Lamellate CMC structure with interlock to metallic support structure

An airfoil assembly comprising:

• a stacked plurality of lamellae, each lamella comprising an outer surface collectively defining an airfoil shape, and each lamella comprising an inner surface collectively defining a core;
• a support structure disposed in the core and comprising at least one interlock feature;
• each lamella comprising an interlock feature cooperatively interfaced with a respective support structure interlock feature, the cooperating interlock features effective to transmit forces there between to support the lamellae relative to the support structure while accommodating differential thermal expansion there between.

A ring segment assembly for a gas turbine engine comprising:

• a first carrier portion comprising an interlock feature;
• a second carrier portion removably attached to the first carrier portion and comprising an interlock feature;
• a stacked plurality of lamellae each comprising a wear surface and an opposed surface defining an interlock feature cooperatively interfaced with the interlock feature of at least one of the first carrier portion and the second carrier portion, the cooperating interlock features effective to support the stacked lamellae relative to the attached carrier portions while accommodating differential thermal growth there between.