Accession Number : ADB059620

Title :   Investigation of a High-Through Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased o.010 Inch and Casing Vortex Generator Configuration 'C' (Configuration 2C).

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 : 103

Abstract : Complete experimental results are presented from tests of an axial compressor with casing 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, *Axial flow compressor blades, *Gas turbines, *Aircraft engines, Axial flow turbine rotors, Vortex generators, Configurations, Performance(Engineering), Gas flow, Flow rate, Pressure, Velocity, Clearances

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE