Effect of Non-Axisymmetric End Wall on a Highly Loaded Compressor Cascade in Multi-Conditions  

作　　者：HUANG Song YANG Chengwu LI Ziliang HAN Ge ZHAO Shengfeng LU Xin’gen 

机构地区：[1]Key Laboratory of Light-duty Gas-turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China [2]University of Chinese Academy of Sciences,Beijing 100049,China

出　　处：《Journal of Thermal Science》2021年第4期1363-1375,共13页热科学学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(No.51606187 and No.51706223);the National Major Science and Technology Project of China(Grant No.2019-II-0004-0024)。

摘　　要：As an effective method to influence end wall flow field,non-axisymmetric profiled end wall can improve the aerodynamic performance of compressor cascades.For a highly loaded low pressure compressor cascade,called V103,the study found the optimal non-axisymmetric profiled end wall decreases total pressure loss coefficient by 4.57%,5.48%and 3.04%under incidences of–3°,0°,and 3°,respectively,compared with those of the planar end wall.The optimal non-axisymmetric profiled end wall changes the structure of secondary flow in hub region,generating a corner vortex near suction surface,inhibiting the development of the passage vortex towards suction surface and reducing flow separation.When the inlet Mach numbers are 0.62 and 0.72,the total pressure loss coefficient decreases by 3.19%and 4.58%for optimal non-axisymmetric profiled end wall compared with those of the planar end wall.Though optimal non-axisymmetric profiled end wall increases total pressure loss near hub region in blade passage under different inlet Mach numbers,the peak value and region of high loss coefficient above 10%span in blade passage significantly decrease.In addition,different incidences affect the secondary flow streamlines and vortex structure near the cascade hub region,however,different inlet Mach numbers hardly change the secondary flow streamlines and vortex structure.In short,the optimal non-axisymmetric profiled end wall shows better aerodynamic performance than the planar end wall for the highly loaded compressor cascade in multi-conditions.

关 键 词：non-axisymmetric profiled end wall total pressure loss highly loaded compressor cascade passage vortex 

分 类 号：TK14[动力工程及工程热物理—热能工程]