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WO2011035772A1 - Procédé pour réparer un rotor constitué d'une seule pièce et rotor correspondant - Google Patents

Procédé pour réparer un rotor constitué d'une seule pièce et rotor correspondant Download PDF

Info

Publication number
WO2011035772A1
WO2011035772A1 PCT/DE2010/001126 DE2010001126W WO2011035772A1 WO 2011035772 A1 WO2011035772 A1 WO 2011035772A1 DE 2010001126 W DE2010001126 W DE 2010001126W WO 2011035772 A1 WO2011035772 A1 WO 2011035772A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
collar
replacement
rotor
welding
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.)
Ceased
Application number
PCT/DE2010/001126
Other languages
German (de)
English (en)
Inventor
Erich Steinhardt
Thomas Uihlein
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Priority to EP10776283A priority Critical patent/EP2344299A1/fr
Publication of WO2011035772A1 publication Critical patent/WO2011035772A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/20—Manufacture essentially without removing material
    • F05B2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05B2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05B2230/239—Inertia or friction 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
    • F05D2230/20—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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • 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 repairing an integral rotor, in particular a rotor of a gas turbine, having a rotor base body and a plurality of blades, as well as such an integral rotor.
  • the object of the invention is to provide an improved repair method for integral rotors.
  • the object of the invention is achieved by a method for repairing an integral rotor, in particular a rotor of a gas turbine, having a rotor base body and a plurality of blades with the following method steps: separating a blade to be replaced from the rotor, wherein a projecting from the rotor body blade stub with a first welding contact surface is formed; Providing a replacement bucket with a second weld contact surface; Attaching a collar to the blade stub and / or to the replacement blade by a thermal spraying method, the material of the collar having a melting point substantially equal to that of the blade stub or the replacement blade; Welding the replacement blade to the blade stump; and at least partially removing the collar.
  • blade stump in the sense of this invention is to be understood as the remainder of the blade to be repaired remaining on the rotor base body.
  • a blade stump can therefore also extend to the blade tip. Accordingly, the replacement bucket may also be just a new bucket tip.
  • a collar By attaching a collar to the blade stub, the blade stub is reinforced against the stresses of welding the replacement blade.
  • a collar allows a fixation of the replacement bucket in the welding device without touching the airfoil surface.
  • the thermal spraying process and the melting point of the material of the collar allow a variety of training of the collar.
  • the collar is attached by high speed or cold gas spraying. This allows high precision in the formation of the collar by a generative process and good material properties of the collar.
  • the replacement blade is welded by a friction welding method, in particular a linear friction welding method.
  • the replacement blade may be welded by a pressure welding process, in particular an inductive low or high frequency compression welding process.
  • the collar can be mounted in the area of the associated weld contact surface.
  • the collar terminates flush with the weld contact surface of the blade stub and / or the replacement blade.
  • the weld contact area can be increased by the collar, which is welded with. In this way, a small and irregularly shaped weld contact surface of the blade stub can be enlarged and / or its geometry can be optimized for welding.
  • the collar is only partially removed after welding the replacement blade, with the resulting replacement blade welded to the rotor creating a has different geometry than the original blade.
  • Such a new geometry can be adapted, for example, to changed structural mechanical requirements.
  • an intermediate element is provided, which is arranged between the blade and the rotor base body.
  • a blade and a rotor base body can be connected to various materials which, because of their material properties, can not be welded directly to one another.
  • the replacement blade is preferably held on the collar provided on it, which significantly reduces their burden.
  • the invention also relates to an integral rotor, in particular a gas turbine, having a rotor base body and a plurality of blades, wherein at least one blade is a replacement blade attached to a blade stump of a remote blade by repair.
  • a collar for enlarging the weld contact surface by a thermal spraying method or cold gas spraying is attached.
  • the material of the collar has a melting point that substantially corresponds to the blade stub or replacement blade.
  • FIGS. 1a-f show successive steps in a method according to the invention for repairing an integral rotor
  • FIG. 2 shows a second embodiment of the collar on the blade stump, which may be present in the method according to the invention.
  • FIG. 3 shows a third embodiment of the collar on the blade stump, which may be present in the inventive method.
  • Figure la shows an integral rotor 10, in particular a gas turbine, with a rotor base body 12 and a plurality of blades 14, wherein a blade 16 to be replaced is damaged.
  • the extent of damage to the blade 16 to be replaced is determined, and the blade 16 to be replaced is separated from the rotor 10 radially inwardly of the damaged location along the cutting plane 18 shown in dotted lines.
  • a blade stub 20 projecting from the rotor base body 12 is formed with a first radially frontal welding contact surface 22, which is illustrated in FIG.
  • An exchange bucket 24 having a frontal, second weld contact surface 26 is provided.
  • the replacement bucket 24 has a shape corresponding to the original geometry of the separated part of the bucket 16 to be replaced.
  • a collar 28 is attached to the blade stub 20 and to the replacement blade 24 by a thermal spraying method (for example high-speed or cold gas spraying).
  • a thermal spraying method for example high-speed or cold gas spraying.
  • the geometry of the collar 28 is selected so that the collar 28 terminates flush with the weld contact surface 22, 26 of the blade stub 20 and the replacement blade 24, respectively, whereby the weld contact surfaces 22, 26 are enlarged by the collar 28.
  • the thickness of each collar 28 may decrease toward the side remote from the weld contact surface 22, 26, or alternatively may be constant or increase over a particular portion.
  • the collars 28 preferably run closed in the circumferential direction around the part to be reinforced.
  • the collar 28 may also change the geometry of the part, for example, the blade contour of the blade stub 20 or the replacement blade 24 may be formed by the collar 28 in a rectangular shape, which facilitates, for example, fixing the parts during subsequent welding.
  • Figure ld shows a linear friction welding method in which the replacement blade 24 is pressed in the radial direction with the second weld contact surface 26 against the first weld contact surface 22 of the blade stub 20 and at the same time the exchange blade 24 is moved linearly oscillating in the tangential direction. Due to the resulting frictional heat, the desired welding temperature is achieved.
  • the geometry of the collar 28 is selected to reduce the stresses on the blade stump 20 during the welding process.
  • Inductive pressing welding the joining zone is heated inductively, the exchange blade 24 is pressed radially against the blade stump 20 on reaching the intended welding temperature.
  • the collar 28 of the replacement bucket 24 may be designed so that a welding device 29 touches the replacement bucket 24 exclusively via the collar 28.
  • the material of the collar 28 has a melting point substantially equal to that of the blade stub 20 and the replacement blade 24, respectively. In this way it is prevented that the material of the collar melts early and gets into the joint zone between the blade stub 20 and replacement blade 24.
  • the melting point of the material of the collar 28 may be, for example, in a temperature range of 150 ° C above the melting point of the material of the component to which it is attached (blade stub 20 or replacement blade 24) to 100 ° C below the melting point of the material of the corresponding component.
  • a disc material is, for example, Inco718 with T so iidus 1260 ° C, Tuquidus 1,996 ° C.
  • alternative alloys only differ by a few 10 ° C in melting point temperatures.
  • the material of the collar 28 preferably corresponds to that of its associated part, ie the associated blade stub 20 or the associated replacement blade 24. Due to the use of the same alloy, only the same material will be present in the joint zone between the replacement blade 24 and the blade stub 20 during welding. The collar material is used to compensate for undersize.
  • Figure le shows the rotor 10 after welding the replacement blade 24 on the blade stub 20.
  • the weld contact surfaces 22, 26 are welded together over their entire surface, whereby the collar 28 of the blade stub 20 and the replacement blade 24 are welded together.
  • FIG. 2 shows an alternative embodiment of the collar 28 on the blade stub 20.
  • the collar 28 likewise extends as far as the rotor base body 12 and thus additionally supports the blade stump 20 with respect to the rotor base body 12.
  • the collar 28 is formed so that the blade stump 20 requires no additional support by the welding device.
  • the collar 28 is thickened for improved support in the direction of the rotor base body 12.
  • FIG. 3 shows an integral rotor 10, in which the blades 14 and the rotor base body 12 are made of different materials.
  • an intermediate element 30 is present, via which the blade 14 and the rotor base body 12 are connected.
  • components can be welded with different materials which, because of their material properties, can not be welded directly to one another, for example different alloys or single-crystalline components with polycrystalline components.
  • the collar 28 may extend over the region of the intermediate element 30, whereby this region is additionally stabilized.
  • the defective blade 16 can be separated radially outside or even in the region of the intermediate element 30.
  • the collar 28 can generally also be attached by thermal spraying of various materials, wherein the material of the collar is in each case adapted to the adjacent component, for example the rotor base body 12, the blade stub 20 or the intermediate element 30.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé pour réparer un rotor (10) constitué d'une seule pièce, en particulier un rotor (10) d'une turbine à gaz, ledit rotor comprenant un corps de base (12) et une pluralité de pales (14). Le procédé selon l'invention comprend les étapes suivantes, consistant à : séparer du rotor (10) une pale à remplacer (16), ce qui entraîne la formation d'un "moignon" (20) faisant saillie par rapport au corps de base (12) et comprenant une première surface de contact de soudure (22); mettre à disposition une pale de remplacement (24) présentant une deuxième surface de contact de soudure (26); mettre en place un collet (28) sur le moignon (20) et/ou sur la pale de remplacement (24) par un procédé d'injection thermique, le matériau du collet (28) présentant un point de fusion correspondant sensiblement à celui du moignon (20) ou de la pale de remplacement (24); souder la pale de remplacement (24) sur le moignon (20); puis retirer au moins partiellement le collet (28).
PCT/DE2010/001126 2009-09-26 2010-09-24 Procédé pour réparer un rotor constitué d'une seule pièce et rotor correspondant Ceased WO2011035772A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10776283A EP2344299A1 (fr) 2009-09-26 2010-09-24 Procédé pour réparer un rotor constitué d'une seule pièce et rotor correspondant

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009043184.5 2009-09-26
DE200910043184 DE102009043184A1 (de) 2009-09-26 2009-09-26 Verfahren zur Reparatur eines integralen Rotors und integraler Rotor

Publications (1)

Publication Number Publication Date
WO2011035772A1 true WO2011035772A1 (fr) 2011-03-31

Family

ID=43478307

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2010/001126 Ceased WO2011035772A1 (fr) 2009-09-26 2010-09-24 Procédé pour réparer un rotor constitué d'une seule pièce et rotor correspondant

Country Status (3)

Country Link
EP (1) EP2344299A1 (fr)
DE (1) DE102009043184A1 (fr)
WO (1) WO2011035772A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013025384A1 (fr) * 2011-08-17 2013-02-21 General Electric Company Réparation de rainure de joint d'étanchéité de rotor
WO2013075815A1 (fr) * 2011-11-22 2013-05-30 Lufthansa Technik Ag Procédé de réparation d'un élément de turbine à gaz
EP2803819A1 (fr) * 2013-05-15 2014-11-19 General Electric Company Aubes de turbine modifiées et procédés de modification d'aubes de turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013226221A1 (de) * 2013-12-17 2015-06-18 Siemens Aktiengesellschaft Fügeverfahren

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3909733A1 (de) * 1988-03-28 1989-10-12 Gen Electric Verfahren und vorrichtung zum verbinden von zwei gegenstaenden
US5551623A (en) * 1994-02-23 1996-09-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Process for welding two blade parts
EP1535692A1 (fr) * 2003-11-27 2005-06-01 Rolls-Royce PLC Méthode de fabrication ou réparation d'un assemblage
EP1604770A2 (fr) * 2004-06-09 2005-12-14 Rolls-Royce Plc Procédé de remplacement des aubes endommagées
DE102006028279A1 (de) * 2006-06-20 2007-12-27 Mtu Aero Engines Gmbh Reparaturverfahren
JP2009039746A (ja) * 2007-08-08 2009-02-26 Ihi Corp 部品の接合方法及び翼部品の補修方法

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004032975A1 (de) * 2004-07-08 2006-02-09 Mtu Aero Engines Gmbh Verfahren zum Verbinden von Schaufelblättern mit Schaufelfüßen oder Rotorscheiben bei der Herstellung und/oder Reparatur von Gasturbinenschaufeln oder integral beschaufelten Gasturbinenrotoren
DE102006008836A1 (de) * 2006-02-25 2007-09-06 Mtu Aero Engines Gmbh Verfahren zur Herstellung und/oder Reparatur eines integral beschaufelten Rotors
DE102006031388A1 (de) * 2006-07-07 2008-01-17 Mtu Aero Engines Gmbh Verfahren für die Reparatur und/oder den Austausch von Einzelelementen eines Bauteils einer Gasturbine
DE102007046386B3 (de) * 2007-09-21 2008-10-02 Siemens Ag Verfahren zur Reparatur eines Bauteils durch Beschichten
DE102007062559A1 (de) * 2007-12-22 2009-06-25 Mtu Aero Engines Gmbh Verfahren zur Herstellung und Reparatur eines Bauteils und Bauteil einer Gasturbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3909733A1 (de) * 1988-03-28 1989-10-12 Gen Electric Verfahren und vorrichtung zum verbinden von zwei gegenstaenden
US5551623A (en) * 1994-02-23 1996-09-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Process for welding two blade parts
EP1535692A1 (fr) * 2003-11-27 2005-06-01 Rolls-Royce PLC Méthode de fabrication ou réparation d'un assemblage
EP1604770A2 (fr) * 2004-06-09 2005-12-14 Rolls-Royce Plc Procédé de remplacement des aubes endommagées
DE102006028279A1 (de) * 2006-06-20 2007-12-27 Mtu Aero Engines Gmbh Reparaturverfahren
JP2009039746A (ja) * 2007-08-08 2009-02-26 Ihi Corp 部品の接合方法及び翼部品の補修方法

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013025384A1 (fr) * 2011-08-17 2013-02-21 General Electric Company Réparation de rainure de joint d'étanchéité de rotor
CN103732862A (zh) * 2011-08-17 2014-04-16 通用电气公司 转子密封线凹槽修复
US8893381B2 (en) 2011-08-17 2014-11-25 General Electric Company Rotor seal wire groove repair
EP2753799B1 (fr) 2011-08-17 2018-06-06 General Electric Company Réparation de rainure de joint d'étanchéité de rotor
WO2013075815A1 (fr) * 2011-11-22 2013-05-30 Lufthansa Technik Ag Procédé de réparation d'un élément de turbine à gaz
EP2803819A1 (fr) * 2013-05-15 2014-11-19 General Electric Company Aubes de turbine modifiées et procédés de modification d'aubes de turbine

Also Published As

Publication number Publication date
DE102009043184A1 (de) 2011-04-07
EP2344299A1 (fr) 2011-07-20

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