METHOD AND SYSTEM FOR INTERFACING A CERAMIC MATRIX COMPOSITE COMPONENT TO A METALLIC COMPONENT

摘要

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

主权项

1. An airfoil assembly for a gas turbine engine, said airfoil assembly comprising a ceramic matrix composite (CMC) material, said airfoil assembly comprising a forward end and an aft end with respect to an axial direction of the gas turbine engine, said airfoil assembly comprising:
a radially outer end component comprising a radially outwardly-facing end surface having a non-compression load-bearing feature extending radially outwardly from said outwardly-facing end surface and formed integrally with said outer end component, said feature configured to mate with a complementary feature formed in a radially inner surface of a first airfoil assembly support structure, said feature selectively positioned orthogonally to a force imparted into said airfoil assembly; a radially inner end component configured to engage a second airfoil assembly support structure positioned radially inward from said radially inner end component; and a hollow airfoil body extending therebetween, said airfoil body configured to receive a strut couplable at a first end to said first airfoil assembly support structure.