Patent ID: 9091174
Filing Date: 2015-07-28
Classification: F01D,F04D,F05D,Y02T,Y10T

Abstract:
1. A method of reducing the fluid flow effects of one or more obstacles in a passage of a gas turbine engine, the method comprising: providing a plurality of aerofoil structures in the passage upstream of the one or more obstacles, wherein the geometry of each aerofoil structure is substantially the same; shortening at least one trailing edge of one or more selected aerofoil structures in a chordwise direction and over at least a spanwise portion of the one or more selected aerofoil structures such that, when in use, the direction of the fluid flow in the vicinity of the one or more selected aerofoil structures is altered and the fluid flow effects of the one or obstacles in the passage are reduced; and arranging the aerofoil structures such that a setting angle of each aerofoil structure is approximately equal; and varying an amount that is shortened from each of the trailing edges such that at least one of the trailing edges is not shortened and is provided adjacent to at least one trailing edge that is shortened.