EP2792848A1 - Procédé de rétablissement d'une précontrainte de la virole des aubes d'une turbine à gaz - Google Patents

Procédé de rétablissement d'une précontrainte de la virole des aubes d'une turbine à gaz Download PDF

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Publication number
EP2792848A1
EP2792848A1 EP13164028.6A EP13164028A EP2792848A1 EP 2792848 A1 EP2792848 A1 EP 2792848A1 EP 13164028 A EP13164028 A EP 13164028A EP 2792848 A1 EP2792848 A1 EP 2792848A1
Authority
EP
European Patent Office
Prior art keywords
blades
cover plate
bracing element
cover plates
gap
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Withdrawn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
EP13164028.6A
Other languages
German (de)
English (en)
Inventor
Yevgen Dr. Kostenko
Andreas Ulma
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP13164028.6A priority Critical patent/EP2792848A1/fr
Priority to EP14718537.5A priority patent/EP2954165A1/fr
Priority to CN201480021839.1A priority patent/CN105121785A/zh
Priority to US14/784,130 priority patent/US20160053615A1/en
Priority to PCT/EP2014/056813 priority patent/WO2014170143A1/fr
Priority to JP2016508079A priority patent/JP2016515682A/ja
Priority to KR1020157029928A priority patent/KR20150132537A/ko
Publication of EP2792848A1 publication Critical patent/EP2792848A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/005—Repairing methods or devices
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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

  • the invention relates to a method for restoring a cover plate prestress of a turbine blade, wherein the blades are formed with cover plates, wherein between two cover plates of adjacent blades, a gap is formed due to damage.
  • turbomachines such as e.g. Steam turbines
  • a flow medium between so-called guide and moving blades is moved.
  • the rotor blades are arranged on the surface of a rotor, wherein the rotor is rotatably mounted about a rotation axis.
  • the individual blades are formed into a so-called blade row, which means that the individual blades are arranged in the circumferential direction on the rotor surface.
  • the rotor is arranged in a housing with the rotor blade rows, which are arranged one after the other in a flow direction, wherein the guide vanes are arranged on an inner surface of the housing.
  • the vanes are arranged such that they are also arranged in a circumferential direction one behind the other and thus form a row of vanes.
  • a flow channel through which the flow medium flows, is created between the guide blade and blade rows.
  • steam flows as a flow medium along the flow channel.
  • the movement of the flow medium in the flow channel causes the rotor to rotate. This rotation can, for example, be exploited to drive electric generators.
  • the blades have an aerodynamic profile, the blades being end-to-end from the axis of rotation seen so-called cover plates. These cover plates are arranged at the blade ends and thus form a boundary for the flow channel.
  • cover plates are arranged at the blade ends and thus form a boundary for the flow channel.
  • the invention seeks to remedy this situation.
  • the invention proposes to arrange an additional component, namely a bracing element between the cover plates, thereby countering the costly replacement of a blade.
  • This bracing member is inserted from an inner side of the blade row into the gap and welded from the inside or the outside.
  • the advantage of this method according to the invention is that the blade row can be tightened again. Such a tension of the blade row until the next inspection is therefore guaranteed cost. A reliable use of the turbine thereby avoids possible damage and further damage to the blade row can be avoided.
  • the blade row forms a blade composite. The blade assembly is thereby secured against the occurrence of further damage.
  • the bracing element is formed with a wedge piece, wherein the wedge piece is wedge-shaped and is arranged in the gap.
  • the bracing element thus has a wedge piece, which projects into the gap and is wedge-shaped.
  • the bracing element is T-shaped and arranged the wedge piece perpendicular to the crossbar.
  • This T-shaped form facilitates insertion of the bracing element into the damaged gap. Furthermore, due to forces such as e.g. Centrifugal forces, a movement of the bracing element between the shrouds effectively avoided.
  • the tension element is arranged such that the crossbar is below the shrouds.
  • the crossbeam is arranged in the flow channel. Therefore, the crossbeam should not have an unnecessarily large shape.
  • a force between the shrouds is exerted by the insertion of the bracing element, which leads to a pushing apart of the shrouds.
  • FIG. 1 is a plan view of a first cover plate 1 and a second cover plate 2 shown.
  • the first cover plate 1 and the second cover plate 2 are arranged at the end on blade profiles 3.
  • the blade profile 3 is in the FIG. 1 represented by dashed lines.
  • the first cover plate 1 and the second cover plate 2 form with the blade profile 3 and a blade root 4 each have a blade.
  • the blade root is arranged in a housing.
  • the blade root 4 is arranged on a rotor.
  • the invention is applicable to both guide and for blades.
  • the first cover plate 1 and the second cover plate 2 are arranged in a circumferential direction 5.
  • the blades form in the circumferential direction 5 a successively arranged arrangement of a row of blades.
  • the gap 6 is formed due to a damage between the first cover plate 1 and the second cover plate 2 of two adjacent blades.
  • the method for repairing the blade row now provides that in a first step, a bracing element 7 is inserted into the gap 6. And in a second step, the bracing element with the cover plates 1, 2 is welded.
  • This welding can be done below, outside or at the front side of the first cover plate 1 or second cover plate 2 as well as outside the first cover plate 1 and the second cover plate 2.
  • the cover plates 1, 2 form in the association circumferentially arranged a shroud.
  • the bracing element 7 is formed with a wedge piece 8, which is wedge-shaped and is arranged in the gap 3.
  • the wedge piece 8 is in this case wedge-shaped, that a movement of the wedge piece 8 in the direction of the first cover plate 1 and the second cover plate 2 exerts a force which leads to a pressing apart of the first cover plate 1 and the second cover plate 2.
  • the bracing element 7 is T-shaped, wherein the wedge piece 8 is arranged perpendicular to the crossbar 9.
  • the crossbar 9 is thus arranged on the inside of the first cover plate 1 and the second cover plate 2.
  • the insertion of the bracing element 7 leads to a force between the first cover plate 1 and second cover plate 2, which leads to the pressing apart of the first cover plate 1 and the second cover plate 2.
  • FIG. 2 shows a sectional view of a portion of the blade row.
  • the bracing element 7 is in this case in the installed state, that is, according to the repair method according to the invention, shown.
  • the bracing element 7 is welded to the first cover plate 1 or to the second cover plate 2. This welding can take place on the shroud surface 10 or on the shroud inner surface 11.
  • FIG. 3 is a perspective view of the blade row shown.
  • only one bracing element 7 has been illustrated in the figures.
  • FIG. 4 shows an alternative embodiment of the bracing element 7.
  • the bracing element 7 is executed twisted by about 180 °. That means, that the transverse bar 9 is arranged above the cover plate 2.
  • the wedge piece 8 is between two cover plates 2. But does not have to be wedge-shaped. Rather, the wedge piece 8 may be formed substantially parallel to the contact surfaces of the cover plate 2. So that the bracing element 7 does not detach from the shroud during operation, it is welded to the cover plates 2.
  • the invention can be used in steam turbines.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13164028.6A 2013-04-17 2013-04-17 Procédé de rétablissement d'une précontrainte de la virole des aubes d'une turbine à gaz Withdrawn EP2792848A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP13164028.6A EP2792848A1 (fr) 2013-04-17 2013-04-17 Procédé de rétablissement d'une précontrainte de la virole des aubes d'une turbine à gaz
EP14718537.5A EP2954165A1 (fr) 2013-04-17 2014-04-04 Procédé servant à rétablir une précontrainte de plaque de recouvrement
CN201480021839.1A CN105121785A (zh) 2013-04-17 2014-04-04 用于恢复覆盖板预紧的方法
US14/784,130 US20160053615A1 (en) 2013-04-17 2014-04-04 Method for restoring a cover plate pretension
PCT/EP2014/056813 WO2014170143A1 (fr) 2013-04-17 2014-04-04 Procédé servant à rétablir une précontrainte de plaque de recouvrement
JP2016508079A JP2016515682A (ja) 2013-04-17 2014-04-04 カバープレートのプレテンションを回復させるための方法
KR1020157029928A KR20150132537A (ko) 2013-04-17 2014-04-04 커버 플레이트 초기 응력의 복원 방법

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13164028.6A EP2792848A1 (fr) 2013-04-17 2013-04-17 Procédé de rétablissement d'une précontrainte de la virole des aubes d'une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2792848A1 true EP2792848A1 (fr) 2014-10-22

Family

ID=48092840

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13164028.6A Withdrawn EP2792848A1 (fr) 2013-04-17 2013-04-17 Procédé de rétablissement d'une précontrainte de la virole des aubes d'une turbine à gaz
EP14718537.5A Withdrawn EP2954165A1 (fr) 2013-04-17 2014-04-04 Procédé servant à rétablir une précontrainte de plaque de recouvrement

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14718537.5A Withdrawn EP2954165A1 (fr) 2013-04-17 2014-04-04 Procédé servant à rétablir une précontrainte de plaque de recouvrement

Country Status (6)

Country Link
US (1) US20160053615A1 (fr)
EP (2) EP2792848A1 (fr)
JP (1) JP2016515682A (fr)
KR (1) KR20150132537A (fr)
CN (1) CN105121785A (fr)
WO (1) WO2014170143A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3079263A1 (fr) * 2018-03-20 2019-09-27 Safran Aircraft Engines Dispositif de carenage pour talon d'aube
US20190337102A1 (en) * 2018-05-07 2019-11-07 General Electric Company Interlocking Stage of Airfoils

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0999009A1 (fr) * 1998-11-02 2000-05-10 General Electric Company Procédé pour appliquer des matériaux résistants à l'usure aux aubes de turbine et aubes de turbine obtenues
EP1375823A2 (fr) * 2002-06-28 2004-01-02 General Electric Company Procédé de réparation du chevauchement des viroles des aubes de turbines à gaz
US20050042092A1 (en) * 2003-07-23 2005-02-24 Andreas Boegli Method of reconditioning a turbine blade

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2511908A1 (fr) * 1981-08-26 1983-03-04 Snecma Procede de brasage-diffusion destine aux pieces en superalliages
JPS61132703A (ja) * 1984-12-01 1986-06-20 Toshiba Corp 蒸気タ−ビンの動翼
JPS6252203U (fr) * 1985-09-18 1987-04-01
US5785496A (en) * 1997-02-24 1998-07-28 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor
JP2002213204A (ja) * 2001-01-15 2002-07-31 Toshiba Corp タービン動翼及びタービン
JP2003097215A (ja) * 2001-09-19 2003-04-03 Mitsubishi Heavy Ind Ltd タービンロータの翼構造、およびターボ機械
JP2004052757A (ja) * 2002-05-31 2004-02-19 Toshiba Corp タービン動翼
US20070079507A1 (en) * 2005-10-12 2007-04-12 Kenny Cheng Blade shroud repair
CN101285404B (zh) * 2008-06-03 2011-08-03 东方电气集团东方汽轮机有限公司 汽轮机动叶片的围带结构及其加工工艺

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0999009A1 (fr) * 1998-11-02 2000-05-10 General Electric Company Procédé pour appliquer des matériaux résistants à l'usure aux aubes de turbine et aubes de turbine obtenues
EP1375823A2 (fr) * 2002-06-28 2004-01-02 General Electric Company Procédé de réparation du chevauchement des viroles des aubes de turbines à gaz
US20050042092A1 (en) * 2003-07-23 2005-02-24 Andreas Boegli Method of reconditioning a turbine blade

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3079263A1 (fr) * 2018-03-20 2019-09-27 Safran Aircraft Engines Dispositif de carenage pour talon d'aube
US20190337102A1 (en) * 2018-05-07 2019-11-07 General Electric Company Interlocking Stage of Airfoils
EP3567214A1 (fr) * 2018-05-07 2019-11-13 General Electric Company Procédé in-situ de rétablissement d'une précontrainte de la virole des aubes d'une turbine à gaz

Also Published As

Publication number Publication date
US20160053615A1 (en) 2016-02-25
JP2016515682A (ja) 2016-05-30
KR20150132537A (ko) 2015-11-25
CN105121785A (zh) 2015-12-02
EP2954165A1 (fr) 2015-12-16
WO2014170143A1 (fr) 2014-10-23

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