Patent ID: 11885241
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 9:
10. A turbine nozzle assembly, comprising:
a first airfoil adjacent a second airfoil;
an inner endwall coupled to a radial inner end of the first airfoil and the second airfoil;
an outer endwall coupled to a radial outer end of the first airfoil and the second airfoil;
a mounting rail coupled to the outer endwall, the mounting rail extending at least partially radially outward from the outer endwall and at least partially circumferentially along the outer endwall, the mounting rail having a radial outer surface and a rail thickness; and
a stress relief structure defined in the mounting rail, the stress relief structure including:
an end opening defined in the radial outer surface of the mounting rail;
a slot defined through the rail thickness of the mounting rail and coupled to the end opening; and
an oblong opening defined through the rail thickness of the mounting rail and coupled to a radial inner end of the slot, the oblong opening being arranged asymmetrically in a circumferential direction relative to the slot and including a pair of arced surfaces on opposing sides of a longitudinal direction of the oblong opening, wherein the arced surfaces in the pair of arced surfaces have different radii of curvature.