Application of Tandem Cascade to Design of Fan Stator with Supersonic Inflow

作     者：Li Qiushi,Wu Hong,Zhou Sheng School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing 100191,China 

作者机构：School of Jet Propulsion Beijing University of Aeronautics and Astronautics Beijing 100191 China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2010年第23卷第1期

页      面：9-14页

核心收录：

学科分类：082502[工学-航空宇航推进理论与工程] 08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：National Natural Science Foundation of China(10577002) Innovation Foundation of BUAA for PhD Graduates 

主　　题：fan/compressor tandem cascade stator supersonic inflow 

摘      要：This article proposes a tandem cascade constructed to tackle the thorny problem of designing the high-loaded stator with a supersonic inflow and a large turning angle. The front cascade adopts a supersonic profile to reduce the shock wave intensity turning the flow into subsonic,while the rear cascade adopts a subsonic profile with a large camber offering the flow a large turning angle. It is disclosed that the losses would be minimized if the leading edge of the rear cas- cade lies close to the pressure side of the front cascade at a distance of 20% pitch in pitch-wise direction without either axial spacing or overlapping in axial direction. The 2D numerical test results show that,with the inflow Mach number of 1.25 and the turning angle of 52° ,the total pressure loss coefficient of the tandem cascade reaches 0. 106 ,and the diffusion factor 0. 745. Finally,this article has designed and simulated a high-loaded fan stage with the proposed tandem stator,which has the pressure ratio of 3.15 and the efficiency of 86.32% at the rotor tip speed of 495.32 m/s.