EP2355947A2 - Procédé de réparation - Google Patents

Procédé de réparation

Info

Publication number
EP2355947A2
EP2355947A2 EP09771488A EP09771488A EP2355947A2 EP 2355947 A2 EP2355947 A2 EP 2355947A2 EP 09771488 A EP09771488 A EP 09771488A EP 09771488 A EP09771488 A EP 09771488A EP 2355947 A2 EP2355947 A2 EP 2355947A2
Authority
EP
European Patent Office
Prior art keywords
gas turbine
process chamber
metal powder
repaired
separating surface
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Withdrawn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
EP09771488A
Other languages
German (de)
English (en)
Inventor
Roland Huttner
Karl-Heinz Dusel
Erwin Bayer
Albin Platz
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
Publication of EP2355947A2 publication Critical patent/EP2355947A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • 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
    • B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
    • 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
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/70—Recycling
    • B22F10/73—Recycling of powder
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • the invention relates to a repair method for gas turbine components, in particular for gas turbine blades. Furthermore, the invention relates to a process chamber for the repair method according to the invention.
  • Gas turbine components such as gas turbine blades of an integrally bladed gas turbine rotor are subject to wear during operation. Wear can make it necessary to repair the gas turbine components after damage by removing damaged portions of the gas turbine components from them and renewing them after removing the damaged portions.
  • stator-side rotor blades of integrally bladed gas turbine rotors are subject to wear, in particular due to oxidation, corrosion, erosion, and bird strike or even hail, so that damaged portions thereof must be removed and replaced after removal.
  • stator-side components such as guide vanes or housing structures are subject to wear, which may require a repair of the same.
  • DE 3909733 A1 discloses a method for repairing, for example, integrally bladed gas turbine rotors, in which a damaged section of the gas turbine blade to be repaired is removed and renewed after removal of the same by welding a replacement part.
  • a damaged section of the gas turbine blade to be repaired is removed and renewed after removal of the same by welding a replacement part.
  • inductive pressure welding is used.
  • rotor blades of a gas turbine rotor can be repaired by renewing same by laser powder build-up welding after removal of a damaged portion from the blade.
  • laser powder build-up welding it is difficult to ensure adequate contour accuracy.
  • the present invention is based on the problem of providing a novel repair method for gas turbine components, in particular for gas turbine blades.
  • the repair method for gas turbine components comprises at least the following steps: a) provision of a gas turbine component to be repaired; b) removing a damaged portion of the gas turbine engine component to be repaired to form a planar interface; c) at least partially arranging the gas turbine component to be repaired in a process chamber, such that the planar separation surface extends approximately horizontally within the process chamber; d) filling the process chamber with a material compatible with the material of the gas turbine component to be repaired metal powder, namely up to the level of the interface; e) building the removed portion on the parting surface by coating metal powder on the parting surface and fusing the metal powder applied to the parting surface layer by layer with the parting surface.
  • a repair of gas turbine components can be realized while ensuring a high contour accuracy.
  • a damaged portion removed from a gas turbine component to be repaired can be renewed with a minimum of oversize.
  • Another advantage of the method according to the invention is that a high quality of the forming material structure can be ensured.
  • the method according to the invention can be automated and therefore enables good reproducibility. Furthermore, the method allows cost-effective repair of gas turbine components compared to other repair methods.
  • a process chamber according to the invention is defined in claim 8. Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Exemplary embodiments of the invention will be explained in more detail with reference to the drawing, without being limited thereto. Showing:
  • FIG. 1 shows a representation to illustrate the method according to the invention and a process chamber according to the invention in the repair of an integrally bladed gas turbine rotor.
  • FIG. 2 a longitudinal section through the arrangement of Fig. 1; and FIG. 3 shows a cross section through the arrangement of FIG. 1.
  • the invention relates to a repair method for gas turbine components, in particular for gas turbine blades.
  • the method is particularly suitable for repairing gas turbine blades of an integrally bladed gas turbine rotor and for repairing complex housing structures of a gas turbine.
  • a gas turbine component to be repaired is provided. Subsequently, in a second step of the method according to the invention, a damaged section is removed from the gas turbine component to be repaired, namely with the formation of an approximately planar separation surface.
  • the gas turbine component to be repaired is positioned at least in sections in a third step in a process chamber, namely such that the planar parting surface is oriented or extends approximately horizontally.
  • the process chamber is filled with metal powder, wherein the metal powder is compound-compatible with the material of the gas turbine component to be repaired.
  • This filling of the process chamber with the metal powder takes place up to the level of the separating surface, ie until the edges of the separating surface are reached.
  • the process chamber can be evacuated or flooded with inert gas or inert gas.
  • the section removed from the gas turbine component is reconstructed on the separation surface in a sixth step of the process according to the invention, namely by applying metal powder layer by layer to the separation surface and by fusing the metal powder applied in layers to the separation surface the interface.
  • This layer-by-layer application of metal powder and fusion thereof with the interface is done in several steps until the removed section has been rebuilt.
  • the fusion of the metal powder applied in layers with the separating surface takes place by using a thermal energy source, in particular using a laser or an electron beam.
  • the erf ⁇ ndungssiee method allows a contour accurate construction of the removed, damaged section on the separation surface with minimal oversize. It forms a high quality of the material structure.
  • smoothing of the rebuilt portion may occur to form the original contour on the repaired gas turbine component.
  • the repair method according to the invention is particularly suitable for the repair of
  • Gas turbine blades such. B. rotor-side blades or stator-side vanes.
  • the repair method of the invention finds use in the repair of blades of an integrally bladed gas turbine rotor. Also can
  • FIGs. 1 to 3 illustrate the invention for the preferred application in the repair of an integrally bladed gas turbine rotor 10 in the region of a blade 11 thereof.
  • a connection portion 19 of the blade 11 in a process chamber 12 wherein the connection portion 19 of the blade 11 via an insertion opening of the process chamber 12 in such a receiving space 13 of the process chamber 12 is introduced, that a parting surface 20 of the blade 11 within the process chamber 12 and within the receiving space 13 thereof extends horizontally.
  • the insertion opening of the process chamber 12 is assigned a sealing device 14 in order to seal the connecting section 19 of the moving blade 11, which is inserted into the receiving space 13 of the same via the insertion opening of the process chamber 12, with respect to the insertion opening.
  • the process chamber 12 can be inserted into the same metal powder via a filling opening 18 and positioned on the separating surface 20 of the blade 11, wherein the process chamber 12 is applied to the separating surface 20 of the blade 11 by means of a translationally displaceable slide 15
  • Metal powder can be made uniform. Alternatively, by processing the process chamber or reducing the volume, the powder in the process chamber can be used for the layer application.
  • the method according to the invention can be carried out particularly preferably in the repair of integrally bladed gas turbine rotors.
  • the process chamber 12 is characterized by a small, compact design, which makes it possible to selectively and safely repair a damaged blade of an integrally bladed gas turbine rotor.
  • the connecting section 19 of the moving blade 11 introduced into the process chamber 12 can be sealed.
  • the slider 15 serves to equalize the metal powder applied to the parting surface 20 of the connecting section 19 of the moving blade 11 and also to even out a surface of a powder bed 21 positioned in the receiving space 13.
  • a section removed from the damaged moving blade 11 can be arranged in layers or layers are renewed in layers, wherein for this purpose the process chamber 12 relative to the blade 11 in the micron range is relatively displaced.
  • a metering device by means of which the metal powder can be introduced via the insertion opening 18 into the receiving space 13 of the process chamber 12, and a beam source, which serves to fuse the metal powder with the material of the blade 11 to be repaired, not shown.
  • a blade 11 of an integrally bladed gas turbine rotor 10 can be selectively renewed.
  • Process chamber are positioned, but only the damaged and to be renewed Blade 11 is arranged in the process chamber 12. Thereby, a local powder bed for selectively renewing the blade 11 of an integrally bladed gas turbine rotor 10 is provided. Interference contours, such as with respect to the parting surface 20 of the damaged blade 11 projecting, adjacent blades do not hinder the repair of the damaged blade 11th
  • the separating surface 20 within the process chamber 12 is realigned by means of a relative movement between the process chamber 12 and the gas turbine rotor 10, with subsequent new metal powder the introduction port 18 of the process chamber is inserted therein to renew the powder layer on the separation surface 20 of the blade 11.
  • the metal powder applied to the separating surface 20 of the blade 11 to be repaired is in turn uniformed by means of the slider 15, in order to then build up a new layer on the connecting region of the blade 11. This relative movement and the layered construction of the blade 11 to be repaired takes place in the ⁇ m range.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)

Abstract

Procédé de réparation pour des pièces de turbine à gaz, en particulier pour des aubes de turbine à gaz, qui comporte au moins les étapes suivantes : (a) sélection d'une pièce de turbine à réparer, (b) élimination d'une partie endommagée de la pièce de turbine à gaz à réparer et formation d'une surface de séparation plane, (c) mise en place, au moins partiellement, de la pièce de turbine à gaz à réparer dans un chambre de traitement, de manière telle que la surface de séparation plane s'étend de manière approximativement horizontale dans la chambre de traitement, (d) remplissage de la chambre de traitement avec une poudre métallique pouvant se lier à la matière qui constitue la pièce de turbine à gaz à réparer, et (e) reconstitution de la partie éliminée sur la surface de séparation par dépôt de couches de poudre métallique sur la surface de séparation et par fonte et adhérence sur la surface de séparation de la poudre métallique déposée par couches sur ladite surface de séparation.
EP09771488A 2008-11-07 2009-11-05 Procédé de réparation Withdrawn EP2355947A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008056336A DE102008056336A1 (de) 2008-11-07 2008-11-07 Reparaturverfahren
PCT/DE2009/001539 WO2010051799A2 (fr) 2008-11-07 2009-11-05 Procédé de réparation

Publications (1)

Publication Number Publication Date
EP2355947A2 true EP2355947A2 (fr) 2011-08-17

Family

ID=42096405

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09771488A Withdrawn EP2355947A2 (fr) 2008-11-07 2009-11-05 Procédé de réparation

Country Status (4)

Country Link
US (1) US8708682B2 (fr)
EP (1) EP2355947A2 (fr)
DE (1) DE102008056336A1 (fr)
WO (1) WO2010051799A2 (fr)

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CA2930572C (fr) 2013-11-14 2019-07-02 General Electric Company Fabrication en couches de composants en alliage monocristallin
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Also Published As

Publication number Publication date
US8708682B2 (en) 2014-04-29
DE102008056336A1 (de) 2010-05-12
US20110217457A1 (en) 2011-09-08
WO2010051799A3 (fr) 2010-07-15
WO2010051799A2 (fr) 2010-05-14

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