基于支板凹腔结构的超燃燃烧室数值研究

推进技术 ›› 2017, Vol. 38 ›› Issue (11): 2555-2561.

基于支板凹腔结构的超燃燃烧室数值研究

杨浩¹,方祥军¹,林鹏²,王霄²

北京航空航天大学能源与动力工程学院，北京 100191,北京航空航天大学能源与动力工程学院，北京 100191,沈阳飞机设计研究院，辽宁沈阳 110035,沈阳飞机设计研究院，辽宁沈阳 110035

发布日期:2021-08-15
作者简介:杨浩，男，硕士生，研究领域为冲压燃烧室火焰稳定。

Numerical Study on Strut/Cavity-Based Scramjet Combustor

School of Energy and Power Engineering，Beihang University，Beijing 100191，China,School of Energy and Power Engineering，Beihang University，Beijing 100191，China,Shenyang Aircraft Design Institute，Shenyang 110035，China and Shenyang Aircraft Design Institute，Shenyang 110035，China

Published:2021-08-15

摘要/Abstract

摘要： 为探究基于支板凹腔结构的超燃燃烧室性能，在超声速来流条件下，采用带中心支板且凹腔长高比为7.5的三维超燃燃烧室模型，针对支板阻塞比、扩张段扩张角、不同燃料喷射方式以及不同燃料当量比对燃烧室相关性能的影响进行了数值研究。研究发现:支板阻塞比会对隔离段内的激波分布以及支板后缘速度分布产生明显影响，而扩张段扩张角会影响超声气流在燃烧室出口的膨胀状态；采用壁面以及中心喷注支板同时喷油方式在保持高燃烧效率的同时会扩大整个燃烧室的燃烧区域；当采用单独壁面喷油方式时，凹腔内静温分布会随着当量比的变化发生相应的改变，同时会在当量比为0.51～0.74时达到相对较高的燃烧效率。

关键词: 超燃燃烧室；中心喷注支板；凹腔；数值模拟

Abstract: In order to investigate the performance of a scramjet combustor with strut/cavity integrated configurations，numerical simulation on a three dimensional scramjet combustor model with a center injection strut and a cavity (L/D=7.5) was performed under supersonic flows. The effects of strut choke ratio，expansion angle of divergent section，various injection modes and equivalence ratio on performances of scramjet combustor were analyzed and compared. The results showed that strut choke ratio had great effect on the distribution of shock wave in the isolator and the velocity distribution on the strut trailing edge. And the expansion angle of divergent section may influence flow’s expansion state at the combustor exit. Injection from both the combustor wall and the strut may serve as an effective tool in expanding the combustion region while keeping high combustion efficiency. When injection just from the combustor wall，the static temperature in cavity changed with the change of the equivalence ratio and the combustion efficiency will reach a relatively high point when the equivalence ratio between 0.51 and 0.74.

Key words: Scramjet combustor；Center injection strut；Cavity；Numerical simulation

杨浩,方祥军,林鹏,王霄. 基于支板凹腔结构的超燃燃烧室数值研究[J]. 推进技术, 2017, 38(11): 2555-2561.

YANG Hao¹,FANG Xiang-jun¹,LIN Peng²,WANG XiaO². Numerical Study on Strut/Cavity-Based Scramjet Combustor[J]. Journal of Propulsion Technology, 2017, 38(11): 2555-2561.

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] Rasmussen C C, Dhanuka S K, Driscoll J F. Visualization of Flameholding Mechanisms in a Supersonic Combustor using PLIF[J]. Proceedings of the Combustion Institute, 2007, 31(2): 2505-2512.
[3] Rasmussen C C, Driscoll J F, Carter C D, et al. Characteristics of Cavity-Stabilized Flames in a Supersonic Flow[J]. Journal of Propulsion and Power, 2005, 21(4):765-768.
[4] Rasmussen C C, Driscoll J F, Hsu K Y, et al. Stability Limits of Cavity-Stabilized Flames in Supersonic Flow[J]. Proceedings of the Combustion Institute, 2005, 30(2):2825-2833.
[5] Driscoll J F, Rasmussen C C. Correlation and Analysis of Blowout Limits of Flames in High-Speed Airflows[J].Journal of Propulsion and Power, 2005, 21(6): 1035-1044.
[6] Driscoll J F, Rasmussen C C. Blowout Limits of Flames in High-Speed Airflows: Critical Damkohler Number[J]. American Institute of Aeronautics and Astronautics, 2008, 21(6): 1035-1044.
[7] 龚诚, 孙明波, 张顺平, 等. 超声速燃烧室氢气强迫点火过程实验[J]. 推进技术, 2012, 33(4): 547-551. (GONG Cheng, SUN Ming-bo, ZHANG Shun-ping, et al. Experimental Study on the Forced Ignition of Hydrogen in a Supersonic Combustor[J]. Journal of Propulsion Technology, 2012, 33(4): 547-551.)
[8] 席文雄, 王振国, 刘卫东, 等. 双模态超燃冲压发动机点火方案对比试验[J]. 推进技术, 2013, 34(3):383-389. (XI Wen-xiong, WANG Zhen-guo, LIU Wei-dong, et al. Experimental Comparison on the Scheme of Ignition in Dual-Mode Scramjet[J]. Journal of Propulsion Technology, 2012, 34(3): 383-389.)
[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, 2010, 26(6): 1237-1246.
[10] Desikan S L N, Kurian J. Mixing Studies in Supersonic Flow Employing Strut Based Hypermixers[R]. AIAA 2005-3643.
[11] Desikan S L N, Kurian J. Strut-Based Gaseous Injection into a Supersonic Stream[J]. Journal of Propulsion and Power, 2006, 22(2): 474-477.
[12] Tam C J, Hsu K Y, Gruber M R, et al. Aerodynamic Performance of an Injector Strut for a Round Scramjet Combustor[R]. AIAA 2007-5403.
[13] Tam C J, Hsu K Y, Gruber M R, et al. Fuel/Air Mixing Characteristics of Strut Injections for Scramjet Combustor Applications[R]. AIAA 2008-6925.
[14] Choubey G, Pandey K M. Effect of Variation of Angle of Attack on the Performance of Two-Strut Scramjet Combustor[J]. International Journal of Hydrogen Energy, 2016, 41(26): 11455-11470.
[15] Yu G, Li J G, Chang X Y, et al. Investigation of Kerosene Combustion Characteristics with Pilot Hydrogen in Model Supersonic Combustors[J]. Journal of Propulsion and Power, 2001, 17(6): 1263-1272.(编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2016-06-28；修订日期:2016-09-05。作者简介:杨浩,男,硕士生,研究领域为冲压燃烧室火焰稳定。E-mail: yhhh_personal@163.com