Combustor Cooled Quench Zone Array

Abstract

In accordance with one aspect of the disclosure, a combustor is disclosed. The combustor may include a shell and a liner disposed within the shell. The combustor may further include a grommet at least partially defining a hole communicating through the shell and liner and a cooling channel communicating through the grommet.

What is claimed is: 
     
         1 . A combustor, comprising:
 a shell;   a grommet at least partially defining a hole communicating through at least the shell; and   a cooling channel communicating through the grommet.   
     
     
         2 . The combustor of  claim 1 , wherein the cooling channel is oriented perpendicular to a radially inward surface of the grommet with respect to an axis extending longitudinally through the combustor. 
     
     
         3 . The combustor of  claim 1 , wherein the cooling channel is provided at a non-perpendicular angle to the radially inward surface of the grommet. 
     
     
         4 . The combustor of  claim 3 , wherein the cooling channel communicates through the grommet from a surrounding surface of the grommet oriented perpendicular to the shell of the combustor and facing away from the hole defined by the grommet to the radially inward surface of the grommet. 
     
     
         5 . The combustor of  claim 4 , wherein the shell is engaged with a radially outward surface of the grommet with respect to the axis of the combustor. 
     
     
         6 . The combustor of  claim 1 , wherein between six to sixteen cooling channels communicate through the grommet. 
     
     
         7 . The combustor of  claim 1 , wherein each cooling channel is separated by a distance about equal to three to ten times the diameter of the cooling channels. 
     
     
         8 . The combustor of  claim 1 , wherein the grommet has a second radially outward surface with respect to the axis of the combustor engaged with the shell of the combustor. 
     
     
         9 . The combustor of  claim 1 , wherein the grommet is unitary with the shell and defines a hole communicating through the shell. 
     
     
         10 . The combustor of  claim 1 , wherein the grommet is separate from the shell and a liner of the combustor, the liner being positioned radially inside the shell with respect to the axis of the combustor, and the grommet being positioned between the shell and liner. 
     
     
         11 . A liner of a combustor, comprising:
 a liner panel having a hot surface;   a grommet defining a hole communicating through the liner panel; and   a cooling channel communicating through the grommet.   
     
     
         12 . The liner of  claim 11 , wherein the grommet has a radially inward surface and a radially outward surface with respect to an axis extending longitudinally through the combustor, and the cooling channel extends from the radially outward surface of the grommet to the radially inward surface of the grommet. 
     
     
         13 . The liner of  claim 11 , wherein the cooling channel is at a non-perpendicular angle to the radially inward surface of the grommet. 
     
     
         14 . The liner of  claim 13 , wherein the cooling channel communicates through the grommet from a surrounding surface of the grommet perpendicular to the radially outward surface of the grommet and facing away from the hole defined by the grommet to the radially inward surface of the grommet. 
     
     
         15 . The liner of  claim 11 , wherein between six to sixteen cooling channels communicate through the grommet. 
     
     
         16 . The liner of  claim 11 , wherein each cooling channel is separated by a distance about equal to three to ten times the diameter of the cooling channels. 
     
     
         17 . The liner of  claim 11 , wherein the grommet is unitary with the liner panel and the radially inward surface of the grommet is the same surface as the hot surface of the liner panel. 
     
     
         18 . The liner of  claim 11 , wherein the grommet is a dilution hole grommet and defines a dilution hole. 
     
     
         19 . A method of cooling a liner of a combustor, comprising:
 providing a grommet with the liner of the combustor, the grommet at least partially defining a hole through the liner panel;   directing cooling air through a cooling channel communicating through the grommet; and   cooling the grommet with the cooling air flowing through the cooling channel by transferring heat from the grommet to the cooling air.   
     
     
         20 . The method of  claim 19 , further comprising blowing a flame in the combustor off the inward surface of the grommet with the cooling air flowing through the cooling channel.