US 12,297,746 B2
Erosion compensated vane geometry
Lawrence A. Binek, Glastonbury, CT (US); and Yoel Bugin, Port St Lucie, FL (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Oct. 11, 2023, as Appl. No. 18/485,103.
Prior Publication US 2025/0122805 A1, Apr. 17, 2025
Int. Cl. F01D 5/14 (2006.01); F01D 5/28 (2006.01); F23R 3/14 (2006.01); B33Y 80/00 (2015.01)
CPC F01D 5/141 (2013.01) [F01D 5/28 (2013.01); F23R 3/14 (2013.01); B33Y 80/00 (2014.12); F05D 2220/32 (2013.01); F05D 2240/305 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine vane for use in a gas turbine engine, the turbine vane comprising:
an airfoil section having a concave sidewall and a convex sidewall, wherein both the concave sidewall and convex sidewall extend spanwise between a platform and a radially outward airfoil tip and chordwise between a leading edge and a trailing edge,
wherein the concave sidewall includes a convex ablative region, wherein the convex ablative region is a non-aerodynamic sacrificial region positioned on the concave sidewall at a location deemed to be susceptible to erosion or burn through damage.