Patent ID: 8894362
Filing Date: 2014-11-25
Classification: F01D,F05D,Y10T

Abstract:
1. A method for adjusting a position of a blade ring relative to a rotor in a gas turbine engine, wherein an outer casing surrounds the blade ring and the blade ring surrounds the rotor, comprising: determining an amount of vertical movement needed to reposition the blade ring relative to the rotor so that the blade ring is at a desired position relative to the rotor; providing at least one torque pin assembly comprising a torque pin and a variable thickness defining structure; determining a change in the thickness of the variable thickness defining structure so as to effect the necessary vertical movement of the blade ring; changing the thickness of the variable thickness defining structure; coupling the at least one torque pin assembly to the outer casing such that at least one torque pin engages the blade ring; the variable thickness defining structure comprises one or more shims removably coupled to the torque pin; the torque pin comprises an elongated body for projecting radially inward through a bore in the outer casing and engaging the blade ring, the elongated body having at least one recess; the one or more shims being received in the at least one recess; the variable thickness defining structure further comprises at least one removable member for being received in the at least one recess; and structure to secure the at least one removable member and the one or more shims to the elongated body.