Abstract
This paper details experimental studies on the flow field around a low-pressure linear turbine cascade. Highly loaded low-pressure turbine (LPT) blades are one of the key paths to successful future aero-engines, however those blades are usually accompanied with separation bubble, especially at cruise condition, eventually leading to the increase in aerodynamic loss. The purpose of this study is to clarify the effect of incoming wakes upon the aerodynamic loss of the rotor blade cascade, through the measurements of wake-affected boundary layers upon including separation bubble for low Reynolds number conditions. Two types of 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 incoming wakes affect the boundary layers containing separation bubble. This paper focuses on difference of bar diameter in the characteristics of the wake affected separated boundary layer.
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