Accession Number : ADB068098
Title : Investigation of a High-Through-Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased 0.020 Inch and Rotor Tip Vortex Generators, Configuration 3.1.
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 : SEP 1982
Pagination or Media Count : 119
Abstract : Complete experimental results are presented from tests of an axial compressor with rotor-mounted vortex generators. The design objectives were for a flow per unit frontal area of 39.7 1b/sec sq. ft., a total pressure ratio of 1.912 and a tip spread 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, Gas turbines, Aircraft engines, Rotors, Vortex generators, Modification, Parametric analysis, Configurations, Rotor blades
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE