Abstract: 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 includes a radially outer end component, a radially inner end component, and a hollow airfoil body extending therebetween. The radially outer end component including a radially outwardly-facing end surface having a non-compression load-bearing feature extending radially outwardly and formed integrally with the outer end component, the load-bearing feature configured to mate with a complementary feature formed in a radially inner surface of a first airfoil assembly support structure and selectively positioned orthogonally to a force imparted into the airfoil assembly.

Abstract: Methods for positioning neighboring nozzles of a gas turbine engine are provided. A method includes assembling a first nozzle assembly. The first nozzle assembly includes a first nozzle and a first nozzle support structure. The method further includes assembling a second nozzle assembly. The second nozzle assembly includes a second nozzle and a second nozzle support structure. The method further includes adjusting the first nozzle assembly and the second nozzle assembly such that an engineering dimension between the first nozzle and the second nozzle is within a predetermined engineering tolerance, and joining the first nozzle support structure and the second nozzle support structure together.

Abstract: 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.

Abstract: Methods for positioning neighboring nozzles of a gas turbine engine are provided. A method includes assembling a first nozzle assembly. The first nozzle assembly includes a first nozzle and a first nozzle support structure. The method further includes assembling a second nozzle assembly. The second nozzle assembly includes a second nozzle and a second nozzle support structure. The method further includes adjusting the first nozzle assembly and the second nozzle assembly such that an engineering dimension between the first nozzle and the second nozzle is within a predetermined engineering tolerance, and joining the first nozzle support structure and the second nozzle support structure together.