An aerodynamic design and numerical investigation of transonic centrifugal compressor stage  

作　　者：Weilin Yi Lucheng Ji Yong Tian Weiwei Shao Weiwei Li Yunhan Xiao 

机构地区：[1]School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China [2]Research Center thr Energy and Power, Chinese Academy of Sciences, Beijing 100190, China

出　　处：《Journal of Thermal Science》2011年第3期211-217,共7页热科学学报（英文版）

摘　　要：In the present paper,the design of a transonic centrifugal compressor stage with the inlet relative Mach number about 1.3 and detailed flow field investigation by three-dimensional CFD are described.Firstly the CFD program was validated by an experimental case.Then the preliminary aerodynamic design of stage completed through in-house one-dimensional code.Three types of impellers and two sets of stages were computed and analyzed.It can be found that the swept shape of leading edge has prominent influence on the performance and can enlarge the flow range.Similarly,the performance of the stage with swept impeller is better than others.The total pressure ratio and adiabatic efficiency of final geometry achieve 7:1 and 80% respectively.The vane diffuser with same airfoils along span increases attack angle at higher span,and the local flow structure and performance is deteriorated.

关 键 词：IMPELLER DIFFUSER CFD Aerodynamic Design 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] U469.11[机械工程—车辆工程]