Modified floatwall panel dilution hole cooling

Abstract

Aspects of the disclosure are directed to a liner of an aircraft. The liner comprises a panel including at least one dilution hole, a rail coupled to the panel, and at least one effusion cooling hole located between a wall of the at least one dilution hole and a side of the rail. The liner may be associated with a combustion engine of the aircraft.

What is claimed is: 
     
         1 . A liner of an aircraft, comprising:
 a panel including at least one dilution hole;   a rail coupled to the panel; and   at least one effusion cooling hole located between a wall of the at least one dilution hole and a side of the rail.   
     
     
         2 . The liner of  claim 1 , wherein the at least one effusion cooling hole includes a plurality of effusion cooling holes. 
     
     
         3 . The liner of  claim 1 , wherein the rail is spaced from the wall by a distance of approximately 6.4 millimeters. 
     
     
         4 . The liner of  claim 3 , wherein the rail is spaced from the wall in a radial direction away from the at least one dilution hole. 
     
     
         5 . The liner of  claim 1 , further comprising:
 at least a second effusion cooling hole located between a second side of the rail and a perimeter of the panel.   
     
     
         6 . The liner of  claim 1 , further comprising:
 a shell coupled to the panel.   
     
     
         7 . The liner of  claim 6 , wherein the rail is configured to seal the panel against the shell to prevent leakage. 
     
     
         8 . The liner of  claim 1 , wherein the liner is associated with a combustion engine of the aircraft.