WO2013029584A1 - Procédé de réalisation, de réparation et/ou d'échange d'un système composite rotor/stator, et système composite rotor/stator réalisé selon le procédé - Google Patents

Procédé de réalisation, de réparation et/ou d'échange d'un système composite rotor/stator, et système composite rotor/stator réalisé selon le procédé Download PDF

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Publication number
WO2013029584A1
WO2013029584A1 PCT/DE2012/000809 DE2012000809W WO2013029584A1 WO 2013029584 A1 WO2013029584 A1 WO 2013029584A1 DE 2012000809 W DE2012000809 W DE 2012000809W WO 2013029584 A1 WO2013029584 A1 WO 2013029584A1
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WO
WIPO (PCT)
Prior art keywords
rotor
stator
composite system
support structure
forming
Prior art date
Application number
PCT/DE2012/000809
Other languages
German (de)
English (en)
Inventor
Edgar MERKL
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 WO2013029584A1 publication Critical patent/WO2013029584A1/fr

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Classifications

    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • B22F10/40—Structures for supporting workpieces or articles during manufacture and removed afterwards
    • 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
    • B22F10/60—Treatment of workpieces or articles after build-up
    • 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
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • 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
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • 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
    • 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
    • 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
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • 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
    • 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
    • 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
    • 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
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a method of manufacturing, repairing and / or replacing a rotor / stator composite system.
  • the rotor-stator composite system is here in particular a rotor / stator composite system of an aircraft engine.
  • a method for producing a high-pressure turbine rotor wherein the turbine rotor is designed as a blisk and a radially inwardly disposed disc and a plurality of projecting from this disc blades or blades forms.
  • the turbine rotor has an inner channel system for air cooling. At least the turbine rotor is generated by a generative manufacturing process.
  • the turbo-engine has a housing that encloses a flow passage in which a rotationally driven first fan rotor rotates. Behind the first fan rotor, a second fan rotor is arranged, which rotates in opposite directions to the first fan rotor. Between the fan rotors is a booster compressor, which has two booster rotors. The first fan rotor accelerates incoming air and drives it into a main flow path and a bypass path. Both flow paths are separated by a tubular spinner. The spinner is mounted in a bearing which is fixed relative to the housing and fixed to a stator with a variable angle of attack.
  • the invention is based on the object to provide a method for producing or forming, repairing and / or replacing an improved composite of rotor and stator, as well as such a rotor / stator composite.
  • a method for manufacturing, repairing and / or replacing a rotor / stator compound system, in particular a compressor or a turbine of an engine, with a rotor having at least one blade element and a stator, the method having the following step : Layer-wise building up of the rotor with the at least one blade element together with the stator by means of a generative manufacturing process.
  • a rotor / stator composite system in particular a compressor or a turbine of an engine, provided with a rotor having at least one blade element and a stator, wherein the rotor is formed with the at least one blade element together with the stator by means of a generative manufacturing process.
  • the method and the system have the advantage that the rotor and the stator can be manufactured in one step and thus can be dispensed with additional flanges or grooves, which were previously necessary for the assembly of the individual parts.
  • the step of constructing the rotor and the stator in layers further comprises the steps of building up a support structure by means of the additive manufacturing process, then forming the rotor-stator composite system on the support structure by means of the additive manufacturing process and removing the support structure Completion of the rotor / stator compound system.
  • the support structure has the advantage that the composite system does not have to be built directly on the base plate.
  • the fixing of the rotor and of the stator takes place by means of a holding device, the support structure subsequently being removed.
  • the support means By the support means, the rotor and stator can be held and fixed in a predetermined, in particular centered position, while the support structure is removed.
  • the step of laminating the rotor and the stator further comprises the step of forming the stator with at least one blade element.
  • the step of constructing the rotor and the stator in layers further comprises the step of forming the stator and the rotor with a plurality of blade elements, wherein the blade elements of the stator and the rotor are offset from one another.
  • the step of laminating the rotor and the stator further comprises the step of forming at least one end of the stator and / or the rotor with at least one mounting portion.
  • the integrally formed with the stator or rotor mounting portion allows a subsequent simplified assembly to other components.
  • the step of constructing the rotor and the stator in layers further comprises the step of forming at least a part of the rotor and the stator from the same material or material combination, or forming at least a part of the rotor and the stator from a different one Material or from a different combination of materials.
  • the blade elements of the rotor and the rotor housing may be made of a different material or combination of materials.
  • the blade elements of the stator and the stator housing may be made of a different material or combination of materials.
  • the blade elements of the rotor, the blade elements of the stator, the rotor housing and / or the stator housing can be made of a different material or material combination or of the same material or the same material combination, depending on the function and purpose.
  • FIG. 1 is a sectional view of a rotor / stator composite system according to an embodiment of the invention
  • Fig. 2 is a flow chart of the manufacture of a rotor / stator composite system according to the invention.
  • Fig. 1 is a sectional view of a rotor / stator composite system 1 according to an embodiment of the invention is shown.
  • the mountability must be taken into account by providing and appropriately positioning respective flanges, grooves and the like.
  • this has the disadvantage that it is a design-, weight and cost-optimized design of the composite considerably more difficult.
  • an integral rotor / stator composite system 1 is provided, which is produced by means of a generative manufacturing process.
  • This has the advantage that rotor 2 and stator 3 are not, as previously, later assembled and accordingly with this additional fastening devices, such as flanges, grooves, etc., must be provided for mounting the items.
  • additive manufacturing processes include so-called rapid manufacturing and so-called rapid prototyping.
  • generative manufacturing components are built up, in particular, in layers by material application.
  • material application for example, in the corresponding processes known as Laser Sintering, Selective Laser Sintering (SLS), Electron Beam Melting (EBM), LaserCusing, Selective Laser Melting (SLM) or 3D Printing, etc.
  • the material to be added or applied is Processed powder.
  • the powder is applied, for example, in layers on a base plate or a carrier.
  • the powder layer is solidified in a device region for forming the device by means of energy radiation, such as a laser beam and / or electron beam.
  • the component can be built layer by layer.
  • the solidification of the respective powder layer is usually carried out on the basis of geometric data, such as CAD data, of the component to be produced.
  • the area of the powder layer can be scanned, for example, and the component area of the powder layer can be solidified by means of energy radiation. By acting on the energy radiation, the powder is sintered or melted in this area.
  • the sectional view of an embodiment of the rotor / stator composite system 1 according to the invention shown in FIG. 1 is in this case for example a compressor, e.g. for an engine, in particular an aircraft engine.
  • the rotor / stator compound system may also include a turbine e.g. for an engine, in particular aircraft engine.
  • the rotor / stator composite system 1 in this case has the rotor 2, which has a rotor housing 4 with a plurality of blade elements 5.
  • the rotor / stator composite system 1 the stator 3, which has a stator 6, on which, as illustrated in the embodiment in Fig. 1, optionally additionally a plurality of blade elements 7 can be provided.
  • the blade elements 5, 7 of rotor 2 and stator 3 can be arranged to each other in such a way that they are arranged, for example offset from one another, as shown in the embodiment in Fig. 2.
  • the rotor 2 and / or the stator 3 can have at least one end of their housing 4, 6 least a mounting portion 8, for example at least one flange or a receptacle.
  • At least one powder which can be solidified by means of an energy radiation is applied as a powder layer to a support 9, here for example a base plate 10.
  • the powder is in particular a metal powder of at least one metal and / or one metal alloy.
  • the at least one powder may also be, for example, a ceramic powder or plastic powder, which can be solidified by means of energy radiation.
  • the powder layer is selectively solidified by means of energy radiation from an energy radiation source 11, eg a laser or an electron beam source.
  • the powder layer is solidified in its component region by means of the energy radiation of the energy radiation source 1 1.
  • the rotor / stator compound system 1 comprises, for example, the rotor housing 4 with a plurality of blade elements 5, the stator housing 6 with a plurality of blade elements 7, in each case a fastening section 8 at both ends of the rotor housing 4 and the stator housing 6 ,
  • a respective powder layer may also have areas with different powders.
  • a portion of the device area which is e.g. comprises the stator 3, can be formed from a first powder and a further portion of the component area, which e.g. comprises the rotor 2 may be formed of a second powder.
  • different metal powders may be chosen for the first and second powders, so that the rotor 2 and the stator 3 are made of different materials, here e.g. various metals or metal alloys are produced.
  • the blade elements 5, 7 of rotor 2 and / or stator 3 made of a different material or material combination than the rotor housing 4 and / or stator 6 are produced in the generative manufacturing process.
  • the invention is not limited to the examples mentioned.
  • the materials or material combinations for the rotor / stator composite system 1 can be varied as desired within the framework of the generative production of the rotor / stator composite system 1.
  • the rotor / stator composite system 1 is manufactured by means of a generative manufacturing process in one step or one piece.
  • the rotor 2 and the stator 3 normally form two separate parts, as shown in the exemplary embodiment in Fig. 1, wherein the rotor 2 and the stator 3, for example, each concentric with each other and have a common longitudinal axis 12.
  • a support structure 13 may optionally be initially formed on the carrier 9, here the base plate 10, before subsequently the actual component 1, ie the rotor / stator composite system 1, is formed.
  • the respective powder layer can be solidified somewhat coarser in the region of the support structure 13 by means of the energy radiation of the energy radiation source 11, so that the support structure 13 is formed, for example, similar to a needle bed, on which then the actual rotor / stator composite system 1 is formed becomes.
  • the rotor / stator composite system 1 does not have to be formed directly on the carrier 9 or the base plate 10.
  • the support structure 13 is removed again, as indicated by the dividing line in Fig. 1.
  • the support structure 13 can additionally be used to position the rotor 2 and the stator 3 relative to one another, for example when the rotor 2 is slightly raised or offset in height relative to the stator 3 or vice versa.
  • Additional fastening sections 8, for example in the form of at least one flange or a receptacle, on the exposed or open upper side 14 of the stator housing 6 or of the rotor housing 4 can, if necessary, be reworked very easily.
  • the rotor 2 and stator 3 can be fixed in a centric position if necessary by means of an additional holding device 15, before the support structure 13 is separated with the base plate 10. After separation of the support structure 13 and the base plate 10, the respective attachment portion 8 at the lower end 16 of the stator housing 6 or rotor housing 4 can also be reworked if necessary.
  • the rotor / stator composite system 1 as an overall system is easy to install.
  • the mounting device 15 can be removed, for example, before assembly or attachment of the rotor / stator composite system 1 to an engine or after attachment to the engine, depending on the function and purpose.
  • the invention also has the advantage that in the generative production of the rotor / stator composite system 1, the blade elements 5, 7 of rotor 2 and stator 3, for example, formed offset from each other. In this way, eliminates a complicated assembly of rotor 2 and stator 3 to each other.
  • Fig. 2 an embodiment of a flow chart for manufacturing a rotor / stator composite system according to the invention is shown.
  • a first step S1 an auxiliary structure or support structure of the component or rotor / stator composite system is first formed on the carrier or the base plate in advance by means of a generative manufacturing process.
  • the support structure will be removed later after completion of the rotor / stator composite system.
  • a powder layer is applied to the baseplate and then irradiated by a suitable energy beam of an energy radiation source, e.g. a laser, a support structure area of the powder layer solidifies. Subsequently, the base plate is moved by a layer thickness, e.g. lowered, and the next powder layer applied to the previous powder layer and in turn solidified the support structure region of this powder layer by means of energy radiation. Step S1 is repeated until the support structure is constructed.
  • an energy radiation source e.g. a laser
  • the actual component here the rotor / stator composite system, built.
  • the rotor / stator composite system is constructed with its rotor and its stator.
  • the rotor comprises a rotor housing having a plurality of vane elements.
  • the stator has a stator housing with a plurality of blade elements, which are arranged offset to the blade elements of the rotor.
  • a fastening portion for example a flange or a receptacle.
  • a new powder layer is applied to the last solidified powder layer and the new powder layer in the component area of the rotor / stator composite system solidified by a suitable energy radiation of an energy radiation source, such as a laser or electron beam source.
  • an energy radiation source such as a laser or electron beam source.
  • the base plate is moved by one layer thickness, for example lowered, and the next powder layer is applied to the previous powder layer and the component area of the rotor / stator composite system of this powder layer is solidified by means of the energy radiation.
  • the step S2 is repeated until the rotor / stator composite system is made entirely of the solidified component regions.
  • a step S3 the non-solidified powder is removed.
  • a subsequent step S4 the support structure of the rotor / stator composite system is removed.
  • the centric positioning of the stator and the rotor can be secured or fixed by means of a suitable mounting device.
  • the mounting device is fastened, for example, to the stator and the rotor, for example to their fastening sections. Subsequently, the support structure is removed.
  • Step S4 * a respective attachment portion of the rotor / stator compound system is machined on the open side of the rotor / stator compound system, if necessary. Step S4 * may take place before removal or after removal of the support structure in step S4.
  • step Sl of producing an additional support structure is optional and the associated step S4, in which the support structure after the completion of the rotor / stator composite system is removed again.
  • step S4 * of reworking a fastening section of the rotor / stator composite system is optional.
  • Blade element (rotor housing)
  • Blade element (stator housing)

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un système composite rotor/stator et un procédé de réalisation, de réparation et/ou d'échange d'un système composite rotor/stator, notamment d'un compresseur ou d'une turbine d'un mécanisme de propulsion, ledit système comprenant un rotor qui présente au moins un élément pale, et un stator. Selon l'invention, le procédé comprend les étapes suivantes : élaboration couche par couche du rotor comprenant le au moins un élément aube, avec le stator au moyen d'un procédé de fabrication génératif.
PCT/DE2012/000809 2011-08-27 2012-08-10 Procédé de réalisation, de réparation et/ou d'échange d'un système composite rotor/stator, et système composite rotor/stator réalisé selon le procédé WO2013029584A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011111848 2011-08-27
DE102011111848.2 2011-08-27

Publications (1)

Publication Number Publication Date
WO2013029584A1 true WO2013029584A1 (fr) 2013-03-07

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015088852A1 (fr) * 2013-12-13 2015-06-18 United Technologies Corporation Fabrication additive de structure de support de carénage
EP3051068A1 (fr) * 2015-02-02 2016-08-03 MTU Aero Engines GmbH Bague d'aube directrice pour une turbomachine et procédé de fabrication additive
DE102015202070A1 (de) * 2015-02-05 2016-08-25 MTU Aero Engines AG Gasturbinenbauteil
WO2016184685A1 (fr) * 2015-05-20 2016-11-24 Man Diesel & Turbo Se Procédé de fabrication d'un rotor de turbomachine
DE102016201581A1 (de) * 2016-02-02 2017-08-03 MTU Aero Engines AG Rotor-Stator-Verbund für eine axiale Strömungsmaschine und Flugtriebwerk
EP3712380A1 (fr) * 2019-03-19 2020-09-23 MTU Aero Engines GmbH Composant pour moteur d'avion, un module d'un moteur d'avion avec un tel composant et procédé de fabrication du composant par fabrication additive

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DE102006023246A1 (de) 2006-05-18 2007-11-22 Deutsches Zentrum für Luft- und Raumfahrt e.V. Turbotriebwerk
EP1905963A2 (fr) * 2006-09-28 2008-04-02 Pratt & Whitney Canada Corp. Redresseurs de flux pour soufflante avec disrupteurs de vorticité dans la chambre de calme
WO2008046386A1 (fr) * 2006-10-18 2008-04-24 Mtu Aero Engines Gmbh Procédé de fabrication d'un élément de turbine à gaz
DE102006049216A1 (de) 2006-10-18 2008-04-24 Mtu Aero Engines Gmbh Hochdruckturbinen-Rotor und Verfahren zur Herstellung eines Hochdruckturbinen-Rotors

Patent Citations (4)

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Publication number Priority date Publication date Assignee Title
DE102006023246A1 (de) 2006-05-18 2007-11-22 Deutsches Zentrum für Luft- und Raumfahrt e.V. Turbotriebwerk
EP1905963A2 (fr) * 2006-09-28 2008-04-02 Pratt & Whitney Canada Corp. Redresseurs de flux pour soufflante avec disrupteurs de vorticité dans la chambre de calme
WO2008046386A1 (fr) * 2006-10-18 2008-04-24 Mtu Aero Engines Gmbh Procédé de fabrication d'un élément de turbine à gaz
DE102006049216A1 (de) 2006-10-18 2008-04-24 Mtu Aero Engines Gmbh Hochdruckturbinen-Rotor und Verfahren zur Herstellung eines Hochdruckturbinen-Rotors

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015088852A1 (fr) * 2013-12-13 2015-06-18 United Technologies Corporation Fabrication additive de structure de support de carénage
EP3051068A1 (fr) * 2015-02-02 2016-08-03 MTU Aero Engines GmbH Bague d'aube directrice pour une turbomachine et procédé de fabrication additive
DE102015201782A1 (de) * 2015-02-02 2016-08-18 MTU Aero Engines AG Leitschaufelring für eine Strömungsmaschine
US10280775B2 (en) 2015-02-02 2019-05-07 MTU Aero Engines AG Guide vane ring for a turbomachine
DE102015202070A1 (de) * 2015-02-05 2016-08-25 MTU Aero Engines AG Gasturbinenbauteil
US11248484B2 (en) 2015-02-05 2022-02-15 MTU Aero Engines AG Gas turbine component
WO2016184685A1 (fr) * 2015-05-20 2016-11-24 Man Diesel & Turbo Se Procédé de fabrication d'un rotor de turbomachine
CN107735196A (zh) * 2015-05-20 2018-02-23 曼柴油机和涡轮机欧洲股份公司 用于制造涡轮机的转子的方法
CN107735196B (zh) * 2015-05-20 2020-12-08 曼恩能源方案有限公司 用于制造涡轮机的转子的方法
US10913113B2 (en) 2015-05-20 2021-02-09 Man Energy Solutions Se Method for producing a rotor of a flow engine
DE102016201581A1 (de) * 2016-02-02 2017-08-03 MTU Aero Engines AG Rotor-Stator-Verbund für eine axiale Strömungsmaschine und Flugtriebwerk
EP3712380A1 (fr) * 2019-03-19 2020-09-23 MTU Aero Engines GmbH Composant pour moteur d'avion, un module d'un moteur d'avion avec un tel composant et procédé de fabrication du composant par fabrication additive

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