Aerodynamic Design and Analysis of a Low-reaction Axial Compressor Stage

作     者：羌晓青 王松涛 冯国泰 王仲奇 

作者机构：哈尔滨工业大学能源科学与工程学院 

基　　金：National Defense Basic Research Program of China 

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

年 卷 期：2008年第21卷第1期

页      码：1-7页

摘      要：There is introduced a new low-reaction, highly-loaded axial compressor design concept which is coupled with boundary layer suction method. The characteristic features of the concept are made clear through its comparison with the MIT boundary layer suction compressor. Also are pointed out the potential applications of this concept as well as its key technological problems. Based on this concept, a single-stage, low-reaction and low-speed axial compressor is constructed in association with analysis and computation of boundary layer suction on vanes with the aid of a three-dimensional numerical approach. The results attest to the effectiveness of this way to control separation in blade cascades by the boundary layer suction and the feasibility of this proposed design concept.

主 题 词：aerospace propulsion system low-reaction axial compressor boundary layer suction energy loss 

学科分类：080704[080704] 08[工学] 0807[工学-电子信息类] 

核心收录：

D　O　I：10.1016/S1000-9361(08)60001-1

馆 藏 号：203892355...