Stud arrangement for gas turbine engine combustor

Abstract

A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a stud free zone downstream of a combustor swirler. A combustor for a gas turbine engine, the combustor including a liner panel mounted to the support shell via a multiple of studs, the liner panel including a stud free zone downstream of each respective combustor swirler, the stud free zone including a multiple of film cooling holes. A method of directing airflow through a wall assembly within a combustor of a gas turbine engine including providing a stud free zone in a forward liner panel downstream of a combustor swirler, the stud free zone including a multiple of film cooling holes.

What is claimed is: 
     
         1 . A liner panel for use in a combustor of a gas turbine engine, the liner panel comprising:
 a stud free zone downstream of a combustor swirler.   
     
     
         2 . The liner panel as recited in  claim 1 , wherein the stud free zone is trapezoidal in shape. 
     
     
         3 . The liner panel as recited in  claim 1 , wherein the stud free zone is defined by a forward liner panel. 
     
     
         4 . The liner panel as recited in  claim 3 , further comprising an aft liner panel aft of the forward liner panel. 
     
     
         5 . The liner panel as recited in  claim 4 , further comprising an aft stud free zone downstream of the forward liner panel stud free zone. 
     
     
         6 . The liner panel as recited in  claim 5 , further comprising at least one major diffusion aperture an aft stud free zone downstream of the forward liner panel stud free zone. 
     
     
         7 . The liner panel as recited in  claim 1 , wherein the stud free zone is trapezoidal in shape and defined by a forward liner panel. 
     
     
         8 . The liner panel as recited in  claim 7 , wherein the stud free zone is located toward an aft edge of the forward liner panel. 
     
     
         9 . The liner panel as recited in  claim 7 , wherein the stud free zone is defined by a truncated triangle with a truncated apex located at combustor swirler. 
     
     
         10 . The liner panel as recited in  claim 7 , wherein the stud free zone includes a multiple of film cooling holes. 
     
     
         11 . A combustor for a gas turbine engine comprising:
 a support shell; and   a liner panel mounted to the support shell via a multiple of studs, the liner panel including a stud free zone downstream of each respective combustor swirler, the stud free zone including a multiple of film cooling holes.   
     
     
         12 . The combustor as recited in  claim 11 , further comprising:
 a forward assembly including a bulkhead support shell, a bulkhead assembly mounted to the bulkhead support shell, and a multiple of the combustor swirlers mounted at least partially through the bulkhead assembly.   
     
     
         13 . The combustor as recited in  claim 12 , wherein the forward assembly is mounted to the support shell. 
     
     
         14 . The combustor as recited in  claim 13 , further comprising a multiple of circumferentially distributed bulkhead liner panels secured to the bulkhead support shell around the swirler opening. 
     
     
         15 . The combustor as recited in  claim 14 , wherein the stud free zone is defined by a forward liner panel. 
     
     
         16 . The combustor as recited in  claim 15 , further comprising an aft liner panel downstream of the forward liner panel, an aft stud free zone downstream of the forward liner panel stud free zone. 
     
     
         17 . A method of directing airflow through a wall assembly within a combustor of a gas turbine engine, comprising:
 providing a stud free zone in a forward liner panel downstream of a combustor swirler, the stud free zone including a multiple of film cooling holes.   
     
     
         18 . The method as recited in  claim 17 , further comprising locating a dilution passage within an aft stud free zone in an aft liner panel, the aft liner panel downstream of the forward liner panel. 
     
     
         19 . The method as recited in  claim 17 , further comprising defining the stud free zone in the forward liner panel as a trapezoidal shape. 
     
     
         20 . The method as recited in  claim 17 , further comprising defining the stud free zone in the forward liner panel as a truncated triangle with a truncated apex located adjacent to the combustion swirler.