Patent ID: 9506348
Filing Date: 2016-11-29
CPC Classification: F01D,F05D,Y02T,Y10T

Claim Text:
1. A method for making a turbine aerofoil starting from a reference aerofoil, comprising the steps of: a) establishing five zones along a trailing edge of the turbine aerofoil with a zone 1 comprising 0-10% thereof, a zone 2 comprising 10-25% thereof, a zone 3 comprising 25-75% thereof, a zone 4 comprising 75-90% thereof, and a zone 5 comprising 90-100% thereof; b) locally reducing the metallic exit angle at the trailing edge with respect to the areas of zones 2 and 4 which correspond substantially, in use, to the position of the peaks of the secondary flows in the boundary layer; and c) increasing the metallic exit angle in the remaining areas of zones 1, 3 and 5 the trailing edge, with respect to that of the reference aerofoil, so as to substantially restore the same average value of the metallic exit angle of the reference aerofoil.