FUEL MANIFOLD ASSEMBLY

A fuel supply assembly (20) for a gas turbine engine (10) comprises a plurality of fuel injectors (22, 22A, 22B) configured for mounting circumferentially to an engine casing (17) of the gas turbine engine (10) and to be serially interconnected. At least one pair (122, 222) of the plurality of the f...

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Bibliographische Detailangaben
Hauptverfasser:	MORENKO, Oleg, KOJOVIC, Aleksandar, BOND, Bryan Michael
Format:	Patent
Sprache:	eng ; fre ; ger
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 supply assembly (20) for a gas turbine engine (10) comprises a plurality of fuel injectors (22, 22A, 22B) configured for mounting circumferentially to an engine casing (17) of the gas turbine engine (10) and to be serially interconnected. At least one pair (122, 222) of the plurality of the fuel injectors (22, 22A, 22B) has a first fuel injector (22A) including a first manifold adapter (26A) having a first outlet (30A) defined around a first outlet axis (31A), and a first stem (28A) connected to the first manifold adapter (26A) at the first outlet (30A) and extending longitudinally along a first stem axis (29A); and a second fuel injector (22B) including a second manifold adapter (26B) having a second outlet (30B) defined around a second outlet axis (31B), and a second stem (28B) connected to the second manifold adapter (26B) at the second outlet (30B), the first and second outlet axes (31A, 31B) being disposed circumferentially between the first and second stem axes (29A, 29B).