GASTURBINE COMBUSTION CHAMBER AND METHOD OF OPERATION THEREOF

A gas turbine engine combustion chamber (36) which has staged combustion to reduce nitrous oxides comprises a first radial flow swirler (70) and a second radial flow swirler (74) which supply primary air into a first fuel and air mixing zone (64). A pilot injector (86) only supplies fuel to be burnt...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	WILLIS, JEFFREY, DOUGLAS, TOON, IAN, JAMES, O'DELL, STEPHEN, JAMES, CURRIN, PAUL, ROYSTON +DI
Format:	Patent
Sprache:	eng
Schlagworte:	AIR 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 METHODSOR APPARATUS FOR COMBUSTION USING FLUID FUELOR SOLID FUEL SUSPENDED IN WEAPONS
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