Accession Number : ADB050857

Title :   Investigation of a High-Through-Flow, Single-Stage Axial-Flow Compressor with Casing Vortex Generator Configuration 'A' (Configuration 1A).

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) : Wennerstrom, Arthur J. ; Law, C. Herbert ; DeRose, Robert D. ; Gurecki, Daniel J. ; Strain, Efren C.

Report Date : JUN 1980

Pagination or Media Count : 104

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, *VORTEX GENERATORS, TURBOJET ENGINES, GAS TURBINES, TURBOJET INLETS, AXIAL FLOW COMPRESSOR BLADES, TRANSONIC FLOW, COMPRESSOR ROTORS, TABLES(DATA), COMPUTER PRINTOUTS.

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE