液氧/液甲烷同轴式喷嘴点火冲击特性

刘云浩; 王春民; 冯远翔; 刘昭宇; 李龙飞

doi:10.13224/j.cnki.jasp.20250036

液氧/液甲烷同轴式喷嘴点火冲击特性

doi: 10.13224/j.cnki.jasp.20250036

1.
西安航天动力研究所航天液体动力全国重点实验室，西安 710100
2.
中国航天科技集团有限公司航天推进技术研究院，西安 710100

详细信息

作者简介:
刘云浩（1997-），男，博士生，主要从事液体火箭发动机流动燃烧研究

中图分类号: V434
计量
- 文章访问数: 407
- HTML浏览量: 221
- PDF量: 28
- 被引次数: 0
出版历程
- 收稿日期: 2025-01-20
- 网络出版日期: 2025-08-12

Ignition impact characteristics of LOX/LCH₄ coaxial injectors

1.
National Key Laboratory of Aerospace Liquid Propulsion，Xi’an Aerospace Propulsion Institute，Xi’an 710100，China
2.
Academy of Aerospace Propulsion Technology，China Aerospace Science and Technology Corporation，Xi’an 710100，China

摘要

摘要:
为研究液氧/液甲烷同轴式喷嘴富氧条件下点火冲击特性，在模型燃烧室中开展了喷嘴相对缩进长度为3的同轴双离心式、同轴离心剪切式、同轴直流剪切式喷嘴的点火试验，获得了喷嘴平稳点火过程和喷嘴大冲击点火过程的特征，获得了喷嘴结构和工况参数对点火冲击特性的影响规律。结果表明：喷嘴点火冲击特性由喷嘴结构和矩形孔液氧射流流量控制，喷嘴结构控制缩进室内推进剂混合进而影响点火特性。在双离心、离心剪切、直流剪切3种喷嘴结构中双离心式喷嘴的点火冲击最小，矩形孔液氧对缩进室内推进剂的遮蔽不利于点火，缩进室液氧流量为0.4～0.5 kg/s，缩进室混合比为12.1～23.8的同轴离心剪切式喷嘴，将矩形孔液氧流量降低至0.7 kg/s能够减弱遮蔽并抑制点火冲击。
- 点火冲击 /
- 同轴式喷嘴 /
- 点火试验 /
- 富氧燃气发生器 /
- 液氧流量
Abstract:
In order to study the ignition impact characteristics of LOX/LCH₄ coaxial injectors under oxygen rich conditions, the ignition experiments of bi-swirl coaxial injector, orifice-swirl coaxial injector and shear coaxial injector with injector relative recess lengths of 3 were carried out in a model chamber. The characteristics of steady ignition process and large impact ignition process of injectors were obtained, and the influences of injectors structure parameters and working condition parameters on ignition impact characteristics were obtained. The results showed that the ignition impact characteristics of the injectors were controlled by the injector structure and the LOX flow rate of the square hole. The injector structure controlled the mixing of the propellant in the indented region and then affected the ignition characteristics. The ignition characteristics of bi-swirl coaxial injector were the best, orifice-swirl coaxial injector was the second and shear coaxial injector was the worst. The shielding of the rectangular LOX to the propellant in the indented region was not conducive to ignition. For an orifice-swirl coaxial injector with recessed chamber liquid oxygen flow rates within the range of 0.4 kg/s to 0.5 kg/s and mixture ratios between 12.1 and 23.8, reducing the LOX flow rate of the square hole to less than 0.7 kg/s can inhibit ignition impact.
- ignition impact /
- coaxial injector /
- ignition experiments /
- oxygen-rich gas generator /
- LOX flow rate

HTML

图 1 同轴式喷嘴结构示意图

Figure 1. Schematic of coaxial injectors

下载: 全尺寸图片幻灯片

图 2 试验系统示意图

Figure 2. Schematic of experimental system

下载: 全尺寸图片幻灯片

图 3 平稳点火过程的典型试验曲线

Figure 3. Typical experiment curve of steady ignition process

下载: 全尺寸图片幻灯片

图 4 大冲击点火过程的典型试验曲线

Figure 4. Typical experiment curve of large impact ignition process

下载: 全尺寸图片幻灯片

图 5 CFD几何模型及网格

Figure 5. CFD geometric model and mesh

下载: 全尺寸图片幻灯片

图 6 缩进室内甲烷质量分数分布

Figure 6. Indented region methane mass fraction distribution

下载: 全尺寸图片幻灯片

图 7 缩进室内密度分布

Figure 7. Indented region density distribution

下载: 全尺寸图片幻灯片

表 1 喷嘴形式与相对缩进长度参数

Table 1. Injector structure and relative recess lengths

序号	喷嘴形式	相对缩进长度（L/D）
A	双离心	3
B	离心剪切	3
C	直流剪切	3

下载: 导出CSV

表 2 试验工况表

Table 2. Experiment conditions

参数	工况1	工况2	工况3	工况4	工况5	工况6
液甲烷流量q_mf/（kg/s）	0.021	0.021	0.033	0.033	0.021	0.021
喷嘴液氧流量q_mo1/（kg/s）	0.4	0.5	0.4	0.5	0.4	0.4
矩形孔液氧流量q_mo2/（kg/s）	1.15	1.05	1.15	1.05	0	0.7
缩进室混合比	19.0	23.8	12.1	15.2	19.0	19.0
燃烧室混合比	73.8	73.8	47.0	47.0	19.0	52.4

下载: 导出CSV

表 3 点火冲击特性表

Table 3. Ignition impact characteristics

喷嘴结构	工况1	工况2	工况3	工况4	工况5	工况6
A	平稳	平稳	平稳	平稳	平稳	平稳
B	平稳	0.93$ \bar{p}_{\rm{c}} $	1.57$ \bar{p}_{\rm{c}} $	3.48$ \bar{p}_{\rm{c}} $	平稳	平稳
C	3.22$ \bar{p}_{\rm{c}} $	平稳
注：虽然喷嘴C工况1和喷嘴B工况4点火过程中压力超过传感器量程，试后检查传感器仍正常工作，认为这两次试验中传感器测量参数仍能表征冲击的相对大小。

下载: 导出CSV

参考文献(22)

[1]	高玉闪, 张晓军, 邢理想, 等. 我国液氧甲烷发动机技术发展概述[J]. 中国航天, 2023(5): 16-23. GAO Yushan, ZHANG Xiaojun, XING Lixiang, et al. Review of technology development for Chinese LOX/methane engines[J]. Aerospace China, 2023(5): 16-23. (in Chinese doi: 10.3969/j.issn.1002-7742.2023.05.003 GAO Yushan, ZHANG Xiaojun, XING Lixiang, et al. Review of technology development for Chinese LOX/methane engines[J]. Aerospace China, 2023(5): 16-23. (in Chinese) doi: 10.3969/j.issn.1002-7742.2023.05.003
[2]	李斌, 张小平, 高玉闪. 我国可重复使用液体火箭发动机发展的思考[J]. 火箭推进, 2017, 43(1): 1-7. LI Bin, ZHANG Xiaoping, GAO Yushan. Consideration on development of reusable liquid rocket engine in China[J]. Journal of Rocket Propulsion, 2017, 43(1): 1-7. (in Chinese LI Bin, ZHANG Xiaoping, GAO Yushan. Consideration on development of reusable liquid rocket engine in China[J]. Journal of Rocket Propulsion, 2017, 43(1): 1-7. (in Chinese)
[3]	杨开, 才满瑞. 国外液氧/甲烷发动机的最新进展[J]. 中国航天, 2017(10): 14-19. YANG Kai, CAI Manrui. The latest development of foreign liquid oxygen/methane engines[J]. Aerospace China, 2017(10): 14-19. (in Chinese doi: 10.3969/j.issn.1002-7742.2017.10.003 YANG Kai, CAI Manrui. The latest development of foreign liquid oxygen/methane engines[J]. Aerospace China, 2017(10): 14-19. (in Chinese) doi: 10.3969/j.issn.1002-7742.2017.10.003
[4]	ZURBACH S, THOMAS J L, VERPLANCKE C. LOX/methane studies for fuel rich preburner: AIAA 2003-5063[R]. Huntsville, US: 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2003.
[5]	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
[6]	VILLEMARETTE M, HURLBERT E, ANGSTADT T, et al. 870 lb_f reaction control system tests using LOx/ethanol and LOx/methane at white sands test facility: AIAA 2008-5247 [R]. Hartford , US: 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2008.
[7]	CHO Yongho, CHANG Haengsoo. Hot firing tests of liquid rocket engine using LOX/LNG: AIAA-2004-3528[R]. Fort Lauderdale, US: 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004.
[8]	李茂, 金平, 邬志岐, 等. 全流量补燃循环发动机富氧预燃室设计与试验[J]. 航空动力学报, 2009, 24(12): 2834-2838. LI Mao, JIN Ping, WU Zhiqi, et al. Design and experiment research for oxygen-rich preburner of FFSC[J]. Journal of Aerospace Power, 2009, 24(12): 2834-2838. (in Chinese LI Mao, JIN Ping, WU Zhiqi, et al. Design and experiment research for oxygen-rich preburner of FFSC[J]. Journal of Aerospace Power, 2009, 24(12): 2834-2838. (in Chinese)
[9]	李庆, 李清廉, 王振国. 燃气发生器结构对燃烧性能的影响[J]. 航空动力学报, 2008, 23(11): 2062-2067. LI Qing, LI Qinglian, WANG Zhenguo. Effect of structure of gas generator on combustion performance[J]. Journal of Aerospace Power, 2008, 23(11): 2062-2067. (in Chinese LI Qing, LI Qinglian, WANG Zhenguo. Effect of structure of gas generator on combustion performance[J]. Journal of Aerospace Power, 2008, 23(11): 2062-2067. (in Chinese)
[10]	KIM K H, JU D S. Development of ‘Chase 10’ liquid rocket engine having 10tf thrust using lox & lng (methane): AIAA 2006-4907 [R]. Sacramento, US: 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2006.
[11]	李春红, 张小平, 马冬英, 等. 液氧/甲烷燃气发生器点火方案研究[J]. 火箭推进, 2010, 36(5): 7-12. LI Chunhong, ZHANG Xiaoping, MA Dongying, et al. Ignition scheme of LOX/methane gas generator[J]. Journal of Rocket Propulsion, 2010, 36(5): 7-12. (in Chinese doi: 10.3969/j.issn.1672-9374.2010.05.002 LI Chunhong, ZHANG Xiaoping, MA Dongying, et al. Ignition scheme of LOX/methane gas generator[J]. Journal of Rocket Propulsion, 2010, 36(5): 7-12. (in Chinese) doi: 10.3969/j.issn.1672-9374.2010.05.002
[12]	郑大勇, 胡骏. 液氧甲烷发动机点火冲击特性研究[J]. 推进技术, 2021, 42(7): 1553-1560. ZHENG Dayong, HU Jun. Ignition shock of LOX/methane liquid rocket engine[J]. Journal of Propulsion Technology, 2021, 42(7): 1553-1560. (in Chinese ZHENG Dayong, HU Jun. Ignition shock of LOX/methane liquid rocket engine[J]. Journal of Propulsion Technology, 2021, 42(7): 1553-1560. (in Chinese)
[13]	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
[14]	张睿文, 李斌, 王丹, 等. 大推力液氧煤油补燃发动机分级起动仿真分析[J]. 航空动力学报, 2024, 39(8): 20220555. ZHANG Ruiwen, LI Bin, WANG Dan, et al. Simulation analysis of staged startup of large thrust LOX/kerosene staged combustion rocket engine[J]. Journal of Aerospace Power, 2024, 39(8): 20220555. (in Chinese ZHANG Ruiwen, LI Bin, WANG Dan, et al. Simulation analysis of staged startup of large thrust LOX/kerosene staged combustion rocket engine[J]. Journal of Aerospace Power, 2024, 39(8): 20220555. (in Chinese)
[15]	陈宏玉, 刘红军, 陈建华. 补燃循环发动机强迫起动过程[J]. 航空动力学报, 2015, 30(12): 3010-3016. CHEN Hongyu, LIU Hongjun, CHEN Jianhua. Forced start-up procedure of a staged combustion cycle engine[J]. Journal of Aerospace Power, 2015, 30(12): 3010-3016. (in Chinese CHEN Hongyu, LIU Hongjun, CHEN Jianhua. Forced start-up procedure of a staged combustion cycle engine[J]. Journal of Aerospace Power, 2015, 30(12): 3010-3016. (in Chinese)
[16]	于涵, 严宇, 杨宝娥, 等. 液氧/液甲烷双离心式喷嘴富氧低频燃烧不稳定性研究[J]. 推进技术, 2022, 43(12): 210773. YU Han, YAN Yu, YANG Baoe, et al. Low frequency combustion instability of LOX/LCH₄ Bi-swirl injector under oxygen rich conditions[J]. Journal of Propulsion Technology, 2022, 43(12): 210773. (in Chinese YU Han, YAN Yu, YANG Baoe, et al. Low frequency combustion instability of LOX/LCH₄ Bi-swirl injector under oxygen rich conditions[J]. Journal of Propulsion Technology, 2022, 43(12): 210773. (in Chinese)
[17]	WANG Xingjian, LI Yixing, WANG Yanxing, et al. Near-field flame dynamics of liquid oxygen/kerosene bi-swirl injectors at supercritical conditions[J]. Combustion and Flame, 2018, 190: 1-11. doi: 10.1016/j.combustflame.2017.11.007
[18]	高玉闪, 严宇, 杨宝娥, 等. 液氧煤油超临界富氧燃烧中的低频振荡特性实验研究[J]. 推进技术, 2023, 44(12): 2212015. GAO Yushan, YAN Yu, YANG Baoe, et al. Experimental investigation on low frequency oscillation of supercritical combustion of LOX/kerosene oxidizer-rich mixture[J]. Journal of Propulsion Technology, 2023, 44(12): 2212015. (in Chinese GAO Yushan, YAN Yu, YANG Baoe, et al. Experimental investigation on low frequency oscillation of supercritical combustion of LOX/kerosene oxidizer-rich mixture[J]. Journal of Propulsion Technology, 2023, 44(12): 2212015. (in Chinese)
[19]	李丹琳, 栾叶君, 孙纪国. 液氧/甲烷气液喷注器试验研究[J]. 火箭推进, 2010, 36(4): 59-62. LI Danlin, LUAN Yejun, SUN Jiguo. Experimental investigation on LOX/CH₄ subscale thrust chamber[J]. Journal of Rocket Propulsion, 2010, 36(4): 59-62. (in Chinese LI Danlin, LUAN Yejun, SUN Jiguo. Experimental investigation on LOX/CH₄ subscale thrust chamber[J]. Journal of Rocket Propulsion, 2010, 36(4): 59-62. (in Chinese)
[20]	CUOCO F, YANG Baoe, BRUNO C, et al. Experimental investigation on LOx/CH₄ ignition: AIAA 2004-4005 [R]. Fort Lauderdale, US: 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004.
[21]	BONANNI M, MOHADDES D, LY N, et al. Toward numerical investigation of ignition and combustion transition in a subscale LOX/methane rocket combustor: AIAA 2021-1141[R]. Nashville, US: AIAA Scitech 2021 Forum, 2021.
[22]	TRAXINGER C, ZIPS J, PFITZNER M. Thermodynamic analysis and large-eddy simulations of LO_x-CH₄ and LO_x-H₂ flames at high pressure: AIAA 2018-4765 [R]. Cincinnati, US: 2018 Joint Propulsion Conference, 2018.