GAS TURBINE COMBUSTION DEVICE

The combustion device (1) of a gas turbine includes burners (2) connected to a front plate (5) of a combustion chamber (3). The front plate (5) has, spaced apart from one another, a front sheet (8) and an impingement sheet (7) with aligned holes (11, 12) housing the burners (2). A piston ring (15) i...

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Bibliographische Detailangaben
Hauptverfasser:	BENZ URS, TRBOJEVIC BOGDAN, TSCHUOR REMIGI
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS 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 SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS WEAPONS
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Beschreibung
Zusammenfassung:	The combustion device (1) of a gas turbine includes burners (2) connected to a front plate (5) of a combustion chamber (3). The front plate (5) has, spaced apart from one another, a front sheet (8) and an impingement sheet (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 front sheet (8) and/or impingement sheet (7) is longer than the thickness of the corresponding front sheet (8) and/or impingement sheet (7).