Shrouded turbine blades with locally increased contact faces

Details Shrouded turbine blades with locally increased contact faces Shrouded turbine blades with locally increased contact faces

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/22 (2006.01)

Patent

CA 2525003

A one-piece blade for a turbine section of a gas turbine engine, the blade comprising a root, an airfoil and a shroud. The shroud extends generally perpendicularly from a tip of the airfoil and is defined by a pair of opposed bearing faces and a pair of opposed non-bearing faces. The bearing faces each have a contact portion adapted to contact a shroud of an adjacent blade. The shroud has a substantially constant nominal thickness and the bearing faces have a substantially constant face thickness across the contact portion, the face thickness being greater than the nominal thickness. The transition between the face thickness and the nominal thickness is substantially discontinuous.

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