Patent ID: 7625174

Claim:
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; forming at least one catch to extend outward from the at least one spline seal body; and inserting the at least one spline seal axially through a trailing end of a slot defined in at least one of the first and second turbine nozzles by deforming a portion of the at least one spline seal within the slot to facilitate positioning the at least one spline seal with respect to the first and second turbine nozzles to facilitate reducing leakage through the gap, such that a portion of the at least one catch is received within a recess defined within the turbine nozzle slot to facilitate retaining the at least one spline seal within the turbine nozzle slot.