Dual orifice pilot fuel injector

A gas turbine engine fuel nozzle assembly (12) has concentric primary and secondary pilot fuel nozzles (58, 59) with circular primary and annular secondary exits (98, 100) respectively and a main fuel nozzle (61) spaced radially outwardly of the pilot fuel nozzles (58, 59). The primary and secondary...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	HSIAO, GEORGE CHIAUN, MANCINI, ALFRED ALBERT, BENJAMIN, MICHAEL ANTHONY, CHAUVETTE, CLAUDE HENRY
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A gas turbine engine fuel nozzle assembly (12) has concentric primary and secondary pilot fuel nozzles (58, 59) with circular primary and annular secondary exits (98, 100) respectively and a main fuel nozzle (61) spaced radially outwardly of the pilot fuel nozzles (58, 59). The primary and secondary pilot fuel nozzles (58, 59) include conical primary and secondary exit holes (166, 167) respectively. The secondary pilot fuel nozzle (59) is located directly adjacent to and surrounding the primary pilot fuel nozzle (58). Alternatively the secondary pilot fuel nozzle (59) may be radially spaced apart from the primary pilot fuel nozzle (58). A fuel injector (10) having a hollow stem (32) may be used to support the fuel nozzle assembly (12). A first pilot swirler (112) may be located radially outwardly of and adjacent to the dual orifice pilot fuel injector tip (57), a second pilot swirler (114) located radially outwardly of the first swirler (112), and a splitter (116) radially positioned between the first and second pilot swirlers (112, 114).