METHOD AND APPARATUS FOR FABRICATING A NOZZLE SEGMENT FOR USE WITH TURBINE ENGINES

摘要

A nozzle singlet (32) for a turbine engine (10) is provided. The nozzle singlet (32) includes an inner band (40), an outer band (38), and at least one airfoil (36) extending therebetween, at least one first row (100) of cooling holes (60) oriented an angle with respect to at least one second row (110) of cooling holes (120), wherein the orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in an airfoil angle without reorienting the cooling hole pattern.