Combustion device of a gas turbine

The combustion device (1) of a gas turbine comprises burners (2) connected to a front plate (5) of a combustion chamber (3). The front plate (5) comprises, spaced apart 5 from one another, a front sheet (8) and an impingement sheets (7) with aligned holes (11, 12) housing the burners (2). A piston r...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	TSCHUOR, REMIGI, TROBJEVIC, BOGDAN, BENZ, URS
Format:	Patent
Sprache:	eng
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:	The combustion device (1) of a gas turbine comprises burners (2) connected to a front plate (5) of a combustion chamber (3). The front plate (5) comprises, spaced apart 5 from one another, a front sheet (8) and an impingement sheets (7) with aligned holes (11, 12) housing the burners (2). A piston ring (15) is provided between the front sheet (8) and impingement sheet (7) to seal the holes (11, 12). The axial length of the border of the hole (11, 12) of the 10 front sheet (8) and/or impingement sheet (7) is longer than the thickness of the corresponding front sheet (8) and/or impingement sheet (7). (Fig. 3) Fig. 9 Fig. 1016Fg 8 157