叶片掠对跨声转子进口流动的影响

昌皓; 朱芳; 金东海; 桂幸民

doi:10.13224/j.cnki.jasp.2016.04.012

叶片掠对跨声转子进口流动的影响

doi: 10.13224/j.cnki.jasp.2016.04.012

1. 北京航空航天大学能源与动力工程学院航空发动机数值仿真研究中心, 北京 100191;
2. 上海电气电站集团上海汽轮机有限公司, 上海 201199

基金项目:

国家自然科学基金(51006005,51236001)

详细信息

作者简介:
昌皓(1986-),男,吉林长春人,博士生,主要从事叶轮机械气体动力学方面的研究.

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2014-08-07
- 刊出日期: 2016-04-28

Effect of blade sweep on inlet flow in transonic compressor rotors

1. Aero-engine Simulation Research Center, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Shanghai Turbine Company Limited, Shanghai Electric Power Generation Group, Shanghai 201199, China

摘要

摘要: 选择NASA Rotor 37跨声转子作为原型叶片,在叶片90%展高以上通过移动叶型基元的弦向位置构造叶尖掠特征,共有包括原型转子、2个前掠转子和2个后掠转子等5种不同叶型几何的算例.利用数值模拟软件计算得到5种转子的总体特性并获得三维流场.结果表明:叶尖前掠减小了叶片尖部进口的平均攻角,而后掠则使攻角增大.引入周向平均无黏动量方程,计算出由周向平均所产生的周向不均匀源项及径向平衡方程的各项数值,并对比其在5个转子进口的分布规律及其与攻角变化之间的关联.通过改变进口的流动平衡,叶尖前掠使轴向速度增大、周向速度减小,进而使得攻角减小;后掠则在叶尖起到了相反的效应.采用这种准三维方法研究了叶片掠对叶片进口流场的影响.
- 掠 /
- 周向不均匀 /
- 径向平衡 /
- 跨声转子 /
- 攻角变化 /
- 准三维
Abstract: NASA Rotor 37 was selected as a baseline blade. Sweep features at tip regions were formed by moving the airfoil sections above the 90% span along the chordwise direction. There were five cases including the baseline rotor, two forward rotor and backward sweep rotors in total. A numerical simulation softwave was used to simulate the five rotors and obtain the overall characteristics and three-dimensional (3-D) flow fields. The results indicated that the tip forward sweep resulted in a decrease of inlet averaged incidence, while the backward sweep caused the reverse consequence. A circumferentially averaged method was introduced to provide the circumferential fluctuation terms as well as values in the inviscid momentum equation. The distributions of the circumferential fluctuation terms in the radial inviscid momentum equation at the blade inlet were calculated for comparison between the five cases, and were analysed for incidence variation. Forward sweep at tip regions resulted in the increase of axial velocity and reduction of circumferential velocity, further reducing the incidence due to the change of flow equilibrium at blade inlet, while backward sweep caused an inverse effect in the same region. The effect of blade sweep on flow fields at blade inlet was studied from the quasi-3-D perspective.
- sweep /
- circumferential fluctuation /
- radial equilibrium /
- transonic rotor /
- incidence variation /
- quasi-3-D

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参考文献(22)

[1]	Wennerstrom A J,Frost G R.Design of a 1500ft/sec,transonic,high-through-flow,single-stage axial-flow compressor with low hub/tip ratio[R].Air Force Aero Propulsion Laboratory AFAPL-TR-76-59,1976.
[2]	Wennerstrom A J,Derose R D,Law C W.Investigation of a 1500ft/sec,transonic,high-through-flow,single-stage axial-flow compressor with low hub/tip ratio[R].AFAPL-TR-76-92,1976.
[3]	Hah C,Wennerstrom A J.Three-dimensional flowfields inside a transonic compressor with swept blades[R].ASME Paper 90GT-359,1990.
[4]	Copenhaver W W,Hah C,Puterbaugh S L.Three-dimensional flow phenomena in a transonic,high-through-flow,axial-flow compressor stage[J].Journal of Turbomachinery,1993,115(2):240-248.
[5]	Puterbaugh S L,Copenhaver W W,Hah C,et al.A three-dimensional shock loss model applied to an aft-swept,transonic compressor rotor[J].Journal of Turbomachinery,1997,119(3):452-459.
[6]	Hah C,Puterbaugh S L,Wadia A R.Control of shock structure and secondary flow field inside transonic compressor rotors through aerodynamic sweep[R].ASME Paper 98-GT-561,1998.
[7]	Wadia A R,Szucs P N,Crall D W.Inner workings of aerodynamic sweep[J].Journal of Turbomachinery,1998,120(4):671-682.
[8]	Wadia A R,Szucs P N,Crall D W,et al.Forward swept rotor studies in multistage fans with inlet distortion[R].ASME Paper GT-2002-30326,2002.
[9]	Denton J D,Xu L.The effects of lean and sweep on transonic fan performance[R].ASME Paper GT-2002-30327,2002.
[10]	Denton J D,Xu L.The exploitation of three-dimensional flow in turbomachinery design[J].Journal of Mechanical Engineering Science,1998,213(2):125-137.
[11]	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.
[12]	McNulty G S,Decker J J,Beacher B F,et al.The impact of forward swept rotors on tip clearance flows in subsonic axial compressors[J].Journal of Turbomachinery,2004,126(4):445-454.
[13]	Gallimore S J,Bolger J J,Cumpsty N A,et al.The use of sweep and dihedral in multistage axial flow compressor blading:Part Ⅰ university research and methods development[J].Journal of Turbomachinery,2002,124(4):521-532.
[14]	Ramakrishna P V,Govardhan M.Numerical study of the stagger angle effects in forward swept axial compressor rotor passages[R].ASME Paper GT2010-23160,2010.
[15]	Vad J,Kwedikha A A,Horváth C,et al.Aerodynamic effects of forward blade skew in axial flow rotors of controlled vortex design[J].Journal of Power and Energy,2007,221(7):1011-1023.
[16]	JIN Hailiang,JIN Donghai,ZHU Fang,et al.Design of a highly loaded transonic two-stage fan using swept and bowed blading[R].ASME Paper GT2011-45988,2011.
[17]	ZHU Fang,JIN Donghai,GUI Xingmin.Corner flow control in high through-flow axial commercial fan/booster using blade 3-D optimization[J].Journal of Thermal Science,2012,21(1):32-41.
[18]	GUI Xingmin,ZHU Fang,WAN Ke,et al.Effects of inlet circumferential fluctuation on the sweep aerodynamic performance of axial fans/compressors[J].Journal of Thermal Science,2013,22(5):383-394.
[19]	Reid L,Moore R.Design and overall performance of four highly-loaded,high-speed inlet stages for an advanced high-pressure-ratio core compressor[R].NASA TP 1337,1978.
[20]	Moore R D,Reid L.Performance of single-stage axial flow transonic compressor with rotor and stator aspect-ratios of 1.19 and 1.26 respectively,and with a design pressure ratio of 2.05[R].NASA TP 1659,1980.
[21]	姜斌,郑群,王松涛,等.跨声速风扇的弯、掠三维设计研究[J].航空动力学报,2012,27(8):1815-1825. JIANG Bin,ZHENG Qun,WANG Songtao,et al.Research on three-dimensional design of bowed and swept blade of transonic fan[J].Journal of Aerospace Power,2012,27(8):1815-1825.(in Chinese)
[22]	胡加国,王如根,李少伟,等.跨声速轴流压气机径向涡现象与失稳机理[J].航空动力学报,2014,29(9):2239-2246. HU Jiaguo,WANG Rugen,LI Shaowei,et al.Radial vortex phenomenon and instability mechanism of transonic axial-flow compressor[J].Journal of Aerospace Power,2014,29(9):2239-2246.(in Chinese)