System for vibration damping of a fuel nozzle within a combustor

Abstract

A system for vibration damping a fuel nozzle within a combustor includes a support plate, a fuel nozzle passage that extends through the support plate and a cylindrical damping insert that is coaxially aligned within the fuel nozzle passage and at least partially defines the fuel nozzle passage. The damping insert may include a metallic-mesh liner.

What is claimed: 
     
         1 . A system for vibration damping a fuel nozzle within a combustor, comprising:
 a. a support plate;   b. a fuel nozzle passage that extends through the support plate; and   c. a cylindrical damping insert coaxially aligned within the fuel nozzle passage, wherein the damping insert at least partially defines the fuel nozzle passage.   
     
     
         2 . The system as in  claim 1 , wherein the damping insert comprises a metallic-mesh liner. 
     
     
         3 . The system as in  claim 2 , wherein the damping insert comprises an annular inner sleeve and an annular outer sleeve, the metallic-mesh liner being disposed between the inner sleeve and the outer sleeve. 
     
     
         4 . The system as in  claim 2 , wherein the damping insert comprises an outer sleeve that at least partially surrounds the metallic-mesh liner. 
     
     
         5 . The system as  claim 2 , wherein the damping insert comprises an annular ring that surrounds the metallic-mesh liner, wherein the annular ring is coupled to the support plate. 
     
     
         6 . The system as in  claim 5 , wherein the damping insert comprises an inner sleeve coaxially aligned within the annular ring, the metallic-mesh liner being disposed between the inner sleeve and the annular ring. 
     
     
         7 . The system as in  claim 1 , wherein the damping insert includes an expansion gap. 
     
     
         8 . The system as in  claim 1 , wherein the damping insert includes an outer sleeve having at least one retaining feature, the system further comprising a retaining plate that extends circumferentially around at least a portion of the fuel nozzle passage, wherein the retainer plate extends at least partially across the retaining feature. 
     
     
         9 . A combustor for a gas turbine, comprising:
 a. an outer casing and an end cover that is coupled to the outer casing;   b. a fuel nozzle that extends downstream from the end cover within the outer casing;   c. a cap assembly that extends radially and axially within the outer casing, the cap assembly having a support plate and a cap plate disposed downstream from the support plate, the cap plate having an opening;   d. a fuel nozzle passage that extends through the support plate, wherein the fuel nozzle extends at least partially through the fuel nozzle passage and the opening of the cap plate; and   e. a cylindrical damping insert coaxially aligned within the fuel nozzle passage, wherein the damping insert extends circumferentially around the fuel nozzle.   
     
     
         10 . The combustor as in  claim 9 , wherein the damping insert comprises a metallic-mesh liner. 
     
     
         11 . The combustor as in  claim 10 , wherein the damping insert comprises an annular inner sleeve and an annular outer sleeve, the metallic-mesh liner being disposed between the inner sleeve and the outer sleeve. 
     
     
         12 . The combustor as in  claim 10 , wherein the damping insert comprises an outer sleeve that at least partially surrounds the metallic-mesh liner. 
     
     
         13 . The combustor as in  claim 10 , wherein the damping insert comprises an annular ring that surrounds the metallic-mesh liner, wherein the annular ring is coupled to the support plate. 
     
     
         14 . The combustor as in  claim 13 , wherein the damping insert comprises an inner sleeve coaxially aligned within the annular ring, the metallic-mesh liner being disposed between the inner sleeve and the annular ring. 
     
     
         15 . The combustor as in  claim 10 , wherein the damping insert includes an expansion gap. 
     
     
         16 . A gas turbine, comprising:
 a. a compressor;   b. a combustor downstream from the compressor, the combustor having an outer casing, an end cover coupled to the outer casing and a fuel nozzle that extends axially downstream from the end cover within the outer casing;   c. a turbine disposed downstream from the combustor; and   d. a system for vibration damping of the fuel nozzle, wherein the system is disposed within the outer casing downstream from the end cover, the vibration damping system comprising:
 i. a support plate; 
 ii. a fuel nozzle passage that extends through the support plate; and 
 iii. a cylindrical damping insert coaxially aligned within the fuel nozzle passage, the damping insert comprising a metallic-mesh liner that circumferentially surrounds a portion of the fuel nozzle, wherein the damping insert at least partially defines the fuel nozzle passage. 
   
     
     
         17 . The gas turbine as in  claim 16 , wherein the damping insert comprises an annular inner sleeve and an annular outer sleeve, the metallic-mesh liner being disposed between the inner sleeve and the outer sleeve. 
     
     
         18 . The gas turbine as in  claim 17 , wherein the damping insert includes an expansion gap. 
     
     
         19 . The gas turbine as in  claim 16 , wherein the damping insert comprises an outer sleeve that at least partially surrounds the metallic-mesh liner. 
     
     
         20 . The combustor as in  claim 10 , wherein the damping insert comprises an annular ring that surrounds the metallic-mesh liner, wherein the annular ring is coupled to the support plate.