Numerical Study on the Influence Mechanism of Inlet Distortion on the Stall Margin in a Transonic Axial Rotor

作     者：Scott C.Morris 

作者机构：Hessert LaboratoryDepartment of Mechanical and Aerospace EngineeringUniversity of Notre Dame 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2012年第21卷第3期

页      面：209-214页

核心收录：

学科分类：080704[工学-流体机械及工程] 08[工学] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 0702[理学-物理学] 

基　　金：supported by National Natural Science Foundation of China with project No.51010007 and No.51106153 

主　　题：Inlet distortion tip leakage flow stall margin axial momentum balance 

摘      要：A numerical study is conducted to investigate the influence of inlet flow condition on tip leakage flow (TLF) and stall margin in a transonic axial rotor.A commercial software package FLUENT,is used in the *** rotor investigated in this paper is ND_TAC rotor,which is the rotor of one-stage transonic compressor in the University of Notre *** varied inlet flow conditions are *** inlet boundary condition with hub distortion provides higher axial velocity for the incoming flow near tip region than that for the clean inflow,while the incoming main flow possesses lower axial velocity near the tip region at tip distortion inlet boundary *** the total pressure ratio curves for the three inlet flow conditions,it is found that the hub dis-torted inlet boundary condition improves the stall margin,while the tip distorted inlet boundary condition dete-riorates compressor *** axial location of interface between tip leakage flow (TLF) and incoming main flow (MF) in the tip gap and the axial momentum ratio of TLF to MF are further *** is demonstrated that the axial momentum balance is the mechanism for interface *** hub distorted inflow could de-crease the axial momentum ratio,suppress the movement of the interface between TLF and MF towards blade leading edge plane and thus enhance compressor stability.