WO2014146997A1 - Procédé génératif servant en particulier à fabriquer un revêtement, dispositif servant à la mise en œuvre dudit procédé, revêtement et procédé de production de composant ainsi que composant - Google Patents

Procédé génératif servant en particulier à fabriquer un revêtement, dispositif servant à la mise en œuvre dudit procédé, revêtement et procédé de production de composant ainsi que composant Download PDF

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Publication number
WO2014146997A1
WO2014146997A1 PCT/EP2014/055235 EP2014055235W WO2014146997A1 WO 2014146997 A1 WO2014146997 A1 WO 2014146997A1 EP 2014055235 W EP2014055235 W EP 2014055235W WO 2014146997 A1 WO2014146997 A1 WO 2014146997A1
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WO
WIPO (PCT)
Prior art keywords
powder
layer
coating
component
last
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.)
Ceased
Application number
PCT/EP2014/055235
Other languages
German (de)
English (en)
Inventor
Bernd Burbaum
Torsten JOKISCH
Sebastian Piegert
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of WO2014146997A1 publication Critical patent/WO2014146997A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
    • 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 invention relates to a generative process, in particular for the production of a coating, to a device for carrying out the process and to a coating. Furthermore, the invention relates to a component manufacturing method and a component.
  • a rotor of a turbomachine for example a rotor of a gas turbine or steam turbine, has a rotor base body and several rotor bodies mounted on the rotor body
  • Blades Each blade has a blade root and an airfoil and a tip and is mounted with the blade foot ⁇ in a corresponding recess of the rotor body.
  • cooling is often insufficient, especially at the blade tip.
  • a temperature difference of about 100 ° Celsius is present. Since ⁇ forth occurs in the region of the blade tip by the thermal and mechanical stress, in particular by a so-called running-in mating sealing surfaces frequently wear on. Cracking on the blade tip is the result. So far, the worn and / or cracked region in the region of the blade tip was mechanically removed locally and restored by build-up welding with an additional material. However, this is very costly and time consuming. A longer life of a blade or blade tip is therefore desirable.
  • DE 103 19 494 A1 discloses a method for repairing a guide vane of a gas turbine, in which a damaged section is cut out of the guide vane to be repaired and a spare part for the cut-out section is produced by means of a rapid manufacturing process. is provided. The ⁇ Asked by the rapid manufacturing process fro spare part integrated into the vane to be repaired by welding or soldering.
  • a first object of the invention is therefore to specify a generative method with which the above-mentioned problem can be reduced or even avoided.
  • a second object is the disclosure of a device for carrying out the method.
  • a third object is to provide a coating wel ⁇ cher solves the above problem.
  • a fourth and a fifth object are to specify a component production method and a component which solves the above-mentioned problem.
  • the first object is achieved by specifying a generative method with the following steps:
  • the powder material mixture comprises at least a first powder and a second powder, wherein the An ⁇ part of the second powder continuously increases from the first layer to the last layer; and wherein the second powder has at least Verschlenfinbe ⁇ resistance and / or oxidation resistance and / or a low coefficient of thermal expansion with respect to high temperatures, so that change with increasing layer, the mechanical and / or thermal properties continuously;
  • the content of the second powder in the ers ⁇ th layer is 0%.
  • the second powder may be locally characterized by a high wear resistance and / or oxidation resistance and / or a low thermal expansion coefficient with respect to high temperatures. Since the proportion of the second powder in the powder material mixture was increased continuously with increasing number of layers, this means that the mechanical and / or thermal properties change continuously with increasing layer. This also means that the thermal expansion due to the higher temperature in, for example, the last layer is the same as the first layer, although this
  • the proportion of the first powder in the last layer is 0%.
  • the suitable properties of the second powder with respect to high temperatures are maximized.
  • the second object is achieved by specifying a device for carrying out the above method, wherein:
  • At least one first powder conveyor with a solidifiable powder is provided,
  • At least a second powder conveyor is provided with a solidifiable powder
  • the at least two powder conveyors can be controlled separately so that the at least two solidifiable powders can be mixed in any ratio.
  • the third object with the indication of a coating for the manufacture or repair of a component, in particular a flow combustion engine, comprising literallyin- is least one first layer having a first solidifiable Pul ⁇ verwerkstoffgemisch and a final layer having a last solidifiable powder material mixture, wherein the first between the and the last layer is provided with a defined number of further layers of solidifiable powder material mixtures.
  • the solidifiable powder material mixture consists of at least a first powder and a second powder, the proportion of the second powder continuously increasing from the first layer to the last layer, and wherein the second powder at least wear resistance and / or oxidation resistance and / or a low coefficient of thermal expansion with respect to high temperatures, so that with increasing layer, the mechanical and / or thermal properties change continuously and wherein the proportion of the second powder in the first layer is 0%.
  • a coating is created which, due to the different powder composition, has different coatings Areas has different properties. Due to a continuous increase of the second powder, the properties also do not change abruptly, but slowly merge or change continuously.
  • the coating is thus adapted for example to the different thermal expansion coefficients or ⁇ union to the expected temperature gradient. This means that the thermal expansion due to the higher temperature in, for example, the last layer is the same as on the first
  • the proportion of the first powder in the last layer is 0%.
  • the appropriate properties of the second powder are maximized with respect to high temperatures.
  • the coating is preferably produced by the above-mentioned generative process and / or the abovementioned device.
  • the coating is particularly easy to Herge ⁇ provides.
  • the third object with the specification of a component manufacturing process, particularly for repair of a component, comprising a base member and a top-called coating is characterized by the following steps ge ⁇ solves:
  • the component manufacturing process according to the invention now makes it possible to repair, for example, high-temperature-stressed components with a suitable coating.
  • the coating can be manufactured separately and be on / in-place at the place of the component to be repaired on / in.
  • an application to the new part is possible;
  • a blade can be cast without a tip and the tip made from a coating.
  • As ⁇ by a particularly temperature-resistant blade can be manufactured with a long life.
  • the joining preferably takes place by joining, in particular friction welding. But it can also be used any other welding / joining process.
  • abrasion occurs by the connection by friction welding of the coating and the base component.
  • the recontouring of the end component includes the post-processing of the abrasion by mechanical processing, in particular by turning or milling. This can be done very easily.
  • the coating is heat treated prior to bonding to the base member.
  • This can be, for example, a hot isostatic pressing (HIP process) in order to set the optimum mechanical properties and, if necessary, to eliminate hot cracks.
  • the final component is heat-treated, so that the structure gets the optimal properties.
  • a component which is repaired or manufactured according to the above component manufacturing ⁇ method may in particular be a component of a gas turbine, for example a blade.
  • the blade at its tip, which is formed by the last layer a large proportion of the second powder, which, for example, a thermal is highly resilient material.
  • the thermal expansion coefficient at the tip of the component or the coating can be adapted to the expected temperature gradients.
  • the second powder may also have other or additional properties.
  • the first powder similar or identical Mate ⁇ rialeigenschaften as the base component on. Is selected as Materi ⁇ aleigenschaft the heat expansion, so can be set by means of this combination that the thermal expansion due to the higher temperature at the final layer (tip) of the coating just as large as the first layer of the coating, although between the tip and ERS ⁇ th layer of the coating a large temperature gradient is sawn. This means a complete compensation of the thermomechanical stresses.
  • FIG. 2 shows a coating according to the invention and a base wing
  • FIG. 3 connecting the coating according to the invention to a base wing
  • the blade 1 shows a turbine blade 1 with a wing profile 3 according to the prior art.
  • This has a blade root 2.
  • the blade 1 comprises a tip 4, which has a crown 5 with an inner crown bottom 6 and an outer crown edge 7.
  • the turbine blade 1 kon ⁇ struiert for (not shown) within a housing animals ro-. It is important that the blade tip 4 precisely in the housing (not shown) fits around the outside to prevent flow of the combustion gases at the blade tip 4 as far as possible ⁇ continuously, as the bypass route these receiving gases no energy on the wing profile 3 of the blade 1 übertra ⁇ gen.
  • the blade 1 may have a thermal barrier coating at its tip. Nevertheless, one or more cracks 10 may occur in the crown 5 of the turbine bucket 1, due to material fatigue at low load cycles occurring during operation of the turbine and acting on the bucket tip 4. If a crack 10 exceeds a critical length, the turbine blade 1 must be taken out of service and / or repaired. So far, cracks 10, unless they exceed a critical length, have been laser-deposited, e.g. with the filler or by e.g. tungsten inert gas welding (TIG welding process) is repaired.
  • TIG welding process tungsten inert gas welding
  • the material on the crown base 6, that is to say at the transition from the airfoil 3 to the crown 5, should be approximately identical to the material of the airfoil 3, so that different coefficients of thermal expansion do not result in critical loads during the heating phase or cooling phase during operation
  • the turbine blade 1 leads loom ⁇ ren.
  • At the crown edge 7 of the tip 4 locally a large wear resistance and oxidation resistance gefor ⁇ changed, which can not be reconciled with the chemical / metallurgical composition tion of the airfoil 3.
  • the coating 35 comprises at least a first layer 21 with a first reinforced powder material mixture and a last layer 25 comprising a last consolidated powder material mixture, and between the first and the last layer 25 a defined number of further layers 22-24, wherein the number is not fixed here to three.
  • the number can be zero, of course; ie no further layer can be provided.
  • Layer 21 increases until the last layer 25. This can be a continuous steady To be ⁇ takeover with very fine layers 21-25.
  • the powder material mixture can also consist of several powders.
  • This first powder 100 is later or when applied to a first, solidified powder 100.
  • the powder 100 or solidified powder 100 is similar or identical to the material and / or has similar or moving ⁇ surface properties, such as the base wings 15. It is especially to be mentioned as similarity ⁇ Liche or same property of the thermal expansion coefficient from ⁇ .
  • the powder 100 is ⁇ example, on a mold 50 ( Figure 4) is applied and then solidified to form a first coating section 31st
  • the mold 50 (FIG. 4) may of course be the base wing 15 itself.
  • At least one second powder 200 is added to the first powder 100 to form a second powder material mixture.
  • a second layer 22 is generated wel ⁇ che subsequently with the first coating section 31 solidified to a new coating portion 32nd
  • the follow ⁇ the layers 23 and 24 are successively applied to the analog-made coating portions 32 and 33rd
  • the last layer 25 is therefore applied to a coating section 34.
  • the powder 200 now has properties which are required in particular for high temperatures. According to the invention, the proportion of powder 200 in the powder material mixture is increased as the number of layers increases. The last
  • Layer 25 so that layer which is particularly exposed to the hot Tempe ⁇ temperature directly by hot gas, con- sists essentially only from the powder 200, which is then solidified or during application.
  • the solidified powder 200 is later exposed directly to the hot gas or the hot temperatures.
  • the solidified powder 200 of the last layer 25 is, so to speak here later on alligator nenkante 7 shows.
  • the solidified powder 200 has now egg ⁇ properties which are Benö particular for high temperatures ⁇ Untitled. These are mainly wear resistance and oxidation resistance and a low coefficient of thermal expansion. Since the proportion of powder 200 in the powder material mixture has been increased continuously as the number of layers increases, this also means that the mechanical and / or thermal properties also change continuously as the layer increases.
  • the blade tip 4 is therefore made graduated.
  • the mixture of at least two powder 100 and powder 200 can by two separately controllable to ⁇ powder feeders 101 and 201 and a coaxial micro schungsdüse 70 carried (FIG 4).
  • the powder material mixture can be mixed in any ratio.
  • the mixture is introduced ⁇ a shape 50 (FIG 4) and solidified.
  • the last solidified powder 200 Since the last layer 25 is directly exposed to the hot gas or temperatures, the last solidified powder 200 also requires a low coefficient of thermal expansion than the layer 21 of the first solidified powder 100 and the base wing 15 in such a way that the cherriesaus ⁇ expansion at the last layer 25 is the same size as at the first layer 21. This, and the continuous change of mechanical and / or thermal properties with increasing layer ideally lead to a nearly fully ⁇ constant compensation of the thermal stresses in the operation of the blade 1 and reduced cracking.
  • the solidification of the layer can take place, for example, by welding.
  • This can be, for example, a build-up welding or laser sintering / laser melting by means of a heat source 60 (FIG. 4) or another generative production method.
  • the layers 21-25 are thus connected to one another in a material-locking manner and thereby ultimately form the desired coating 35.
  • the coating 35 is cut to fit the base blade 15, for example, the blank of the coating 35 may be a spare blade tip 30 (FIG. 3).
  • the coating 35 can be tailored to any other component, such as heat shields or other parts in the power plant ⁇ .
  • An application is also conceivable outside of power plant technology.
  • the replacement blade tip 30 (FIG. 3) can be heat treated, for example by hot isostatic pressing (HIP), to eliminate joining defects and to produce the optimum mechanical properties.
  • the replacement blade tip 30 (FIG. 3) is joined to the base blade 15 (FIG. 3) to form a replacement blade 41 (FIG. 3) 12.
  • the joining 12 can take place, for example, by means of friction welding (FIG. 3) or other known joining methods.
  • the resulting from the joining 12 abrasion or burrs or seams are remedied by a post-processing (re-contouring) by means of mechanical processing, such as milling or grinding.
  • the replacement blade 41 (FIG 3) are heat treated again.
  • the base blade 15 can be produced and continued as described above, or the complete blade 1 (FIG. 1) is graduated as described above.
  • other components such as burners, heat shields, etc. can be manufactured or repaired with the invention.
  • thermo-mechanical stress in the Be ⁇ drive it is possible to thermo-mechanical stress in the Be ⁇ drive to avoid or at least reduce at high temperature charge components. Cracking or degradation can thus be avoided. The components thus have a much longer life.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)

Abstract

L'invention concerne un procédé génératif servant en particulier à fabriquer un revêtement (35). Ledit procédé comprend les étapes suivantes consistant à : appliquer une première couche (21) d'un premier mélange de matières pulvérulentes et solidifier ladite première couche pour former une première section de revêtement (31) ; appliquer une deuxième couche (22) d'un deuxième mélange de matières pulvérulentes sur la première section de revêtement (31) fabriquée et solidifier ladite deuxième couche (22) pour former une nouvelle section de revêtement (32) ; appliquer de manière successive d'autres couches (23-24) composées de mélanges de matières pulvérulentes sur la nouvelle section de revêtement (32 - 33) respectivement fabriquée et solidifier de manière successive lesdites autres couches (23-24) pour former une nouvelle section de revêtement (33-34) respective jusqu'à obtenir une dernière couche (25) prédéterminée comprenant un dernier mélange de matières pulvérulentes et solidifier la dernière couche (25) pour obtenir un revêtement (35). La solidification est effectuée par un procédé de fusion par rayonnement, de préférence sous la forme d'un procédé de frittage au laser ou par bombardement électronique. Le mélange de matières pulvérulentes comprend au moins une première poudre (100) et une deuxième poudre (200), la fraction de la deuxième poudre (200) augmentant en continu de la première couche (21) à la dernière couche (25). La deuxième poudre est au moins résistante à l'usure et/ou à l'oxydation et/ou présente un coefficient de dilatation thermique faible par rapport à des températures élevées de sorte que les propriétés mécaniques et/ou thermiques varient en continu d'une couche à l'autre. La fraction de la deuxième poudre (200) dans le cas de la première couche (21) est de 0 %. L'invention concerne par ailleurs un dispositif servant à la mise en œuvre du procédé, un revêtement et un procédé de fabrication de composants ainsi qu'un composant.
PCT/EP2014/055235 2013-03-21 2014-03-17 Procédé génératif servant en particulier à fabriquer un revêtement, dispositif servant à la mise en œuvre dudit procédé, revêtement et procédé de production de composant ainsi que composant Ceased WO2014146997A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP13160283.1A EP2781622A1 (fr) 2013-03-21 2013-03-21 Procédé génératif, notamment de fabrication d'un revêtement, dispositif d'exécution du procédé, revêtement et procédé de fabrication de composant et composant
EP13160283.1 2013-03-21

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WO2014146997A1 true WO2014146997A1 (fr) 2014-09-25

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PCT/EP2014/055235 Ceased WO2014146997A1 (fr) 2013-03-21 2014-03-17 Procédé génératif servant en particulier à fabriquer un revêtement, dispositif servant à la mise en œuvre dudit procédé, revêtement et procédé de production de composant ainsi que composant

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WO (1) WO2014146997A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014221222A1 (de) * 2014-10-20 2016-04-21 MTU Aero Engines AG Pulverpatrone für ein Verfahren und eine Vorrichtung zur generativen Herstellung von Bauteilen sowie entsprechend hergestellte Bauteile
DE102017200749A1 (de) 2017-01-18 2018-07-19 Siemens Aktiengesellschaft Schichtsystem mit zwei Zwischenschichten und Verfahren
EP3933067A1 (fr) * 2020-07-03 2022-01-05 Flender GmbH Procédé de fabrication d'un revêtement, revêtement, composant doté d'un revêtement
US12129769B2 (en) 2022-10-25 2024-10-29 Ge Infrastructure Technology Llc Erosion-shielded turbine blades and methods of manufacturing the same
US12571311B2 (en) 2022-10-25 2026-03-10 General Electric Company Erosion-shielded turbine blades and methods of manufacturing the same

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993005194A1 (fr) * 1991-09-05 1993-03-18 Technalum Research, Inc. Procede de production de revetements a gradient de composition continu
EP1382707A1 (fr) * 2002-07-17 2004-01-21 Siemens Aktiengesellschaft Systeme stratifie
DE10319494A1 (de) * 2003-04-30 2004-11-18 Mtu Aero Engines Gmbh Verfahren zur Reparatur und/oder Modifikation von Bauteilen einer Gasturbine
EP1712657A2 (fr) * 2005-04-14 2006-10-18 United Technologies Corporation Methode de fabrication et dispositif pour fabriquer un materiauà gradient fonctionnel par pulvérisation à froid
DE102006019900A1 (de) * 2006-04-28 2007-11-08 Siemens Ag Piezoaktor mit Gradient-Verkapselungsschicht und Verfahren zu seiner Herstellung
WO2008009267A1 (fr) * 2006-07-19 2008-01-24 Mtu Aero Engines Gmbh Procédé de réparation d'aubes de turbine
DE102008058140A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zur Reparatur von einkristallinen Turbinenschaufeln
WO2011008143A1 (fr) * 2009-07-15 2011-01-20 Arcam Ab Procédé et appareil de production d’objets tridimensionnels
DE102011008809A1 (de) * 2011-01-19 2012-07-19 Mtu Aero Engines Gmbh Generativ hergestellte Turbinenschaufel sowie Vorrichtung und Verfahren zu ihrer Herstellung

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993005194A1 (fr) * 1991-09-05 1993-03-18 Technalum Research, Inc. Procede de production de revetements a gradient de composition continu
EP1382707A1 (fr) * 2002-07-17 2004-01-21 Siemens Aktiengesellschaft Systeme stratifie
DE10319494A1 (de) * 2003-04-30 2004-11-18 Mtu Aero Engines Gmbh Verfahren zur Reparatur und/oder Modifikation von Bauteilen einer Gasturbine
EP1712657A2 (fr) * 2005-04-14 2006-10-18 United Technologies Corporation Methode de fabrication et dispositif pour fabriquer un materiauà gradient fonctionnel par pulvérisation à froid
DE102006019900A1 (de) * 2006-04-28 2007-11-08 Siemens Ag Piezoaktor mit Gradient-Verkapselungsschicht und Verfahren zu seiner Herstellung
WO2008009267A1 (fr) * 2006-07-19 2008-01-24 Mtu Aero Engines Gmbh Procédé de réparation d'aubes de turbine
DE102008058140A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zur Reparatur von einkristallinen Turbinenschaufeln
WO2011008143A1 (fr) * 2009-07-15 2011-01-20 Arcam Ab Procédé et appareil de production d’objets tridimensionnels
DE102011008809A1 (de) * 2011-01-19 2012-07-19 Mtu Aero Engines Gmbh Generativ hergestellte Turbinenschaufel sowie Vorrichtung und Verfahren zu ihrer Herstellung

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