Liner for a Gas Turbine Engine Combustor

Abstract

A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a film cooling hole extending from the second side to the first side, the film cooling hole defining an outlet on the first side of the liner, the liner including an airflow feature on the first side of the of the liner adjacent to the outlet of the film cooling hole to increase a cooling of the liner.

What is claimed is: 
     
         1 . A gas turbine engine combustor comprising:
 a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a film cooling hole extending from the second side to the first side, the film cooling hole defining an outlet on the first side of the liner, the liner comprising an airflow feature on the first side of the of the liner adjacent to the outlet of the film cooling hole to increase a cooling of the liner.   
     
     
         2 . The gas turbine engine of  claim 1 , wherein the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, and wherein the airflow feature is positioned at least partially downstream of the outlet along the airflow direction. 
     
     
         3 . The gas turbine engine of  claim 2 , wherein the airflow feature is a first airflow feature, wherein the liner further comprises a second airflow feature also positioned at least partially downstream of the outlet along the airflow direction, wherein the combustion chamber further defines a transverse direction perpendicular to the airflow direction, and wherein the second airflow feature is spaced from the first airflow feature along the transverse direction. 
     
     
         4 . The gas turbine engine of  claim 3 , wherein the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is an indentation on the first side of liner. 
     
     
         5 . The gas turbine engine of  claim 1 , wherein the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, and wherein the airflow feature is positioned at least partially upstream of the outlet along the airflow direction. 
     
     
         6 . The gas turbine engine of  claim 5 , wherein the airflow feature is a first airflow feature, wherein the liner further comprises a second airflow feature also positioned at least partially upstream of the outlet along the airflow direction, wherein the combustion chamber further defines a transverse direction perpendicular to the airflow direction, and wherein the second airflow feature is spaced from the first airflow feature along the transverse direction. 
     
     
         7 . The gas turbine engine of  claim 6 , wherein the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is an indentation on the first side of liner. 
     
     
         8 . The gas turbine engine of  claim 6 , wherein the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is also a protrusion on the first side of the liner extending into the combustion chamber. 
     
     
         9 . The gas turbine engine of  claim 6 , wherein the liner further comprises a third airflow feature and a fourth airflow feature, wherein the third airflow feature and the fourth airflow feature are each positioned at least partially downstream of the outlet along the airflow direction and spaced from one another along the transverse direction. 
     
     
         10 . The gas turbine engine of  claim 9 , wherein at least one of the first airflow feature, the second airflow feature, the third airflow feature, and the fourth airflow feature is a protrusion extending into the combustion chamber, and wherein at least one of the first airflow feature, the second airflow feature, the third airflow feature, and the fourth airflow feature is an indentation on the first side of liner. 
     
     
         11 . The gas turbine engine of  claim 1 , wherein the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, wherein the airflow feature is a first airflow feature, wherein the liner further comprises a second airflow feature, wherein the first and second airflow features are aligned with one another and the outlet of the film cooling hole along the airflow direction, and wherein the first airflow feature is positioned adjacent to the second airflow feature along the airflow direction. 
     
     
         12 . The gas turbine engine of  claim 1 , wherein the combustion chamber defines an airflow direction over the film cooling hole on the first side of the liner and a transverse direction perpendicular to the airflow direction, wherein the airflow feature defines a length along the airflow direction and a width along the transverse direction, and wherein the width of the airflow feature is greater than the length of the airflow feature and up to about five times the length of the airflow feature. 
     
     
         13 . The gas turbine engine of  claim 1 , wherein the film cooling hole defines a diameter at the outlet, wherein the airflow feature defines a width and a height, wherein the width of the airflow feature is greater than or equal to about 0.1 times the diameter of the of the film cooling hole and up to about 6 times the diameter of the film cooling hole, and wherein the height of the airflow feature is greater than or equal to about 0.1 times the diameter of the film cooling hole and up to about 6 times the diameter of the film cooling hole. 
     
     
         14 . The gas turbine engine of  claim 1 , wherein the film cooling hole is a first film cooling hole of a plurality of film cooling holes defined by the liner. 
     
     
         15 . The gas turbine engine of  claim 1 , wherein the film cooling hole defines a substantially constant diameter along a length thereof. 
     
     
         16 . A gas turbine engine comprising:
 a combustion section comprising a combustor liner, the combustor liner defining at least in part a combustion chamber, a hot side exposed to the combustion chamber, a cold side opposite the hot side, and a plurality of film cooling holes extending from the cold side to the hot side, the plurality of film cooling holes each defining an outlet on the hot side of the liner, the liner comprising a plurality of airflow features on the hot side of the of the liner, each airflow feature of the plurality of airflow features positioned adjacent to the outlet of one of the plurality of film cooling holes to increase a cooling of the liner.   
     
     
         17 . The gas turbine engine of  claim 16 , wherein the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner, and wherein the airflow features are each positioned at least partially downstream of the outlet of one of the plurality of film cooling holes along the airflow direction. 
     
     
         18 . The gas turbine engine of  claim 16 , wherein the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner, and wherein the airflow features are each positioned at least partially upstream of the outlet of one of the plurality of film cooling holes along the airflow direction. 
     
     
         19 . The gas turbine engine of  claim 16 , wherein the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner and a transverse direction perpendicular to the airflow direction, wherein each airflow feature defines a length along the airflow direction and a width along the transverse direction, and wherein the width of each airflow feature is greater than the length of the airflow feature and up to about five times the length of the airflow feature. 
     
     
         20 . The gas turbine engine of  claim 16 , wherein a first film cooling hole of the plurality of film cooling holes defines a diameter at its outlet, wherein a first airflow feature of the plurality of airflow features defines a width and a height, wherein the width of the first airflow feature is greater than or equal to about 0.1 times the diameter of the of the first film cooling hole and up to about 6 times the diameter of the first film cooling hole, and wherein the height of the first airflow feature is greater than or equal to about 0.1 times the diameter of the first film cooling hole and up to about 6 times the diameter of the first film cooling hole.