Doppelströmige Turbomaschine

The double flow gas turbine comprises a fan whose blades (17) occupy both primary (10) and secondary (13) gas flow paths separated by a gap (18) between collars (11,12). The collars are interrupted to allow passage of the blades which are provided with internal (19) and external (20) annular platfor...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	WURNIESKY, PASCAL CLAUDE, GUYONNET, XAVIER JEAN-MICHEL ANDRE
Format:	Patent
Sprache:	ger
Schlagworte:	BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS 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 double flow gas turbine comprises a fan whose blades (17) occupy both primary (10) and secondary (13) gas flow paths separated by a gap (18) between collars (11,12). The collars are interrupted to allow passage of the blades which are provided with internal (19) and external (20) annular platforms between the two parts of the collars. These platforms re-establish as far as possible sealing of the air flow paths. The fitting gaps (21) between the platforms and the collars inevitably lead to a loss of gas between the two paths through the gap. An intermediate annular flow path (22), through which gas flow is induced, occupies a part of the gap between the loose fittings. This intermediate path is defined by a third annular platform (23) and the external platform. The diameters of the platform delimiting the intermediate path increase towards the downstream side of the fan.