Patent ID: 6896485
Filing Date: 2005-05-24
Classification: C25D,F01D,F05D,Y02T

Abstract:
1. A combustion engine comprising a compressor, a combustor, and a turbine portion, said turbine portion having a rotor blade and a shroud facing a tip end of said rotor blade, wherein an abrasive layer having a matrix and many abrasive particles dispersed in said matrix is formed at tip end portion of said rotor blade, some of said abrasive particles are dispersed so as to protrude from said matrix and the remaining abrasive particles are dispersed so as to be embedded in said matrix, and the ratio (Np/Nb) of the number of particles protruding from said matrix (Np) to the number of particles embedded in said matrix (Nb) is not lower than 30/70 and not hither than 80/20.