曲げ振動する遷音速圧縮機環状翼列に作用する非定常空気力の測定(第2報)

概要

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For clarification of unstalled supersonic ben-ding mode cascade flutter, aerodynamic damp-ing forces acting on an oscillating blade of a supersonic annular compressor cascade have been investigated in both aerodynamic stable and unstable domains, using an annular cascade test facility. In the facility, whole blades composing the cascade were controlled-oscil-lated in the bending mode by a developed high speed mechanical drive system. In the experiment, the reduced frequency K based on a half chord was changed from 0.037 to 0.190 with a range of inlet Mach No. Ml from 0.829 to 1.06,and at a constant inter-blade phase angle. Through the force data, the occur-rence of unstalled supersonic bending mode compressor cascade flutter was made clear in low back-pressure conditions as well as the significance of K and M1 for flutter. The effect of shock wave movement due to blade oscilla-tion on flutter occurrence was also clarified in the experiment.
社団法人日本ガスタービン学会の論文
1991-12-10