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

Report Date:

1981-04-01

Pagination or Media Count:

109.0

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 lbsecsq ft, a total pressure ratio of 1.912 and a tip speed of 1500 ftsec. 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

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE