Patent ID: 7575415
Filing Date: 2009-08-18
Classification: F01D,F02C,F05D,Y10T

Abstract:
1. A method for assembling a gas turbine engine, said method comprising: coupling a first turbine nozzle within the engine; coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles; providing at least one spline seal including a substantially planar body and at least one retainer tab that extends outward from the body and that is formed integrally with the body; and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, a stop projection is defined within the slot, such that the at least one retainer tab and the stop projection facilitate retaining the at least one spline seal within the turbine nozzle slot.