US 11,840,930 B2
Component with feather seal slots for a gas turbine engine
Tracy A. Propheter-Hinckley, Rocky Hill, CT (US); Craig R. McGarrah, Southington, CT (US); Kyle J. Brevick, Windsor, CT (US); and Egon Salimusaj, East Hartford, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on May 17, 2019, as Appl. No. 16/415,865.
Prior Publication US 2020/0362715 A1, Nov. 19, 2020
Int. Cl. F01D 11/00 (2006.01); F02C 7/28 (2006.01)
CPC F01D 11/005 (2013.01) [F02C 7/28 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2240/55 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A vane for a gas turbine engine, the vane including:
an inner diameter platform and an outer diameter platform and an airfoil that extends between the inner diameter platform and the outer diameter platform, the airfoil having a leading edge, a trailing edge, a pressure side and a suction side;
an axial feather seal slot and a radial seal slot located on a suction side mate face and a pressure side mate face of the inner diameter platform, the axial feather seal slot includes a leading edge portion that extends from the radial seal slot towards a leading edge of the vane and a trailing edge portion that extends from the radial seal slot towards a trailing edge of the vane, and a chamfer extends between the radial seal slot and the trailing edge portion of the axial feather seal slot, wherein the suction side mate face and the pressure side mate face of the inner diameter platform each have a first feather seal and a second feather seal located in the axial feather seal slot and the radial seal slot.