WO2009103268A1 - Method for coating components - Google Patents

Method for coating components Download PDF

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Publication number
WO2009103268A1
WO2009103268A1 PCT/DE2009/000199 DE2009000199W WO2009103268A1 WO 2009103268 A1 WO2009103268 A1 WO 2009103268A1 DE 2009000199 W DE2009000199 W DE 2009000199W WO 2009103268 A1 WO2009103268 A1 WO 2009103268A1
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WO
WIPO (PCT)
Prior art keywords
component
coating
bore
metal
gas turbine
Prior art date
Application number
PCT/DE2009/000199
Other languages
German (de)
French (fr)
Inventor
Andreas Jakimov
Manuel Hertter
Stefan Schneiderbanger
Wolfgang Wachter
Ralf Stolle
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 WO2009103268A1 publication Critical patent/WO2009103268A1/en

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Classifications

    • 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
    • F01D5/288—Protective coatings for blades
    • 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
    • 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
    • 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 for coating a component with at least one opening and / or bore, in particular for coating components of a gas turbine or an aircraft engine.
  • protective layers are provided with protective layers. These are in particular corrosion, oxidation and wear protection layers of metallic and / or ceramic materials. Such protective layers are applied in particular by thermal spraying. For components with openings or holes, such. B. in blades of gas turbines with cooling air holes results in the thermal spraying of protective layers, however, the problem that the openings and / or holes are closed in the manufacture of new parts or after repair by the applied spray process. The subsequent exposure and reworking of the openings and / or holes is possible only with a very high and costly work.
  • An inventive method for coating a component having at least one opening and / or bore in particular for coating components of a gas turbine or an aircraft engine is inventively characterized in that the coating of the component at least in the region of the opening and / or the bore by means of a cold gas spraying process takes place and the component is aligned approximately perpendicular to the beam direction of the applied and the coating forming particles.
  • the use according to the invention of the cold gas spraying method also referred to as kinetic cold gas compacting, permits reliable and cost-effective coating of components with openings and / or bores since the accelerated particles adhere only at an approximately vertical spraying angle and thus openings and / or bores in the component only very little or can not close.
  • the possibility of using sprayed protective layers on components having openings and / or bores can be carried out inexpensively by the method according to the invention, so that there is also an extension of the service life and the operational safety of the corresponding component.
  • the component may be a blade of a rotor of a gas turbine or an aircraft engine with at least one cooling air bore.
  • the method according to the invention can be used advantageously, since the accelerated particles of the material forming the protective layer only very little or do not adhere to the generally oblique cooling-air bores. A closure of these cooling air bores by the mentioned particles is thus almost impossible to exclude.
  • a further advantage of the method according to the invention lies in the use of small beam cross sections, by means of which an extremely exact coating of the corresponding components is made possible.
  • an erosion and / or corrosion and / or oxidation and / or wear protection layer or a thermal barrier coating is formed by the coating.
  • the pulverulent particles to be applied at high speed and forming the protective layer may be composed of a metal, a metal alloy, a metal mixture, a metal-ceramic mixture and / or a mixture of a metal alloy with ceramic.
  • consist mik. So z. B. consist of the titanium nitride particles for the formation of an erosion control layer.
  • the temperature of the particles during cold gas spraying is between room temperature and 800 ° C.
  • the powdery particles are applied to the component or component surface in a solid or doughy state and adhere to it.
  • the surface material to be coated or the material of the component may consist of metal or a metal alloy, in particular one of an iron, cobalt, nickel or titanium-based alloy.
  • Typical speeds of the particles during cold gas spraying are about 500 to 1,500 m / s.
  • the erf ⁇ ndungswele method has the advantage that the cold gas injection method has a high spray efficiency with little splash loss, so that a coverage of non-coated areas of the component is almost not required.
  • An inventive use of the method described above results in the production or repair of engine components with at least one opening and / or bore, in particular for the manufacture, repair and coating of blades with cooling air holes of integral rotor construction (BLISK o- BLING).
  • a component according to the invention of a gas turbine or an aircraft engine is produced according to a method described above.
  • the component may be a blade with at least one cooling air bore of a rotor of a gas turbine, wherein the blade may be formed as part of an integral rotor construction (BLISK or BLING).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present invention relates to a method for coating a component having at least one opening and/or bore, particularly for coating components of a gas turbine or an aircraft engine, wherein the coating of the component is carried out at least in the region of the opening and/or the bore using a cold gas spraying method and the component is oriented approximately perpendicular to the jet direction of the particles to be applied and forming the coating.

Description

Verfahren zur Beschichtung von Bauteilen Method for coating components
Beschreibungdescription
Die vorliegende Erfindung betrifft ein Verfahren zur Beschichtung eines Bauteils mit mindestens einer Öffnung und/oder Bohrung, insbesondere zur Beschichtung von Bauteilen einer Gasturbine oder eines Flugtriebwerkes.The present invention relates to a method for coating a component with at least one opening and / or bore, in particular for coating components of a gas turbine or an aircraft engine.
Zur Verlängerung der Lebensdauer und insbesondere zur Betriebssicherheit werden Bautei- Ie von Gasturbinen oder Flugtriebwerken mit Schutzschichten versehen. Dabei handelt es sich insbesondere um Korrosions-, Oxidations- und Verschleißschutzschichten aus metallischen und/oder keramischen Werkstoffen. Derartige Schutzschichten werden insbesondere durch thermische Spritzverfahren aufgetragen. Bei Bauteilen mit Öffnungen oder Bohrungen, wie z. B. bei Schaufeln von Gasturbinen mit Kühlluftbohrungen ergibt sich bei dem thermischen Spritzen von Schutzschichten jedoch das Problem, dass die Öffnungen und/oder Bohrungen bei der Neuteilfertigung oder nach einer Reparatur durch das angewandte Spritzverfahren verschlossen werden. Die anschließende Freilegung und Nachbearbeitung der Öffnungen und/oder Bohrungen ist nur mit einem sehr hohen und kostenintensiven Arbeitsaufwand möglich.To extend the service life and in particular for operational safety, components of gas turbines or aircraft engines are provided with protective layers. These are in particular corrosion, oxidation and wear protection layers of metallic and / or ceramic materials. Such protective layers are applied in particular by thermal spraying. For components with openings or holes, such. B. in blades of gas turbines with cooling air holes results in the thermal spraying of protective layers, however, the problem that the openings and / or holes are closed in the manufacture of new parts or after repair by the applied spray process. The subsequent exposure and reworking of the openings and / or holes is possible only with a very high and costly work.
Es ist daher Aufgabe der vorliegenden Erfindung ein gattungsgemäßes Verfahren zur Beschichtung eines Bauteils mit mindestens einer Öffnung und/oder Bohrung, insbesondere zur Beschichtung von Bauteilen einer Gasturbine oder eines Flugtriebwerkes bereitzustellen, welches eine sichere und kostengünstige Beschichtung des Bauteils ermöglicht.It is therefore an object of the present invention to provide a generic method for coating a component with at least one opening and / or bore, in particular for coating components of a gas turbine or an aircraft engine, which enables a safe and cost-effective coating of the component.
Gelöst wird diese Aufgabe durch ein Verfahren gemäß den Merkmalen des Anspruchs 1.This object is achieved by a method according to the features of claim 1.
Vorteilhafte Ausgestaltungen der Erfindung sind in den jeweiligen Unteransprüchen beschrieben. Ein erfindungsgemäßes Verfahren zur Beschichtung eines Bauteils mit mindestens einer Öffnung und/oder Bohrung, insbesondere zur Beschichtung von Bauteilen einer Gasturbine oder eines Flugtriebwerks zeichnet sich erfindungsgemäß dadurch aus, dass die Beschichtung des Bauteils zumindest im Bereich der Öffnung und/oder der Bohrung mittels eines Kaltgasspritzverfahrens erfolgt und das Bauteil ungefähr senkrecht zur Strahlrichtung der aufzubringenden und die Beschichtung ausbildenden Partikel ausgerichtet ist. Durch die erfindungsgemäße Anwendung des Kaltgasspritzverfahrens, auch als Kinetisches-Kaltgas- Kompaktieren bezeichnet, ist eine sichere und kostengünstige Beschichtung von Bauteilen mit Öffnungen und/oder Bohrungen möglich, da die beschleunigten Partikel nur bei einem ungefähr senkrechten Spritzwinkel haften und somit Öffnungen und/oder Bohrungen in dem Bauteil nur sehr wenig oder nicht verschließen können. Vorteilhafterweise ist durch das erfindungsgemäße Verfahren die Möglichkeit der Verwendung gespritzter Schutzschichten auf Bauteilen mit Öffnungen und/oder Bohrungen kostengünstig durchführbar, so dass es auch zu einer Verlängerung der Lebensdauer und der Betriebssicherheit des ent- sprechenden Bauteils kommt. Dabei kann das Bauteil eine Schaufel eines Rotors einer Gasturbine oder eines Flugtriebwerks mit mindestens einer Kühlluftbohrung sein. Insbesondere bei Schaufeln mit Kühlluftbohrungen ist das erfindungsgemäße Verfahren vorteilhaft einsetzbar, da die beschleunigten Partikel des die Schutzschicht ausbildenden Werkstoffs auf den in der Regel schrägen Kühlluftbohrungen nur sehr wenig oder nicht anhaften. Ein Ver- Schluss dieser Kühlluftbohrungen durch die genannten Partikel ist somit nahezu ausschließbar. Ein weiterer Vorteil des erfindungsgemäßen Verfahrens liegt in der Verwendung von kleinen Strahlquerschnitten, durch die eine äußerst exakte Beschichtung der entsprechenden Bauteile ermöglicht wird.Advantageous embodiments of the invention are described in the respective subclaims. An inventive method for coating a component having at least one opening and / or bore, in particular for coating components of a gas turbine or an aircraft engine is inventively characterized in that the coating of the component at least in the region of the opening and / or the bore by means of a cold gas spraying process takes place and the component is aligned approximately perpendicular to the beam direction of the applied and the coating forming particles. The use according to the invention of the cold gas spraying method, also referred to as kinetic cold gas compacting, permits reliable and cost-effective coating of components with openings and / or bores since the accelerated particles adhere only at an approximately vertical spraying angle and thus openings and / or bores in the component only very little or can not close. Advantageously, the possibility of using sprayed protective layers on components having openings and / or bores can be carried out inexpensively by the method according to the invention, so that there is also an extension of the service life and the operational safety of the corresponding component. In this case, the component may be a blade of a rotor of a gas turbine or an aircraft engine with at least one cooling air bore. Particularly in the case of blades with cooling-air bores, the method according to the invention can be used advantageously, since the accelerated particles of the material forming the protective layer only very little or do not adhere to the generally oblique cooling-air bores. A closure of these cooling air bores by the mentioned particles is thus almost impossible to exclude. A further advantage of the method according to the invention lies in the use of small beam cross sections, by means of which an extremely exact coating of the corresponding components is made possible.
In weiteren vorteilhaften Ausgestaltungen des erfindungsgemäßen Verfahrens wird durch die Beschichtung eine Erosions- und/oder Korrosions- und/oder Oxidations- und/oder Verschleißschutzschicht oder eine Wärmedämmschicht ausgebildet. Hierfür können die mit hoher Geschwindigkeit aufzubringenden und die Schutzschicht bildenden pulverförmigen Partikel aus einem Metall, einer Metall-Legierung, aus einem Metallgemisch, aus einem Metall-Keramik-Gemisch und/oder aus einem Gemisch einer Metall-Legierung mit Kera- mik bestehen. So können z. B. für die Ausbildung einer Erosionsschutzschicht die Partikel aus Titannitrid bestehen.In further advantageous embodiments of the method according to the invention, an erosion and / or corrosion and / or oxidation and / or wear protection layer or a thermal barrier coating is formed by the coating. For this purpose, the pulverulent particles to be applied at high speed and forming the protective layer may be composed of a metal, a metal alloy, a metal mixture, a metal-ceramic mixture and / or a mixture of a metal alloy with ceramic. consist mik. So z. B. consist of the titanium nitride particles for the formation of an erosion control layer.
In einer weiteren vorteilhaften Ausgestaltung des erfindungsgemäßen Verfahrens beträgt die Temperatur der Partikel beim Kaltgasspritzen zwischen Raumtemperatur und 800° C. Vorteilhafterweise ergibt sich im Gegensatz zu anderen Verfahren des thermischen Sprit- zens kein Aufschmelzen er Partikel. Durch den kaltkinetischen Kompaktierungsprozess werden die pulverförmigen Partikel in festem oder teigigem Zustand auf das Bauteil bzw. die Bauteiloberfläche aufgetragen und haften daran. Dabei kann der zu beschichtende O- berflächenwerkstoff oder Werkstoff des Bauteils aus Metall oder einer Metall-Legierung, insbesondere einer aus einer Eisen-, Kobalt-, Nickel- oder Titanbasislegierung bestehen. Übliche Geschwindigkeiten der Partikel beim Kaltgasspritzen betragen ca. 500 bis 1.500 m/s. Zudem weist das erfϊndungsgemäße Verfahren den Vorteil auf, dass das Kaltgas- spritzverfahren einen hohen Spritzwirkungsgrad mit wenig Spritzverlust aufweist, so dass eine Abdeckung von nicht zu beschichtenden Bereichen des Bauteils nahezu nicht erforderlich ist.In a further advantageous embodiment of the method according to the invention, the temperature of the particles during cold gas spraying is between room temperature and 800 ° C. Advantageously, in contrast to other methods of thermal spraying, there is no melting of the particles. Due to the cold-kinetic compaction process, the powdery particles are applied to the component or component surface in a solid or doughy state and adhere to it. In this case, the surface material to be coated or the material of the component may consist of metal or a metal alloy, in particular one of an iron, cobalt, nickel or titanium-based alloy. Typical speeds of the particles during cold gas spraying are about 500 to 1,500 m / s. In addition, the erfϊndungsgemäße method has the advantage that the cold gas injection method has a high spray efficiency with little splash loss, so that a coverage of non-coated areas of the component is almost not required.
Eine erfindungsgemäße Verwendung eines der im vorhergehenden beschriebenen Verfahren ergibt sich bei der Herstellung oder Reparatur von Triebwerksbauteilen mit mindestens einer Öffnung und/oder Bohrung, insbesondere zur Herstellung, Reparatur und Beschich- tung von Schaufeln mit Kühlluftbohrungen von integralen Rotor-Konstruktion (BLISK o- der BLING).An inventive use of the method described above results in the production or repair of engine components with at least one opening and / or bore, in particular for the manufacture, repair and coating of blades with cooling air holes of integral rotor construction (BLISK o- BLING).
Ein erfindungsgemäßes Bauteil einer Gasturbine oder eines Flugtriebwerks wird nach ei- nem im vorstehenden beschriebenen Verfahren hergestellt. Dabei kann das Bauteil eine Schaufel mit mindestens einer Kühlluftbohrung eines Rotors einer Gasturbine sein, wobei die Schaufel als Bestandteil einer integralen Rotor-Konstruktion (BLISK oder BLING) ausgebildet sein kann. A component according to the invention of a gas turbine or an aircraft engine is produced according to a method described above. In this case, the component may be a blade with at least one cooling air bore of a rotor of a gas turbine, wherein the blade may be formed as part of an integral rotor construction (BLISK or BLING).

Claims

Patentansprüche claims
1. Verfahren zur Beschichtung eines Bauteils mit mindestens einer Öffnung und/oder Bohrung, insbesondere zur Beschichtung von Bauteilen einer Gasturbine oder eines Flugtrieb- 5 werkes, dadurch gekennzeichnet, dass die Beschichtung des Bauteils zumindest im Bereich der Öffnung und/oder der Bohrung mittels eines Kaltgasspritzverfahrens erfolgt und das Bauteil ungefähr senkrecht zur Strahlrichtung der aufzubringenden und die Beschichtung ausbildenden Partikel ausgerichtet ist. 01. A method for coating a component with at least one opening and / or bore, in particular for the coating of components of a gas turbine or a Aircraft 5 plant, characterized in that the coating of the component at least in the region of the opening and / or the bore by means of a Cold gas spraying is carried out and the component is aligned approximately perpendicular to the beam direction of the applied and the coating forming particles. 0
2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass das Bauteil eine Schaufel eines Rotors einer Gasturbine oder eines Flugtriebwerks mit mindestens einer Kühlluftbohrung ist.2. The method according to claim 1, characterized in that the component is a blade of a rotor of a gas turbine or an aircraft engine with at least one cooling air bore.
3. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass durch die Beschich-5 tung eine Erosions- und/oder Korrosions- und/oder Oxidations- und/oder Verschleißschutzschicht oder eine Wärmedämmschicht ausgebildet wird.3. The method according to claim 1 or 2, characterized in that an erosion and / or corrosion and / or oxidation and / or wear protection layer or a thermal barrier coating is formed by the Beschich-5 device.
4. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der zu beschichtende Oberflächenwerkstoff oder Werkstoff des Bauteils aus Metall oder einer0 Metall-Legierung, insbesondere einer aus einer Eisen-, Kobalt-, Nickel- oder Titanbasislegierung besteht.4. The method according to any one of the preceding claims, characterized in that the surface material to be coated or material of the component consists of metal or a metal alloy, in particular one of an iron, cobalt, nickel or titanium-based alloy.
5. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die aufzubringenden Partikel pulverförmig sind und aus einem Metall, einer Metall-Legierung,5 aus einem Metallgemisch, aus Keramik, aus einem Metall-Keramik-Gemisch und/oder aus einem Gemisch einer Metall-Legierung mit Keramik bestehen.5. The method according to any one of the preceding claims, characterized in that the particles to be applied are powdery and made of a metal, a metal alloy, 5 of a metal mixture, of ceramic, of a metal-ceramic mixture and / or of a mixture of a Metal alloy with ceramic.
6. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Temperatur der Partikel beim Kaltgasspritzen zwischen Raumtemperatur und 800°C be- o trägt bei einer Geschwindigkeit zwischen 500 bis 1500 m/s und einem Druck von 30 bis 40 bar. 6. The method according to any one of the preceding claims, characterized in that the temperature of the particles in the cold gas spraying between room temperature and 800 ° C oe carries at a speed between 500 to 1500 m / s and a pressure of 30 to 40 bar.
7. Verwendung eines Verfahrens nach einem der vorhergehenden Ansprüche zur Herstel- hang oder Reparatur von Triebwerksbauteilen mit mindestens einer Öffnung und/oder Bohrung, insbesondere zur Herstellung, Reparatur und Beschichtung von Schaufeln mit Kühl- luftbohrungen von integralen Rotor-Konstruktionen (BLISK oder BLING).7. Use of a method according to one of the preceding claims for the manufacture or repair of engine components with at least one opening and / or bore, in particular for the manufacture, repair and coating of blades with cooling air bores of integral rotor constructions (BLISK or BLING) ,
8. Bauteil einer Gasturbine oder eines Flugtriebwerkes, dadurch gekennzeichnet, dass das Bauteil nach einem Verfahren gemäß einem der Ansprüche 1 bis 6 hergestellt ist.8. component of a gas turbine or an aircraft engine, characterized in that the component is produced by a method according to one of claims 1 to 6.
9. Bauteil nach Anspruch 8, dadurch gekennzeichnet, dass das Bauteil eine Schaufel mit mindestens einer Kühlluftbohrung eines Rotors einer Gasturbine ist.9. Component according to claim 8, characterized in that the component is a blade with at least one cooling air bore of a rotor of a gas turbine.
10. Bauteil nach Anspruch 9, dadurch gekennzeichnet, dass die Schaufel Bestandteil einer integralen Rotor-Konstruktion (BLISK oder BLING) ist. 10. Component according to claim 9, characterized in that the blade is part of an integral rotor construction (BLISK or BLING).
PCT/DE2009/000199 2008-02-20 2009-02-13 Method for coating components WO2009103268A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008010623.2 2008-02-20
DE102008010623A DE102008010623A1 (en) 2008-02-20 2008-02-20 Method for coating components

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WO2009103268A1 true WO2009103268A1 (en) 2009-08-27

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014003424A1 (en) * 2014-03-04 2015-09-10 VDM Metals GmbH Cathode for the electrolytic zinc extraction

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010005389A1 (en) * 2010-01-22 2011-07-28 MTU Aero Engines GmbH, 80995 Structured surface coating by means of kinetic cold gas spraying

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1398394A1 (en) * 2002-08-13 2004-03-17 Howmet Research Corporation Cold spraying method for MCrAIX coating
EP1705266A2 (en) * 2005-03-23 2006-09-27 United Technologies Corporation Applying bond coat to engine components using cold spray
WO2007093609A1 (en) * 2006-02-16 2007-08-23 Siemens Aktiengesellschaft Component with a layer comprising nanoscalar structural elements and method for producing this layer

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1398394A1 (en) * 2002-08-13 2004-03-17 Howmet Research Corporation Cold spraying method for MCrAIX coating
EP1705266A2 (en) * 2005-03-23 2006-09-27 United Technologies Corporation Applying bond coat to engine components using cold spray
WO2007093609A1 (en) * 2006-02-16 2007-08-23 Siemens Aktiengesellschaft Component with a layer comprising nanoscalar structural elements and method for producing this layer

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014003424A1 (en) * 2014-03-04 2015-09-10 VDM Metals GmbH Cathode for the electrolytic zinc extraction
DE102014003424B4 (en) * 2014-03-04 2017-04-13 Vdm Metals International Gmbh Cathode for the electrolytic zinc extraction

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