Accession Number : ADB059618
Title : Investigation of a High-Through-Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased 0.020 Inch (Configuration 3).
Descriptive Note : Interim rept. 1 Mar 76-1 Jul 77,
Corporate Author : AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH
Personal Author(s) : Law,C. Herbert ; DeRose,Robert D. ; Gurecki,Daniel J. ; Strain,Efren C.
Report Date : APR 1981
Pagination or Media Count : 109
Abstract : Complete experimental results are presented from tests of an axial compressor. 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, *Axial flow compressor blades, *Gas turbines, *Aircraft engines, Axial flow turbine rotors, Configurations, Performance(Engineering), Gas flow, Flow rate, Pressure, Velocity, Clearances, Base lines, Modification, Parametric analysis
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE