Unsteady combustion process of ethylene flame with pilot hydrogen
-
摘要:
基于脉冲燃烧直连式试验台,开展了超燃冲压发动机氢气引导乙烯火焰的非定常燃烧过程研究。燃烧室入口条件为马赫数2、总温950 K和总压1.0 MPa。试验过程分为4个阶段:冷流、引导氢气单独燃烧、引导氢气点燃乙烯、乙烯单独燃烧。基于高频壁面压力测量和火焰荧光高速摄影,获得了代表性测点的压力时间曲线及燃烧室内火焰发展历程,提取了压力平均值、振荡幅度和频率、着火时间及反应位置等重要信息,分析了不同燃烧阶段的非定常特性。试验结果表明:在氢气单独燃烧阶段,非定常特性源于凹槽后斜坡区域氢气反应强度的变化。在氢气点燃乙烯阶段,非定常特性由氢气和乙烯火焰的“交接”引起。在乙烯单独燃烧阶段,非定常特性由燃烧和超声速流动之间的耦合引起。
Abstract:Unsteady supersonic combustion process of hydrogen piloted ethylene flame in a scramjet combustor was carried out based on a direct-connected facility. The results were obtained under the inflow conditions of Mach number 2, total temperature 950 K and total pressure 1.0 MPa respectively. Ambient ethylene was used as the main fuel and ignited by pilot hydrogen. The whole experimental process could be divided into four periods: cold flow without combustion, hydrogen combustion alone, ethylene igniting by hydrogen, ethylene combustion alone. The curves of wall pressure with time and combustion development processes at five important locations in the combustor were gained through high frequency pressure transducers and flame photographs. Some insight information, including the wall pressure average value, oscillation extent and frequency, ignition time and location, were picked out. Then the unsteady combustion characteristics in different periods were analyzed and discussed. The unsteadiness came from the change of acting intensity at cavity aft-step in period of hydrogen combustion alone. The transfer between hydrogen and ethylene produced unsteady combustion in period of ethylene igniting by hydrogen. In period of ethylene combustion alone, the unsteadiness emerged from the coupling of flow and combustion.
-
Key words:
- scramjet /
- flame /
- unsteady /
- combustion /
- supersonic /
- flow
-
表 1 燃烧室入口气流参数
Table 1. Gas parameters at combustor entry
Ma pt/MPa Tt/K $x_{{\rm{H}}_2{\rm{O}}} $/% $x_{{\rm{O}}_2} $/% $x_{{\rm{N}}_2} $/% 3 2.7 1 850 30 21 49 -
[1] SUN Mingbo,GONG Chen,ZHANG Shunping,et al. Spark ignition process in a scramjet combustor fueled by hydorgen and equipped with multi-cavities at mach 4 flight condition[J]. Experimental Thermal and Fluid Science,2012,43: 90-96. doi: 10.1016/j.expthermflusci.2012.03.028 [2] SUN Mingbo,LEI Jing,WU Haiyan,et al. Flow patterns and mixing characteristics of gaseous fuel multiple injections in a non-reacting supersonic combustor[J]. Heat Mass Transfer,2011,47: 1499-1516. doi: 10.1007/s00231-011-0804-x [3] MATHUR T,GRUBER M,JACKSON K,et al. Super combustion experiments with a cavity-based fuel injector[J]. Journal of Propulsion and Power,2001,17(6): 1305-1312. doi: 10.2514/2.5879 [4] SUN Mingbo,WANG Hongbo,BAI Xuesong,et al. Flame stabilization in a supersonic combustor with hydrogen injection upstream of cavity flameholders: experiments and simulations[J]. Journal of Aerospace Engineering,2011,225: 1351-1365. doi: 10.1177/0954410011401498 [5] LI Xiaopeng, LIU Weidong, PAN Yu, et al. Characterization of ignition transient processes in kerosene-fueled model scramjet engine by dual-pulse laser-induced plasma [J]. Acta Astronautica, 2018, 114: 23-29. [6] MA Fuhua, LI Jian, YANG V, et al. Thermoacoustic flow instability in a scramjet combustor[R]. AIAA 2005-3824, 2005. [7] LI Jian, MA Fuhua, YANG V, et al. A comprehensive study of combustion oscillations in a hydrocarbon-fueled scramjet engine[R]. AIAA 2007-836, 2007. [8] LIN Kuocheng, JACKSON K, BEHDADNIA R, et al. Acoustic characterization of an ethylene-fueled scramjet combustor with a recessed cavity flameholder[R]. AIAA 2007-5382, 2007. [9] LIN Kuocheng,JACKSON K,BEHDADNIA R,et al. Acoustic characterization of an ethylene-fueled scramjet combustor with a cavity flameholder[J]. Journal of Propulsion and Power,2010,26(6): 1161-1169. doi: 10.2514/1.43338 [10] MICKA D J. Combustion stabilization, structure, and spreading in a laboratory dual-mode scramjet combustor[D]. Michigan, US: University of Michigan, 2010. [11] WANG Zhenguo, SUN Mingbo, WANG Hongbo, et al. Mixing-related low frequency oscillation of combustion in an ethylene-fueled supersonic combustor[EB/OL]. [2021-12-13]. http: //dx. doi.org/10.1016/j.proci.2014.09.005. [12] SUN Mingbo,CUI Xingda,WANG Hongbo,et al. Flame flashback in a supersonic combustor fueled by ethylene with cavity flameholder[J]. Journal of Propulsion and Power,2015,31(3): 976-980. doi: 10.2514/1.B35580 [13] 邓维鑫,乐嘉陵,杨顺华,等. 注油方式对超燃冲压发动机燃烧性能的影响[J]. 航空动力学报,2013,28(7): 1449-1457. doi: 10.13224/j.cnki.jasp.2013.07.007DENG Weixin,LE Jialing,YANG Shunhua,et al. Effect of fueling scheme on scramjet combustion performance[J]. Journal of Aerospace Power,2013,28(7): 1449-1457. (in Chinese) doi: 10.13224/j.cnki.jasp.2013.07.007 [14] TIAN Ye,XIAO Baoguo,ZHANG Shunping,et al. Experimental and computational study on combustion performance of a kerosene fueled dual-mode scramjet engine[J]. Aerospace Science and Technology,2015,46: 451-458. doi: 10.1016/j.ast.2015.09.002 [15] TIAN Ye,YANG Shunhua,LE Jialing,et al. Numerical study on effect of air throttling on combustion mode formation and transition in a dual-mode scramjet combustor[J]. Aerospace Science and Technology,2016,52: 173-180. doi: 10.1016/j.ast.2016.02.027 [16] TIAN Ye,YANG Shunhua,LE Jialing,et al. Study on flame stabilization of a hydrogen and kerosene fueled combustor[J]. Aerospace Science and Technology,2016,59: 183-188. doi: 10.1016/j.ast.2016.10.023 [17] DENG Weixin,YANG Shunhua,LE Jialing,et al. Experimental research of air-throttling ignition for scramjet at Ma 6.5[J]. Chinese Journal of Aeronautics,2017,30(3): 932-938. doi: 10.1016/j.cja.2017.03.017 [18] SHI Wen,TIAN Ye,ZHANG Wanzhou,et al. Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen[J]. Journal of Zhejiang University:Science A (Applied Physics and Engineering),2020,21(8): 663-672. doi: 10.1631/jzus.A1900565 [19] WILLIAM H H, DAVID T P, DANIEL H D, et al. Hypersonic airbreathing propulsion[M]. Washington DC: AIAA, 1994: 333-334