基于CFD结果的轴流压气机附面层堵塞计算方法

doi:10.13675/j.cnki. tjjs. 180492

推进技术 ›› 2019, Vol. 40 ›› Issue (8): 1710-1719.DOI: 10.13675/j.cnki. tjjs. 180492

基于CFD结果的轴流压气机附面层堵塞计算方法

1.大连理工大学能源与动力学院;2.中国科学院工程热物理研究所，北京;100190

发布日期:2021-08-15
作者简介:杨金广，博士，副教授，研究领域为叶轮机械气动热力学。E-mail：jinguang_yang@dlut.edu.cn
基金资助:
国家自然科学基金青年基金 51606026国家自然科学基金青年基金（51606026）。

A Computational Method of Boundary Layer Blockage inAxial Compressors Based on CFD Results

1.School of Energy and Power Engineering,Dalian University of Technology,Dalian 116024,China;2.Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China

Published:2021-08-15

摘要/Abstract

摘要： 为研究轴流压气机附面层堵塞计算方法，提出一种基于计算流体力学结果自动提取附面层厚度的多参数组合方法，该方法整合了多种附面层判断准则，可有效避免单参数判断准则的局限性。通过多个算例，包括二维平板、多级轴流压气机端壁、进口导流叶片以及带有分离区的静子叶片等，对该多参数判断准则进行了检验。结果表明，此附面层提取方法具有很好的有效性和普适性。该研究建立了多级轴流压气机中端壁堵塞从高维向低维模型的反馈，为压气机设计体系改进提供了更多可能。

关键词: 轴流压气机;附面层堵塞;位移厚度;多参数判断准则

Abstract: In order to calculate boundary layer blockage of axial flow compressor, a novel hybrid method is proposed to automatically extract the boundary layer thickness based on results of computational fluid dynamics. It integrates different boundary layer identification criteria, and can effectively avoid limitations of each single parameter criterion. The hybrid criterion was tested by extracting boundary layer in several cases, including a two-dimensional flat plate, endwall of multi-stage axial compressors, and blade surfaces of an inlet guide vane and a stator with separation. Results demonstrate a good accuracy and universality of the hybrid method. In addition, the procedure established in this paper can transfer information of the endwall blockage from 3D results to reduced order models in multi-stage compressors, and provide more possibility for further improvements of current aerodynamic design system.

Key words: Axial compressor;Boundary-layer blockage;Displacement thickness;Hybrid criteria

. 基于CFD结果的轴流压气机附面层堵塞计算方法[J]. 推进技术, 2019, 40(8): 1710-1719.

参考文献

[1] McDougall N M, Cumpsty N A， Hynes T P. Stall Inception in Axial Compressors[J]. Journal of Turbomachinery， 1990， 112(1): 116-123.
[2] Wheeler A P， Miller R J， Hodson H P. The Effect of Wake Induced Structures on Compressor Boundary-Layers[J]. Journal of Turbomachinery， 2007， 129(4): 705-712.
[3] Mellor G L， Wood G M. An Axial Compressor End-Wall Boundary Layer Theory[J]. Journal of Basic Engineering， 1971， 93(2): 300-314.
[4] Hunter I H， Cumpsty N A. Casing Wall Boundary-Layer Development Through an Isolated Compressor Rotor[J]. Journal of Engineering for Power， 1982， 104(4): 805-817.
[5] Rastogi A K， Rodi W. Calculation of General Three-Dimensional Turbulent Boundary Layers[J]. AIAA Journal， 1978， 16(2): 151-159.
[6] Zheng X， Yang H. End-Wall Boundary Layers and Blockages of Multistage Axial Compressors under Different Conditions[J]. Journal of Propulsion & Power， 2016， 33(4): 1-9.
[7] Li Zhi-hui， Zheng Xin-qian， Liu Yan-ming， et al. The Effect of End Wall Boundary Layer on Matching and Corresponding Flow Control Technique for Multistage Axial Compressor[J]. Proceedings of the Institution of Mechanical Engineers， Part G: Journal of Aerospace Engineering， 2016， 230(12): 2179-2194.
[8] 陈绍文，孙士珺，兰云鹤，等. 来流附面层对吸附式压气机叶栅影响的数值研究[J]. 机械工程学报， 2014， 50(24): 158-163.
[9] Berdanier R A， Key N L. Quantifying Blockage in a Multistage Compressor for Different Tip Clearances Using Steady and Unsteady Pressure Measurements[C]. Boston: 54th AIAA Aerospace Sciences Meeting， 2016.
[10] Suder K L. Blockage Development in a Transonic Axial Compressor Rotor[R]. ASME 1997-GT-394.
[11] Khalid S A， Khalsa A S， Waitz I A， et al. Endwall Blockage in Axial Compressors[J]. Journal of Turbomachinery， 1999， 121(3): 499-509.
[12] Haimes R， Kenwright D. On the Velocity Gradient Tensor and Fluid Feature Extraction[C]. San Diego： 14th Computational Fluid Dynamics Conference， 1999.
[13] Kulkarni S. Development of a Methodology to Estimate Aero-Performance and Aero-Operability Limits of a Multistage Axial Flow Compressor for Use in Preliminary Design[D]. USA: Case Western Reserve University， 2012.
[14] Alfredsson P H， Segalini A， ?rlü R. A New Scaling for the Streamwise Turbulence Intensity in Wall-Bounded Turbulent Flows and What It Tells Us about the “Outer” Peak[J]. Physics of Fluids， 2011， 23(4).
[15] Cliquet J， Houdeville R， Arnal D. Application of Laminar-Turbulent Transition Criteria in Navier-Stokes Computations[J]. AIAA Journal， 2008， 46(5): 1182-1190.
[16] 杨金广，吴虎. 改进的Baldwin-Lomax湍流模型及其在叶轮机械中的应用[J]. 工程热物理学报， 2014， 35(3): 451-455.
[17] Drela M. Two-Dimensional Transonic Aerodynamic Design and Analysis Using the Euler Equation[D]. Massachusetts： Massachusetts Institute of Technology， 1985.
[18] Lejon M， Gr?nstedt T， Glodic N， et al. Multidisciplinary Design of a Three Stage High Speed Booster[R]. ASME 2017-GT-64466.
[19] Lakshminarayana B， Suryavamshl N， Prato J， et al. Experimental Investigation of the Flow Field in a Multistage Axial Flow Compressor[R]. ASME 1994-GT-455.

基于CFD结果的轴流压气机附面层堵塞计算方法

A Computational Method of Boundary Layer Blockage inAxial Compressors Based on CFD Results

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