WO2010002295A1 - Procédé de soudage - Google Patents

Procédé de soudage Download PDF

Info

Publication number
WO2010002295A1
WO2010002295A1 PCT/SE2008/000430 SE2008000430W WO2010002295A1 WO 2010002295 A1 WO2010002295 A1 WO 2010002295A1 SE 2008000430 W SE2008000430 W SE 2008000430W WO 2010002295 A1 WO2010002295 A1 WO 2010002295A1
Authority
WO
WIPO (PCT)
Prior art keywords
metal
metal object
vane
buildup
providing
Prior art date
Application number
PCT/SE2008/000430
Other languages
English (en)
Inventor
Henrik Gustavsson
Peter Jonsson
Original Assignee
Volvo Aero Corporation
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 Volvo Aero Corporation filed Critical Volvo Aero Corporation
Priority to PCT/SE2008/000430 priority Critical patent/WO2010002295A1/fr
Publication of WO2010002295A1 publication Critical patent/WO2010002295A1/fr

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
    • B23K33/00—Specially-profiled edge portions of workpieces for making soldering or welding connections; Filling the seams formed thereby
    • 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
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines

Definitions

  • the present invention relates to a welding method comprising providing a metal object intended to be welded at at least one weld region to at least one metal device.
  • weld joint can provide a structural weakness, for example in attracting stress concentrations, in the resulting assembled unit.
  • gas turbine engines for example where vanes are welded at their ends and extend through a gas flow channel, it is important to provide weld joints that are able to withstand structural stresses under extreme conditions, in particular high temperatures.
  • the gas turbine engine is used for airplane propulsion purposes, it is of course important to keep weight of structural components, including weld joints, as low as possible.
  • a welding method comprising providing, a metal object intended to be welded at at least one weld region to at least one metal device, characterized in that it comprises providing by metal deposition at least one metal buildup element at the weld region, and thereafter welding the metal object to the metal device, at least a part of the metal buildup element forming at least a part of the weld joint.
  • the method is advantageously applied in production or repair of a gas turbine engines, for example where blades or vanes are welded to a metal device such as a structure or a structural portion in the form of an outer casing or a hub of an engine part, or where blades or vanes are welded to a metal device such as a base or a platform which mates with a recess in an outer casing or a hub.
  • Providing the metal object intended to be welded can include producing the metal object in a number of alternative manners, as exemplified below, which metal object presents at least one designated weld region, i.e. a region of the metal object where the weld joint is to be formed when the object is welded to the metal device.
  • the metal buildup element is produced by metal deposition after the provision of the metal object, and is therefore provided by additional material.
  • the metal buildup element serves as a reinforcement at the weld region. Thereby, more material is presented at the region of the intended weld joint, providing a wider welding joint compensating for any reduction in structural properties caused by the welding.
  • weld reinforcements are produced separately by metal deposition, other steps in the production are independent of the reinforcement production. This means that the metal object itself can be produced in a manner providing a high structural integrity.
  • a less advantageous alternative to the invention is producing the blades or vanes by casting the blades or vanes, whereby the blades or vanes are designed so that they present a thicker portion at one or both of their ends, after which the blades or vanes are welded to a structural portion, such as an outer casing, of the engine part, whereby the thicker portion forms a part of the weld joint.
  • a problem with such a solution, avoided by the invention is that casting processes usually gives as a result that the material of the objects are structurally inferior than the material of objects produced in other manners, such as forging. Therefore, more material has to be used for objects produced by casting, which adds weight to the finished product, which is often a disadvantage, for example in the case of gas turbine engines for airplane propulsion applications.
  • the metal object can be produced in a manner, for example involving forging, providing a higher structural integrity than that of casting.
  • Another advantage with involving forging sheet metal in the provision of the metal object is that the dimensional tolerances thereof are better that in the case of casting. Such an improvement of the tolerances contributes to possibilities of reducing weight of the metal object.
  • the provision of the metal object can advantageously include any suitable wroughting measure.
  • the material used for the metal object could be for example a suitable titanium, nickel, steel or aluminum alloy.
  • the metal deposition can be carried out by a variety of alternative processes, known in the art of metal deposition, and could involve building up a three dimensional geometry in metal by using a welding source, (weld build-up or weld deposition), including for example laser beam, electron beam, or gas tungsten arc welding (GTAW), (also known as tungsten inert gas (TIG) welding), at which the material could be fed in any suitable manner, for example in the form of a wire or powder. More specific metal deposition examples include laser cladding and direct laser forming. In gas turbine engine applications, the material fed could be for example a suitable titanium, nickel, steel or aluminum alloy.
  • weld deposition is known from EP 1260300 A2 for the production of vanes for gas turbine engines, it is not known to be used to overcome the problems mentioned above specifically arising at joining by welding.
  • the welding of the metal object to the metal device can be done in a variety of manners known per se in the art of welding, and could involve for example laser beam, electron beam, or GTAW (TIG).
  • GTAW GTAW
  • the metal object can be provided in a variety of manners.
  • the step of providing the metal object can comprise a metal extrusion process for producing a plurality of metal objects with a constant cross-sectional shape, or even producing the metal object by casting.
  • the metal object may be a hollow structure, and at least one of the at least one metal buildup element can be located on the outside of the metal object, or alternatively on the inside of the metal object.
  • the method comprises providing by metal deposition at least two metal buildup elements at the weld region, at least one of the metal buildup elements being located on the inside of the metal object, and at least one of the metal buildup elements being located on the outside of the metal object.
  • the metal object is a vane for a stationary part of a gas turbine engine.
  • a stationary part would normally present a central axis and the vane could be adapted to extend at last partly radially in relation to the central axis.
  • the weld region could be located at an end of the vane forming an inner or an outer end of the vane in the stationary part.
  • the metal device could be for example an inner portion or an outer portion of the stationary part.
  • the metal device could a base or a platform which is intended to mate with a complementary recess in an inner portion or an outer portion of the stationary part.
  • the inner and outer portion is herein also referred to as a hub and an outer casing, respectively.
  • the metal object is a blade for a rotatable part of a gas turbine engine, the weld region being located at an end of the blade forming an inner or an outer end of the blade in the rotatable part.
  • - fig. 1 shows a schematic perspective view of a metal object intended to be mounted on a metal device
  • - fig. 2 shows a cross-sectional view of the metal object, with the section oriented along the line H-II in fig. 1,
  • - fig. 3 shows a cross-sectional view of the metal object, with the section oriented along the line IH-III in fig. 2, - fig. 4 shows a cross-sectional view corresponding to the one in fig, 3, after a further production stage of the metal object,
  • - fig. 5 shows a view corresponding to the one in fig. 1, of the metal object at the same stage in production as shown in fig. 4,
  • - fig. 6 shows a cross-sectional view corresponding to the one in fig. 4, after another production stage of the metal object,
  • - fig. 7 shows a cross-sectional view corresponding to the one in fig. 6, of the result of a further alternative embodiment of the invention
  • - fig. 7a and 7b show side views of a metal plate with metal buildup elements in an alternative method of providing the result in fig. 7, - fig. 8 and fig. 9 show cross-sectional views corresponding to the one in fig. 6, of respective results of additional embodiments of the invention, and
  • Fig. 1 shows a schematic perspective view of a metal object 1 in the form of a vane intended to be welded to a metal device in the form of a hub, herein also referred to as an inner portion, in the production of a stationary part of a gas turbine engine.
  • the vane could be intended to be welded to a metal device in the form of an outer casing of the stationary part, the outer casing being herein also referred to as an outer portion.
  • the vane is a hollow structure with an aerofoil shape.
  • the vane is produced from two forged sheet metal pieces 2, 3, which have been joined by welding at the leading edge 4 and the trailing edge 5 of the resulting vane 1.
  • the vane 1 is to be welded to the hub at a weld region 6 (fig. 1 and fig. 3) at one end of the vane 1, which vane end will be the inner end of the vane when mounted in the stationary part of the gas turbine engine.
  • the weld region 6 is formed by the end surface 6 at the inner end.
  • a metal buildup element 7 is provided on the weld region 6 by metal deposition.
  • the metal buildup element 7 surrounds the inner end of the vane.
  • a plurality of metal buildup elements 7 can be provided along the inner end of the vane 1.
  • the vane is welded to the hub 8, so that the weld joint follows the entire inner end of the vane 1, and the metal buildup element 7 forms a part of the weld joint.
  • the hub 8 presents a protruding portion 81 which is complementary to the inner portion of the vane 1.
  • Fig. 7 depicts an alternative embodiment of the invention, where two metal buildup elements 7 are located on the inside of the vane 1. This will eliminate the risk of the metal buildup elements 7 disturbing a gas flow in the gas turbine engine.
  • the embodiment depicted in fig. 7, the metal buildup element 7 is provided before the two forged sheet metal pieces 2, 3 (fig. 2) are joined.
  • Fig. 7a and fig. 7b depicts steps in an alternative method of providing the metal buildup elements 7 as presented in fig. 7.
  • the metal buildup elements 7 are provided at the weld region. Thereafter, the plate is forged so as to provide the form as depicted in fig. 7b, whereupon the ends of the forged plate is joined by welding to form the trailing edge 5 of the vane.
  • Fig. 8 depicts a further alternative of the invention, where a metal buildup element 7 is located on the inside of the vane 1, and a further metal buildup element 7 is located on the outside of the vane 1. This will reduce any tendency for deformation of the vane 1 as a result of the metal deposition.
  • at least the inner metal buildup element 7 is provided before the two forged sheet metal pieces 2, 3 (fig. 2) are joined.
  • Fig. 9 depicts a yet another alternative of the invention, similar to the one described above with reference to fig. 1 - fig- 6, with the exception that the hub 8 does not present any protruding portion which is complementary to the inner portion of the vane 1.
  • fig. 10 As has been mentioned above, the invention is of course also applicable for the purpose of joining the outer end of the vane 1 to an outer casing, which outer end is the upper end in fig. 10. Thereby, similarly to what has been described above concerning the inner end of the vane 1, a metal buildup element 7 can be provided at the outer end of the vane 1 before welding the vane to the outer casing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)

Abstract

L'invention porte sur un procédé de soudage qui comporte l’utilisation d'un objet métallique (1) destiné à être soudé en au moins une région de soudure (6) à au moins un dispositif métallique (8), le procédé étant caractérisé par le fait qu'il comporte l’utilisation, par dépôt de métal, d'au moins un élément d'accumulation de métal (7) au niveau de la région de soudure (6), puis le soudage de l'objet métallique (1) au dispositif métallique (8), au moins une partie de l'élément d'accumulation de métal (7) formant au moins une partie du joint de soudure.
PCT/SE2008/000430 2008-07-04 2008-07-04 Procédé de soudage WO2010002295A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/SE2008/000430 WO2010002295A1 (fr) 2008-07-04 2008-07-04 Procédé de soudage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2008/000430 WO2010002295A1 (fr) 2008-07-04 2008-07-04 Procédé de soudage

Publications (1)

Publication Number Publication Date
WO2010002295A1 true WO2010002295A1 (fr) 2010-01-07

Family

ID=41466177

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2008/000430 WO2010002295A1 (fr) 2008-07-04 2008-07-04 Procédé de soudage

Country Status (1)

Country Link
WO (1) WO2010002295A1 (fr)

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013075815A1 (fr) * 2011-11-22 2013-05-30 Lufthansa Technik Ag Procédé de réparation d'un élément de turbine à gaz
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
US9850774B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Flow diverter element and assembly
US9890663B2 (en) 2012-12-31 2018-02-13 United Technologies Corporation Turbine exhaust case multi-piece frame
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
US9903216B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Gas turbine seal assembly and seal support
US9982564B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Turbine frame assembly and method of designing turbine frame assembly
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US10006306B2 (en) 2012-12-29 2018-06-26 United Technologies Corporation Turbine exhaust case architecture
US10054009B2 (en) 2012-12-31 2018-08-21 United Technologies Corporation Turbine exhaust case multi-piece frame
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
US10240532B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Frame junction cooling holes
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10329957B2 (en) 2012-12-31 2019-06-25 United Technologies Corporation Turbine exhaust case multi-piece framed
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US10330011B2 (en) 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1260300B1 (fr) * 2001-05-26 2005-08-24 ROLLS-ROYCE plc Procédé de fabrication d'une pièce
WO2006005296A1 (fr) * 2004-07-08 2006-01-19 Mtu Aero Engines Gmbh Procede de liaison d'aubes a des emplantures ou a des disques de rotor lors de la fabrication et / ou de la reparation d'aubes de turbines a gaz ou de rotors de turbines a gaz a aubes constituees d'un seul tenant avec le rotor
WO2007073976A1 (fr) * 2005-12-22 2007-07-05 Alstom Technology Ltd Procede de fabrication d'un rotor soudé pour turbine à gaz basse pression par soudage avec apport de matière et revenu de détente

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1260300B1 (fr) * 2001-05-26 2005-08-24 ROLLS-ROYCE plc Procédé de fabrication d'une pièce
WO2006005296A1 (fr) * 2004-07-08 2006-01-19 Mtu Aero Engines Gmbh Procede de liaison d'aubes a des emplantures ou a des disques de rotor lors de la fabrication et / ou de la reparation d'aubes de turbines a gaz ou de rotors de turbines a gaz a aubes constituees d'un seul tenant avec le rotor
WO2007073976A1 (fr) * 2005-12-22 2007-07-05 Alstom Technology Ltd Procede de fabrication d'un rotor soudé pour turbine à gaz basse pression par soudage avec apport de matière et revenu de détente

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013075815A1 (fr) * 2011-11-22 2013-05-30 Lufthansa Technik Ag Procédé de réparation d'un élément de turbine à gaz
US10240532B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Frame junction cooling holes
US9850774B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Flow diverter element and assembly
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
US9903216B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Gas turbine seal assembly and seal support
US9982564B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Turbine frame assembly and method of designing turbine frame assembly
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
US10941674B2 (en) 2012-12-29 2021-03-09 Raytheon Technologies Corporation Multi-piece heat shield
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
US10006306B2 (en) 2012-12-29 2018-06-26 United Technologies Corporation Turbine exhaust case architecture
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US10329957B2 (en) 2012-12-31 2019-06-25 United Technologies Corporation Turbine exhaust case multi-piece framed
US10054009B2 (en) 2012-12-31 2018-08-21 United Technologies Corporation Turbine exhaust case multi-piece frame
US9890663B2 (en) 2012-12-31 2018-02-13 United Technologies Corporation Turbine exhaust case multi-piece frame
US10330011B2 (en) 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing

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