Combustor wall assembly for gas turbine engine

A combustor of a gas turbine engine, the combustor comprising:

• an outer shell;
• a plurality of inner panels mounted to the outer shell, the plurality of inner panels spaced inwardly from the outer shell to define a double-wall configuration with the outer shell, the plurality of inner panels having a higher heat resistance than the outer shell;
• a damper disposed between the outer shell and a first inner panel of the plurality of inner panels;
• and
• an insert disposed between the first inner panel and the outer shell, wherein:
• the first inner panel and a second inner panel of the plurality of inner panels are positioned to define a gap therebetween;
• part of the insert is disposed in the gap between the first inner panel and the second inner panel;
• the part of the insert disposed in the gap includes first sealing faces oriented obliquely to a normal of an inner surface of the outer shell;
• the first inner panel and the second inner panel each include a second sealing face oriented obliquely to the normal of the inner surface of the outer shell;
• and
• the first sealing faces of the insert are in respective sliding engagement with the second sealing faces of the first inner panel and of the second inner panel;
• the insert includes:
• a first flange engaged with a first bracket of the first inner panel, the first flange being spaced apart from the outer shell;
• and
• a second flange engaged with a second bracket of the second inner panel, the second flange being spaced apart from the outer shell;
• wherein:
• the first bracket of the first inner panel defines a first channel separate from the outer shell, the first flange of the insert being received in the first channel;
• and
• the second bracket of the second inner panel defines a second channel separate from the outer shell, the second flange of the insert being received in the second channel.