某发动机风扇进气畸变数值模拟

刘永泉; 刘火星; 郑宁

某发动机风扇进气畸变数值模拟

1.
中国航空工业集团公司沈阳发动机设计研究所沈阳 110015
2.
北京航空航天大学能源与动力工程学院, 北京 100191

计量
- 文章访问数: 2347
- HTML浏览量: 357
- PDF量: 649
- 被引次数: 0
出版历程
- 收稿日期: 2012-05-12
- 刊出日期: 2012-09-28

Numerical simulation of an aero-engine fan with inlet distortion

1.
Shenyang Aeroengine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China
2.
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 采用周向平均体积力的方法将叶片对气流的作用简化为体积力源项研究进气畸变对某航空发动机风扇的影响.分别对该风扇在均匀进气条件下和进口存在稳态总压畸变条件下的流场进行了模拟计算,得到了和雷诺平均Navier-Stockes(RANS)计算几乎完全一致的特性线以及流场主要结构特征,在进行进气畸变条件下流场模拟计算时成功地捕捉到了进口畸变扰动在流场中的传播情况,并能够正确反映进气畸变对压气机的影响.结果表明:压气机进气畸变流场有着大尺度、强耦合、信息传播三维性明显等特征,采用周向平均体积力研究方法可以利用非常少的计算资源加深对进气畸变流动的认识.
- 风扇/压气机 /
- 进气畸变 /
- 体积力模型 /
- 稳定性 /
- 源项
Abstract: The method of replacing the blade row forces with distributed bulk body force source terms was developed to simulate fan flow field with inlet distortion.The fan with clean inlet and inlet steady total pressure distortion in an aeroengine were simulated respectively.It demonstrates that the results of fan with clean inlet agree well with the solutions of RANS(Reynolds-averaged Navier-Stokes).In the case with inlet distortion,this code can obtain the propagation of inlet distortion correctly.The unsteady simulation shows that large-scale strong reaction and three-dimentional transportation were main property of flow field with inlet distortion. The attraction of the distributed bulk body force model is obvious in that it can be relatively independent of the empiricism while at the same time demands much less computer resources.
- fan/compressor /
- inlet distortion /
- body force model /
- stability /
- source term

HTML

参考文献(18)

[1]	Mazzawy R S.Multiple segment parallel compressor model for circumferential flow distortion[J].ASME Journal of Engineering for Power,1977,99(2):288-296.
[2]	好毕斯嘎拉图,周胜田,张志舒,等.总压畸变对整机稳定性的影响研究分析[J].航空发动机,2012,38(4):34-37. HAO bisigalatu,ZHOU Shengtian,ZHANG Zhishu,et al.Effect of total pressure distortion on aeroengine stability[J].Aeroengine, 2012,38(4):34-37.(in Chinese)
[3]	芮长胜,吴虎. 周向总压畸变条件下多级轴流压气机失速首发级预测分析[J].航空发动机,2011,37(5):49-52. RUI Changsheng,WU Hu.Prediction analysis of first stall stage of multistage axial flow compressor with circumferential total pressure distortion[J].Aeroengine, 2011,37(5):49-52.(in Chinese)
[4]	芮长胜,吴虎.周向总压畸变对多级轴流压气机稳定性影响的逐级模拟方法[J].航空发动机,2007,33(3):11-14. RUI Changsheng,WU Hu.Stage-by-stage simulation method of circumferential total pressure distortion effect on multistage axial flow compressor stability[J].Aeroengine,2007,33(3):11-14.(in Chinese)
[5]	TanC S,Mccune J E,Mitchell N A,et al.Non-axisymmetric flow through annular actuator disks:inlet distortion problem[J].ASME Journal of Engineering for Power,1977,100:604-617.
[6]	Yao J,Gorrell S D,Wadia A R.A time-accurate CFD analysis of inlet distortion induced swirl in multistage fans[J].AIAA 2007-5059,2007.
[7]	Gorrell S E,Yao J,Wadia A R.High fidelity URANS analysis of swirl generation and fan response to inlet distortion[J].AIAA 2008-4985,2008.
[8]	Yao J,Gorrell S E,Wadia A R.High-fidelity numerical analysis of per-rev-type inlet distortion transfer in multistage fans Part Ⅰ:simulations with selected blade rows. ASME GT2008-50812,2008.
[9]	Yao J,Gorrell S E,Wadia A R.High-fidelity numerical analysis of per-rev-type inlet distortion transfer in multistage fans Part Ⅱ:entire component simulation and inves tigation. ASME GT2008-50813,2008.
[10]	Hale A,O'Brien W O.Three-dimensional turbine engine analysis compressor code (TEACC)for steady-state inlet distortion[J].Journal of Turbo-machinery,1998,120(7):422-430.
[11]	Fidalgo V J,Hall C A,Colin Y.A study of fan-distortion interaction within the NASA rotor 67 transonic stage. ASME GT2010-22914,2010.
[12]	Chima R V.A three-dimensional unsteady CFD model of compressor stability. ASME GT 2006-90040,2006.
[13]	郑宁,邹正平,徐力平.风扇进气畸变三维非定常数值模拟技术研究[J]. 航空动力学报,2007,22(1):60-65. ZHENG Ning,ZOU Zhengping,XU Liping.3-D unsteady numerical simulation of fan/compressor with inlet distortion[J]. Journal of AerospacePower,2007,22(1):60-65.(in Chinese)
[14]	Gong Y,C S Tan,K A Gordon,et al.A computational model for short-wavelength stall inception and development in multistage compressors[J].Trans.of ASME,Journal of Turbomachinery,1999,121(4):726-734.
[15]	Gong Y.A computational model for rotating stall and inlet distortions in multistage compressors. MA:Massachusetts Institute of Technology,1999.
[16]	Xu L.Assessing viscous body forces for unsteady calculations. ASME GT-2002-30359,2002.
[17]	刘超,宁方飞.黏性彻体力建模方法及其应用[J].航空动力学报,2011,26(1):128-135. LIU Chao,NING Fangfei.Investigation on distributed viscous body force modeling and its application[J].Journal of Aerospace Power,2011,26(1):128-135.(in Chinese)
[18]	Longley J P,Greitzer E M.Inlet distortion effects in aircraft propulsion system integration. AGARD Lecture Series,AGARD LS-183,1992.