Combustor section of a gas turbine engine

Abstract

A liner for a gas turbine engine includes a cold side having a partition which extends therefrom to define a forward cavity and an aft cavity, each cavity having a plurality of film holes to communicate a coolant from the cold side to the hot side.

What is claimed is: 
     
         1 . A liner for use in a combustor of a gas turbine engine comprising:
 a hot side; and   a cold side with one or more raised rails that project from said cold side to form partitions that define at least a forward cavity and an aft cavity, each said cavity having a plurality of holes to communicate a coolant from said cold side to said hot side.   
     
     
         2 . The liner as recited in  claim 1 , wherein an area of said aft cavity is less than approximately twenty-five percent 25% that of said forward cavity. 
     
     
         3 . The liner as recited in  claim 1 , wherein an axial length of said aft cavity is less than approximately fifteen percent 15% an axial length of said forward cavity. 
     
     
         4 . The liner as recited in  claim 1 , wherein said aft cavity is transverse to a longitudinal length of said liner. 
     
     
         5 . The liner as recited in  claim 1 , further comprising a plurality of studs which extend from said cold side. 
     
     
         6 . The liner as recited in  claim 1 , further comprising a plurality of studs which extend from said cold side, said plurality of studs extend from within said forward cavity. 
     
     
         7 . The liner as recited in  claim 1 , wherein said liner is mountable within a diffuser case module such that said aft cavity is immediately upstream of a Nozzle Guide Vane (NGV). 
     
     
         8 . The liner as recited in  claim 1 , wherein said partition is generally rectilinear to define said aft cavity. 
     
     
         9 . The liner as recited in  claim 8 , wherein a rail of said partition is adjacent to an edge of said liner. 
     
     
         10 . A wall for use in a combustor of a gas turbine engine comprising:
 a shell; and   a liner mountable to said shell to define a forward cavity and an aft cavity, said aft cavity operable at a pressure different than said forward cavity.   
     
     
         11 . The wall as recited in  claim 10 , wherein said aft cavity is operable at a pressure greater than said forward cavity. 
     
     
         12 . The wall as recited in  claim 10 , further comprising a plurality of studs which extend from said liner and through said shell. 
     
     
         13 . The wall as recited in  claim 10 , further comprising a partition which extends from a cold side of said liner into contact with said shell to define said forward cavity and said aft cavity to define a respective pressure. 
     
     
         14 . The wall as recited in  claim 10 , wherein said shell defines a plurality of Cooling impingement holes to communicate coolant into said forward cavity and said aft cavity. 
     
     
         15 . The wall as recited in  claim 10 , wherein said shell defines a plurality of Cooling impingement holes to communicate coolant into said forward cavity and said aft cavity to generate a desired pressure within each. 
     
     
         16 . The wall as recited in  claim 10 , wherein said liner is mountable within a diffuser case module such that said aft cavity is immediately upstream of a Nozzle Guide Vane (NGV) and directly adjacent a mount flange of said shell. 
     
     
         17 . A method of controlling a thermal load in a combustor of a gas turbine engine comprising:
 generating a pressure in an aft cavity of a combustor wall different than a pressure in a forward cavity of the combustor wall, the aft cavity immediately upstream of a Nozzle Guide Vane (NGV).   
     
     
         18 . The method as recited in  claim 17 , further comprising:
 generating a higher pressure in the aft cavity relative to said forward cavity.