Nothing Special   »   [go: up one dir, main page]

EP1838493A1 - Method for repairing turbine blades - Google Patents

Method for repairing turbine blades

Info

Publication number
EP1838493A1
EP1838493A1 EP06705784A EP06705784A EP1838493A1 EP 1838493 A1 EP1838493 A1 EP 1838493A1 EP 06705784 A EP06705784 A EP 06705784A EP 06705784 A EP06705784 A EP 06705784A EP 1838493 A1 EP1838493 A1 EP 1838493A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
section
damaged
turbine blade
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Withdrawn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
EP06705784A
Other languages
German (de)
French (fr)
Inventor
Frank Seidel
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.)
MTU Aero Engines AG
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 EP1838493A1 publication Critical patent/EP1838493A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/233—Electron beam welding
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/234—Laser welding
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/235—TIG or MIG welding
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering

Definitions

  • the invention relates to a method for repairing turbine blades of a gas turbine.
  • a gas turbine in particular an aircraft engine, comprises, in addition to a combustion chamber, at least one compressor and at least one turbine.
  • a turbine In the first stages of a turbine usually internally cooled turbine blades are used, which are designed as hollow blades. This is partly due to the fact that in the first stages of the turbine very high temperatures prevail, whereby an internal cooling of the blades is required.
  • Such internally cooled blades have a complex internal geometry.
  • less turbocharged turbine blades are designed as full blades.
  • Turbine blades of gas turbines are subject during operation to high loads and thus wear, in particular by abrasion, cracking, oxidation, burns or even erosion and corrosion. Due to the above wear, it is necessary to repair the turbine blades after damage.
  • the present invention is based on the problem of providing a novel method for repairing turbine blades.
  • This problem is solved by a method of repairing turbine blades according to claim 1.
  • the method comprises at least the following steps: a) providing a turbine blade to be repaired; b) removing a damaged airfoil portion from the turbine blade to form a blade stub; c) establishing a replacement section for the damaged and removed airfoil section of the turbine blade; d) connecting the replacement section with the corresponding blade stump.
  • the method according to the invention for repairing turbine blades of a gas turbine is described below by way of example using the example of a turbine blade designed as a hollow blade. It should be noted at this point that the method according to the invention can also be used in turbine blade segments or integrally bladed rotors.
  • the turbine blades to be repaired by the method according to the invention can be designed as hollow blades or as full blades.
  • the procedure is such that a damaged blade section is removed from a provided turbine blade to be repaired to form a blade stump.
  • a parting plane and thus a subsequent joining plane is approximately parallel to a rotation axis of a gas turbine rotor and thus approximately horizontal.
  • the damaged blade section is preferably separated from the hollow blade in such a way that the separation plane runs as close as possible to the blade tip of the hollow blade. It is also possible to position the parting plane as far as the blade platform or a blade root.
  • This replacement section has exactly the geometry of the damaged, severed airfoil section in undamaged form.
  • the replacement section is produced by investment casting or by powder metallurgy manufacturing, in particular by powder metallurgical injection molding. It is possible to make the replacement section of the same material as the damaged and severed airfoil section. However, it is also possible to produce the replacement section from another material with a better wear behavior or better joining properties.
  • the replacement section produced is connected to the blade stump which has formed in the region of the severed damaged blade section.
  • the joining surfaces of the blade stub and the replacement section are machined by grinding.
  • the joining or joining of the replacement section with the corresponding blade stump is carried out either by beam welding or by soldering.
  • the replacement section is connected to the corresponding blade stump by beam welding, in particular laser beam welding or electron beam welding is used. Due to the small focus that can be realized during laser beam welding and electron beam welding, precise joining of the blade stump to the replacement section is possible so that both inner contours and outer contours are completely welded. This is important in the case of hollow blades, since no reworking is possible on the inner contours of the hollow blades after welding.
  • connection of the replacement section with the blade stump can be done by soldering.
  • the soldering is carried out using as little solder as possible, in particular using thin solder foils or so-called solder tapes, which are geometrically adapted to the joining surface.
  • a solder foil which is geometrically preformed according to the respective joining surface is applied to the joining surface, and subsequently the replacement section is connected to the blade stump in a soldering process.
  • this method enables the setting of a defined monocrystalline or directionally solidified microstructure within the joining zone, with slow cooling from the soldering temperature. Thus, a decrease in strength in the joint zone at the respective solder seams can be avoided.
  • the present invention proposes a method of repairing turbine blades, which is particularly suitable for repairing turbine blades, which are usually made of superalloys and can be configured as hollow blades.
  • the method according to the invention is particularly suitable for repairing turbine blades of a high-pressure turbine and a low-pressure turbine.
  • the repairable damage spectrum of turbine blades is significantly expanded, since complex damage patterns can now also be repaired. It can also be repaired large damage that could not be repaired with previously used methods for crack and construction welding.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a method for repairing the turbine blades of a gas turbine comprising the following steps: a) provision of a turbine blade to be repaired; b) removal of a damaged vane section from the turbine blade to form a blade stump; c) production of a substitute section for the damaged and removed vane section of the turbine blade; d) connection of the substitute section to the corresponding blade stump.

Description

Verfahren zur Reparatur von Turbinenlaufschaufeln Method of repairing turbine blades
Die Erfindung betrifft ein Verfahren zur Reparatur von Turbinenlaufschaufeln einer Gasturbine .The invention relates to a method for repairing turbine blades of a gas turbine.
Eine Gasturbine , insbesondere ein Flugtriebwerk, umfasst neben einer Brennkammer mindestens einen Verdichter sowie mindestens eine Turbine . In den ersten Stufen einer Turbine kommen in der Regel innengekühlte Turbinenlaufschaufeln zum Einsatz , die als Hohlschaufeln ausgebildet sind. Dies liegt unter anderem darin begründet , dass in den ersten Stufen der Turbine sehr hohe Temperaturen herrschen, wodurch eine Innenkühlung der Laufschaufeln erforderlich wird. Derartige innengekühlte Laufschaufeln verfügen über eine komplexe Innengeometrie . Neben Hohlschaufeln werden weniger temperaturbelastete Turbinenlaufschaufeln als Vollschaufeln ausgeführt .A gas turbine, in particular an aircraft engine, comprises, in addition to a combustion chamber, at least one compressor and at least one turbine. In the first stages of a turbine usually internally cooled turbine blades are used, which are designed as hollow blades. This is partly due to the fact that in the first stages of the turbine very high temperatures prevail, whereby an internal cooling of the blades is required. Such internally cooled blades have a complex internal geometry. In addition to hollow blades less turbocharged turbine blades are designed as full blades.
Turbinenlaufschaufeln von Gasturbinen, insbesondere von Flugtriebwerken, unterliegen während des Betriebs hohen Belastungen und somit einem Verschleiß, insbesondere durch Abrasion, Rissbildung, Oxidation, Verbrennungen oder auch Erosion und Korrosion . Durch den oben genannten Verschleiß ist es erforderlich, die Turbinenlaufschaufeln j e nach Beschädigung zu reparieren .Turbine blades of gas turbines, in particular of aircraft engines, are subject during operation to high loads and thus wear, in particular by abrasion, cracking, oxidation, burns or even erosion and corrosion. Due to the above wear, it is necessary to repair the turbine blades after damage.
Nach dem Stand der Technik wird zur Reparatur von Turbinenlaufschaufeln so vorgegangen, dass ein beschädigter Abschnitt der Turbinenlaufschaufeln entfernt und durch Auftragschweißen erneuert wird. Das Auftragschweißen von Turbinenlaufschaufeln mit komplexen Innengeometrien ist j edoch verfahrenstechnisch sehr anspruchsvoll , sodass sich viele Schadensbilder nicht reparieren lassen .In the prior art, repair of turbine blades is accomplished by removing a damaged portion of the turbine blades and renewing it by buildup welding. However, the overlay welding of turbine blades with complex internal geometries is very demanding in terms of process engineering, so that many damage patterns can not be repaired.
Des weiteren wird das Auftragschweißen dadurch erschwert , dass die Turbinenlaufschaufeln aus Superlegierungen und damit aus Werkstoffen hergestellt sind, bei welchen ein Wiederaufbau beschädigter Abschnitte durch Auftragschweißen ohnehin sehr problematisch ist . Dies gilt insbesondere dann, wenn die Turbinenlaufschaufeln aus polykristallinen, einkristallinen oder gerichtet erstarrten Werkstoffen hergestellt sind .Furthermore, buildup welding is made more difficult by the fact that the turbine blades are made of superalloys and thus of materials in which a reconstruction of damaged sections by build-up welding is very problematic anyway. This is especially true when the turbine blades are made of polycrystalline, monocrystalline or directionally solidified materials.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Reparatur von Turbinenlaufschaufeln zu schaffen . Dieses Problem wird durch ein Verfahren zur Reparatur von Turbinenlaufschaufeln gemäß Patentanspruch 1 gelöst . Erfindungsgemäß umfasst das Verfahren zumindest die folgenden Schritte : a) Bereitstellen einer zu reparierenden Turbinenlaufschaufel ; b) Entfernen eines beschädigten Schaufelblattabschnitts von der Turbinenlaufschaufel unter Bildung eines Schaufelstumpfes ; c) Herstellen eines Austauschabschnitts für den beschädigten sowie entfernten Schaufelblattabschnitt der Turbinenlaufschaufel ; d) Verbinden des Austauschabschnitts mit dem entsprechenden Schaufelstumpf .On this basis, the present invention is based on the problem of providing a novel method for repairing turbine blades. This problem is solved by a method of repairing turbine blades according to claim 1. According to the invention, the method comprises at least the following steps: a) providing a turbine blade to be repaired; b) removing a damaged airfoil portion from the turbine blade to form a blade stub; c) establishing a replacement section for the damaged and removed airfoil section of the turbine blade; d) connecting the replacement section with the corresponding blade stump.
Bevorzugte Weiterbildungen der Erfindung ergeben sich, ohne hierauf beschränkt zu sein, aus den Unteransprüchen und der nachfolgenden Beschreibung .Preferred embodiments of the invention will become apparent from, but not limited to, the subclaims and the description below.
Das erfindungsgemäße Verfahren zur Reparatur von Turbinenlaufschaufeln einer Gasturbine wird nachfolgend am Beispiel einer als Hohlschaufel ausgebildeten Turbinenlaufschaufel exemplarisch beschrieben . Es sei an dieser Stelle darauf hingewiesen, dass das erfindungsgemäße Verfahren auch bei Turbinenlaufschaufelsegmenten oder integral beschaufelten Rotoren zum Einsatz kommen kann . Die mit dem erfindungsgemäßen Verfahren zu reparierenden Turbinenlaufschaufeln können als Hohlschaufeln oder als Vollschaufeln ausgeführt sein .The method according to the invention for repairing turbine blades of a gas turbine is described below by way of example using the example of a turbine blade designed as a hollow blade. It should be noted at this point that the method according to the invention can also be used in turbine blade segments or integrally bladed rotors. The turbine blades to be repaired by the method according to the invention can be designed as hollow blades or as full blades.
Nach dem erfindungsgemäßen Verfahren wird so vorgegangen, dass von einer bereitgestellten, zu reparierenden Turbinenlaufschaufel ein beschädigter Schaufelblattabschnitt unter Bildung eines Schaufelstumpfes entfernt wird. Beim Entfernen bzw . Abtrennen des beschädigten Schaufelblattabschnitts der Hohlschaufel wird so vorgegangen, dass eine Trennebene und damit eine spätere Fügeebene in etwa parallel zu einer Drehachse eines Gasturbinenrotors und damit in etwa horizontal verläuft . Der beschädigte Schaufelblattabschnitt wird von der Hohlschaufel vorzugsweise derart abgetrennt , dass die Trennebene möglichst nahe zur Schaufelspitze der Hohlschaufel verläuft . Es ist auch möglicht , die Trennebene bis an die Schaufelplattform oder einen Schaufelfuß zu positionieren .According to the method of the invention, the procedure is such that a damaged blade section is removed from a provided turbine blade to be repaired to form a blade stump. When removing or. Separation of the damaged blade leaf portion of the hollow blade is so proceeded that a parting plane and thus a subsequent joining plane is approximately parallel to a rotation axis of a gas turbine rotor and thus approximately horizontal. The damaged blade section is preferably separated from the hollow blade in such a way that the separation plane runs as close as possible to the blade tip of the hollow blade. It is also possible to position the parting plane as far as the blade platform or a blade root.
Anschließend wird ein Austauschabschnitt bzw. ein Ersatzteil für den beschädigten sowie entfernten Schaufelblattabschnitt der Hohlschaufel hergestellt . Dieser Austauschabschnitt verfügt exakt über die Geometrie des beschädigten, abgetrennten Schaufelblattabschnitts in ungeschädigter Form. Die Herstellung des Austauschabschnitts erfolgt durch Feingießen oder durch pulvermetallurgisches Fertigen, insbesondere durch pulvermetallur- gisches Spritzgießen . Es ist dabei möglich, den Austauschabschnitt aus dem gleichen Werkstoff herzustellen, wie der beschädigte und abgetrennte Schaufelblattabschnitt . Es ist j edoch auch möglich, den Austauschab- schnitt aus einem anderen Werkstoff mit einem besseren Verschleißverhalten oder besseren Fügeeigenschaften herzustellen .Subsequently, a replacement portion for the damaged and removed airfoil portion of the hollow blade is produced. This replacement section has exactly the geometry of the damaged, severed airfoil section in undamaged form. The replacement section is produced by investment casting or by powder metallurgy manufacturing, in particular by powder metallurgical injection molding. It is possible to make the replacement section of the same material as the damaged and severed airfoil section. However, it is also possible to produce the replacement section from another material with a better wear behavior or better joining properties.
Anschließend wird der hergestellte Austauschabschnitt mit dem im Bereich des abgetrennten, beschädigten Schaufelblattabschnitt entstandenen Schaufelstumpf verbunden . Vor dem Verbinden werden die Fügeflächen von Schaufelstumpf und Austauschabschnitt durch Schleifen bearbeitet . Das Verbinden bzw. Fügen des Austauschabschnitts mit dem entsprechenden Schaufelstumpf erfolgt entweder durch Strahlschweißen oder durch Löten .Subsequently, the replacement section produced is connected to the blade stump which has formed in the region of the severed damaged blade section. Before joining, the joining surfaces of the blade stub and the replacement section are machined by grinding. The joining or joining of the replacement section with the corresponding blade stump is carried out either by beam welding or by soldering.
Wird der Austauschabschnitt mit dem entsprechenden Schaufelstumpf durch Strahlschweißen verbunden, so findet insbesondere Laserstrahlschweißen oder Elektronenstrahlschweißen Verwendung . Durch den beim Laserstrahlschweißen sowie Elektronenstrahlschweißen realisierbaren kleinen Fokus ist ein exaktes Fügen des Schaufelstumpfs mit dem Austauschabschnitt möglich, so dass sowohl Innenkonturen als auch Außenkonturen vollständig verschweißt werden . Dies ist bei Hohlschaufeln von Bedeutung, da an den Innenkonturen der Hohlschaufeln nach dem Schweißen keine Nachbearbeitung möglich ist .If the replacement section is connected to the corresponding blade stump by beam welding, in particular laser beam welding or electron beam welding is used. Due to the small focus that can be realized during laser beam welding and electron beam welding, precise joining of the blade stump to the replacement section is possible so that both inner contours and outer contours are completely welded. This is important in the case of hollow blades, since no reworking is possible on the inner contours of the hollow blades after welding.
Alternativ kann die Verbindung des Austauschabschnitts mit dem Schaufelstumpf durch Löten erfolgen . Das Löten erfolgt unter Verwendung von möglichst wenig Lot , insbesondere unter Verwendung dünner Lötfolien bzw. sogenannter Löttapes , die an die Fügefläche geometrisch angepasst sind. So wird zum Löten eine entsprechend der j eweiligen Fügefläche geometrisch vorgeformte Lötfolie auf die Fügefläche aufgebracht und anschließend wird der Austauschabschnitt mit dem Schaufelstumpf in einem Lötprozess verbunden . Für einkristalline Werkstoffe oder für gerichtet erstarrte Werkstoffe ermöglicht dieses Verfahren bei langsamer Abkühlung von der Löttemperatur die Einstellung einer definierten einkristallinen oder gerichtet erstarrten Gefügestruktur innerhalb der Fügezone . Damit kann ein Festigkeitsabfall in der Fügezone an den j eweiligen Lotnähten vermieden werden .Alternatively, the connection of the replacement section with the blade stump can be done by soldering. The soldering is carried out using as little solder as possible, in particular using thin solder foils or so-called solder tapes, which are geometrically adapted to the joining surface. Thus, for soldering, a solder foil which is geometrically preformed according to the respective joining surface is applied to the joining surface, and subsequently the replacement section is connected to the blade stump in a soldering process. For monocrystalline materials or for directionally solidified materials, this method enables the setting of a defined monocrystalline or directionally solidified microstructure within the joining zone, with slow cooling from the soldering temperature. Thus, a decrease in strength in the joint zone at the respective solder seams can be avoided.
Mit der hier vorliegenden Erfindung wird ein Verfahren zur Reparatur von Turbinenlaufschaufeln vorgeschlagen, welches sich speziell zum Reparieren von Turbinenlaufschaufeln eignet , die üblicherweise aus Superlegierungen hergestellt sind und als Hohlschaufeln ausgeführt sein können . So eignet sich das erfindungsgemäße Verfahren insbesondere zur Reparatur von Turbinenlaufschaufeln einer Hochdruckturbine sowie einer Niederdruckturbine . Mit dem erfindungsgemäßen Verfahren wird das reparierbare SchadensSpektrum an Turbinenlaufschaufeln deutlich erweitert , da nun auch komplexe Schadensbilder reparabel sind. Es können auch große Beschädigungen repariert werden, die mit bislang eingesetzten Methoden zum Riss- und Aufbauschweißen nicht repariert werden konnten . The present invention proposes a method of repairing turbine blades, which is particularly suitable for repairing turbine blades, which are usually made of superalloys and can be configured as hollow blades. Thus, the method according to the invention is particularly suitable for repairing turbine blades of a high-pressure turbine and a low-pressure turbine. With the method according to the invention, the repairable damage spectrum of turbine blades is significantly expanded, since complex damage patterns can now also be repaired. It can also be repaired large damage that could not be repaired with previously used methods for crack and construction welding.

Claims

Patentansprüche claims
1. Verfahren zur Reparatur von Turbinenlaufschaufeln einer Gasturbine, mit folgenden Schritten: a) Bereitstellen einer zu reparierenden Turbinenlaufschaufel ; b) Entfernen eines beschädigten Schaufelblattabschnitts von der Turbinenlaufschaufel unter Bildung eines Schaufelstumpfes; c) Herstellen eines Austauschabschnitts für den beschädigten sowie entfernten Schaufelblattabschnitt der Turbinenlaufschaufel ; d) Verbinden des Austauschabschnitts mit dem entsprechenden Schaufelstumpf .A method of repairing turbine blades of a gas turbine comprising the steps of: a) providing a turbine blade to be repaired; b) removing a damaged airfoil portion from the turbine blade to form a blade stub; c) establishing a replacement section for the damaged and removed airfoil section of the turbine blade; d) connecting the replacement section with the corresponding blade stump.
2. Verfahren nach Anspruch 1 , dadurch gekennzeichnet, dass als zu reparierende Turbinenlaufschaufel eine Hohlschaufel, insbesondere einer Hochdruckturbine, bereitgestellt wird.2. The method according to claim 1, characterized in that as a turbine blade to be repaired, a hollow blade, in particular a high-pressure turbine, is provided.
3. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass als zu reparierende Turbinenlaufschaufel eine Vollschaufel, insbesondere einer Hochdruckturbine, bereitgestellt wird.3. The method according to claim 1, characterized in that as a turbine blade to be repaired, a full blade, in particular a high-pressure turbine, is provided.
4. Verfahren nach einem oder mehreren der Ansprüche 1 bis 3 , dadurch gekennzeichnet, dass der beschädigte Schaufelblattabschnitt der Turbinenlaufschaufel derart von einem Rumpfbereich derselben abgetrennt wird, dass eine Trennebene in etwa parallel zu eine Drehachse eines Rotors verläuft .4. The method according to one or more of claims 1 to 3, characterized in that the damaged airfoil section of the turbine blade is so separated from a body portion thereof that a parting plane is approximately parallel to a rotational axis of a rotor.
5. Verfahren nach einem oder mehreren der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass der beschädigte Schaufelblattabschnitt der Turbinenlaufschaufel derart von einem Rumpfbereich derselben abgetrennt wird, dass eine Trennebene in etwa horizontal verläuft .5. The method according to one or more of claims 1 to 4, characterized in that the damaged airfoil section of the turbine blade is so separated from a body portion thereof that a parting plane is approximately horizontal.
6. Verfahren nach einem oder mehreren der Ansprüche 1 bis 5 , dadurch gekennzeichnet, dass der beschädigte Schaufelblattabschnitt der Turbinenlaufschaufel derart von einem Rumpfbereich derselben abgetrennt wird, dass eine Trennebene möglichst nahe zur Schaufelspitze derselben verläuft . 6. The method according to one or more of claims 1 to 5, characterized in that the damaged blade airfoil section of the turbine blade is so separated from a body portion thereof that a parting plane as close as possible to the blade tip thereof.
7. Verfahren nach einem oder mehreren der Ansprüche 1 bis 6 , dadurch gekennzeichnet, dass der Austauschabschnitt durch Gießen, insbesondere durch Feingießen, hergestellt wird.7. The method according to one or more of claims 1 to 6, characterized in that the exchange section is produced by casting, in particular by investment casting.
8. Verfahren nach einem oder mehreren der Ansprüche 1 bis 6 , dadurch gekennzeichnet, dass der Austauschabschnitt durch pulvermetallurgisches Fertigen, insbesondere durch pulvermetallurgisches Spritzgießen, hergestellt wird.8. The method according to one or more of claims 1 to 6, characterized in that the replacement section by powder metallurgy manufacturing, in particular by powder metallurgy injection molding, is prepared.
9. Verfahren nach einem oder mehreren der Ansprüche 1 bis 8 , dadurch gekennzeichnet , dass der Austauschabschnitt mit dem entsprechenden Schaufelstumpf durch Strahlschweißen, insbesondere durch Laserstrahlschweißen oder Elektronenstrahlschweißen, verbunden wird.9. The method according to one or more of claims 1 to 8, characterized in that the exchange section with the corresponding blade stump by beam welding, in particular by laser beam welding or electron beam welding, is connected.
10. Verfahren nach einem oder mehreren der Ansprüche 1 bis 8 , dadurch gekennzeichnet , dass der Austauschabschnitt mit dem entsprechenden Schaufelstumpf durch Löten verbunden wird.10. The method according to one or more of claims 1 to 8, characterized in that the exchange portion is connected to the corresponding blade stump by soldering.
11. Verfahren nach Anspruch 10 , dadurch gekennzeichnet , dass hierzu im Bereich der Trennebene und damit Fügefläche eine an die Form der Fügefläche angepasste Lötfolie aufgebracht wird, und dass anschließend der Austauschabschnitt mit dem entsprechenden Schaufelstumpf verlötet wird. 11. The method according to claim 10, characterized in that for this purpose in the region of the parting plane and thus joining surface adapted to the shape of the joining surface soldering foil is applied, and that subsequently the exchange portion is soldered to the corresponding blade stump.
EP06705784A 2005-01-20 2006-01-13 Method for repairing turbine blades Withdrawn EP1838493A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200510002609 DE102005002609A1 (en) 2005-01-20 2005-01-20 Method of repairing turbine blades
PCT/DE2006/000045 WO2006076884A1 (en) 2005-01-20 2006-01-13 Method for repairing turbine blades

Publications (1)

Publication Number Publication Date
EP1838493A1 true EP1838493A1 (en) 2007-10-03

Family

ID=36169150

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06705784A Withdrawn EP1838493A1 (en) 2005-01-20 2006-01-13 Method for repairing turbine blades

Country Status (3)

Country Link
EP (1) EP1838493A1 (en)
DE (1) DE102005002609A1 (en)
WO (1) WO2006076884A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006049219A1 (en) 2006-10-18 2008-04-30 Mtu Aero Engines Gmbh High pressure turbine blade and method of repairing high pressure turbine blades
DE102008025848A1 (en) * 2008-05-29 2009-12-03 Mtu Aero Engines Gmbh Process for repairing single-crystal high-pressure turbine blades by diffusion soldering
DE102008058140A1 (en) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Method for repair of single crystal turbine blades, particularly high-pressure turbine stage, involves removing damaged blade part of turbine blades at parting plane on remaining blade
FR2949366B1 (en) * 2009-08-31 2011-11-18 Snecma MIM PROCESSING OF A PIECE PIECE FOR THE REPAIR OF A TURBINE DISPENSER BLADE
EP2583781B1 (en) * 2011-10-21 2014-06-25 Siemens Aktiengesellschaft Combined welding-soldering process for joining two workpieces

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0401187A2 (en) * 1989-06-01 1990-12-05 Abb Stal Ab Method for reconstruction of blades and vanes in steam turbines at existing erosion damages
US20010014403A1 (en) * 1997-08-12 2001-08-16 Lawrence Evans Brown Method and apparatus for making components by direct laser processing

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4152488A (en) * 1977-05-03 1979-05-01 United Technologies Corporation Gas turbine blade tip alloy and composite
US4883216A (en) * 1988-03-28 1989-11-28 General Electric Company Method for bonding an article projection
DE19642980C1 (en) * 1996-10-18 1998-08-13 Mtu Muenchen Gmbh Procedure for repairing worn blade tips of compressor and turbine blades
US5822852A (en) * 1997-07-14 1998-10-20 General Electric Company Method for replacing blade tips of directionally solidified and single crystal turbine blades
DE19831736C2 (en) * 1998-07-15 2000-05-31 Mtu Muenchen Gmbh Method for repairing and manufacturing an integrally bladed rotor for a turbomachine
JP2000263247A (en) * 1999-03-10 2000-09-26 Ishikawajima Harima Heavy Ind Co Ltd Method of repairing parts of directional control crystal alloy
US6238187B1 (en) * 1999-10-14 2001-05-29 Lsp Technologies, Inc. Method using laser shock peening to process airfoil weld repairs pertaining to blade cut and weld techniques
US6508000B2 (en) * 2001-02-08 2003-01-21 Siemens Westinghouse Power Corporation Transient liquid phase bonding repair for advanced turbine blades and vanes
US6908288B2 (en) * 2001-10-31 2005-06-21 General Electric Company Repair of advanced gas turbine blades
DE10319494A1 (en) * 2003-04-30 2004-11-18 Mtu Aero Engines Gmbh Process for repairing and / or modifying components of a gas turbine
US20050091848A1 (en) * 2003-11-03 2005-05-05 Nenov Krassimir P. Turbine blade and a method of manufacturing and repairing a turbine blade
US20050102835A1 (en) * 2003-11-14 2005-05-19 Trewiler Gary E. Method for repairing gas turbine rotor blades

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0401187A2 (en) * 1989-06-01 1990-12-05 Abb Stal Ab Method for reconstruction of blades and vanes in steam turbines at existing erosion damages
US20010014403A1 (en) * 1997-08-12 2001-08-16 Lawrence Evans Brown Method and apparatus for making components by direct laser processing

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2006076884A1 *

Also Published As

Publication number Publication date
WO2006076884A1 (en) 2006-07-27
DE102005002609A1 (en) 2006-08-03

Similar Documents

Publication Publication Date Title
EP2352615B1 (en) Method for manufacturing or repairing blisk
DE60010288T2 (en) METHOD FOR REPLACING TURBINE GUIDE SHOVELS
DE60126723T2 (en) Repair method for a turbine nozzle
DE60211228T2 (en) Method for repairing a turbine nozzle
EP1678410B1 (en) Method for joining blades to blade roots or rotor disks when producing and/or repairing gas turbine blades or integrally bladed gas turbine rotors
DE68907881T2 (en) Manufacturing or repair process for an integrated blade rotor assembly.
EP2064025B1 (en) Method of repair
DE102009033835B4 (en) Method for replacing a blade of a rotor with integrated blading and such a rotor
DE60319492T2 (en) Repair method for a turbine nozzle and turbine nozzle
EP2484481A1 (en) Method for repairing or reconditioning a badly damaged component, in particular from the hot gas region of a gas turbine
EP1670612A1 (en) Method for the production of a hole and device
WO2007003160A1 (en) Method for the production of an armor plating for a blade tip
DE102008058140A1 (en) Method for repair of single crystal turbine blades, particularly high-pressure turbine stage, involves removing damaged blade part of turbine blades at parting plane on remaining blade
EP1838493A1 (en) Method for repairing turbine blades
DE102004036066A1 (en) Method for repairing or manufacturing a component
DE102007019949A1 (en) A semi-finished product for producing a repaired blade for a gas turbine and repair method for repairing a blade for a gas turbine
DE102015219513B4 (en) Repair procedure for sealing segments
EP2004361A1 (en) Method for repairing a guide vane segment
EP2781622A1 (en) Generative method particularly for producing a coating, device for carrying out the method, coating and a component manufacturing method and a component
DE102009048632A1 (en) joining methods
EP2230041A2 (en) Process for the fabrication of a hole
DE102008025848A1 (en) Process for repairing single-crystal high-pressure turbine blades by diffusion soldering
EP0882545A2 (en) Repairing method for integrally cast stator rings of a turbine
DE102006057912A1 (en) Vane ring and method for producing the same
DE69120175T2 (en) Repair technology for shovel feet

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20070716

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20081113

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES GMBH

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES AG

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20170801