Integral refilmer lip for floatwall panels

For a liner for a combustor of a gas turbine engine having a generally cylindrically shaped shell and a plurality of spaced co-extensive panels extending circumferentially and axially relative to said shell, said shell having an outer surface being exposed to cooler air and said panels each having an inner surface being exposed to combustion gases, said shell being bent radially inwardly to define a bend and forming a reduced diameter portion, the upstream and downstream ends of adjacent axial panels mounted adjacent said bend, at least one combustion/dilution air hole formed integrally in one of said panels and having a cup portion radially extending through an opening in said shell, said cup having a lip extending radially and axially circumscribing 180.degree. disposed adjacent said inner surface and having an inner diameter having a smaller diameter than the diameter of the combustion/dilution hole in said cup so that the inner diameter projects in the stream of the combustion/dilution air passing through said combustion/dilution air hole and diverts a portion of said dilution/combustion air to flow along said lip to form a cooling film stream directed to flow adjacent the inner surface of said panel.