This paper presents results of an experimental aerodynamic study conducted in the rotating frame of reference downstream of an isolated compressor rotor with both thick and thin inlet endwall boundary layers. The paper focuses on those aspects of the data having particular significance to the assumptions and application of throughflow theory. These aspects include the spanwise distributions of static pressure and blockage, and the radial redistribution of fluid as it passes through the blade row. It is demonstrated that the main contributions to total pressure loss, blockage, and the distortion of the static pressure field were due to the hub corner stall and tip leakage. This is a significant departure from previous conclusions which looked to the endwall boundary layer and to secondary flow as major loss and blockage producing mechanisms.
Inlet Boundary Layer Effects in an Axial Compressor Rotor: Part II—Throughflow Effects
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Wagner, J. H., Dring, R. P., and Joslyn, H. D. (April 1, 1985). "Inlet Boundary Layer Effects in an Axial Compressor Rotor: Part II—Throughflow Effects." ASME. J. Eng. Gas Turbines Power. April 1985; 107(2): 381–386. https://doi.org/10.1115/1.3239735
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