In order to further understand the flow characteristics of scramjet engines and optimize the combustion chamber flow field, the numerical simulation has been carried out to investigate the effects of different combination mode of cantilever ramp/cavity in scramjet combustor on mixing characteristics, flame stabilizing ability and combustion efficiency of flow field. The study find that the spanwise vortex of the trailing edge of the cavity in the longitudinal cantilever ramp/cavity combination structure is larger than that of the transverse combination, and the temperature in the cavity is higher and the flame stabilizing ability is better. The high turbulent kinetic energy region of longitudinal combination is larger, and the mixing efficiency is enlarged. There is little difference in the total pressure loss caused by the vertical and the lateral combinations, but the former one has higher combustion efficiency.
YANG Wenjia
,
GAO Feng
,
ZHANG Han
,
XIA Xuefeng
. Study on Combined Structure of Cantilever Ramp/Cavity of Scramjet Combustor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2017
, 37(6)
: 79
-84
.
DOI: 10.15892/j.cnki.djzdxb.2017.06.018
[1] SEGAL Corin. The scramjet engine: processes and characteristics[M].Cambridge: Cambridge University Press, 2009: 85-86.
[2] 陈方, 陈立红, 张新宇. 超声速燃烧室凹腔火焰稳定器的数值模拟[J].推进技术, 2007, 28(2): 135-140.
[3] 徐旭, 陈兵, 徐大军. 冲压发动机原理及技术[M].北京航空航天大学出版社, 2014: 175-200.
[4] 蔡国彪, 徐大军. 高超声速飞行器技术[M].北京: 科学出版社, 2012: 77-95.
[5] 黄桂彬, 吴达,王应洋,等. 基于正交试验的超燃燃烧室小肋片数值优化[J].空军工程大学学报(自然科学版), 2017, 18(5): 12-17.
[6] 苏义. 支板超声速混合增强技术及其阻力特性研究[D].长沙: 国防科学技术大学, 2006: 5-6, 50-57.
[7] 高峰, 王宏宇, 张涵. 超燃冲压发动机燃烧室流场数值分析研究综述[J].飞航导弹, 2014(1): 80-84.
[8] 黄伟, 覃慧, 罗世彬, 等. 激波诱燃冲压发动机关键技术研究[J].中国科学(技术科学), 2010, 40(1): 64-70.
[9] PARENT B, SISLIAN J P. Turbulent hypervelocity fuel/air mixing by cantilevered ramp injectors. AIAA 2001-1888[R].[S.l.]:AIAA, 2001.
[10] ARAI T, SAKAUE S, HAYASE H, et al. Stream wise vortices introduced by “Hyper-Mixer” on supersonic mixing: AIAA 2011-2342[R].[S.l.]:AIAA,2001.
[11] HUANG Wei, LI Shi-bin, YAN Li, et al. Performance evaluation and parametric analysis on cantilevered ramp injector in supersonic flows[J].Acta Astronautica, 2013, 84: 141-152.
[12] BEN-YAKER Adela, HANSON Ronald K. Cavity flameholders for ignition and flame stabilization in scramjets: Review and experimental study[C]//AIAA. Proceedings of 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Joint Propulsion Conferences.[S.l.]: AIAA, 1998.
[13] 贾真. 超声速燃烧室中壁面凹腔结构的稳焰机理[J].航空动力学报, 2013, 28(6): 1392-1401.
[14] 余勇, 丁猛, 刘卫东, 等. 煤油超音速燃烧的试验研究[J].国防科技大学学报, 2004, 26(1): 1-4.
[15] BEN-YAKER Adela, HANSON Ronald K. Cavity flameholders for ignition and flame stabilization in scramjets: An overview[J].Journal of Propulsion nad Power, 2001, 17(4):869877.
[16] 陈立红, 顾洪斌, 张新宇. 支板凹腔一体化超燃冲压发动机实验研究[J].工程热物理学报, 2007, 28(4): 717-719.
[17] 刘金林. 乙烯超燃燃烧室支板/凹腔结构组合的数值研究[D].哈尔滨: 哈尔滨工程大学, 2012.
[18] EKLUND D R, GRUBER M R. Study of a supersonic combuster employing an aerodynamic ramp pilot injector[C]//AIAA. Proceedings of 35th Joint Propulsion Conference and Exhibit.[S.l.]: AIAA, 1999.
