Abstract
Low-pressure turbines are a common element of many modern jet engines. Flow separation from the suction side of the constituent blades at low Reynolds number conditions can noticeably deteriorate overall engine performance. Two separation control strategies for an aggressive low-pressure turbine blade that was designed for an integrated o w control were investigated numerically using a hybrid turbulence modeling approach: Pulsed vortex generator jets are shown to result in an earlier transitioning of the o w and successful separation control. An even more ecien t separation control can be accomplished by harmonic blowing through a slot. The astounding eectiv eness of the latter control scheme is attributed to the suppression of three-dimensional structures. Instead, the o w is dominated by strong spanwise coherent structures that very eectiv ely reduce separation.
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