US 12,326,100 B1
Gas turbine engine component fillets formed of CMC plies
Christian X. Campbell, West Hartford, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Jan. 31, 2024, as Appl. No. 18/428,819.
Int. Cl. F01D 5/28 (2006.01); F02C 7/00 (2006.01)
CPC F01D 5/282 (2013.01) [F02C 7/00 (2013.01); F05D 2230/20 (2013.01); F05D 2300/6033 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine static vane comprising:
a radially outer platform, a radially inner platform, and an airfoil extending between a leading edge and a trailing edge, and having a suction side and a pressure side;
the radially inner and outer platforms and the airfoil all being formed of ceramic matrix composite plies, and there being an outer platform fillet and an inlet platform fillet merging the airfoil into the radially outer platform and the radially inner platform and along each of the pressure side and the suction side, with the fillets formed with radially outer ply layers extending from the radially outer platform, through the airfoil, and to the radially inner platform, and radially inner ply layers extending from the radially outer platform, through the airfoil, and to the radially inner platform; and
wherein none of the radially outer ply layers and the radially inner ply layers cover the entirety of the radially outer platform, the radially inner platform or the airfoil, and have edges which overlap each other such that the radially outer ply layers and radially inner ply layers include layers of different shapes.