Catalytically Stabilized Gas Turbine Combustor

Abstract

A gas turbine combustor. The gas turbine combustor may include a central combustion nozzle with a catalyst therein and a number of outer combustion nozzles surrounding the central combustion nozzle.

1 . A gas turbine combustor, comprising:
 a central combustion nozzle;   the central combustion nozzle comprising a catalyst therein; and   a plurality of outer combustion nozzles surrounding the central combustion nozzle.   
   
   
       2 . The gas turbine combustor of  claim 1 , wherein the plurality of outer combustion nozzles comprises five (5) combustion nozzles. 
   
   
       3 . The gas turbine combustor of  claim 1 , wherein the central combustion nozzle comprises a central combustion nozzle manifold. 
   
   
       4 . The gas turbine combustor of  claim 1 , wherein the catalyst comprises precious metals, Group VIII noble metals, base metals, metal oxides, or a combination thereof. 
   
   
       5 . The gas turbine combustor of  claim 1 , wherein the catalyst comprises zirconium, vanadium, chromium, manganese, copper, platinum, palladium, osmium, iridium, rhodium, cerium, lanthanum, other elements of the lanthanide series, cobalt, nickel, or iron. 
   
   
       6 . The gas turbine combustor of  claim 1 , wherein the central combustion nozzle comprises a combustion stream in a temperature range of about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius). 
   
   
       7 . The gas turbine combustor of  claim 1 , wherein one or more of the plurality of outer combustion nozzles comprise a catalyst therein. 
   
   
       8 . The gas turbine combustor of  claim 1 , wherein the catalyst comprises one or more catalyst layers. 
   
   
       9 . A method operating a gas turbine combustor with a central combustion nozzle and a plurality of outer combustion nozzles, comprising:
 positioning a catalyst within the central combustion nozzle; and   modulating a fuel-air mixture exiting the central combustion nozzle to a temperature range of about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius).   
   
   
       10 . The method of  claim 9 , further comprising modulating a fuel-air mixture exiting the plurality of outer combustion nozzles to a temperature less than about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius). 
   
   
       11 . The method of  claim 9 , further comprising positioning a catalyst within one or more of the outer combustion nozzles. 
   
   
       12 . A gas turbine combustor, comprising:
 a catalytic combustion nozzle;   the catalytic combustion nozzle comprising a catalyst therein; and   a plurality of non-catalytic combustion nozzles positioned about the catalytic combustion nozzle.   
   
   
       13 . The gas turbine combustor of  claim 12 , wherein the catalytic combustion nozzle comprise a central combustion nozzle and wherein the plurality of non-catalytic combustion nozzles comprise a plurality of non-catalytic nozzles surrounding the central combustion nozzle. 
   
   
       14 . The gas turbine combustor of  claim 12 , wherein the catalytic combustion nozzle comprises a catalytic combustion nozzle manifold. 
   
   
       15 . The gas turbine combustor of  claim 12 , wherein the catalyst comprises precious metals, Group VIII noble metals, base metals, metal oxides, or a combination thereof. 
   
   
       16 . The gas turbine combustor of  claim 12 , wherein the catalyst comprises zirconium, vanadium, chromium, manganese, copper, platinum, palladium, osmium, iridium, rhodium, cerium, lanthanum, other elements of the lanthanide series, cobalt, nickel, or iron. 
   
   
       17 . The gas turbine combustor of  claim 12 , wherein the catalytic combustion nozzle comprises a combustion stream in a temperature range of about 1000 to about 1500 degrees Fahrenheit (about 538 to about 816 degrees Celsius). 
   
   
       18 . The gas turbine combustor of  claim 12 , further comprises a plurality of catalytic combustion nozzles. 
   
   
       19 . The gas turbine combustor of  claim 12 , wherein the catalyst comprises one or more catalyst layers.