Effects of Injection Scheme on Low-Frequency Oscillation
in a Cavity-Based Scramjet Combustor

Journal of Propulsion Technology ›› 2018, Vol. 39 ›› Issue (10): 2370-2380.

Previous Articles Next Articles

Effects of Injection Scheme on Low-Frequency Oscillation in a Cavity-Based Scramjet Combustor

Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，China,Science and Technology on Scramjet Laboratory，National University of Defense Technology，Changsha 410073，China,Science and Technology on Scramjet Laboratory，National University of Defense Technology，Changsha 410073，China,Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，China and Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，China

Published:2021-08-15

喷注方案对凹腔稳焰燃烧室低频振荡的影响研究

崔兴达¹,孙明波²,汪洪波²,江雄¹,李伟¹

中国空气动力研究与发展中心计算空气动力研究所，四川绵阳 621000,国防科技大学高超声速冲压发动机技术重点实验室，湖南长沙 410073,国防科技大学高超声速冲压发动机技术重点实验室，湖南长沙 410073,中国空气动力研究与发展中心计算空气动力研究所，四川绵阳 621000,中国空气动力研究与发展中心计算空气动力研究所，四川绵阳 621000

作者简介:崔兴达，男，硕士，研究实习员，研究领域为高超声速推进技术。
基金资助:
国家自然科学基金(11472305；91016028)。

Abstract

Abstract: In order to investigate the effects of different ethylene fuel injection location upstream of a cavity flameholder on low-frequency combustion oscillation in a model engine combustor at the inflow conditions of Mach 2.52 with the stagnation temperature of 1486 K， high-frequency pressure sensor and high-speed imaging camera were used to investigate the characteristics of pressure and flame dynamics in an engine under the schemes of fuel injection close or far upstream of a cavity in a direct-connected supersonic combustion test facility with total mass flow rate of 1kg/s. The experimental results suggest that when the fuel is injected closely upstream of the cavity flameholder there exist great range of subsonic flow regions in the condition of present equivalence ratio， and low-frequency pressure oscillation which is driven by thermo-acoustic instability with a broad frequency range of 50～400Hz can occur while the amplitude of oscillation is weak. For the case that distance between the fuel injection and cavity is long， periodic flame oscillation which is charactered by flame flashback and blow-off is observed in combustor. It is suggested that long fuel injection distance is advantageous to sufficient mixing of fuel/air and produces a premixed region from the injection to the cavity， which leads to a rapid flame flashback against the incoming flow. The flame flashback is related to flame acceleration in a deflagration-to-detonation transition procedure. This process couples with the flame blow-off and a low-frequency pressure oscillation can be formed with a specific dominant frequency (about 85Hz) and strong amplitude.

Key words: Low-frequency oscillation；Injection location；Cavity flameholder；Thermal-acoustic instability；Flame flashback；Flame acceleration；Deflagration-to-detonation

摘要： 为了研究在入口来流马赫数2.52，总温1486K的超声速来流条件下，稳焰凹腔上游不同位置乙烯横向喷注对模型发动机燃烧室内低频燃烧振荡特性的影响，通过1kg/s直连式超燃试验平台，利用高频压力传感器、高速摄影相机等设备，对凹腔上游近距离、远距离喷注等方案的发动机内部压力与火焰动态特性进行了研究。试验结果表明:在当前当量比条件下，当稳焰凹腔上游近距离喷注燃料时，燃烧室存在较大范围亚声速区域，并出现由热声不稳定性激励的低频压力振荡，频率分布范围较宽(50～400Hz)且振幅较弱。对于燃料喷注位置到稳焰凹腔距离较远的情况，燃烧室内出现以火焰逆传和火焰吹脱为特征的周期性火焰振荡现象。分析认为较远喷注距离有利于燃料-空气充分混合并形成预混区，导致火焰快速逆传。火焰逆传与DDT(爆燃转爆震)中的火焰加速传播过程有关。周期性火焰逆传与火焰吹脱过程相耦合形成了具有特定主频(约85Hz)且振幅较大的低频压力振荡。

关键词: 低频燃烧振荡；喷注位置；稳焰凹腔；热声不稳定性；火焰逆传；火焰加速；爆燃转爆震

CUI Xing-da¹,SUN Ming-bO²,WANG Hong-bO²,JIANG Xiong¹,LI Wei¹. Effects of Injection Scheme on Low-Frequency Oscillation in a Cavity-Based Scramjet Combustor[J]. Journal of Propulsion Technology, 2018, 39(10): 2370-2380.

崔兴达,孙明波,汪洪波,江雄,李伟. 喷注方案对凹腔稳焰燃烧室低频振荡的影响研究[J]. 推进技术, 2018, 39(10): 2370-2380.

References

[1] 乐嘉陵, 胡欲立, 刘陵. 双模态超燃冲压发动机研究进展[J]. 流体力学实验与测量, 2000, 14(1): 1-12.
[2] 刘兴洲. 中国超燃冲压发动机研究回顾[J]. 推进技术, 2008, 29(4): 385-395. (LIU Xing-zhou. Review of Scramjet Research in China[J]. Journal of Propulsion Technology, 2008, 29(4): 385-395.)
[3] 汪洪波. 超声速来流中凹腔稳定的射流燃烧模式及振荡机制研究[D]. 长沙:国防科技大学, 2012.
[4] Ma F H, Li J, Yang V. Thermoacoustic Flow Instability in a Scramjet Combustor[R]. AIAA 2005-3824.
[5] Li J, Ma F H, Yang V, et al. A Comprehensive Study of Combustion Oscillations in a Hydrocarbon-Fueled Scramjet Engine[R]. AIAA 2007-836.
[6] Lin K C, Ma F H, Li J, et al. Acoustic Characterization of an Ethylene-Fueled Scramjet Combustor with a Recessed Cavity Flameholder[R]. AIAA 2007-5382.
[7] Lin K C, 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.
[8] 汪洪波, 孙明波, 梁剑寒, 等. 带凹腔超燃燃烧室内燃烧振荡的数值研究[C]. 黄山:第二届高超声速科技学术会议, 2009.
[9] McManus K R, Poinsot T, Candel S M. A Review of Active Control of Combustion Instabilities[J]. Progress in Energy Combustion Science, 1993, 19: 1-29.
[10] Choi J Y, Ma F, Yang V. Combustion Oscillations in a Scramjet Engine Combustor with Transverse Fuel Injection[J]. Proceedings of the Combustion Institute, 2005, 30: 2851-2858.
[11] Wang H B, Wang Z G, Sun M B, et al. Large-Eddy/Reynolds-Averaged NaviereStokes Simulation of Combustion Oscillations in a Cavity-Based Supersonic Combustor[J]. International Journal of Hydrogen Energy, 2013, 38: 5918-5927.
[12] Micka D J, Driscoll J F. Combustion Characteristics of a Dual-Mode Scramjet Combustor with Cavity Flameholder[J]. Proceedings of the Combustion Institute, 2009, 32: 2397-2404.
[13] Micka D J. Combustion Stabilization, Structure, and Spreading in a Laboratory Dual-Mode Scramjet Combustor [D]. Michigan: The University of Michigan, 2010.
[14] 李大鹏, 丁猛, 梁剑寒, 等. Ma=4液体碳氢燃料超燃冲压发动机点火试验 [J]. 推进技术, 2009, 30(4): 385-389. (LI Da-peng, DING Meng, LIANG Jian-han, et al. Ignition Experimental for Liquid Hydrocarbon Fueled Scramjet with Simulated Flight Mach 4[J]. Journal of Propulsion Technology, 2009, 30(4): 385-389.)
[15] 蔡尊, 王振国, 李西鹏, 等. 基于超声速气流中凹腔主动喷注的强迫点火方案研究[J]. 推进技术, 2015, 36(8): 1186-1192. (CAI Zun, WANG Zhen-guo, LI Xi-peng, et al. Investigation of Forced Ignition Scheme Based on Active Cavity Injection in Supersonic Flow[J]. Journal of Propulsion Technology, 2015, 36(8): 1186-1192.)
[16] Yang V, Anderson W E. Liquid Rocket Engine Combustion Instability[M]. Pennsylvania: Pennsylvania State University, 1995.
[17] Yu K, Pang B, Hsu O. Implementing Active Combustion Control in Propulsion Systems[R]. AIAA 2001-3849.
[18] 聂万胜, 丰松江. 液体火箭发动机燃烧动力学模型与数值计算[M]. 北京:国防工业出版社, 2011.
[19] Fichera A, Losenno C, Pagano A. Experimental Analysis of Thermo-Acoustic Combustion Instability[J]. Applied Energy, 2001, 70: 179-191.
[20] Bayley D J, Hartfield R J. Experimental Investigation of Angled Injection in a Compressible Flow[R]. AIAA 1995-2414.
[21] Lee J H S. The Detonation Phenomenon [M]. UK: Cambridge University Press, 2008.
[22] Akkerman V, Bychkov V, Kuznetsov M, et al. Fast Flame Acceleration and Deflagration-to-Detonation Transition in Smooth and Obstructed Tubes, Channels and Slits [C]. University of Utah: 8th U.S.National Combustion Meeting, 2013.
[23] Valiev D, Bychkov V, Akkerman V, et al. Different Stages of Flame Acceleration from Slow Burning to Chapman-Jouguet Deflagration[J]. Physical Review E, 2009, 80(3).
[24] Bychkov V, Akkerman V, Fru G, et al. Flame Acceleration in the Early Stages of Burning in Tubes[J]. Combustion and Flame, 2007, 150(4): 263-276.
[25] Dorofeev S B. Flame Acceleration and Explosion Safety Applications[J]. Proceedings of the Combustion Institute, 2011, 33(2): 2161-2175.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2016-11-10；修订日期:2016-12-29。基金项目:国家自然科学基金(11472305；91016028)。作者简介:崔兴达,男,硕士,研究实习员,研究领域为高超声速推进技术。E-mail: cui2016sdu@163.com

Effects of Injection Scheme on Low-Frequency Oscillation in a Cavity-Based Scramjet Combustor

喷注方案对凹腔稳焰燃烧室低频振荡的影响研究

PDF

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 0

Recommended Articles

Metrics

Comments