Patent ID: 8038389
Filing Date: 2011-10-18
Classification: F01D,F05D

Abstract:
1. A method for assembling a turbine nozzle assembly with respect to a combustor of a gas turbine engine, said method comprising: coupling a radial outer retaining ring to an aft end of the combustor, wherein the outer retaining ring includes an aft end flange; providing a plurality of turbine nozzles each comprising an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band; coupling the outer band of each turbine nozzle to the outer retaining ring, wherein the outer band includes a slot and a passage that are each defined at a trailing edge of the outer band; coupling an inner retaining ring positioned about an axis of the gas turbine engine to the inner band of each turbine nozzle to define the turbine nozzle assembly; and coupling a retention seal between the outer band and the outer retaining ring, wherein the retention seal includes a first end, a generally opposing second end contacting the outer retaining ring, and a body extending therebetween, wherein the body includes an insertion portion that is inserted within the passage, the first end extends radially outwardly from the body to contact with the aft end flange to facilitate coupling the turbine nozzle to the outer retaining ring.