DE102007056451A1 - Method for repairing a gas turbine component - Google Patents
Method for repairing a gas turbine component Download PDFInfo
- Publication number
- DE102007056451A1 DE102007056451A1 DE200710056451 DE102007056451A DE102007056451A1 DE 102007056451 A1 DE102007056451 A1 DE 102007056451A1 DE 200710056451 DE200710056451 DE 200710056451 DE 102007056451 A DE102007056451 A DE 102007056451A DE 102007056451 A1 DE102007056451 A1 DE 102007056451A1
- Authority
- DE
- Germany
- Prior art keywords
- turbine component
- gas turbine
- gas
- section
- renewed
- 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- Withdrawn
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
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- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Die Erfindung betrifft ein 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. Erfindungsgemäß wird der beschädigte und entfernte Abschnitt durch kinetisches Kaltgasspritzen erneuert.The invention relates to a method for repairing a gas turbine component, in particular a sealing device such as a sealing fin, wherein at least one damaged section is removed from a gas turbine component to be repaired and the same is renewed. According to the invention, the damaged and removed section is renewed by kinetic cold gas spraying.
Description
Die Erfindung betrifft ein Verfahren zur Reparatur eines Gasturbinenbauteils, insbesondere einer Dichteinrichtung, nach dem Oberbegriff des Anspruchs 1.The The invention relates to a method for repairing a gas turbine component, in particular a sealing device, according to the preamble of the 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. B. in gas turbines, are designed as sealing fins Sealing devices in particular the sealing of a gap between the stator Assemblies and rotor-side assemblies of the turbomachine. Operational Sealing devices are subject to wear so that they are repaired after damage Need to become.
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.To The practice is trained in the repair of sealing fins Sealing devices proceeded so that of a repaired Sealing device at least one damaged section is removed, the same by welding a metallic material is renewed. At out of practice known repair method is after welding of the metallic material, the geometry provided by welding adapted by grinding a new part geometry, followed by a after the grinding forming tip of the sealing device coated by thermal spraying with a ceramic material so as to armor the tip of the 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 z. B. sealing fins by welding a metallic material by z. B. laser powder deposition welding allows in principle the repair of sealing fins, often However, if the parts to be welded are such according to the current state of the art, not or only conditionally melt-weldable materials, their repair welding too inadmissible welding defects like cracks leads. There is therefore a need for a method for repairing a Gas turbine component, with which avoids the above disadvantages can be.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Reparatur eines Gasturbinenbauteils, insbesondere einer Dichteinrichtung, zu schaffen.Of these, Based on the present invention, the problem underlying a novel method for repair of a gas turbine component, in particular a sealing device to create.
Dieses Problem wird durch ein Verfahren gemäß Anspruch 1 gelöst.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 damaged and renewed section 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, separated portion of a gas turbine component by kinetic Cold gas spraying. The renewed section can with minimal porosity and maximum Adhesive strength can be applied. Furthermore, with the help of kinetic cold gas spraying several millimeters thick layers are applied. Farther is the formation of cracks, which usually form during welding operations, avoided.
Vorzugsweise wird nach dem Erneuern des beschädigten Abschnitts zumindest der erneuerte Abschnitt einer Wärmebehandlung unterzogen.Preferably will after renewing the damaged one Section at least the renewed section of a heat treatment subjected.
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 Further developments of the invention will become apparent from the dependent claims and the following description. Embodiments of the invention without being limited to this to be closer below explained.
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 The invention relates to a method for repairing a gas turbine component, in particular a sealing device such. B. a sealing fin. to Repair of such a gas turbine component is first of a at least one damaged section to be repaired gas turbine component removed, renewing the removed section. For the purpose of the present invention is renewing the damaged and removed section 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.At the Kinetic cold gas syringes contain particles in a carrier gas, with the help of which the damaged and removed section should be renewed. In the method according to the invention is the particle size of the carrier gas contained particles between 10 and 70 microns. The particles contained in the carrier gas are at a speed between 300 and 900 m / s on the directed to be repaired gas turbine component. The gas temperature the carrier gas in 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 The kinetic cold spraying can layer thicknesses of up to 10 mm applied to the gas turbine component to be repaired become.
Bei den im Trägergas enthaltenen Partikeln handelt es sich vorzugsweise um Partikel, deren Werkstoff artgleich zum Werkstoff des zu reparierenden Gasturbinenbauteils ist.at in the carrier gas contained particles are preferably particles, the same material as the material of the repaired gas turbine component is.
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, if the gas turbine component to be repaired z. B. of a nickel-based alloy is made, consist of the particles contained in the carrier gas preferably also of a nickel-based alloy.
Im Anschluss an das Erneuern des beschädigten Abschnitts durch kinetisches Kaltgasspritzen 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.After renewing the damaged portion by kinetic cold gas spraying, 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.in the Connection to the heat treatment the renewed section of the gas turbine component is machined to final gauge. This is preferably done mechanically by z. B. turning.
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, around the carrier gas together with those in the carrier gas contained particles on the gas turbine component to be repaired to judge. In this case, in the spray gun preferably a pressure set between 30 and 40 bar.
Claims (7)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200710056451 DE102007056451A1 (en) | 2007-11-23 | 2007-11-23 | Method for repairing a gas turbine component |
PCT/DE2008/001893 WO2009065385A1 (en) | 2007-11-23 | 2008-11-18 | Method for repairing a gas turbine component |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200710056451 DE102007056451A1 (en) | 2007-11-23 | 2007-11-23 | Method for repairing a gas turbine component |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102007056451A1 true DE102007056451A1 (en) | 2009-05-28 |
Family
ID=40445649
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200710056451 Withdrawn DE102007056451A1 (en) | 2007-11-23 | 2007-11-23 | Method for repairing a gas turbine component |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE102007056451A1 (en) |
WO (1) | WO2009065385A1 (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009036407A1 (en) * | 2009-08-06 | 2011-02-10 | Mtu Aero Engines Gmbh | Abradable blade tip pad |
CN102303205A (en) * | 2011-09-05 | 2012-01-04 | 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 |
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 |
WO2013049456A3 (en) * | 2011-09-30 | 2013-06-13 | General Electric Company | A method of repairing rotating machine components |
EP3647615A1 (en) * | 2018-10-29 | 2020-05-06 | Aktiebolaget SKF | Metallic rolling or bearing component |
EP3769902A1 (en) * | 2019-07-20 | 2021-01-27 | General Electric Company | Cold spray repair of engine components |
EP4116012A1 (en) * | 2021-07-07 | 2023-01-11 | Industria de Turbo Propulsores S.A. | Material deposition method for repairing aeronautical components |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
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DE102008057162A1 (en) * | 2008-11-13 | 2010-05-20 | Mtu Aero Engines Gmbh | Method for repairing the component of a gas turbine |
FR2978076B1 (en) * | 2011-07-22 | 2013-08-16 | Snecma | ASSEMBLY OF A TITANIUM HULL AND A TITANIUM FIRE RESISTANT ALLOY COVER BY DEPOT BY COLD-SPRAY |
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 |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
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US6905728B1 (en) * | 2004-03-22 | 2005-06-14 | Honeywell International, Inc. | Cold gas-dynamic spray repair on gas turbine engine components |
US20060045785A1 (en) * | 2004-08-30 | 2006-03-02 | Yiping Hu | Method for repairing titanium alloy components |
US20060121183A1 (en) * | 2004-12-03 | 2006-06-08 | United Technologies Corporation | Superalloy repair using cold spray |
US7378132B2 (en) * | 2004-12-14 | 2008-05-27 | Honeywell International, Inc. | Method for applying environmental-resistant MCrAlY coatings on gas turbine components |
US20060134320A1 (en) * | 2004-12-21 | 2006-06-22 | United Technologies Corporation | Structural repair using cold sprayed aluminum materials |
US20060134321A1 (en) * | 2004-12-22 | 2006-06-22 | United Technologies Corporation | Blade platform restoration using cold spray |
US7479299B2 (en) * | 2005-01-26 | 2009-01-20 | Honeywell International Inc. | Methods of forming high strength coatings |
SG141297A1 (en) * | 2006-09-11 | 2008-04-28 | United Technologies Corp | Method for processing titanium alloy components |
-
2007
- 2007-11-23 DE DE200710056451 patent/DE102007056451A1/en not_active Withdrawn
-
2008
- 2008-11-18 WO PCT/DE2008/001893 patent/WO2009065385A1/en active Application Filing
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009036407A1 (en) * | 2009-08-06 | 2011-02-10 | Mtu Aero Engines Gmbh | Abradable blade tip pad |
US9260784B2 (en) | 2009-08-06 | 2016-02-16 | Mtu Aero Engines Gmbh | Blade tip coating that can be rubbed off |
DE102010048336A1 (en) * | 2010-10-13 | 2012-04-19 | Mtu Aero Engines Gmbh | Component and method for forming, repairing and / or constructing such a component |
WO2012051978A3 (en) * | 2010-10-13 | 2012-06-28 | Mtu Aero Engines Gmbh | Component, and method for developing, 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 |
CN102303205A (en) * | 2011-09-05 | 2012-01-04 | 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 |
WO2013049456A3 (en) * | 2011-09-30 | 2013-06-13 | General Electric Company | A method of repairing rotating machine components |
CN104010762A (en) * | 2011-09-30 | 2014-08-27 | 通用电气公司 | A method of repairing rotating machine components |
EP3647615A1 (en) * | 2018-10-29 | 2020-05-06 | Aktiebolaget SKF | Metallic rolling or bearing component |
EP3769902A1 (en) * | 2019-07-20 | 2021-01-27 | General Electric Company | Cold spray repair of engine components |
US11104998B2 (en) | 2019-07-20 | 2021-08-31 | General Electric Company | Cold spray repair of engine components |
EP4116012A1 (en) * | 2021-07-07 | 2023-01-11 | Industria de Turbo Propulsores S.A. | Material deposition method for repairing aeronautical components |
Also Published As
Publication number | Publication date |
---|---|
WO2009065385A1 (en) | 2009-05-28 |
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8139 | Disposal/non-payment of the annual fee |