Combustor assembly for a gas turbine engine
A combustor assembly for a gas turbine engine includes a combustor defining a combustion chamber. The combustor assembly includes a combustor liner support shell, and a plurality of liner tiles defining at least part of the combustion chamber. Each liner tile of the plurality of liner tiles defines a protrusion and a recess opposite the protrusion where the recess is configured to at least partially receive the protrusion of an adjacent liner tile of the plurality of liner tiles. A fastener assembly is at least partially disposed in the recess for coupling a respective liner tile to the combustor liner support shell.
1 . A combustor assembly for a gas turbine engine, the gas turbine engine including a combustor defining a combustion chamber, the combustor assembly comprising:
a combustor liner support shell;
a plurality of liner tiles defining at least part of the combustion chamber, wherein each liner tile of the plurality of liner tiles defines a protrusion and a recess opposite the protrusion, wherein the recess is configured to at least partially receive the protrusion of an adjacent liner tile of the plurality of liner tiles; and
a fastener assembly at least partially disposed in the recess for coupling a respective liner tile to the combustor liner support shell,
wherein each liner tile of the plurality of liner tiles defines a liner tile panel defining at least part of the combustion chamber; an attachment flange spaced apart from the liner tile panel to define the recess; and a support flange extending from the liner tile panel to the attachment flange, and
wherein at least a portion of the fastener assembly extends through the attachment flange and the combustor liner support shell.
2 . The combustor assembly of claim 1 , wherein each liner tile of the plurality of liner tiles defines a first liner tile end and a second liner tile end opposite the first liner tile end, and wherein the recess is positioned at the first liner tile end, and wherein the protrusion is positioned at the second liner tile end.
3 . The combustor assembly of claim 1 , wherein each liner tile of the plurality of liner tiles comprises:
the support flange extending radially from the liner tile panel and defining at least part of the recess; and
a support leg extending radially from the liner tile panel and spaced apart from the support flange, the support leg supporting the protrusion.
4 . The combustor assembly of claim 3 , wherein the liner tile panel, the support flange, and the support leg define a cooling air cavity between the respective liner tile and the combustor liner support shell.
5 . The combustor assembly of claim 1 , wherein the plurality of liner tiles define an outer combustor liner, and wherein the combustor liner support shell is positioned radially outward from the plurality of liner tiles.
6 . The combustor assembly of claim 1 , wherein each liner tile of the plurality of liner tiles comprises:
the liner tile panel defining one or more liner tile cooling apertures;
the support flange extending radially from the liner tile panel and defining at least part of the recess; and
a support leg extending radially from the liner tile panel and spaced apart from the support flange, the support leg supporting the protrusion; and
wherein the combustor liner support shell defines one or more support shell apertures to allow a cooling airflow to flow to the one or more liner tile cooling apertures.
7 . The combustor assembly of claim 1 , wherein the fastener assembly comprises:
a fastener extending through the combustor liner support shell and the attachment flange; and
a securing member positioned within the recess to engage the fastener to couple the attachment flange to the combustor liner support shell.
8 . The combustor assembly of claim 1 , wherein each liner tile of the plurality of liner tiles comprises:
the support flange extending radially from the liner tile panel to the attachment flange, wherein the liner tile panel, the attachment flange, and the support flange define the recess, the recess having an open end at a liner tile end of the respective liner tile, and wherein the support flange defines a closed end of the recess; and
wherein the fastener assembly is at least partially disposed between the closed end of the recess and the protrusion of the adjacent liner tile.
9 . The combustor assembly of claim 8 , wherein the protrusion of the adjacent liner tile is positioned within the open end of the recess.
10 . The combustor assembly of claim 8 , wherein the fastener assembly comprises:
a fastener extending through the combustor liner support shell and the attachment flange; and
a securing member positioned between the protrusion and the closed end of the recess to engage the fastener.
11 . A combustor assembly for a gas turbine engine, the combustor assembly comprising:
a combustor liner support shell;
a plurality of liner tiles defining at least part of the combustion chamber, wherein the plurality of liner tiles comprises:
a first liner tile defining a recess; and
a second liner tile positioned adjacent the first liner tile, the second liner tile defining a protrusion, and wherein the recess is configured to at least partially receive the protrusion;
a fastener extending through the combustor liner support shell and at least a portion of the first liner tile; and
a securing member coupled to the first liner tile within the recess to engage the fastener.
12 . The combustor assembly of claim 11 , wherein the first liner tile comprises an attachment flange defining at least part of the recess, and wherein the fastener extends through the attachment flange.
13 . The combustor assembly of claim 12 , wherein the first liner tile comprises a liner tile panel defining at least part of the combustion chamber, and further comprising a cooling air cavity defined between the liner tile panel and the combustor liner support shell.
14 . The combustor assembly of claim 11 , wherein the first liner tile comprises:
a liner tile panel defining at least part of the combustion chamber;
an attachment flange spaced radially apart from the liner tile panel; and
a support flange extending radially from the liner tile panel to the attachment flange, and wherein the liner tile panel, the attachment flange, and the support flange define the recess.
15 . The combustor assembly of claim 14 , wherein the liner tile panel defines one or more liner tile cooling apertures.
16 . The combustor assembly of claim 14 , wherein the attachment flange is positioned against an inner surface of the combustor liner support shell.
17 . The combustor assembly of claim 14 , wherein the securing member is positioned between the support flange and the protrusion.