US 11,719,439 B2
Panel burn through tolerant shell design
Carey Clum, East Hartford, CT (US); and Dennis M Moura, South Windsor, CT (US)
Assigned to Raythehon Technologies Corporation, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Jul. 20, 2021, as Appl. No. 17/380,494.
Application 17/380,494 is a division of application No. 15/903,592, filed on Feb. 23, 2018, granted, now 11,098,899.
Claims priority of provisional application 62/618,841, filed on Jan. 18, 2018.
Prior Publication US 2021/0348761 A1, Nov. 11, 2021
This patent is subject to a terminal disclaimer.
Int. Cl. F23R 3/00 (2006.01)
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
OG exemplary drawing
 
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.