タービン翼面上のはく離を伴う流れ場における境界層バイパス遷移(境界層・せん断流・遷移(2),一般講演)

概要

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This paper presents experimental results on the bypass transition of the boundary layer on the low-pressure turbine blade with separation bubble, and examines the sensitivity of this transition process to freestream turbulence and Reynolds number. Hot-wire probe measurements were performed on a suction side of low-pressure linear turbine blades. The results from the present experiment show that the magnitude of the velocity fluctuation in the separated shear layer increase considerably, the velocity fluctuation downstream of the reattachment point are more dispersed and extend farther from the wall, and bypass transition occurs. The size of separation bubble becomes small as Reynolds number increase, but the location of turbulent transition removes upstream. Increase of Reynolds number has an inhibitive effect on separation, but doesn't lead the delay of turbulent transition.
日本流体力学会の論文
2008-09-04