Method and apparatus for controlling combustor operability
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...
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| Format: | Patent |
| Sprache: | eng |
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| Zusammenfassung: | 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. |
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