跨声速风扇的弯、掠三维设计研究

姜斌; 郑群; 王松涛; 冯国泰

跨声速风扇的弯、掠三维设计研究

1.
哈尔滨工程大学动力与能源工程学院,哈尔滨 150001
2.
哈尔滨工业大学能源科学与工程学院,哈尔滨 150001

基金项目: 国家重点基础研究发展计划(2007CB210104); 中央高校基金(GK2030260109)

计量
- 文章访问数: 1597
- HTML浏览量: 0
- PDF量: 543
- 被引次数: 0
出版历程
- 收稿日期: 2011-09-02
- 刊出日期: 2012-08-28

Research on three-dimensional design of bowed and swept blade of transonic fan

1.
College of Power and Energy Engineering, Harbin Engineering University,Harbin 150001,China
2.
School of Energy Science and Engineering, Harbin Institute of Technology,Harbin 150001,China

摘要

摘要: 以某小型跨声速单级轴流风扇为平台,采用数值模拟的方法,研究并探讨了弯、掠三维设计技术对具有较高负荷的跨声速轴流压气机性能改善所起到的作用和抑制流动损失增加的机理.分别探讨了在动叶上半叶高和静叶端区采用不同的弯、掠形式对风扇设计点以及等转速线上的小流量工况性能的影响.研究结果表明:动叶上半叶高采用反弯设计能够有效改变动叶端区压力梯度,减少泄漏流在出口压力面侧的堆积,增加动叶顶部的通流能力.静叶端区采用前缘反弯和尾缘正弯的复合弯、扭技术,同时实现了端区增容和控制二次流发展的目的,随着流量的减小,弯、扭设计静叶更好地控制住了端区二次流的恶化,端区损失增长明显较直叶片缓慢,风扇的稳定工作范围得到提高.
- 跨声速风扇 /
- 弯、掠叶片 /
- 数值模拟 /
- 稳定工作范围 /
- 气动设计
Abstract: Effects of bowed and swept blade on the improvement of transonic fan performance and inhibition of the flow loss were studied by numerical simulation based on a small transonic axial fan.The swept and bowed design concept for the up half spanwise of rotor and later half spanwise of stator was discussed at the design flow condition and the less flow condition.The results show that negative bowed design for up half spanwise of rotor changes the pressure gradient near the endwall ,thus ,the accumulation of boundary layer near the side of pressure surface at outlet caused by the leakage flow is decreased,and the flow capacity is enhanced.The negative bowed design at leading edge and positive bowed design at trailing edge were adopted in the design of stator.The complex bowed and twisted technology can realize the increase of flow rate near the endwall and the control of the secondary flow at the same time.The bowed and twisted stator can also control the deterioration of secondary flow better with the decrease of flow rate and enlarge the range of steady operation condition obviously.
- transonic fan /
- bowed and swept blade /
- numerical simulation /
- range of steady operation condition /
- aerodynamic design

HTML

参考文献(14)

[1]	Wellborn S R,Robert A D.Redesign of a 12-stage axial-flow compressor using multistage CFD .ASME Paper GT-2001-0351,2001.
[2]	Gümmer V,Wenger U,Kau H P.Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressor[J].Journal of Turbomachinery,2001,123(1):40-48.
[3]	Gallimore S J,Bolger J J,Cumpsty N A,et al.The use of sweep and dihedral in multistage axial flow compressor blading Part 1:university research and methods development .ASME Paper GT-2002-30328,2002.
[4]	Gallimore S J,Bolger J J,Cumpsty N A,et al.The use of sweep and dihedral in multistage axial flow compressor blading Part 2:low and high speed designs and test verification .ASME Paper GT-2002-30329,2002.
[5]	Brilliant L,Balamucki S,Burger G,et al.Application of multistage CFD analysis to low pressure compressor design .ASME Paper GT-2004-54263,2004.
[6]	Tubbs H,Rea A.Aerodynamic development of the high pressure compressor for the IAEV 2500 aero engine .ImechEC423ö023,1991.
[7]	Yamaguchi N,Tominaga T,Hattori S,et al.Secondary-loss reduction by forward-skewing of axial compressor rotor blading //Proceedings of 1991 Yokohama International Gas Turbine Congress.Yokohama:IGTC,1991:61-68.
[8]	Gümmer V,Wenger U,Kau H P.Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressors .ASME Paper 2000-GT-0491,2000.
[9]	李绍斌,苏杰先,王仲奇.采用高负荷弯曲静叶的压气机改型研究[J].航空动力学报,2006,21(4):741-746. LI Shaobin,SUN Jiexian,WANG Zhongqi.Redesign of a transonic compressor stage using highly loaded bowed stator[J].Journal of Aerospace Power,2006,21(4):741-746.(in Chinese)
[10]	Braun M,Reume J R.Forward sweep in a four-stage high-speed axial compressor .ASME Paper GT-2006-90218,2006.
[11]	李绍斌.跨音速压气机高负荷弯、扭静叶设计及其气动性能研究 .哈尔滨:哈尔滨工业大学,2007. LI Shaobin.Design of highly loaded dihedral stator and investigation on the aerodynamic stage performance in an axial transonic compressor .Harbin:Harbin Institute of Technology,2007.(in Chinese)
[12]	姜斌,王松涛,冯国泰,等.高负荷低压风扇三维气动设计与损失分析[J].航空动力学报,2010,25(2):424-433. JIANG Bin,WANG Songtao,FENG Guotai,et al.Research on three-dimensional aerodynamic design of transonic fan and loss analysis[J].Journal of Aerospace Power,2010,25(2):424-433.(in Chinese)
[13]	Reid L,Moore R D.Performance of single stage axial flow transonic compressor with rotor and stator aspect ratios of 1119 and 1126,respectively,and with design pressure .NASA2TP21337,1978.
[14]	Reid L,Moore R D.Performance of single stage axial flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26,respectively,and with design pressure ratio of 1.82 .NASA2TP21338,1978.