WO2010057475A1 - Procédé de fabrication et/ou de réparation d'un rotor d'une turbomachine et rotor associé - Google Patents

Procédé de fabrication et/ou de réparation d'un rotor d'une turbomachine et rotor associé Download PDF

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Publication number
WO2010057475A1
WO2010057475A1 PCT/DE2009/001636 DE2009001636W WO2010057475A1 WO 2010057475 A1 WO2010057475 A1 WO 2010057475A1 DE 2009001636 W DE2009001636 W DE 2009001636W WO 2010057475 A1 WO2010057475 A1 WO 2010057475A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
blade
base body
metal alloy
rotor base
Prior art date
Application number
PCT/DE2009/001636
Other languages
German (de)
English (en)
Inventor
Erwin Bayer
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 WO2010057475A1 publication Critical patent/WO2010057475A1/fr

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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
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • 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
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • 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
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • 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
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/514—Porosity
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to a method for producing and / or repairing a rotor of a turbomachine.
  • the invention further relates to a rotor for a turbomachine specified in the preamble of claim 11 type and a turbomachine specified in the preamble of claim 13 type with perspectivess- least one rotor.
  • Rotors of turbomachines are technically only expensive and correspond to costly to produce and repair.
  • the rotors are thereby increasingly formed as integrally bladed rotors, which, if a disk-shaped rotor body is present, as a blisk (bladed disk) or, if an annular rotor body is present, as a bling (bladed ring) are called.
  • Prior art methods of manufacturing or repairing require blades having a solid blade root to initiate the forces of the linear friction welding process used to join the blade to the rotor body.
  • Such blades, so-called hollow blades are usually produced by superplastic forming processes and diffusion bonding of two blade halves with a third, folded intermediate layer. The intermediate layer is connected alternately on one or the other blade half and thus increases the blade stiffness.
  • a disadvantage of the known rotors is the fact that they are technically complex and expensive to manufacture.
  • Object of the present invention is therefore to provide such a rotor, which is easier and less expensive to produce and / or repairable.
  • the object is achieved by a method according to claim 1 for manufacturing and / or repairing a rotor of a turbomachine, a rotor having the features of claim 11 for a turbomachine and a turbomachine with the features of claim 13.
  • Advantageous embodiments 5 with expedient developments of the invention are specified in the respective subclaims, wherein advantageous embodiments of the method - if applicable - are to be regarded as advantageous embodiments of the rotor or the turbomachine and vice versa.
  • a rotor base body and at least one blade are provided, wherein the blade comprises a porous shaped body, which is coated at least in regions with a metal alloy.
  • the at least one blade is arranged on the rotor base body and connected to the rotor main body.
  • the vibration stiffness is achieved by the difference in the modulus of elasticity (modulus of elasticity) between the preferably isotropic shaped body and the o metal alloy of the at least one blade serving as surface or wall material.
  • modulus of elasticity modulus of elasticity
  • the advantages achieved in the manufacture of the rotor are basically also achieved in the case of a repair, since missing or damaged surface material of the at least one blade can be repaired simply and cost-effectively by recoating with the metal alloy.
  • at least one blade is provided, which comprises a sintered and / or glued and / or foamed molding. In this way, the respectively most suitable blade can be variably selected and provided, whereby the rotor can be optimally adapted to its respective application point during production.
  • the shaped body can be made out of be sintered or glued hollow balls produced molded body, wherein the hollow balls may consist of a metallic or ceramic material, a composite material or the like. Likewise, it can be provided that a molding consisting of a metal foam is provided. Alternatively or additionally, the shaped body can also be produced in several parts or from different materials.
  • At least one blade is provided, in which the metal alloy is applied to the shaped body by means of a thermal spraying method, in particular a cold-kinetic compacting method.
  • the metal alloy can thus be applied to the molding, without this on or melt.
  • a high surface quality of the blade and thus an optimized functionality of the rotor is ensured.
  • K3 or cold spray method has the particular advantage that the supply of thermal energy can at least largely be dispensed with and thus the requirements for oxide-poor surface layers can be reliably fulfilled.
  • particularly precise layer thicknesses, hardnesses and porosities can be produced.
  • flame spraying method plasma spraying method, detonation spraying method, arc wire spraying method and the like can also be used.
  • flame spraying method plasma spraying method, detonation spraying method, arc wire spraying method and the like
  • arc wire spraying method Corresponding to 5 in the case of a repair of the blade or the rotor, by missing or damaged surface material can be easily repaired by re-coating with the metal alloy.
  • the at least one blade is processed, in particular finely worked and / or repaired, before and / or after connection to the rotor base body.
  • a blade is provided in which the metal alloy with respect to the desired outer contour of the blade was at least partially applied with an oversize 5 on the molding. With the help of such an overmeasure or dimensions, possible manufacturing tolerances can be better taken into account and an actual outer contour of the blade can be easily adapted to the desired outer contour.
  • a blade may be provided which fits excessively in a connection region provided for connecting the blade to the rotor base body of the rotor, thereby achieving improved mechanical stability and weldability.
  • the desired outer contour of the blade is produced after the coating of the shaped body, at least in the region of the excess, by means of a separation method, in particular by means of a chip method and / or an electrochemical removal method. In this way, the desired desired outer contour 5 can be produced quickly, reliably and precisely.
  • the use of cutting processes with a geometrically defined cutting edge, for example milling has proved to be advantageous in order to produce the desired outer contour of the blade inexpensively with the desired precision.
  • ECM electrochemical removal processes
  • PECM electrochemical metal working processes
  • the separation method can be used in the case of a repair of the blade or of the rotor analogously to the simple, quick and precise removal of excess metal alloy.
  • the at least one blade is welded to the rotor base body.
  • the blade can be easily, inexpensively and o process-reliable connected to the rotor body.
  • a connection region of the at least one blade provided for connecting the at least one blade to the rotor is welded over its entire area to the rotor base body and / or that the metal alloy serving as wall material is welded to the rotor base body 5. If the shaped body of the blade is completely or at least coated in the connection region with the metal alloy, the blade can be welded according to the entire surface with the rotor base body of the rotor in order to achieve a mechanically high-strength connection.
  • the aforementioned pressure welding methods can also be used to advantage for the possibility of repositioning the rotor and for replacing the at least one blade.
  • the use of a diffusion welding method allows a joining of the blade with a comparatively low compression pressure on the joint surface, so that it can be advantageously dispensed with collars and the like and mechanical deformation of the rotor are particularly reliable 5 excluded.
  • the rotor is processed at least in the connection region of the at least one blade by means of a separation process, in particular a chip process and / or a removal process.
  • a separation process in particular a chip process and / or a removal process.
  • a multi-blade rotor having the advantages mentioned above can be manufactured and / or repaired.
  • a further aspect of the invention relates to a rotor for a turbomachine, in particular an integrally bladed blisk and / or bling for a gas turbine, with a rotor main body, which is connected to at least one blade.
  • a simpler and more cost-effective manufacturability of the rotor according to the invention is given by the fact that the at least one blade comprises a porous molded body, which is at least partially coated with a metal alloy.
  • more cost-effective and material-reduced manufacturability of the rotor according to the invention is also reduced in weight and has a high vibration stiffness.
  • the vibration stiffness is achieved by the difference in the modulus of elasticity (modulus of elasticity) between the preferably isotropic shaped body and the surface or wall material serving metal alloy of the blade.
  • the invention relates to a turbomachine, in particular a gas turbine, with at least one rotor, in particular with an integrally bladed blisk and / or bling, the rotor being manufactured according to the invention by means of a method according to one of the preceding embodiments and / or according to one the previous embodiments is formed.
  • a rotor base body and at least one blade are provided, wherein the blade comprises a porous shaped body, which is coated at least partially with a metal alloy.
  • the porous shaped body can be made, for example, from a metal foam and / or sintered or glued hollow spheres.
  • the shaped body which preferably already has an outer contour which corresponds to a desired outer contour of the blade, is subsequently surrounded by a titanium alloy, which is applied to the shaped body by means of a cold-kinetic compacting method with superimposed or oversized dimensions. It can also be provided that the shaped body is repeatedly coated with the metal alloy and / or with different metal alloys in order to obtain special properties of the blade.
  • the shaped body is not coated, in particular in a connection area provided for connecting the blade to a rotor base body, so that only coated wall areas of the blade are connected to the rotor base body in a later joining step.
  • the excess of the metal alloy is removed by means of milling or electrochemical metal machining (ECM) or precise electrochemical metal working (PECM), so that the desired target outer contour of the blade is produced.
  • ECM electrochemical metal machining
  • PECM precise electrochemical metal working
  • the blade is placed on the rotor body and connected thereto.
  • an inductive high-frequency pressure welding method (IHFP) is used as joining method, whereby a notch-free connection between the blade and the rotor base body is achieved.
  • IHFP inductive high-frequency pressure welding method
  • only coated wall areas of the blade can be connected to the rotor base body, so that no full-surface welding between the blade and the rotor base body is carried out, but only the relevant wall area is joined.
  • the testability of the joint connection is given thanks to the smooth weld bead.
  • the repair of the rotor is included given this production route. In particular, a blade exchange via IHFP is possible.
  • a blade can be provided which is also coated with the metal alloy in the joining region and, as a result, is welded over its entire surface to the rotor base body serving as the hub. Any existing or produced during welding on or oversize in the joining area can be easily removed, for example, by a subsequent milling process.
  • a plurality of blades are connected in one of the aforementioned ways with the rotor base body, whereby a multi-blade rotor can be produced with the said advantages.
  • missing surface material of a damaged blade can be supplemented with the aid of the cold-kinetic compacting method and brought back to the desired outer contour by adaptive milling or manual adjustment.
  • the rotor can be produced quickly, easily, inexpensively and with reduced material.
  • the rotor thus produced is very resistant to vibration and weight reduction compared to conventional rotors.
  • the oscillation rigidity is achieved in particular by the difference in the modulus of elasticity (modulus of elasticity) between the isotropic shaped body and the wall material of the blade consisting of the metal alloy.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé de fabrication et/ou de réparation d'un rotor d'une turbomachine, en particulier d'un disque aubagé monobloc et/ou d'un anneau aubagé monobloc d'une turbine à gaz, lequel procédé comprend au moins les étapes consistant à préparer un corps de base de rotor, à préparer au moins une aube qui comprend un corps moulé poreux au moins partiellement recouvert d'un alliage métallique, à placer l'aube sur le corps de base de rotor ainsi qu'à assembler l'aube et le corps de base de rotor. L'invention concerne également un rotor pour une turbomachine et une turbomachine munie d'au moins un rotor.
PCT/DE2009/001636 2008-11-20 2009-11-14 Procédé de fabrication et/ou de réparation d'un rotor d'une turbomachine et rotor associé WO2010057475A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008058142.9 2008-11-20
DE102008058142A DE102008058142A1 (de) 2008-11-20 2008-11-20 Verfahren zum Herstellen und/oder Reparieren eines Rotors einer Strömungsmaschine und Rotor hierzu

Publications (1)

Publication Number Publication Date
WO2010057475A1 true WO2010057475A1 (fr) 2010-05-27

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2009/001636 WO2010057475A1 (fr) 2008-11-20 2009-11-14 Procédé de fabrication et/ou de réparation d'un rotor d'une turbomachine et rotor associé

Country Status (2)

Country Link
DE (1) DE102008058142A1 (fr)
WO (1) WO2010057475A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005016588A2 (fr) * 2003-08-18 2005-02-24 Mtu Aero Engines Gmbh Procede pour realiser et/ou reparer des pieces de turbines a gaz
EP1553203A1 (fr) * 2004-01-10 2005-07-13 MTU Aero Engines GmbH Procédé pour fabriquer des aubes creuses, aussi pour un rotor avec les aubes creuses
DE102005019077A1 (de) * 2005-04-23 2006-10-26 Mtu Aero Engines Gmbh Schaufel einer Strömungsmaschine und Verfahren zur Herstellung und/oder Reparatur derselben

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DE19942916A1 (de) * 1999-09-08 2001-03-15 Linde Gas Ag Herstellen von aufschäumbaren Metallkörpern und Metallschäumen
EP1186748A1 (fr) * 2000-09-05 2002-03-13 Siemens Aktiengesellschaft Aube de rotor pour une turbomachine et turbomachine
EP1382707A1 (fr) * 2002-07-17 2004-01-21 Siemens Aktiengesellschaft Systeme stratifie
DE10246454A1 (de) * 2002-10-04 2004-04-15 Rwth Aachen Herstellung beschichteter geschäumter Bauteile und Bauteile mit keramischer oder Hartstoffbeschichtung
EP1475567A1 (fr) * 2003-05-08 2004-11-10 Siemens Aktiengesellschaft Structure stratifiée et procédé de fabrication de la structure stratifiée
EP1481747A3 (fr) * 2003-05-27 2007-05-02 Alstom Technology Ltd Procédé de fabrication d'une pièce chargée par chaleur et piéce
EP1566519A1 (fr) * 2004-02-23 2005-08-24 Siemens Aktiengesellschaft Composant à haute température d'une turbomachine et turbomachine
EP1707651A1 (fr) * 2005-03-31 2006-10-04 Siemens Aktiengesellschaft Système de revêtement et procédé de fabrication d'une système de revêtement
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