US Patent 11834967 Liner for anti-rotation tab and ceramic component

A gas turbine engine includes a first component, a second component, an anti-rotation tab, and a liner. The first component has a first wall that includes a first slot, and the second component has a second wall that includes a second slot that is in register with the first slot to define a groove. The anti-rotation tab extends into the groove and limits rotation of the first component and the second component. The liner lines the groove to limit wear between the anti-rotation tab and the first component and between the anti-rotation tab and the second component.