A-9 航空エンジン用超高負荷低圧タービン翼に関する研究(空力I,一般講演)

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This paper details experimental studies on the flow field around a low-pressure linear turbine cascade whose load-peark position is changeable. Highly loaded low-pressure turbine (LPT) blades or ultra-high lift airfoils are one of the key paths to successful future aero-engines, 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 performance of newly designed aft-loaded LPT blade(Aft-Loaded Model) and compare it to that of the conventional LPT blade(Base Model) through the measurements of wake-affected boundary layers upon including separation bubble for low Reynolds number 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 extent and how the interaction of incoming wakes affect the boundary layers containing separation bubble. In particular, from the viewpoint of providing database for blade designing, this paper focuses on differences of characteristics of the separated boundary layer influenced by the wake passing, making a comparison between the measurements for base and aft-loaded types of airfoils.
公益社団法人日本ガスタービン学会の論文
2008-10-01