METHOD FOR REPAIRING A ROTOR OF A MULTI-STAGE AXIAL COMPRESSOR OF A GAS TURBINE

The method comprises the steps of: a) cutting the shaft of the rotor at a section plane perpendicular to the axis of rotation of the shaft so as to separate the end portion of the shaft on which the bladed discs to be replaced are mounted from the remaining portion of the shaft; b) providing, for ea...

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Bibliographic Details
Main Authors Valsania, Massimo, Forno, Luca
Format Patent
LanguageEnglish
Published 12.03.2020
Subjects
BLASTING
COMBINED OPERATIONS
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINE TOOLS
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
METAL-WORKING NOT OTHERWISE PROVIDED FOR
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
OTHER WORKING OF METAL
PERFORMING OPERATIONS
STEAM ENGINES
TRANSPORTING
UNIVERSAL MACHINE TOOLS
WEAPONS
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Summary:The method comprises the steps of: a) cutting the shaft of the rotor at a section plane perpendicular to the axis of rotation of the shaft so as to separate the end portion of the shaft on which the bladed discs to be replaced are mounted from the remaining portion of the shaft; b) providing, for each bladed disc to be replaced, a corresponding new bladed disc with a respective hub having a solid cross-section; c) providing a new end portion of the shaft with a solid cross-section; and d) clamping the new bladed discs between the remaining portion of the shaft and the new end portion of the shaft, securing them to the remaining portion of the shaft by anchor bolts.
Bibliography:Application Number: US201916562058