Patent ID: 7207772
Filing Date: 2007-04-24
Classification: F01D,F04D,F05D,Y02T

Abstract:
1. An aircraft engine compressor having compressor blades attached to a compressor disk, which compressor blades, under operating conditions, are loaded by natural frequencies and by compression shocks on suction sides thereof at a certain distance from leading edges thereof, with a flow transition fixation mechanism being provided on the suction side of each compressor blade in a portion of the compressor blade located upstream of an area of action of the compression shocks essentially vertical to a boundary layer flow extending at a compressor blade surface which limits oscillation of a flow transition point between an initially laminar end subsequently turbulent boundary layer flow and, thus, oscillation of the compression shocks, and suppresses their reaction on first and second bending modes as well as on a first torsional mode of the compressor blade occurring under certain conditions of flight.