Method and apparatus for fabricating a nozzle segment for...

Details Method and apparatus for fabricating a nozzle segment for... Method and apparatus for fabricating a nozzle segment for...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F01D 9/06 (2006.01) F01D 25/12 (2006.01)

Patent

CA 2597660

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.

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