SEAL ASSEMBLY FOR USE WITH TURBINE NOZZLES

摘要

A method for assembling a turbine nozzle assembly with respect to a combustor of a gas turbine engine is provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles is provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.