Patent ID: 6533542
Filing Date: 2003-03-18
Classification: F01D

Abstract:
A split ring for a gas turbine casing comprising a plurality of split segments arranged on an inner wall of the gas turbine casing in a circumferential direction at predetermined intervals so that the split segments form a ring disposed between tips of turbine blades and the inner wall opposing the tips of the turbine blades, wherein each of the split segments includes two circumferential end faces which oppose the end faces of the adjacent split segments and an inner face substantially perpendicular to the end faces and opposing the tips of the turbine blades and a transition face formed between at least one of the end faces and the inner face and, wherein the surface of the transition face is formed in such a manner that the clearance between the tips of the turbine blades and the surface of the transition face increases from the inner face toward the end face, wherein one transition face is formed on each split segment between the inner face and the end face located on the downstream side of the split segment with respect to the direction of rotation of the turbine blades.