Method and apparatus for controlling combustor operability
AssigneeGeneral Electric Company
InventorsGilbert O. Kraemer, John Joseph Lipinski, Jonathan Lloyd Male
Life of this patent
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Abstract
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.
Claims18
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.
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.
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.
Dependencies are inferred from the claim text.