Accession Number : ADP005509
Title : Vortex Shedding in Compressor Blade Wakes,
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE GAS TURBINE LAB
Personal Author(s) : Epstein,A. H. ; Gertz,J. B. ; Owen,P. R. ; Giles,M. B.
Report Date : MAR 1987
Pagination or Media Count : 13
Abstract : The wakes of highly loaded axial compressor blades have often been considered to be turbulent, unstructured flows. Recent work has suggested that the blade wakes are in fact dominated by a vortex street-like structure. This paper reviews the work on wake structure at MIT, presents the results of a viscous numerical simulation, compares of the wake structure on compressor performance. In particular, a two-dimensional, time accurate, viscous calculation shows both a periodic wake structure and time variations in the passage shock strength. The numerical calculations are compared to laser anemometer and high frequency response probe data. The effect of the wake structure on the entropy production and apparent adiabatic efficiency of the compressor rotor is discussed.
Descriptors : *AXIAL FLOW COMPRESSOR BLADES, *VORTEX SHEDDING, *WAKE, TURBULENT FLOW, LASER ANEMOMETERS, SHOCK WAVES, VISCOUS FLOW, ADIABATIC CONDITIONS
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE