Patent ID: 7806650
Filing Date: 2010-10-05
Classification: F01D,F05D

Abstract:
1. A method for orienting cooling holes of a nozzle singlet for a turbine engine, said method comprising: providing a nozzle singlet having an inner band that includes an inner band leading edge, an outer band that includes an outer band leading edge, and an airfoil extending between the inner band and the outer band, the airfoil including an airfoil leading edge; forming at least one first row of the cooling holes at an angle with respect to at least one second row of the cooling holes about the airfoil leading edge and along at least one of the inner band leading edge and the outer band leading edge, wherein an 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 orientation of the airfoil without reorienting the cooling hole pattern.