EP2876183A2 - Procédé et dispositif d'application automatique d'un revêtement par pulvérisation - Google Patents

Procédé et dispositif d'application automatique d'un revêtement par pulvérisation Download PDF

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Publication number
EP2876183A2
EP2876183A2 EP14188316.5A EP14188316A EP2876183A2 EP 2876183 A2 EP2876183 A2 EP 2876183A2 EP 14188316 A EP14188316 A EP 14188316A EP 2876183 A2 EP2876183 A2 EP 2876183A2
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EP
European Patent Office
Prior art keywords
coating
data
resolved
coated
deviation
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.)
Granted
Application number
EP14188316.5A
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German (de)
English (en)
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EP2876183A3 (fr
EP2876183B1 (fr
Inventor
Andy Borchardt
Tobias Brett
Karsten Klein
Khaled Maiz
Catrina Michel
Alexandr Sadovoy
Martin Witzel
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Siemens AG
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Siemens AG
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Filing date
Publication date
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Publication of EP2876183A3 publication Critical patent/EP2876183A3/fr
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Publication of EP2876183B1 publication Critical patent/EP2876183B1/fr
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D1/00—Processes for applying liquids or other fluent materials
    • B05D1/02—Processes for applying liquids or other fluent materials performed by spraying
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B12/00—Arrangements for controlling delivery; Arrangements for controlling the spray area
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B13/00—Machines or plants for applying liquids or other fluent materials to surfaces of objects or other work by spraying, not covered by groups B05B1/00 - B05B11/00
    • B05B13/02—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work
    • B05B13/04—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work the spray heads being moved during spraying operation
    • B05B13/0431—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work the spray heads being moved during spraying operation with spray heads moved by robots or articulated arms, e.g. for applying liquid or other fluent material to 3D-surfaces

Definitions

  • the present invention relates to a coating method for the automated application of a spray coating onto a component surface of a component to be coated.
  • the component may in particular be a turbine component, such as a turbine blade.
  • the present invention relates to a coating apparatus for the automated application of a spray coating on a component surface to be coated of a component.
  • the object of the present invention is to provide an advantageous method and an advantageous apparatus for the automated application of a spray coating to a component surface of a component to be coated, which allow a rapid reaction to deviations of the coating from the desired coating.
  • This object is achieved by a coating method according to claim 1 or a coating device according to claim 16.
  • it is an object to provide an advantageous monitoring device for monitoring the automated application of a Spray coating to provide. This object is achieved by a monitoring device according to claim 13.
  • the dependent claims contain advantageous embodiments of the invention.
  • the simulation of the coating based on the detected web data and the acquired process data makes it possible to quickly determine a deviation of the actual coating from the desired coating, which in turn makes it possible to quickly make corrections to the coating, in particular in an automated manner.
  • An automated correction of the coating on the component surface to be coated can take place, in particular, if the calculation of the deviation results in a deviation of the simulated coating from the desired coating, which exceeds a permissible deviation. If the calculation of the deviation occurs during or immediately after the injection process, a possible correction can be made even before the turbine blade is removed from the coating machine. In this way, no re-clamping of the turbine blade in the coating machine is necessary, thereby ensuring that the orientation of the turbine blade during correction coincides with the orientation during the original spraying process.
  • the correction takes place by applying a correction coating by means of a further spraying process after the completion of the spraying process for which the web data and the process data were recorded in a time-resolved manner. This may be done immediately following the application of the original coating having the deviation, so that it is not necessary to clamp and relock the blade into the coating machine.
  • the web data and the process data for the further injection process are derived from the deviation of the simulated injection process obtained with the simulated injection process Coating determined from the desired coating.
  • the injection process is simulated during the execution of that injection process in which the web data and the process data are recorded in a time-resolved manner.
  • an online simulation of this injection process takes place during the original injection process.
  • online simulation offers the possibility of correcting the process data of the current injection process by means of correction data.
  • the correction data are determined from the deviation of the simulated coating obtained from the simulated injection process from the desired coating.
  • the application of the coating and the correction of the coating can take place in the same injection process.
  • the correction data are determined within a time period in the range of less than 5 seconds, in particular less than 1 second, and preferably in the range of less than 100 milliseconds, so that a rapid correction is possible, d. H. as long as the spray nozzle is still in or near the coating area to be corrected.
  • updated path data and / or updated process data can be determined based on the deviation of the simulated coating obtained from the simulated spraying process based on which the web data and / or the process data for the next for a component with the same Geometry of the surface to be coated to be performed injection process to be updated. In this way, in the case of the next component, the deviations between the simulated coating detected in the previously coated component and the actual coating avoided or at least reduced.
  • the deviation of the simulated coating obtained by the simulated injection process from the desired coating can be graphically represented.
  • Such a representation can provide an operator with meaningful information about the spraying process carried out. If the graphical representation is generated within a time range of less than 5 seconds, in particular less than 1 second, and preferably in the range of less than 100 milliseconds, an online monitoring of the injection process that has just been carried out can be achieved.
  • the monitoring device according to the invention together with a spraying device, makes it possible to carry out the method according to the invention and thus makes it possible to realize the properties and advantages described with reference to the method according to the invention. Reference is therefore made to the properties and advantages described with reference to the method according to the invention.
  • the latter additionally comprises a correction data calculation unit that is connected to the deviation calculation unit for receiving the calculated deviation.
  • the correction data calculation unit calculates correction data for Correcting the coating on the component surface to be coated if the calculated deviation exceeds a permissible deviation.
  • the correction data calculation unit therefore makes it possible to correct the applied coating as described above in the context of the method according to the invention, in particular if it is part of a coating device, which also has a spraying device with a spray nozzle which can be moved along a specific path relative to the component surface to be coated in the course of an injection process Having control unit for controlling the injection process.
  • this embodiment makes it possible to rework the web and process data for the application of the coating to the next component to be coated with the same surface geometry of the component surface to be coated.
  • the coating apparatus of the present embodiment includes a spraying apparatus 1 including a spray nozzle 3 and a control unit 5.
  • the spray nozzle 3 can be moved to apply a spray coating on a component surface to be coated component of a component relative to the component surface to be coated.
  • the component to be coated is a turbine component, namely an in FIG. 1
  • This turbine blade 7 has a blade blade 9, a blade platform 11 adjoining the blade blade 9, and a blade root 13 extending from the blade platform.
  • the component surface to be coated corresponds in such a turbine blade usually the surface of the blade 9 and parts of the surface of the blade platform 11.
  • the surface of the blade root and the blade root facing portions of the surface of the blade platform 11, however, are usually not spray-coated.
  • the present invention is described according to the embodiment by the spray coating of a turbine blade 7, the invention can also in the context of coating surfaces of other components, in particular other turbine components come into use. Examples of other turbine components include combustor liners or burner parts.
  • the spray device 1 has an in FIG. 1 not shown kinematics, which may be any suitable kinematics, which provides sufficient degrees of freedom to allow the coating of the surface to be coated of the turbine blade 7.
  • a robot arm can be used, in particular one that provides 6 degrees of freedom, namely 3 translatory degrees of freedom and 3 rotational degrees of freedom.
  • the control unit 5 of the spray device 1 controls the path along which the spray nozzle 3 is moved when coating the surface of the turbine blade 7 to be coated relative to the surface to be coated.
  • the control unit 5 controls the spraying parameters of the spraying process, which can be different parameters depending on the spraying method used. As parameters, for example, the feed rate at which the spray powder is supplied, and, depending on the spray method, an applied voltage, a feed rate for fuel gas, etc. into consideration.
  • Parameters that can be indirectly influenced by the controller are, for example, the kinetic energy with which the sprayed particles impinge on the component surface to be coated, the degree to which the sprayed particles are melted, the particles either not being melted at all, such as For example, during cold gas spraying, partially melted or completely melted.
  • atmospheric plasma spraying APS
  • low pressure plasma spraying LPPS
  • low vacuum plasma spraying LVPS
  • high velocity oxygen spraying HVOF
  • similar thermal spraying techniques are contemplated as spraying techniques.
  • the coating device according to the invention further comprises a monitoring device according to the invention with which the injection process can be monitored.
  • This monitoring device 14 comprises an input interface 15, via which geometry data of the surface to be coated can be entered into the monitoring device.
  • the geometry data can be obtained, for example, from a computer-implemented model of the turbine blade 7.
  • the geometric data may also include data on the position and orientation of the turbine blade 7 or of the respective component to be coated in the coating device.
  • the monitoring device comprises a web data acquisition unit 17 and a process data acquisition unit 19.
  • the two units are connected to the control unit 5 of the spray device 1 and receive from the control unit 5 time-resolved the web data of the spray nozzle 13 relative to the surface to be coated of the turbine blade 7 or time-resolved process data, which are the basis of the injection process.
  • the web data contains both data on the position of the spray nozzle and on their orientation, in each case relative to the component surface to be coated.
  • the time-resolved acquisition of the process data can be coupled to the time-resolved detection of the web data, so that in each case a pair of the web data and the associated process data is formed for any time.
  • the position and orientation of the spray nozzle relative to the surface to be coated is known for each time of detecting web data, this position and the associated orientation of the spray nozzle for each time acquiring the process data.
  • the monitoring device comprises 14, a simulation unit 21 connected to receive the geometry data for the surface to be coated with the input interface 15, receive the time-resolved trajectory data with the trajectory data acquisition unit 17 and receive the time-resolved process data with the process data acquisition unit 19.
  • the simulation unit the application of the spray coating to the surface of the turbine blade 7 to be coated is simulated on the basis of the geometry of the surface to be coated, the time-resolved path data and the time-resolved process data. The result of the simulation keeps the simulation unit ready for output in the form of simulation data.
  • a deviation calculation unit 23 for receiving the simulation data is connected to the simulation unit 21.
  • the deviation calculation unit 23 calculates a deviation of the simulated coating from the desired coating on the basis of the simulation data. Deviations may be present, for example, with regard to the layer thickness or the layer quality. Deviations in layer quality may be, for example, deviations in the microstructure of the simulated layer from the desired microstructure or deviations in the porosity of the simulated layer from the desired porosity.
  • the determined deviation is output to a display unit 25 connected to the deviation calculation unit 23, which generates a display signal which enables the visual representation of the deviation on a monitor 27 or another suitable display unit.
  • the operator of the sprayer receives meaningful information on possible risks during the injection process carried out.
  • the determined deviation of the simulated coating from the desired coating is in the present embodiment, moreover, to a correction data calculation unit connected to the deviation calculation unit 29 issued.
  • the correction data calculation unit 29 checks whether the deviation calculated by the deviation calculation unit 23 exceeds an allowable deviation. If this is the case, the correction data calculation unit calculates correction data with which the coating on the component surface to be coated can be corrected.
  • a correction of the original coating can then be carried out, for example, in a further coating process carried out after completion of the original coating process.
  • the second coating process can be carried out immediately after completion of the first coating process, so that the turbine blade can remain clamped in the coating device.
  • the correction data for correcting the coating can, as shown in the present exemplary embodiment, be output by the correction data calculation unit directly to the control unit 5 of the spray device 1, so that an automated correction can take place.
  • the correction still takes place in the context of the original coating process.
  • the simulation of the coating process the calculation of the deviation of the simulated coating from the desired coating and the calculation of the correction data with a short time offset to the current coating process takes place.
  • the time offset should be as small as possible to be less than 5 seconds, in particular less than 1 second, and preferably in the range of less than 100 milliseconds in order to act as quickly as possible on the currently performed coating process can.
  • selected stopping points are present in the program sequence in the control program for the injection process, on which the process data and / or the web data of the coating process can be updated.
  • the control program running in the control unit 5 of the spray device must enable an up-and-download of control programs or process and / or trajectory data.
  • the described monitoring of the spraying process allows the web data and / or process data for the next spraying process to be matched with an identical surface to be coated to reduce or eliminate the observed deviation of the simulated coating from the desired coating.
  • FIG. 2 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110.
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • Such alloys are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 are known from the EP 0 486 489 B1 .
  • MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 3 shows a perspective view of a blade 120 or guide vane 130 of a turbomachine, which extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjacent thereto and an airfoil 406 and a blade tip 415.
  • the blade 130 may have at its blade tip 415 another platform (not shown).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the airfoil 406.
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • the blade 120, 130 can be made by a casting process, also by 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 which are exposed to high mechanical, thermal and / or chemical stresses during operation.
  • Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, i.e., grains that run the full length of the workpiece and here, in common usage, are referred to as directionally solidified) or a monocrystalline structure, i. the whole workpiece consists of a single crystal.
  • a columnar grain structure columnar, i.e., grains that run the full length of the workpiece and here, in common usage, are referred to as directionally solidified
  • a monocrystalline structure i. the whole workpiece consists of a single crystal.
  • directionally solidified microstructures which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. M is at least one element of 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 ones Earth, or hafnium (Hf)).
  • M is at least one element of 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 ones Earth, or hafnium (Hf)).
  • Such alloys are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 are known from the EP 0 486 489 B1 .
  • the density is preferably 95% of the theoretical density.
  • the layer composition comprises Co-30Ni-28Cr-8Al-0.6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10A1-0,4Y-1 are also preferably used , 5RE.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • the thermal barrier coating covers the entire MCrAlX layer.
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 4 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a plurality of burners 107 arranged around a rotation axis 102 in the circumferential direction open into a common combustion chamber space 154, which generate flames 156.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M side with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 made of an alloy is equipped on the working medium side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least one element of 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).
  • MCrAlX means: M is at least one element of 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 the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 is known from the EP 0 486 489 B1 .
  • a ceramic thermal barrier coating may be present and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • thermal barrier coating may 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 (eg by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired. Thereafter, a re-coating of the heat shield elements 155 and a renewed use of the heat shield elements 155.
  • the heat shield elements 155 are then, for example, hollow and possibly still have cooling holes (not shown) which open into the combustion chamber space 154.
  • a process simulation in particular of layer thickness and / or quality of a spray coating on the basis of the detected real web data and the acquired real process data has been described.
  • this simulation can take place after the coating of a component or during the process with a short time offset.
  • a correction coating can be proposed and the (component) individual coating program required for this (including web data for the robot arm or a CNC machine and including adapted process data) take place directly after the coating has already taken place, so that no re-clamping of the component is required.
  • the simulating subsequently allows the coating of the component to adapt all coating parameters, including web data for the next component to be coated. As a result, significantly lower fluctuations in the layer quality and the layer thickness can be generated.
  • the simulation takes place during the injection process with a short time offset, as described a direct influence on the process data and the web data of the spraying process is possible.
  • simulating during the process with a short time offset can also be a visual representation of the process progress, to provide the operator with meaningful pointers to potential risks.
  • the present invention has been described with reference to an embodiment, it should be understood that this embodiment is merely illustrative of the invention and that variations from this embodiment are possible.
  • the correction data calculation unit and / or the presentation unit need not necessarily be present.
  • the time-resolved process data are coupled to the time-resolved path data in order to associate the time-resolved process data about the path data with a position and an orientation of the spray nozzle relative to the component surface.
  • a device which detects the orientation and position of the spray nozzle relative to the component surface to be coated independently of the web data.
  • the optical detection of the component and the spray nozzle at different angles together with an image analysis software is conceivable. It is also possible to detect the web data in this way, so that the web data acquisition unit need not be connected to the control unit of the spray device.

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  • 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)
  • Spray Control Apparatus (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
EP14188316.5A 2013-11-20 2014-10-09 Procédé et dispositif d'application automatique d'un revêtement par pulvérisation Not-in-force EP2876183B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013223688.3A DE102013223688A1 (de) 2013-11-20 2013-11-20 Verfahren und Vorrichtung zum automatisierten Aufbringen einer Spritzbeschichtung

Publications (3)

Publication Number Publication Date
EP2876183A2 true EP2876183A2 (fr) 2015-05-27
EP2876183A3 EP2876183A3 (fr) 2015-06-03
EP2876183B1 EP2876183B1 (fr) 2019-04-17

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US (1) US20150140199A1 (fr)
EP (1) EP2876183B1 (fr)
DE (1) DE102013223688A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
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WO2016055325A1 (fr) * 2014-10-06 2016-04-14 Siemens Aktiengesellschaft Surveillance et commande d'une opération de revêtement avec distribution de chaleur sur la pièce

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015219055A1 (de) * 2015-10-01 2017-04-06 Volkswagen Aktiengesellschaft Verfahren und Beschichtung zum Schutz eines Bauteils vor Korrosion
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EP2876183A3 (fr) 2015-06-03
DE102013223688A1 (de) 2015-05-21
EP2876183B1 (fr) 2019-04-17

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