Resonator for damping acoustic frequencies in combustion systems by optimizing impingement holes and shell volume

Abstract

A resonator in a combustor of a gas turbine comprises a flow sleeve defining an air path to provide air flow to a combustion chamber of the combustor, and one or more impingement holes disposed on the flow sleeve tuned to a damping frequency.

What is claimed is: 
     
         1 . A combustor of a gas turbine, comprising:
 a combustion chamber in which mixture of air and fuel is combusted;   a flow sleeve defining an air path to provide air flow to the combustion chamber; and   one or more impingement holes disposed on the flow sleeve tuned to a damping frequency.   
     
     
         2 . The combustor of  claim 1 , wherein the one or more impingement holes and a shell volume of the combustor forms a Helmholtz resonator tuned to the damping frequency. 
     
     
         3 . The combustor of  claim 1 , wherein at least one of the one or more impingement holes is disposed at an anti-node location within the combustor. 
     
     
         4 . The combustor of  claim 1 , wherein the one or more impingement holes are cylindrical. 
     
     
         5 . The combustor of  claim 1 , wherein the one or more impingement holes are polygonal. 
     
     
         6 . The combustor of  claim 1 , wherein the one or more impingement holes have different shapes. 
     
     
         7 . The combustor of  claim 1 , wherein the one or more impingement holes have different sizes. 
     
     
         8 . A resonator in a combustor of a gas turbine, comprising:
 a flow sleeve defining an air path to provide air flow to a combustion chamber of the combustor; and   one or more impingement holes disposed on the flow sleeve tuned to a damping frequency.   
     
     
         9 . The resonator of  claim 8 , wherein the one or more impingement holes and a shell volume of the combustor forms a Helmholtz resonator tuned to the damping frequency. 
     
     
         10 . The resonator of  claim 8 , wherein at least one of the one or more impingement holes is disposed at an anti-node location within the combustor. 
     
     
         11 . The resonator of  claim 8 , wherein the one or more impingement holes are cylindrical. 
     
     
         12 . The resonator of  claim 8 , wherein the one or more impingement holes are polygonal. 
     
     
         13 . The resonator of  claim 8 , wherein the one or more impingement holes have different shapes. 
     
     
         14 . The resonator of  claim 8 , wherein the one or more impingement holes have different sizes. 
     
     
         15 . A method of damping acoustic frequencies in a combustor of a gas turbine, comprising the steps of:
 providing air flow to a combustion chamber through an air path defined by a flow sleeve to form an air and fuel mixture in the combustion chamber;   combusting the air and fuel mixture in the combustion chamber; and   generating at least one damping frequency via one or more impingement holes disposed on the flow sleeve tuned to the at least one damping frequency to damp acoustic frequencies generated by the combusting.   
     
     
         16 . The method of  claim 15 , wherein the one or more impingement holes and a shell volume of the combustor forms a Helmholtz resonator tuned to the damping frequency. 
     
     
         17 . The method of  claim 15 , wherein at least one of the one or more impingement holes is disposed at an anti-node location within the combustor. 
     
     
         18 . The method of  claim 15 , wherein the one or more impingement holes have different shapes. 
     
     
         19 . The method of  claim 15 , wherein the one or more impingement holes have different sizes. 
     
     
         20 . The method of  claim 15 , wherein the one or more impingement holes are cylindrical or polygonal.