Measurements were taken of the vortex system and turbulent flow that resulted from the interaction between a stator blade and the approaching endwall boundary layer in a linear cascade of compressor blades. Data were taken at a Reynolds number based on blade chord of 640,000. Five-hole pressure measurements were conducted upstream and downstream of the blade row. The approaching boundary layer was also characterized with the laser-Doppler velocimeter. Downstream three-component laser-Doppler velocimetry surveys were conducted at three streamwise stations to map the location and velocity characteristics of the wake and vortex system. Results clearly showed the extent of the vortex emanating from the separation of the boundary layer on the suction side of the blade. Finally, all components of mean flow velocity and turbulence are documented for the last survey station. These data will form a challenging test case for numerical code validation.
Three-Component LDV Measurements in the Wake of a Compressor Cascade With Flow Separation
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Hobson, G. V., Caruso, T. M., and Carlson, J. R. (January 14, 2008). "Three-Component LDV Measurements in the Wake of a Compressor Cascade With Flow Separation." ASME. J. Turbomach. January 2008; 130(1): 011008. https://doi.org/10.1115/1.2364883
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