Combustor for gas turbine engine

A gas turbine engine comprises a combustor (16). The combustor (16) comprises an annular combustor chamber formed between an inner liner (20) and an outer liner (30) spaced apart from the inner liner (20). An annular fuel manifold (40) has fuel nozzles distributed circumferentially on the fuel manif...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
1. Verfasser:	MORENKO, OLEG
Format:	Patent
Sprache:	eng ; pol
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A gas turbine engine comprises a combustor (16). The combustor (16) comprises an annular combustor chamber formed between an inner liner (20) and an outer liner (30) spaced apart from the inner liner (20). An annular fuel manifold (40) has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold (40) and fuel nozzles positioned entirely inside the combustion chamber.