Patent ID: 9156114
Filing Date: 2015-10-13
Classification: B23H,B23P,F01D,Y10T

Abstract:
1. A method comprising: providing a turbine nozzle including: forming an aperture extending through the outer surface of the fillet region to the at least one cavity of the airfoil; forming a groove on a portion of the inner surface of the at least one cavity, such that the groove extends continuously along a majority of an axial length of the airfoil between the airfoil leading edge and the airfoil trailing edge; coupling a cover plate to the inner surface of the at least one cavity of the turbine nozzle to substantially cover a portion of the groove; and forming a non-linear cooling conduit from the aperture, the groove and the cover plate, the non-linear cooling conduit located between the cavity of the airfoil and the outer surface of the fillet region.