Numerical Investigation of a High-subsonic Axial-flow Compressor Rotor with Non-axisymmetric Hub Endwall  

作　　者：Shuzhen Hu Xingen Lu Hongwu Zhang Junqiang Zhu Qiang Xu 

机构地区：[1]Laboratory of Advanced Energy and Power Technology, lET, CAS, Beijing 100190, China [2]Graduate School, Chinese Academy of Sciences, Beijing 100190, China [3]Shanghai Electric Power Generation Equipment Co., Ltd

出　　处：《Journal of Thermal Science》2010年第1期14-20,共7页热科学学报（英文版）

基　　金：Financial supports for the work presented are provided by National Natural Science Foundation of China (Project No: 50806073);China Postdoctoral Science Foundation (Project No: 20070420068);K C Wong Education Foundation, these supports are greatly appreciated

摘　　要：The major source of loss in modem compressors is the secondary loss. Non-axisymmetric endwall profile contouring is now a well established design methodology in axial flow turbines. However, flow development in axial compressors is differ from turbines, the effects of non-axisymmetric endwall to axial compressors requires flow analysis in detail. This paper presents both experimental and numerical data to deal with the application of a non-axisymmetric hub endwall in a high-subsonic axial-flow compressor. The aims of the experiment here were to make sure the numerically obtained flow fields is the physical mechanism responsible for the improvement in efficiency, due to the non-axisymmetric hub endwall. The computational results were first compared with avail- able measured data of axisymmetric hub endwall. The results agreed well with the experimental data for estima- tion of the global performance. The coupled flow of the compressor rotor with non-axisymmetric hub endwall was simulated by a state-of-the-art multi-block flow solver. The non-axisymmetric hub endwall was designed for a subsonic compressor rotor with the help of sine and cosine functions. This type of non-axisymmetric hub end- wall was found to have a significant improvement in efficiency of 0.45% approximately and a slightly increase for the total pressure ratio. The fundamental mechanisms of non-axisymmetric hub endwall and their effects on the subsonic axial-flow compressor endwall flow field were analyzed in detail. It is concluded that the non-axisymmetric endwall profiling, though not optimum, can mitigate the secondary flow in the vicinity of the hub endwall, resulting in the improvement of aerodynamic performance of the compressor rotor.

关 键 词：axial-flow compressor non-axisymmetric hub endwali and numerical investigation 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] TH453[机械工程—机械制造及自动化]