Coated high temperature combustor liner.

摘要

Each panel (18) of the louver liner of the combustor of a gas turbine engine is coated with a ceramic composition on the surface adjacent the combustion zone with a tapered end (32) at the lip (34) of the cooling air film generating mechanism. A second taper (36) may be incorporated at the back side of the lip (34) of the next adjacent cooling air film generating mechanism.