发动机[M]. 北京: 国防工业出版社,2005.
[3]	汪小卫,金平,张国舟,等. 全流量补燃循环试验发动机启动过程[J]. 推进技术,2008,29(4): 407-411. WANG Xiaowei,JIN Ping,ZHANG Guozhou,et al. Start-up in a subscale full flow staged combustion cycle engine[J]. Journal of Propulsion Technology,2008,29(4): 407-411. (in Chinese doi: 10.3321/j.issn:1001-4055.2008.04.004 WANG Xiaowei, JIN Ping, ZHANG Guozhou, et al. Start-up in a subscale full flow staged combustion cycle engine[J]. Journal of Propulsion Technology, 2008, 29(4): 407-411. (in Chinese) doi: 10.3321/j.issn:1001-4055.2008.04.004
[4]	孙靖阳,马原,张淼,等. 燃气发生器内气体吹除过程压降特性实验研究[J]. 西安交通大学学报,2023,57(3): 79-85,96. SUN Jingyang,MA Yuan,ZHANG Miao,et al. Experimental study of pressure drop characteristics on gas injection and emulsification process in gas generator chamber[J]. Journal of Xi’an Jiaotong University,2023,57(3): 79-85,96. (in Chinese doi: 10.7652/xjtuxb202303007 SUN Jingyang, MA Yuan, ZHANG Miao, et al. Experimental study of pressure drop characteristics on gas injection and emulsification process in gas generator chamber[J]. Journal of Xi’an Jiaotong University, 2023, 57(3): 79-85, 96. (in Chinese) doi: 10.7652/xjtuxb202303007
[5]	岳春国,李进贤,侯晓,等. 变推力液体火箭发动机综述[J]. 中国科学(E辑: 技术科学),2009,39(3): 464-468. YUE Chunguo,LI Jinxian,HOU Xiao,et al. Summary of variable thrust liquid rocket engine[J]. Science in China (Series E:Technological Sciences),2009,39(3): 464-468. (in Chinese YUE Chunguo, LI Jinxian, HOU Xiao, et al. Summary of variable thrust liquid rocket engine[J]. Science in China (Series E: Technological Sciences), 2009, 39(3): 464-468. (in Chinese)
[6]	张小平,丁丰年. 富氧补燃循环发动机启动过程[J]. 推进技术,2004,25(1): 82-85. ZHANG Xiaoping,DING Fengnian. Starting process of oxidizer-rich staged combustion rocket engine[J]. Journal of Propulsion Technology,2004,25(1): 82-85. (in Chinese doi: 10.3321/j.issn:1001-4055.2004.01.022 ZHANG Xiaoping, DING Fengnian. Starting process of oxidizer-rich staged combustion rocket engine[J]. Journal of Propulsion Technology, 2004, 25(1): 82-85. (in Chinese) doi: 10.3321/j.issn:1001-4055.2004.01.022
[7]	马冬英,卢钢,张小平,等. 液氧/甲烷燃气发生器试验研究[J]. 火箭推进,2013,39(3): 21-26. MA Dongying,LU Gang,ZHANG Xiaoping,et al. Research on hot tests of LOX/methane gas generator[J]. Journal of Rocket Propulsion,2013,39(3): 21-26. (in Chinese doi: 10.3969/j.issn.1672-9374.2013.03.004 MA Dongying, LU Gang, ZHANG Xiaoping, et al. Research on hot tests of LOX/methane gas generator[J]. Journal of Rocket Propulsion, 2013, 39(3): 21-26. (in Chinese) doi: 10.3969/j.issn.1672-9374.2013.03.004
[8]	DRESSLER G. Summary of deep throttling rocket engines with emphasis on Apollo LMDE [R]. AIAA-2006-5220,2006.
[9]	CASIANO M J,HULKA J R,YANG V. Liquid-propellant rocket engine throttling: a comprehensive review[J]. Journal of Propulsion and Power,2010,26(5): 897-923. doi: 10.2514/1.49791
[10]	曹泰岳. 火箭发动机动力学[M]. 长沙: 国防科技大学出版社,2004.
[11]	BELYAEV E N,CHVANOV V K,CHERVAKOV V V. The outflow of a two-phase gas-liquid mixture from the mixing head of a gas generator when starting a liquid-propellant rocket engine[J]. High Temperature,2005,43(3): 446-451.
[12]	张远君. 两相流体动力学: 基础理论及工程应用[M]. 北京: 北京航空学院出版社,1987.
[13]	李程,刘站国,徐浩海. 双推力室起动同步性研究[J]. 火箭推进,2014,40(4): 16-21,56. LI Cheng,LIU Zhanguo,XU Haohai. Study on synchronous ignition of dual-thrust chamber engine[J]. Journal of Rocket Propulsion,2014,40(4): 16-21,56. (in Chinese doi: 10.3969/j.issn.1672-9374.2014.04.004 LI Cheng, LIU Zhanguo, XU Haohai. Study on synchronous ignition of dual-thrust chamber engine[J]. Journal of Rocket Propulsion, 2014, 40(4): 16-21, 56. (in Chinese) doi: 10.3969/j.issn.1672-9374.2014.04.004
[14]	谭永华,杜飞平,陈建华,等. 液氧煤油高压补燃循环发动机深度变推力系统方案研究[J]. 推进技术,2018,39(6): 1201-1209. TAN Yonghua,DU Feiping,CHEN Jianhua,et al. Study on deep variable thrust system of LOX/kerosene high pressure staged combustion engine[J]. Journal of Propulsion Technology,2018,39(6): 1201-1209. (in Chinese TAN Yonghua, DU Feiping, CHEN Jianhua, et al. Study on deep variable thrust system of LOX/kerosene high pressure staged combustion engine[J]. Journal of Propulsion Technology, 2018, 39(6): 1201-1209. (in Chinese)
[15]	GAUFFRE M C,NEAU H,SIMONIN O,et al. Numerical simulation of dome filling in an experimental rocket engine mockup[J]. Journal of Propulsion and Power,2014,30(3): 617-627. doi: 10.2514/1.B34904
[16]	刘昆,张育林. 液体推进系统充填过程的有限元状态变量模型[J]. 推进技术,2001,22(1): 19-21. LIU Kun,ZHANG Yulin. Finite element state-variable models for the priming process of feed lines[J]. Journal of Propulsion Technology,2001,22(1): 19-21. (in Chinese doi: 10.3321/j.issn:1001-4055.2001.01.005 LIU Kun, ZHANG Yulin. Finite element state-variable models for the priming process of feed lines[J]. Journal of Propulsion Technology, 2001, 22(1): 19-21. (in Chinese) doi: 10.3321/j.issn:1001-4055.2001.01.005
[17]	张育林,刘昆,程谋森. 液体火箭发动机动力学理论与应用[M]. 北京: 科学出版社,2005.
[18]	陈宏玉,刘红军,陈建华,等. 基于谱方法的管路充填过程仿真[J]. 航空动力学报,2012,27(9): 2134-2139. CHEN Hongyu,LIU Hongjun,CHEN Jianhua,et al. Investigation of priming process of propellant lines using Fourier spectral method[J]. Journal of Aerospace Power,2012,27(9): 2134-2139. (in Chinese CHEN Hongyu, LIU Hongjun, CHEN Jianhua, et al. Investigation of priming process of propellant lines using Fourier spectral method[J]. Journal of Aerospace Power, 2012, 27(9): 2134-2139. (in Chinese)