Coated high temperature combustor liner

Claim 1

For a combustor for a gas turbine power plant having a plurality of louver panels attached end to end to define a combustion chamber wherein cool air is heated to hot gases, each of said louver panels having an inner surface being subjected to the hot gases in said combustion chamber and an outer surface being subjected to the cooler air of said power plant, cooling air film generating means including a discharge lip formed on the end of each of said louver panels for receiving said cooler air and injecting a film of said cooler air adjacent said inner surface of said, louver panels a ceramic coating on said inner surface of each of said louver panels contiguous with said combustion chamber each of said louver panels being subjected to axial bending stresses and the largest bending stress occurring at a point intermediate its ends, said coating being dimensioned so that one end is gradually tapering from a thickest portion immediately adjacent the point of the largest axial bending stress of each of said louver panels to an upstream end adjacent said tip where the film of cool air is formed.