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Method and equipment for assembling rotary machine

一种转子、组件的技术，应用在机械设备、用于弹性流体的泵送装置的部件、化学仪器和方法等方向

Inactive Publication Date: 2008-07-30
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, since the geometry of adjacent blades can be different, the rotor can still experience a balance shift during operation that is not related to the moment weight of each blade

Method used

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  • Method and equipment for assembling rotary machine
  • Method and equipment for assembling rotary machine
  • Method and equipment for assembling rotary machine

Examples

Experimental program
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Embodiment Construction

[0012] FIG. 1 is a schematic diagram of an exemplary gas turbine 10 including a rotor 11 including a low pressure compressor 12 , a high pressure compressor 14 and a combustor 16 . The gas turbine 10 also includes a high pressure turbine 18 , a low pressure turbine 20 , and an exhaust frame 22 and casing 24 . A first shaft 26 engages the low pressure compressor 12 and the low pressure turbine 20 and a second shaft 28 engages the high pressure compressor 14 and the high pressure turbine 18 . The gas turbine 10 has an axis of symmetry 32 extending rearwardly from an upstream side 34 of the gas turbine 10 to a downstream side 36 of the gas turbine 10 . In one embodiment, the gas turbine 10 is a GE90 gas turbine manufactured and sold by the General Electrical Company, Cincinnati, Ohio.

[0013] In operation, air flows through the low pressure compressor 12 and compressed air is supplied to the high pressure compressor 14 . High pressure compressed air is delivered to the combust...

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PUM

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Abstract

A method (300) and apparatus for assembling a rotatable machine is provided. The machine includes a plurality of blades that extend radially outwardly from a rotor. The method (300) includes determining (302) a moment weight of each blade in a row of blades, determining (304) a geometric parameter of each blade in the same row of blades, and determining (306) a mapping order of each blade using the moment weight and the geometric parameter. The apparatus includes a computer system that includes a software product code segment for minimizing imbalance in a bladed rotor wherein the segment is configured to receive a moment weight value for each blade to be installed in said rotor, receive a geometric parameter value for each blade to be installed in said rotor, calculate a blade location on the rotor based on the received values, and generate a blade map based on the calculated location.

Description

technical field [0001] The present invention relates generally to gas turbines, and more particularly to the assembly of rotating components of gas turbines. Background technique [0002] At least some known gas turbines include a core gas turbine having a fan blade assembly and a high pressure compressor that compresses the air flow entering the gas turbine in a series flow arrangement. The combustor ignites the fuel-air mixture, which is then directed through a turbine nozzle assembly to low- and high-pressure turbines, each of which includes a plurality of rotor blades that extract rotational energy from the airflow exiting the combustor. Gas turbines are used in different operating environments, such as to provide propulsion for aircraft and / or to provide power in land-based and sea-based power systems. [0003] In normal operation, gas turbines experience high rotational speeds. Imbalances in the rotor may cause the rotor to vibrate and create stress in the rotor bear...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/02F01D5/30G01M1/36F02C3/045F01D5/10F02C7/00F04D29/32F04D29/34F04D29/66
CPCY10S416/50Y02T50/672F05B2230/60F05D2230/60F01D5/3007F01D5/30F01D5/027Y02T50/673F04D29/662Y02T50/60Y10T29/49321
Inventor T·R·亨宁G·J·范德梅尔维W·C·吕尔D·E·莫尔曼
Owner GENERAL ELECTRIC CO
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