Accession Number : ADP006212
Title : Investigation of Dihedral Effects in Compressor Cascades,
Corporate Author : VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)
Personal Author(s) : Breugelmans, F. A.
Report Date : SEP 1987
Pagination or Media Count : 14
Abstract : An experimental investigation of the influence of blade dihedral on the secondary flow in a two dimensional NASA 65-series compressor cascade is performed. Different inlet boundary layer thicknesses are used on the endwalls. Three different stacking lines have been chosen, namely a straight line inclined at 15, 25 and 35, a circular arc and an elliptic arc. The incidence range up to stall has been investigated and the local beneficial effect on overall and secondary flow loss. Some limitations have to be accepted, depending on boundary layer thickness and incidence.
Descriptors : *COMPRESSOR BLADES, CASCADES(FLUID DYNAMICS), BOUNDARY LAYER, DIHEDRAL ANGLE, SECONDARY FLOW, BOUNDARY LAYER, CASCADE STRUCTURES, COMPRESSORS, INLETS, LOSSES, RANGE(EXTREMES), SECONDARY FLOW, THICKNESS.
Subject Categories : Helicopters
Distribution Statement : APPROVED FOR PUBLIC RELEASE