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EP2456957B1 - Method for coating of turbine blades - Google Patents

Method for coating of turbine blades Download PDF

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Publication number
EP2456957B1
EP2456957B1 EP10740509.4A EP10740509A EP2456957B1 EP 2456957 B1 EP2456957 B1 EP 2456957B1 EP 10740509 A EP10740509 A EP 10740509A EP 2456957 B1 EP2456957 B1 EP 2456957B1
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EP
European Patent Office
Prior art keywords
intermediate layer
armor
component surface
nickel
contact surface
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.)
Not-in-force
Application number
EP10740509.4A
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German (de)
French (fr)
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EP2456957A1 (en
Inventor
Karl-Hermann Richter
Ulrich Knott
Piotr Kowalczyk
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
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MTU Aero Engines AG
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Publication date
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Publication of EP2456957A1 publication Critical patent/EP2456957A1/en
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Publication of EP2456957B1 publication Critical patent/EP2456957B1/en
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Classifications

    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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

Definitions

  • the present invention relates to a method for providing a metallic component surface with a coating according to the preamble of claim 1, as in the document US 5,890,274 is described.
  • Turbomachinery blades for low-pressure turbines often consist of nickel-base alloys or superalloys such as IN 713, MAR 227 and B 1900.
  • their shroud side Z-shaped contact surfaces are usually cobalt-chromium alloys (Co-Cr alloys or Stellite® ) armored.
  • the height of the armor is in the finished state usually 2 mm.
  • TIG micro plasma or laser beam welding is typically used.
  • the turbine blades consist of the material titanium aluminide (TiA1), they can not be provided with Stellit® armor because of a mixing of the titanium aluminide with the Stellit® brittle phases and resulting cracks in the armor and in the base material titanium aluminide of the shroud can arise.
  • Object of the present invention is to provide a method for providing a metallic component surface, in particular a contact surface of a turbine blade made of a TiAl alloy, with a coating that eliminates the aforementioned disadvantages and allows a hard armor, and to provide a turbine blade with such armor ,
  • a method according to the invention for providing a TiAl component surface, in particular a shroud surface of a turbine blade, with a coating of a Co-Cr alloy first the component surface is undersized and a body made of Co-Cr alloy manufactured. Then, the body is fixed to the component surface and joined by means of high-temperature soldering, wherein the intermediate layer of a different material, in particular Inconel® 718 or nickel, is first applied to the body.
  • the intermediate layer the adhesion of the body to the component increases, as a result, a uniform solder wetting of the body and the component surface can be achieved.
  • the body is joined via the intermediate layer with the component surface.
  • the soldering temperature for joining the intermediate layer with a component surface is less than or equal to 900 ° C.
  • One advantage of the material-sparing coating method according to the invention is that the component surfaces can be provided with a stable coating or armor without fear of crack formation in the armor or in the base material of the component. Thicknesses which can not be achieved by alternative coating methods such as galvanic coating, PVD (Physical Vapor Deposition) or plasma spraying can be achieved by forming the armor as a separate body, so that layer thicknesses of more than 2 mm are possible when using the method according to the invention.
  • the body has at least two dimensions that already correspond to two target dimensions of the armor to be achieved before soldering. It is conceivable, for example, already to manufacture the body with a desired height and desired width of the armor, so that a finishing exclusively on lateral, the depth of the armor limiting side surfaces.
  • the intermediate layer is preferably joined to the body at a soldering temperature which is higher than a soldering temperature for joining the intermediate layer to the component surface.
  • An exemplary soldering temperature for applying the intermediate layer to the body when using a nickel-based solder such as AMS 4777 ca, 1050 ° C and an exemplary soldering temperature for joining the intermediate layer with the component surface is using a nickel alloy with a high precious metal content such as gold, silver or palladium ( Au, Ag, Pd) equal to or less than 900 ° C.
  • a temperature in the range of about 900 ° C is particularly advantageous when using the material Titanaluminids, as this in principle does not tolerate higher soldering temperatures.
  • the body is first nickel-plated on the circumference and then joined to the component surface.
  • the nickel layer acts quasi as an intermediate layer for adhesion improvement.
  • soldered In a variant of the method without an intermediate layer is inductively, for example in a high vacuum oven or under inert gas, soldered.
  • a soldering temperature of about 1050 ° C can be set without fear of damaging the base material.
  • the use of the solder AMS 4777 is possible, which is characterized by a uniform wetting of, for example, Stellit® bodies and TiAl components.
  • a turbine blade according to the invention has an armor applied by the method according to the invention.
  • the armor is resilient and may have a height or thickness of several millimeters. Damage to the turbine material or the armor itself or a weakening of the turbine material or the armor by cracks when applying the armor is excluded by the application of the material-sparing method according to the invention.
  • FIG. 1 shows a plan view of a blade tip side shroud 2 a blade of a turbomachine, in particular a gas turbine.
  • the shroud 2 consists of a high-strength and high temperature resistant titanium aluminide alloy (TiAl alloy). It has a substantially plate-like shape with two spaced-apart, rotationally extending outer sealing lips or sealing webs 6, 8 for minimizing flow losses and with two Z-shaped side surfaces 10, 12.
  • the Z-shaped side surfaces 10, 12 each define a side gap to a shroud of an adjacent blade and each have a planar contact surface 14, 16 for mutual support with the adjacent blade for vibration damping.
  • the contact surfaces 14, 16 each provided with an armor 18,20.
  • the armor 18 and 20 an approximately cuboidal body 22 on.
  • the body or chip 22 is preferably made of a Co-Cr alloy, for example Stellit® 694, and has a rectangular cross-section with a plane base surface 24 facing the contact surface 14 or 16 of the shroud 2.
  • the contact surface 14 is made according to Untertn beau.
  • the body 22 is made separately from the shroud 2, for example cast or sintered. He has a height that corresponds to a target height of the armor 18.
  • the width of the base surface 24 preferably corresponds to a width of the contact surface 14.
  • the body 22 After the body 22 has been fabricated, it is fixed on its contact surface 14 via its base 24 and then soldered to it with the formation of a large-area solder layer 26.
  • the soldering is carried out inductively, for example in a high vacuum oven or under inert gas at a temperature in the range of about 1050 ° C using the nickel-based solder AMS 4777, which is characterized by a uniform wetting of the Stellite contact surface 24 and the TiAI component surface 14.
  • the armor 18 is mechanically machined to final gauge. Since the body 22 already has a width corresponding to the contact surface 14 and, moreover, the total height of the body 22 corresponds to the desired height of the armor 18, machining to final gauge, for example by grinding, is only necessary insofar as the body 22 is in terms of its Depth to a depth of the contact surface 14 is set. Of course, however, the body 22 may be formed with excess dimensions to compensate for component and assembly tolerances, so that a machining to final dimensions in principle also respect. The height and / or width of the armor 18 is necessary. Likewise, it is of course possible to provide the body 22 already with the desired dimensions of the armor in every dimension, so that a finish for setting the target dimensions can be completely eliminated.
  • the body 22 may also be connected via an intermediate layer 28 with the contact surface 14 and 16 of the shroud 2.
  • the intermediate layer 28 is disposed between the contact surface 14 and the base 24 and serves to improve the adhesion conditions of the body 22 on the shroud 2. It consists primarily of a nickel-based alloy or superalloy such as INCONEL® 718 and is as a thin sheet or a foil with a constant material thickness.
  • the base 24 of the body 22 and the intermediate layer 28 each have a geometry corresponding to the contact surface 14, so that a maximum connection region between the contact surface 14 and the intermediate layer 28 and between the intermediate layer 28 and the base 24 is provided.
  • the contact surface 14 is made according to undersize.
  • the body 22 is manufactured separately from the shroud 2 and the intermediate layer 28 is provided.
  • the height of the body 22 corresponds to the desired height of the armor 18 reduced by the thickness of the intermediate layer 28.
  • the width of the base 24 preferably corresponds to the width of the contact surface 14.
  • the intermediate layer 28 also has a width, which corresponds to the contact surface width.
  • the intermediate layer 28 is soldered to the base 24, so that a large-area solder layer 30 is formed. This takes place at about 1050 ° C.
  • a preferred solder is a nickel-based solder such as AMS 4777, since this evenly wets both TiAl materials and Stellite®.
  • the body 22 is fixed indirectly via the intermediate layer 28 on the contact surface 14. Subsequently, the intermediate layer 28 is soldered to the contact surface 14 to form a large-area solder layer 32. This is done at a temperature less than the temperature for brazing the intermediate layer 28 to the body 22. Preferably, a temperature in the range of less than or equal to 900 ° C is selected.
  • a preferred solder is nickel-based and has a high noble metal content of, for example, gold, silver or palladium. Examples are Gapasil® 9, Palcusil® 10 and Palnisi® 10.
  • the armor 18 After soldering the body 22 or the intermediate layer 28 with the shroud 2, the armor 18 is mechanically manufactured to final dimensions. Since the body 22 and the intermediate layer 28 already have a width corresponding to the contact surface 14 and, moreover, the total height of the body 22 with the intermediate layer 28 corresponds to the desired height of the armor 18, processing of the armor 18 to its final dimension is only with regard to one dimension, here the depth, necessary. Of course, however, the body 22 and the intermediate layer 28 may be formed with excess dimensions to compensate for component and assembly tolerances, so that a machining to final dimensions in principle also respect. The height and / or width of the armor 22 is necessary.
  • the body 22 may be circumferentially coated with a nickel layer 34, in which case the arranged on the base 24 nickel layer serves as an intermediate layer to improve the conditions of adhesion.
  • the geometry of the body base 24 corresponds to the geometry of the contact surface 14 or 16. Its height corresponds to the desired height of the armor 18th
  • the contact surface 14 is respectively made according to undersize.
  • the body 22 is separated from the shroud 2 manufactured and nickel-plated on the circumference. Since a subsequent processing of the armor 18 due to the nickel plating is not possible to their desired dimensions, the body 22 before the nickel plating, the target dimensions of the armor 18, ie, the body 22 has a height before the nickel plating, the target Height of the armor corresponds to 18 and its base 24 corresponds both in terms of their width and their depth of the width or depth of the contact surface 14. After nickeling, the body 22 is fixed with its nickel-plated base 24 at the contact surface 14 and at a temperature from about 900 ° C with this soldered over a solder layer 36.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Arc Welding In General (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Description

Die vorliegende Erfindung betrifft ein Verfahren zum Versehen einer metallischen Bauteilfläche mit einer Beschichtung nach dem Oberbegriff des Anspruchs 1, wie in der Druckschrift US 5,890,274 beschrieben ist.The present invention relates to a method for providing a metallic component surface with a coating according to the preamble of claim 1, as in the document US 5,890,274 is described.

Die Druckschrift US 3,702,763 offenbart ein Lot mit einer Schmelztemperatur von unter 900°C, das zum Verbinden von zwei Bauteilen aus Ti-6Al-4V verwendet wird.The publication US 3,702,763 discloses a solder having a melting temperature below 900 ° C which is used to join two Ti-6Al-4V components.

Turbinenschaufeln für Niederdruckturbinen bestehen häufig aus Nickelbasislegierungen bzw. Superlegierungen wie zum Beispiel IN 713, MAR 227 und B 1900. Zur Reduzierung des Abriebs sind ihre deckbandseitigen Z-förmigen Kontaktflächen gewöhnlich mit Cobalt-Chrom-Legierungen (Co-Cr-Legierungen bzw. Stellite®) gepanzert. Die Höhe der Panzerung beträgt im endbearbeiteten Zustand meistens 2 mm. Als Verfahren zur Herstellung der Panzerung wird typischerweise ein WIG-, Mikroplasma- oder Laserstrahlschweißen eingesetzt. Bestehen die Turbinenschaufeln jedoch aus dem Werkstoff Titanaluminid (TiA1), so können diese nicht mit einer Stellit®-Panzerung versehen werden, da infolge einer Durchmischung des Titanaluminids mit dem Stellit® spröde Phasen und daraus resultierend Risse in der Panzerung und im Grundwerkstoff Titanaluminid des Deckbandes entstehen können.Turbomachinery blades for low-pressure turbines often consist of nickel-base alloys or superalloys such as IN 713, MAR 227 and B 1900. To reduce abrasion, their shroud side Z-shaped contact surfaces are usually cobalt-chromium alloys (Co-Cr alloys or Stellite® ) armored. The height of the armor is in the finished state usually 2 mm. As a method of producing the armor, TIG, micro plasma or laser beam welding is typically used. However, if the turbine blades consist of the material titanium aluminide (TiA1), they can not be provided with Stellit® armor because of a mixing of the titanium aluminide with the Stellit® brittle phases and resulting cracks in the armor and in the base material titanium aluminide of the shroud can arise.

Aufgabe der vorliegenden Erfindung ist es, ein Verfahren zum Versehen einer metallischen Bauteilfläche, insbesondere eine Kontaktfläche einer Turbinenschaufel aus einer TiA1-Legierung, mit einer Beschichtung, das die vorgenannten Nachteile beseitigt und eine belastbare Panzerung ermöglicht, sowie eine Turbinenschaufel mit einer derartigen Panzerung zu schaffen.Object of the present invention is to provide a method for providing a metallic component surface, in particular a contact surface of a turbine blade made of a TiAl alloy, with a coating that eliminates the aforementioned disadvantages and allows a hard armor, and to provide a turbine blade with such armor ,

Diese Aufgabe wird gelöst durch ein Verfahren mit den Schritten des Patentanspruches 1.This object is achieved by a method having the steps of claim 1.

Bei einem erfindungsgemäßen Verfahren zum Versehen einer TiAl- Bauteilfläche, insbesondere eine Deckbandfläche einer Turbinenschaufel, mit einer Beschichtung aus einer Co-Cr-Legierung, wird zuerst die Bauteilfläche auf Untermaß und ein Körper aus Co-Cr-Legierung gefertigt. Dann wird der Körper an der Bauteilfläche fixiert und mittels Hochtemperaturlötens mit dieser gefügt, wobei die Zwischenschicht aus einem andersartigen Werkstoff, insbesondere Inconel® 718 oder Nickel, zuerst auf den Körper aufgetragen wird. Durch die Zwischenschicht erhöht sich die Haftung des Körpers an dem Bauteil, da hierdurch eine gleichmäßige Lotbenetzung des Körpers und der Bauteilfläche erreichbar ist. Dann wird der Körper über die Zwischenschicht mit der Bauteilfläche gefügt. Die Löttemperatur zum Fügen der Zwischenschicht mit einer Bauteilfläche ist kleiner oder gleich 900°C.In a method according to the invention for providing a TiAl component surface, in particular a shroud surface of a turbine blade, with a coating of a Co-Cr alloy, first the component surface is undersized and a body made of Co-Cr alloy manufactured. Then, the body is fixed to the component surface and joined by means of high-temperature soldering, wherein the intermediate layer of a different material, in particular Inconel® 718 or nickel, is first applied to the body. By the intermediate layer, the adhesion of the body to the component increases, as a result, a uniform solder wetting of the body and the component surface can be achieved. Then the body is joined via the intermediate layer with the component surface. The soldering temperature for joining the intermediate layer with a component surface is less than or equal to 900 ° C.

Ein Vorteil des erfindungsgemäßen materialschonenden Beschichtungsverfahren besteht darin, dass die Bauteilflächen mit einer stabilen Beschichtung bzw. Panzerung versehen werden können, ohne dass eine Rissbildung in der Panzerung oder im Grundwerkstoff des Bauteils zu befürchten ist. Dabei sind durch die Bildung der Panzerung als separater Körper Dicken erzielbar, die mit alternativen Beschichtungsverfahren wie galvanische Beschichtung, PVD (Physical Vapour Deposition) oder Plasmaspritzen nicht erreichbar sind, so dass bei Anwendung des erfindungsgemäßen Verfahrens Schichtdicken von mehr als 2 mm möglich sind.One advantage of the material-sparing coating method according to the invention is that the component surfaces can be provided with a stable coating or armor without fear of crack formation in the armor or in the base material of the component. Thicknesses which can not be achieved by alternative coating methods such as galvanic coating, PVD (Physical Vapor Deposition) or plasma spraying can be achieved by forming the armor as a separate body, so that layer thicknesses of more than 2 mm are possible when using the method according to the invention.

Um den Aufwand für eine Endbearbeitung der Panzerung gering zu halten, ist es vorteilhaft, wenn der Körper zumindest zwei Dimensionen aufweist, die bereits vor dem Verlöten zwei Soll-Dimensionen der zu erzielenden Panzerung entsprechen. Vorstellbar ist es zum Beispiel, den Körpers bereits mit einer Soll-Höhe und Soll-Breite der Panzerung zu fertigen, so dass eine Endbearbeitung ausschließlich an seitlichen, die Tiefe der Panzerung begrenzenden Seitenflächen erfolgt.To keep the cost of finishing the armor low, it is advantageous if the body has at least two dimensions that already correspond to two target dimensions of the armor to be achieved before soldering. It is conceivable, for example, already to manufacture the body with a desired height and desired width of the armor, so that a finishing exclusively on lateral, the depth of the armor limiting side surfaces.

Vorzugsweise wird die Zwischenschicht bei einer Löttemperatur mit dem Körper gefügt, die höher ist als eine Löttemperatur zum Fügen der Zwischenschicht mit der Bauteilfläche. Eine beispielhafte Löttemperatur zum Auftragen der Zwischenschicht auf den Körper beträgt bei Verwendung eines Nickelbasislotes wie AMS 4777 ca, 1050°C und eine beispielhafte Löttemperatur zum Fügen der Zwischenschicht mit der Bauteilfläche beträgt unter Verwendung eines Nickellotes mit einem hohen Edelmetallanteil wie Gold, Silber oder Palladium (Au, Ag, Pd) gleich bzw. weniger als 900°C. Eine Temperatur im Bereich von ca. 900°C ist insbesondere bei der Verwendung des Werkstoff Titanaluminids vorteilhaft, da dieser prinzipiell keine höheren Löttemperaturen verträgt.The intermediate layer is preferably joined to the body at a soldering temperature which is higher than a soldering temperature for joining the intermediate layer to the component surface. An exemplary soldering temperature for applying the intermediate layer to the body when using a nickel-based solder such as AMS 4777 ca, 1050 ° C and an exemplary soldering temperature for joining the intermediate layer with the component surface is using a nickel alloy with a high precious metal content such as gold, silver or palladium ( Au, Ag, Pd) equal to or less than 900 ° C. A temperature in the range of about 900 ° C is particularly advantageous when using the material Titanaluminids, as this in principle does not tolerate higher soldering temperatures.

Bei einem anderen erfindungsgemäßen Ausführungsbeispiel wird der Körper zuerst umfangsseitig vernickelt und dann mit der Bauteilfläche gefügt. Somit wirkt die Nickelschicht quasi als Zwischenschicht zur Haftverbesserung.In another embodiment according to the invention, the body is first nickel-plated on the circumference and then joined to the component surface. Thus, the nickel layer acts quasi as an intermediate layer for adhesion improvement.

Bei einer Verfahrensvariante ohne eine Zwischenschicht wird induktiv, beispielsweise in einem Hochvakuumofen oder unter Schutzgas, gelötet. Hierdurch kann bei Verwendung des Grundwerkstoffes Titanaluminid für das Bauteil kurzzeitig eine Löttemperatur von ca. 1050°C eingestellt werden, ohne eine Beschädigung des Grundwerkstoffs zu befürchten. Beispielsweise ist somit der Einsatz des Lotes AMS 4777 möglich, welches sich durch eine gleichmäßige Benetzung von zum Beispiel Stellit®-Körpern und TiAl-Bauteilen auszeichnet.In a variant of the method without an intermediate layer is inductively, for example in a high vacuum oven or under inert gas, soldered. As a result, when using the base material titanium aluminide for the component briefly a soldering temperature of about 1050 ° C can be set without fear of damaging the base material. For example, the use of the solder AMS 4777 is possible, which is characterized by a uniform wetting of, for example, Stellit® bodies and TiAl components.

Eine erfindungsgemäße Turbinenschaufel weist eine Panzerung auf, die nach dem erfindungsgemäßen Verfahren aufgetragen wurde. Die Panzerung ist belastbar und kann eine Höhe bzw. Dicke von mehreren Millimetern aufweisen. Eine Beschädigung des Turbinenwerkstoffs oder der Panzerung an sich bzw. eine Schwächung des Turbinenwerkstoffs oder der Panzerung durch Risse beim Auftragen der Panzerung ist durch die Anwendung des erfindungsgemäßen materialschonenden Verfahrens ausgeschlossen.A turbine blade according to the invention has an armor applied by the method according to the invention. The armor is resilient and may have a height or thickness of several millimeters. Damage to the turbine material or the armor itself or a weakening of the turbine material or the armor by cracks when applying the armor is excluded by the application of the material-sparing method according to the invention.

Sonstige vorteilhafte Ausführungsbeispiele der vorliegenden Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the present invention are the subject of further subclaims.

Im Folgenden werden bevorzugte Ausführungsbeispiele der vorliegenden Erfindung anhand schematischer Darstellungen näher erläutert. Es zeigen:

  • Figur 1 eine Draufsicht auf ein Deckband einer Laufschaufel einer Strömungsmaschine,
  • Figur 2 einen Querschnitt durch einen Panzerungsbereich des Deckbandes, das mit einer ersten erfindungsgemäßen Panzerung versehen ist,
  • Figur 3 einen Querschnitt durch einen Panzerungsbereich des Deckbandes, das mit einer zweiten erfindungsgemäßen Panzerung versehen ist, und
  • Figur 4 einen Querschnitt durch einen Panzerungsbereich des Deckbandes, das mit einer dritten erfindungsgemäßen Panzerung versehen ist.
In the following, preferred embodiments of the present invention are explained in more detail with reference to schematic representations. Show it:
  • FIG. 1 a top view of a shroud of a blade of a turbomachine,
  • FIG. 2 a cross section through an armor region of the shroud, which is provided with a first armor according to the invention,
  • FIG. 3 a cross section through an armor region of the shroud, which is provided with a second armor according to the invention, and
  • FIG. 4 a cross section through an armor region of the shroud, which is provided with a third armor according to the invention.

Figur 1. zeigt eine Draufsicht auf ein blattspitzenseitiges Deckband 2 einer Laufschaufel einer Strömungsmaschine, insbesondere einer Gasturbine. Das Deckband 2 besteht aus einer hochfesten und hochtemperaturbeständigen Titanaluminid-Legierung (TiAl-Legierung). Es hat im Wesentlichen eine plattenartige Gestalt mit zwei voneinander beabstandeten sich in Rotationsrichtung erstreckenden außenliegenden Dichtlippen bzw. Dichtstegen 6, 8 zur Minimierung von Strömungsverlusten und mit zwei Z-förmigen Seitenflächen 10, 12. Die Z-formigen Seitenflächen 10, 12 definieren jeweils einen Seitenspalt zu einem Deckband einer benachbarten Laufschaufel und weisen jeweils eine plane Kontaktfläche 14, 16 zur gegenseitigen Abstützung mit der benachbarten Laufschaufel zur Schwingungsdämpfung auf. Zur Reduzierung eines mechanischen Abriebs sind die Kontaktflächen 14, 16 jeweils mit einer Panzerung 18,20 versehen. FIG. 1 , shows a plan view of a blade tip side shroud 2 a blade of a turbomachine, in particular a gas turbine. The shroud 2 consists of a high-strength and high temperature resistant titanium aluminide alloy (TiAl alloy). It has a substantially plate-like shape with two spaced-apart, rotationally extending outer sealing lips or sealing webs 6, 8 for minimizing flow losses and with two Z-shaped side surfaces 10, 12. The Z-shaped side surfaces 10, 12 each define a side gap to a shroud of an adjacent blade and each have a planar contact surface 14, 16 for mutual support with the adjacent blade for vibration damping. To reduce mechanical abrasion, the contact surfaces 14, 16 each provided with an armor 18,20.

Gemäß Figur 2, die ein erstes erfindungsgemäßes Ausführungsbeispiel der Erfindung zeigt, weist die Panzerung 18 bzw. 20 einen etwa quaderartiger Körper 22 auf. Der Körper bzw. Chip 22 besteht vorzugsweise aus einer Co-Cr-Legierung, beispielsweise Stellit® 694, und hat einen rechteckigen Querschnitt mit einer der Kontaktfläche 14 bzw. 16 des Deckbandes 2 zugewandten planen Grundfläche 24.According to FIG. 2 showing a first embodiment of the invention according to the invention, the armor 18 and 20, an approximately cuboidal body 22 on. The body or chip 22 is preferably made of a Co-Cr alloy, for example Stellit® 694, and has a rectangular cross-section with a plane base surface 24 facing the contact surface 14 or 16 of the shroud 2.

Zum Versehen der Kontaktfläche 14 mit der Panzerung 18 wird die Kontaktfläche 14 entsprechend auf Untertnaß gefertigt. Der Körper 22 wird getrennt von dem Deckband 2 hergestellt, beispielsweise gegossen oder gesintert. Er hat eine Höhe, die einer Soll-Höhe der Panzerung 18 entspricht. Die Breite der Grundfläche 24 entspricht vorzugsweise einer Breite der Kontaktfläche 14.To provide the contact surface 14 with the armor 18, the contact surface 14 is made according to Untertnaß. The body 22 is made separately from the shroud 2, for example cast or sintered. He has a height that corresponds to a target height of the armor 18. The width of the base surface 24 preferably corresponds to a width of the contact surface 14.

Nach dem Fertigen des Körpers 22 wird dieser über seine Grundfläche 24 an der Kontaktfläche 14 fixiert und anschließend unter Bildung einer großflächigen Lotschicht 26 mit dieser verlötet. Die Verlötung erfolgt induktiv beispielsweise in einem Hochvakuumofen oder unter Schutzgas bei einer Temperatur im Bereich von etwa 1050°C unter Verwendung des Nickelbasislotes AMS 4777, welches sich durch eine gleichmäßige Benetzung der Stellite-Kontaktfläche 24 und der TiAI-Bauteilfläche 14 auszeichnet.After the body 22 has been fabricated, it is fixed on its contact surface 14 via its base 24 and then soldered to it with the formation of a large-area solder layer 26. The soldering is carried out inductively, for example in a high vacuum oven or under inert gas at a temperature in the range of about 1050 ° C using the nickel-based solder AMS 4777, which is characterized by a uniform wetting of the Stellite contact surface 24 and the TiAI component surface 14.

Nach dem Verlöten des Körpers 22 mit dem Deckband 2 wird die Panzerung 18 mechanisch auf Endmaß gefertigt. Da bereits der Körper 22 eine der Kontaktfläche 14 entsprechende Breite aufweist und darüber hinaus die Gesamthöhe des Körpers 22 der Soll-Höhe der Panzerung 18 entspricht, ist eine Bearbeitung auf Endmaß, beispielsweise durch Schleifen, lediglich insofern notwendig, als das der Körper 22 hinsichtlich seiner Tiefe auf eine Tiefe der Kontaktfläche 14 einzustellen ist. Selbstverständlich kann jedoch auch der Körper 22 mit Übermaßen zum Ausgleich von Bauteil- und Montagetoleranzen ausgebildeten sein, so dass eine Bearbeitung auf Endmaß grundsätzlich auch bzgl. der Höhe und/oder der Breite der Panzerung 18 notwendig ist. Ebenso ist es selbstverständlich möglich, den Körper 22 bereits mit den Soll-Maßen der Panzerung in jeder Dimension zu versehen, so dass eine Endbearbeitung zur Einstellung der Soll-Maße gänzlich entfallen kann.After soldering the body 22 to the shroud 2, the armor 18 is mechanically machined to final gauge. Since the body 22 already has a width corresponding to the contact surface 14 and, moreover, the total height of the body 22 corresponds to the desired height of the armor 18, machining to final gauge, for example by grinding, is only necessary insofar as the body 22 is in terms of its Depth to a depth of the contact surface 14 is set. Of course, however, the body 22 may be formed with excess dimensions to compensate for component and assembly tolerances, so that a machining to final dimensions in principle also respect. The height and / or width of the armor 18 is necessary. Likewise, it is of course possible to provide the body 22 already with the desired dimensions of the armor in every dimension, so that a finish for setting the target dimensions can be completely eliminated.

Gemäß Figur 3, die ein zweites erfindungsgemäßes Ausführungsbeispiel der Panzerung 18 bzw. 20 zeigt, kann der Körper 22 auch über eine Zwischenschicht 28 mit der Kontaktfläche 14 bzw. 16 des Deckbands 2 verbunden sein. Die Zwischenschicht 28 ist zwischen der Kontaktfläche 14 und der Grundfläche 24 angeordnet und dient zur Verbesserung der Haftbedingungen des Körpers 22 an dem Deckband 2. Sie besteht vornehmlich aus einer Nickelbasislegierung bzw. Superlegierung wie INCONEL® 718 und ist als ein dünnen Blech oder einer Folie mit einer konstanten Materialstärke ausgeführt. Die Grundfläche 24 des Körpers 22 und die Zwischenschicht 28 haben jeweils eine der Kontaktfläche 14 entsprechende Geometrie, so dass ein maximaler Verbindungsbereich zwischen der Kontaktfläche 14 und der Zwischenschicht 28 sowie zwischen der Zwischenschicht 28 und der Grundfläche 24 geschaffen ist.According to FIG. 3 showing a second inventive embodiment of the armor 18 and 20, the body 22 may also be connected via an intermediate layer 28 with the contact surface 14 and 16 of the shroud 2. The intermediate layer 28 is disposed between the contact surface 14 and the base 24 and serves to improve the adhesion conditions of the body 22 on the shroud 2. It consists primarily of a nickel-based alloy or superalloy such as INCONEL® 718 and is as a thin sheet or a foil with a constant material thickness. The base 24 of the body 22 and the intermediate layer 28 each have a geometry corresponding to the contact surface 14, so that a maximum connection region between the contact surface 14 and the intermediate layer 28 and between the intermediate layer 28 and the base 24 is provided.

Zum Versehen der Kontaktfläche 14 mit der Panzerung 22 wird die Kontaktfläche 14 entsprechend auf Untermaß gefertigt. Der Körper 22 wird getrennt von dem Deckband 2 hergestellt und die Zwischenschicht 28 wird bereitgestellt. Die Höhe des Körpers 22 entspricht der Soll-Höhe der Panzerung 18 reduziert um die Dicke der Zwischenschicht 28. Die Breite der Grundfläche 24 entspricht vorzugsweise der Breite der Kontaktfläche 14. Die Zwischenschicht 28 hat vornehmlich ebenfalls eine Breite, die der Kontaktflächenbreite entspricht.To provide the contact surface 14 with the armor 22, the contact surface 14 is made according to undersize. The body 22 is manufactured separately from the shroud 2 and the intermediate layer 28 is provided. The height of the body 22 corresponds to the desired height of the armor 18 reduced by the thickness of the intermediate layer 28. The width of the base 24 preferably corresponds to the width of the contact surface 14. The intermediate layer 28 also has a width, which corresponds to the contact surface width.

Dann wird die Zwischenschicht 28 mit der Grundfläche 24 verlötet, so dass eine großflächige Lotschicht 30 gebildet wird. Dies erfolgt bei circa 1050°C. Ein bevorzugtes Lot ist ein Nickelbasislot wie AMS 4777, da dies sowohl TiAl-Werkstoffe als auch Stellite® gleichmäßig benetzt.Then, the intermediate layer 28 is soldered to the base 24, so that a large-area solder layer 30 is formed. This takes place at about 1050 ° C. A preferred solder is a nickel-based solder such as AMS 4777, since this evenly wets both TiAl materials and Stellite®.

Nach dem Auftragen der Zwischenschicht 28 auf die Grundfläche 24 wird der Körper 22 mittelbar über die Zwischenschicht 28 an der Kontaktfläche 14 fixiert. Anschließend wird die Zwischenschicht 28 mit der Kontaktfläche 14 unter Bildung einer großflächigen Lotschicht 32 verlötet. Dies erfolgt bei einer Temperatur, die kleiner ist als die Temperatur zum Verlöten der Zwischenschicht 28 mit dem Körper 22. Vorzugsweise wird eine Temperatur im Bereich von kleiner oder gleich 900°C gewählt. Ein bevorzugtes Lot ist nickelbasiert und weist einen hohen Edelmetallanteil von beispielsweise Gold, Silber oder Palladium auf. Beispiele sind Gapasil® 9, Palcusil® 10 und Palnisi® 10.After the application of the intermediate layer 28 to the base 24, the body 22 is fixed indirectly via the intermediate layer 28 on the contact surface 14. Subsequently, the intermediate layer 28 is soldered to the contact surface 14 to form a large-area solder layer 32. This is done at a temperature less than the temperature for brazing the intermediate layer 28 to the body 22. Preferably, a temperature in the range of less than or equal to 900 ° C is selected. A preferred solder is nickel-based and has a high noble metal content of, for example, gold, silver or palladium. Examples are Gapasil® 9, Palcusil® 10 and Palnisi® 10.

Nach dem Verlöten des Körpers 22 bzw. der Zwischenschicht 28 mit dem Deckband 2 wird die Panzerung 18 mechanisch auf Endmaß gefertigt. Da bereits der Körper 22 und die Zwischenschicht 28 eine der Kontaktfläche 14 entsprechende Breite aufweisen und darüber hinaus die Gesamthöhe des Körpers 22 mit der Zwischenschicht28 der Soll-Höhe der Panzerung 18 entspricht, ist eine Bearbeitung der Panzerung 18 auf Endmaß lediglich bezüglicher einer Dimension, hier die Tiefe, notwendig. Selbstverständlich können jedoch auch der Körper 22 sowie die Zwischenschicht 28 mit Übermaßen zum Ausgleich von Bauteil- und Montagetoleranzen ausgebildeten sein, so dass eine Bearbeitung auf Endmaß grundsätzlich auch bzgl. der Höhe und/oder der Breite der Panzerung 22 notwendig ist.After soldering the body 22 or the intermediate layer 28 with the shroud 2, the armor 18 is mechanically manufactured to final dimensions. Since the body 22 and the intermediate layer 28 already have a width corresponding to the contact surface 14 and, moreover, the total height of the body 22 with the intermediate layer 28 corresponds to the desired height of the armor 18, processing of the armor 18 to its final dimension is only with regard to one dimension, here the depth, necessary. Of course, however, the body 22 and the intermediate layer 28 may be formed with excess dimensions to compensate for component and assembly tolerances, so that a machining to final dimensions in principle also respect. The height and / or width of the armor 22 is necessary.

Gemäß dem in Figur 4 gezeigten dritten Ausführungsbeispiel der Panzerung 18 bzw. 20 kann der Körper 22 auch umfangsseitig mit einer Nickelschicht 34 beschichtet sein, wobei dann die auf der Grundfläche 24 angeordnete Nickelschicht quasi als Zwischenschicht zur Verbesserung der Haftbedingungen dient. Die Geometrie der Körpergrundfläche 24 entspricht der Geometrie der Kontaktfläche 14 bzw. 16. Seine Höhe entspricht der Soll-Höhe der Panzerung 18.According to the in FIG. 4 shown third embodiment of the armor 18 and 20, the body 22 may be circumferentially coated with a nickel layer 34, in which case the arranged on the base 24 nickel layer serves as an intermediate layer to improve the conditions of adhesion. The geometry of the body base 24 corresponds to the geometry of the contact surface 14 or 16. Its height corresponds to the desired height of the armor 18th

Zum Versehen jeweils der Kontaktfläche 14 mit der Panzerung 18 wird die Kontaktfläche 14 jeweils entsprechend auf Untermaß gefertigt. Der Körper 22 wird getrennt von den Deckband 2 hergestellt und umfangsseitig vernickelt. Da aufgrund der Vernickelung eine nachträgliche Bearbeitung der Panzerung 18 auf ihre Soll-Maße nicht möglich ist, weist der Körper 22 bereits vor der Vernickelung die Soll-Maße der Panzerung 18 auf, d.h. der Körper 22 hat vor der Vernickelung eine Höhe, die der Soll-Höhe der Panzerung 18 entspricht und seine Grundfläche 24 entspricht sowohl bzgl. ihrer Breite als auch ihrer Tiefe der Breite bzw. Tiefe der Kontaktfläche 14. Nach dem Vernickeln wird der Körper 22 mit seiner vernickelten Grundfläche 24 an der Kontaktfläche 14 fixiert und bei einer Temperatur von etwa 900°C mit dieser über eine Lotschicht 36 verlötet.To provide each of the contact surface 14 with the armor 18, the contact surface 14 is respectively made according to undersize. The body 22 is separated from the shroud 2 manufactured and nickel-plated on the circumference. Since a subsequent processing of the armor 18 due to the nickel plating is not possible to their desired dimensions, the body 22 before the nickel plating, the target dimensions of the armor 18, ie, the body 22 has a height before the nickel plating, the target Height of the armor corresponds to 18 and its base 24 corresponds both in terms of their width and their depth of the width or depth of the contact surface 14. After nickeling, the body 22 is fixed with its nickel-plated base 24 at the contact surface 14 and at a temperature from about 900 ° C with this soldered over a solder layer 36.

Offenbart ist Verfahren zur Panzerung einer metallischen Bauteilfläche aus einer TiAl-Legierung, mit zumindest einem metallischen Werkstoff aus einer Co-Cr-Legierung, wobei die Panzerung getrennt von der Bauteilfläche hergestellt wird und anschließend in einem Hochtemperaturlötverfahren an dieser gefügt wird, sowie eine Turbinenschaufel mit einer derartigen Panzerung, vornehmlich in einem Deckbandbereich.Disclosed is a method for armoring a metallic component surface of a TiAl alloy, with at least one metallic material of a Co-Cr alloy, wherein the armor is made separately from the component surface and then joined in a Hochtemperaturlötverfahren to this, and a turbine blade with Such armor, especially in a shroud area.

Claims (7)

  1. Method to provide a metallic component surface (14, 16), in particular a cover band surface of a turbine blade, with a coating (18, 20) made from a Co-Cr alloy, having the steps:
    - producing the component surface (14, 16) to be undersized,
    - producing a body (22) consisting of the Co-Cr alloy,
    - fixing the body (22) to the component surface (14, 16), and
    - joining the body (22) to the component surface (14, 16) by means of high-temperature brazing,
    characterised in that
    an intermediate layer (28) made from a different material, in particular Inconel® 718 or nickel, is firstly applied to the body (22), wherein the intermediate layer (28) increases the adhesion of the body to the component surface (14, 16), and then the intermediate layer (28) is joined to the component surface (14, 16) made from TiAl, wherein the brazing temperature to join the intermediate layer (28) to the component surface is less than or equal to 900°C.
  2. Method according to claim 1, wherein the body (22) has at least two dimensions before the joining, said dimensions corresponding to two target dimensions of the coating (18, 20).
  3. Method according to claim 2, wherein the body (22) is processed to final dimensions with regard to its width and/or depth after the brazing.
  4. Method according to one of the preceding claims, wherein the intermediate layer (28) is joined to the body (22) at a brazing temperature which is greater than a brazing temperature to join the intermediate layer (28) to the component surface (14, 16).
  5. Method according to claim 4, wherein the brazing temperature to apply the intermediate layer (28) amounts to approx. 1050 °C.
  6. Method according to claim 5, wherein solders based on nickel and having a high proportion of precious metal, for example gold, silver and palladium, are used.
  7. Method according to one of claims 1 to 4, wherein the body (22) is nickel-plated peripherally before the joining with the component surface (14, 16).
EP10740509.4A 2009-07-22 2010-07-08 Method for coating of turbine blades Not-in-force EP2456957B1 (en)

Applications Claiming Priority (2)

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DE102009034168 2009-07-22
PCT/DE2010/000792 WO2011009430A1 (en) 2009-07-22 2010-07-08 Method for coating a turbine blade

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EP2456957B1 true EP2456957B1 (en) 2016-05-04

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EP3216554B1 (en) * 2016-03-09 2020-05-06 MTU Aero Engines GmbH Component with wear- resistant openings and depressions and method for producing the same
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US20120125980A1 (en) 2012-05-24
WO2011009430A1 (en) 2011-01-27
US8393528B2 (en) 2013-03-12
EP2456957A1 (en) 2012-05-30
ES2580227T3 (en) 2016-08-22
WO2011009430A9 (en) 2011-03-17

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