EP1903127A1 - Procédé de fabrication des composants par pulvérisation de gaz à froid et composant de turbine - Google Patents

Procédé de fabrication des composants par pulvérisation de gaz à froid et composant de turbine Download PDF

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Publication number
EP1903127A1
EP1903127A1 EP06090174A EP06090174A EP1903127A1 EP 1903127 A1 EP1903127 A1 EP 1903127A1 EP 06090174 A EP06090174 A EP 06090174A EP 06090174 A EP06090174 A EP 06090174A EP 1903127 A1 EP1903127 A1 EP 1903127A1
Authority
EP
European Patent Office
Prior art keywords
base material
core
component
turbine component
sprayed onto
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Withdrawn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
EP06090174A
Other languages
German (de)
English (en)
Inventor
Rene Jabado
Jens Dahl Dr. Jensen
Ursus Dr. Krüger
Daniel Körtvelyessy
Volkmar Dr. Lüthen
Ralph Reiche
Michael Rindler
Raymond Ullrich
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP06090174A priority Critical patent/EP1903127A1/fr
Publication of EP1903127A1 publication Critical patent/EP1903127A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D23/00—Casting processes not provided for in groups B22D1/00 - B22D21/00
    • B22D23/003—Moulding by spraying metal on a surface
    • 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
    • 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
    • B22F7/08—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 with one or more parts not made from powder
    • 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
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F05D2230/30—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
    • F05D2230/90—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
    • F05D2260/95—Preventing corrosion
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • 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 components, in particular turbine components.
  • Turbine components today typically consist of a base body on which a layer system is often still applied.
  • a method for producing a layer system is for example EP 1 382 707 A1 known.
  • an intermediate layer and a thermal barrier coating are applied to a substrate by atmospheric plasma spraying or cold gas spraying.
  • the substrate which forms the base body here is, for example, a nickel- or cobalt-based superalloy.
  • the intermediate layer serves as a corrosion, oxidation, or adhesion-promoting layer and consists, for example, of MCrAlY, where M is an element of the group iron (Fe), cobalt (Co) or nickel (Ni).
  • the thermal barrier coating is, for example, ceramic and consists, for example, of partially or fully stabilized zirconium oxide with up to 8% yttrium oxide or other rare earth oxides.
  • the layer system described can be used in particular in turbine blades.
  • Turbine blades and other turbine components are cast from the nickel or cobalt based superalloys and then coated. This requires several process steps and offers only a small degree of flexibility, since the casting molds have to be changed to change the component geometry. In addition, due to the high temperatures during casting, oxidation processes can occur on the superalloy material, so that it is not always possible to achieve the theoretically possible optimum result.
  • the invention has for its object to provide a method for the manufacture of components, in particular of turbine components, available, in which the above-mentioned problem does not occur.
  • Another object is to provide a turbine component with improved component properties.
  • the object is achieved in a method for producing components which consist of a base material in which powdered base material is sprayed onto a core by means of a cold gas spraying process and the spraying is carried out in such a way that the contour of the component is worked out during spraying.
  • components consisting of a base material for example turbine components such as blades or transition pieces
  • turbine components such as blades or transition pieces
  • inert gas eg helium or nitrogen
  • the spray parameters such. Particle velocity or mass flow can be varied.
  • the powder parameters e.g. the powder composition can be varied. This makes it possible to produce layered components and components with varying material properties (e.g., graded material composition).
  • a porous region may be formed as a porous layer. This can form the surface of the component, but it can also be arranged between two dense layers.
  • a heat-insulating material may be sprayed onto the base material to provide better protection against high temperatures.
  • the heat-insulating material can either be designed so that it forms a porous layer after spraying, or so that it forms a dense layer after spraying. Porosity can improve the thermal insulation properties of the layer.
  • a corrosion- and / or oxidation-inhibiting material can be sprayed on between the base material and the heat-insulating material, so that additional protection of the base material against corrosion and / or oxidation is ensured.
  • a corrosion and / or oxidation-inhibiting material for example, a MCrAlX material can be used.
  • MCrAlX M stands for at least one element of the group iron, cobalt or nickel and X for an active element such as yttrium (Y) and / or silicon (Si) and / or at least one element of the rare earths or hafnium (Hf).
  • Such alloys are, for example, from EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 known.
  • the corrosion and / or oxidation-inhibiting material can also be added as sacrificial anodes acting particles.
  • a base material in particular a superalloy on nickel, cobalt or iron base can be sprayed, which is a high-temperature resistant material.
  • a ceramic material can be sprayed as a base material, which offers a high corrosion and temperature resistance. It may then be possible to dispense with corrosion-inhibiting / oxidation-inhibiting coatings and thermal barrier coatings altogether.
  • a ceramic core for example, can be used, which can be rinsed after completion of the component by means of a strong acid, such as hydrofluoric acid.
  • a strong acid such as hydrofluoric acid.
  • HASTELLOY ® C-2000 or INCONEL ® Super alloys are resistant to strong acids such as sulfurous acid, hydrochloric acid or hydrofluoric acid.
  • a further advantageous development consists in a turbine component which is produced by the method according to the invention and comprises a material which has regions of different porosity.
  • the areas of different porosity may possibly serve for the passage of cooling air.
  • the material of the turbine component with the regions of different porosity can be coating material, ie the regions of different porosity are present in a coating. But it is also possible that the material is present with the areas of different porosity base material. In other words, the regions of different porosity are already present in the uncoated turbine component. Of course, also base materials with areas different porosity mut coatings, which have areas of different porosity combined.
  • FIG. 1 schematically shows the production of a turbine component 28 by a method according to the invention.
  • Base material 24 is sprayed onto a ceramic core 26 by a cold gas spray nozzle 22.
  • the spray parameters can be varied, in particular the mass flow, the particle velocity, the particle size and the particle composition.
  • the particle size determines the porosity properties of the sprayed base material.
  • the turbine component is formed by the relative movement between the ceramic core 26 and spray nozzle 22.
  • the base material is sprayed, for example, a Ni, Co or Fe based superalloy.
  • Suitable superalloys are e.g., those known under the designations HASTELLOY ® or INCONEL ® superalloys.
  • the composition of the spray powder is, for example, changed to a MCrAlX composition and a primer layer (not shown in Fig. 1) applied to the base material.
  • a further change in the composition of the spray powder for example to Y-stabilized zirconium oxide (ZrO 2 )
  • ZrO 2 Y-stabilized zirconium oxide
  • a thermal thermal barrier coating is finally sprayed onto the MCrAlX layer.
  • the ceramic core 26 is leached, for example by hydrofluoric acid (HF).
  • HF hydrofluoric acid
  • the leaching of the ceramic core 26 can be carried out either after the completion of the turbine component or after the spraying of the base material, but before completion of the entire turbine component 28, for example, before the application of a coating.
  • the advantage of premature leaching is that it can avoid possible damage to a ceramic coating (eg, ceramic thermal barrier coating, TBC) during the leaching process.
  • a ceramic material is sprayed as a base material for the turbine component 28 instead of a superalloy.
  • the core may, for example, consist of a burn-out material.
  • the material of the core should be chosen so that removal of the core is possible without attacking the ceramic base material.
  • FIG. 2 shows a perspective view of a blade 12 as an example of a component made by cold gas spraying on a core which is leached.
  • the rotor blade 12 has a fastening region 14, a blade platform 18 and an airfoil region 16.
  • a blade root 20 is formed, which is for fastening the blade 12 to a shaft of a turbomachine, also not shown, in particular a gas turbine.
  • the turbine blade 12, particularly in its airfoil region 16, has a complex geometry which can be produced by a method according to the invention, with a high degree of flexibility with respect to changes in the geometry of the rotor blade.
  • a section through the wall of a turbine component 28 according to a first embodiment variant is shown in highly schematic form in FIG.
  • a core 26 is a applied by cold gas spraying dense layer 2, which consists of a base material and forms the inside of the component wall.
  • the dense layer 2 may consist of a superalloy or of a ceramic material as the base material.
  • the core 26 may be made in a superalloy as a dense layer 2, for example. Made of ceramic.
  • the pores 7 of the porous layer 3 can be traversed by a cooling air flow 5, which serves to cool the turbine component 28.
  • the size of the pores can be adjusted by choosing the size of the spattered particles.
  • this dense layer 4 is also applied by cold gas spraying.
  • This dense layer 4 may be wholly or partly made of a thermally insulating or of a corrosion and / or oxidation-inhibiting material, such as e.g. MCrA1X exist.
  • a part of the dense layer 4 can also form the outer surface of the turbine component 28 as a thermal barrier coating (TBC). It is also possible to spray the thermal barrier coating directly onto the base material.
  • FIG. 4 shows a schematic cross section through a turbine component 28, for example a turbine blade, with a central one Air duct 6, which consists of a dense portion 8 and a porous portion 10 with pores 7.
  • the central air channel is created by leaching the ceramic core after spraying the base material.
  • a cooling air flow 5 flows in through the central air duct 6 and out through the pores 7 of the porous section 10, thus cooling the porous section 10.
  • the two sections are as well as the dense layers 2 and 4 and the porous layer 3 in FIG Cold gas spraying made.
  • Porous sections are preferably formed where the thermal loading of the turbine component 28 is greatest. By suitable position of the porous sections in the turbine component 28 and by suitable shaping and dimensioning of these sections, the generation of cooling air films over the outer surface of the turbine component 28 can also be achieved.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Composite Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06090174A 2006-09-21 2006-09-21 Procédé de fabrication des composants par pulvérisation de gaz à froid et composant de turbine Withdrawn EP1903127A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06090174A EP1903127A1 (fr) 2006-09-21 2006-09-21 Procédé de fabrication des composants par pulvérisation de gaz à froid et composant de turbine

Applications Claiming Priority (1)

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EP06090174A EP1903127A1 (fr) 2006-09-21 2006-09-21 Procédé de fabrication des composants par pulvérisation de gaz à froid et composant de turbine

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008052030A1 (de) * 2008-10-16 2010-04-22 Mtu Aero Engines Gmbh Verfahren zum Verbinden wenigstens einer Turbinenschaufel mit einer Turbinenscheibe oder einem Turbinenring
DE102008057159A1 (de) * 2008-11-13 2010-05-20 Mtu Aero Engines Gmbh Gasturbine
WO2010094273A3 (fr) * 2009-02-21 2011-01-20 Mtu Aero Engines Gmbh Fabrication d'aubes et disque combinés de turbine avec une couche de protection contre l'oxydation ou la corrosion
DE102009036407A1 (de) * 2009-08-06 2011-02-10 Mtu Aero Engines Gmbh Abreibbarer Schaufelspitzenbelag
DE102009037894A1 (de) * 2009-08-18 2011-02-24 Mtu Aero Engines Gmbh Dünnwandiges Strukturbauteil und Verfahren zu seiner Herstellung
GB2474345A (en) * 2009-10-07 2011-04-13 Gen Electric Fabricating and repairing turbine rotors by cold spraying powder
WO2011044876A1 (fr) 2009-10-17 2011-04-21 Mtu Aero Engines Gmbh Procédé de fabrication d'une aube mobile ou de stator et aube de ce type
DE102010022597A1 (de) * 2010-05-31 2011-12-01 Siemens Aktiengesellschaft Verfahren zum Herstellen einer Schicht mittels Kaltgasspritzen und Verwendung einer solchen Schicht
WO2012051978A3 (fr) * 2010-10-13 2012-06-28 Mtu Aero Engines Gmbh Pièce et procédé pour concevoir, réparer et/ou construire une pièce de ce type
EP2617869A2 (fr) * 2012-01-20 2013-07-24 General Electric Company Procédé de fabrication d'un revêtement de barrière thermique et article présentant un revêtement de barrière thermique pulvérisé à froid
US8697184B2 (en) 2009-07-17 2014-04-15 Mtu Aero Engines Gmbh Gas dynamic cold spraying of oxide-containing protective layers
EP2725120A1 (fr) * 2012-10-24 2014-04-30 Hitachi Ltd. Composants à haute température avec des revêtements de barrière thermique pour turbine à gaz
WO2014197789A2 (fr) * 2013-06-07 2014-12-11 General Electric Company Objets métalliques creux et leurs procédés de fabrication
EP2845918A1 (fr) * 2013-09-04 2015-03-11 Siemens Aktiengesellschaft Procédé destiné à revêtir au moins partiellement une aube, dispositif de revêtement et aube
WO2015150071A3 (fr) * 2014-03-31 2015-11-26 Siemens Aktiengesellschaft Procédé de fabrication d'un corps creux par pulvérisation par gaz froid et noyau de formage approprié pour la mise en œuvre dudit procédé
US11662300B2 (en) 2019-09-19 2023-05-30 Westinghouse Electric Company Llc Apparatus for performing in-situ adhesion test of cold spray deposits and method of employing
US11898986B2 (en) 2012-10-10 2024-02-13 Westinghouse Electric Company Llc Systems and methods for steam generator tube analysis for detection of tube degradation
US11935662B2 (en) 2019-07-02 2024-03-19 Westinghouse Electric Company Llc Elongate SiC fuel elements

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WO2002061177A2 (fr) * 2001-01-30 2002-08-08 Siemens Westinghouse Power Corporation Revetement a isolation thermique applique grace a une technique de pulverisation a froid
EP1659195A2 (fr) * 2004-11-23 2006-05-24 United Technologies Corporation Projection gazodynamique à froid de cuivre à haute résistance

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WO2002061177A2 (fr) * 2001-01-30 2002-08-08 Siemens Westinghouse Power Corporation Revetement a isolation thermique applique grace a une technique de pulverisation a froid
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Title
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PATTISON J ET AL: "Cold gas dynamic manufacturing: A non-thermal approach to freeform fabrication", NTERNATIONAL JOURNAL OF MACHINE TOOLS AND MANUFACTURE, vol. 47, no. 3-4, 12 June 2006 (2006-06-12), pages 627 - 634, XP002423531 *
SCHMITT-THOMAS KH G ET AL: "Korrosionsuntersuchungen an Aluminium-Korrosionsschutzüberzügen für Verdichterschaufeln", WERKSTOFFE UND KORROSION, vol. 41, no. 9, September 1990 (1990-09-01), pages 523 - 536, XP002423622 *

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008052030B4 (de) * 2008-10-16 2011-06-16 Mtu Aero Engines Gmbh Verfahren zum Verbinden wenigstens einer Turbinenschaufel mit einer Turbinenscheibe oder einem Turbinenring
DE102008052030A1 (de) * 2008-10-16 2010-04-22 Mtu Aero Engines Gmbh Verfahren zum Verbinden wenigstens einer Turbinenschaufel mit einer Turbinenscheibe oder einem Turbinenring
DE102008057159A1 (de) * 2008-11-13 2010-05-20 Mtu Aero Engines Gmbh Gasturbine
WO2010094273A3 (fr) * 2009-02-21 2011-01-20 Mtu Aero Engines Gmbh Fabrication d'aubes et disque combinés de turbine avec une couche de protection contre l'oxydation ou la corrosion
US8697184B2 (en) 2009-07-17 2014-04-15 Mtu Aero Engines Gmbh Gas dynamic cold spraying of oxide-containing protective layers
DE102009036407A1 (de) * 2009-08-06 2011-02-10 Mtu Aero Engines Gmbh Abreibbarer Schaufelspitzenbelag
US9260784B2 (en) 2009-08-06 2016-02-16 Mtu Aero Engines Gmbh Blade tip coating that can be rubbed off
US9393622B2 (en) 2009-08-18 2016-07-19 Mtu Aero Engines Gmbh Thin-walled structural component, and method for the production thereof
DE102009037894A1 (de) * 2009-08-18 2011-02-24 Mtu Aero Engines Gmbh Dünnwandiges Strukturbauteil und Verfahren zu seiner Herstellung
US8261444B2 (en) 2009-10-07 2012-09-11 General Electric Company Turbine rotor fabrication using cold spraying
US9138838B2 (en) 2009-10-07 2015-09-22 General Electric Company Method of repairing a turbine rotor using cold spraying
GB2474345A (en) * 2009-10-07 2011-04-13 Gen Electric Fabricating and repairing turbine rotors by cold spraying powder
GB2474345B (en) * 2009-10-07 2015-06-03 Gen Electric Turbine rotor fabrication using cold spraying
US9132508B2 (en) * 2009-10-17 2015-09-15 Mtu Aero Engines Gmbh Method for producing a rotor or stator blade and such a blade
US20120201691A1 (en) * 2009-10-17 2012-08-09 Mtu Aero Engines Gmbh Method for producing a rotor or stator blade and such a blade
WO2011044876A1 (fr) 2009-10-17 2011-04-21 Mtu Aero Engines Gmbh Procédé de fabrication d'une aube mobile ou de stator et aube de ce type
DE102009049707A1 (de) 2009-10-17 2011-07-28 MTU Aero Engines GmbH, 80995 Verfahren zur Herstellung einer Lauf- oder Statorschaufel und eine derartige Schaufel
GB2487024B (en) * 2009-10-17 2015-08-12 MTU Aero Engines AG Method for producing a rotor blade or stator blade and such a blade
GB2487024A (en) * 2009-10-17 2012-07-04 Mtu Aero Engines Gmbh Method for producing a rotor or stator blade and such a blade
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