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The problem of flow separation from a low pressure turbine blade
was investigated. The operating conditions under which the
separation occurred were documented through measurement of surface
pressure coefficients, boundary layer velocity and turbulence
profiles, total pressure loss coefficient and wake velocity
momentum deficit. Three different means for reducing the losses
associated with the flow separation were also investigated. A
boundary layer trip, dimples, and V -grooves were studied as
passive means requiring no additional energy to reduce the
separation losses. The boundary layer trip was only successful for
an inlet and axial chord Reynolds number of 50k with a reduction in
loss coefficient of 58.2%. Three sets of dimples were tested with
the placement of each at axial chord locations of 50%, 55%, and
65%.
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