CERAMIC MATRIX COMPOSITE AIRFOIL ASSEMBLY

摘要

An airfoil assembly (200) for a gas turbine engine (100) and a method (1400) of transferring load from the ceramic matrix composite (CMC) airfoil assembly (200) to a metallic vane assembly support member (212, 214) are provided. The airfoil assembly (200) includes a forward end and an aft end with respect to an axial direction (215) of the gas turbine engine (100). The airfoil assembly (200) further includes a radially outer end component (216) including a radially outwardly-facing end surface (302) having a non-compression load-bearing feature (304) extending radially outwardly from the outwardly-facing end surface (302) and formed integrally with the outer end component (216), the feature (304) configured to mate with a complementary feature (312) formed in a radially inner surface (308) of a first airfoil assembly support structure (214), the feature (304) selectively positioned orthogonally to a force imparted into the airfoil assembly (200). The airfoil assembly (200) also includes a radially inner end component (204), and a hollow airfoil body (210) extending therebetween, the airfoil body (210) configured to receive a strut (208) couplable at a first end (206) to the first airfoil assembly support structure (214).