GB2315697A - Repairing by welding parts made of Ni-based alloys - Google Patents

Repairing by welding parts made of Ni-based alloys Download PDF

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Publication number
GB2315697A
GB2315697A GB9714455A GB9714455A GB2315697A GB 2315697 A GB2315697 A GB 2315697A GB 9714455 A GB9714455 A GB 9714455A GB 9714455 A GB9714455 A GB 9714455A GB 2315697 A GB2315697 A GB 2315697A
Authority
GB
United Kingdom
Prior art keywords
component
welding
susceptor
repair part
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.)
Granted
Application number
GB9714455A
Other versions
GB9714455D0 (en
GB2315697B (en
Inventor
Reinhold Meier
Bernd Stimper
Heinz Leger
Herbert Hanrieder
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 GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen 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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB9714455D0 publication Critical patent/GB9714455D0/en
Publication of GB2315697A publication Critical patent/GB2315697A/en
Application granted granted Critical
Publication of GB2315697B publication Critical patent/GB2315697B/en
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • 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
    • B23K13/00—Welding by high-frequency current heating
    • B23K13/01—Welding by high-frequency current heating by induction heating
    • 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
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/60—Preliminary treatment
    • 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
    • B23K9/16—Arc welding or cutting making use of shielding gas
    • B23K9/167—Arc welding or cutting making use of shielding gas and of a non-consumable electrode
    • 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
    • B23K9/235—Preliminary treatment
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • 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

Abstract

A component (1) to be repaired is arranged in thermal contact within an induction-flow susceptor (3). A repair part (2) adapted to the component (1) is attached thereto and the component (1) is preheated by inductively heating the susceptor (3). The repair part (2) is then welded to the component (1). The component may be a turbine blade.

Description

2315697 A process and agoaratus for repairing by welding parts made of
Ni-based alloys This invention relates to a process and apparatus for the repairing by welding of parts made of Ni-based alloys, wherein a repair part is welded to a component to be repaired.
In the case of components made of Ni-based alloys and subjected to wear, such as vanes of turbo-engines and in particular turbine blades, there is a constant need to restore the worn components. For reasons of economy, this restoration frequently takes the form of welding repair parts to the worn component instead of complete replacement of that component, for example a turbine blade.
Ni-based alloy, a material frequently used to manufacture turbine blades, is difficult to weld or not weldable at all, and thus the repair of components, in particular turbine blades, made of this material is problematic, all the more so since extremely high demands are placed on these components with respect to the strength and reliability of the repair undertaken, for example the weld between the component and the welded-on repair part.
The repair welding of Ni alloys has hitherto been carried out by electronbeam, laser, TIG or plasma welding, if at all, with simultaneous preheating of the parts to be welded. For example, in current conventional repair-welding processes, the tip of a turbine blade with, 2 large dimensions is welded on in a plurality of widths and layers. As subsequent adaptation to the blade profile is necessary, large welding passes are required. This procedure is laborious and impractical.
An object of the invention is to provide a process and apparatus for repairing by welding parts made of superalloys, in particular Ni-based alloys, by means of which repair welding is simple and practical.

Claims (22)

  1. The invention provides a process as claimed in Claim 1.
    An advantage of the process according to the invention is that reliable repair welding of parts made of superalloys, in particular Ni-based alloys, can be carried out in a simple manner.
    A further advantage of the process according to the invention is that precise heat conduction is achievable before, during and after welding and, as a result, discontinuities in the temperature gradient and corresponding negative effects on the component structure are avoidable.
    Preferably, in the process according to the invention, shielding gas is supplied to the weld during the welding operation in step (d).
    Preferabl, the component to be repaired is held by the susceptor.
    The welding operation in step (d) may be carried out by means of electronbeam, laser, TIG or plasma welding.
    3 Preferably, the welding operation in step (d) is a plug welding process. This has the advantage that welding takes place without the use of a filler metal, thereby simplifying the welding operation.
    The process according to the invention for repairing turbine blades, in particular of jet engines, is particularly advantageous.
    According to a particularly advantageous embodiment of the process according to the invention, a preformed repair part is used to repair turbine blades, in particular turbine blades of jet engines. The repair part has a slot adapted to the end profile of the turbine blade for accommodating the end thereof. This enables a large number of turbine blades to be repaired cost-effectively with uniform high quality.
    For this purpose, a repair part is preferably used which is of substantially uniform thickness. This has the advantage that it ensures welding with constant welding parameters in the material.
    Preferably, after step (d), the welded-on repair part is shaped, by surface working, to the profile of the component to be repaired.
    The invenfion further provides apparatus as claimed in Claim 11.
    An advaritage of the apparatus according to the invention is that it is easy to hondle. A further advantage is that repair welds of uniformly high quality and reliability can be produced.
    The fact that, the susceptor, in use, surrounds the component to be repaired and is adapted to the shape thereof means that there is good 4 thermal contact between the component and the susceptor; the region of the component to be repaired, to which the repair part is to be welded, is left free of the susceptor. The advantage of this is that the component is uniformly preheated by the susceptor.
    Preferably, the susceptor is a two-part form openable to receive the component to be repaired.
    The means for generating the inducflon flow is preferably an induction coil surrounding the susceptor.
    The welding means is preferably a welding torch.
    The welding means may provide electron-beam, laser, TIG or plasma welding.
    According to a particularly advantageous embodiment of the invention, the susceptor has a contact surface arranged opposite the welding means for the component to be repaired and/or the repair part. This has the advantage that the component is well preheated in the region of the weld.
    According to another advantageous embodiment, the apparatus has two opp6Sed welding torches for acting upon the component to be repaired Ond the repair part with energy from two sides. The advantage of this is that the welding parameters within the welding region are practically uniform and so achieve the best welding results.
    According to a further embodiment of the invention, one or more heat sensors for measuring the temperature of the component to be repaired are arranged in the susceptor. It is thereby possible to preheat the component precisely to a predetermined temperature by regulating the induction flow through the susceptor.
    According to a further embodiment, the apparatus has means for supplying shielding gas to the weld.
    These means for supplying shielding gas are preferably formed by gas supply ducts provided in the susceptor.
    The apparaf us according to the invention may be used to repair by welding turbine blades, in particular of jet engines.
    An embodiment of the invention will now be described with reference to the accompanying drawings, wherein:
    Fig. 1 is a cross-sectional side view of apparatus for repairing by welding parts made of Ni-based alloys according to one embodiment of the invention; Fig. 2 is a c,:ross-sectional view through the apparatus shown in Fig. 1.
    In Fig. 1, the reference numeral 1 designates a component to be repaired, for example <3 turbine blade of a jet engine, the profile of which is shown in Fig. 2. The component I is held by a susceptor 3 surrounding the component 1 and adapted to the shape thereof, thus producing good thermal contact between the component 1 and the 6 susceptor 3. The susceptor 3 comprises a material of high magnetic susceptibility and is surrounded by apparatus for generating an induction flow through the susceptor 3, the apparatus being formed by an induction coil 5 surrounding the susceptor 3. Insulation 4 comprising ceramic material is arranged between the induction coil 5 and the susceptor 3 and insulates the induction coil 5 from the susceptor 3 both thermally and electrically. The susceptor 3 is formed as a two-part form which can be opened to receive the component 1, i.e. the turbine blade in the present embodiment.
    As can be seen from Fig. 2 in particular, a plurality of heat sensors 7 are arranged inside the susceptor 3 on the surface of the recess provided to receive the component 1 so that they are in thermal contact with the component 1. The purpose of the heat sensors 7 is to measure the temperature of the component 1 being repaired. The current through the induction coil 5 is regulated by means of this measured temperature so that the component 1 has a desired predetermined temperature in the region of the weld to be produced.
    Adjacent the end of the component 1, the susceptor 3 has a contact surface 3a, on which the repair part 2 to be welded to the component 1 rests. The repair part 2 is a preformed part having a slot shaped to the end profile, of the component 1 and provided for receiving the end thereof. Welding apparatus in the form of a welding torch 6 is arranged in the reglon of the weld between the component 1 and the repair part 2.
    7 Gas supply ducts 8 are formed in the susceptor 3 and supply shielding gas to the region of the weld between the component 1 and the repair part 2.
    To weld the repair part 2 to the component 1, the component 1 is first arranged in the susceptor 3, where it comes into close thermal contact therewith. The repair part 2 is then attached to the component 1. By supplying electric current to the induction coil 5, a strong magnetic field flows through the susceptor 3 and heats it. The heating of the susceptor is regulated by the temperature measured by the heat sensors 7. When a desired predetermined temperature optimum for welding has been reached, the repair part 2 is welded to the component 1 by means of the welding torch 6, and shielding gas is simultaneously supplied by the shieiding-gas supply ducts 8.
    Welding is preferably by means of a plug welding process and therefore it is not necessary to use a filler metal.
    The repair part is of substantially uniform thickness.
    The welded-on repair part is then shaped, by surface working, to the profile of the component being repaired.
    8 Claims 1 A process for repairing by welding a component and a repair part both made of Ni-based alloys including the following steps:
    (a) the component is arranged in an induction-flow suscepfor adapted to the shape thereof and surrounding the component and in thermal contact therewith, (b) the repair part adapted to the component is arranged thereagainst, (c) the component and/or the repair part is preheated by inductively heating the susceptor, and (d) the repair part is welded to the component.
  2. 2. A process according to Claim 1, wherein shielding gas is supplied to the weld during the welding in step (d).
  3. 3. A process according to Claim I or 2, wherein the component is held by the susceptor.
  4. 4. A peocess according to any one of Claims 1 to 3, wherein the welding in step (d) is carried out by means of electron-beam, laser, TIG or plasma welding.
  5. 5. A process according to any one of Claims 1 to 4, wherein the welding in step (d) is a plug welding process.
    9
  6. 6. A process according to any one of Claims 1 to 5, wherein the component is a turbine blade.
  7. 7. A process according to Claim 6, wherein the repair part is preformed and has a slot adapted to the end profile of the turbine blade for accommodating the end thereof.
  8. 8. A process according to Claim 7, wherein the repair part is of substantially uniform thickness.
  9. 9. A process according to any one of Claims 1 to 8, wherein after step (d), the welded-on repair part is shaped by surface working to the profile of the component being repaired.
  10. 10. Apparatus for repairing by welding a component and a repair part both made of Ni-based alloys including:
    an induction-flow susceptor for surrounding and being in thermal contact with the component, means for generating an -induction flow through the susceptor, welding means for welding together the component and a repair part.
  11. 11. Apparatus according to Claim 10, wherein the susceptor is a twopart form openable to receive the component.
  12. 12. Apparatus according to Claim 10 or 11, wherein the means for generating the induction flow is an induction coil surrounding the susceptor.
  13. 13. Apparaf us according to any one of Claims 10 to 12, wherein the welding means is a welding torch.
  14. 14. Apparatus according to any one of Claims 10 to 12, wherein the welding means provides electron-beam, laser, TIG or plasma welding.
  15. 15. Apparatus according to any one of Claims 10 to 14, wherein the susceptor has a contact surface arranged opposite the welding means for supporting the component and/or the repair part.
  16. 16. Apparatus according to any one of Claims 10 to 15, and including two opposed welding torches for acting upon the component and the repair part from two sides.
  17. 17. Apparatus according to any one of Claims 10 to 16, wherein one or more heat sensors for measuring the temperature of the cortiponent are arranged in the susceptor.
  18. 18. Apparatus according to any one of Claims 10 to 17, and including means for supplying shielding gas to the weld.
  19. 19. Apparatus according to Claim 18, wherein the means for supplying shielding gas comprise gas supply ducts in the susceptor.
  20. 20. Apparatus for repairing a turbine blade substantially as herein described with reference to the accompanying drawings.
  21. 21. A process for repairing a turbine blade by welding substantially as herein described with reference to the accompanying drawings.
  22. 22. A turbine blade repaired by the process as claimed in any one of Claims 1 to 9 and 21.
    1
GB9714455A 1996-07-30 1997-07-08 A process and apparatus for repairing by welding parts made of Ni-based alloys Expired - Fee Related GB2315697B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19630703A DE19630703C2 (en) 1996-07-30 1996-07-30 Method and device for repair welding of parts made of Ni-based alloys and application of the method and device

Publications (3)

Publication Number Publication Date
GB9714455D0 GB9714455D0 (en) 1997-09-10
GB2315697A true GB2315697A (en) 1998-02-11
GB2315697B GB2315697B (en) 2000-02-16

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Family Applications (1)

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GB9714455A Expired - Fee Related GB2315697B (en) 1996-07-30 1997-07-08 A process and apparatus for repairing by welding parts made of Ni-based alloys

Country Status (3)

Country Link
DE (1) DE19630703C2 (en)
FR (1) FR2751903B1 (en)
GB (1) GB2315697B (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007308798A (en) * 2006-05-17 2007-11-29 General Electric Co <Ge> Device for repairing high-pressure turbine blade
US8022330B2 (en) 2003-09-24 2011-09-20 Mtu Aero Engines Gmbh Method and device for welding structural components
EP2777857A3 (en) * 2013-03-14 2015-07-15 General Electric Company Joining methods and temperature controlled fluid treating systems for joining
CN110773839A (en) * 2019-11-13 2020-02-11 安徽应流集团霍山铸造有限公司 Welding process method for preventing repair welding cracks of nickel-based alloy bent pipe

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19807637C2 (en) * 1998-02-23 2001-01-11 Mtu Muenchen Gmbh Friction welding process for blading a rotor for a turbomachine
DE10047492A1 (en) * 2000-09-26 2002-04-25 Schweistechnische Lehr Und Ver Welding metallic work material with inductive preheating has conventional welding tools like arc welders or roller electrodes coupled with inductor(s) with inductor power of 15 to 30 kW
SG155788A1 (en) * 2008-03-18 2009-10-29 Turbine Overhaul Services Pte Methods and apparatuses for correcting twist angle in a gas turbine engine blade
US8809724B2 (en) 2008-08-04 2014-08-19 General Electric Company Strategically placed large grains in superalloy casting to improve weldability
DE102008047042A1 (en) * 2008-09-13 2010-03-18 Mtu Aero Engines Gmbh Device and method for inductive heating of metallic components
CN114043043B (en) * 2021-11-23 2023-03-14 成都飞机工业（集团）有限责任公司 Repair method for nickel-based superalloy by CMT (controlled mechanical Transmission) arc repair

Citations (3)

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Publication number Priority date Publication date Assignee Title
GB2008011A (en) * 1977-11-09 1979-05-31 Union Carbide Corp Stress relieving of metal/ceramic abdradable seals
GB1568826A (en) * 1975-11-24 1980-06-04 Gen Electric Method and apparatus for vacuum induction bonding
GB2262901A (en) * 1991-12-19 1993-07-07 Mtu Maintenance Gmbh Method and apparatus for welding superalloys

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE776589A (en) * 1970-12-21 1972-04-04 Krupp Ag Huettenwerke PROCESS FOR THE REALIZATION OF LARGE ROTATING STEEL PARTS INTENDED FOR THE CONSTRUCTION OF LARGE MACHINES (CONSTRUCTION OF GENERATOR AND TURBINE SHAFTS)
NL7103019A (en) * 1971-03-06 1972-09-08

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1568826A (en) * 1975-11-24 1980-06-04 Gen Electric Method and apparatus for vacuum induction bonding
GB2008011A (en) * 1977-11-09 1979-05-31 Union Carbide Corp Stress relieving of metal/ceramic abdradable seals
GB2262901A (en) * 1991-12-19 1993-07-07 Mtu Maintenance Gmbh Method and apparatus for welding superalloys

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8022330B2 (en) 2003-09-24 2011-09-20 Mtu Aero Engines Gmbh Method and device for welding structural components
JP2007308798A (en) * 2006-05-17 2007-11-29 General Electric Co <Ge> Device for repairing high-pressure turbine blade
US7875135B2 (en) 2006-05-17 2011-01-25 General Electric Company High pressure turbine airfoil recovery device and method of heat treatment
EP2777857A3 (en) * 2013-03-14 2015-07-15 General Electric Company Joining methods and temperature controlled fluid treating systems for joining
CN110773839A (en) * 2019-11-13 2020-02-11 安徽应流集团霍山铸造有限公司 Welding process method for preventing repair welding cracks of nickel-based alloy bent pipe

Also Published As

Publication number Publication date
GB9714455D0 (en) 1997-09-10
FR2751903A1 (en) 1998-02-06
FR2751903B1 (en) 1999-09-03
DE19630703A1 (en) 1998-02-05
DE19630703C2 (en) 2000-02-10
GB2315697B (en) 2000-02-16

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Effective date: 20130708