Compressor assembly for gas turbine

The present invention generally relates to a compressor assembly, and more in general relates to a compressor for a gas turbine. According to preferred embodiments, the present solution teaches to locate within a cavity formed by the outer casing of the compressor and the inner vane carrier a separa...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Zierer, Thomas, Olmes, Sven, Gomez-Lor-Lopez, Isaac-Eliseo
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The present invention generally relates to a compressor assembly, and more in general relates to a compressor for a gas turbine. According to preferred embodiments, the present solution teaches to locate within a cavity formed by the outer casing of the compressor and the inner vane carrier a separator element, or membrane, such to divide the cavity into two sub-cavities. This advantageously results in a more flexible design with respect to the positioning of the flange blow-off extractor and to the cavity sizing, as the flange position is not necessarily the boundary for the flow anymore as it would be without the separator element.