某带分流叶片的亚声速离心压气机叶轮CFD结果确认及分析

李培元; 顾春伟

某带分流叶片的亚声速离心压气机叶轮CFD结果确认及分析

清华大学热能工程系热科学与动力工程教育部重点实验室, 北京 100084

基金项目: 国家自然科学重点基金(51136003)

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出版历程
- 收稿日期: 2012-10-29
- 刊出日期: 2013-11-28

CFD result validation and analysis of a subsonic centrifugal compressor impeller with splitter blades

Key laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering, Tsinghua University, Beijing 100084, China

摘要

摘要: 为了研究数值模拟结果的准确性,使用计算流体动力学(CFD)软件Numeca,采用Spalart-Allmaras(S-A)模型和shear stress transport(SST)模型对某压比为1.5的亚声速离心压气机叶轮的性能进行了计算,并将4个不同截面上的速度分布等计算结果和实验数据进行了对比.结果表明:S-A模型和SST模型的计算结果几乎完全相同,误差小于1%;整体性能的模拟计算结果和实验值吻合较好,在设计工况点,误差在2%以内,在非设计工况点,误差也小于6%;不同截面上速度分布的计算结果和实验值相差较大,在轮毂附近,最大误差在20%左右,在轮缘附近,部分截面最大误差高于100%,不能真实反映轮缘附近的流动情况.
- 数值模拟 /
- 离心压气机叶轮 /
- 湍流模型 /
- 速度分布 /
- 低能区
Abstract: A subsonic centrifugal compressor impeller with splitter blades of 1.5 pressure ratio was analyzed by CFD software of Numeca using Spalart-Allmaras(S-A) and shear stress transport(SST) models to study the accuracy of numerical simulation results. The measured results of the impeller and verifications of CFD at four sections were presented with respect to the velocity distribution, etc. Results show that the simulation results of S-A and SST models are almost the same, with the difference less than 1%; In general, the numerical simulation agrees well with the experiment, the difference is less than 2% at design point and 6% in off-design condition. The difference of numerical simulation and experiment results of velocity distribution is large in different cross sections. There are relatively big differences about 20% near hub and more than 100% near shroud, which can not truly reflect the flow condition near the shroud.
- numerical simulation /
- centrifugal compressor impeller /
- turbulence model /
- velocity distribution /
- low energy region

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参考文献(16)

[1]	Dean R C,Senoo Y.Rotating wakes invaneless diffusers[J].Journal of Basic Engineering,1960,82(3):563-574.
[2]	Eckardt D.Instantaneous measurements in jet-wake discharge flow of a centrifugal compressor impeller[J].Journal of Engineering for Power,1975,97(3):337-346.
[3]	Eckardt D.Detailed flow investigations within a high-speed centrifugal-compressor impeller[J].Journal of Fluids Engineering,1976,98(3),390-402.
[4]	Eckardt D.Flow field analysis of radial and backswept centrifugal compressor impellers:Part 1 flow measurements using a laser velocimeter.New York:Performance Prediction of Centrifugal Pumps and Compressors,1979.
[5]	Krain H,Hoffmann B,Par H.Aerodynamics of a centrifugal compressor impeller with transonic inlet conditions.ASME Paper 95-GT-79,1995.
[6]	Krain H,Karpinski G,Beversdorff M.Flow analysis in a transonic centrifugal compressor rotor using 3-component laser velocimetry.ASME Paper 2001-GT-0315,2001.
[7]	Krain H,Richter F,Teide V.Investigations of the flow through a high pressure ratio centrifugal impeller.ASME Paper GT2002-30394,2002
[8]	Hirotaka H,Kiyoshi H,Kunio S,et al.Detailed flow study of Mach number 1.6 high transonic flow with a shock wave in a pressure ratio 11 centrifugal compressor impeller.ASME Paper GT 2004-53435,2004.
[9]	Hirotaka H,Susumu M, Masayuki S,et al.Detailed flow study of Mach number 1.6 high transonic flow in a pressure ratio 11 centrifugal compressor impeller:Part 2 effect of inducer shroud bleed and development of a low energy region along the shroud.ASME Paper GT2007-27694,2007.
[10]	Shabbir A,Zhu J,Celestina M.Assessment of three turbulence models in a compressor rotor.ASME Paper 96-GT-198,1996.
[11]	Roberts D A,Steed R.Comparison of steady-state centrifugal stage CFD analysis to experimental rig data.Pittsburgh,US:ANSYS User's Conference,2004.
[12]	Denton J D,Dawes W N.Computational fluid dynamics for turbomachinery design[J].Journal of Mechanical Engineering Science,1998,213(2):107-124.
[13]	Mangani L,Mauri S.Assessment of various turbulence models in a high pressure ratio centrifugal compressor with an object oriented CFD code[J].Journal of Turbomachinery,2012,134(6):061033.1-061033.10.
[14]	Bourgeois J,Martinuzzi R,Savory E.Assessment of turbulence model predictions for an aero-engine centrifugal compressor[J].Journal of Turbomachinery,2012,133(1):011025.1-011025.15.
[15]	GU Chunwei.The investigation of unsteady flow character in centrifugal compressor.Tokyo:Tokyo University,1999.
[16]	Yamada K,Tamagawa Y,Fukushima H.Comparative study on tip clearance flow fields in two types of transonic centrifugal compressor impeller with splitter blades.ASME Paper GT2010-23345,2010.