基于DES模型的超燃气动斜坡/燃气发生器方案仿真研究

流体力学与飞行力学

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基于DES模型的超燃气动斜坡/燃气发生器方案仿真研究

韦宝禧¹, 宋冈霖¹, 徐旭¹, 孙海忠², 杨阳¹

1. 北京航空航天大学宇航学院, 北京 100191;
2. 中国人民解放军63999部队, 北京 100094

收稿日期:2011-09-05 修回日期:2011-11-10 出版日期:2012-07-25 发布日期:2012-07-24
通讯作者: 徐旭,Tel.: 010-82339692 E-mail: xuxu@buaa.edu.cn E-mail:xuxu@buaa.edu.cn

DES Computational Study of Aero-ramp Injectors Integrated with Gas-portfire in Supersonic Flow

WEI Baoxi¹, SONG Ganglin¹, XU Xu¹, SUN Haizhong², YANG Yang¹

1. School of Astronautics, Beihang University, Beijing 100191, China;
2. No. 63999 Unit, People’s Liberation Army, Beijing 100094, China

Received:2011-09-05 Revised:2011-11-10 Online:2012-07-25 Published:2012-07-24

摘要/Abstract

摘要： 采用基于剪切应力输运(SST)k-ω两方程湍流模型的分离涡(DES)方法和雷诺时均Navier-Stokes(RANS)方法对超燃气动斜坡结合燃气发生器增进掺混方案进行数值仿真研究。通过对比DES仿真结果、RANS仿真结果与试验结果,发现DES仿真结果对流场内涡结构的捕捉和分辨能力强于RANS方法获得的结果。选取燃气发生器喷流形成的壁面涡流特征角为比较标准, DES仿真结果显示该角度为48°,RANS仿真结果为37°,而试验测得该角度为47°。可见DES仿真结果与试验结果更为接近,说明对于气动斜坡结合燃气发生器的超燃掺混方案,DES方法仿真结果是合理的。

关键词: 超声速掺混, DES模型, 气动斜坡, 燃气发生器, 超燃冲压发动机

Abstract: Detached eddy simulation (DES) and Reynolds average Navier-Stokes (RANS) models based on shear stress transport (SST) k-ω two-equation model are used to simulate the flow field of aero-ramp injectors integrated with gas-portfire, which is a new method to enhance mixing in supersonic flow. Results show that the DES model is able to capture more detailed flow structures such as eddies and separation zones as compared with the RANS method. A characteristic degree is selected to evaluate the accuracy of DES and RANS results by comparing them with experimental results. The results show that the characteristic degree in DES, RANS and experiments are 48°, 37° and 47°respectively. The results obtained by the DES model agree much better with experimental results than the RANS method. Therefore, the DES model is considered more suitable to simulate an aero-ramp injectors integrated with a gas-portfire flow field.

Key words: supersonic mixing, DES model, aero-ramp, gas-portfire, scramjet

中图分类号:

V231

韦宝禧, 宋冈霖, 徐旭, 孙海忠, 杨阳. 基于DES模型的超燃气动斜坡/燃气发生器方案仿真研究[J]. 航空学报, 2012, 33(7): 1201-1208.

WEI Baoxi, SONG Ganglin, XU Xu, SUN Haizhong, YANG Yang. DES Computational Study of Aero-ramp Injectors Integrated with Gas-portfire in Supersonic Flow[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(7): 1201-1208.

参考文献

[1] Shi X X. Numerical and experimental study on aerodynamic ramp injector in a supersonic combustor. Beijing: School of Jet Propulsion, Beihang University, 2010.(in Chinese)

史新兴. 基于气动斜坡的超燃燃烧室数值模拟及试验研究. 北京:北京航空航天大学能源与动力工程学院, 2010.

[2] Gallimore S D, Jacobsen L S, O’Brien W F, et al. An integrated aeroramp injector plasma-igniter for hydrocarbon fuels in a supersonic flow—Part B:experimental studies of the operating conditions. AIAA-2001-1767, 2001.

[3] Olmstead D T. Cavity coupled aeroramp injector combustion study. AIAA-2009-5227, 2009.

[4] Gruber M, Donbar J, Jackson T, et al. Performance of an aerodynamic ramp fuel injector in a scramjet combustor. AIAA-2000-36858, 2000.

[5] Eklund D R, Baurle R A, Gruber M R. Numerical study of a scramjet combustor fueled by an aerodynamic ramp injector in dual-mode combustion. AIAA-2001-379, 2001.

[6] Donbar J. Post-test analysis of flush-wall fuel injection [JP2]experiments in a scramjet combustor. AIAA-2001-3197, 2001.[JP]

[7] Maddalena L, Campioli T R, Schetz J A. Experimental and computational investigation of light-gas injectors in Mach 4.0 crossflow. Journal of Propulsion and Power, 2006, 22(5): 1027-1038.

[8] Anderson C D. Liquid-fuel aeroramp for scramjets. Journal of Propulsion and Power, 2005, 21(2): 317-374.

[9] Wei B X, Yan M L, Yang Y, et al. A study on integrated aerodynamic-ramp-injector/gas-portfire in a supersonic combustor: part two, experimental aspects. Proceedings of 2010 Asia-Pacific International Symposium on Aerospace Technology. Xi’an: Chinese Society of Aeronautics and Astronautics, 2010, 1: 1079-1083.

[10] Ye J. Large-eddy simulation of blade boundary layer spatio-temporal evolution under unsteady disturbances. Beijing: School of Jet Propulsion, Beihang University, 2008.(in Chinese)

叶建. 非定常环境中叶片边界层时空演化机制的大涡模拟. 北京:北京航空航天大学能源与动力工程学院,2008.

[11] David P. Detached eddy simulations of flush wall injection into a supersonic freestream. AIAA-2006-4576, 2006.

[12] Liu X Q, Wu Y Z, Cheng K M. Computation of lateral turbulent jets using M-SST DES model. Acta Mechanica Sinica, 2004, 36(4): 401-406. (in Chinese)

刘学强, 伍贻兆, 程克明. 用基于M-SST模型的DES数值模拟喷流流场. 力学学报, 2004, 36(4): 401-406.

[13] Li D, Igor M, Yoshiaki N. Is DES approach better than rans approach for airfoil stall simulation. Journal of Northwestern Polytechnical University, 2006, 24(2): 228-231. (in Chinese)

李栋, Igor M, 中村佳朗. 翼型失速特性的RANS方法与DES方法数值模拟对比分析. 西北工业大学学报, 2006, 24(2): 228-231.

[14] Menter F R. Zonal two-equation k-ω turbulence model for aerodynamic flows. AIAA-1993-2906, 1993.

[15] Hunt J C, Wray R, Moin P. Eddies, stream and convergence zones in turbulent flows. Proceedings of the 1988 Summer Program. Center for Turbulence Research, Stanford University, 1988.

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于DES模型的超燃气动斜坡/燃气发生器方案仿真研究

DES Computational Study of Aero-ramp Injectors Integrated with Gas-portfire in Supersonic Flow

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