COMBUSTION CHAMBER ASSEMBLY FOR OPERATION WITH LIQUID AND/OR GASEOUS FUEL, GAS TURBINE ASSEMBLY AND METHOD

The invention concerns a combustion chamber assembly, in particular for use in an aircraft engine, including:a peripheral wall which borders a combustion space oriented along a longitudinal axis, andat least one, preferably a plurality of fuel nozzle(s) arranged on the input side of the combustion s...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	DÖRR, Thomas, CLEMEN, Carsten
Format:	Patent
Sprache:	eng
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
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Beschreibung
Zusammenfassung:	The invention concerns a combustion chamber assembly, in particular for use in an aircraft engine, including:a peripheral wall which borders a combustion space oriented along a longitudinal axis, andat least one, preferably a plurality of fuel nozzle(s) arranged on the input side of the combustion space for the supply of liquid fuel to the combustion space.An alternative and/or combined optimised operation with fuels of different aggregate states can be achieved with comparatively low structural complexity in that the combustion chamber assembly is configured for operation with liquid and/or gaseous fuel, wherein at least one, preferably a plurality of gas supply openings arranged downstream of the fuel nozzle(s) on the peripheral wall is/are present, by means of which gaseous fuel can be introduced into the combustion space.