Combustion panel grommet

Abstract

A gas turbine engine and a combustor panel assembly are disclosed. The gas turbine engine includes a combustor panel with a panel dilution hole formed therethrough, a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material, and a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.

What is claimed is: 
     
         1 . A combustor panel assembly for use with a combustor, the combustor panel assembly comprising:
 a combustor panel with a panel dilution hole formed therethrough;   a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material; and   a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.   
     
     
         2 . The combustor panel assembly of  claim 1 , wherein the grommet has a frustroconical shape. 
     
     
         3 . The combustor panel assembly of  claim 1 , wherein the second material is a ceramic matric composite. 
     
     
         4 . The combustor panel assembly of  claim 1 , wherein the second material is a molybdenum alloy. 
     
     
         5 . The combustor panel assembly of  claim 1 , wherein the second material is a nickel alloy. 
     
     
         6 . The combustor panel assembly of  claim 1 , wherein the second material is a monolithic ceramic. 
     
     
         7 . The combustor panel assembly of  claim 1 , wherein the grommet is affixed to the combustor panel. 
     
     
         8 . The combustor panel assembly of  claim 7 , wherein the grommet is affixed to the combustor panel via a fastener. 
     
     
         9 . The combustor panel assembly of  claim 7 , wherein the grommet is affixed to the combustor panel via a brazed joint. 
     
     
         10 . The combustor panel assembly of  claim 7 , wherein the grommet is affixed to the combustor panel via a welded joint. 
     
     
         11 . The combustor panel assembly of  claim 7 , wherein the grommet is affixed to the combustor panel via a threaded connection. 
     
     
         12 . A combustor, comprising:
 a combustor panel with a panel dilution hole formed therethrough;   a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material; and   a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.   
     
     
         13 . The combustor of  claim 12 , wherein the grommet has a frustroconical shape. 
     
     
         14 . The combustor of  claim 12 , wherein the second material is a ceramic matric composite. 
     
     
         15 . The combustor of  claim 12 , wherein the second material is a molybdenum alloy. 
     
     
         16 . The combustor of  claim 12 , wherein the second material is a nickel alloy. 
     
     
         17 . A gas turbine engine, comprising:
 a combustor, including:
 a combustor panel with a panel dilution hole formed therethrough; 
 a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material; and 
 a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material. 
   
     
     
         18 . The gas turbine engine of  claim 17 , wherein the grommet has a frustroconical shape. 
     
     
         19 . The gas turbine engine of  claim 17 , wherein the second material is a ceramic matric composite. 
     
     
         20 . The gas turbine engine of  claim 17 , wherein the second material is a molybdenum alloy.