Patent ID: 8128354
Filing Date: 2012-03-06
Classification: F01D,F04D,F05D

Abstract:
1. A gas turbine engine comprising: an outer casing with a circumferential casing slot; a plurality of circumferentially positioned vane segments coupled to said outer casing, each vane segment comprising at least one vane airfoil, a radially inner shroud coupled to a first end of said airfoil, a radially outer shroud coupled to a second end of said airfoil, and a strongback fixedly coupled to said outer shroud; and at least one tangential load block provided between two adjacent ones of said vane segments so as to transfer a tangential load from a first one of said vane segments to a second one of said vane segments; wherein said strongback in each of said adjacent ones of said vane segments is provided with a corresponding recess for receiving said load block.