Accession Number : ADB059689

Title :   Investigation of a High-Through-Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased 0.020 Inch and Casing Vortex Generator Configuration A (Configuration 3A).

Descriptive Note : Interim technical 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 : 95

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 pounds per second per square feet, a total pressure ratio of 1.912 and a tip speed of 1500 feet per second. 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, Modification, Aircraft engines, Compressor blades, Clearances, Gas flow, Flow rate, Computer aided design, Test methods, Test vehicles, Test facilities, Graphs, Tables(Data), Experimental data

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE