多凹腔燃烧室煤油非定常超声速燃烧流动过程研究

推进技术 ›› 2016, Vol. 37 ›› Issue (9): 1688-1695.

多凹腔燃烧室煤油非定常超声速燃烧流动过程研究

刘刚¹,朱韶华¹,郭新华²,田亮¹,徐旭¹

北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191,北京动力机械研究所高超声速冲压发动机技术重点实验室，北京 100074,北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191

发布日期:2021-08-15
作者简介:刘刚，男，博士生，研究领域为超燃冲压发动机燃烧流动的实验与数值仿真。

Investigation on Transient Process of Supersonic

School of Astronautics，Beihang University，Beijing 100191，China,School of Astronautics，Beihang University，Beijing 100191，China,Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China,School of Astronautics，Beihang University，Beijing 100191，China and School of Astronautics，Beihang University，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为探究多凹腔燃烧室的燃烧流动过程，采用非定常方法对液态煤油超声速燃烧特性进行了数值研究。计算结果发现，随着燃烧释热的进行，一道拟正激波被推到靠近隔离段入口处，最大压比达到3.77，燃烧达到稳态需要22ms；上游凹腔处煤油液滴运动轨迹表现出很强的非定常性，其运动方向与当地流动时刻的压力条件相匹配，上凹腔附近的液滴穿透深度明显大于下凹腔的，液滴个数也大于后者；出口总压恢复系数为47.09%，与实验值47.50%很接近，出口燃烧效率达到72.91%，体现了多凹腔燃烧室在保证燃烧性能较好时总压损失较低的优点；扩张型面上的凹腔质量交换律大于平直型面上的，表明型面扩张有利于增强凹腔内燃料与主流空气的质量交换；计算预测的燃烧室侧壁、上壁、下壁压力均与实验值吻合得较好。

关键词: 多凹腔燃烧室；非定常燃烧流动；液滴轨迹；穿透深度；凹腔质量交换律；数值研究

Abstract: In order to explore the process of combustion and flow based on a multi-cavity combustor，transient method is used to numerically investigate the supersonic combustion characteristics of liquid kerosene. The numerical results show that an approximate normal shock is pushed back to the isolator inlet as the heat release from combustion proceeds. The maximal ratio of pressure increase is up to 3.77，and the flowfield reaches steady within 22ms. Track of kerosene droplet in the upstream cavities presents strong transient characteristics. Its movement direction matches the pressure in local flow time. Penetration depth of droplet near the up cavity is obviously larger than that of the down cavity，and the droplet number of the former is much more than that of the latter. The total pressure recovery coefficient in the combustor outlet is equal to 47.09%，which is close to the experimental value 47.50%. The combustion efficiency is up to 72.91%，which displays the advantage of a low total pressure loss with a good combustion characteristics for the multi-cavity-based combustor. Mass entrainment rate where cavity located at the expanding surface is larger than that of the level surface，indicating that the expanding surface is beneficial to enhance the mass entrainment between the fuel in the cavity and the mainflow air. Numerically predicted static pressure on the side，up and down wall of the combustor has a good agreement with the experimental datum.

Key words: Multi-cavity combustor；Transient combustion and flow；Droplet track；Penetration depth；Mass entrainment rate of cavity；Numerical study

刘刚,朱韶华,郭新华,田亮,徐旭. 多凹腔燃烧室煤油非定常超声速燃烧流动过程研究[J]. 推进技术, 2016, 37(9): 1688-1695.

LIU Gang¹,ZHU Shao-hua¹,GUO Xin-hua²,TIAN Liang¹,XU Xu¹. Investigation on Transient Process of Supersonic[J]. Journal of Propulsion Technology, 2016, 37(9): 1688-1695.

参考文献

[1] 徐胜利, Archer R D, Milton B E, 等. 煤油在超声速气流中非定常横向喷射的实验观察[J]. 空气动力学学报, 2000, 18(3):272-279.
[2] 耿辉, 周进, 翟振辰, 等. 凹腔结构对超声速燃烧室中横向燃料喷流流动与燃烧的影响[J]. 推进技术, 2007, 28(6): 599-606. (GENG Hui, ZHOU Jin, ZHAI Zhen-chen, et al. Influence of Cavity Geometry on Flow and Combustion of Transverse Fuel Jets in a Supersonic Combustor[J]. Journal of Propulsion Technology, 2007, 28(6): 599-606.)
[3] 刘敬华, 凌文辉, 刘兴洲, 等. 超音速燃烧室性能非定常准一维流数值模拟[J]. 推进技术, 1998, 19(1):1-6. (LIU Jing-hua, LING Wen-hui, LIU Xing-zhou, et al. A Quasi-One Dimensional Unsteady Numerical Analysis of Supersonic Combustor Performance[J]. Journal of Propulsion Technology, 1998, 19(1): 1-6.)
[4] Yungster S, Radhakrishnan K. Simulation of Unsteady Hypersonic Combustion Around Projectiles in an Expansion Tube[J]. Shock Waves, 2001, 11: 167-177.
[5] 刘陵, 唐明, 张榛, 等. 氢气超音速燃烧非定常过程数值模拟[J]. 推进技术, 1996, 17(3): 1-5. (LIU Ling, TANG Ming, ZHANG Zhen, et al. A Numerical Simulation of Unsteady Supersonic Combustion with Transverse Hydrogen[J]. Journal of Propulsion Technology, 1996, 17(3): 1-5.)
[6] 汪洪波. 超声速燃烧凹腔剪切层非定常特性研究[D]. 长沙:国防科学技术大学研究生院, 2007.
[7] Martin M P. DNS of Hypersonic Turbulent Boundary Layers[R]. AIAA 2004-2337.
[8] Ihme M, Pitsch H. LES of a Non-Premixed Flame Using an Extended Flamelet/Progress Variable Model[R]. AIAA 2005-0558.
[9] 范晓樯, 李桦, 丁猛. 等截面矩形隔离段内流场的三维数值模拟[J]. 推进技术, 2002, 23(2): 129-131. (FAN Xiao-qiang, LI Hua, DING Meng. 3-D Numerical Simulation on Inner Flow Field in Rectangular Cross Section Isolator[J]. Journal of Propulsion Technology, 2002, 23(2): 129-131.)
[10] Matsuo A, Fujii K. Detailed Mechanism of the Unsteady Combustion Around Hypersonic Projectiles[J]. AIAA Journal, 1996, 34(10): 2082-2089.
[11] Luetke N, Mohieldin T O, Tiwari S N. Unsteady Numerical Analysis of Hydrogen Combustion in a Dual Mode Engine[R]. AIAA 2007-5425.
[12] Eremeev A C, Grishin V G, Nikitenko L K, et al. Enhanced Ignition and Mixing of Kerosene Fuel in High-Speed Air Streams[R]. AIAA 2005-0614.
[13] Baurle R A, Gruber M R. A Study of Recessed Cavity Flowfields for Supersonic Combustion Applications[R]. AIAA 98-0938.
[14] 孙明波, 梁剑寒, 王振国. 超声速燃烧火焰稳定凹腔质量交换特性的数值研究[J]. 力学学报, 2007, 39(2): 188-194.
[15] 刘欧子, 蔡晋生. 凹槽非定常超音速流动的研究[J]. 航空计算技术, 2011, 41(4): 28-31.
[16] Baurle R A, Tam C -J, Dasgupta S. Analysis of Unsteady Cavity Flows for Scramjet Applications[R]. AIAA 2000-3617.
[17] Yentsch R J, Gaitonde D V. Unsteady Three-Dimensional Mode Transition Phenomena in a Scramjet Flowpath[J]. Journal of Propulsion and Power, 2015, 31(1): 104-122.
[18] Yu G, Li J G, Chang X Y, et al. Fuel Injection and Flame Stabilization in a Liquid-Kerosene-Fueled Supersonic Combustor[J]. Journal of Propulsion and Power, 2003, 19 (5): 885-893.
[19] Kumaran K, Babu V. Mixing and Combustion Characteristics of Kerosene in a Model Supersonic Combustor[J]. Journal of Propulsion and Power, 2009, 25(3):583-592.
[20] Menter F R. Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications[J]. AIAA Journal, 1994, 32(8): 1598-1605.
[21] Liu G, Xu X, Xie Y F. Numerical Investigation on the Supersonic Combustion of Liquid Kerosene in a Dual-Staged Strut Based Scramjet Combustor[R]. AIAA 2014-3665.
[22] 刘刚, 朱韶华, 郭新华, 等. 喷射方式对煤油超声速燃烧性能影响的数值研究[J]. 推进技术, 2016, 37(2). (LIU Gang, ZHU Shao-hua, GUO Xin-hua, et al. Numerical Investigation on the Influence of Injection Mode upon Supersonic Combustion of Kerosene[J]. Journal of Propulsion Technology, 2016, 37(2).)
[23] Thomas R A, Bussing, Murmant E M. Finite-Volume Method for the Calculation of Compressible Chemically Reacting Flows[J]. AIAA Journal, 1988, 26(9): 1070-1078.
[24] 邢建文, 杨样. H2O污染对超燃冲压发动机燃烧室性能影响的三维数值模拟[J]. 推进技术, 2011, 32(1): 5-10. (XING Jian-wen, YANG Yang. Three-Dimensional Simulation of H2O Vitiation Effects on Combustor Performance for Scramjet[J]. Journal of Propulsion Technology, 2011, 32(1): 5-10.)
[25] Baurle R A, Mathur T, Gruber M R, et al. A Numerical and Experimental Investigation of a Scramjet Combustor for Hypersonic Missile Applications[R]. AIAA 98-3121.
[26] Kumaran K, Behera P R, Babu V. Numerical Investigation of the Supersonic Combustion of Kerosene in a Strut-Based Combustor[J]. Journal of Propulsion and Power, 2010, 26(5): 1084-1091.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2015-03-30；修订日期:2015-05-11。作者简介:刘刚,男,博士生,研究领域为超燃冲压发动机燃烧流动的实验与数值仿真。E-mail: liugangence@sina.com