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Theoretical Effect of Inlet Hub-tip-radius Ratio and Design Specific Mass Flow on Design Performance of Axial-flow Compressors

Chung-Hua WuZhonghua WuJohn T. SinnetteRobert E. Forrette

出版	National Advisory Committee for Aeronautics, 1950
URL	http://books.google.com.hk/books?id=J9fWSgAACAAJ&hl=&source=gbs_api

註釋Analysis indicated that design rotor speed and pressure ratio per stage decreased as specific mass flow increased for given inlet hub-tip radius ratio. Maximum pressure ratio per stage and rotor speed decreased as inlet hub-tip radius ratio decreased. Specific power input per stage was fairly constant over practical range of design specific mass flow and varied only slightly with inlet hub-tip radius ratio. When limited by an exit hub-tip radius ratio of 0.9, over-all pressure ratio, specific power input, and design specific mass flow increased with decreasing inlet hub-tip radius ratio over most of the range.