WO2011000348A1 - Revêtement et procédé de revêtement d’un élément - Google Patents

Revêtement et procédé de revêtement d’un élément Download PDF

Info

Publication number
WO2011000348A1
WO2011000348A1 PCT/DE2010/000708 DE2010000708W WO2011000348A1 WO 2011000348 A1 WO2011000348 A1 WO 2011000348A1 DE 2010000708 W DE2010000708 W DE 2010000708W WO 2011000348 A1 WO2011000348 A1 WO 2011000348A1
Authority
WO
WIPO (PCT)
Prior art keywords
coating
layer
solder
matrix material
particles
Prior art date
Application number
PCT/DE2010/000708
Other languages
German (de)
English (en)
Inventor
Maik Zeugner
Jürgen RÖSING
Frank Seidel
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 WO2011000348A1 publication Critical patent/WO2011000348A1/fr

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2203/00—Non-metallic inorganic materials
    • F05C2203/08—Ceramics; Oxides
    • F05C2203/0804—Non-oxide ceramics
    • F05C2203/083—Nitrides
    • F05C2203/0839—Nitrides of boron
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2283—Nitrides of silicon

Definitions

  • the present invention relates to a coating for or on a component, in particular for or on a blade for a turbomachine, and to a method for coating a component.
  • Axial compressors and gas turbines such as used in gas turbine engines for aircraft or other mobile or stationary applications, typically include multiple stages with rotating blades and fixed vanes or stator vanes.
  • the rotor blades are rigidly connected to a rotor and rotate with it at high speed about an axis.
  • An essential feature of axial compressors and gas turbines are the pressure differences existing between the upstream side and the downstream side of each blade ring. Any pressure loss at the outer edge of a rotor blade ring or at the inner edge of a stator blade ring reduces the efficiency.
  • a sealing fin on the rotating component engages in a groove on the stationary component or vice versa.
  • EP 0 270 785 A2 discloses a coating of a blade tip with a mixture of powders of two MCrAlY alloys with different melting points. The coating is heated to a temperature above the melting temperature of one and below the melting temperature of the other MCrAlY alloy.
  • a blade tip armor with a metallic adhesive layer and a metallic cover layer is known.
  • the metallic cover layer has abrasive particles embedded in a metallic matrix material.
  • the metallic adhesive layer and the metallic matrix material are each formed from an MCrA-IY material.
  • a method for connecting an abrasive layer with a blade tip of a gas turbine is known.
  • the abrasive layer contains alumina particles coated with a thin layer of reactive material.
  • WO 2008/135803 A1 discloses a method for coating a rotor blade tip of a gas turbine, in which first a layer of a powder of an alloy having a high melting point and abrasive particles and then a layer of a powder of an alloy having a low melting point are applied , Both are then heated to a temperature above the low and below the high melting temperature.
  • US Pat. No. 7,063,250 B2 discloses a solder coating and a method for producing a blade tip armor.
  • the solder coating comprises a metallic solder layer, which has been added with boron, and a layer of material applied thereto, which contains CBN abrasive particles embedded in a binder and MCrAlY particles.
  • This layer formation is applied in the form of an adhesive tape to the blade tip and heated together with the rotor blade in a vacuum oven to about 600 ° C until the binder of the material layer has volatilized. Subsequently, the furnace is heated above the melting temperature of the solder (about 1000 ° C), and the liquefied solder penetrates into the material layer.
  • the boron of the solder layer diffuses into the MCrAlY particles and lowers their melting temperature.
  • the MCrAlY particles are thereby melted into a Condition convoluted, allowing a mixture of MCrAlY alloy with the already liquid solder.
  • a solid layer of CBN abrasive particles embedded in an MCrAlY matrix is formed. With the heating of the blade tip, however, there is still the risk of melting or crystallizing of the blade tip material.
  • the matrix material is a material suitable for embedding the coated hard material particles, in particular a material which also has a corrosion protection at high temperatures, for example an MCrAlY alloy.
  • the coated hard material particles can be embedded in the pure matrix material, or else in a mixture of the matrix material and another material, for example a solder. In the case of embedding the coated hard material particles in a mixture of the matrix material and the solder, this mixture may be a homogeneous or single-phase mixture or a heterogeneous or multiphase mixture.
  • the matrix material is in the form of particles or of a powder which is embedded in the solder, with essential properties, such as the corrosion protection, being determined by the matrix material. In this case, components of the mat Rixmaterials be diffused into the solder and / or components of the solder in the matrix material.
  • the coating of the individual hard material particles is in particular selected and designed to facilitate a cohesive connection of the hard material particles with the matrix material.
  • the hard-material particles are coated, for example, with a material which reacts chemically with the matrix material and / or, if appropriate, with a solder used for the coating, which is chemically similar to the matrix material or, if appropriate, to the solder or which, although not provided with the matrix material or If necessary, it reacts chemically with the solder, but due to its chemical and physical properties it is wetted by the matrix material or, if appropriate, by the solder.
  • the coating of the hard material particles has, for example, at least one of Ti, Cr, Hf, another reactive element, Ni, Co, Al or Fe.
  • the coating may comprise exclusively or almost exclusively one or more of the named elements, the sum of the mass fractions of further elements being less than 10% or less than 5% or less than 1%.
  • the coating comprises an alloy with one or more of said elements as main alloy components, wherein in particular the mass fractions of all further elements or even the sum of the mass fractions of all further elements are smaller than the mass fractions of the main alloy components.
  • the coating has, for example, a thickness of at most 50 ⁇ m or at most 20 ⁇ m or at most 10 ⁇ m.
  • a coating is advantageous whose mass is not greater than that of the uncoated hard material particle.
  • CVD chemical vapor deposition
  • PVD physical vapor deposition
  • galvanically on the hard material particles galvanically on the hard material particles.
  • One advantage of this coating is that the excellent properties of cubic boron nitride, silicon nitride, and silicon aluminum oxynitride, which have been proven by the Applicant to be used on blades of turbomachinery in particular as hard material particles can now be combined with a fixed integration into the matrix material.
  • the coating of the hard material particles improves their incorporation into the material structure of the coating, in particular into the matrix material and / or the solder.
  • the coated hard material particles of cubic boron nitride, silicon nitride or silicium aluminum oxynitride can be embedded or embedded in a layer which, apart from the coated hard material particles, essentially consists only of the solid matrix material, for example an MCrAlY alloy.
  • the matrix material is originally present as a powder, which is mixed with the hard material particles at least on the surface of the coating.
  • a solder For bonding the layer of the powder of the matrix material and the hard material particles, a solder can be used which wets the powder particles of the matrix material and the coated hard material particles at least after the application of the coating to the component and a corresponding thermal treatment, and the open-pore structure of the particles completely penetrates, so that the powder particles of the matrix material and the hard particles are embedded in the finished coating in the solder.
  • a solder wets the powder particles of the matrix material and the coated hard material particles at least after the application of the coating to the component and a corresponding thermal treatment, and the open-pore structure of the particles completely penetrates, so that the powder particles of the matrix material and the hard particles are embedded in the finished coating in the solder.
  • the coating may comprise a solder for the material-locking connection of the matrix material to the component or a surface of the component.
  • the solder is in particular a cobalt base solder having a cobalt mass fraction of at least 30% or at least 40%, preferably with a cobalt mass fraction of between 50% and 60%, in particular 55.6%.
  • the composition of the solder it is advantageous for many applications. liable if the solidus temperature of the solder is below the solidus temperatures of the matrix material and the hard material particles.
  • the matrix material and the solder can be chosen such that at a predetermined temperature above the solidus temperature of the solder and below the solidus temperature of the matrix material at least either constituents of the matrix material (28) into the solder (23) or constituents of the solder (23) into the solder Diffuse matrix material (28). This can go to a breakdown of matrix material and material of the solder and to form a new alloy. As a result, the material properties of the solder and the material-o-positive connection between the solder and the powder particles of the matrix material can be further improved.
  • the matrix material has, for example, the following mass fractions: 22% ⁇ 5% (in particular approx. 22.5%) Cr; 10% ⁇ 2% (especially about 10%) Al; 0.5% to 1.5% Y. Remaining mass fractions can be formed by any metals or even non-metals, in the case of the matrix material, in particular Ni.
  • the coating may comprise a layer structure having a first layer and a second layer, wherein the first layer comprises the solder, and wherein the second layer comprises the matrix material or the matrix material and the hard material particles.
  • the layer structure may further comprise a third layer whose composition is different from the compositions of the first layer and the second layer and which is disposed between the first layer and the second layer.
  • the third layer and / or a fourth or fifth or further layer each have a mixture of solder and a matrix material or a mixture of a solder, a matrix material and a hard material (in particular in particle form).
  • alloys other than solder, matrix material or hard material may be present in the third, fourth, fifth or further layer, for example.
  • positive properties can be achieved with respect to segregation effects.
  • the setting of an optimized thermal expansion system is possible.
  • the coating may also have a predetermined variation in composition continuous in the direction of its thickness.
  • the coating may alternatively or additionally comprise a predetermined predetermined variation of the composition in the lateral direction or in the direction parallel to the coating and perpendicular to the direction of the thickness of the coating.
  • a lateral variation in composition allows for lateral variation of the abrasive properties or other properties of the coating.
  • the proportion of the solder decreases from the side facing the component to the side facing away from the component, the proportion of the hard material particles increases in the same direction and the proportion of the matrix material has a maximum in between.
  • Such continuous variation of the composition enables a particularly strong structure with a particularly low risk of detachment of individual layers.
  • the coating may have the properties described above both before application to the component (for example in the form of a tape, in particular adhesive tape, or a film, in particular adhesive film) as well as after application or after a thermal
  • the present invention further includes a blade for a turbomachine having one of the above-described coatings on one blade tip (which may be a squealer surface) and / or on another squealer surface.
  • the coating can act there in particular as wear protection.
  • a matrix material and hard material particles containing and coated at least either cubic boron nitride or silicon nitride or silicon aluminum oxynitride are applied to the component and by local heating of the blade tip the matrix material and the hard particles with the component joined materially or connected.
  • the local heating or heating of the blade tip takes place, for example, by ohmic losses of inductively induced eddy current fields.
  • the cohesive joining comprises, for example, a melting of a solder, a wetting of at least the component and the matrix material, optionally also the coated hard material particles, by the solder and a solidification of the solder.
  • a melting of a solder a wetting of at least the component and the matrix material, optionally also the coated hard material particles, by the solder and a solidification of the solder.
  • a partial or complete homogenization with regard to the composition can take place.
  • one or more new alloys can arise, which have different solids and / or liquidus temperatures.
  • the isothermal solidification of the system of solder and matrix material is possible.
  • the application of the matrix material and the hard material particles may include applying a tape, a wire, a foam or a film with the matrix material to the hard particles and optionally the solder.
  • both the matrix material and the optional solder are in each case in a solid state of aggregation, for example as a powder or in the form of a band, a wire, a foam, a film or another semifinished product.
  • the concentrations of the matrix material, the hard material particles and optionally the solder in the direction of the thickness of the coating can vary continuously.
  • the coating may comprise a layered structure having a first layer, a second layer, and optionally a third layer.
  • the first layer may optionally comprise the solder
  • the second layer may comprise the hard material particles
  • the third layer may be arranged between the first layer and the second layer and have a different composition than the first layer and the second layer.
  • the coating or parts of the coating described-in particular individual layers- can be applied by thermal spraying, painting, printing or other means.
  • one of the coatings described above can be applied using the described method.
  • Figure 1 is a schematic representation of a cross section of a component and a coating to be applied to the component;
  • Figure 2 is a schematic representation of a cross section of a coated hard particle
  • Figure 3 is a schematic representation of a cross section of a further coating
  • Figure 4 is a schematic representation of a cross section of a further coating
  • Figure 5 is a schematic flow diagram of a method for coating a
  • FIG. 1 shows a schematic illustration of a cross section of a component 10 with a surface 12 to be coated and a coating 20 present here in the form of a film and to be applied to the surface 12 of the component 10 to be coated.
  • the illustrated sectional plane lies - as in FIGS and 4 - vertical or in Substantially perpendicular to the surface to be coated 12 and parallel to the normal to the plane of the largest extent of the coating 20.
  • the coating 20 is spaced from the surface to be coated 12 and thus in an arrangement immediately prior to applying the coating 20 to the surface to be coated 12 is shown.
  • the component 10 is in particular a blade of a turbomachine or for a turbomachine. Shown in Figure 1 is primarily the blade tip of the blade.
  • the reference numeral 10 denotes insofar is especially the blade tip.
  • the coating 20 has an adhesive layer 21 which faces the surface 12 to be coated.
  • the adhesive layer 21 comprises, for example, an organic adhesive.
  • the coating 20 can first be stapled to the surface 12 to be coated.
  • the adhesive layer 21 is designed such that it disappears without residue or substantially without residue in a subsequent thermal treatment.
  • the coating 20 further comprises a solder layer 22 with solder particles 23 in a matrix of an organic binder 24.
  • the binder 24 of the solder layer 22 is similar to the adhesive layer 21 formed to disappear in a subsequent thermal treatment without residue or substantially residue-free.
  • the illustrated embodiment of the solder layer 22 in the form of solder particles 23 in a matrix of a binder 24 has a high elastic and especially plastic deformability and other manufacturing advantages.
  • the solder layer 22 is a layer of solid solder without a binder.
  • the coating 20 further comprises a functional layer 26 with a, in particular organic, binder 27.
  • a functional layer 26 with a, in particular organic, binder 27.
  • the binder 27 are embedded MCrAlY particles 28 and hard material particles 30 containing at least either cubic boron nitride or silicon nitride or silicon aluminum mini oxynitride.
  • the binder 27 of the functional layer 26 is in particular designed to be free of residue or in a subsequent thermal treatment. considerably disappear without leaving a trace.
  • the functional layer 26 deviating from the illustration in Figure 1, no binder 27, instead, the MCrAlY alloy is solid and contains embedded Hartstofrpumble 30.
  • the functional layer 26 - in the form of a powder or other solid form - Contain another suitable matrix material.
  • FIG. 2 shows a schematic representation of a cross section through a coated hard material particle 30.
  • the hard material particle 30 has a coating 32 on its surface.
  • the material of the coating 32 is chosen such that it forms a solid material connection with the material of the hard material particle 30 on the one hand and wetting of the hard material particle 30 by the matrix material and / or by the solder and a cohesive connection between the hard material particles 30 and the matrix material and / or the Lot promotes. This may be due to the chemical and / or physical properties of the material of the coating 32.
  • Figure 3 shows a schematic representation of a cross section through a coating 20, which differs from the coating shown above with reference to Figure 1 in that it consists of - the adhesive layer 21 not included - three layers 22, 26, 34.
  • the solder layer 22 comprises solder particles 23 in a binder 24.
  • the solder layer 22 may be a solid solder layer without a binder 24.
  • the example shown in FIG. 3 has only MCrAlY particles 28 in the functional layer 26, but no hard material particles 30.
  • the functional layer 26 can be an MCrAl Y Alloy (or other matrix material) in solid form without a binder 27.
  • the coating 20 shown in FIG. 3 also has a hard material particle layer 34.
  • the hard material particle layer 34 comprises hard material particles 30, similar to those described above with reference to FIGS. 1 and 2, in an organic binder, for example.
  • the binder 35 is also designed to be free of residue or substantially in a subsequent thermal treatment to disappear without residue.
  • the coating 20 has only one layer, in the solder particles 23, MCrAl Y particles 28 and coated hard material particles 30 are arranged.
  • the coated hard material particles 30 comprise at least one of either cubic boron nitride or silicon nitride or silicon aluminum oxynitride.
  • concentrations of the solder particles 23, the MCr Al Y particles 28 and the coated hard material particles 30 in a binder 24, in particular organic, vary in the direction of the thickness of the coating 20.
  • the solder particles 23 have a side facing the surface of a component to be coated high concentration, which decreases towards the opposite side.
  • the hard material particles 30 have a high concentration at the side facing away from the component to be coated, which decreases towards the side which is to be turned to the surface to be coated.
  • the concentration of MCrAlY particles has a maximum in between.
  • FIG. 5 shows a schematic flow diagram of a method for coating a surface of a component, in particular a blade tip of a blade of an axial compressor, a gas turbine or another turbomachine.
  • the method can also be carried out with coatings which differ from the examples described above with reference to FIGS. 1 to 4, reference numerals from FIGS. 1 to 4 are used by way of example in order to facilitate an understanding.
  • hard particles 30 of cubic boron nitride, silicon nitride or silicon aluminum oxynitride are coated.
  • already coated hard material particles 30 are provided.
  • the coating of the hard material particle Kel 30 is designed to facilitate or improve a wetting and a cohesive connection of the hard material particles 30 with a matrix material and / or a solder in subsequent process steps.
  • a solder is applied to a surface 12 to be coated of a component 10, for example in the form of a solid solder layer or in the form of solder particles 23, which are embedded in a binder 24.
  • a matrix material is applied to the surface 12 to be coated, for example in the form of a solid layer or in the form of a powder of the matrix material, which is embedded in a binder 27.
  • hard material particles 30 are applied to the surface 12 to be coated.
  • the hard material particles 30 are in the applied in the third step 103 matrix material or in a binder 27; 35; 24 embedded.
  • the second step 102, the third step 103, and the fourth step 104 may be performed sequentially or partially or completely simultaneously.
  • the second step 102, the third step 103 and the fourth step 104 may be carried out simultaneously by applying one of the layer structures in the form of a tape or a film as described above with reference to FIGS. 1, 3 and 4.
  • a fifth step 105 the solder, the matrix material, the hard material particles and at least the surface 12 to be coated of the component 10 are heated, for example by ohmic losses of induced eddy current fields.
  • adhesive layer 21 and binder 24, 27, 35 initially evaporate and / or decompose, if present. After evaporation of and / or decomposition of adhesive layer 21 and binder 24, 27, 35, the temperature is increased to such an extent that it exceeds the temperature Solidus temperature of the solder or solder particles 23, but below the solidus temperature of the matrix material or the powder particles 28 of the matrix material.
  • a sixth step 106 which proceeds almost simultaneously with the fifth step 105, the solder 23 melts and wets the surface 12 of the component 10 to be coated and also the matrix material and, if the matrix material is present as a powder, the hard material particles 30.
  • the solder, the matrix material and that reached Temperature may be selected so that at a substantially concurrent seventh step 107, the matrix material dissolves at least partially in the solder.
  • the temperature of the solder, the matrix material, the hard particles 30 and the surface 12 to be coated is lowered below the solidus point of the solder.
  • the solder solidifies and forms a material connection between the surface to be coated 12 on the one hand and the matrix material and the hard material particles 30 on the other.
  • the cohesive connection of the solder to the hard material particles 30 is direct if the matrix material is in the form of a powder which is penetrated by the liquid solder due to capillary forces.
  • the cohesive connection of the solder with the hard material particles 30 is an indirect one, when the hard material particles 30 are embedded in a solid layer of the matrix material, unlike in FIGS. 1, 3 and 4.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

Un revêtement (20) pour un élément (10) ou appliqué sur un élément (10), en particulier une aube d’une turbomachine, comprend un matériau de matrice (28) et des particules dures (30), qui contiennent au moins du nitrure de bore cubique, du nitrure de silicium ou de l’oxynitrure de silicium et d’aluminium, les particules dures (30) étant revêtues..
PCT/DE2010/000708 2009-06-30 2010-06-21 Revêtement et procédé de revêtement d’un élément WO2011000348A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009031313.3 2009-06-30
DE102009031313.3A DE102009031313B4 (de) 2009-06-30 2009-06-30 Beschichtung und Verfahren zum Beschichten eines Bauteils

Publications (1)

Publication Number Publication Date
WO2011000348A1 true WO2011000348A1 (fr) 2011-01-06

Family

ID=42764655

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2010/000708 WO2011000348A1 (fr) 2009-06-30 2010-06-21 Revêtement et procédé de revêtement d’un élément

Country Status (2)

Country Link
DE (1) DE102009031313B4 (fr)
WO (1) WO2011000348A1 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2444513A1 (fr) * 2010-10-25 2012-04-25 United Technologies Corporation Revêtement céramique d'arbre de rotor abrasif
WO2013032626A3 (fr) * 2011-08-31 2013-07-11 TDY Industries, LLC Procédés de formation de couches résistantes à l'usure sur des surfaces métalliques
EP2662474A1 (fr) * 2012-05-07 2013-11-13 Siemens Aktiengesellschaft Procédé destiné à lýapplication dýune couche de protection sur un composant de turbine
US8637127B2 (en) 2005-06-27 2014-01-28 Kennametal Inc. Composite article with coolant channels and tool fabrication method
US8697258B2 (en) 2006-10-25 2014-04-15 Kennametal Inc. Articles having improved resistance to thermal cracking
US9016406B2 (en) 2011-09-22 2015-04-28 Kennametal Inc. Cutting inserts for earth-boring bits
EP2963144A3 (fr) * 2014-07-02 2016-02-10 United Technologies Corporation Revêtement abrasif et procédés de fabrication et d'utilisation
EP3222812A1 (fr) * 2016-03-24 2017-09-27 Siemens Aktiengesellschaft Procede de fabrication ou de reparation d'une aube directrice, aube directrice, procede de fabrication ou de reparation d'un boitier d'une turbomachine et boitier
GB2551527A (en) * 2016-06-21 2017-12-27 Rolls Royce Plc Method of producing a gas turbine engine component with an abrasive coating
US10012095B2 (en) 2014-07-02 2018-07-03 United Technologies Corporation Abrasive coating and manufacture and use methods
US10786875B2 (en) 2014-07-02 2020-09-29 Raytheon Technologies Corporation Abrasive preforms and manufacture and use methods

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0270785A2 (fr) 1986-11-28 1988-06-15 General Electric Company Corps d'usure, ainsi que la poudre et leur procédé de fabrication
US5359770A (en) 1992-09-08 1994-11-01 General Motors Corporation Method for bonding abrasive blade tips to the tip of a gas turbine blade
EP1367147A1 (fr) * 2001-02-28 2003-12-03 Mitsubishi Heavy Industries, Ltd. Revetement resistant a l'usure et procede d'application correspondant
US20040091627A1 (en) * 2001-05-31 2004-05-13 Minoru Ohara Coating forming method and coating forming material, and abbrasive coating forming sheet
WO2007003160A1 (fr) * 2005-07-01 2007-01-11 Mtu Aero Engines Gmbh Procede de fabrication d'un blindage pour une aube de turbine
WO2007115551A1 (fr) 2006-04-11 2007-10-18 Mtu Aero Engines Gmbh Composant dote d'un blindage
WO2008135803A1 (fr) 2007-05-04 2008-11-13 Mtu Aero Engines Gmbh Procédé de fabrication d'un revêtement abrasif sur un composant de turbine à gaz

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5349770A (en) * 1993-02-23 1994-09-27 Roy Bursey Frame display arrangement for displaying thin, flat objects

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0270785A2 (fr) 1986-11-28 1988-06-15 General Electric Company Corps d'usure, ainsi que la poudre et leur procédé de fabrication
US5359770A (en) 1992-09-08 1994-11-01 General Motors Corporation Method for bonding abrasive blade tips to the tip of a gas turbine blade
EP1367147A1 (fr) * 2001-02-28 2003-12-03 Mitsubishi Heavy Industries, Ltd. Revetement resistant a l'usure et procede d'application correspondant
US20040091627A1 (en) * 2001-05-31 2004-05-13 Minoru Ohara Coating forming method and coating forming material, and abbrasive coating forming sheet
US7063250B2 (en) 2001-05-31 2006-06-20 Mitsubishi Heavy Industries, Ltd. Coating forming method and coating forming material, and abrasive coating forming sheet
WO2007003160A1 (fr) * 2005-07-01 2007-01-11 Mtu Aero Engines Gmbh Procede de fabrication d'un blindage pour une aube de turbine
WO2007115551A1 (fr) 2006-04-11 2007-10-18 Mtu Aero Engines Gmbh Composant dote d'un blindage
WO2008135803A1 (fr) 2007-05-04 2008-11-13 Mtu Aero Engines Gmbh Procédé de fabrication d'un revêtement abrasif sur un composant de turbine à gaz

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8637127B2 (en) 2005-06-27 2014-01-28 Kennametal Inc. Composite article with coolant channels and tool fabrication method
US8808591B2 (en) 2005-06-27 2014-08-19 Kennametal Inc. Coextrusion fabrication method
US8841005B2 (en) 2006-10-25 2014-09-23 Kennametal Inc. Articles having improved resistance to thermal cracking
US8697258B2 (en) 2006-10-25 2014-04-15 Kennametal Inc. Articles having improved resistance to thermal cracking
EP2444513A1 (fr) * 2010-10-25 2012-04-25 United Technologies Corporation Revêtement céramique d'arbre de rotor abrasif
US8790078B2 (en) 2010-10-25 2014-07-29 United Technologies Corporation Abrasive rotor shaft ceramic coating
WO2013032626A3 (fr) * 2011-08-31 2013-07-11 TDY Industries, LLC Procédés de formation de couches résistantes à l'usure sur des surfaces métalliques
CN103917692A (zh) * 2011-08-31 2014-07-09 钴碳化钨硬质合金公司 用于在金属表面上形成耐磨损层的方法
US8800848B2 (en) 2011-08-31 2014-08-12 Kennametal Inc. Methods of forming wear resistant layers on metallic surfaces
US9016406B2 (en) 2011-09-22 2015-04-28 Kennametal Inc. Cutting inserts for earth-boring bits
EP2662474A1 (fr) * 2012-05-07 2013-11-13 Siemens Aktiengesellschaft Procédé destiné à lýapplication dýune couche de protection sur un composant de turbine
WO2013167334A1 (fr) * 2012-05-07 2013-11-14 Siemens Aktiengesellschaft Procédé pour appliquer une couche protectrice sur un élément de turbine
US9309597B2 (en) 2012-05-07 2016-04-12 Siemens Aktiengesellschaft Process for applying a protective layer to a turbine component
EP2963144A3 (fr) * 2014-07-02 2016-02-10 United Technologies Corporation Revêtement abrasif et procédés de fabrication et d'utilisation
US10012095B2 (en) 2014-07-02 2018-07-03 United Technologies Corporation Abrasive coating and manufacture and use methods
US10018056B2 (en) 2014-07-02 2018-07-10 United Technologies Corporation Abrasive coating and manufacture and use methods
US10786875B2 (en) 2014-07-02 2020-09-29 Raytheon Technologies Corporation Abrasive preforms and manufacture and use methods
US11752578B2 (en) 2014-07-02 2023-09-12 Rtx Corporation Abrasive preforms and manufacture and use methods
EP3222812A1 (fr) * 2016-03-24 2017-09-27 Siemens Aktiengesellschaft Procede de fabrication ou de reparation d'une aube directrice, aube directrice, procede de fabrication ou de reparation d'un boitier d'une turbomachine et boitier
GB2551527A (en) * 2016-06-21 2017-12-27 Rolls Royce Plc Method of producing a gas turbine engine component with an abrasive coating

Also Published As

Publication number Publication date
DE102009031313B4 (de) 2018-07-05
DE102009031313A1 (de) 2011-05-05

Similar Documents

Publication Publication Date Title
DE102009031313B4 (de) Beschichtung und Verfahren zum Beschichten eines Bauteils
DE102011055246B4 (de) Verfahren zur Herstellung und Beschichtung von Komponenten mit einspringend ausgebildeten Kühlkanälen
DE102011055612B4 (de) Turbinenkomponenten mit Kühleinrichtungen und Verfahren zur Herstellung derselben
EP2548685B1 (fr) Brasure pour brasage haute température et procédé de réparation ou de fabrication de composants en utilisant cette brasure
DE2637443C2 (fr)
EP2783076B1 (fr) Procédé de blindage de l'encoche en z de pales en tial
CH704833A1 (de) Komponente für eine Turbomaschine und ein Verfahren zum Herstellen einer derartigen Komponente.
EP2780552B1 (fr) Blindage d'ailettes d'étanchéité d'aubes en tial par dépôt de particules de matériau dur par brasage par induction
DE102008003100A1 (de) Lötbeschichtung, Verfahren zum Beschichten eines Bauteils, Bauteil und Klebeband mit einer Lötbeschichtung
EP3170609A1 (fr) Procédé de fabrication d'une roue à aubes pour une turbomachine ; roue à aubes correspondante
WO2010094273A2 (fr) Fabrication d'aubes et disque combinés de turbine avec une couche de protection contre l'oxydation ou la corrosion
EP2203271A2 (fr) PROCÉDÉ D'APPLICATION DE JOINT ET DE MATÉRIAU POUR UNE PIÈCE COMPORTANT UNE ZONE CONSTITUÉE D'UN ALLIAGE Ti-Al
EP2414125A1 (fr) Elément de brasage double comprenant au moins une première couche constituée d'un matériau d'apport de brasage à base de ni, ainsi qu'au moins une deuxième couche présentant un élément actif, procédé pour sa fabrication et utilisations dudit élément
EP2422051A2 (fr) Procédé de production d'un revêtement dur d'un bout d'aube de turbine à gaz et aube de turbine à gaz
EP2796588B1 (fr) Procédé de fabrication d'un revêtement de protection haute température
EP0840809B1 (fr) Produit avec un corps de base metallique pourvu de canaux de refroidissement et sa fabrication
WO2011015187A1 (fr) Revêtement de bout d'aube abrasable
WO2018029060A1 (fr) Procédé d'assemblage de matériaux et composite
CH709882B1 (de) Verfahren für das metallurgische Festzustandsverbinden verschiedener Hochtemperaturmaterialien und damit hergestellter Artikel.
EP2695964B1 (fr) Couche de protection adaptée au composant
DE102005044991A1 (de) Verfahren zur Herstellung einer Schutzschicht, Schutzschicht und Bauteil mit einer Schutzschicht
EP2737103B1 (fr) Procédé d'application d'une couche de protection contre l'usure sur un composant de turbomachine
DE4010076A1 (de) Materialsysteme fuer den einsatz in bei hoeherer temperatur einsetzbaren strahltriebwerken
DE10208868A1 (de) Verfahren zur Herstellung eines Bauteils und/oder einer Schicht aus einer schwingungsdämpfenden Legierung oder intermetallischen Verbindung sowie Bauteil, das durch dieses Verfahren hergestellt wurde
EP1892311B1 (fr) Aube de turbine avec une système de revêtement

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 10739842

Country of ref document: EP

Kind code of ref document: A1

122 Ep: pct application non-entry in european phase

Ref document number: 10739842

Country of ref document: EP

Kind code of ref document: A1