Patent ID: 6305899
Filing Date: 2001-10-23
Classification: F01D,Y02T

Abstract:
A gas turbine engine including a casing enclosing a rotary stage of aerofoil blades, said casing comprising two axially adjacent annular cross-section casing portions, one of which is provided with a flange located at one of its axial extents for connection to a corresponding flange provided on the other casing portion, one of said flanges being of generally L-shaped cross-section in a circumferential direction so as to comprise radially outwardly and axially extending portions and the other being generally radially outwardly extending, said radially outwardly extending portions of said flanges axially abutting each other and said axially extending portion of said L-shaped flange locating adjacent and radially outwardly of the radial extent of said other flange, said radially outwardly extending axially abutting flange portions being positioned radially outwardly of and in radial alignment with said rotary stage of aerofoil blades, said one of said flanges being formed so that the rigidity of its said annular casing portion matches the rigidity of the other of said two axially adjacent annular cross-section portions.