Methods and apparatus for cooling gas turbine nozzles

摘要

A method for assembling a turbine nozzle (50) for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil (76) and a trailing airfoil (78) coupled by at least one platform (54), wherein each airfoil includes a first sidewall and a second sidewall (82) that extend between a respective leading and trailing edge. The method also includes inserting an insert (102) into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including (124) a second plurality of cooling openings (144) extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.