EP1963043A1 - Procede de soudage et dispositif de soudage - Google Patents

Procede de soudage et dispositif de soudage

Info

Publication number
EP1963043A1
EP1963043A1 EP06830251A EP06830251A EP1963043A1 EP 1963043 A1 EP1963043 A1 EP 1963043A1 EP 06830251 A EP06830251 A EP 06830251A EP 06830251 A EP06830251 A EP 06830251A EP 1963043 A1 EP1963043 A1 EP 1963043A1
Authority
EP
European Patent Office
Prior art keywords
welding
plate
component
welding device
repaired
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Withdrawn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
EP06830251A
Other languages
German (de)
English (en)
Inventor
Francis-Jurjen Ladru
Gerhard Reich
Helge Reymann
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 EP06830251A priority Critical patent/EP1963043A1/fr
Publication of EP1963043A1 publication Critical patent/EP1963043A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K37/00—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups
    • B23K37/06—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups for positioning the molten material, e.g. confining it to a desired area
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K9/00—Arc welding or cutting
    • B23K9/04—Welding for other purposes than joining, e.g. built-up welding

Definitions

  • the invention relates to a welding method according to the preamble of claim 1 and a welding device according to claim 5.
  • the substrate of a component is melted so that cracks in the substrate close, wherein optionally a filler metal, in particular in the form of powder, is added, which is melted during welding and allowed to solidify.
  • the object is achieved by a welding method according to claim 1 and a welding device according to claim 5.
  • the measures listed in the subclaims can be combined as desired in order to achieve further advantages.
  • the process start point of the welding process is here according to the invention thus on the flow plate, so that when reaching the recess starting point of the welding process is stable and from the beginning high-quality and gleichdorfige properties of the entire welded area can be achieved.
  • FIG. 2 shows a device according to the invention
  • FIGS. 3, 4 show specific components of the welding device according to the invention
  • FIG. 5 shows the sequence of the welding method according to the invention
  • FIG. 6 shows a perspective view of a turbine blade
  • Figure 7 is a perspective view of a combustion chamber
  • Figure 8 is a perspective view of a gas turbine.
  • Figure 1 shows a device for welding according to the prior art.
  • a welding filler material 13 is added to a point to be repaired 10 in a substrate 4 via a Pulverforderer 31, 13 by means of a heat source 34, in particular by an electron beam gun, a laser 34 or by plasma welding, melted and allowed to solidify ,
  • a heat source 34 in particular by an electron beam gun, a laser 34 or by plasma welding
  • either the substrate 4 or the powder requestor 31 or the beams 37 of the heat source 34 are moved in a welding direction 40.
  • an elongate crack 10 or depression 10 propagates as a site 10 to be repaired. The method begins at a starting point 22 of the recess 10 and an end point 25 of the point 10 to be repaired.
  • FIG. 2 shows a device 1 according to the invention with which the welding method according to the invention can be carried out.
  • the substrate 4 of a component 120, 130, 138, 155 has a surface 7, of which a partial area, the point 10 to be repaired, is to be welded. This may be a crack 10 or a well 10 (to be exemplified below) that needs to be filled. Likewise, large-area material can be applied in order to achieve a thickening of a wall, in particular in the case of hollow components 120, 130.
  • the welding filler material 13 is used, which fills the crack 10, the recess 10 or the surface 10 thickened.
  • the welding filler material 13 may be continuously supplied in the form of powder during welding or may have been introduced into the recess 10 in the form of a tape or wire.
  • the welding process does not start at the starting point 22 of the point to be repaired 10, from which the supply or the presence of the welding filler material 13 would be necessary, but first on a separate flow plate 19 which either rests completely on the surface 7 (indicated by dashed lines) ) or at a certain angle ⁇ is applied to the surface 7 at the starting point 22.
  • a separate flow plate 19 which either rests completely on the surface 7 (indicated by dashed lines) ) or at a certain angle ⁇ is applied to the surface 7 at the starting point 22.
  • the flow plate 19 is not part of the component 120, 130, 138, 155 or a welded portion 14. A gap between the flow plate 19 and surface 7 may be present.
  • the process start point 43 of the welding process is here according to the invention thus on the flow plate 19, so that upon reaching the pit start point 22, the process of welding is stable, and from the beginning, high quality and uniform properties of the entire welded area are achieved.
  • a separate follower plate 16 may be present at the end point 25 and bears against the end point 25, the follower plate 16 likewise being provided with the welding filler material 13 and the method at the process end point 46 being terminated.
  • the leading or trailing plate 16, 19, which are preferably formed plate-shaped, is applied to the surface 10 of the substrate 4, that as possible no, preferably only a small gap between the surface 10 and an edge, so the contact surface 49 of Lead 16 or follower plate 19 results (Figure 3), d. H. the front edge of the flow plate 16 is oblique.
  • the contact surface 49 of the plates 16, 19, such as a curved surface 10 of a component 4, as is the case, for example, with turbine blades 120, 130 are curved (FIG. 4).
  • FIG. 4 shows the sequence of the welding method according to the invention.
  • a feed plate 19 is used on which the welding process is started at a process end point 43. At least at the starting point 22, the shitting process is stable ( Figure 4a).
  • the distance between the method starting point 43 and the starting point 22 is preferably 2 mm - 10 mm.
  • the welding process is carried out up to the recess end point 25 and then preferably continues to run over a follower plate 16 until it reaches a process end point 46 (FIG. 5d).
  • FIG. 6 shows a perspective view of a moving blade 120 or guide blade 130 of a flow machine, which extends along a longitudinal axis 121.
  • the flow machine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjacent thereto and an airfoil 406.
  • the blade 130 may have at its blade tip 415 another platform (not shown).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a flow-on edge 409 and a downstream edge 412 for a medium that flows past the blade 406.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloy.
  • the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a Fras vide or combinations thereof.
  • Single-crystalline structures or structures are used as components for machines that are subject to high mechanical, thermal and / or chemical stresses during operation.
  • the production of such monocrystalline workpieces for example, by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy solidifies to a monocrystalline structure, ie to a single-crystalline workpiece, or directionally.
  • dendritic crystals are aligned along the warm flow and form either a prismatic crystalline grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common usage, are referred to as directionally solidified) or a monocrystalline structure, ie the whole
  • the work consists of a single crystal.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which should be part of this disclosure with regard to the chemical composition of the alloy.
  • a thermal insulation layer consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • Suitable coating processes such as electron beam evaporation (EB-PVD), produce protuberant grains in the thermal insulation layer or, for example, atmospheric plasma spraying (APS) produces porous, micro- and macrocracked grains in the thermal insulation layer.
  • EB-PVD electron beam evaporation
  • APS atmospheric plasma spraying
  • Refurbishment means that components 120, 130 may have to be freed of protective layers after use (eg by sandblasting). After that removal of the corrosion and / or oxidation layers or products takes place. Optionally, even cracks in the component 120, 130 are repaired with the inventive method. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. When the blade 120, 130 is to be cooled, it is hollow and possibly still has film cooling holes 418 (indicated by dashed lines).
  • FIG. 7 shows a combustion chamber 110 of a gas turbine 100 (FIG. 8).
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged in the circumferential direction around a rotation axis 102 pass into a common combustion chamber space 154, which produce flames 156.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C. to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M with an inner lining formed of heat shield elements 155.
  • Each heat shield element 155 made of an alloy is equipped on the working medium side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least an element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf) ,
  • MCrAlX means: M is at least an element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf) ,
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which should be part of this disclosure with regard to the chemical composition of the alloy.
  • ceramic maintenance can medamm Mrs be present and consists for example of ZrC> 2, Y2Ü3-ZrO 2, ie, it is not partially full text or ⁇ dig stabilized by yttrium oxide and / or calcium and / or magnesium oxide.
  • Electron Beam Evaporation produces proton grains in the thermal insulation layer.
  • Refurbishment means that heat shield elements 155 may need to be deprotected (e.g., by sandblasting) after use. This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired by the method according to the invention. This is followed by a re-coating of the heat shield elements 155 and a renewed use of the heat shield elements 155.
  • a cooling system can additionally be provided for the heat shield elements 155 or for their holding elements.
  • the heat shield elements 155 are then hollow, for example, and may still have film cooling holes (not shown) which still touch the combustion chamber space 154.
  • FIG. 8 shows by way of example a gas turbine 100 in a long partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
  • a compressor 105 for example, a torus-like
  • Combustion chamber 110 in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust gas housing 109.
  • the annular combustion chamber 110 communicates with an example annular hot gas channel 111.
  • Each turbine stage 112 is formed, for example, from two blade rings.
  • a series of guide vanes 115 follows a series of vanes 120 in the hot gas duct 111 of a row of vanes 115.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the rotor blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is guided to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 relaxes on the rotor blades 120 in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during the operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113 are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only slow grains (DS structure).
  • SX structure monocrystalline
  • DS structure slow grains
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloys.
  • the vane 130 has a Leitschaufelfuß facing the réellegehause 138 of the turbine 108 (not shown here) and a Leitschaufelfuß the opposite vane head on.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Plasma & Fusion (AREA)
  • Optics & Photonics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Les procédés de soudage de la technique connue ont l'inconvénient de fournir, au début du processus de soudage, de plus mauvais points de soudage que lors du déroulement ultérieur du processus. En conséquence, le procédé selon l'invention est caractérisé en ce qu'on utilise une plaque d'entrée (19) sur laquelle commence le processus de soudage, et qui est ensuite guidée, lorsque le processus est en mesure de fournir une qualité uniforme des points de soudage (13), vers les points à réparer (10).
EP06830251A 2005-12-19 2006-11-30 Procede de soudage et dispositif de soudage Withdrawn EP1963043A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06830251A EP1963043A1 (fr) 2005-12-19 2006-11-30 Procede de soudage et dispositif de soudage

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05027790A EP1797985A1 (fr) 2005-12-19 2005-12-19 Procédé et dispositif de soudage
EP06830251A EP1963043A1 (fr) 2005-12-19 2006-11-30 Procede de soudage et dispositif de soudage
PCT/EP2006/069157 WO2007071537A1 (fr) 2005-12-19 2006-11-30 Procede de soudage et dispositif de soudage

Publications (1)

Publication Number Publication Date
EP1963043A1 true EP1963043A1 (fr) 2008-09-03

Family

ID=36423619

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05027790A Withdrawn EP1797985A1 (fr) 2005-12-19 2005-12-19 Procédé et dispositif de soudage
EP06830251A Withdrawn EP1963043A1 (fr) 2005-12-19 2006-11-30 Procede de soudage et dispositif de soudage

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05027790A Withdrawn EP1797985A1 (fr) 2005-12-19 2005-12-19 Procédé et dispositif de soudage

Country Status (3)

Country Link
US (1) US8158906B2 (fr)
EP (2) EP1797985A1 (fr)
WO (1) WO2007071537A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9321116B2 (en) * 2009-03-05 2016-04-26 United Technologies Corporation Cold metal transfer gas metal arc welding apparatus and method of operation
FR2984783B1 (fr) * 2011-12-23 2014-09-12 Snecma Dispositif de rechargement d’une piece en alliage metallique
US9126287B2 (en) 2012-03-12 2015-09-08 Siemens Energy, Inc. Advanced pass progression for build-up welding
CN107452577B (zh) * 2017-06-13 2023-05-12 湖北汉光科技股份有限公司 速调管电子枪薄壁侧热屏零件制造方法
WO2020158878A1 (fr) * 2019-02-01 2020-08-06 株式会社Ihi Procédé de réparation de fissure
CN116140910B (zh) * 2023-04-21 2023-07-07 成都和鸿科技股份有限公司 一种导向叶片测量管和安装支架的焊接工装及焊接方法

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE419026A (fr) *
US3073948A (en) * 1959-06-25 1963-01-15 Arcos Corp Process for welding by fusing a metal strip and article produced
GB1131031A (en) * 1964-12-02 1968-10-16 Arcos Corp Improvements in overlay welding
US3493713A (en) * 1967-02-20 1970-02-03 Arcos Corp Electric arc overlay welding
US3596041A (en) * 1969-07-31 1971-07-27 Stoody Co Roller rebuilding system
JPS5017349A (fr) * 1973-06-19 1975-02-24
US4234776A (en) * 1978-07-12 1980-11-18 Thermatool Corp. Method of producing areas of alloy metal on a metal part using electric currents
US4266110A (en) * 1978-12-13 1981-05-05 Combustion Engineering, Inc. Clad welding on an inclined surface
FR2761627B1 (fr) * 1997-04-04 1999-07-09 Proner Comatel Sa Procede de realisation d'une bande metallique a brasure incorporee, pour constituer des pieces de contact
US6049060A (en) * 1998-12-15 2000-04-11 General Electric Company Method for welding an article and terminating the weldment within the perimeter of the article

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007071537A1 *

Also Published As

Publication number Publication date
US20090001065A1 (en) 2009-01-01
US8158906B2 (en) 2012-04-17
EP1797985A1 (fr) 2007-06-20
WO2007071537A1 (fr) 2007-06-28

Similar Documents

Publication Publication Date Title
EP1857218A1 (fr) Procédé de réparation d'élément et un élement
EP2547488B1 (fr) Procédé de reconditionnement d'une aube de turbine avec au moins une plate-forme
EP1645653A1 (fr) Revêtement protecteur
EP1867423A1 (fr) Procédé de réparation d'une pièce par brasage d'une tôle revêtue de brasure
EP1941965A1 (fr) Réouverture de trous à l'aide de la thermographie et d'un composant
EP1816316B1 (fr) Procédé de réparation de composants
WO2011113831A1 (fr) Réparation d'arêtes de pièces structurales au moyen de préformes préfrittées en bandes (psp) et pièce structurale
EP1963043A1 (fr) Procede de soudage et dispositif de soudage
EP2391744B1 (fr) Revêtement par des procédés de revêtement thermiques et non thermiques
EP2373824A1 (fr) Procédé pour recouvrir un composant pourvu de trous de refroidissement pelliculaire et composant
EP2274130A1 (fr) Composant avec cordon de soudure et procédé de fabrication d'un cordon de soudure
WO2009118313A2 (fr) Élément à soudures superposées et procédé de production correspondant
WO2008049460A1 (fr) PROCÉDÉ POUR RÉGLER LA RUGOSITÉ de surface LORS D'UNE OPÉRATION DE REVÊTEMENT À BASSE TEMPÉRATURE, ET ÉLÉMENT DE CONSTRUCTION
EP2240293A1 (fr) Procédé et dispositif pour fondre des surfaces incurvées
EP2226149A1 (fr) Procédé de soudure en deux étapes
EP2217400A1 (fr) Procédé de brasage de fissures larges
WO2009087189A2 (fr) Brasage de trous, procédé de revêtement et baguettes de brasure
WO2006069822A1 (fr) Procede de creation d'un trou
WO2009053154A1 (fr) Procédé pour éliminer une couche métallique au moyen du procédé fic au cours d'une étape intermédiaire
EP1658924A1 (fr) Pièce avec une rainure remplie
EP1808251B1 (fr) Procédé de dressage d'un électrode d'érosion et d'usinage par électro-érosion
EP1930115A1 (fr) Fil, son utilisation et procédé de soudage
WO2007085512A1 (fr) Procede de fabrication d'un composant dote de trous
EP1867749A1 (fr) Procédé de revêtement d'un matériau à une pièce
WO2009089840A1 (fr) Procédé et dispositif d'usinage par électro-érosion régulé

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20080421

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

17Q First examination report despatched

Effective date: 20140710

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20150725