CA2383082A1 - Method and device for the surface threatment of a component - Google Patents
Method and device for the surface threatment of a component Download PDFInfo
- Publication number
- CA2383082A1 CA2383082A1 CA002383082A CA2383082A CA2383082A1 CA 2383082 A1 CA2383082 A1 CA 2383082A1 CA 002383082 A CA002383082 A CA 002383082A CA 2383082 A CA2383082 A CA 2383082A CA 2383082 A1 CA2383082 A1 CA 2383082A1
- Authority
- CA
- Canada
- Prior art keywords
- component
- coating
- blasting
- base body
- particle
- 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.)
- Abandoned
Links
- 238000000034 method Methods 0.000 title claims abstract description 67
- 239000002245 particle Substances 0.000 claims abstract description 129
- 239000000463 material Substances 0.000 claims abstract description 46
- 238000004381 surface treatment Methods 0.000 claims abstract description 34
- 238000005422 blasting Methods 0.000 claims description 78
- 238000000576 coating method Methods 0.000 claims description 61
- 239000011248 coating agent Substances 0.000 claims description 55
- 238000009434 installation Methods 0.000 claims description 12
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 10
- 238000002485 combustion reaction Methods 0.000 claims description 10
- 229910045601 alloy Inorganic materials 0.000 claims description 9
- 239000000956 alloy Substances 0.000 claims description 9
- 239000000919 ceramic Substances 0.000 claims description 8
- 239000011651 chromium Substances 0.000 claims description 7
- 229910017052 cobalt Inorganic materials 0.000 claims description 5
- 239000010941 cobalt Substances 0.000 claims description 5
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 5
- 229910052759 nickel Inorganic materials 0.000 claims description 5
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical group [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 4
- 229910052804 chromium Inorganic materials 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052727 yttrium Inorganic materials 0.000 claims description 3
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims description 3
- 229910052742 iron Inorganic materials 0.000 claims description 2
- 229910052702 rhenium Inorganic materials 0.000 claims description 2
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 claims description 2
- 230000003746 surface roughness Effects 0.000 abstract description 21
- 239000010410 layer Substances 0.000 description 40
- 239000007789 gas Substances 0.000 description 20
- 239000012720 thermal barrier coating Substances 0.000 description 15
- 238000004140 cleaning Methods 0.000 description 8
- 238000002360 preparation method Methods 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000005240 physical vapour deposition Methods 0.000 description 5
- 238000007750 plasma spraying Methods 0.000 description 5
- 230000004913 activation Effects 0.000 description 4
- 229910052593 corundum Inorganic materials 0.000 description 4
- 239000010431 corundum Substances 0.000 description 4
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 4
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 description 4
- 229910000601 superalloy Inorganic materials 0.000 description 4
- 229910001928 zirconium oxide Inorganic materials 0.000 description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000001513 hot isostatic pressing Methods 0.000 description 3
- 239000011241 protective layer Substances 0.000 description 3
- 235000019592 roughness Nutrition 0.000 description 3
- 229910000951 Aluminide Inorganic materials 0.000 description 2
- 229910001018 Cast iron Inorganic materials 0.000 description 2
- BPQQTUXANYXVAA-UHFFFAOYSA-N Orthosilicate Chemical compound [O-][Si]([O-])([O-])[O-] BPQQTUXANYXVAA-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 238000005328 electron beam physical vapour deposition Methods 0.000 description 2
- 238000010894 electron beam technology Methods 0.000 description 2
- 229910000765 intermetallic Inorganic materials 0.000 description 2
- 229910052746 lanthanum Inorganic materials 0.000 description 2
- -1 lanthanum aluminate Chemical class 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 2
- 239000004576 sand Substances 0.000 description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 2
- 229910010271 silicon carbide Inorganic materials 0.000 description 2
- 229910002076 stabilized zirconia Inorganic materials 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 239000006004 Quartz sand Substances 0.000 description 1
- WGLPBDUCMAPZCE-UHFFFAOYSA-N Trioxochromium Chemical compound O=[Cr](=O)=O WGLPBDUCMAPZCE-UHFFFAOYSA-N 0.000 description 1
- MCMNRKCIXSYSNV-UHFFFAOYSA-N ZrO2 Inorganic materials O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 229910000420 cerium oxide Inorganic materials 0.000 description 1
- 229910000423 chromium oxide Inorganic materials 0.000 description 1
- 238000012885 constant function Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009499 grossing Methods 0.000 description 1
- 229910052735 hafnium Inorganic materials 0.000 description 1
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229910044991 metal oxide Inorganic materials 0.000 description 1
- 150000004706 metal oxides Chemical class 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 229910003455 mixed metal oxide Inorganic materials 0.000 description 1
- 150000004767 nitrides Chemical class 0.000 description 1
- BMMGVYCKOGBVEV-UHFFFAOYSA-N oxo(oxoceriooxy)cerium Chemical compound [Ce]=O.O=[Ce]=O BMMGVYCKOGBVEV-UHFFFAOYSA-N 0.000 description 1
- SIWVEOZUMHYXCS-UHFFFAOYSA-N oxo(oxoyttriooxy)yttrium Chemical compound O=[Y]O[Y]=O SIWVEOZUMHYXCS-UHFFFAOYSA-N 0.000 description 1
- 229910052697 platinum Inorganic materials 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 229910052596 spinel Inorganic materials 0.000 description 1
- 239000011029 spinel Substances 0.000 description 1
- 229910052566 spinel group Inorganic materials 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/06—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for producing matt surfaces, e.g. on plastic materials, on glass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C3/00—Abrasive blasting machines or devices; Plants
- B24C3/02—Abrasive blasting machines or devices; Plants characterised by the arrangement of the component assemblies with respect to each other
- B24C3/04—Abrasive blasting machines or devices; Plants characterised by the arrangement of the component assemblies with respect to each other stationary
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/02—Pretreatment of the material to be coated
- C23C14/028—Physical treatment to alter the texture of the substrate surface, e.g. grinding, polishing
-
- 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
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/10—Manufacture by removing material
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Exposure And Positioning Against Photoresist Photosensitive Materials (AREA)
- Analysing Materials By The Use Of Radiation (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a method for treating the surface of a part (1) having a curved surface (3). According to the invention, material is removed from the surface (3) of the part along a contour line (9), which is located on the surface (3) of the part, by means of a particle stream (7) generated by a particle source (5). To this end, at least one of the stream parameters is specifically adapted to the contour line (9) in such a manner that a desired, especially homogeneous, surface roughness appears along the contour line (9).
The invention also relates to a jet system (47) for carrying out an automated surface treatment of a part (1).
The invention also relates to a jet system (47) for carrying out an automated surface treatment of a part (1).
Description
A
Description Method and device for the surface treatment of a component The invention relates to a method for the surface treatment of a component having a curved component surface, in which material is removed from the component surface by means of a particle jet which is generated from a particle source. The invention also relates to a device for the surface treatment of a component having a curved component surface.
The book "Plasma Spraying of Metallic and Ceramic Materials" by D. Matejka and B. Benko, John Wiley &
Sons, Chichester, U.K., 1989, has disclosed the method of plasma spraying together with applications, for example on components of an internal combustion engine of a motor vehicle. The section 6.1 "Preliminary preparation of surface prior to spraying" describes various methods which are used to prepare a component which is to be coated. This section describes a method for cleaning the surface of the product by means of a jet of abrasive particles prior to the actual coating operation. The abrasive particles are entrained in a compressed-air stream and preferably impinge on the surface to be treated at right angles. The blasting treatment with the abrasive particles can be carried out in a chamber or using a suction device, so that substantially the entire quantity of abrasive particles is recovered and is available for a further blasting treatment. Abrasive particles can in this case be produced from cast iron, steel from synthetic corundum (aluminum oxide A1203), silicon carbide or silicate sand (quartz sand). The abrasive particles may have a diameter of between 350 ~m and 1400 Vim. The blasting is preferably carried out by means of what is referred to as grit blasting, in which the abrasive particles , CA 02383082 2002-02-27 are corundum particles with a diameter of between 200 ~m and 800 ~tm. These particles are used to prepare a surface having a coating with a layer thickness of up to 200 ~,m, which coating is applied to the prepared surface in a coating process. Particle diameters of up to 1400 ~m are used for coatings with a greater layer thickness. The compressed air in which the abrasive particles are entrained is preferably at a pressure of up to 0.35 MPa when using corundum.
US patent 4,321,310 has described a method for producing a coating on a gas turbine component which is a turbine blade or vane . The turbine blade or vane has a base body made from a base material. The base material used is a cobalt-base or nickel-base alloy, such as for example IN 100, MAR M200, MAR M509 or WI 52. A bonding layer of the type MCrAlY is applied to this base material. In this context, M denotes, for example, a combination of the metals nickel and cobalt.
Cr represents chromium, A1 represents aluminum and Y
represents yttrium. A ceramic layer of zirconium oxide, which is grown on in columnar form, the columns being oriented substantially perpendicular to the surface of the base body, is applied to this bonding layer. Prior to the application of the zirconium oxide layer used as thermal barrier coating to the bonding layer, the bonding layer is polished until a surface roughness of approximately 1 ~m is established.
US patent 5,683,825 likewise reveals a method for applying a thermal barrier coating to a component of a gas turbine. An NiCrAlY bonding layer is applied to a base body by low-pressure plasma spraying. The surface of the bonding layer is polished, so that it has a surface roughness of approximately 2 Vim. A ceramic thermal barrier coating comprising yttrium-stabilized zirconia is applied to the bonding layer which has been polished in this way by means of a physical vapor deposition (PVD) method. The thermal barrier coating is in this case preferably applied using the electron beam PVD method. The thermal barrier coating may also be applied by means of plasma spraying. US patent 5,498,484 likewise describes the application of a thermal barrier coating to a bonding layer of a component of a gas turbine. The mean surface roughness of the bonding layer is given as being at least over 10 Vim.
US patent 5,645,893 relates to a coated component having a base body made from a superalloy and having a bonding layer and a thermal barrier coating. The bonding layer includes a platinum aluminide and an adjoining thin oxide layer. The thin oxide layer includes aluminum oxide. This oxide layer is adjoined by the thermal barrier coating, which is applied by means of the electron beam PVD method. In this case, yttrium-stabilized zirconia is applied to the bonding layer. Prior to the application of the bonding layer, the surface of the base body is cleaned by means of a grit blasting method. Alumina grit is used for the material-removing preparation of the base body.
WO 97/047781 A1 has disclosed a gas turbine component, for example a gas turbine blade or vane or a heat shield element of a combustion chamber. The base material of the gas turbine component is a nickel-base or cobalt-base superalloy. A bond coat comprising a nitride is applied to the base material. The bond coat is adjoined by a ceramic thermal barrier coating. The surface of the bond coat has a mean surface roughness of over 6 Vim, in particular between 9 ~m and 14 Vim.
Description Method and device for the surface treatment of a component The invention relates to a method for the surface treatment of a component having a curved component surface, in which material is removed from the component surface by means of a particle jet which is generated from a particle source. The invention also relates to a device for the surface treatment of a component having a curved component surface.
The book "Plasma Spraying of Metallic and Ceramic Materials" by D. Matejka and B. Benko, John Wiley &
Sons, Chichester, U.K., 1989, has disclosed the method of plasma spraying together with applications, for example on components of an internal combustion engine of a motor vehicle. The section 6.1 "Preliminary preparation of surface prior to spraying" describes various methods which are used to prepare a component which is to be coated. This section describes a method for cleaning the surface of the product by means of a jet of abrasive particles prior to the actual coating operation. The abrasive particles are entrained in a compressed-air stream and preferably impinge on the surface to be treated at right angles. The blasting treatment with the abrasive particles can be carried out in a chamber or using a suction device, so that substantially the entire quantity of abrasive particles is recovered and is available for a further blasting treatment. Abrasive particles can in this case be produced from cast iron, steel from synthetic corundum (aluminum oxide A1203), silicon carbide or silicate sand (quartz sand). The abrasive particles may have a diameter of between 350 ~m and 1400 Vim. The blasting is preferably carried out by means of what is referred to as grit blasting, in which the abrasive particles , CA 02383082 2002-02-27 are corundum particles with a diameter of between 200 ~m and 800 ~tm. These particles are used to prepare a surface having a coating with a layer thickness of up to 200 ~,m, which coating is applied to the prepared surface in a coating process. Particle diameters of up to 1400 ~m are used for coatings with a greater layer thickness. The compressed air in which the abrasive particles are entrained is preferably at a pressure of up to 0.35 MPa when using corundum.
US patent 4,321,310 has described a method for producing a coating on a gas turbine component which is a turbine blade or vane . The turbine blade or vane has a base body made from a base material. The base material used is a cobalt-base or nickel-base alloy, such as for example IN 100, MAR M200, MAR M509 or WI 52. A bonding layer of the type MCrAlY is applied to this base material. In this context, M denotes, for example, a combination of the metals nickel and cobalt.
Cr represents chromium, A1 represents aluminum and Y
represents yttrium. A ceramic layer of zirconium oxide, which is grown on in columnar form, the columns being oriented substantially perpendicular to the surface of the base body, is applied to this bonding layer. Prior to the application of the zirconium oxide layer used as thermal barrier coating to the bonding layer, the bonding layer is polished until a surface roughness of approximately 1 ~m is established.
US patent 5,683,825 likewise reveals a method for applying a thermal barrier coating to a component of a gas turbine. An NiCrAlY bonding layer is applied to a base body by low-pressure plasma spraying. The surface of the bonding layer is polished, so that it has a surface roughness of approximately 2 Vim. A ceramic thermal barrier coating comprising yttrium-stabilized zirconia is applied to the bonding layer which has been polished in this way by means of a physical vapor deposition (PVD) method. The thermal barrier coating is in this case preferably applied using the electron beam PVD method. The thermal barrier coating may also be applied by means of plasma spraying. US patent 5,498,484 likewise describes the application of a thermal barrier coating to a bonding layer of a component of a gas turbine. The mean surface roughness of the bonding layer is given as being at least over 10 Vim.
US patent 5,645,893 relates to a coated component having a base body made from a superalloy and having a bonding layer and a thermal barrier coating. The bonding layer includes a platinum aluminide and an adjoining thin oxide layer. The thin oxide layer includes aluminum oxide. This oxide layer is adjoined by the thermal barrier coating, which is applied by means of the electron beam PVD method. In this case, yttrium-stabilized zirconia is applied to the bonding layer. Prior to the application of the bonding layer, the surface of the base body is cleaned by means of a grit blasting method. Alumina grit is used for the material-removing preparation of the base body.
WO 97/047781 A1 has disclosed a gas turbine component, for example a gas turbine blade or vane or a heat shield element of a combustion chamber. The base material of the gas turbine component is a nickel-base or cobalt-base superalloy. A bond coat comprising a nitride is applied to the base material. The bond coat is adjoined by a ceramic thermal barrier coating. The surface of the bond coat has a mean surface roughness of over 6 Vim, in particular between 9 ~m and 14 Vim.
2 has described a method for producing a protective coating on a base body which is designed to be exposed to hot gases in order to protect against oxidation and/or corrosion. The protective layer is compressed by a hot isostatic pressing method, during which it remains unsealed. In the process, the protective layer remains chemically substantially unchanged. During the hot isostatic pressing, a pressure exerted by a compressed gas is used to compress the porous protective layer for a time of between approximately 0.1 and 3 hours at temperatures of from approximately 800°C to 1200°C. Unlike the documents mentioned above, the hot isostatic pressing is a surface treatment which does not involve removal of material.
It is an object of the invention to describe a method for the surface treatment of a component. It is a further object of the invention to provide a device for the surface treatment of a component.
According to the invention, the object relating to a method is achieved by a method for the surface treatment of a component (having a curved component surface, in which material is removed from the component surface along a contour line on the component surface by means of a particle jet which is generated from a particle source and is characterized by the jet parameters blasting distance, blasting intensity, blasting angle and blasting time, in which method at least one of the jet parameters is deliberately matched to the contour line in such a way that a homogeneous surface roughness is established along the contour line.
The invention is based on the consideration that irregularities in the component surface and uneven removal of material during the material-removing 1999P03591W0 - 4a -preparation of component surfaces have an adverse effect on the quality of the component surface and therefore on its usability. In methods for the surface treatment of components which have been disclosed hitherto, in particular in the case of material-removing preparation, uniform surface preparation of the component is not ensured over the entire component surface or over relatively large adjoining regions of the component surface. Particularly in the case of components with a complex component geometry, in particular with a curved component surface, the curvature leads to a local variation in the jet parameters. By way of example, a complex component geometry leads to a variation in the jet distance, i.e.
the distance from the particle source to the component surface which is to be treated, which leads, for example, to different surface roughnesses in different areas of the component surface. This is true in particular of those areas of the component surface which have a different curvature. Furthermore, those areas of the component surface which have a curvature which varies greatly on a local basis and those areas which are difficult for the particle jet to gain access to using conventional methods are subject to irregularities (inhomogeneities) in the surface structure. Furthermore, only limited reproducibility can be ensured in the surface treatment of a multiplicity of components.
The method has for the first time taken account of characteristic jet parameters of the particle jet in relation to the local component geometry. In this context, the term blasting distance refers to the distance from the particle source to the point of impingement of the particle jet on the component surface. The blasting angle is defined in a local, component-related system of coordinates. In this reference system, the blasting angle is the angle between the blasting direction of the particle jet and the local normal to the component surface at the point of impingement of the particle jet on the component surface. The blasting intensity is understood as , 1999P03591W0 - 5a -meaning the number of particles emitted from the particle force per second and solid angle, i.e. the blasting intensity is given as a particle flow rate.
The number of particles which impinge each second on a local surface region on the component surface therefore results in a simple way from the blasting distance, the size of the surface region and the blasting angle. The blasting time is understood as meaning the residence time of the particle jet on a selected section of the contour line. The residence of the particle jet and therefore the number of particles which locally impinge on the component surface can be varied by means of the speed at which the particle jet is guided along the contour line.
The method allows the amount of material removed from the component surface to be deliberately matched to the geometry of the component. In this way, it is possible to produce a predeterminable homogeneous surface roughness along the contour line. As a result of a plurality of cohesive contour lines being tracked in succession, it is possible for large areas of the component surface to be treated and homogenized in terms of their roughness. In particular, the entire component surface can be subjected to a surface treatment of this type.
For an efficient application of the method, the method will preferably be operated continuously. For this purpose, the particle jet is guided along the contour line as a continuous function of time. As an alternative, the removal of material from the component surface along the contour line could also be carried out discontinuously, with the method being temporarily interrupted. With the method, it is possible to deliberately set the surface roughness characteristic variables, for example maximum profile height, maximum profile depth, roughness average. The roughness average, that is to say the arithmetic mean of the absolute values of the profile deviations within a reference distance (e. g. a partial section of a contour line) is in this case preferably used to compare surfaces of identical or similar character.
It is also possible for various partial regions of the 1999P03591W0 - 6a -component surface, which may, for example, be differently curved or oriented, to be deliberately produced with different predeterminable surface roughnesses. Each partial region in this case has a homogeneous surface roughness. Where appropriate and intended, it would also be possible for the surface roughness to be set according to a predeterminable, optionally non-constant function along a contour line.
By means of the blasting matched to the contour line using the particle jet, the component surface is smoothed in order to set a predetermined surface roughness in a predetermined region of the component surface.
Furthermore, the blasting with the particle jet can be used for surface cleaning of the component surface, leading to activation of the component surface. In this way, the component surface is prepared for other methods for example methods which follow the surface treatment.
It is preferable for the jet parameters to be adapted automatically. This ensures good reproducibility.
Furthermore, manual interventions in the method are no longer required.
It is preferable for the particle source and the component to be moved relative to one another. This involves relative translational movements, relative rotational movements and or combinations of translational movements and rotational movements. This relative movement of particle source and component makes it possible to guide the particle jet to a desired location and along a contour line on the component surface. The speed at which the relative movements are carried out allows the blasting time to be varied. Particularly in the case of components with a complex component geometry, for example with a curved component surface, the relative movements are used to influence jet parameters, such as for example blasting angle and blasting distance. A wide range of operating modes with regard to the relative movements of component and particle source are possible. A few preferred configurations in the method are described below:
In a preferred configuration of the method, the particle source is moved relative to the component in such a way that the blasting distance is constant. As a result, given a constant blasting intensity of the particle source, the number of particles which impinge each second on a surface element of the component surface which is arranged at right angles at a constant blasting distance, is a constant value. Furthermore, it is preferable for the particle source to be moved relative to the component in such a way that the blasting angle is constant. If an operating mode in which both the blasting distance and the blasting angle are constant is selected, removal of material which is particularly is well matched to the geometry of the component is ensured, and in particular homogeneous surface treatment of the component is possible as a result.
The relative movements are carried out in such a way that, in a preferred method configuration, the particle source is moved in a plurality of axes with respect to the component which is simultaneously stationary. In this context, the term in a plurality of axes means that the particle source is moved along at least two Cartesian coordinate axes. The combination of movements in a first axis and in a second axis which is perpendicular thereto also allows the particle source to rotate about a rotation axis, for example about an axis which runs through the component (cf. Figure axis). Furthermore, it is preferable for the particle source to be moved in a plurality of axes with respect to the component which is simultaneously rotating.
Furthermore, it is preferable for the particle source to be moved in a plurality of axes with respect to the component which is simultaneously being moved in a ~
1999P03591W0 - 8a -plurality of axes.
Preferably, the component is moved in a plurality of axes with respect to the particle source which is simultaneously stationary. The wide range of different method configurations with regard to the relative movements provides a high level of flexibility.
The combination of the various movement modes allows very complex component geometries to be subj ected to a surface treatment in the method.
The component preferably has a base body with a base material, the base body having the component surface which, for a first coating to be applied to the base body, is treated with a first coating material. The blasting with a stream of particles leads to surface cleaning of the base body. This surface cleaning results in activation of the surface. As a result, particularly good bonding of a first coating to the base body is possible in a coating method. The method can therefore be used as a subprocess of a method for producing a layer on a component. The method allows high-quality preparation of the component surface prior to a coating operation. This has a very advantageous effect on the coating which is to be applied to the base body, primarily its adhesion and layer quality.
The base body is produced, for example, from a metallic material. In this case, in the case of high-temperature applications, alloys which are able to withstand high temperatures, for example nickel, cobalt or chromium superalloys, are used as material for the base body.
In this case, it is preferable for an alloy or an intermetallic compound to be used as the first coating material in the coating process. The first coating material used is preferably an alloy which forms a bonding layer, such as for example an alloy of the type MCrAIX. In this context, M represents a metal, in particular one or more elements selected from the group consisting of nickel, cobalt and iron. Cr represents chromium and Al represents aluminum. X represents one or more elements selected from the group consisting of yttrium, rhenium and the rare earths, such as for example hafnium.
Alloys of this type are provided in particular in high-temperature applications.
The first coating preferably also has the component surface which, for a second coating to be applied to the component, is treated with a second layer material.
In a preferred configuration, the component has a base body with a base material, a first coating comprising a first coating material being applied to the base body, and the coated component, for a second coating to be applied to the component, being treated with a second coating material. The method is advantageously suitable not only for treating the surface of a base body, but also for the treatment and preparation of a layer which has been applied to the base body prior to the application of a further layer to the first layer. The method can therefore be integrated in a process for producing a layer system on a component. This allows very high-quality layer systems, which in particular have sufficient long-term stability and have a complex geometry of the base body, to be produced significantly more successfully.
In the coating process, it is preferable for a ceramic to be used as the second coating material. Examples of suitable ceramic materials are those which include zirconium oxide (Zr02), which has been partially or completely stabilized by yttrium oxide, cerium oxide or another oxide. A second coating of this type, which includes a ceramic, is, for example, a thermal barrier coating and as such has a layer thickness of approximately > 50 Vim, in particular approximately >
200 ~,m. A thermal barrier coating may also include other metal-ceramic oxides, in particular including metal-ceramic mixed oxide systems, for example perovskites (e. g. lanthanum aluminate), pyrochlores (e.g. lanthanum hafnate) or spinels such as ' CA 02383082 2002-02-27 for example the classic magnesium aluminate spinel MgA1204 .
A layer system on a metallic base body which has a bonding layer as the first coating and a thermal barrier coating, which adjoins the bonding layer, as second coating, is used in particular for high-temperature applications. In a preferred configuration of the method, the component is designed for a hot gas to flow around it. Furthermore, it is preferable for the component used to be a turbine rotor blade, a turbine guide vane or a heat shield element of a combustion chamber. Components of thermal machines, such as for example a gas turbine, an internal combustion engine, a furnace or the like, have to be designed to be exposed to a hot aggressive medium, in particular a hot gas. The temperatures to which a component is exposed during normal use may in this case be well over 1000°C.
The particle jet preferably includes abrasive particles which are entrained in a pressurized carrier medium, in particular compressed air. The abrasive particles preferably impinge on the component surface at a blasting angle of approximately 20° to 90°C, in particular of approximately 50° to 90°. The diameter of the abrasive particles, the blasting angle and the pressure of the pressurized carrier medium depend on the material of the abrasive particles, the material of the component surface on which they impinge, and on the effect which is to be achieved, in particular with regard to surface cleaning or removal of material in order to establish a desired surface roughness. If a large amount of material is to be removed, the angle at which the abrasive particles impinge on the surface is approximately between 50° and 90°, in particular approximately 60°. For cleaning and activation of the component surface, the angle is in a range between 20°
1999P03591W0 - lla -and 60° . The abrasive particles which are entrained in the carrier medium may be provided in the form of a powder or, if relatively large particles are present (globular particles), can be broken up by a milling process, in order to produce sharp-edged abrasive particles which then have an increased abrasive action on the component surf ace .
According to the invention, the object relating to a device for the surface treatment of a component is achieved by a blasting installation for the automated surface treatment of a component having a curved component surface, which installation has a particle source for generating a particle jet and a component holder for holding the component, the particle source and the component being movable relative to one another in such a way that , to produce a homogeneous component surface in a blasting process using the particle jet, the blasting distance and/or the blasting angle adopts a predetermined, in particular constant value along a contour line on the component surface.
The method and the device are explained in more detail with reference to the exemplary embodiments in the drawing, in which, in some cases not to scale and diagrammatically:
FIG 1 to FIG 3 show part of a base body of a component with a free, in particular curved component surface, FIG 4 shows part of a component in which a first coating has been applied to a base body, FIG 5 shows part of a component in which a first coating and a second coating have been applied to a base body, FIG 6 shows a perspective view of the turbine blade or vane, FIG 7 shows a heat shield element of a combustion chamber, in a perspective illustration, FIG 8 shows a blasting installation for surface treatment, with a component arranged in the blasting installation.
Identical reference symbols have the same meaning throughout the figures.
Figure 1 shows part of a base body 11 of a component 1 (cf. for example Figure 6 or 7) which is not shown in more detail and has a base material 13, in particular a nickel or cobalt superalloy. The base body 11 has a component surface 3. For surface treatment of the component surface 3, for example for pretreatment prior to the application of a coating to the component surface 3, the component surface 3 is blasted with abrasive particles 27 from a particle jet 7, which are entrained in a pressurized carrier medium 29, in particular compressed air 29. A particle source 5 is provided for generating a particle jet of this type comprising the carrier medium 29 and the abrasive particles 27 entrained therein. The treatment of the component surface 3 with abrasive particles 27 is used to smooth the component surface 3, producing a predetermined surface roughness. Furthermore, the blasting of the component surface is used to clean and activate the component surface. For this purpose, the abrasive particles 27 impinge on the component surface 3 at an angle a. The abrasive particles 27 in this case preferably consist of the base material 13 or of a material which is the same as a coating material which is to be applied to the base body 11 following the 1999P03591W0 - 13a -blasting with the abrasive particles 27. To achieve a desired, in particular homogeneous surface roughness, the particle source 5 can move relative to the component 1. The particle source 5 can execute movements along a horizontal axis 31 and along a vertical axis 33 relative to the component 1. Furthermore, the particle source 5 can rotate about an axis of rotation 35. The axis of rotation 35 extends perpendicular to a plane which is defined by the vertical axis 33 and the horizontal axis 31. Consequently, the particle jet 7 which is emitted from the particle source 5 can be guided along a contour line 9 on the component surface 3. In particular, different regions on the component surface 3 along the contour line 9 can be subjected to material-removing processing by the abrasive particles 27. To achieve a homogeneous surface roughness, the jet parameters are in the process deliberately matched to the contour line. This is illustrated in Figures 1 to 3, which show a chronological sequence of the surface treatment along the contour line 9. In this case, the particle source 5 is moved relative to the component 1 in such a way that the blasting distance d is constant.
At the same time, the particle source 5 is moved relative to the component 1 in such a way that the blasting angle a is constant. As a result, different regions of the component surface 3 along the contour line 9 can be treated in the same way. While Figure 1 shows a convexly curved region of the contour line 9 being treated by the particle jet 7, in Figure 2 the particle jet 7 is acting on a concavely curved region of the contour line 9. In Figure 3, the material-removing processing of the component surface 3 takes place in a region of the contour line 9 which is approximately planar. The particle source 5 is controlled automatically. In this case, by way of example, the precise component geometry, in particular the component surface, can be recorded by a measurement system (not shown), and this actual data can be compared with desired data. These data sets can be used 1999P03591W0 - 14a -as input data for a control system (not shown) which controls the particle source 5 in terms of the jet parameters relative to the component 1. The result is automatic surface treatment of the component 1.
Figure 4 shows the base body 11 from Figures 1 to 3, a first coating 15 comprising a first coating material 17 having been applied to the base body 11. The first coating is preferably a bonding layer and has been applied by means of a physical vapor deposition method, for example electron beam physical vapor deposition (EB-PVD) or a plasma spraying method. The first coating has a first coating material 17 which, particularly when coating a gas turbine component, is an alloy of the type MCrAlX or an aluminide. The first coating 15 has now formed a component surface 3 of the component 1 15 on that side of the coating 15 which is remote from the base body 11. This component surface 3 is now being prepared for the application of a second coating 19.
For this purpose, the surface 3 is blasted with abrasive particles 27 from the particle source 5. The abrasive particles 27 are entrained in a pressurized carrier medium 29 in a particle jet 7. Compressed air is preferably used as the carrier medium 29. The abrasive particles 27 impinge on the component surface 3 at a blasting angle a, which is identical to or different than the blasting angle a used in the blasting of the base body 11 shown in Figures 1 to 3.
The specific choice of the blasting angle a and of the blasting distance d and the pressure applied to the carrier medium 29 depends on the type of material used for the abrasive particles 27, the nature of the first coating material 17 and, for example, also on a surface roughness or cleaning of the component surface 3 which is to be achieved. During the material-removing surface treatment of the layer 15, the particle jet 7 is guided along a contour line 9 in such a manner that a surface roughness which is to be achieved and is generally homogeneous is established along the contour line. The method in particular allows contour lines 9 which are present on curved component surfaces 3 to be processed with high quality and reproducibility. It is advantageous that the first coating 15 has already been produced with a high boding capacity and a high creep strength on the base body 11 using the method.
Figure 5 shows part of the product l, in which, in addition to the first coating 15, a second coating 19 comprising a second coating material 21 is also been applied to the base body 11. An oxide layer 69 as interlayer 69 is arranged between the second coating 19, which in the case of a component of a gas turbine is preferably a thermal barrier coating comprising a metal oxide or a mixed metal oxide system, for example partially or fully stabilized zirconium oxide. This oxide layer 35 includes aluminum oxide and/or chromium oxide and may have been formed through thermal oxidation of the first coating 15 (thermally grown oxide, TGO) or has been applied to the first coating 15 in an intermediate step. Therefore, the method can be used for layer systems on components 1 with a complex component geometry with a complex component geometry, in particular with a curved component surface 3. As a result, the quality of a layer system is considerably improved.
Figure 6 shows a perspective view of a component 1, in this case a turbine rotor blade 23, which has a blade region 37 which has been coated with a coating 19, namely a thermal barrier coating. During operation of the turbine blade 23, for example in a gas turbine (not shown), a hot aggressive medium M, in particular a hot gas M, which results from combustion of a fuel, flows around the blade region 37. The blade region 37 is adjoined on one side by a securing region 39, in which the turbine rotor blade 23 of the gas turbine is secured, and on the other side by a cover plate 4lwhich is used to seal the turbine rotor blade 23 with respect to a further component (not shown) of the gas turbine. The turbine rotor blade 23 has a component surface 3 which has a complex component geometry with regions with a greatly differing curvature.
Figure 7 shows a perspective illustration of a component 1, a heat shield element 25 of a combustion chamber (not shown) of a gas turbine. The heat shield element 25 has a covering element 43 with a connection hole 45 arranged centrally therein. The connection hole 45 allows the covering element 43 to be guided over a connection element (not shown) and allows the heat shield element 25 to be secured to a wall (not shown) of the combustion chamber. A combustion chamber of a gas turbine is lined with a multiplicity of heat shield elements 25 of this type . Like the turbine rotor blade 23 shown in Figure 6, the heat shield element 25 has a complex, in particular curved component surface 3.
While the heat shield element 25 is in use, its thermal barrier coating 19 is exposed to a hot aggressive medium M, in particular a hot gas M.
Figure 8 shows a diagrammatic illustration, not to scale, of a blasting installation 47 for the automated surface treatment of a component 1. The blasting installation 47 has a blasting chamber 65 in which a component holder 49 is arranged. A component 1 is held by the component holder 49. The component 1 has a curved component surface 3. A first particle source 5A
and a second particle source 5B are arranged in the blasting chamber 65. The particle sources 5A, 5B are arranged in such a way that, for a blasting process, they reach opposite regions of the component surface 3.
To generate a particle jet 7A, 7B which includes abrasive particles 27 and a carrier medium 29, an abrasive particle reservoir 57 and a carrier medium reservoir 53 are provided in the blasting installation 47. The carrier medium reservoir 53 supplies the particle source 5A, 5B via a first supply line 51 for carrier medium 29. To supply the particle source 5A, 5B with abrasive particles 27, there is a supply line 55 for abrasive particles 27.
Furthermore, the blasting chamber 65 has an outlet system 59. The outlet system 59 is fitted, for example, as a suction device. In this way, substantially the entire quantity of the abrasively acting abrasive particles 27 can be recovered and reused for blasting.
The abrasive particles 27 may in this case be produced from cast iron, steel, from synthetic corundum (aluminum oxide, A1203), silicon carbide or silicate sand. In addition, abrasive particles 27 made from alloys or intermetallic compounds are possible. The particle source 5A, 5B and the component holder 49 together with the component 1 can move relative to one another. By way of example, the particle source 5A, 5B
can move in a plurality of axes with respect to the stationary component 1. Alternatively, the component 1 can move in a plurality of axes by means of the component holder 49, with respect to the particle source 5A, 5B. In particular, the component holder 49 with the component 1 is arranged so that it can rotate about a vertical axis of rotation 67. This is highly advantageous in particular for the material-removing surface treatment of rotationally symmetrical components 1. For automated surface treatment of the component 1, the blasting installation 47 is equipped with a control system 61. The particle source 5A, 5B
and the component holder 49 are connected to the control system 61 via respective control signal lines 63A, 63B, 63C. In this way, automated control of the movement of component 1 and particle source 5A, 5B is possible. In particular, the relevant jet parameters of the particle source 5A, 5B can be automatically controlled, so that to produce a 1999P03591W0 - 18a -preferably homogeneous component surface 3 in a blasting process, the blasting distance d and the blasting angle a along a contour line 9A, 9B on the component surface 3 adopt a predeterminable, preferably constant value. Fitting the blasting installation 47 with a plurality of particle sources 5A, 5B allows simultaneous surface treatment of the component 1 along various contour lines 9A, 9B on the component surface 3.
In a method for the surface treatment of the component 1 in the automated blasting installation 47, the particle source 5A, 5B is supplied with abrasive particles 27 and with carrier medium 29, in particular compressed air 29, via the reservoirs 53, 57. Material is removed from the component surface 3 along a contour line 9A, 9B on the component surface 3 by the particle jet 7A, 7B which is generated by means of the particle sources 5A, 5B and is characterized by the jet parameters blasting distance d, blasting angle a and blasting time. The blasting parameters are deliberately matched to the contour line 9A, 9B in such a way that a predetermined, preferably homogeneous surface roughness is established along the contour line 9A, 9B. In the process, the jet parameters are automatically adapted by means of the control system 61, which controls the relative movement of the component 1 and of the particle sources 5A, 5B. The mode of operation in which the particle source 5A, 5B is moved relative to the component 1 in such a way that the blasting distance d and the blasting angle a are constant is particularly favorable. The control system 61 is responsible for accurate positioning and controlling of component 1 and of the particle source 5A, 5B. This allows the surface treatment of components 1 with a complex geometry, in particular with a curved component surface 3, with high quality and reproducibility. This is highly advantageous in particular for series production of components 1 and their surface treatment.
The invention is distinguished by the fact that the component surface of a component which, in particular, has regions of different curvature is blasted with 1999P03591W0 - 19a -abrasive particles for the purpose of surface treatment of the component. This results in smoothing and/or cleaning with, if appropriate, activation of the component surface. The ' CA 02383082 2002-02-27 method is suitable for processing the base body of a component and for preliminary processing of a component which is to be coated. In particular, the method can be integrated in a method for producing a layer system on a base body of a component. The material-removing processing of the component surface is deliberately matched to the geometry of the component, resulting in a homogeneous surface treatment.
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11-13-2001 - a~ EP000804 1. A method for the surface treatment of a component ( 1 ) having a curved component surf ace ( 3 ) , in which material is removed from the component surface (3) along a contour line on the component surface (3) by means of a particle jet (7) which is generated from a particle source (5) and is characterized by the jet parameters blasting distance (d), blasting intensity, blasting angle (a) and blasting time, characterized in that during the surface treatment, at least once, at least one of the jet parameters is deliberately matched to the contour line in such a way that a homogeneous surface roughness is established along the contour line.
AMENDED SHEET
It is an object of the invention to describe a method for the surface treatment of a component. It is a further object of the invention to provide a device for the surface treatment of a component.
According to the invention, the object relating to a method is achieved by a method for the surface treatment of a component (having a curved component surface, in which material is removed from the component surface along a contour line on the component surface by means of a particle jet which is generated from a particle source and is characterized by the jet parameters blasting distance, blasting intensity, blasting angle and blasting time, in which method at least one of the jet parameters is deliberately matched to the contour line in such a way that a homogeneous surface roughness is established along the contour line.
The invention is based on the consideration that irregularities in the component surface and uneven removal of material during the material-removing 1999P03591W0 - 4a -preparation of component surfaces have an adverse effect on the quality of the component surface and therefore on its usability. In methods for the surface treatment of components which have been disclosed hitherto, in particular in the case of material-removing preparation, uniform surface preparation of the component is not ensured over the entire component surface or over relatively large adjoining regions of the component surface. Particularly in the case of components with a complex component geometry, in particular with a curved component surface, the curvature leads to a local variation in the jet parameters. By way of example, a complex component geometry leads to a variation in the jet distance, i.e.
the distance from the particle source to the component surface which is to be treated, which leads, for example, to different surface roughnesses in different areas of the component surface. This is true in particular of those areas of the component surface which have a different curvature. Furthermore, those areas of the component surface which have a curvature which varies greatly on a local basis and those areas which are difficult for the particle jet to gain access to using conventional methods are subject to irregularities (inhomogeneities) in the surface structure. Furthermore, only limited reproducibility can be ensured in the surface treatment of a multiplicity of components.
The method has for the first time taken account of characteristic jet parameters of the particle jet in relation to the local component geometry. In this context, the term blasting distance refers to the distance from the particle source to the point of impingement of the particle jet on the component surface. The blasting angle is defined in a local, component-related system of coordinates. In this reference system, the blasting angle is the angle between the blasting direction of the particle jet and the local normal to the component surface at the point of impingement of the particle jet on the component surface. The blasting intensity is understood as , 1999P03591W0 - 5a -meaning the number of particles emitted from the particle force per second and solid angle, i.e. the blasting intensity is given as a particle flow rate.
The number of particles which impinge each second on a local surface region on the component surface therefore results in a simple way from the blasting distance, the size of the surface region and the blasting angle. The blasting time is understood as meaning the residence time of the particle jet on a selected section of the contour line. The residence of the particle jet and therefore the number of particles which locally impinge on the component surface can be varied by means of the speed at which the particle jet is guided along the contour line.
The method allows the amount of material removed from the component surface to be deliberately matched to the geometry of the component. In this way, it is possible to produce a predeterminable homogeneous surface roughness along the contour line. As a result of a plurality of cohesive contour lines being tracked in succession, it is possible for large areas of the component surface to be treated and homogenized in terms of their roughness. In particular, the entire component surface can be subjected to a surface treatment of this type.
For an efficient application of the method, the method will preferably be operated continuously. For this purpose, the particle jet is guided along the contour line as a continuous function of time. As an alternative, the removal of material from the component surface along the contour line could also be carried out discontinuously, with the method being temporarily interrupted. With the method, it is possible to deliberately set the surface roughness characteristic variables, for example maximum profile height, maximum profile depth, roughness average. The roughness average, that is to say the arithmetic mean of the absolute values of the profile deviations within a reference distance (e. g. a partial section of a contour line) is in this case preferably used to compare surfaces of identical or similar character.
It is also possible for various partial regions of the 1999P03591W0 - 6a -component surface, which may, for example, be differently curved or oriented, to be deliberately produced with different predeterminable surface roughnesses. Each partial region in this case has a homogeneous surface roughness. Where appropriate and intended, it would also be possible for the surface roughness to be set according to a predeterminable, optionally non-constant function along a contour line.
By means of the blasting matched to the contour line using the particle jet, the component surface is smoothed in order to set a predetermined surface roughness in a predetermined region of the component surface.
Furthermore, the blasting with the particle jet can be used for surface cleaning of the component surface, leading to activation of the component surface. In this way, the component surface is prepared for other methods for example methods which follow the surface treatment.
It is preferable for the jet parameters to be adapted automatically. This ensures good reproducibility.
Furthermore, manual interventions in the method are no longer required.
It is preferable for the particle source and the component to be moved relative to one another. This involves relative translational movements, relative rotational movements and or combinations of translational movements and rotational movements. This relative movement of particle source and component makes it possible to guide the particle jet to a desired location and along a contour line on the component surface. The speed at which the relative movements are carried out allows the blasting time to be varied. Particularly in the case of components with a complex component geometry, for example with a curved component surface, the relative movements are used to influence jet parameters, such as for example blasting angle and blasting distance. A wide range of operating modes with regard to the relative movements of component and particle source are possible. A few preferred configurations in the method are described below:
In a preferred configuration of the method, the particle source is moved relative to the component in such a way that the blasting distance is constant. As a result, given a constant blasting intensity of the particle source, the number of particles which impinge each second on a surface element of the component surface which is arranged at right angles at a constant blasting distance, is a constant value. Furthermore, it is preferable for the particle source to be moved relative to the component in such a way that the blasting angle is constant. If an operating mode in which both the blasting distance and the blasting angle are constant is selected, removal of material which is particularly is well matched to the geometry of the component is ensured, and in particular homogeneous surface treatment of the component is possible as a result.
The relative movements are carried out in such a way that, in a preferred method configuration, the particle source is moved in a plurality of axes with respect to the component which is simultaneously stationary. In this context, the term in a plurality of axes means that the particle source is moved along at least two Cartesian coordinate axes. The combination of movements in a first axis and in a second axis which is perpendicular thereto also allows the particle source to rotate about a rotation axis, for example about an axis which runs through the component (cf. Figure axis). Furthermore, it is preferable for the particle source to be moved in a plurality of axes with respect to the component which is simultaneously rotating.
Furthermore, it is preferable for the particle source to be moved in a plurality of axes with respect to the component which is simultaneously being moved in a ~
1999P03591W0 - 8a -plurality of axes.
Preferably, the component is moved in a plurality of axes with respect to the particle source which is simultaneously stationary. The wide range of different method configurations with regard to the relative movements provides a high level of flexibility.
The combination of the various movement modes allows very complex component geometries to be subj ected to a surface treatment in the method.
The component preferably has a base body with a base material, the base body having the component surface which, for a first coating to be applied to the base body, is treated with a first coating material. The blasting with a stream of particles leads to surface cleaning of the base body. This surface cleaning results in activation of the surface. As a result, particularly good bonding of a first coating to the base body is possible in a coating method. The method can therefore be used as a subprocess of a method for producing a layer on a component. The method allows high-quality preparation of the component surface prior to a coating operation. This has a very advantageous effect on the coating which is to be applied to the base body, primarily its adhesion and layer quality.
The base body is produced, for example, from a metallic material. In this case, in the case of high-temperature applications, alloys which are able to withstand high temperatures, for example nickel, cobalt or chromium superalloys, are used as material for the base body.
In this case, it is preferable for an alloy or an intermetallic compound to be used as the first coating material in the coating process. The first coating material used is preferably an alloy which forms a bonding layer, such as for example an alloy of the type MCrAIX. In this context, M represents a metal, in particular one or more elements selected from the group consisting of nickel, cobalt and iron. Cr represents chromium and Al represents aluminum. X represents one or more elements selected from the group consisting of yttrium, rhenium and the rare earths, such as for example hafnium.
Alloys of this type are provided in particular in high-temperature applications.
The first coating preferably also has the component surface which, for a second coating to be applied to the component, is treated with a second layer material.
In a preferred configuration, the component has a base body with a base material, a first coating comprising a first coating material being applied to the base body, and the coated component, for a second coating to be applied to the component, being treated with a second coating material. The method is advantageously suitable not only for treating the surface of a base body, but also for the treatment and preparation of a layer which has been applied to the base body prior to the application of a further layer to the first layer. The method can therefore be integrated in a process for producing a layer system on a component. This allows very high-quality layer systems, which in particular have sufficient long-term stability and have a complex geometry of the base body, to be produced significantly more successfully.
In the coating process, it is preferable for a ceramic to be used as the second coating material. Examples of suitable ceramic materials are those which include zirconium oxide (Zr02), which has been partially or completely stabilized by yttrium oxide, cerium oxide or another oxide. A second coating of this type, which includes a ceramic, is, for example, a thermal barrier coating and as such has a layer thickness of approximately > 50 Vim, in particular approximately >
200 ~,m. A thermal barrier coating may also include other metal-ceramic oxides, in particular including metal-ceramic mixed oxide systems, for example perovskites (e. g. lanthanum aluminate), pyrochlores (e.g. lanthanum hafnate) or spinels such as ' CA 02383082 2002-02-27 for example the classic magnesium aluminate spinel MgA1204 .
A layer system on a metallic base body which has a bonding layer as the first coating and a thermal barrier coating, which adjoins the bonding layer, as second coating, is used in particular for high-temperature applications. In a preferred configuration of the method, the component is designed for a hot gas to flow around it. Furthermore, it is preferable for the component used to be a turbine rotor blade, a turbine guide vane or a heat shield element of a combustion chamber. Components of thermal machines, such as for example a gas turbine, an internal combustion engine, a furnace or the like, have to be designed to be exposed to a hot aggressive medium, in particular a hot gas. The temperatures to which a component is exposed during normal use may in this case be well over 1000°C.
The particle jet preferably includes abrasive particles which are entrained in a pressurized carrier medium, in particular compressed air. The abrasive particles preferably impinge on the component surface at a blasting angle of approximately 20° to 90°C, in particular of approximately 50° to 90°. The diameter of the abrasive particles, the blasting angle and the pressure of the pressurized carrier medium depend on the material of the abrasive particles, the material of the component surface on which they impinge, and on the effect which is to be achieved, in particular with regard to surface cleaning or removal of material in order to establish a desired surface roughness. If a large amount of material is to be removed, the angle at which the abrasive particles impinge on the surface is approximately between 50° and 90°, in particular approximately 60°. For cleaning and activation of the component surface, the angle is in a range between 20°
1999P03591W0 - lla -and 60° . The abrasive particles which are entrained in the carrier medium may be provided in the form of a powder or, if relatively large particles are present (globular particles), can be broken up by a milling process, in order to produce sharp-edged abrasive particles which then have an increased abrasive action on the component surf ace .
According to the invention, the object relating to a device for the surface treatment of a component is achieved by a blasting installation for the automated surface treatment of a component having a curved component surface, which installation has a particle source for generating a particle jet and a component holder for holding the component, the particle source and the component being movable relative to one another in such a way that , to produce a homogeneous component surface in a blasting process using the particle jet, the blasting distance and/or the blasting angle adopts a predetermined, in particular constant value along a contour line on the component surface.
The method and the device are explained in more detail with reference to the exemplary embodiments in the drawing, in which, in some cases not to scale and diagrammatically:
FIG 1 to FIG 3 show part of a base body of a component with a free, in particular curved component surface, FIG 4 shows part of a component in which a first coating has been applied to a base body, FIG 5 shows part of a component in which a first coating and a second coating have been applied to a base body, FIG 6 shows a perspective view of the turbine blade or vane, FIG 7 shows a heat shield element of a combustion chamber, in a perspective illustration, FIG 8 shows a blasting installation for surface treatment, with a component arranged in the blasting installation.
Identical reference symbols have the same meaning throughout the figures.
Figure 1 shows part of a base body 11 of a component 1 (cf. for example Figure 6 or 7) which is not shown in more detail and has a base material 13, in particular a nickel or cobalt superalloy. The base body 11 has a component surface 3. For surface treatment of the component surface 3, for example for pretreatment prior to the application of a coating to the component surface 3, the component surface 3 is blasted with abrasive particles 27 from a particle jet 7, which are entrained in a pressurized carrier medium 29, in particular compressed air 29. A particle source 5 is provided for generating a particle jet of this type comprising the carrier medium 29 and the abrasive particles 27 entrained therein. The treatment of the component surface 3 with abrasive particles 27 is used to smooth the component surface 3, producing a predetermined surface roughness. Furthermore, the blasting of the component surface is used to clean and activate the component surface. For this purpose, the abrasive particles 27 impinge on the component surface 3 at an angle a. The abrasive particles 27 in this case preferably consist of the base material 13 or of a material which is the same as a coating material which is to be applied to the base body 11 following the 1999P03591W0 - 13a -blasting with the abrasive particles 27. To achieve a desired, in particular homogeneous surface roughness, the particle source 5 can move relative to the component 1. The particle source 5 can execute movements along a horizontal axis 31 and along a vertical axis 33 relative to the component 1. Furthermore, the particle source 5 can rotate about an axis of rotation 35. The axis of rotation 35 extends perpendicular to a plane which is defined by the vertical axis 33 and the horizontal axis 31. Consequently, the particle jet 7 which is emitted from the particle source 5 can be guided along a contour line 9 on the component surface 3. In particular, different regions on the component surface 3 along the contour line 9 can be subjected to material-removing processing by the abrasive particles 27. To achieve a homogeneous surface roughness, the jet parameters are in the process deliberately matched to the contour line. This is illustrated in Figures 1 to 3, which show a chronological sequence of the surface treatment along the contour line 9. In this case, the particle source 5 is moved relative to the component 1 in such a way that the blasting distance d is constant.
At the same time, the particle source 5 is moved relative to the component 1 in such a way that the blasting angle a is constant. As a result, different regions of the component surface 3 along the contour line 9 can be treated in the same way. While Figure 1 shows a convexly curved region of the contour line 9 being treated by the particle jet 7, in Figure 2 the particle jet 7 is acting on a concavely curved region of the contour line 9. In Figure 3, the material-removing processing of the component surface 3 takes place in a region of the contour line 9 which is approximately planar. The particle source 5 is controlled automatically. In this case, by way of example, the precise component geometry, in particular the component surface, can be recorded by a measurement system (not shown), and this actual data can be compared with desired data. These data sets can be used 1999P03591W0 - 14a -as input data for a control system (not shown) which controls the particle source 5 in terms of the jet parameters relative to the component 1. The result is automatic surface treatment of the component 1.
Figure 4 shows the base body 11 from Figures 1 to 3, a first coating 15 comprising a first coating material 17 having been applied to the base body 11. The first coating is preferably a bonding layer and has been applied by means of a physical vapor deposition method, for example electron beam physical vapor deposition (EB-PVD) or a plasma spraying method. The first coating has a first coating material 17 which, particularly when coating a gas turbine component, is an alloy of the type MCrAlX or an aluminide. The first coating 15 has now formed a component surface 3 of the component 1 15 on that side of the coating 15 which is remote from the base body 11. This component surface 3 is now being prepared for the application of a second coating 19.
For this purpose, the surface 3 is blasted with abrasive particles 27 from the particle source 5. The abrasive particles 27 are entrained in a pressurized carrier medium 29 in a particle jet 7. Compressed air is preferably used as the carrier medium 29. The abrasive particles 27 impinge on the component surface 3 at a blasting angle a, which is identical to or different than the blasting angle a used in the blasting of the base body 11 shown in Figures 1 to 3.
The specific choice of the blasting angle a and of the blasting distance d and the pressure applied to the carrier medium 29 depends on the type of material used for the abrasive particles 27, the nature of the first coating material 17 and, for example, also on a surface roughness or cleaning of the component surface 3 which is to be achieved. During the material-removing surface treatment of the layer 15, the particle jet 7 is guided along a contour line 9 in such a manner that a surface roughness which is to be achieved and is generally homogeneous is established along the contour line. The method in particular allows contour lines 9 which are present on curved component surfaces 3 to be processed with high quality and reproducibility. It is advantageous that the first coating 15 has already been produced with a high boding capacity and a high creep strength on the base body 11 using the method.
Figure 5 shows part of the product l, in which, in addition to the first coating 15, a second coating 19 comprising a second coating material 21 is also been applied to the base body 11. An oxide layer 69 as interlayer 69 is arranged between the second coating 19, which in the case of a component of a gas turbine is preferably a thermal barrier coating comprising a metal oxide or a mixed metal oxide system, for example partially or fully stabilized zirconium oxide. This oxide layer 35 includes aluminum oxide and/or chromium oxide and may have been formed through thermal oxidation of the first coating 15 (thermally grown oxide, TGO) or has been applied to the first coating 15 in an intermediate step. Therefore, the method can be used for layer systems on components 1 with a complex component geometry with a complex component geometry, in particular with a curved component surface 3. As a result, the quality of a layer system is considerably improved.
Figure 6 shows a perspective view of a component 1, in this case a turbine rotor blade 23, which has a blade region 37 which has been coated with a coating 19, namely a thermal barrier coating. During operation of the turbine blade 23, for example in a gas turbine (not shown), a hot aggressive medium M, in particular a hot gas M, which results from combustion of a fuel, flows around the blade region 37. The blade region 37 is adjoined on one side by a securing region 39, in which the turbine rotor blade 23 of the gas turbine is secured, and on the other side by a cover plate 4lwhich is used to seal the turbine rotor blade 23 with respect to a further component (not shown) of the gas turbine. The turbine rotor blade 23 has a component surface 3 which has a complex component geometry with regions with a greatly differing curvature.
Figure 7 shows a perspective illustration of a component 1, a heat shield element 25 of a combustion chamber (not shown) of a gas turbine. The heat shield element 25 has a covering element 43 with a connection hole 45 arranged centrally therein. The connection hole 45 allows the covering element 43 to be guided over a connection element (not shown) and allows the heat shield element 25 to be secured to a wall (not shown) of the combustion chamber. A combustion chamber of a gas turbine is lined with a multiplicity of heat shield elements 25 of this type . Like the turbine rotor blade 23 shown in Figure 6, the heat shield element 25 has a complex, in particular curved component surface 3.
While the heat shield element 25 is in use, its thermal barrier coating 19 is exposed to a hot aggressive medium M, in particular a hot gas M.
Figure 8 shows a diagrammatic illustration, not to scale, of a blasting installation 47 for the automated surface treatment of a component 1. The blasting installation 47 has a blasting chamber 65 in which a component holder 49 is arranged. A component 1 is held by the component holder 49. The component 1 has a curved component surface 3. A first particle source 5A
and a second particle source 5B are arranged in the blasting chamber 65. The particle sources 5A, 5B are arranged in such a way that, for a blasting process, they reach opposite regions of the component surface 3.
To generate a particle jet 7A, 7B which includes abrasive particles 27 and a carrier medium 29, an abrasive particle reservoir 57 and a carrier medium reservoir 53 are provided in the blasting installation 47. The carrier medium reservoir 53 supplies the particle source 5A, 5B via a first supply line 51 for carrier medium 29. To supply the particle source 5A, 5B with abrasive particles 27, there is a supply line 55 for abrasive particles 27.
Furthermore, the blasting chamber 65 has an outlet system 59. The outlet system 59 is fitted, for example, as a suction device. In this way, substantially the entire quantity of the abrasively acting abrasive particles 27 can be recovered and reused for blasting.
The abrasive particles 27 may in this case be produced from cast iron, steel, from synthetic corundum (aluminum oxide, A1203), silicon carbide or silicate sand. In addition, abrasive particles 27 made from alloys or intermetallic compounds are possible. The particle source 5A, 5B and the component holder 49 together with the component 1 can move relative to one another. By way of example, the particle source 5A, 5B
can move in a plurality of axes with respect to the stationary component 1. Alternatively, the component 1 can move in a plurality of axes by means of the component holder 49, with respect to the particle source 5A, 5B. In particular, the component holder 49 with the component 1 is arranged so that it can rotate about a vertical axis of rotation 67. This is highly advantageous in particular for the material-removing surface treatment of rotationally symmetrical components 1. For automated surface treatment of the component 1, the blasting installation 47 is equipped with a control system 61. The particle source 5A, 5B
and the component holder 49 are connected to the control system 61 via respective control signal lines 63A, 63B, 63C. In this way, automated control of the movement of component 1 and particle source 5A, 5B is possible. In particular, the relevant jet parameters of the particle source 5A, 5B can be automatically controlled, so that to produce a 1999P03591W0 - 18a -preferably homogeneous component surface 3 in a blasting process, the blasting distance d and the blasting angle a along a contour line 9A, 9B on the component surface 3 adopt a predeterminable, preferably constant value. Fitting the blasting installation 47 with a plurality of particle sources 5A, 5B allows simultaneous surface treatment of the component 1 along various contour lines 9A, 9B on the component surface 3.
In a method for the surface treatment of the component 1 in the automated blasting installation 47, the particle source 5A, 5B is supplied with abrasive particles 27 and with carrier medium 29, in particular compressed air 29, via the reservoirs 53, 57. Material is removed from the component surface 3 along a contour line 9A, 9B on the component surface 3 by the particle jet 7A, 7B which is generated by means of the particle sources 5A, 5B and is characterized by the jet parameters blasting distance d, blasting angle a and blasting time. The blasting parameters are deliberately matched to the contour line 9A, 9B in such a way that a predetermined, preferably homogeneous surface roughness is established along the contour line 9A, 9B. In the process, the jet parameters are automatically adapted by means of the control system 61, which controls the relative movement of the component 1 and of the particle sources 5A, 5B. The mode of operation in which the particle source 5A, 5B is moved relative to the component 1 in such a way that the blasting distance d and the blasting angle a are constant is particularly favorable. The control system 61 is responsible for accurate positioning and controlling of component 1 and of the particle source 5A, 5B. This allows the surface treatment of components 1 with a complex geometry, in particular with a curved component surface 3, with high quality and reproducibility. This is highly advantageous in particular for series production of components 1 and their surface treatment.
The invention is distinguished by the fact that the component surface of a component which, in particular, has regions of different curvature is blasted with 1999P03591W0 - 19a -abrasive particles for the purpose of surface treatment of the component. This results in smoothing and/or cleaning with, if appropriate, activation of the component surface. The ' CA 02383082 2002-02-27 method is suitable for processing the base body of a component and for preliminary processing of a component which is to be coated. In particular, the method can be integrated in a method for producing a layer system on a base body of a component. The material-removing processing of the component surface is deliberately matched to the geometry of the component, resulting in a homogeneous surface treatment.
~
11-13-2001 - a~ EP000804 1. A method for the surface treatment of a component ( 1 ) having a curved component surf ace ( 3 ) , in which material is removed from the component surface (3) along a contour line on the component surface (3) by means of a particle jet (7) which is generated from a particle source (5) and is characterized by the jet parameters blasting distance (d), blasting intensity, blasting angle (a) and blasting time, characterized in that during the surface treatment, at least once, at least one of the jet parameters is deliberately matched to the contour line in such a way that a homogeneous surface roughness is established along the contour line.
AMENDED SHEET
Claims (14)
- Claims
- 2. The method as claimed in claim 1, characterized in that the matching of the jet parameters takes place automatically.
- 3. The method as claimed in claim 1 or 2, characterized in that the particle source (5) and the component (1) are moved relative to one another.
- 4. The method as claimed in claim 1, 2 or 3, characterized in that the particle source (5) is moved relative to the component (1) in such a way that the blasting distance (d) is constant.
- 5. The method as claimed in one of the preceding claims, characterized in that the particle source (5) is moved relative to the component (1) in such a way that the blasting angle (.alpha.) is constant.
- 6. The method as claimed in one of the preceding claims, characterized in that the component (1) has a base body (11) with a base material (13), the base body (11) having the component surface (3) which, for a first coating (15) to be applied to the base body (11), is treated with a first coating material (17).
- 7. The method as claimed in claim 6, characterized in that the first coating material (17) used is an MCrAlX
alloy, where M represents one or more elements comprising iron, cobalt and nickel, Cr represents chromium, Al represents aluminum and X represents one or more elements selected from the group consisting of yttrium, rhenium and the rare earths. - 8. The method as claimed in claim 6 or 7, characterized in that the first coating (15) also has the component surface (3) which, for a second coating (19) to be applied to the component (1), is treated with a second coating material (21).
- 9. The method as claimed in one of claims 1 to 5, characterized in that the component (1) has a base body (11) with a base material (13), a first coating (15) comprising a first coating material (17) being applied to the base body (11), and the coated component (1), for a second coating (19) to be applied to the component (1), being treated with a second coating material (21).
- 10. The method as claimed in claim 8 or 9, characterized in that, in the coating process, a ceramic is used as the second coating material (21).
- 11. The method as claimed in one of the preceding claims, characterized in that the component (1) is designed for a hot gas to flow around it.
- 12. The method as claimed in one of the preceding claims, characterized in that the component (1) used is a turbine rotor blade (23), a turbine guide vane or a heat shield element (25) of a combustion chamber.
- 13. The method as claimed in one of the preceding claims, characterized in that the blasting angle (.alpha.) on the component surface (3) is approximately 20° to 90°, in particular approximately 50° to 90°.
- 14. A blasting installation (47) for the automated surface treatment of a component (1) having a curved component surface (3), which installation has a particle source (5) for generating a particle jet (7) and a component holder (49) for holding the component (1), it being possible to change the position of the particle source (5) and of the component (1) during the surface treatment in such a way that, to produce a homogeneous component surface (3) in a blasting process using the particle jet (17), the blasting distance (d) and/or the blasting angle (.alpha.) adopts a predetermined, in particular constant value along a contour line on the component surface (3).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP99117220 | 1999-09-01 | ||
| EP99117220.6 | 1999-09-01 | ||
| PCT/EP2000/008049 WO2001015866A1 (en) | 1999-09-01 | 2000-08-17 | Method and device for treating the surface of a part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2383082A1 true CA2383082A1 (en) | 2001-03-08 |
Family
ID=8238905
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002383082A Abandoned CA2383082A1 (en) | 1999-09-01 | 2000-08-17 | Method and device for the surface threatment of a component |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US20020098776A1 (en) |
| EP (1) | EP1218145B1 (en) |
| JP (1) | JP2003508238A (en) |
| KR (1) | KR20020029120A (en) |
| CN (1) | CN1372502A (en) |
| CA (1) | CA2383082A1 (en) |
| DE (1) | DE50008357D1 (en) |
| WO (1) | WO2001015866A1 (en) |
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| US20030124955A1 (en) * | 2001-12-27 | 2003-07-03 | Hanson D. Jack | Abrasive blasting unit for controlled blasting |
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| US7516547B2 (en) * | 2005-12-21 | 2009-04-14 | General Electric Company | Dovetail surface enhancement for durability |
| DE102006002371A1 (en) * | 2006-01-17 | 2007-07-19 | Kennametal Widia Produktions Gmbh & Co. Kg | Process for coating a cemented carbide or cermet substrate body and coated cemented carbide or cermet body |
| US20070258910A1 (en) * | 2006-05-08 | 2007-11-08 | Arola Dwayne D | Methods and devices for remineralization of hard tissues |
| KR101350022B1 (en) * | 2006-09-28 | 2014-01-13 | 코닝 제팬 가부시끼 가이샤 | Apparatus and method for edge processing of a sheet of brittle material |
| ITPR20060103A1 (en) * | 2006-11-22 | 2008-05-23 | Turbocoating S P A | PROCEDURE FOR SURFACE PREPARATION OF COMPONENTS TO BE COVERED |
| EP2030958B1 (en) * | 2007-08-27 | 2013-04-10 | Rohm and Haas Electronic Materials LLC | Method for producing polycrystalline monolithic magnesium aluminate spinels |
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| DE102010017859B4 (en) * | 2010-04-22 | 2012-05-31 | Mtu Aero Engines Gmbh | Method for processing a surface of a component |
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| GB2519047B (en) * | 2012-08-14 | 2018-08-22 | Snecma | A method of measuring the temperature reached by a part, in particular a turbine engine part |
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| JP6326290B2 (en) * | 2014-05-28 | 2018-05-16 | 日本特殊陶業株式会社 | Method for manufacturing molded body, method for manufacturing spark plug, method for manufacturing sensor |
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| US10836012B2 (en) | 2017-08-31 | 2020-11-17 | The Boeing Company | Method and apparatus for fluid cavitation abrasive surface finishing |
| US11679454B2 (en) | 2017-08-31 | 2023-06-20 | The Boeing Company | Portable cavitation peening method and apparatus |
| RU2018124439A (en) * | 2017-08-31 | 2020-01-13 | Зе Боинг Компани | METHOD FOR CAVITATION NAKLEPP AND MOBILE DEVICE FOR ITS IMPLEMENTATION |
| CN111684101B (en) | 2018-02-06 | 2023-02-17 | 佳能安内华股份有限公司 | Substrate processing apparatus and substrate processing method |
| US11167375B2 (en) | 2018-08-10 | 2021-11-09 | The Research Foundation For The State University Of New York | Additive manufacturing processes and additively manufactured products |
| CN108972354B (en) * | 2018-08-21 | 2020-02-14 | 中国航发航空科技股份有限公司 | Numerical control grinding and finishing machining method for shot blasting surface of blade |
| FR3102694B1 (en) * | 2019-10-30 | 2022-06-03 | Safran Aircraft Engines | PROCESS FOR COMPACTING AN ANTI-CORROSION COATING |
| FR3122595B1 (en) * | 2021-05-05 | 2024-04-26 | Safran Helicopter Engines | Process for manufacturing a turbine blade for a turbomachine |
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| CS272689B1 (en) * | 1989-03-02 | 1991-02-12 | Josef Ing Hlavsa | Method of glass hollow products', especially lighting glass, matting |
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| EP0970811B1 (en) * | 1998-07-06 | 2005-09-21 | L.A.C. Corporation | Automatic painting device |
-
2000
- 2000-08-17 CN CN00812393A patent/CN1372502A/en active Pending
- 2000-08-17 DE DE50008357T patent/DE50008357D1/en not_active Expired - Fee Related
- 2000-08-17 JP JP2001520263A patent/JP2003508238A/en not_active Withdrawn
- 2000-08-17 CA CA002383082A patent/CA2383082A1/en not_active Abandoned
- 2000-08-17 EP EP00960478A patent/EP1218145B1/en not_active Expired - Lifetime
- 2000-08-17 WO PCT/EP2000/008049 patent/WO2001015866A1/en not_active Application Discontinuation
- 2000-08-17 KR KR1020027002765A patent/KR20020029120A/en not_active Application Discontinuation
-
2002
- 2002-02-28 US US10/085,527 patent/US20020098776A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| CN1372502A (en) | 2002-10-02 |
| US20020098776A1 (en) | 2002-07-25 |
| JP2003508238A (en) | 2003-03-04 |
| KR20020029120A (en) | 2002-04-17 |
| DE50008357D1 (en) | 2004-11-25 |
| EP1218145A1 (en) | 2002-07-03 |
| EP1218145B1 (en) | 2004-10-20 |
| WO2001015866A1 (en) | 2001-03-08 |
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