Combustor assembly for a gas turbine engine

A gas turbine engine defining an axial direction, the gas turbine engine comprising:

• a fan section comprising a fan;
• and
• a turbomachine drivably coupled to the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order, the combustion section comprising:
• a plurality of liner tiles defining at least part of a combustion chamber, the combustion chamber extending between a forward end and an aft end generally along the axial direction;
• a combustor liner support assembly positioned on a cold side of the plurality of liner tiles, the combustor liner support assembly defining a rail extending radially toward the combustion chamber;
• and
• a retainer assembly comprising a bushing, the bushing extending through at least a portion of at least one liner tile of the plurality of liner tiles, wherein the at least one liner tile is floatably coupled to the rail via the bushing.

A combustor assembly for a gas turbine engine, the gas turbine engine defining an axial direction, the combustor assembly comprising:

• a combustor liner support assembly;
• a plurality of liner tiles defining at least part of a combustion chamber, the combustion chamber extending between a forward end and an aft end generally along the axial direction with respect to the combustor liner support assembly, wherein the plurality of liner tiles comprise a first liner tile and a second liner tile adjacent the first liner tile, wherein a first liner tile spacing is defined between the first and second liner tiles at a first temperature of the combustion chamber, and a second liner tile spacing greater than the first liner tile spacing is defined between the first and second liner tiles at a second temperature of the combustion chamber greater than the first temperature;
• a spline seal positioned between the first and second liner tiles, wherein the spline seal defines a spline seal cooling aperture, the spline seal cooling aperture positioned to provide a greater cooling airflow through the spline seal cooling aperture at the second liner tile spacing than the first liner tile spacing;
• a rail extending radially toward the combustion chamber;
• and
• a fastener element coupling a bushing to the rail,
• wherein at least one of the first liner tile or the second liner tile is floatably coupled to the bushing, and wherein the bushing extends through at least a portion of the at least one of the first liner tile or the second liner tile.