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

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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