US 12,448,896 B2
Localized thickening ply reinforcement within ceramic matrix composite airfoil cavity
Howard J. Liles, Newington, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Aug. 21, 2023, as Appl. No. 18/236,263.
Prior Publication US 2025/0067184 A1, Feb. 27, 2025
Int. Cl. F01D 5/28 (2006.01)
CPC F01D 5/282 (2013.01) [F05B 2230/30 (2013.01); F05B 2280/6003 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A ceramic matrix composite vane for a gas turbine engine comprising:
an airfoil comprising:
a leading edge;
a trailing edge;
a suction sidewall; and
a pressure sidewall joined to the suction sidewall at the leading edge and the trailing edge, the pressure sidewall comprising a locally-thickened region,
a first platform; and
a second platform, wherein the airfoil is connected to and extends between the first platform and the second platform;
wherein the locally-thickened region extends from one of the first platform and the second platform to a midspan region of the airfoil and wherein the locally-thickened region has a first thickness, the first thickness being a maximum thickness of the pressure sidewall;
wherein the suction sidewall has a second thickness, the second thickness being a maximum thickness of the suction sidewall;
wherein the first thickness is greater than the second thickness; and
wherein the airfoil comprises a plurality of fiber plies;
wherein at least one of the plurality of plies is disposed only in the locally thickened region of the airfoil and one of the first platform and the second platform.