A comprehensive study of the three-dimensional turbulent boundary layer on a compressor rotor blade at peak pressure rise coefficient is reported in this paper. The measurements were carried out at various chordwise and radial locations on a compressor rotor blade using a rotating miniature V configuration hot-wire probe. The data are compared with the measurement at the design condition. Substantial changes in the blade boundary layer characteristics are observed, especially in the outer 16 percent of the blade span. The increased chordwise pressure gradient and the leakage flow at the peak pressure coefficient have a cumulative effect in increasing the boundary layer growth on the suction surface. The leakage flow has a beneficial effect on the pressure surface. The momentum and boundary layer thicknesses increase substantially from those at the design condition, especially near the outer radii of the suction surface.
Three-Dimensional Boundary Layer on a Compressor Rotor Blade at Peak Pressure Rise Coefficient
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Lakshminarayana, B., and Popovski, P. (January 1, 1987). "Three-Dimensional Boundary Layer on a Compressor Rotor Blade at Peak Pressure Rise Coefficient." ASME. J. Turbomach. January 1987; 109(1): 91–98. https://doi.org/10.1115/1.3262075
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