Combustor assembly for a gas turbine engine

A combustor assembly for a gas turbine engine, the gas turbine engine including a combustor defining a combustion chamber, the combustor assembly comprising:

• a combustor liner support shell;
• a plurality of liner tiles defining at least part of the combustion chamber, wherein each liner tile of the plurality of liner tiles defines a protrusion and a recess opposite the protrusion, wherein the recess is configured to at least partially receive the protrusion of an adjacent liner tile of the plurality of liner tiles;
• and
• a fastener assembly at least partially disposed in the recess for coupling a respective liner tile to the combustor liner support shell,
• wherein each liner tile of the plurality of liner tiles defines a liner tile panel defining at least part of the combustion chamber;
• an attachment flange spaced apart from the liner tile panel to define the recess;
• and a support flange extending from the liner tile panel to the attachment flange, and
• wherein at least a portion of the fastener assembly extends through the attachment flange and the combustor liner support shell.