FUEL NOZZLE AND A COMBUSTOR FOR A GAS TURBINE

A fuel nozzle for a gas turbine includes an annular passage configured to flow a fuel and a disk concentric with and disposed at a second end of the annular passage. The disk extends radially outward from the second end. A plurality of passages extend through the disk and are configured to impart sw...

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Bibliographische Detailangaben
Hauptverfasser:	SIDDAGANGAIAH PRABHU KUMAR IPPADI, KALEESWARAN KARTHICK
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A fuel nozzle for a gas turbine includes an annular passage configured to flow a fuel and a disk concentric with and disposed at a second end of the annular passage. The disk extends radially outward from the second end. A plurality of passages extend through the disk and are configured to impart swirl to a working fluid flowing through the passages. A shroud including an upstream end axially separated from a downstream end surrounds the disk and extends downstream from the disk.