AXIAL COMPRESSOR AND ASSOCIATED OPERATING METHOD

PROBLEM TO BE SOLVED: To provide an axial compressor, especially for a gas turbine, for compressing a flow medium.SOLUTION: The compressor includes a plurality of compressor stator blades, which are assembled to form stator blade rows and fastened in each case on a stator blade carrier, and a plural...

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Bibliographische Detailangaben
Hauptverfasser:	HOELL HARALD, DUNGS SASCHA, BENKLER FRANCOIS
Format:	Patent
Sprache:	eng
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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 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:	PROBLEM TO BE SOLVED: To provide an axial compressor, especially for a gas turbine, for compressing a flow medium.SOLUTION: The compressor includes a plurality of compressor stator blades, which are assembled to form stator blade rows and fastened in each case on a stator blade carrier, and a plurality of compressor rotor blades, which are assembled to form rotor blade rows and fastened in each case on a compressor disk of a compressor shaft, wherein two consecutive compressor disks in each case enclose a hollow space lying between them, and wherein the last compressor disk, as seen in the flow direction of the flow medium, delimits a rear hollow space.