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Method and auxiliary device for balancing a gas turbine rotor

A technology of gas turbines and gas turbines, which is applied to mechanical equipment, engine components, machines/engines, etc., and can solve problems such as complex rotation angles, failures, and inappropriateness

Active Publication Date: 2018-07-03
ANSALDO ENERGIA SPA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] Unfortunately, identifying which blisk needs to be rotated and by how much is extremely complex, and often what is agreed on paper is not appropriate in practice as various unknowns cannot be fully accounted for
For example, the interface between successive blisks may deform or fail due to use, which can cause unforeseen relative rotation
If the theoretical solution does not provide the expected results, or testing shows that the rotor is not balanced or not sufficiently balanced, the process must be repeated, wasting a great deal of time

Method used

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  • Method and auxiliary device for balancing a gas turbine rotor
  • Method and auxiliary device for balancing a gas turbine rotor
  • Method and auxiliary device for balancing a gas turbine rotor

Examples

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Embodiment Construction

[0038] refer to figure 1 , the power generation system gas turbine rotor as a whole is indicated by reference numeral 1 , which includes a plurality of blisks 2 arranged along an axis A and sandwiched by a central tie bar 3 . The first blisk set 2 with the respective first rotor blades 5 defines the compression section 1 a of the rotor 1 , while the second blisk set 2 with the second rotor blades 6 defines the turbine section 1 b of the rotor 1 . The compression section 1 a and the turbine section 1 b are separated from each other by a substantially cylindrical blisk 2 without blades, which in practice acts as a spacer element. In use, the annular combustor (not shown) of the gas turbine may be arranged around the spacer blisk 2 .

[0039] The front bearing interface 7 and the rear bearing interface 8 are respectively contained in the first and second end discs, respectively also called front or front hollow shaft and rear hollow shaft, indicated here by reference numerals 2a...

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Abstract

A method for balancing a rotor (1) of a gas turbine having a plurality of discs (2) arranged in succession along a line (A) includes the steps of: acquiring eccentricity measurements (ER1,..., ERP) of the discs (2) of the rotor (1) of a gas turbine in an initial configuration; based on the eccentricity measurements (ER1,..., ERP), identifying at least two critical areas of the rotor (1), in which variations of eccentricity between consecutive discs (2) are not in compliance with an acceptance criterion; identifying at least a first group of consecutive discs (2), arranged between two critical areas; determining at least one corrective action of the rotor (1), the corrective action including a relative rotation about the axis (A) between two consecutive discs (2) of the first group of discs (2); and performing the corrective action.

Description

technical field [0001] The invention relates to a method and an auxiliary device for balancing a gas turbine rotor. Background technique [0002] As is known, gas turbine rotors used in industrial systems for power generation typically include a plurality of bladed blisks and one or more spacer elements, aligned along the axis and coupled at the front. The blisks and spacer elements are clamped by a central tie rod. The blisks have respective arrays of blades, and each blisk defines a rotor stage of a compressor or turbine. [0003] The rotors of gas turbines must be manufactured and assembled with high precision to ensure near perfect balance. Considering the mass and the high speed of rotation (usually 3000rpm or 3600rpm according to the standards of different countries), even the smallest error can cause dangerous vibrations and often lead to premature aging of some components. [0004] No matter how properly balanced a factory gas turbine rotor is considered to be, th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/02F01D5/06
CPCF01D5/06F01D5/027
Inventor 恩里科·皮尼奥内
Owner ANSALDO ENERGIA SPA