超音速軸流圧縮機翼形の超音速部について

概要

論文の詳細を見る
The supersonic cascade, in which a normal shock occurs and a flow is decelerated from supersonic to subsonic, is used in supersonic axial flow compressors. For cascades of this type, supersonic starting at the given inlet Mach number, high compression efficiency, larger deflection angles and thick blades enough not to be destroyed are required. Therefore it is considered to be hopeful that a blade section is divided into a supersonic part and a subsonic part, and the former gives most deflection angle to a flow and the latter gives little, consisting of straight surfaces. This report describes the method which dicides such a supersonic part of a blade section and the results of the analytical calculation about the obtainable deflection angles and compression efficiencies in the supersonic regions for the inlet Mach number from 1 to 2.
一般社団法人日本機械学会の論文
1962-11-25