Accession Number : ADB059621
Title : Investigation of a High-Through-Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased 0.010 Inch (Configuration 2).
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 : 100
Abstract : This report presents the results of an experimental evaluation of the single-stage axial compressor with tip clearance increased 0.010 inch. This clearance increase was accomplished by grinding this amount off the tips of the rotor blades. The casing was untouched. The performance goals of this stage were based on a preliminary design study of a multi-stage compressor for an advanced turbojet engine. The results of the tests, reported herein, were achieved with one of a series of minor parametric modifications to the compressor stage. The parametric modifications considered consisted of three casing vortex generator configurations, three separate rotor tip running clearances, and one rotor tip vortex generator configuration. No casing or rotor tip vortex generators were used on the configuration reported herein.
Descriptors : *Axial flow compressors, *Axial flow compressor blades, *Turbojet engines, Gas flow, Pressure, Base lines, Modification, Clearances, Grinding, Performance(Engineering), Rotor blades, Vortex generators
Subject Categories : Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE