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Aerodynamic Design and Analysis of a Low-reaction Axial Compressor Stage
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, asingle-stage, low-reaction and low-speed axial compressor is constructed in association with analysis and computation of boundary layersuction 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.
作 者： Qiang Xiaoqing Wang Songtao Feng Guotai Wang Zhongqi 作者單位： School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China 刊 名： 中國航空學報（英文版） ISTIC 英文刊名： CHINESE JOURNAL OF AERONAUTICS 年，卷(期)： 2008 21(1) 分類號： V2 關鍵詞： aerospace propulsion system low-reaction axial compressor boundary layer suction energy loss【Aerodynamic Design and Analysis of a】相關文章：
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