COMBUSTOR FUEL MANIFOLD

A gas turbine engine (20) may include a fuel manifold (110; 210; 310; 410) extending circumferentially around a diffuser case (64) of the gas turbine engine (20). The fuel manifold (110; 210; 310; 410) may include a fuel supply inlet interface (112) for receiving fuel into the fuel manifold (110; 21...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	CHEUNG, Albert K
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 gas turbine engine (20) may include a fuel manifold (110; 210; 310; 410) extending circumferentially around a diffuser case (64) of the gas turbine engine (20). The fuel manifold (110; 210; 310; 410) may include a fuel supply inlet interface (112) for receiving fuel into the fuel manifold (110; 210; 310; 410) and a plurality of fuel delivery outlet interfaces (114) for delivering fuel to a combustor (56) of the gas turbine engine (20). The gas turbine engine (20) may also include a valve (120) coupled to the fuel manifold (110; 210; 310; 410). The valve (120) may be configured to control fuel distribution in the fuel manifold (110; 210; 310; 410). The valve (120) may be disposed between two fuel delivery outlet interfaces of the plurality of fuel delivery outlet interfaces (114). The valve (120) may be configured to at least decrease fuel flow to one of the plurality of fuel delivery outlet interfaces (114). The valve (120) may be configured to at least decrease fuel flow to half of the plurality of fuel delivery outlet interfaces (114).