壁面喷射当量比对支板凹腔耦合燃烧的影响

doi:10.13700/j.bh.1001-5965.2016.0352

北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (5): 969-974.doi: 10.13700/j.bh.1001-5965.2016.0352

壁面喷射当量比对支板凹腔耦合燃烧的影响

韩啸¹, 林宇震^1,2, 张弛¹, 王建臣¹

1. 北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室, 北京 100083;
2. 先进航空发动机协同创新中心, 北京 100083

收稿日期:2016-04-28 出版日期:2017-05-20 发布日期:2017-05-27
通讯作者: 林宇震,E-mail:linyuzhen@buaa.edu.cn E-mail:linyuzhen@buaa.edu.cn
作者简介:韩啸,男,博士研究生。主要研究方向:液雾燃烧;林宇震,男,博士,教授,博士生导师。主要研究方向:航空发动机燃烧室及超声速燃烧;张弛,男,博士,副教授,硕士生导师。主要研究方向:航空发动机燃烧室及替代燃料;王建臣,男,博士。主要研究方向:超声速燃烧。

Effect of equivalence ratio of wall injection on strut-cavity coupled combustion

HAN Xiao¹, LIN Yuzhen^1,2, ZHANG Chi¹, WANG Jianchen¹

1. National Key Laboratory of Science and Technology on Aero-engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100083, China

Received:2016-04-28 Online:2017-05-20 Published:2017-05-27

摘要/Abstract

摘要： 在纯净空气来流条件下，对于全高后掠支板与凹腔耦合的燃烧室，采用分级喷射供油，对比研究了壁面喷射当量比对壁面压力和燃烧性能的影响。结果表明：在支板喷射当量比一定的情况下，随着壁面喷射当量比增加，壁面静压峰值升高，静压开始提升的位置向上游移动，总当量比达到1.1时发生溢流；一维分析表明，马赫数在支板附近降到1以下，在凹腔处达到0.5左右，在出口扩张段恢复至1以上，燃烧室处于亚燃模态；燃烧性能方面，保持支板喷射当量比一定，随着壁面喷射当量比的增加，总压恢复系数提高，出口总温增加，燃烧效率降低。

关键词: 支板, 凹腔, 分级喷射, 壁面喷射, 一维分析

Abstract: For the combustor based on full-height swept strut coupled with cavity, the experiments were conducted under clean air conditions and the inlet air was preheated by storage heater. Liquid kerosene was used as fuel and was injected by stages from the wall and strut. The effect of equivalence ratio of wall injection on the static pressure distribution and combustion performance was studied by experiments and one-dimensional analysis. The results show that as the equivalence ratio of strut was constant, with the increasing of wall injection equivalence ratio, the peak static pressure increased, and the position of the lifting of pressure was moved upward. When the total equivalence ratio reached 1.1, an inlet unstart occurred. One-dimensional analysis shows that the Mach number decreased below 1 in the strut area, then reached 0.5 in cavity and finally back to more than 1 in diverging area of outlet. The combustor worked in subsonic mode. In the combustion performance aspect, increasing of wall injection equivalence ratio ledes to increase of total pressure recovery coefficient, increase of total temperature at exit, but reduction of combustion efficiency.

Key words: strut, cavity, staged injection, wall injection, one-dimensional analysis

中图分类号:

韩啸, 林宇震, 张弛, 王建臣. 壁面喷射当量比对支板凹腔耦合燃烧的影响[J]. 北京航空航天大学学报, 2017, 43(5): 969-974.

HAN Xiao, LIN Yuzhen, ZHANG Chi, WANG Jianchen. Effect of equivalence ratio of wall injection on strut-cavity coupled combustion[J]. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2017, 43(5): 969-974.

参考文献

[1] BEN-YAKAR A,HANSON R K.Cavity flame-holders for ignition and flame stabilization in scramjets:An overview[J].Journal of Propulsion and Power,2001,17(4):869-877.
[2] BOGDANOFF D W.Advanced injection and mixing techniques for scramjet combustors[J].Journal of Propulsion and Power,1994,10(2):183-190.
[3] 刘世杰,潘余,刘卫东. 超燃冲压发动机支板喷射燃料的燃烧过程试验[J]. 航空动力学报,2009,24(1):55-59. LIU S J,PAN Y,LIU W D. Experimental study on the combustion and flow process in a scramjet with strut injector[J].Journal of Aerospace Power,2009,24(1):55-59(in Chinese).
[4] FREEBORN A B,KING P I,GRUBER M R. Gruberl characterization of pylon effects on a scramjet cavity flameholder flowfield:AIAA-2008-86[R].Reston:AIAA,2008.
[5] FREEBORN A B,KING P I,GRUBER M R. Leading edge pylon effects on a scramjet pylon-cavity flameholder flowfield:AIAA-2008-4709[R].Reston:AIAA,2008.
[6] FREEBORN A B,KING P I,GRUBER M R. Swept-leading-edge pylon effects on a scramjet pylon-cavity flameholder flowfield[J].Journal of Propulsion and Power,2009,25(3):571-582.
[7] PITZ R W,CARTER C D.Supersonic flow over a ramped-wall cavity flame holder with an upstream strut[J]. Journal of Propulsion and Power,2012,28(5):982-990.
[8] ZHAO Y,LIANG J,ZHAO Y. Non-reacting flow visualization of supersonic combustor based on cavity and cavity-strut flameholder[J]. Acta Astronautica,2016,121:282-291.
[9] HSU K Y,CARTER C D,GRUBER M R,et al. Experimental study of cavity-strut combustion in supersonic flow[J]. Journal of Propulsion and Power,2007,26(6):1237-1246.
[10] GHODKE C D,CHOI J J, SRINIVASAN S,et al. Large eddy simulation of supersonic combustion in a cavity-strut flameholder[C]//49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.Reston:AIAA,2011.
[11] 俞刚,李建国.氢/空气超声速燃烧研究[J].流体力学实验与测量，1999,13(1):1-12.YU G,LI J G.Studies on hydrogen/air supersonic combustion[J].Experiments and Measurements in Fluid Mechanics,1999,13(1):1-12(in Chinese).
[12] TOMIOKA S,MURAKAMI A,KUDO K,et al. Combustion tests of a staged supersonic combustor with a strut[J].Journal of Propulsion and Power,2001,17(2):293-300.
[13] TOMIOKA S,KAN K,KUDO K,et al.Effects of injection configuration on performance of a staged supersonic combustor[J]. Journal of Propulsion and Power,2003,19(5):876-884.
[14] TOMIOKA S,KAN K,KUDO K,et al.Distributed fuel injection for performance improvement of staged supersonic combustor[J]. Journal of Propulsion and Power,2005,21(4):760-763.
[15] UEDA S,TOMIOKA S,ONO F,et al. Mach 6 test of a scramjet engine with multi-staged fuel injection[C]//44th AIAA Aerospace Sciences Meeting and Exhibit.Reston:AIAA,2006.
[16] HOU L,WEIGAND B,BANICA M.Effects of staged injection on supersonic mixing and combustion[J].Chinese Journal of Aeronautics,2011,24(5):584-589.
[17] ABU-FARAH L,HAIDN O J,KAU H P. Numerical simulations of single and multi-staged injection of H₂ in a supersonic scramjet combustor[J]. Propulsion & Power Research,2015,2(4):175-186.
[18] YANG Q,CHETEHOUNA K,GASCOIN N,et al. Experimental study on combustion modes and thrust performance of a staged-combustor of the scramjet with dual-strut[J].Acta Astronautica,2016,122:28-34.
[19] 范学军,仲峰泉,王晶,等.双路喷注超临界态煤油的超燃特性研究[C]//第一届高超声速科技学术会议论文集.丽江:中国力学学会,2008:177-183.FAN X J,ZHONG F Q,WANG J,et al.Performance of supersonic model combustors with twostaged supercritical kerosene injection[C]//The 1st National Conference on Hypersonic Technology. Lijiang: The Chinese Society of Theoretical and Applied Mechanics,2008:177-183(in Chinese).
[20] ZHANG T C,YUAN Y M,LI J G,et al.Characteristics of a supersonic model combustor with two-staged injections of supercritical kerosene[C]//48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston:AIAA,2012.
[21] 王建臣,林宇震,郭新华,等. 纯净空气来流下支板凹腔耦合超燃燃烧室性能研究[J]. 推进技术,2015,36(12):1868-1873. WANG J C,LIN Y Z,GUO X H,et al. Experimental investigation of performance of a strut-cavity based scramjet combustor in clean air [J]. Journal of Propulsion Technology, 2015,36(12):1868-1873(in Chinese).
[22] 赵永胜,林宇震,王建臣,等.支板/凹腔超声速燃烧室总压损失特性研究[J].推进技术,2016,37(2):339-345.ZHAO Y S,LIN Y Z,WANG J C,et al. Total pressure loss characteristics in a strut-cavity based scramjet combustor[J]. Journal of Propulsion Technology,2016,37(2):339-345(in Chinese).
[23] HEISER W H,PRATT D T. Hypersonic airbreathing propulsion[M].Reston:AIAA,1994:52-82.
[24] 王建臣.超声速燃烧中支板凹腔稳焰技术研究[D].北京：北京航空航天大学,2015:117-124.WANG J C.Studies on flameholding technology of strut-cavity flameholders in supersonic combustion[D].Beijing:Beihang University,2015:117-124(in Chinese).
[25] 黄勇，林宇震，樊未军，等. 燃烧与燃烧室[M].北京：北京航空航天大学出版社，2009:239-240.HUANG Y,LIN Y Z,FAN W J,et al.Combustion and combustor[M].Beijing:Beihang University Press,2009:239-240 (in Chinese).

壁面喷射当量比对支板凹腔耦合燃烧的影响

Effect of equivalence ratio of wall injection on strut-cavity coupled combustion

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