Experimental study of air/ethanol mono-injector gas generator
-
摘要: 针对引射系统的安全性、经济性及小型化要求，提出了一种基于航空发动机燃烧室结构的双油路燃气发生器方案，并设计、加工了单喷嘴试验件，进行了多工况下的热试车。试验结果表明，燃气发生器设计方案可行，采用高能火花塞直接点火方式可实现燃气发生器可靠点火；燃气发生器点火迅速，主要工作参数基本满足设计指标；能在较宽的流量范围内稳定工作，余气系数下限达到3.9；燃气发生器燃烧效率较高，但随着余气系数的增加而明显降低。Abstract: With regard to the safety, economy and miniaturization of the ejector system, a mono-injector air/ethanol gas generator based on the aero-engine combustor structure was designed. A series of ignition tests were carried out. The results show that:the technical design scheme of the gas generator is feasible, and reliable ignition of the gas generator can be realized by direct ignition of the high energy spark plug. The pressure curve indicates a rapid ignition of the generator, and the main working parameters basically meet the design index. The low limit of the excess air coefficient of the gas generator for reliable ignition is 3.9, showing a wide mass flow-rate range. The combustion efficiency is high, decreasing obviously with the increase of the excess air coefficient.
-
Key words:
- ejector system /
- aero-engine combustor /
- gas generator /
- mono-injector /
- excess air coefficient
-
图 5 火焰筒头部冷却结构
Figure 5. Schematic diagram of cooling structure of combustion liner head
图 6 火焰筒壁面冷却结构
Figure 6. Schematic diagram of cooling structure of combustion liner wall
图 8 燃气发生器设计工况工作压力曲线
Figure 8. Operation pressure curves of gas generator under design condition
图 9 燃气发生器设计工况工作流量曲线
Figure 9. Operation mass flow-rate curves of gas generator under design condition
图 10 设计工况燃气发生器出口温度曲线
Figure 10. Temperature distribution of gas generator outlet under design condition
图 11 火焰筒壁面热电偶测点布局示意
Figure 11. Temperature measuring point distribution of combustion liner
图 12 燃气发生器工况1工作压力曲线(余气系数α≈3.0)
Figure 12. Operation pressure curves of gas generator under No.1 condition (excess air coefficient α≈3.0)
图 13 燃气发生器工况1发生器出口温度分布(余气系数α≈3.0)
Figure 13. Temperature distribution of gas generator outlet under No.1 condition (excess air coefficient α≈3.0)
图 14 燃气发生器工况1直筒段出口温度分布(余气系数α≈3.0)
Figure 14. Temperature distribution of straight section outlet under No.1 condition (excess air coefficient α≈3.0)
图 17 燃气发生器工况4工作压力曲线(未点燃)
Figure 17. Ignition failure pressure curves of gas generator (excess air coefficient≈4.1)
表 1 燃气发生器设计参数
Table 1. Design parameters of gas generator
设计参数 数值 余气系数 3.0 酒精流量/(kg·s-1) 0.92 燃烧室压力(无量纲) 4.0 空气流量/(kg·s-1) 25 燃气总温/K 1100 
下载: 导出CSV
表 2 贫油点火试验工况
Table 2. Operating conditions of lean ignition
No. ma/(kg·s-1) mj/(kg·s-1) α 1 0.31 8.30 3.00 2 0.28 8.30 3.30 3 0.24 8.30 3.90 4 0.22 8.30 4.10
下载: 导出CSV
表 3 不同余气系数条件下试验结果
Table 3. Experimental results for different excess air coefficients
α 点火结果 备注 3.0 1.35 成功 - 3.3 1.28 成功 - 3.9 1.90 成功 - 4.1 0.70 失败 未点燃
下载: 导出CSV
表 4 燃气发生器各工况下的燃烧效率
Table 4. Combustion efficiency of gas generator
工况 余气系数 燃烧效率 设计工况(双油路) ~3.0 96.8% No.1 ~3.0 95.0% No.2 ~3.3 92.0% No.3 ~3.9 88.5%
下载: 导出CSV
-
[1] FABRI J, PAULON J. Theory and experiments on super-sonic air-to-air ejectors[R]. NACA-TM-1410, 1958. [2] 徐万武, 邹建军, 王振国, 等.超声速环型引射器启动特性试验研究[J].火箭推进, 2005, 31(6): 7-11. doi: 10.3969/j.issn.1672-9374.2005.06.002XU W W, ZOU J J, WANG Z G, et al. Experimental investigation of the start performances of the supersonic annular ejector[J]. Journal of Rocket Propulsion, 2005, 31(6): 7-11. doi: 10.3969/j.issn.1672-9374.2005.06.002 [3] 陈健, 王振国, 吴继平, 等.等截面超-超引射器流场结构及引射性能[J].强激光与粒子束, 2012, 24(6): 1301-1305. http://d.old.wanfangdata.com.cn/Periodical/qjgylzs201206009CHEN J, WANG Z G, WU J P, et al. Flow structure and performance of constant-area, supersonic-supersonic ejector[J]. High Power Laser and Particle Beams, 2012, 24(6): 1301-1305. http://d.old.wanfangdata.com.cn/Periodical/qjgylzs201206009 [4] CONNAUGHTON J C. Application of a hydrazine gas generator to vacuum ejector pumping of a chemical laser[R]. AIAA-77-0892. [5] 曹再勇, 蔡体敏, 谭永华.富氧燃气发生器三维燃烧流场的数值模拟[J].西北工业大学学报, 2005, 23(5): 557-561. doi: 10.3969/j.issn.1000-2758.2005.05.003CAO Z Y, CAI T M, TAN Y H. Furnishing some theoretical basis for design of oxygen-rich gas generator[J]. Journal of Northwestern Polytechnical University, 2005, 23(5): 557-561. doi: 10.3969/j.issn.1000-2758.2005.05.003 [6] 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. doi: 10.3969/j.issn.1672-9374.2013.03.004MA D Y, LU G, ZHANG X P, et al. Research on hot tests of LOX/methane gas generator[J]. Journal of Rocket Propulsion, 2013, 39(3): 21-26. doi: 10.3969/j.issn.1672-9374.2013.03.004 [7] 冯军红, 沈赤兵, 赵芳.液氧与气氧对空气加热器燃烧流场的影响分析[J].国防科技大学学报, 2012, 34(4): 43-48. doi: 10.3969/j.issn.1001-2486.2012.04.009FENG J H, SHEN C B, ZHAO F. Analysis of liquid and gaseous oxygen influence on the combustion flow field of air heater[J]. Journal of National University of Defense Technology, 2012, 34(4): 43-48. doi: 10.3969/j.issn.1001-2486.2012.04.009 [8] 李茂, 高玉闪, 陈泽, 等.气氢/气氧富燃预燃室设计与试验[J].航空动力学报, 2011, 26(6): 1426-1430. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201106032LI M, GAO Y S, CHEN Z, et al. Design and experiment for a GH2/ GO2 fuel rich preburner[J]. Journal of Aerospace Power, 2011, 26(6): 1426-1430. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201106032 [9] 俞南嘉, 蔡国飙, 张国舟, 等.富氧预燃室初步试验研究[J].宇航学报, 2006, 27(5): 834-838. doi: 10.3321/j.issn:1000-1328.2006.05.003YU N J, CAI G B, ZHANG G Z, et al. Initial experiment research of oxidizer rich preburner[J]. Journal of Astronautics, 2006, 27(5): 834-838. doi: 10.3321/j.issn:1000-1328.2006.05.003 [10] 金平, 俞南嘉, 邬志岐, 等.氢氧全流量补燃循环发动机燃预燃室试验[J].推进技术, 2008, 29(3): 273-277. doi: 10.3321/j.issn:1001-4055.2008.03.004JIN P, YU N J, WU Z Q, et al. Experimental investigation of fuel rich preburner of hydrogen/oxygen FFSC cycle engine[J]. Journal of Propulsion Technology, 2008, 29(3): 273-277. doi: 10.3321/j.issn:1001-4055.2008.03.004 [11] 李清廉, 李庆, 王振国.氧气/醇类燃气发生器启动过程试验研究[J].火箭推进, 2010, 36(1): 13-18. doi: 10.3969/j.issn.1672-9374.2010.01.003LI Q L, LI Q, WANG Z G. Experimental research of the start-up process of gaseous oxygen/ethanol gas generator[J]. Journal of Rocket Propulsion, 2010, 36(1): 13-18. doi: 10.3969/j.issn.1672-9374.2010.01.003 [12] 张新桥, 李清廉, 康忠涛.空气/煤油/水燃气发生器点火特性试验[J].国防科技大学学报, 2013, 35(4): 35-40. doi: 10.3969/j.issn.1001-2486.2013.04.007ZHANG X Q, LI Q L, KANG Z T. Experimental researches on ignition characteristic of air /kerosene /water gas generator[J]. Journal of National University of Defense Technology, 2013, 35(4): 35-40. doi: 10.3969/j.issn.1001-2486.2013.04.007 [13] 金盛宇, 许宏博, 吉林.空气/煤油燃气发生器技术研究[J].火箭推进, 2014, 40(3): 29-32. doi: 10.3969/j.issn.1672-9374.2014.03.005JIN S Y, XU H B, JI L. Technology research on air/jet fuel gas generator[J]. Journal of Rocket Propulsion, 2014, 40(3): 29-32. doi: 10.3969/j.issn.1672-9374.2014.03.005 [14] 陈志强, 廖达雄, 刘宗政, 等.过氧化氢加酒精补燃气体发生器实验研究[J].强激光与粒子束, 2007, 19(9): 1409-1412. http://d.old.wanfangdata.com.cn/Periodical/qjgylzs200709001CHEN Z Q, LIAO D X, LIU Z Z, et al. Experimental studies of gas generator based on hydrogen peroxide and hypergolic ethanol[J]. High Power Laser and Particle Beams, 2007, 19(9): 1409-1412. http://d.old.wanfangdata.com.cn/Periodical/qjgylzs200709001 [15] 刘景华, 谭建国, 杨涛, 等.过氧化氢发动机中的低频振荡[J].国防科技大学学报, 2007, 29(5): 23-26. doi: 10.3969/j.issn.1001-2486.2007.05.006LIU J H, TAN J G, YANG T, et al. Research on low-frequency oscillation in hydrogen peroxide engine[J]. Journal of National University of Defense Technology, 2007, 29(5): 23-26. doi: 10.3969/j.issn.1001-2486.2007.05.006 [16] 刘盛田, 胡兴伟, 柳琪, 等.一氧化二氮/乙醇燃气发生器试验研究[J].舰船科学与技术, 2008, 30(6): 223-226. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=jckxjs2008z2012LIU S T, HU X W, LIU Q, et al. The experimental studies of gas generator based on nitrous oxide and ethanol[J]. Ship Science and Tech-nology, 2008, 30(6): 223-226. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=jckxjs2008z2012 [17] 廖达雄, 任泽斌, 余永生, 等.等压混合引射器设计与实验研究[J].强激光与粒子束, 2006, 18(5): 728-732. http://d.old.wanfangdata.com.cn/Periodical/qjgylzs200605007LIAO D X, REN Z B, YU Y S, et al. Design and experiment of constant pressure mixing ejector[J]. High Power Laser and Particle Beams, 2006, 18(5): 728-732. http://d.old.wanfangdata.com.cn/Periodical/qjgylzs200605007 [18] 廖达雄.气体引射器原理及设计[M].北京: 国防工业出版社, 2018.LIAO D X. Principle and design of gas ejector[M]. Beijing: National Defense Industry Press, 2018. [19] LEFEBVRE A H. Gas turbine combustion[M]. Washington: Hemisphere Publishing Corp, 1983. [20] MELLOR A M. Design of modern turbine combustors[M]. New York: Academic Press Inc, 1990. -
点击查看大图
计量
- 文章访问数: 366
- HTML全文浏览量: 197
- PDF下载量: 7
- 被引次数: 0
