A three-dimensional inverse method based on moving no-slip boundary for profiled end wall design  

作　　者：Hanwen GUO Donghai JIN Jiancheng ZHANG Xingmin GUI 

机构地区：[1]School of Energy and Power Engineering,Beihang University,Beijing 100191,China [2]Jiangxi Research Institute of Beihang University,Nanchang 330096,China

出　　处：《Chinese Journal of Aeronautics》2024年第10期221-233,共13页中国航空学报（英文版）

基　　金：Supported by the National Natural Science Foundation of China(No.52376021).

摘　　要：How to utilize existing flow control mechanisms to make profiled end wall design more flexible,efficient,and physical is a meaningful challenge.This study presents a three-dimensional inverse method for profiled end wall design to achieve the application of flow control mechanisms.The predetermined pressure distribution on the end wall is reached by modifying the end wall geometry during flow field calculation.A motion velocity model is derived from the normal momentum equation of the moving no-slip boundary to modify the end wall geometry.A Reynolds-Averaged Navier-Stokes(RANS)solver based on the Semi-Implicit Method for Pressure Linked Equations(SIMPLE)algorithm is adopted to simulate the flow field.Based on the mechanism understanding obtained through numerical optimization results,this study adopts the inverse method to redesign an optimized end wall in a compressor cascade.The results indicate that the redesigned end wall exhibits better loss reduction,reducing the overall total pressure loss by 5.5%,whereas the optimized end wall reduces it by 3%.The inverse method allows the imposition of desired influences on the end wall flow without constructing a database,making it highly flexible,efficient,and physical.

关 键 词：COMPRESSOR Flow control Corner separation Profiled end wall Inverse method 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]