GAS TURBINE COMPRISING COOLED ROTOR DISKS

A gas turbine comprises a rotor made of a plurality of rotor disks adjacent arranged along the rotor axis and shaped for realizing cavities between the respectively adjacent disks. The rotor comprises a last rotor disk and has a downstream portion for supporting a bearing cover and an upstream porti...

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Bibliographic Details
Main Authors DUSOMOS, Gerard, MCFEAT, Jose Anguisola, DÖBBELING, Klaus
Format Patent
LanguageEnglish
French
German
Published 04.07.2018
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
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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Summary:A gas turbine comprises a rotor made of a plurality of rotor disks adjacent arranged along the rotor axis and shaped for realizing cavities between the respectively adjacent disks. The rotor comprises a last rotor disk and has a downstream portion for supporting a bearing cover and an upstream portion for supporting a last turbine blade. The gas turbine is provided with a cooling duct system configured for supplying cooling air from a downstream end of the turbine section to the last turbine blade passing inside the last rotor disk. The cooling duct system comprises an axial bore in the downstream portion of the last rotor disk along the rotor axis and a first plurality of inclined radial bores in the upstream portion of the last rotor disk off the axis.
Bibliography:Application Number: EP20160207650