Parameter study on numerical simulation of corner separation in LMFA-NACA65 linear compressor cascade  

作　　者：Gao Feng Ma Wei Sun Jinjing Jérome Boudet Xavier Ottavy Liu Yangwei Lu Lipeng Shao Liang 

机构地区：[1]National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beihang University, Beijing 100191, China [2]Department of Mechanical Engineering Sciences, University of Surrey, Guildford GU2 7XH, UK [3]School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China [4]Laboratoire de Mecanique des Fluides et d'Acoustique, Ecole Centrale de Lyon, Ecully 69134, France

出　　处：《Chinese Journal of Aeronautics》2017年第1期15-30,共16页中国航空学报（英文版）

基　　金：funded by the Sino-French project AXIOOM (funding: NSFC and ANR);the supports from NSFC (Nos. 51420105008, 51376001, 51506121 and 51676007);performed using HPC resources from GENCICINES (No.2014-2a6081)

摘　　要：Large-eddy simulation（LES） is compared with experiment and Reynolds-averaged Navier-Stokes（RANS）, and LES is shown to be superior to RANS in reproducing corner separation in the LMFA-NACA65 linear compressor cascade, in terms of surface limiting streamlines,blade pressure coefficient, total pressure losses and blade suction side boundary layer profiles. However, LES is too expensive to conduct an influencing parameter study of the corner separation.RANS approach, despite over-predicting the corner separation, gives reasonable descriptions of the corner separated flow, and is thus selected to conduct a parametric study in this paper. Two kinds of influencing parameters on corner separation, numerical and physical parameters, are analyzed and discussed： second order spatial scheme is necessary for a RANS simulation; incidence angle and inflow boundary layer thickness are found to show the most significant influences on the corner separation among the parameters studied; unsteady RANS with the imposed inflow unsteadiness（inflow angle varying sinusoidally with fluctuating amplitude of 0.92°） does not show any non-linear effect on the corner separation.Large-eddy simulation（LES） is compared with experiment and Reynolds-averaged Navier-Stokes（RANS）, and LES is shown to be superior to RANS in reproducing corner separation in the LMFA-NACA65 linear compressor cascade, in terms of surface limiting streamlines,blade pressure coefficient, total pressure losses and blade suction side boundary layer profiles. However, LES is too expensive to conduct an influencing parameter study of the corner separation.RANS approach, despite over-predicting the corner separation, gives reasonable descriptions of the corner separated flow, and is thus selected to conduct a parametric study in this paper. Two kinds of influencing parameters on corner separation, numerical and physical parameters, are analyzed and discussed： second order spatial scheme is necessary for a RANS simulation; incidence angle and inflow boundary layer thickness are found to show the most significant influences on the corner separation among the parameters studied; unsteady RANS with the imposed inflow unsteadiness（inflow angle varying sinusoidally with fluctuating amplitude of 0.92°） does not show any non-linear effect on the corner separation.

关 键 词：Corner separation Influencing parameter LES Linear compressor cascade RANS 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]