ASSEMBLY FOR A GAS TURBINE

The present document concerns an assembly (46a, 46b) for a gas turbine comprising a nozzle having radial blades (54) linked at their radially inner ends to an inner annular platform (52) and at their radially outer ends to an outer annular platform, in which at least one of the inner annular platfor...

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Bibliographische Detailangaben
Hauptverfasser:	BETBEDER- LAÜQUE, Xavier, Roger, OBERMANN, Guillaume, PLAINO, Cédric, Jean Daniel, RENAULT, Lionel, Victor, George, PEDARAZACQ, David
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES ENGINE PLANTS IN GENERAL GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The present document concerns an assembly (46a, 46b) for a gas turbine comprising a nozzle having radial blades (54) linked at their radially inner ends to an inner annular platform (52) and at their radially outer ends to an outer annular platform, in which at least one of the inner annular platform (52) and the outer annular platform (50) is linked to an angled annular portion (58a, 58b) formed in one piece with the annular platform (50, 52) to which it is linked.