B-21 失速域近傍流れにおける振動翼列非定常特性の数値解析(構造・空力・翼振動,一般講演)

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Unsteady aerodynamic characteristics of an oscillating compressor cascade, 5^<th> Standard Configuration, were numerically studied under subsonic and near-stall conditions. The flow separated from the leading edge and reattached at 15 percent chord position. The cascade was oscillated in a pitching mode about mid-chord with fixed inter-blade phase angle of π. Aerodynamic work on the blade was calculated for seven reduced frequencies ranging from 0.04 to 1.28. The computation was conducted with a two-dimensional in-house Navier-Stokes code. It was indicated that aerodynamic work mainly depends on the unsteady pressure phase on the narrow area of surface where the separation bubble was located. A large phase jump was found to exist within the area, which corresponded to the boundary between positive dumping and negative dumping parts. The correlation between flutter stability and microscopic unsteady flow field around the separation bubble was discussed based on the numerical results.
公益社団法人日本ガスタービン学会の論文
2009-10-21