Hotwire measurements of the turbulent flow into a cascade of controlled-diffusion compressor blades
Wakefield, Bryce Edwin.
Hobson, Garth V.
Shreeve, Raymond P.
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Turbulence measurements near the leading edge of a compressor stator were made in a subsonic cascade wind tunnel with a hotwire system. Using a single hot-film probe, velocity and turbulence distortion data were obtained about the leading edge of the Controlled-Diffusion (CD) blades in order to verify Laser Doppler Velocimetry (LDV) data taken in earlier studies. Measurements were conducted at a Mach number of .25, a Reynolds number of 711000 and an inlet flow angle of 48 degrees. Turbulence profiles obtained in the pitch-wise direction were found to be in good agreement with previous LDV measurements. These data indicated a localized increase in turbulence around the leading edge due to the interaction of the free-shear layer with the inlet turbulence. This free-shear layer extends over the separation bubble, which forms on the suction side of the blades' leading edge.
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