Accession Number : ADP003089

Title :   Compressor Rotor Aerodynamics,

Corporate Author : UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT

Personal Author(s) : Dring,R. P. ; Joslyn,H. D. ; Wagner,J. H.

Report Date : SEP 1983

Pagination or Media Count : 16

Abstract : 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 radial/circumferential 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 fo these results for through-flow analyes are discussed.

Descriptors :   *Boundary layer, *Compressor rotors, Pressure measurement, Losses, Blocking, Flow fields, Compressor rotors, Pressure distribution, Downstream flow, Axial flow compressors, Aerodynamics, Data acquisition

Distribution Statement : APPROVED FOR PUBLIC RELEASE