CPC F23R 3/002 (2013.01) [F23M 2900/05004 (2013.01); F23R 2900/00018 (2013.01); F23R 2900/03043 (2013.01); F23R 2900/03045 (2013.01)] | 6 Claims |
1. A gas turbine engine combustor, comprising:
a shell having a first side and a second side opposite the first side, the shell comprises a shell material;
a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot combustion gas flows, wherein the first side of the shell faces the panel and the hot gas path;
a thermal barrier coating (TBC) disposed on the shell material on the first side of the shell, wherein the TBC is comprised of a metallic layer;
a first heat transfer augmentation feature extending from the second side of the shell, wherein the first heat augmentation feature comprises a trip strip; and
a second heat transfer augmentation feature extending from the second side of the shell, wherein the second heat transfer augmentation feature comprises a cooling fin;
wherein a shape of the first heat augmentation feature is different from a shape of the second heat transfer augmentation feature, and a height of the cooling fin is greater than a height of the trip strip.
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