Patent ID: 6609880
Filing Date: 2003-08-26
Classification: F01D,F05D,Y02T

Abstract:
A method for assembling a turbine nozzle for a gas turbine engine, said method comprising:providing a hollow turbine nozzle including a leading airfoil vane and a trailing airfoil vane coupled by at least one platform that is formed integrally with the airfoil vanes, and wherein each airfoil vane includes a first sidewall and a second sidewall connected at a leading edge and a trailing edge, inserting a first insert into the leading airfoil vane that includes a first sidewall including a first plurality of cooling openings extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough; and inserting a second insert into the trailing airfoil vane, wherein the first insert and the second inserts are identical and are configured to facilitate cooling each respective airfoil vane first sidewall more than each respective airfoil vane second sidewall.