EP3177750B1 - Surveillance et commande d'une opération de revêtement avec distribution de chaleur sur la pièce - Google Patents

Surveillance et commande d'une opération de revêtement avec distribution de chaleur sur la pièce Download PDF

Info

Publication number
EP3177750B1
EP3177750B1 EP15775425.0A EP15775425A EP3177750B1 EP 3177750 B1 EP3177750 B1 EP 3177750B1 EP 15775425 A EP15775425 A EP 15775425A EP 3177750 B1 EP3177750 B1 EP 3177750B1
Authority
EP
European Patent Office
Prior art keywords
coating
heat distribution
workpiece
detected
heat
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.)
Active
Application number
EP15775425.0A
Other languages
German (de)
English (en)
Other versions
EP3177750A1 (fr
Inventor
Arturo Flores Renteria
Sascha Martin Kyeck
Catrina Michel
Alexandr Sadovoy
Tolga YAGCI
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 Energy Global GmbH and Co KG
Original Assignee
Siemens AG
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 filed Critical Siemens AG
Publication of EP3177750A1 publication Critical patent/EP3177750A1/fr
Application granted granted Critical
Publication of EP3177750B1 publication Critical patent/EP3177750B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/129—Flame spraying

Definitions

  • the invention relates to a method for coating a workpiece using a spray device and a device for performing the method according to the invention.
  • the workpiece to be coated can in particular be a turbine blade or some other component located in a hot gas path of a gas turbine.
  • Components that are subject to high thermal and mechanical loads such as turbine components and, in particular, turbine blades, are usually coated with a coating material in order to increase the temperature resistance and / or the abrasion resistance of the workpiece.
  • Typical coatings that are used to coat turbine blades are so-called MCrAlX coatings, where M for a metal, for example iron (Fe), cobalt (Co) or nickel (Ni), Cr for chromium, Al for aluminum and X for Yttrium (Y) and / or silicon (Si), scandium (Sc) and / or at least one rare earth element or hafnium.
  • ceramic thermal barrier coatings such as zirconium oxide, the structure of which is at least partially stabilized by yttrium oxide, are used in particular for turbine blades.
  • TBC Thermal Barrier Coating
  • zirconium oxide the structure of which is at least partially stabilized by yttrium oxide
  • the coatings described are applied to the components to be coated by means of a spraying process. Examples of such spraying methods are high-speed flame spraying and plasma spraying.
  • the object of the present invention is therefore to provide an advantageous method and an advantageous device for coating a workpiece using a spray device which enable a quick reaction to deviations of the coating produced from the desired coating properties.
  • the invention is based on and includes the insight that the course of the coating process can be monitored and controlled by detecting the heat input on or into the workpiece due to the spray jet of the spray device in order to ensure that the desired coating properties of the finished coating are achieved .
  • the spray jet or the coating material transported in it is strongly heated in conventional coating processes such as high-speed flame spraying or plasma spraying during the spraying or spraying process, so that the local distribution and the mass or density of the on the surface of the workpiece Assess adhering coating material using a thermal image and compare different coating processes on workpieces of the same type.
  • the method according to the invention can advantageously be used, with corresponding local cooling resulting instead of an input of heat. Nevertheless, in the following, heat input and heat distribution are referred to, although the mentioned exceptional cases should not be excluded.
  • the temperature of the workpiece when carrying out the method according to the invention, it is advantageous to bring the temperature of the workpiece to a certain value in order to create reproducible conditions for different coating processes of copies of the same workpiece type.
  • the workpiece to be coated can particularly preferably be kept at the selected temperature by determining the temperature and heating or cooling the workpiece accordingly.
  • the spray jet from the spray device and thus the work area is usually guided along a predetermined path over the surface of the workpiece (of course, the workpiece can in principle also be guided along the spray device).
  • the working area denotes that area of the surface of the workpiece in which the coating material is currently being sprayed on. In a fully automated process, this path remains the same for every workpiece of the same type, which is why the heat input into the workpiece by the spray jet should also be the same if the specified coating parameters are observed. If a discrepancy between the detected heat distribution and the expected heat distribution is determined, the at least one coating parameter can be adapted in order to carry out the coating process as closely as possible following the specifications.
  • the recorded heat distribution is compared with stored reference heat distributions. From the stored reference heat distributions, a reference heat distribution that most closely resembles the detected heat distribution is then selected. The at least one coating parameter is finally adapted as a function of a coating parameter data set assigned to the selected reference heat distribution.
  • a deviation of the actual coating parameter or parameters from the specified values is determined by considering a deviation of the detected heat distribution from an expectation. It is assumed here that the actual coating parameters deviate from the specification in the same way as is the case for the coating parameter data sets assigned to the respective reference heat distributions.
  • the recorded heat distribution deviates from the reference heat distribution assigned to the current coating parameters and is similar, for example, to a reference heat distribution with an increased supply rate of the coating material, it can be concluded from the coating parameter data record assigned to this reference heat distribution that the coating parameter is currently supplied faster than desired and specified. The specification for the feed rate can then be reduced accordingly.
  • a difference is preferably determined between the coating parameter data set, the reference heat distribution most closely resembling the detected heat distribution, and the current at least one coating parameter used for the coating.
  • the current at least one coating parameter can then be adapted as a function of this difference.
  • the degree of adaptation of the at least one coating parameter can be proportional to the difference. This means that even larger deviations from the specification can be quickly compensated for.
  • the reference heat distributions and the coating parameter data records assigned to the reference heat distributions are preferably obtained on the basis of carrying out coating processes using the assigned coating parameter data records.
  • specimens of the workpiece type to be coated or, in a more economical embodiment, material samples, for example tile-shaped material samples, can be coated with different coating parameters and the properties of the coatings obtained in this way can be assessed.
  • the stored reference heat distributions are divided into a plurality of groups, each of the groups being assigned to a respective surface region of the workpiece.
  • the recorded heat distribution can be compared with that group of stored reference heat distributions that is assigned to that surface region of the workpiece in which the work area for which the recorded heat distribution was recorded is located.
  • special features such as the local geometry or other properties of the workpiece, which cause variable coating properties and therefore require special coating parameters, can be taken into account when coating the workpiece.
  • Each stored reference heat distribution is preferably assigned an evaluation which contains a statement about at least one coating property, in particular about a coating porosity, a coating roughness or a coating thickness.
  • the deviations of the coating process from the specification recognized on the basis of the recorded heat distribution can be assessed on the basis of their expected effects on the resulting coating properties. This allows a prediction to be made about the quality of the coated workpiece and can be used to control the coating process, for example when adapting the at least one coating parameter.
  • the heat distribution in the working area of the surface of the workpiece can be recorded with a pyrometer or an infrared camera.
  • a pyrometer or an infrared camera.
  • the at least one coating parameter can comprise at least one coating parameter selected from the group consisting of plasma voltage, powder feed rate of the coating material or composition of a plasma gas.
  • a second aspect of the invention relates to a device for coating a workpiece.
  • the device is equipped with a spray device, a heat measuring device and a control unit connected to the spray device and the heat measuring device.
  • the control unit is designed to carry out the method according to the invention.
  • Figure 1 shows an embodiment of the method according to the invention in the form of a flowchart.
  • the method begins in a start step S1.
  • a workpiece to be coated is provided and a path is determined along which the spray device is guided over the surface of the workpiece.
  • the relevant coating parameter or parameters are selected and preset according to the coating to be applied and its desired properties.
  • these coating parameters can in particular include a feed rate of the coating material, a plasma voltage or a composition of the plasma gas.
  • step S3 the coating process is started or carried out in accordance with the predetermined coating parameter (s).
  • the coating process can be carried out continuously or regularly interrupted for carrying out the further method steps S4 to S10. However, because of the shorter process time, continuous coating is preferred.
  • step S4 a heat distribution of the work area on the surface of the workpiece is detected. This is preferably carried out using an imaging method which determines a respective temperature for the individual locations on the surface of the workpiece. The higher the resolution of the imaging process, the more precisely the heat distribution can be assessed.
  • step S5 the detected heat distribution is compared with a plurality of reference heat distributions.
  • a group of reference heat distributions from the total quantity can be selected for the comparison on reference heat distributions which are regarded as representative of the currently coated partial surface of the workpiece.
  • the comparison determines that reference heat distribution which most closely resembles the detected heat distribution.
  • step S6 the coating parameter data set assigned to the determined reference heat distribution is compared with the currently specified coating parameter or parameters.
  • the coating parameter data record reproduces those coating parameters which led to the assigned reference heat distribution during a trial of the coating process. Since the resulting heat distribution depends on the actual coating parameters, conclusions are drawn about the actual values of the coating parameters of the current coating process by considering the coating parameters assigned to the determined reference heat distribution.
  • step S7 a discrepancy between the assigned coating parameter data set and the specified coating parameter (s) is determined. It is assumed here that the specified at least one coating parameter is not adhered to by the spray device if a detected heat distribution that deviates from the expectation has occurred.
  • step S8 a correction value or a set of correction values is then calculated as a function of the previously determined deviation, by which the at least one coating parameter is adapted in step S9.
  • the adaptation of the at least one coating parameter is intended to ensure that the coating process is carried out more precisely in accordance with the specifications.
  • step S10 it is finally checked whether the end of the path along which the workpiece is coated has been reached. If this is not the case, the coating process and the method according to the invention are continued by branching back to step S3; otherwise the method is ended in step S11. An investigation can then be carried out the properties of the coating and, if necessary, adjustments to the coating parameter data sets assigned to the reference heat distributions are made. It is also conceivable to select one or more from the heat distributions recorded during the implementation of the method and to make them available as reference heat distributions for further process runs. For this purpose, the recorded heat distributions and the associated respective coating parameter (s) can be stored while the method is being carried out. In particular, it is also conceivable to assess the informative value of the individual (reference) heat distributions and to achieve improved reproducibility of the coating process over a large number of process steps.
  • the Figure 2 shows an example of a gas turbine 100 in a partial longitudinal section.
  • the method according to the invention is particularly suitable for coating components of such a gas turbine 100.
  • the gas turbine 100 has in the interior a rotor 103 which is rotatably mounted about an axis of rotation 102 and has a shaft 101, which is also referred to as a turbine rotor.
  • the annular combustion chamber 110 communicates with an, for example, annular hot gas duct 111.
  • annular hot gas duct 111 There, for example, four turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. In the direction of flow of a working medium 113, as seen in the hot gas duct 111, a row of guide vanes 115 is followed by a row 125 formed from rotor blades 120.
  • the guide blades 130 are attached to an inner housing 138 of a stator 143, whereas the rotor blades 120 of a row 125 are attached to the rotor 103, for example by means of a turbine disk 133.
  • a generator or a work machine (not shown) is coupled to the rotor 103.
  • the compressor 105 sucks in air 135 through the suction housing 104 and compresses it.
  • the compressed air provided at the turbine-side end of the compressor 105 is fed to the burners 107 and mixed there with a fuel.
  • the mixture is then burned in the combustion chamber 110 with the formation of the working medium 113.
  • the working medium 113 flows along the hot gas duct 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 relaxes, transferring impulses, so that the rotor blades 120 drive the rotor 103 and the rotor 103 drives the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during the operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112 seen in the flow direction of the working medium 113 are subjected to the greatest thermal load.
  • Substrates of the components can also have a directional structure, ie they are monocrystalline (SX structure) or only have longitudinally oriented grains (DS structure).
  • SX structure monocrystalline
  • DS structure longitudinally oriented grains
  • Iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blades 120, 130 and components of the combustion chamber 110.
  • Such superalloys are for example from EP 1 204 776 B1 , EP 1 306 454 , EP 1 319 729 A1 , WO 99/67435 or WO 00/44949 known.
  • the blades 120, 130 can also have coatings against corrosion (MCrAlX; M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earths or hafnium).
  • M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earths or hafnium).
  • Such alloys are known from EP 0 486 489 B1 , EP 0 786 017 B1 , EP 0 412 397 B1 or EP 1 306 454 A1 .
  • a thermal insulation layer can also be present on the MCrAlX and consists, for example, of ZrO2, Y2O3-ZrO2, i.e. it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • EB-PVD Electron beam evaporation
  • the guide vane 130 has a guide vane root (not shown here) facing the inner casing 138 of the turbine 108 and a guide vane head opposite the guide vane root.
  • the guide vane head faces the rotor 103 and is fixed on a fastening ring 140 of the stator 143.
  • FIG. 8 shows a perspective view of a rotor blade 120 or guide vane 130 of a turbomachine that extends along a longitudinal axis 121.
  • the turbomachine can be a gas turbine of an aircraft or a power plant for generating electricity, a steam turbine or a compressor.
  • the blade 120, 130 has, one after the other along the longitudinal axis 121, a fastening area 400, a blade platform 403 adjoining it, and a blade 406 and a blade tip 415.
  • the vane 130 can have a further platform at its vane tip 415 (not shown).
  • a blade root 183 is formed which is used to fasten the rotor blades 120, 130 to a shaft or a disk (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other configurations than a fir tree or dovetail foot are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium that flows past the airfoil 406.
  • Such superalloys are for example from EP 1 204 776 B1 , EP 1 306 454 , EP 1 319 729 A1 , WO 99/67435 or WO 00/44949 known.
  • the blade 120, 130 can in this case be manufactured by a casting process, also by means of directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces with a monocrystalline structure or structures are used as components for machines that are exposed to high mechanical, thermal and / or chemical loads during operation.
  • Such monocrystalline workpieces are manufactured e.g. by directional solidification from the melt. These are casting processes in which the liquid metallic alloy is converted into a monocrystalline structure, i.e. to a single crystal workpiece, or solidified in a directional manner.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, i.e. grains that run over the entire length of the workpiece and are referred to here, according to common usage, as directionally solidified) or a monocrystalline structure, i.e. the entire workpiece consists of a single crystal.
  • a columnar grain structure columnar, i.e. grains that run over the entire length of the workpiece and are referred to here, according to common usage, as directionally solidified
  • a monocrystalline structure i.e. the entire workpiece consists of a single crystal.
  • directionally solidified structures are generally referred to, this means both single crystals that have no grain boundaries or at most small-angle grain boundaries, as well as columnar crystal structures that have grain boundaries running in the longitudinal direction but no transverse grain boundaries. These second-mentioned crystalline structures are also referred to as directionally solidified structures.
  • the blades 120, 130 can have coatings against corrosion or oxidation, e.g. B. (MCrAlX; M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one rare element Earth, or hafnium (Hf)).
  • M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one rare element Earth, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1 , EP 0 786 017 B1 , EP 0 412 397 B1 or EP 1 306 454 A1 .
  • the density is preferably 95% of the theoretical density.
  • the layer composition preferably has Co-30Ni-28Cr-8Al-0.6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y.
  • nickel-based protective coatings such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1 are also preferably used , 5Re.
  • a thermal insulation layer which is preferably the outermost layer, can also be present on the MCrAlX and consists, for example, of ZrO2, Y2O3-ZrO2, i.e. it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • the thermal insulation layer covers the entire MCrAlX layer.
  • EB-PVD Electron beam evaporation
  • the thermal insulation layer can have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal insulation layer is therefore preferably more porous than the MCrAlX layer.
  • Refurbishment means that components 120, 130 may have to be freed of protective layers after their use (e.g. by sandblasting). The corrosion and / or oxidation layers or products are then removed. If necessary, cracks in the component 120, 130 are also repaired. Then the component 120, 130 is recoated and the component 120, 130 is used again.
  • the blade 120, 130 can be made hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and optionally also has film cooling holes 418 (indicated by dashed lines).
  • the Figure 4 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as a so-called annular combustion chamber in which a plurality of burners 107 arranged in the circumferential direction around an axis of rotation 102 open into a common combustion chamber 154, which generate flames 156.
  • the combustion chamber 110 is designed in its entirety as an annular structure which is positioned around the axis of rotation 102.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of approximately 1000 degrees Celsius to 1600 degrees Celsius.
  • the combustion chamber wall 153 is provided on its side facing the working medium M with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 made of an alloy has a particularly heat-resistant one on the working medium side Protective layer (MCrAlX layer and / or ceramic coating) or is made of high temperature resistant material (solid ceramic stones).
  • M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths or hafnium (Hf).
  • Such alloys are known from EP 0 486 489 B1 , EP 0 786 017 B1 , EP 0 412 397 B1 or EP 1 306 454 A1 .
  • a ceramic thermal insulation layer for example, can also be present on the MCrAlX and consists, for example, of ZrO2, Y2O3-ZrO2, i.e. it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • EB-PVD Electron beam evaporation
  • thermal insulation layer can have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • Refurbishment means that heat shield elements 155 may have to be freed of protective layers after their use (for example by sandblasting). The corrosion and / or oxidation layers or products are then removed. If necessary, cracks in the heat shield element 155 are also repaired. Thereafter, the heat shield elements 155 are recoated and the heat shield elements 155 are used again.
  • a cooling system can also be provided for the heat shield elements 155 or for their holding elements.
  • the heat shield elements 155 are then, for example, hollow and possibly also have cooling holes (not shown) opening into the combustion chamber space 154.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Claims (8)

  1. Procédé de revêtement d'une pièce en utilisant un système de pulvérisation,
    dans lequel on effectue la pulvérisation sur la pièce suivant au moins un paramètre de revêtement et
    dans lequel, pendant le revêtement, on effectue au moins les stades suivants :
    - on relève une répartition spatiale de chaleur dans une partie de travail d'une surface de la pièce ; et
    - on adapte le au moins un paramètre de revêtement en fonction de la répartition de chaleur, qui a été relevée, dans lequel on compare la répartition de chaleur, qui a été relevée, à des répartitions de chaleur de référence mises en mémoire et dans lequel on adapte le au moins un paramètre de revêtement en fonction d'un ensemble de données de paramètre de revêtement associé à une répartition de chaleur de référence, la plus semblable à la répartition de chaleur, qui a été détectée, parmi les répartitions de référence mises en mémoire,
    dans lequel les répartitions de chaleur de référence mises en mémoire sont subdivisées en une pluralité de groupes,
    dans lequel chacun des groupes est associé à une région de surface respective de la pièce et
    dans lequel, lors de la comparaison de la répartition de chaleur, qui a été relevée, aux répartitions de chaleur de référence mises en mémoire, on compare la répartition de chaleur, qui a été relevée, au groupe de répartitions de chaleur de référence mis en mémoire, qui est associé à la région de surface de la pièce, dans laquelle se trouve la partie de travail, pour laquelle la répartition de chaleur a été relevée.
  2. Procédé suivant la revendication 1,
    dans lequel on détermine une différence entre l'ensemble de données de paramètre de revêtement de la répartition de chaleur de référence la plus semblable à la répartition de chaleur, qui a été relevée, et le au moins un paramètre de revêtement en cours utilisé pour le revêtement et on adapte le au moins un paramètre de revêtement en cours en fonction de cette différence.
  3. Procédé suivant l'une des revendications 1 ou 2,
    dans lequel on obtient les répartitions de chaleur de référence et les ensembles de données de paramètre de revêtement associés, respectivement, aux répartitions de chaleur de référence, en effectuant des opérations de revêtement en utilisant les ensembles de données de paramètre de revêtement associés.
  4. Procédé suivant l'une des revendications 1 à 3,
    dans lequel, à chaque répartition de chaleur de référence mise en mémoire, est associée une évaluation, qui contient une proposition sur au moins une propriété du revêtement, notamment sur une porosité du revêtement, un rugosité du revêtement ou une épaisseur du revêtement.
  5. Procédé suivant l'une des revendications précédentes, dans lequel on relève la répartition de chaleur dans la partie de travail de la surface de la pièce par un pyromètre ou par une caméra infrarouge.
  6. Procédé suivant l'une des revendications précédentes, dans lequel on utilise un procédé de pulvérisation au plasma.
  7. Procédé suivant la revendication précédente,
    dans lequel le au moins un paramètre de revêtement comprend au moins l'un de la tension de plasma, du taux d'apport de poudre ou de la composition d'un gaz de plasma.
  8. Système de revêtement d'une pièce et comprenant un système de pulvérisation, un système de mesure de la chaleur et une unité de commande reliée au système de pulvérisation et au système de mesure de la chaleur, qui est constitué pour effectuer le procédé suivant l'une des revendications précédentes.
EP15775425.0A 2014-10-06 2015-09-30 Surveillance et commande d'une opération de revêtement avec distribution de chaleur sur la pièce Active EP3177750B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014220180.2A DE102014220180A1 (de) 2014-10-06 2014-10-06 Überwachung und Steuerung eines Beschichtungsvorgangs anhand einer Wärmeverteilung auf dem Werkstück
PCT/EP2015/072543 WO2016055325A1 (fr) 2014-10-06 2015-09-30 Surveillance et commande d'une opération de revêtement avec distribution de chaleur sur la pièce

Publications (2)

Publication Number Publication Date
EP3177750A1 EP3177750A1 (fr) 2017-06-14
EP3177750B1 true EP3177750B1 (fr) 2020-11-25

Family

ID=54256738

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15775425.0A Active EP3177750B1 (fr) 2014-10-06 2015-09-30 Surveillance et commande d'une opération de revêtement avec distribution de chaleur sur la pièce

Country Status (4)

Country Link
US (1) US10975463B2 (fr)
EP (1) EP3177750B1 (fr)
DE (1) DE102014220180A1 (fr)
WO (1) WO2016055325A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10969216B2 (en) 2017-08-04 2021-04-06 Rolls-Royce North American Technologies, Inc. Adaptive control of coating thickness
US11679898B2 (en) 2020-06-15 2023-06-20 General Electric Company Inspection and repair tool

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4656331A (en) * 1982-04-26 1987-04-07 General Electric Company Infrared sensor for the control of plasma-jet spray coating and electric are heating processes
JP2773050B2 (ja) 1989-08-10 1998-07-09 シーメンス アクチエンゲゼルシヤフト 耐熱性耐食性の保護被覆層
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
US5047612A (en) * 1990-02-05 1991-09-10 General Electric Company Apparatus and method for controlling powder deposition in a plasma spray process
DE59505454D1 (de) 1994-10-14 1999-04-29 Siemens Ag Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung
DE19535078B4 (de) * 1995-09-21 2006-06-08 Robert Bosch Gmbh Überwachung und Regelung von thermischen Spritzverfahren
US6296043B1 (en) * 1996-12-10 2001-10-02 Howmet Research Corporation Spraycast method and article
EP0892090B1 (fr) 1997-02-24 2008-04-23 Sulzer Innotec Ag Procédé de fabrication de structure monocristallines
EP0861927A1 (fr) 1997-02-24 1998-09-02 Sulzer Innotec Ag Procédé de fabrication de structures monocristallines
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
DE19837400C1 (de) * 1998-08-18 1999-11-18 Siemens Ag Verfahren und Vorrichtung zur Beschichtung von Hochtemperaturbauteilen mittels Plasmaspritzens
DE19857737A1 (de) * 1998-11-25 2000-05-31 Joma Chemicals As Limingen Werkstoff und Verfahren zum Herstellen einer korrosions- und verschleißfesten Schicht durch thermisches Spritzen
US6231692B1 (en) 1999-01-28 2001-05-15 Howmet Research Corporation Nickel base superalloy with improved machinability and method of making thereof
WO2001009403A1 (fr) 1999-07-29 2001-02-08 Siemens Aktiengesellschaft Piece resistant a des temperatures elevees et son procede de production
GB0026868D0 (en) 2000-11-03 2000-12-20 Isis Innovation Control of deposition and other processes
DE50104022D1 (de) 2001-10-24 2004-11-11 Siemens Ag Rhenium enthaltende Schutzschicht zum Schutz eines Bauteils gegen Korrosion und Oxidation bei hohen Temperaturen
DE50112339D1 (de) 2001-12-13 2007-05-24 Siemens Ag Hochtemperaturbeständiges Bauteil aus einkristalliner oder polykristalliner Nickel-Basis-Superlegierung
FR2836619B1 (fr) * 2002-02-28 2004-04-16 Snecma Services Instrument de projection thermique
DE10244037A1 (de) * 2002-09-21 2004-04-08 Mtu Aero Engines Gmbh Verfahren zur Beschichtung eines Werkstücks
DE102004010782A1 (de) * 2004-03-05 2005-09-22 Mtu Aero Engines Gmbh Verfahren zur Beschichtung eines Werkstücks
DE102004059549A1 (de) * 2004-12-10 2006-06-22 Mtu Aero Engines Gmbh Verfahren zur Beschichtung eines Werkstücks
DE102008048262B4 (de) * 2008-09-22 2021-03-18 Linde Gmbh Verfahren und Vorrichtung zur Bestimmung des Einschmelzgrads einer thermisch gespritzten Oberfläche sowie Verfahren und Vorrichtung zum automatischen Einschmelzen einer thermisch gespritzten Oberfläche
DE102009048706A1 (de) * 2009-10-08 2011-04-28 Hermle Maschinenbau Gmbh Verfahren und Vorrichtung zur Herstellung eines Formteils mittels generativen Auftragens
DE102012021265A1 (de) * 2012-10-29 2014-04-30 Kennametal Inc. Verfahren und Vorrichtung zur berührungslosen und verschleißfreien Überwachung von Schweiß- und Spritzprozessen
DE102013223688A1 (de) 2013-11-20 2015-05-21 Siemens Aktiengesellschaft Verfahren und Vorrichtung zum automatisierten Aufbringen einer Spritzbeschichtung

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP3177750A1 (fr) 2017-06-14
US10975463B2 (en) 2021-04-13
US20170321317A1 (en) 2017-11-09
WO2016055325A1 (fr) 2016-04-14
DE102014220180A1 (de) 2016-06-09

Similar Documents

Publication Publication Date Title
EP2280801B1 (fr) Procédé de soudage de pièces d'usinage en alliages superréfractaires
EP2311597B1 (fr) Procédé de soudage laser de pièces en superalliages haute température avec contrôle de certains paramètres du soudage laser pour obtenir une vitesse de refroidissement particulière
EP2876183B1 (fr) Procédé et dispositif d'application automatique d'un revêtement par pulvérisation
EP2259892A1 (fr) Procédé de soudage à courbe de température régulée et dispositif utilisé à cette fin
EP3068921B1 (fr) Aube de compresseur dotée d'un revêtement dur résistant à la corrosion
EP1952931A1 (fr) Mechtrode ayant une alimentation en poudre et procédé d'utilisation de cette mechtrode
EP1941965A1 (fr) Réouverture de trous à l'aide de la thermographie et d'un composant
EP2312267A1 (fr) Procédé de mesure de l'épaisseur de couche par triangulation laser et dispositif
EP2391744B1 (fr) Revêtement par des procédés de revêtement thermiques et non thermiques
EP2186594A1 (fr) Procédé et dispositif de préchauffage lors du soudage utilisant un deuxième faisceau laser
EP3177750B1 (fr) Surveillance et commande d'une opération de revêtement avec distribution de chaleur sur la pièce
EP2227346A2 (fr) Brasage de trous, procédé de revêtement et baguettes de brasure
WO2009100794A1 (fr) Procédé et dispositif pour fondre des surfaces incurvées
EP1797985A1 (fr) Procédé et dispositif de soudage
EP2583784A1 (fr) Préparation d'au moins un poste à souder avant le soudage et composant
EP2460608A1 (fr) Fabrication d'un fil d'acier à l'aide du procédé de prototypage rapide, fil d'acier et procédé de soudage
WO2018114766A1 (fr) Procédé d'assemblage de segments de composants à gaz chaud par brasage et composant à gaz chaud correspondant
EP1978790B1 (fr) Dispositif et procédé destinés au revêtement d'un composant doté d'un dispositif d'ajustement
WO2009118213A1 (fr) Dispositif de soudage à chambre de soudage et procédé de soudage correspondant
EP2099948A2 (fr) Procédé pour l'enduction d'un composant
EP2177643A1 (fr) Procédé de réparation d'un superalliage à l'aide de la même poudre de superalliage et de céramique
WO2009089840A1 (fr) Procédé et dispositif d'usinage par électro-érosion régulé
EP2241391A1 (fr) Procédé de fabrication d'un moule négatif destiné à couler une aube de turbine et moule de fabrication d'un modèle en cire d'une aube de turbine
WO2010149189A1 (fr) Barrettes de brasage, brasage de trous, procédé de revêtement
WO2009098106A1 (fr) Dispositif chauffant pour une aube de turbine et procédé de soudage

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

Free format text: ORIGINAL CODE: 0009012

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170308

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

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

Owner name: SIEMENS AKTIENGESELLSCHAFT

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20190326

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20200616

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1338397

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201215

Ref country code: DE

Ref legal event code: R081

Ref document number: 502015013909

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502015013909

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG

REG Reference to a national code

Ref country code: NL

Ref legal event code: FP

Ref country code: NL

Ref legal event code: PD

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG; DE

Free format text: DETAILS ASSIGNMENT: CHANGE OF OWNER(S), ASSIGNMENT; FORMER OWNER NAME: SIEMENS AKTIENGESELLSCHAFT

Effective date: 20210129

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210225

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210325

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210226

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210225

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210325

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015013909

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

26N No opposition filed

Effective date: 20210826

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20210930

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20210930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210325

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210930

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210930

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210930

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210930

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210930

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 20220908

Year of fee payment: 8

Ref country code: DE

Payment date: 20220617

Year of fee payment: 8

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1338397

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210930

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20220921

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210930

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20220926

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20150930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502015013909

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201125

REG Reference to a national code

Ref country code: NL

Ref legal event code: MM

Effective date: 20231001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20231001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20231001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230930

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240403