Three-dimensional laser-Doppler velocimetry measurements in the end-wall region of a linear cascade

Measurements were taken of the vortex system and turbulent flow that resulted from the interaction between a stator blade and the approaching end-wall boundary layer in a linear cascade of compressor blades. Data were taken at Reynolds numbers based on blade chord of 240000 and 711000. Total pressure measurements were conducted upstream and downstream of the blades row. The approaching boundary layer was characterized with the laser-Doppler velocimeter for the low Reynolds number test case, and with a single hotfilm probe for the high Reynolds number test case. Downstream three-component laser-Doppler velocimetry surveys were conducted to map the location and velocity characteristics of the downstream wake and vortex system. Results clearly showed the effect that the overall secondary now had on the location of the two oppositely rotating vortices. These vortices formed from the horse-shoe vortex, which emanated at the leading edge of the blades.