Compressor Rotor Aerodynamics
UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT EAST HARTFORD United States
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Although numerical sophistication of multi-stage turbomachinery through-flow calculations has evolved to a very high level, the aerodynamic inputs of total pressure loss, deviation and blockage are subject to a high degree of empiricism. There is need for detailed flow field data in a multi-stage environment in order to bring some discipline to this important aspect of turbomachinery design. This paper presents a survey of some of the initial results of an in-depth investigation of the aerodynamics of the second stage of a large scale two-stage axial compressor. The second stage rotor data is compared with data obtained on an isolated rotor with very thin and then very thick inlet hub and tip boundary layers. The single and multi-stage rotor data presented include surface flow visualization and rotating frame radialcircumferential traverse measurements presented in the form of fullspan contour plots of rotary total pressure. Also presented are the spanwise distributions of loss, deviation and blockage. Some implications of these results for through-flow analyses are discussed.