前掠对高负荷风扇转子泄漏涡结构的影响

王雷; 刘波; 赵鹏程

前掠对高负荷风扇转子泄漏涡结构的影响

1.
西北工业大学动力与能源学院, 西安 710072

基金项目:

国家自然科学基金项目(50976093)资助

详细信息

作者简介:
王雷(1985-)，博士研究生，研究方向为高负荷风扇设计，recoba201@gmail.com;刘波(联系人)，教授，博士生导师，liubo704@nwpu.edu.cn

王雷(1985-)，博士研究生，研究方向为高负荷风扇设计，recoba201@gmail.com;刘波(联系人)，教授，博士生导师，liubo704@nwpu.edu.cn

计量
- 文章访问数: 164
- HTML全文浏览量: 16
- PDF下载量: 5
- 被引次数: 0
出版历程
- 收稿日期: 2011-04-19
- 刊出日期: 2015-06-10

Numerically Investigating Effects of Highly-loaded and Forward-swept Fan Rotor on Tip Clearance Vortex

1.
School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072

摘要

摘要: 以高负荷两级风扇第一级前掠转子为研究对象,通过数值模拟手段对近失速点叶尖流场进行了深入分析。为比较前掠对泄漏涡结构的影响,与同等气动性能下的常规转子进行了对比。结果表明前掠转子在近失速工况下泄漏涡涡心并未发生破碎,气动负荷展向分布更加均匀。对前掠转子不同于常规转子的叶尖泄漏涡结构产生机理提出了新的解释。
- 高负荷 /
- 前掠 /
- 泄漏涡 /
- 涡破碎
Abstract: We numerically calculate the three-dimensional viscous flow field near the blade tip region at the near stall margin of a highly-loaded and forward-swept fan rotor. We compare the effects of the forward-swept fan rotor on the tip clearance vortex structure with those of a conventionally stacked radial rotor that has aerodynamically equal performance. The comparison results show that both the stall margin of the forward-swept fan rotor and the distribu-tion of its aerodynamic tip loading are improved. Our detailed analysis of its flow field reveals that the tip clearance vortex of the forward-swept fan rotor does not break under the near stall condition, thus providing a novel explanation why the tip clearance vortex structure of a forward-swept fan rotor is different from that of a conventional fan rotor.
- flow field /
- stall margin /
- highly-loaded and forward-swept fan rotor /
- tip clearance vortex

HTML全文

参考文献(16)

[1]	Adamczyk J J,Celestina M L,Greitzer E M.The role of tipclearance in high-speed fan stall[J].Journal of Turbomach-inery,1993,115(1):28～39
[2]	Gerolymos G A,Vallet I.Tip-clearance and secondary flows in atransonic compressor rotor[J].Journal of Turbomachinery,1999,121:751～762
[3]	Chima R V.Calculation of tip clearance effects in a transoniccompressor rotor[J].Journal of Turbomachinery,1998,120
[4]	Suder K L,Celestina M L.Experimental and computational in-vestigation of the tip clearance flow in a transonic axial compres-sor rotor[J].Journal of Turbomachinery,1996,118
[5]	Hoeger M,Fritsch G,Bauer D.Numerical simulation of theshock-tip leakage vortex interaction in a HPC front stage[J].Journal of Turbomachinery,1999,121:456～468
[6]	Liu B J,Yu X J,Yuan H J,Liu H X,Jiang H K,Xu Y T.Ap-plication of SPIV in turbomachinery[J].Experiments in Flu-ids,2006,40:621～642
[7]	Yu X J,Liu B J,Jiang H K.Characteristics of the tip leakagevortex in a low-speed axial compressor[J].AIAA Journal,2009,45(4):870～878
[8]	Wadia A R,Szucs P N,Crall D W.Inner workings of aerody-namic sweep[J].Journal of Turbomachinery,1998,120
[9]	Wadia A R,Szucs P N,Crall D W,Rabe D C.Forward SweptRotor Studies in Multistage Fans with Inlet Distortion[R].ASME Paper No.GT-2002-30326
[10]	Passrucker H,Engber M.The effect of forward sweep in a tran-sonic compressor rotor[J].Journal of Power and Energy,2003,217:357～365
[11]	Bergner J,Hennecke D K.Darmstadt rotor No.2,III experi-mental analysis of an aft-swept axial transonic compressor stage[J].International Journal of Rotating Machinery,2003,9:385～391
[12]	季路成,陈江,林峰.轴流压气机设计中掠的另类认识[J].工程热物理学报,2005,26(4):567～571
[13]	Hah H,Rabe D C,Wadia A R.Role of Tip-Leakage Vorticesand Passage Shock in Stall Inception in a Swept TransonicCompressor Rotor[R].ASME Paper No.GT-2004-53867
[14]	McNulty G S,Deckers J J,Beacher B F.The impact of forwardswept rotors on tip-limited low-speed axial compressors[J].Journal of Turbomachinery,2004,125:445～454
[15]	Van Zante D E,Strazisar A J,Wood J R,Hathaway M D.Rec-ommendations for achieving accurate numerical simulation of tipclearance flows in transonic compressor rotors[J].Journal ofTurbomachinery,2000,122:733～741
[16]	Leibovich S.The structure of vortex breakdown[J].Annual Re-view of Fluid Mechanics,1978,10:221～246