A-2 航空エンジン用低圧タービンの翼面境界層バイパス遷移に関する研究(空力,一般講演)

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This paper deals with experimental study on the flow field around a low-pressure turbine blade. The experiments were conducted in a linear cascade facility at Reynolds numbers between 1.3 and 2.1 × 10^5 with free stream turbulence intensities(FSTI) up to 6 percent. Hot-wire probe measurements were conducted over the airfoil suction surface to understand the transitional process of the boundary layer. At low FSTI, K-H (Kelvin-Helmholtz) instability plays an important role in the separated boundary layer transition. FFT(Fast Fourier transformation) analysis of these data reveals that this instability grows from the separation point. With high FSTI, the transition appears to occur in a bypass mode, similar to that in attached boundary layer. The streaky structures exist prior to transition onset in the boundary layer. The results of the present experiments show that the transition onset shifts more upstream as FSTI increases.
公益社団法人日本ガスタービン学会の論文
2010-10-20