Additively manufactured combustor with adaptive cooling passage

Abstract

A combustor for a gas turbine system includes an additively manufactured (AM) combustor body including a one-piece member that defines a combustion liner and a transition piece at an aft end of the combustion liner. A thermal barrier coating (TBC) is disposed over an inner surface of the combustor body. Adaptive cooling passage(s) are defined in the combustion liner and/or transition piece. Each adaptive cooling passage includes an open end in fluid communication with a coolant air source and a terminating end in the body spaced from the inner surface by a distance. When a spall in the TBC occurs at a location adjacent the terminating end and the high temperature of the body reaches or exceeds a predetermined temperature, the terminating end opens at the location through the distance to allow a flow of the coolant air through to an inside of the AM combustor body.