COMPACT TURBOMACHINE COMBUSTOR

COMPACT TURBOMACHINE COMBUSTOR

Combustors (14), gas turbines (10), and associated methods of operation are provided. A method for operating a combustor (14) includes firing a bundled tube fuel nozzle assembly (100) within a combustion liner (36) of the combustor (14) to generate combustion gases (26) at a first temperature within...

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Bibliographische Detailangaben
Hauptverfasser: ZIMINSKY, Willy Steve, STOIA, Lucas John, NATARAJAN, Jayaprakash, PINSON, Mark William
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Beschreibung
Zusammenfassung:Combustors (14), gas turbines (10), and associated methods of operation are provided. A method for operating a combustor (14) includes firing a bundled tube fuel nozzle assembly (100) within a combustion liner (36) of the combustor (14) to generate combustion gases (26) at a first temperature within a first combustion zone length (92). The method further includes firing a fuel injector (60) downstream from the bundled tube fuel nozzle assembly (100) within the combustion liner (36) of the combustor (14) to generate combustion gases (26) at a second temperature within a second combustion zone length (94). The first combustion zone length (92) is less than the second combustion zone length (94). The combustion gases (26) travel through the first combustion zone length (92) in a first time period and through the second combustion zone length (94) in a second time period. The second time period is less than the first time period.