Method and system for interfacing a ceramic matrix composite component to a metallic component

A method of transferring load from a ceramic matrix composite (CMC) vane assembly to a metallic vane assembly support member, said method comprising:

• providing the CMC vane assembly, the vane assembly including:
• a radially outer end component including a radially outwardly facing surface having a forward flange on a forward end, an aft flange on an aft end and one or more radially outwardly extending load transfer features located in a portion between the forward flange and the aft flange;
• a radially inner end component;
• and
• an airfoil body extending therebetween;
• engaging the radially outer end component to at least one of a plurality of metallic vane assembly support members spaced circumferentially about a gas flow path, the vane assembly support members including one or more load receiving features shaped complementary to the load transfer features, the load transfer feature including a wedge-shaped cross-section.

A gas turbine engine comprising:

• an inner support structure formed of a first metallic material, said inner support structure comprising a strut, said strut comprising a first mating end, a second opposing mating end and a strut body extending radially therebetween;
• an outer support structure formed of a second metallic material;
• an airfoil assembly comprising a ceramic matrix composite (CMC) material and extending between said inner support structure and said outer support structure, said airfoil assembly comprising:
• a radially outer end component comprising a radially outwardly-facing end surface having a forward flange on a forward end, an aft flange on an aft end and a non-compression load-bearing feature extending radially outwardly from said outwardly-facing end surface and formed integrally with said outer end component, said non-compression load-bearing feature located in a portion between the forward flange and the aft flange and configured to mate with a complementary feature formed in a radially inner surface of said outer support structure, said non-compression load-bearing feature selectively positioned orthogonally to a force imparted into said radially outwardly-facing end surface;
• a 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 outer support structure.

A nozzle segment assembly comprising:

• an inner support structure formed of a first metallic material, said inner support structure comprising a strut, said strut comprising a first mating end, a second opposing mating end and a strut body extending radially therebetween;
• an outer support structure formed of a second metallic material and comprising a radially outwardly extending hollow receptacle configured to receive said second opposing mating end;
• an airfoil assembly comprising a ceramic matrix composite (CMC) material and extending between said inner support structure and said outer support structure, said airfoil assembly comprising:
• a radially outer end component comprising a radially outwardly-facing end surface having a forward flange on a forward end, an aft flange on an aft end and a non-compression load-bearing feature extending radially outwardly from said outwardly-facing end surface and formed integrally with said outer end component, said non-compression load-bearing feature located in a portion between the forward flange and the aft flange and configured to mate with a complementary feature formed in a radially inner surface of said outer support structure, said non-compression load-bearing feature selectively positioned orthogonally to a force imparted into said radially outwardly-facing end surface, said non-compression load-bearing feature forming a seal along an aft facing flange of the radially outwardly-facing end surface and a forward facing flange of the outer support structure.