| 主权项 |
1. A vane assembly for a gas turbine engine, the assembly comprising
an inner platform and an outer platform spaced apart from the inner platform to define a gas path therebetween, and a ceramic-matrix composite airfoil that extends from the inner platform to the outer platform across the gas path, the ceramic-matrix composite airfoil formed to include a pressure side, a suction side, and a plurality of ribs spaced radially apart from one another between the inner platform and the outer platform that interconnect the pressure side with the suction side, wherein the ceramic-matrix composite airfoil includes (i) a core having a plurality of rib-containing sections and at least one hollow section stacked radially on top of one another to form the plurality of ribs, and (ii) an overwrap that wraps around the core to form the pressure side and the suction side of the airfoil. |
