1742 航空エンジン用低圧タービンの高負荷化に関する研究 : 後流通過時の剥離を伴う翼面境界層の非定常挙動(S33-4 タービン・その他,S33 流体機械の諸問題)

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This paper details with experimental studies on the flow field around a low-pressure linear turbine cascade whose solidity is changeable. Highly loaded low-pressure turbine (LPT) blades or ultra-high lift airfoils are one of the key paths to successful future aeroengines, however those blades are usually accompanied with separation bubble, eventually leading to the increase in aero-dynamic loss. The purpose of this study is to clarify the effect of incoming wakes upon the aerodynamic loss of the rotor blade cascade with solidity, through the investigation of wake-affected boundary layers upon including separation bubble for low Reynolds number conditions and/or low solidity conditions. Cylindrical bars on the timing belts work as wake generator to emulate upstream stator wakes that impact the rotor blade. Hot-wire probe measurement is conducted over the blade suction surface to understand to what extant and how the interaction of incoming wakes affect the boundary layers containing separation bubble.
社団法人日本機械学会の論文
2007-09-07