Combustion Chamber Cooling Method and System

Abstract

A cooling system for use with a gas turbine combustion assembly having a flame tube and a surrounding air delivery sleeve, the system comprising a vessel shaped and dimensioned to surround the air delivery sleeve and adapted for fluid flow there through. A method of cooling a combustion assembly includes the step of directing a flow of fluid over an outer surface of the delivery sleeve.

1 . A method for cooling a gas turbine combustion assembly having a flame tube and a surrounding air delivery sleeve, the method comprising the step of directing a flow of fluid over an outer surface of the delivery sleeve. 
     
     
         2 . A method of  claim 1  further comprising confining the fluid flow along a substantially annular vessel surrounding the delivery sleeve. 
     
     
         3 . A method of  claim 1  further comprising supplying air for cooling the delivery sleeve by bleeding air from a supply for the air delivery sleeve. 
     
     
         4 . A method of  claim 3  comprising the further step of utilizing the air that has cooled the delivery sleeve to drive a compressor for the fuel gas being fed to the flame tube. 
     
     
         5 . A cooling system for use with a gas turbine combustion assembly having a flame tube and a surrounding air delivery sleeve, the system comprising a vessel shaped and dimensioned to surround the air delivery sleeve and adapted for fluid flow there through. 
     
     
         6 . A cooling system of  claim 5 , wherein the vessel is substantially annular in form and comprises a fluid inlet and a fluid outlet. 
     
     
         7 . A cooling system of  claim 5 , wherein the system comprises means for directing air from a supply for the air delivery sleeve to the fluid inlet. 
     
     
         8 . A cooling system of  claim 5 , wherein the system comprises means for directing air from the fluid outlet to a turbine/compressor assembly for compressing the fuel gas to be supplied to the flame tube. 
     
     
         9 . A cooling system for use with a gas turbine combustion assembly having a flame tube and a surrounding air delivery sleeve, the system comprising a substantially annular vessel concentrically surrounding the air delivery sleeve and adapted for fluid flow there through, and a means for directing air, wherein the vessel includes a fluid inlet and a fluid outlet.