EP2708697A1 - Verfahren zur Verbindung zweier Rotorabschnitte sowie Turbinenrotor - Google Patents

Verfahren zur Verbindung zweier Rotorabschnitte sowie Turbinenrotor Download PDF

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Publication number
EP2708697A1
EP2708697A1 EP12184721.4A EP12184721A EP2708697A1 EP 2708697 A1 EP2708697 A1 EP 2708697A1 EP 12184721 A EP12184721 A EP 12184721A EP 2708697 A1 EP2708697 A1 EP 2708697A1
Authority
EP
European Patent Office
Prior art keywords
rotor
coupling
sections
rotor sections
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12184721.4A
Other languages
English (en)
French (fr)
Inventor
Nikola Zelenovic
Christopher Kentish
Timothy George Shurrock
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP12184721.4A priority Critical patent/EP2708697A1/de
Priority to RU2013142236/06A priority patent/RU2013142236A/ru
Priority to JP2013191783A priority patent/JP2014058972A/ja
Priority to US14/028,829 priority patent/US20140079547A1/en
Priority to CN201310423432.9A priority patent/CN103670527A/zh
Publication of EP2708697A1 publication Critical patent/EP2708697A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/026—Shaft to shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods

Definitions

  • This invention relates generally to a rotor assembly and method of refitting a large rotor, particularly for turbines such as low pressure steam turbines.
  • At least some known turbine rotor assemblies include a rotor wheel to which a plurality of blades are coupled.
  • the rotor is typically assembled from several large cylindrical forgings or machined sections. The sections are either welded, bolted or connected through a heat shrinking process.
  • the rotor is supported at the ends or intermediate positions along its length by bearings.
  • bearings In the case of a large multi-stage steam turbine that includes high-pressure turbine, intermediate pressure turbines and low pressure turbines there are typically bearings to support the rotor at the end and between the stages.
  • rotors for large turbines weigh may weigh 155 tons or more and in spite of this considerable weight have to rotate at typically full or half-frequency of the power grid frequency, i.e. at 50 Hz or 60 Hz.
  • an unbalanced mass of the rotor causes the rotor to bend or buckle.
  • the amplitude of such vibrations often passes through a maximum that is called a critical speed. Given the high tolerances to which modern turbines are manufactured, such out-of-position movement can cause damage and malfunction of the turbine.
  • a rotor to carry the rotating parts of a turbine for the generation of electrical power for a public grid with the rotor including at least two sections coupled with a coupling of increased diameter exceeding the nominal diameter of the rotor, wherein at least one of the rotor sections includes one or more cavities at the end of at least one rotor section and in the vicinity of the coupling such that the boundaries of the one or more cavities are all interior surfaces when the rotor sections are coupled.
  • the one or more cavities at the end of the at least one rotor section and in the vicinity of the coupling extend from the wall of the rotor into a part of the coupling exceeding the nominal diameter of the rotor or are placed in a volume extending from the wall of the rotor into a part of the coupling exceeding the nominal diameter of the rotor.
  • the at least one of the rotor sections carries the rotating parts of a low pressure steam turbine, such as the rotating blades or airfoils and their respective platforms.
  • a method of coupling at two sections of rotor to carry the rotating parts of a turbine for the generation of electrical power for a public grid with a coupling of increased diameter exceeding the nominal diameter of the rotor including the step of removing mass from a volume lying exclusively within the interior of the sections when coupled.
  • mass is removed to increase the critical lateral speed of the coupled rotor sections such that the difference between operational speed and the critical lateral speed is enlarged compared to coupled rotor sections with flat ends.
  • Fig. 1 shows a schematic diagram of two rotor sections 11, 12 linked by coupling 111, 112.
  • the rotor section can be, for example, two sections of a rotor for low pressure steam turbines. Such rotor sections are typically either solid or else have cylindrical shape with thick walls. At the coupling area 111, 112 the thickness of the wall and hence the outer radius of the rotor exceed the nominal outer radius of the rotor to provide openings for bolts or screws.
  • the nominal radius can be regarded as the radius of the rotor in the coupling area derived by linearly extrapolating the radius of the rotor before the coupling section up to the end of the rotor section.
  • the rotor when provided may be optimized to provide, integrity at the lowest possible weight, lowest use of material, or else to ensure the interchangeability of components in order to minimize the number of spares.
  • the original rotor can be replaced by an improved rotor leaving some limited degrees of freedom to change the overall dimensions of the rotor.
  • FIG. 2 shows an alternative way of shifting the lateral critical speed of the coupling or overhang modes far enough away from the normal operating speed.
  • Fig. 2 there is shown a coupling with an original rotor section on the left side and an altered section on the right side thus illustrating the alterations as per an example of the invention.
  • the coupling 111,112 of this example is shrunk onto the actual rotor.
  • the original rotor section 12 has an essentially plane surface 13 facing the other section.
  • the surface may have a very shallow indention (not shown) machined into it to restrict the contact areas with the other section.
  • a cavity 14 is machined into the previously flat surface 13 by removing part of the wall of the rotor section 12. In the example shown it extends further radially into the coupling area or volume outside the nominal radius of the rotor.
  • the nominal radius is again defined as the radius of the rotor in the coupling area derived by linearly extrapolating the radius of the rotor before the coupling section up to the end of the rotor section.
  • the cavity 14 is fully enclosed within the interior of the rotor.
  • the walls of the cavity are thus not exposed to the air flow along the outside of the rotor.
  • the cavity is rotationally symmetric to facilitate the balancing of the rotor.
  • FIG. 3 Another example is shown in Fig. 3 .
  • the rotor has a forged solid coupling 111,112 on both ends of the rotor sections 11, 12.
  • a cavity 14 is machined into the walls of the rotor and part of the coupling.
  • a ring of coupling material 15 is removed from the outside of the coupling.
  • the plots of FIG. 4 show the shift of the vibrational spectrum of a rotor before (top plot) and after (bottom plot) creating a cavity at the coupling.
  • the spectrum between the top and bottom plot is essentially identical but slightly shifted to the right.
  • the cavity causes critical lateral speed to move away from the operational speed of the rotor. More precise measurements show a shift of the critical lateral speed from 1840 rpm to 1870 rpm, with a corresponding reduction in vibration amplitude at 1800 rpm (normal operating speed) of 20 ⁇ m peak to peak (from 45 ⁇ m to 35 ⁇ m zero-to-peak).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12184721.4A 2012-09-17 2012-09-17 Verfahren zur Verbindung zweier Rotorabschnitte sowie Turbinenrotor Withdrawn EP2708697A1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP12184721.4A EP2708697A1 (de) 2012-09-17 2012-09-17 Verfahren zur Verbindung zweier Rotorabschnitte sowie Turbinenrotor
RU2013142236/06A RU2013142236A (ru) 2012-09-17 2013-09-16 Роторный узел и способ переоборудования
JP2013191783A JP2014058972A (ja) 2012-09-17 2013-09-17 ロータアッセンブリ及び改装方法
US14/028,829 US20140079547A1 (en) 2012-09-17 2013-09-17 Rotor assembly and refit method
CN201310423432.9A CN103670527A (zh) 2012-09-17 2013-09-17 转子组件和改装方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12184721.4A EP2708697A1 (de) 2012-09-17 2012-09-17 Verfahren zur Verbindung zweier Rotorabschnitte sowie Turbinenrotor

Publications (1)

Publication Number Publication Date
EP2708697A1 true EP2708697A1 (de) 2014-03-19

Family

ID=46967996

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12184721.4A Withdrawn EP2708697A1 (de) 2012-09-17 2012-09-17 Verfahren zur Verbindung zweier Rotorabschnitte sowie Turbinenrotor

Country Status (5)

Country Link
US (1) US20140079547A1 (de)
EP (1) EP2708697A1 (de)
JP (1) JP2014058972A (de)
CN (1) CN103670527A (de)
RU (1) RU2013142236A (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9803647B2 (en) 2015-07-21 2017-10-31 General Electric Company Method and system for repairing turbomachine dovetail slots

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1801398A1 (de) * 1968-10-02 1970-10-01 Aeg Kanis Turbinen Laeufer einer Axialstroemungsmaschine
US4208003A (en) * 1977-09-06 1980-06-17 Bbc Brown Boveri & Company Limited Method of joining shaft sections
DE2931193A1 (de) * 1979-08-01 1981-02-05 Motoren Turbinen Union Einrichtung zur beseitigung von rotorunwuchten bei stroemungsmaschinen
EP0846844A1 (de) * 1996-12-04 1998-06-10 Asea Brown Boveri AG Rotorzusammenbau mit kraftschlüssig und gleichzeitig form- bzw. materialschlüssig verbundenen Rotorscheiben
EP0964135A2 (de) * 1998-06-09 1999-12-15 Mitsubishi Heavy Industries, Ltd. Rotor für eine Dampfturbine, der aus verschiedenen Werkstoffen zusammengeschweisst ist
US6837685B2 (en) 2002-12-13 2005-01-04 General Electric Company Methods and apparatus for repairing a rotor assembly of a turbine
US7309211B2 (en) * 2004-12-18 2007-12-18 Rolls-Royce Plc Balancing method
US20110164982A1 (en) * 2010-01-06 2011-07-07 General Electric Company Apparatus and method for a low distortion weld for rotors

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE462184A (de) * 1944-10-06
GB723882A (en) * 1951-09-05 1955-02-16 Vickers Electrical Co Ltd Improvements in the construction of rotors for steam- and gas-turbines
JPH0243401U (de) * 1988-09-20 1990-03-26
JPH0777005A (ja) * 1993-09-09 1995-03-20 Mitsubishi Heavy Ind Ltd 中空回転軸の結合装置
US7286643B2 (en) * 2003-12-23 2007-10-23 General Electric Company X-ray tube target balancing features
JP5072278B2 (ja) * 2006-07-18 2012-11-14 三菱重工業株式会社 油圧着脱式カップリング
US20090060735A1 (en) * 2007-08-31 2009-03-05 General Electric Company Turbine rotor apparatus and system
US8177487B2 (en) * 2009-05-04 2012-05-15 General Electric Company Rotary machine balance weights
CN101956572A (zh) * 2010-10-08 2011-01-26 东方电气集团东方汽轮机有限公司 涡轮机的转子结构

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1801398A1 (de) * 1968-10-02 1970-10-01 Aeg Kanis Turbinen Laeufer einer Axialstroemungsmaschine
US4208003A (en) * 1977-09-06 1980-06-17 Bbc Brown Boveri & Company Limited Method of joining shaft sections
DE2931193A1 (de) * 1979-08-01 1981-02-05 Motoren Turbinen Union Einrichtung zur beseitigung von rotorunwuchten bei stroemungsmaschinen
EP0846844A1 (de) * 1996-12-04 1998-06-10 Asea Brown Boveri AG Rotorzusammenbau mit kraftschlüssig und gleichzeitig form- bzw. materialschlüssig verbundenen Rotorscheiben
EP0964135A2 (de) * 1998-06-09 1999-12-15 Mitsubishi Heavy Industries, Ltd. Rotor für eine Dampfturbine, der aus verschiedenen Werkstoffen zusammengeschweisst ist
US6837685B2 (en) 2002-12-13 2005-01-04 General Electric Company Methods and apparatus for repairing a rotor assembly of a turbine
US7309211B2 (en) * 2004-12-18 2007-12-18 Rolls-Royce Plc Balancing method
US20110164982A1 (en) * 2010-01-06 2011-07-07 General Electric Company Apparatus and method for a low distortion weld for rotors

Also Published As

Publication number Publication date
RU2013142236A (ru) 2015-03-27
CN103670527A (zh) 2014-03-26
JP2014058972A (ja) 2014-04-03
US20140079547A1 (en) 2014-03-20

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