WO2009065385A1 - Method for repairing a gas turbine component - Google Patents

Method for repairing a gas turbine component Download PDF

Info

Publication number
WO2009065385A1
WO2009065385A1 PCT/DE2008/001893 DE2008001893W WO2009065385A1 WO 2009065385 A1 WO2009065385 A1 WO 2009065385A1 DE 2008001893 W DE2008001893 W DE 2008001893W WO 2009065385 A1 WO2009065385 A1 WO 2009065385A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine component
gas turbine
gas
repaired
renewed
Prior art date
Application number
PCT/DE2008/001893
Other languages
German (de)
French (fr)
Inventor
Hans Banhirl
Wolfgang Eichmann
Dieter Schmidt
Martin Fischer
Stefan Schneiderbanger
Ralf Stolle
Wolfgang Werner
Hans Bernhard Winkler
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 WO2009065385A1 publication Critical patent/WO2009065385A1/en

Links

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
    • 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
    • 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

Definitions

  • the invention relates to a method for repairing a gas turbine component, in particular a sealing device, according to the preamble of claim 1.
  • sealing fins formed sealing means in particular the sealing of a gap between the stator side assemblies and rotor-side assemblies of the turbomachine.
  • sealing devices are subject to wear, so they must be repaired after damage.
  • the procedure is such that at least one damaged section is removed from a sealing device to be repaired, the same being renewed by welding on a metallic material.
  • the geometry provided by welding is adapted by grinding a new part geometry after welding of the metallic material, wherein subsequently a forming after grinding tip of the sealing device is coated by thermal spraying with a ceramic material, so as the tip of the To arm sealing device.
  • the present invention is based on the problem to provide a novel method for repair of a gas turbine component, in particular a sealing device. This problem is solved by a method according to claim 1.
  • the damaged and removed section is renewed by kinetic cold gas spraying.
  • the renewal of a damaged, severed section of a gas turbine component is carried out by kinetic cold gas spraying.
  • the renewed section can be applied with minimal porosity and maximum adhesion.
  • several millimeters thick layers can be applied.
  • the formation of cracks, which usually form during welding operations, is avoided.
  • At least the renewed portion is subjected to a heat treatment.
  • the invention relates to a method for repairing a gas turbine component, in particular a sealing device, such as e.g. a sealing fin.
  • a sealing device such as e.g. a sealing fin.
  • the renewal of the damaged and removed portion is carried out by kinetic cold gas spraying.
  • particles are contained in a carrier gas, with the aid of which the damaged and removed section is to be renewed.
  • the particle size of the particles contained in the carrier gas is between 10 and 70 microns.
  • the particles contained in the carrier gas are at a speed between 300 and 900 m / s directed to the gas turbine component to be repaired.
  • the gas temperature of the carrier gas in the kinetic cold gas spraying is between 600 and 900 ° C.
  • layer thicknesses of up to 10 mm can be applied to the gas turbine component to be repaired.
  • the particles contained in the carrier gas are preferably particles whose material is identical to the material of the gas turbine component to be repaired.
  • the particles contained in the carrier gas preferably also consist of a nickel-based alloy.
  • the renewed portion of the gas turbine component is subjected to a heat treatment. This allows the renewed section to be ductilised. Also, the entire repaired component may be subjected to a heat treatment following the replacement of the damaged portion.
  • the renewed section of the gas turbine component is machined to final gauge. This is preferably done mechanically by e.g. Rotate.
  • the kinetic cold gas spraying is carried out using a spray gun to direct the carrier gas together with the particles contained in the carrier gas on the gas turbine component to be repaired.
  • a pressure between 30 and 40 bar is preferably set in the spray gun.

Abstract

The invention relates to a method for repairing a gas turbine component, especially a sealing structure such as a sealing fin, wherein at least one damaged section of a gas turbine component to be repaired is removed and is then replaced. The invention is characterized in that the damaged section that has been removed is replaced by kinetic cold spray.

Description

Verfahren zur Reparatur eines Gasturbinenbauteils Method for repairing a gas turbine component
Die Erfindung betrifft ein Verfahren zur Reparatur eines Gasturbinenbauteils, insbesondere einer Dichteinrichtung, nach dem Oberbegriff des Anspruchs 1.The invention relates to a method for repairing a gas turbine component, in particular a sealing device, according to the preamble of claim 1.
In Turbomaschinen, wie z.B. in Gasturbinen, dienen als Dichtfins ausgebildete Dichteinrichtungen insbesondere der Abdichtung eines Spalts zwischen statorseitigen Baugruppen und rotorseitigen Baugruppen der Turbomaschine. Im Betrieb unterliegen Dichteinrichtungen einem Verschleiß, so dass dieselben nach Beschädigung repariert werden müssen.In turbomachinery, such as in gas turbines serve as sealing fins formed sealing means, in particular the sealing of a gap between the stator side assemblies and rotor-side assemblies of the turbomachine. In operation, sealing devices are subject to wear, so they must be repaired after damage.
Nach der Praxis wird bei der Reparatur von als Dichtfins ausgebildeten Dichteinrichtungen so vorgegangen, dass von einer zu reparierenden Dichteinrichtung mindestens ein beschädigter Abschnitt entfernt wird, wobei derselbe durch Aufschweißen eines metallischen Werkstoffs erneuert wird. Bei aus der Praxis bekannten Reparaturverfahren wird nach dem Aufschweißen des metallischen Werkstoffs die durch Aufschweißen bereitgestellte Geometrie durch Schleifen einer Neuteilgeometrie angepasst, wobei anschließend eine sich nach dem Schleifen ausbildende Spitze der Dichteinrichtung durch thermisches Spritzen mit einem keramischen Werkstoff beschichtet wird, um so die Spitze der Dichteinrichtung zu panzern.In practice, when repairing sealing devices designed as sealing fins, the procedure is such that at least one damaged section is removed from a sealing device to be repaired, the same being renewed by welding on a metallic material. In repair processes known from practice, the geometry provided by welding is adapted by grinding a new part geometry after welding of the metallic material, wherein subsequently a forming after grinding tip of the sealing device is coated by thermal spraying with a ceramic material, so as the tip of the To arm sealing device.
Die Reparatur von z.B. Dichtfins durch Aufschweißen eines metallischen Werkstoffs durch z.B. Laserpulverauftragsschweißen erlaubt zwar prinzipiell die Reparatur von Dichtfins, häufig handelt es sich jedoch bei den aufzuschweißenden Teilen um solche aus, nach aktuellem Stand der Technik, nicht oder nur bedingt schmelzschweißbaren Werkstoffen, deren Reparaturschweißung zu unzulässigen Schweißfehlern wie Rissen führt. Es besteht daher ein Bedarf an einem Verfahren zur Reparatur eines Gasturbinenbauteils, mit welchem die obigen Nachteile vermieden werden können.The repair of e.g. Sealing fins by welding a metallic material through e.g. Although laser powder build-up welding basically permits the repair of sealing fins, the parts to be welded are frequently made of state-of-the-art materials that are not or only partially melt weldable, repair welding of which leads to inadmissible welding defects such as cracks. There is therefore a need for a method of repairing a gas turbine component with which the above disadvantages can be avoided.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Reparatur eines Gasturbinenbauteils, insbesondere einer Dichteinrichtung, zu schaffen. Dieses Problem wird durch ein Verfahren gemäß Anspruch 1 gelöst.On this basis, the present invention is based on the problem to provide a novel method for repair of a gas turbine component, in particular a sealing device. This problem is solved by a method according to claim 1.
Erfindungsgemäß wird der beschädigte und entfernte Abschnitt durch kinetisches Kaltgasspritzen erneuert.According to the invention, the damaged and removed section is renewed by kinetic cold gas spraying.
Erfindungsgemäß erfolgt die Erneuerung eines beschädigten, abgetrennten Abschnitts von einem Gasturbinenbauteil durch kinetisches Kaltgasspritzen. Der erneuerte Abschnitt kann mit minimaler Porosität und maximaler Haftfestigkeit aufgetragen werden. Weiterhin können mit Hilfe des kinetischen Kaltgasspritzens mehrere Millimeter dicke Schichten aufgetragen werden. Weiterhin wird die Ausbildung von Rissen, die sich üblicherweise bei Schweißvorgängen ausbilden, vermieden.According to the invention, the renewal of a damaged, severed section of a gas turbine component is carried out by kinetic cold gas spraying. The renewed section can be applied with minimal porosity and maximum adhesion. Furthermore, with the help of kinetic cold gas spraying several millimeters thick layers can be applied. Furthermore, the formation of cracks, which usually form during welding operations, is avoided.
Vorzugsweise wird nach dem Erneuern des beschädigten Abschnitts zumindest der erneuerte Abschnitt einer Wärmebehandlung unterzogen.Preferably, after renewing the damaged portion, at least the renewed portion is subjected to a heat treatment.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, nachfolgend näher erläutert.Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be explained in more detail below, without being limited thereto.
Die Erfindung betrifft ein Verfahren zur Reparatur eines Gasturbinenbauteils, insbesondere einer Dichteinrichtung wie z.B. eines Dichtfins. Zur Reparatur eines solchen Gasturbinenbauteils wird zuerst von einem zu reparierenden Gasturbinenbauteil mindestens ein beschädigter Abschnitt entfernt, wobei der entfernte Abschnitt erneuert wird. Im Sinne der hier vorliegenden Erfindung erfolgt das Erneuern des beschädigten und entfernten Abschnitts durch kinetisches Kaltgasspritzen.The invention relates to a method for repairing a gas turbine component, in particular a sealing device, such as e.g. a sealing fin. To repair such a gas turbine component, at least one damaged portion is first removed from a gas turbine component to be repaired, with the removed portion being renewed. For the purposes of the present invention, the renewal of the damaged and removed portion is carried out by kinetic cold gas spraying.
Beim kinetischen Kaltgasspritzen sind in einem Trägergas Partikel enthalten, mit Hilfe derer der beschädigte und entfernte Abschnitt erneuert werden soll. Beim erfindungsgemäßen Verfahren beträgt die Partikelgröße der im Trägergas enthaltenen Partikel zwischen 10 und 70 μm. Die im Trägergas enthaltenen Partikel werden mit einer Geschwindigkeit zwischen 300 und 900 m/s auf das zu reparierende Gasturbinenbauteil gerichtet. Die Gastemperatur des Trägergases beim kinetischen Kaltgasspritzen liegt zwischen 600 und 900 °C.In kinetic cold gas spraying, particles are contained in a carrier gas, with the aid of which the damaged and removed section is to be renewed. In the method according to the invention, the particle size of the particles contained in the carrier gas is between 10 and 70 microns. The particles contained in the carrier gas are at a speed between 300 and 900 m / s directed to the gas turbine component to be repaired. The gas temperature of the carrier gas in the kinetic cold gas spraying is between 600 and 900 ° C.
Mit dem kinetischen Kaltgasspritzen können Schichtdicken von bis zu 10 mm auf das zu reparierende Gasturbinenbauteil aufgetragen werden.With kinetic cold gas spraying, layer thicknesses of up to 10 mm can be applied to the gas turbine component to be repaired.
Bei den im Trägergas enthaltenen Partikeln handelt es sich vorzugsweise um Partikel, deren Werkstoff artgleich zum Werkstoff des zu reparierenden Gasturbinenbauteils ist.The particles contained in the carrier gas are preferably particles whose material is identical to the material of the gas turbine component to be repaired.
Dann, wenn das zu reparierende Gasturbinenbauteil z.B. aus einer Nickelbasislegierung gefertigt ist, bestehen die im Trägergas enthaltenen Partikel vorzugsweise auch aus einer Nickelbasislegierung.Then, when the gas turbine component to be repaired e.g. is made of a nickel-based alloy, the particles contained in the carrier gas preferably also consist of a nickel-based alloy.
Im Anschluss an das Erneuern des beschädigten Abschnitts durch kinetisches Kartgasspritzen wird zumindest der erneuerte Abschnitt des Gasturbinenbauteils einer Wärmebehandlung unterzogen. Hierdurch kann der erneuerte Abschnitt duktilisiert werden. Es kann auch das gesamte reparierte Bauteil im Anschluss an das Erneuern des beschädigten Abschnitts einer Wärmebehandlung unterzogen werden.Following renewal of the damaged portion by kinetic kart gas injection, at least the renewed portion of the gas turbine component is subjected to a heat treatment. This allows the renewed section to be ductilised. Also, the entire repaired component may be subjected to a heat treatment following the replacement of the damaged portion.
Im Anschluss an die Wärmebehandlung wird der erneuerte Abschnitt des Gasturbinenbauteils auf Endmaß bearbeitet. Dies erfolgt vorzugsweise mechanisch durch z.B. Drehen.Following the heat treatment, the renewed section of the gas turbine component is machined to final gauge. This is preferably done mechanically by e.g. Rotate.
Das kinetische Kaltgasspritzen erfolgt unter Verwendung einer Spritzpistole, um das Trägergas zusammen mit den im Trägergas enthaltenen Partikeln auf das zu reparierende Gasturbinenbauteil zu richten. Dabei wird in der Spritzpistole vorzugsweise ein Druck zwischen 30 und 40 bar eingestellt. The kinetic cold gas spraying is carried out using a spray gun to direct the carrier gas together with the particles contained in the carrier gas on the gas turbine component to be repaired. In this case, a pressure between 30 and 40 bar is preferably set in the spray gun.

Claims

Patentansprüche claims
1. Verfahren zur Reparatur eines Gasturbinenbauteils, insbesondere einer Dichteinrichtung wie eines Dichtfins, wobei von einem zu reparierenden Gasturbinenbauteil mindestens ein beschädigter Abschnitt entfernt und derselbe erneuert wird, dadurch gekennzeichnet, dass der beschädigte und entfernte Abschnitt durch kinetisches Kaltgasspritzen erneuert wird.A method of repairing a gas turbine component, in particular a sealing device such as a sealing fin, wherein at least one damaged section is removed and replaced by a gas turbine component to be repaired, characterized in that the damaged and removed section is renewed by kinetic cold gas spraying.
2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass nach dem Erneuern des beschädigten Abschnitts zumindest der erneuerte Abschnitt einer Wärmebehandlung unterzogen wird.2. The method according to claim 1, characterized in that after renewing the damaged portion, at least the renewed portion is subjected to a heat treatment.
3. Verfahren nach Anspruch 2, dadurch gekennzeichnet, dass nach der Wärmebehandlung des erneuerten Abschnitts derselbe auf Endmaß bearbeitet wird.3. The method according to claim 2, characterized in that after the heat treatment of the renewed section of the same is machined to final gauge.
4. Verfahren nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass eine Gastemperatur eines Trägergases beim kinetischen Kaltgasspritzen zwischen 600 und 900 0C liegt.4. The method according to any one of claims 1 to 3, characterized in that a gas temperature of a carrier gas in the kinetic cold gas spraying between 600 and 900 0 C.
5. Verfahren nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass beim kinetischen Kaltgasspritzen in einem Trägergas Partikel mit einer Partikelgröße zwischen 10 und 70 μm enthalten sind.5. The method according to any one of claims 1 to 4, characterized in that the kinetic cold gas spraying in a carrier gas particles are contained with a particle size between 10 and 70 microns.
6. Verfahren nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass beim kinetischen Kaltgasspritzen in einem Trägergas Partikel enthalten sind, die mit einer Geschwindigkeit zwischen 300 und 900 m/s auf das zu reparierenden Gasturbinenbauteil gerichtet werden.6. The method according to any one of claims 1 to 5, characterized that in the kinetic cold gas spraying in a carrier gas particles are contained, which are directed at a speed between 300 and 900 m / s on the repaired gas turbine component.
7. Verfahren nach Anspruch 5 oder 6, dadurch gekennzeichnet, dass im Trägergas Partikel enthalten sind, deren Werkstoff artgleich zum Werkstoff des zu reparierenden Gasturbinenbauteils ist. 7. The method according to claim 5 or 6, characterized in that particles are contained in the carrier gas, the material of the same type is the material of the gas turbine component to be repaired.
PCT/DE2008/001893 2007-11-23 2008-11-18 Method for repairing a gas turbine component WO2009065385A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200710056451 DE102007056451A1 (en) 2007-11-23 2007-11-23 Method for repairing a gas turbine component
DE102007056451.3 2007-11-23

Publications (1)

Publication Number Publication Date
WO2009065385A1 true WO2009065385A1 (en) 2009-05-28

Family

ID=40445649

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2008/001893 WO2009065385A1 (en) 2007-11-23 2008-11-18 Method for repairing a gas turbine component

Country Status (2)

Country Link
DE (1) DE102007056451A1 (en)
WO (1) WO2009065385A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010054643A1 (en) * 2008-11-13 2010-05-20 Mtu Aero Engines Gmbh Method for repairing the component of a gas turbine
FR2978076A1 (en) * 2011-07-22 2013-01-25 Snecma Method for assembling metal shell utilized for making high pressure compressor casings, involves depositing powder of alloy by cold projection at supersonic speed on face such that shell is formed on another shell
EP2778256A1 (en) * 2013-03-15 2014-09-17 Bell Helicopter Textron Inc. Methods utilizing cold spray techniques for repairing and protecting rotary components of aviation propulsion systems
CN112323057A (en) * 2019-07-20 2021-02-05 通用电气公司 Cold spray repair of engine parts

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009036407A1 (en) * 2009-08-06 2011-02-10 Mtu Aero Engines Gmbh Abradable blade tip pad
DE102010048336A1 (en) * 2010-10-13 2012-04-19 Mtu Aero Engines Gmbh Component and method for forming, repairing and / or constructing such a component
EP2503026A1 (en) * 2011-03-21 2012-09-26 MTU Aero Engines GmbH Method for repairing a layer on a substrate
CN102303205B (en) * 2011-09-05 2013-06-26 广州市天河区金棠表面工程技术有限公司 Split deformation or deflation field spraying repair process for steam turbine cylinder
US20130082446A1 (en) * 2011-09-30 2013-04-04 General Electric Company Method of repairing rotating machine components
DE102018218507A1 (en) * 2018-10-29 2020-04-30 Aktiebolaget Skf Metallic rolling or plain bearing component
EP4116012A1 (en) * 2021-07-07 2023-01-11 Industria de Turbo Propulsores S.A. Material deposition method for repairing aeronautical components

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005093128A1 (en) * 2004-03-22 2005-10-06 Honeywell International, Inc. Cold gas-dynamic spray repair on gas turbine engine components
EP1666635A1 (en) * 2004-12-03 2006-06-07 United Technologies Corporation Superalloy repair using cold spray
EP1672175A1 (en) * 2004-12-14 2006-06-21 Honeywell International Inc. A method for applying environmental-resistant mcraly coatings on gas turbine components
EP1674595A2 (en) * 2004-12-21 2006-06-28 United Technologies Corporation Structural repair using cold sprayed aluminum material
EP1674594A1 (en) * 2004-12-22 2006-06-28 United Technologies Corporation Blade platform restoration using cold spray
US20060166020A1 (en) * 2005-01-26 2006-07-27 Honeywell International, Inc. High strength amorphous and microcrystaline structures and coatings
WO2007027177A1 (en) * 2004-08-30 2007-03-08 Honeywell International Inc. Method for repairing titanium alloy components
EP1897972A1 (en) * 2006-09-11 2008-03-12 United Technologies Corporation Method for processing titanium alloy components

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005093128A1 (en) * 2004-03-22 2005-10-06 Honeywell International, Inc. Cold gas-dynamic spray repair on gas turbine engine components
WO2007027177A1 (en) * 2004-08-30 2007-03-08 Honeywell International Inc. Method for repairing titanium alloy components
EP1666635A1 (en) * 2004-12-03 2006-06-07 United Technologies Corporation Superalloy repair using cold spray
EP1672175A1 (en) * 2004-12-14 2006-06-21 Honeywell International Inc. A method for applying environmental-resistant mcraly coatings on gas turbine components
EP1674595A2 (en) * 2004-12-21 2006-06-28 United Technologies Corporation Structural repair using cold sprayed aluminum material
EP1674594A1 (en) * 2004-12-22 2006-06-28 United Technologies Corporation Blade platform restoration using cold spray
US20060166020A1 (en) * 2005-01-26 2006-07-27 Honeywell International, Inc. High strength amorphous and microcrystaline structures and coatings
EP1897972A1 (en) * 2006-09-11 2008-03-12 United Technologies Corporation Method for processing titanium alloy components

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010054643A1 (en) * 2008-11-13 2010-05-20 Mtu Aero Engines Gmbh Method for repairing the component of a gas turbine
FR2978076A1 (en) * 2011-07-22 2013-01-25 Snecma Method for assembling metal shell utilized for making high pressure compressor casings, involves depositing powder of alloy by cold projection at supersonic speed on face such that shell is formed on another shell
EP2778256A1 (en) * 2013-03-15 2014-09-17 Bell Helicopter Textron Inc. Methods utilizing cold spray techniques for repairing and protecting rotary components of aviation propulsion systems
US9394063B2 (en) 2013-03-15 2016-07-19 Bell Helicopter Textron Inc. Methods utilizing cold spray techniques for repairing and protecting rotary components of aviation propulsion systems
CN112323057A (en) * 2019-07-20 2021-02-05 通用电气公司 Cold spray repair of engine parts

Also Published As

Publication number Publication date
DE102007056451A1 (en) 2009-05-28

Similar Documents

Publication Publication Date Title
WO2009065385A1 (en) Method for repairing a gas turbine component
EP2099582B1 (en) Device and method for the repair or production of blade tips of blades of a gas turbine, in particular of an aircraft engine
DE3730266C2 (en)
EP3562608A1 (en) Method and device for the powder bed-based additive building up of a plurality of identical components
EP1951990A1 (en) Method of repairing a shroud segment of a gas turbine
DE602004007743T2 (en) Method for producing or repairing an assembly
EP2783076B1 (en) Method for hardfacing the z-notch of tial blades
DE102006044555A1 (en) repair procedures
DE102010026084A1 (en) Applying material layer on workpiece made of material containing titanium aluminide, comprises heating workpiece by induction at preheating temperature and applying powdery additive on heated surface of workpiece by deposition welding
EP2038083B1 (en) Method for repairing and/or replacing individual elements of a gas turbine component
WO2010094273A2 (en) Production of a turbine blisk having an oxidation and/or corrosion protection layer
EP2062997A2 (en) Device for coating components
WO2006026955A1 (en) Method for repairing turbomachine blades
EP1816235B9 (en) Method of repairing defects in castings
EP2647798B1 (en) Method for producing an abradable
EP2781622A1 (en) Generative method particularly for producing a coating, device for carrying out the method, coating and a component manufacturing method and a component
DE102008036450A1 (en) Labyrinth-sealing web-repairing process for gas turbine, comprises subjecting a metal melt on a component surface to be constructed, where the metal melt is produced by melting of particles of metal powder using laser beam
DE102010048336A1 (en) Component and method for forming, repairing and / or constructing such a component
WO2015176923A1 (en) Method for repairing an airfoil, and cooling collar
DE102006050792A1 (en) Repair process for seal fin of gas turbine involves welding on ceramic material in addition to metal material
WO2018215322A1 (en) Use of powder tubes for supplying solder mixtures in the generative manufacturing of components by means of laser deposition welding
EP3493931A1 (en) Method for producing a channel structure and component
WO2009103268A1 (en) Method for coating components
DE102017204507A1 (en) Method for closing an opening of a turbine blade
DE102017201645A1 (en) A method and apparatus for repairing a damaged blade tip of an armored and blade-coated turbine blade

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 08852072

Country of ref document: EP

Kind code of ref document: A1

122 Ep: pct application non-entry in european phase

Ref document number: 08852072

Country of ref document: EP

Kind code of ref document: A1