Seal assembly with ductile wear liner

A gas turbine engine comprising:

• an engine case extending along an engine longitudinal axis;
• an array of blades rotatable about the engine longitudinal axis;
• and
• a seal support mounted to the engine case, the seal support including a plurality of support hooks;
• an array of blade outer air seal assemblies distributed about the array of blades to bound a core flow path, wherein each of the seal assemblies comprises:
• a seal including a seal body extending circumferentially between opposed mate faces, the seal body having a seal face that bounds the core flow path and an opposed backside face, and a plurality of rail apertures defined in a pair of rails extending outwardly from the backside face;
• a plurality of wear liners received between respective ones of the support hooks and surfaces of the rail apertures to mount the seal;
• and
• wherein the pair of rails are constructed from a ceramic matrix composite (CMC) including a plurality of ply layers that define the rail apertures.

A method of assembly for a gas turbine engine comprising:

• providing a blade outer air seal (BOAS) including a seal body extending circumferentially between opposed mate faces and a rail extending outwardly from the seal body, the seal body having a seal face that bounds a gas path, the rail defining a rail aperture, and the rail comprises ceramic;
• inserting a wear liner into the rail aperture, the wear liner including a liner body defining a liner aperture;
• mounting the blade outer air seal (BOAS) to a seal support, including inserting a support hook of the seal support into the liner aperture such that the wear liner is sandwiched between the support hook and surfaces of the rail defining the rail aperture;
• and
• wherein the support hook comprises a first material having a first modulus of elasticity, and the liner body comprises a second material having a second modulus of elasticity that is less than the first modulus of elasticity.