带凹腔的支板火焰稳定器三维大涡模拟

邹咪; 金捷; 王旭东

doi:10.13224/j.cnki.jasp.2017.03.012

带凹腔的支板火焰稳定器三维大涡模拟

doi: 10.13224/j.cnki.jasp.2017.03.012

北京航空航天大学能源与动力工程学院,北京 100191

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出版历程
- 收稿日期: 2015-07-02
- 刊出日期: 2017-03-28

Three-dimensional large eddy simulation of strut flame-holder with cavity

摘要

摘要: 为研究支板冷态流场,应用LES(大涡模拟)的方法对带凹腔的支板火焰稳定器在Ma=0.06和 Ma=0.09两种工况下分别进行三维数值模拟.对比试验和仿真结果表明:三维大涡模拟结果具有与试验相似的流场结构,定量对比试验和LES结果的尾涡脱落频率的最大相对误差为9.4%；支板尾部截面流向时均速度的最大相对误差为7.7%.表明数值模拟方法和边界条件设置的正确性和可信度.又对支板的三维流场进行分析:速度越大,支板尾涡的尺寸和强度越大；支板流场存在明显的三维效应,并且随着速度变大,三维效应越明显.
- 加力燃烧室 /
- 支板 /
- 凹腔 /
- 大涡模拟 /
- 尾涡 /
- 三维效应
Abstract: In order to study the cold flow field of strut, three-dimensional LES (large eddy simulation) of strut flame-holder with cavity at Ma=0.06 and Ma=0.09 was carried out respectively. The simulation results were compared with experiment data. It showed that the flow field structure of three-dimensional LES was similar with that of experiment. Whats more, two quantitative comparisons in the frequency of wake vortex and time-averaged stream-wise velocity on strut rear section were made. And the maximum relative errors were 9.4% and 7.7% respectively, proving that the model of numerical calculation at boundary conditions was correct and believable. Then by analyzing the three-dimensional flow field of strut, a conclusion that the faster velocity means the bigger size and intensity of wake vortex. Besides, the result of three-dimensional LES shows an obvious phenomenon of three-dimensional effect which gets stronger when the velocity gets faster.
- after-burner /
- strut /
- cavity /
- large eddy simulation /
- wake vortex /
- three-dimensional effect

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参考文献(25)

[1]	Lovett J A,Brogan T P,Philippona D S.Development needs for advanced afterburner designs［R］.AIAA-2004-4192,2004.
[2]	Desclaux J,Serre J.Advanced new generation engine for Rafale Multirole Fighter［R］.AIAA-2003-2610,2003.
[3]	黄勇,林宇震,李峰,等.燃烧与燃烧室［M］.北京:北京航空航天大学出版社,2009:314-321.
[4]	季鹤鸣,樊未军,杨茂林.新型内突扩加力燃烧室方案可行性分析［J］.航空发动机,2006,32(1):35-37.JI Heming,FAN Weijun,YANG Maolin.Feasibility analysis of a new inner dumped afterburner concept［J］.Aeroengine,2006,32(1):35-37.(in Chinese)
[5]	金莉,谭永华.火焰稳定器综述［J］.火箭推进,2006,32(1):30-34.JIN Li,TAN Yonghua.Study on flameholders［J］.Journal of Rocket Propulsion,2006,32(1):30-34.(in Chinese)
[6]	郑殿峰,张会强,林文漪,等.带U型槽射流缝隙式稳定器燃烧性能的试验研究［J］.航空动力学报,2003,18(6):808-812.ZHENG Dianfeng,ZHANG Huiqiang,LIN Wenyi,et al.Experimental investigation of combustion performance of U-type flame holder［J］.Journal of Aerospace Power,2003,18(6):808-812.(in Chinese)
[7]	张洪滨,王纪根.双Ⅴ型稳定器的研制及应用［J］.推进技术,1994,15(3):39-43.ZHANG Hongbin,WANG Jigen.Development and application of double Ⅴ type flame stabilizaer［J］.Journal of Propulsion Technology,1994,15(3):39-43.(in Chinese)
[8]	付藻群.吸入式稳定器设计研究与试验［J］.航空发动机,1998(3):28-32.FU Zaoqun.Design and experiment on suction stabilizier［J］.Aeroengine,1998(3):28-32.(in Chinese)
[9]	岳连捷,杨茂林,黄勇,等.尾缘吹气式火焰稳定器流场计算［J］.航空动力学报,1998,13(2):180-184,221.YUE Lianjie,YANG Maolin,HUANG Yong,et al.Numerical prediction of cold flow field behind EBMC flameholder［J］.Journal of Aerospace Power,1998,13(2):180-184,221.(in Chinese)
[10]	Huellmantel L W,Ziemer R W,Cambel A B.Stabilization of premixed propane-air flames in recessed ducts［J］.Journal of Jet Propulsion,1957,27(1):31-34.
[11]	Hsu K Y,Goss L P,Trump D D.Performance of a trapped vortex combustor［J］.AIAA 95-0810,1995.
[12]	JIN Yi,HE Xiaomin,JIANG Bo,et al.Effect of cavity-injector/radial-strut relative position on performance of a trapped vortex combustor［J］.Aerospace Science and Technology,2014,32(1):10-18.
[13]	ZHANG Rongchun,FAN Weijun.Flow field measurements in the cavity of a trapped vortex combustor using PIV［J］.Journal of Thermal Science,2012,21(4):359-367.
[14]	秦伟林,何小民,金义,等.凹腔驻涡与支板稳焰组合加力燃烧室模型冷态流场试验［J］.航空动力学报,2012,27(6):1347-1354.QIN Weilin,HE Xiaomin,JIN Yi,et al.Experimental investigation on cold flow characteristics of afterburner with cavity/strut hybrid flameholders［J］.Journal of Aerospace Power,2012,27(6):1347-1354.(in Chinese)
[15]	刘玉英,李瑞明,杨茂林,等.驻涡燃烧室凹腔流场结构试验［J］.推进技术,2010,31(1):29-33.LIU Yuying,LI Ruiming,YANG Maolin,et al.Experiment on flow field of cavity in trapped vortex combustor［J］.Journal of Propulsion Technology,2010,31(1):29-33.(in Chinese)
[16]	Merlin C,Domingo P,Vervisch L.Large eddy simulation of turbulent flames in a trapped vortex combustor (TVC):a flamelet presumed-PDF closure preserving laminar flame speed［J］.Comptes Rendus Mécanique,2012,340(11/12):917-932.
[17]	Ghodke C D,Choi J J,Srinivasan S.Large eddy simulation of supersonic combustion in a cavity-strut flameholder［R］.AIAA-2011-323,2011.
[18]	JIN Yi,HE Xiaomin,ZHANG Jingyu.Numerical investigation on flow structures of a laboratory-scale trapped vortex combustor［J］.Applied Thermal Engineering,2014,66(1/2):318-327.
[19]	Clements T R,Graves C B.Augmentor burner:US,US5385015A［P］.1995-01-31.
[20]	李峰,郭瑞卿,李龙贤,等.整流支板和火焰稳定器的一体化设计加力燃烧室性能数值模拟［J］.航空发动机,2012,38(5):6-9.LI Feng,GUO Ruiqing,LI Longxian et al.Numercial simulation of characteristics for aftrerburner with integrated flow plate and flameholder［J］.Aeroengine,2012,38(5):6-9.(in Chinese)
[21]	孙雨超,张志学,李江宁,等.一体化加力燃烧室方案设计及数值研究［J］.航空科学技术,2011(4):71-74.SUN Yuchao,ZHANG Zhixue,LI Jiangning,et al.Design and numerical research of integrated rear frame and afterburner［J］.Aeronautical Science and Technology,2011(4):71-74.(in Chinese)
[22]	马梦颖.一体化加力燃烧室火焰稳定装置数值计算与试验研究［D］.北京:北京航空航天大学,2010.MA Mengying.Computational and experimental investigation of integrated afterburner flame stabilizer［D］.Beijing:Beijing University of Aeronautics and Astronautics,2010.(in Chinese)
[23]	吴迪.新型一体化加力燃烧室冷态流场试验研究［D］.北京:北京航空航天大学,2010.WU Di.Experimental research of non-reacting flow fields in a novel integrated afterburner［D］.Beijing:Beijing University of Aeronautics and Astronautics,2010.(in Chinese)
[24]	王海龙.新型火焰稳定器设计与研究［D］.北京:北京航空航天大学,2011.WANG Hailong.Design and research on new-type flame stabilizer［D］.Beijing:Beijing University of Aeronautics and Astronautics,2011.(in Chinese)
[25]	刘雯佳.新型一体化加力燃烧室支板冷态流场数值仿真［D］.北京:北京航空航天大学,2010.LIU Weijia.Numerical simulation for cool flow-field of strut on novel integrated afterburner［D］.Beijing:Beijing University of Aeronautics and Astronautics,2010.(in Chinese)