Accession Number : ADB068306
Title : Investigation of a High-through-Flow Single-Stage, Axial-Flow Compressor with Tip Clearance Increased 0.020 Inch, Rotor Tip Vortex Generators, and Casing Vortex Generators Configuration B, Configuration 3.1.B.
Descriptive Note : Interim technical rept. 1 Jul-30 Dec 77,
Corporate Author : AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH
Personal Author(s) : Wennerstrom,Arthur J. ; Law,C. Herbert ; DeRose,Robert D. ; Strain,Efren C.
Report Date : AUG 1982
Pagination or Media Count : 118
Abstract : Complete experimental results are presented from tests of an axial compressor combining both rotor-mounted and casing-mounted vortex generators. The design objectives were for a flow per unit frontal area of 39.7 lb/sec/sq.ft., a total pressure ratio of 1.912 and a tip speed of 1500 ft/sec. These experimental results were achieved with one of a series of minor parametric modifications to the baseline compressor stage. No conclusions concerning the effects of these modifications will be drawn until the complete series of tests has been reported. (Author)
Descriptors : *Axial flow compressors, *Vortex generators, *Gas turbines, *Turbojet engines, Modification, Base lines, Transonic flow, Configurations, Performance(Engineering), Computerized simulation
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE