Patent ID: 6652220
Filing Date: 2003-11-25
Classification: F01D,F05D,Y02T

Abstract:
A method for assembling a turbine nozzle for a gas turbine engine, said method comprising:providing a hollow doublet including a leading airfoil vane and a trailing airfoil vane coupled by at least one platform, wherein each airfoil vane includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge; inserting an insert into at least one of the airfoil vanes, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate cooling the airfoil more than the second plurality of cooling openings; inserting second insert into the remaining airfoil vane, wherein the first and second inserts non-identical.