초록 ▼

A method for assembling a gas turbine engine includes providing at least one combustor assembly defining a combustion chamber. At least one fuel nozzle is positioned at a forward end of the combustion chamber. The at least one fuel nozzle is configured to inject a premixed fuel/air mixture into the

A method for assembling a gas turbine engine includes providing at least one combustor assembly defining a combustion chamber. At least one fuel nozzle is positioned at a forward end of the combustion chamber. The at least one fuel nozzle is configured to inject a premixed fuel/air mixture into the combustion chamber. A catalytic material is applied to at least a portion of the at least one fuel nozzle.

대표청구항 ▼

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: providing at least one combustor assembly defining a combustion chamber; positioning at least one fuel nozzle at a forward end of the combustion chamber, the at least one fuel nozzle configured to inject a

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: providing at least one combustor assembly defining a combustion chamber; positioning at least one fuel nozzle at a forward end of the combustion chamber, the at least one fuel nozzle configured to inject a premixed fuel/air mixture into the combustion chamber; bonding a thermal insulating coating to at least a portion of the at least one fuel nozzle; and applying a catalytic material to at least a portion of the thermal insulating coating. 2. A method in accordance with claim 1 further comprising arranging a plurality of fuel nozzles around the at least one fuel nozzle. 3. A method in accordance with claim 1 wherein said applying a catalytic material to at least a portion of the at least one fuel nozzle further comprises coating an inner surface of the at least one fuel nozzle with the catalytic material. 4. A method in accordance with claim 1 wherein said applying a catalytic material to at least a portion of the at least one fuel nozzle further comprises coating a tip portion of the at least one fuel nozzle with the catalytic material. 5. A method in accordance with claim 1 wherein said positioning at least one fuel nozzle at a forward end of the combustion chamber further comprises providing the at least one fuel nozzle that includes a tip portion that defines a concave region. 6. A method in accordance with claim 5 wherein said applying a catalytic material to at least a portion of the at least one fuel nozzle further comprises coating at least a portion of the concave region with the catalytic material. 7. A method in accordance with claim 1 wherein said applying a catalytic material to at least a portion of the at least one fuel nozzle further comprises bonding the catalytic material to at least one of a metal surface, a thermal barrier coating and a wash coat bonded to the at least one fuel nozzle. 8. A method in accordance with claim 1 wherein said providing at least one combustor assembly defining a combustion chamber further comprises providing at least one combustor assembly that includes a center fuel nozzle substrate surface region that defines a concave interior surface. 9. A method in accordance with claim 8 wherein said applying a catalytic material to at least a portion of the at least one fuel nozzle further comprises coating the concave interior surface with the catalytic material for facilitating developing a reactive fuel/air mixture to enhance flame stabilization. 10. A method in accordance with claim 1 further comprising: providing the at least one fuel nozzle having a substrate surface region defining a concave interior surface; applying at least one thermal barrier coating layer to the substrate surface region; and applying a catalytic coating to an outer thermal barrier layer for facilitating developing a reactive fuel/air mixture to enhance flame stabilization. 11. A gas turbine engine comprising: a combustor defining a combustion chamber; a plurality of fuel nozzles positioned at a forward end of said combustion chamber such that each of said plurality of fuel nozzles is positioned to inject a premixed fuel/air mixture into said combustion chamber, a thermal insulating coating bonded to at least a portion of at least one of said plurality of fuel nozzles, and a catalytic material bonded to said thermal insulating coating. 12. A gas turbine engine in accordance with claim 11 wherein said plurality of fuel nozzles further comprises a plurality of outer fuel nozzles arranged around at least one center fuel nozzle. 13. A gas turbine engine in accordance with claim 11 wherein an inner surface of said at least one fuel nozzle is coated with said catalytic material. 14. A gas turbine engine in accordance with claim 11 wherein a tip portion of said at least one fuel nozzle is coated with said catalytic material. 15. A gas turbine engine in accordance with claim 14 wherein said tip portion forms a concave interior surface region, at least a portion of said concave interior surface region coated with said catalytic material. 16. A gas turbine engine in accordance with claim 11 wherein said catalytic material is bonded to at least one of a metal surface of said at least one fuel nozzle, a thermal insulating coating bonded to said at least one fuel nozzle and a wash coat bonded to said at least one fuel nozzle. 17. A nozzle assembly for a gas turbine engine, said nozzle assembly comprising: a fuel nozzle comprising a substrate surface region, said substrate surface region defining a concave interior surface region of said fuel nozzle; a thermal insulating coating applied to said concave interior surface region; and a catalytic material applied to said thermal insulating material. 18. A nozzle assembly in accordance with claim 17 further comprising a wash coat applied to said substrate surface region, said catalytic material dispersed within said wash coat.