Accession Number : ADP006217

Title :   Experimental Investigation of a Supercritical Compressor Rotor Blade Section,

Corporate Author : DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V COLOGNE (GERMANY F R)

Personal Author(s) : Fuchs, R. ; Kaymaz, R. ; Starken, H. ; Steinert, W.

Report Date : SEP 1987

Pagination or Media Count : 11

Abstract : A controlled diffusion rotor blade section was designed for a supercritical inlet Mach number of M1=0.85 and a flow turning of 20. The blade section has been tested in a cascade wind tunnel under various inlet flow conditions and axial velocity density ratios. Detailed investigation about transition and separation points were carried out at the design and at two off design inlet flow conditions. The results are presented and discussed.

Descriptors :   *AXIAL FLOW COMPRESSOR BLADES, *ROTOR BLADES(TURBOMACHINERY), CASCADES(FLUID DYNAMICS), INLETS, WIND TUNNELS, BOUNDARY LAYER, BLADES, DENSITY, FLOW, INLETS, MACH NUMBER, RATIOS, SUPERCRITICAL FLOW, VELOCITY, WIND TUNNELS.

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE