A liner panel for use in a combustor of a gas turbine engine includes a substrate with a hot side and a cold side; a bond coat on at least one of the hot side and the cold side of the substrate; and a convective feature on the cold side of the substrate of a material different than a material of the substrate. A wall assembly for use in a combustor of a gas turbine engine includes a shell with a multiple of impingement flow passages; and a liner panel mounted to the shell, where the panel includes a convective feature which faces the shell. A method of cooling a liner panel for a combustor section of a gas turbine engine includes directing an impingement flow towards a convective feature of a liner panel; and directing an effusion flow though the liner panel.