A fuel nozzle for a combustor of a gas turbine engine

A fuel nozzle (70) for a gas turbine (10) generally includes a main body (72) having an upstream end (78) axially separated from a downstream end (80). The main body at least partially defines a fuel supply passage (86) that extends through the upstream end and at least partially through the main bo...

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Bibliographische Detailangaben
Hauptverfasser:	Thomas, Larry Lou, McMahan, Kevin Weston, Belsom, Keith Cletus
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:	A fuel nozzle (70) for a gas turbine (10) generally includes a main body (72) having an upstream end (78) axially separated from a downstream end (80). The main body at least partially defines a fuel supply passage (86) that extends through the upstream end and at least partially through the main body. A fuel distribution manifold (74) is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages (92) that extend through the fuel distribution manifold. A plurality of fuel injection ports (96) defines a flow path (98) between the fuel supply passage and each of the plurality of axially extending passages.