Gas turbine engine combustor liner panel

Abstract

A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.

What is claimed is: 
     
         1 . A liner panel for a combustor of a gas turbine engine, the liner panel comprising:
 a multiple of heat transfer augmentors;   at least one of said multiple of heat transfer augmentors including a depression; and   said depression including an entrance to at least one passage through said liner panel.   
     
     
         2 . The liner panel as recited in  claim 1 , wherein said entrance to said at least one passage through said liner panel is displaced from a surface of said liner panel. 
     
     
         3 . The liner panel as recited in  claim 2 , wherein said at least one passage is an effusion flow passage. 
     
     
         4 . The liner panel as recited in  claim 3 , wherein
 said depression is a hemi-spherical depression; and   said entrance is within said hemi-spherical depression.   
     
     
         5 . The liner panel as recited in  claim 4 , wherein said entrance is centered within said hemi-spherical depression. 
     
     
         6 . The liner panel as recited in  claim 5 , wherein said at least one passage defines an angle through the liner panel. 
     
     
         7 . The liner panel as recited in  claim 1 , wherein at least one of said multiple of impingement flow passages is directed between said hemi-spherical protuberance 
     
     
         8 . A liner panel for a combustor of a gas turbine engine, the liner panel comprising:
 a multiple of heat transfer augmentors;   a subset of said multiple of heat transfer augmentors including a hemi-spherical protuberance with a hemi-spherical depression; and   said hemi-spherical depression including an entrance to at least one passage through said liner panel.   
     
     
         9 . The liner panel as recited in  claim 8 , wherein said entrance to said at least one passage through said liner panel is displaced from a surface of said liner panel. 
     
     
         10 . The liner panel as recited in  claim 8 , wherein said at least one passage is an effusion flow passage. 
     
     
         11 . The liner panel as recited in  claim 8 , wherein said entrance is centered within a hemi-spherical depression. 
     
     
         12 . The liner panel as recited in  claim 8 , wherein at least one of said multiple of impingement flow passages is directed between said hemi-spherical protuberance. 
     
     
         13 . The liner panel as recited in  claim 8 , wherein said at least one passage defines an angle through the liner panel. 
     
     
         14 . A combustor of a gas turbine engine, the combustor comprising:
 a shell with a multiple of impingement flow passages; and   a liner panel mounted to said shell;   said liner panel including a multiple of heat transfer augmentors which extend from a cold side thereof toward said shell;   at least one of said multiple of heat transfer augmentors including a hemi-spherical protuberance with a hemi-spherical depression; and   said hemi-spherical depression including an entrance to at least one passage through said liner panel.   
     
     
         15 . The combustor as recited in  claim 14 , further comprising a plurality of studs which extend from a cold side of said liner panel. 
     
     
         16 . The combustor as recited in  claim 14 , wherein at least one of said multiple of impingement flow passages is directed between said hemi-spherical protuberance. 
     
     
         17 . The liner panel as recited in  claim 14 , wherein said effusion flow passage defines an angle through the liner panel. 
     
     
         18 . The combustor as recited in  claim 14 , wherein at least one of said multiple of impingement flow passages directs an impingement jet between a subset of said multiple of heat transfer augmentors then over and into said a hemi-spherical depression of said hemi-spherical protuberance.