EP2456957B1 - Procédé pour le revêtement des aubes de turbines - Google Patents

Procédé pour le revêtement des aubes de turbines 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)
English (en)
Other versions
EP2456957A1 (fr
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 of EP2456957A1 publication Critical patent/EP2456957A1/fr
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Publication of EP2456957B1 publication Critical patent/EP2456957B1/fr
Not-in-force legal-status Critical Current
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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
    • F01D5/12—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.

Claims (7)

  1. Procédé d'équipement d'une surface de composant métallique (14, 16), plus particulièrement une surface de bande de recouvrement d'une pale de turbine, d'un revêtement (18, 20) constitué d'un alliage Co-Cr, comprenant les étapes suivantes ;
    - réalisatior de la surface de composant (14, 16) sur côte sous-dimensionnée,
    - réalisation d'un corps (22) constitué de l'alliage Co-Cr,
    - fixation du corps (22) sur la surface de composant (14, 16), et
    - assemblage du corps (22) avec la surface de composant (14, 16) au moyen d'un brasage à haute température,
    caractérisé en ce qu'
    une couche intermédiaire (28), constituée d'un autre matériau, plus particulièrement de l'Inconel® 718 ou du nickel, est d'abord rappliqué sur le corps (22), la couche intermédiaire (28) augmentant l'adhérence du corps à la surface de composant (14, 16), puis la couche intermédiaire (28) est assemblée avec La surface de composant (14, 16) en TiAl, la température de brassage pour 1'assemblage de la couche intermédiaire (28) avec la surface de composant étant inférieure ou égale à 900 °C.
  2. Procédé selon à revendications 1, le corps (22) présentant, avant l'assemblage, au moins deux dimensions, qui correspondant à deux dimensions de consigne du revêtement (18, 20).
  3. Procédé selon la revendication 2, le corps (22) étant usiné à ses dimensions finales, après le brasage, en ce qui concerne sa largeur et/ou sa profondeur.
  4. Procédé selon l'une des revendications précédentes, la couche intermédiaire (28) étant assemblée avec le corps (22) avec une température de brasage qui est supérieure à une température de brasage pour l'assemblage de la couche intermédiaire (28) avec la surface de composant (14, 16).
  5. Procédé selon la revendication 4, la température de brasage pour l'application de la couche intermédiaire (28) étant d'environ 1050 °C.
  6. Procédé selon la revendication 5, des soudures à base de nickel et avec une forte teneur en métaux nobles, par exemple de l'or, de l'argent et du palladium, sont utilisées.
  7. Procédé selon l'une des revendications 1 à 4, le corps (22) étant nickelé sur sa circonférence avant l'assemblage avec la surface de composant (14, 16).
EP10740509.4A 2009-07-22 2010-07-08 Procédé pour le revêtement des aubes de turbines Not-in-force EP2456957B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009034168 2009-07-22
PCT/DE2010/000792 WO2011009430A1 (fr) 2009-07-22 2010-07-08 Procédé de revêtement d'une aube de turbine

Publications (2)

Publication Number Publication Date
EP2456957A1 EP2456957A1 (fr) 2012-05-30
EP2456957B1 true EP2456957B1 (fr) 2016-05-04

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP10740509.4A Not-in-force EP2456957B1 (fr) 2009-07-22 2010-07-08 Procédé pour le revêtement des aubes de turbines

Country Status (4)

Country Link
US (1) US8393528B2 (fr)
EP (1) EP2456957B1 (fr)
ES (1) ES2580227T3 (fr)
WO (1) WO2011009430A1 (fr)

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Publication number Priority date Publication date Assignee Title
DE102011086524A1 (de) * 2011-11-17 2013-05-23 Mtu Aero Engines Gmbh Panzerung von Dichtfins von TiAl-Schaufeln durch induktives Auftragslöten von Hartstoffpartikeln
DE102011087158A1 (de) 2011-11-25 2013-05-29 Mtu Aero Engines Gmbh Verfahren zur Panzerung der Z-Notch von TiAl-Schaufeln
US20130202439A1 (en) * 2012-02-08 2013-08-08 General Electric Company Rotating assembly for a turbine assembly
US9862029B2 (en) 2013-03-15 2018-01-09 Kennametal Inc Methods of making metal matrix composite and alloy articles
US9346101B2 (en) 2013-03-15 2016-05-24 Kennametal Inc. Cladded articles and methods of making the same
US9849533B2 (en) 2013-05-30 2017-12-26 General Electric Company Hybrid diffusion-brazing process and hybrid diffusion-brazed article
DE102013216393A1 (de) 2013-08-19 2015-03-12 MTU Aero Engines AG Intermetallische Verschleißschutzschicht für Titan-Werkstoffe
DE102014224156A1 (de) 2014-11-26 2016-06-02 MTU Aero Engines AG Lötverfahren zur Panzerung der Z-Notch von TIAL-Schaufeln
EP3216554B1 (fr) * 2016-03-09 2020-05-06 MTU Aero Engines GmbH Composant comprenant des ouvertures et des evidements proteges contre l'usure et son procede de fabrication
US11117208B2 (en) 2017-03-21 2021-09-14 Kennametal Inc. Imparting wear resistance to superalloy articles
GB2568063B (en) 2017-11-02 2019-10-30 Hardide Plc Water droplet erosion resistant coatings for turbine blades and other components
FR3084399B1 (fr) * 2018-07-24 2021-05-14 Safran Aircraft Engines Aube mobile pour une roue d'une turbomachine
CN109352197A (zh) * 2018-11-18 2019-02-19 湖南新融创科技有限公司 一种手机组装生产用焊接装置

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US5198308A (en) 1990-12-21 1993-03-30 Zimmer, Inc. Titanium porous surface bonded to a cobalt-based alloy substrate in an orthopaedic implant device
FR2746043B1 (fr) * 1996-03-14 1998-04-17 Soc Nat Detude Et De Construction De Moteurs Daviation Snecma Procede de realisation d'un apport sur une zone localisee de piece en superalliage
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Also Published As

Publication number Publication date
US20120125980A1 (en) 2012-05-24
US8393528B2 (en) 2013-03-12
WO2011009430A9 (fr) 2011-03-17
EP2456957A1 (fr) 2012-05-30
WO2011009430A1 (fr) 2011-01-27
ES2580227T3 (es) 2016-08-22

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