遷音速ファンの高負荷曲げ翼列フラッタに関する実験的研究

概要

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The aerodynamic damping characteristics of a transonic fan are experimentally investigated using a linear cascade wind tunnel. The cascade consists of 7 blades with its center blade oscillated in bending mode by mechanical system. Unsteady aerodynamic forces are measured at supersonic inlet and high back pressure conditions, which cover from started to unstarted flow regimes. Unsteady aerodynamic works per cycle in traveling-wave mode are estimated by means of the influence coefficient method. It is revealed that an increase in vibration frequency has a stabilizing effect, while an increase in pressure ratio has a destabilizing effect on blade oscillations. An increase in the inlet Mach number has a destabilizing effect at low supersonic inlet Mach numbers, but a further increase in the inlet Mach number causes a strong shock-boundary-layer interaction and reduces the maxi-mum of aerodynamic exciting forces.
社団法人日本ガスタービン学会の論文
1997-12-10