EP1797215A1 - Element dote d'un revetement et procede pour realiser un revetement - Google Patents
Element dote d'un revetement et procede pour realiser un revetementInfo
- Publication number
- EP1797215A1 EP1797215A1 EP05784519A EP05784519A EP1797215A1 EP 1797215 A1 EP1797215 A1 EP 1797215A1 EP 05784519 A EP05784519 A EP 05784519A EP 05784519 A EP05784519 A EP 05784519A EP 1797215 A1 EP1797215 A1 EP 1797215A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- coating
- component
- base material
- expansion joints
- thermal barrier
- 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.)
- Withdrawn
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/04—Coating on selected surface areas, e.g. using masks
- C23C14/042—Coating on selected surface areas, e.g. using masks using masks
Definitions
- the present invention relates to a component with a coating and to a method for producing a coating on a component surface.
- Components with coatings such. B. with cherriesdämmbeSchich ⁇ lines, for example, in turbines, such as in gas turbines for power generation, before.
- turbines such as in gas turbines for power generation
- TBC Thermal Barrier Coating
- an adhesion promoter layer is generally used, which is applied to the metallic base material of the component before it is coated with the ceramic coating material.
- Another cause of buckling and flaking is the fact that some ceramic coatings are permeable to oxygen at high temperatures, so that oxidizable portions of the primer layer can be oxidized. If the oxidation is associated with an increase in volume, this can cause the coating to flake or buckle.
- EP 0 935 009 B1 proposes to provide the surface of the body with a skeleton structure in the form of a net or a grid, and to apply the coating to the surface provided with the skeleton structure. This results in the application of the coating cavities in the coating, which provide an expansion tolerance of the coating.
- DE 42 38 369 A1 describes a component comprising a metallic base substrate with a ceramic coating, in which the surface of the base substrate is provided with a multiplicity of vertically projecting webs. The height at which the webs protrude beyond the surface is less than the thickness of the coating.
- segmentation cracks develop in the region above the webs, which continue into the coating surface. These segmentation cracks broaden at operating temperature and close at room temperature, which results in an increased strain tolerance of the coating.
- a metallic base body with a metallic anchoring matrix in order to increase the adhesion of a ceramic layer to the base body.
- the anchoring matrix can be constructed, for example, from honeycomb structures, needle-shaped structures or pin-shaped structures.
- the first object is achieved by a component according to claim 1, the second object by a method according to claim 9.
- An inventive component of a base material, in particular of a metallic base material, with a coating applied over the base material is characterized in that expansion joints are present in the coating.
- the expansion tolerance of the coating can be increased.
- large-area components for example hub components of gas turbines
- buckling and flaking are avoided in the component according to the invention without metallic elements extending from the component surface into the heat-insulating coating.
- Metallic elements have a good thermal conductivity, whereby the thermal insulation properties of the thermal barrier coating deteriorate compared to thermal barrier coatings without metallic elements.
- the expansion joints are distributed in a network over the surface of the Beschich ⁇ device.
- the expansion properties of the coating can be specifically adapted to the geometry of the component. In order to further increase the stretching tolerance of the coating, it may have a porosity.
- the coating can be designed as a ceramic coating for thermal insulation.
- the base material is a metallic base material, it is advantageous if an adhesion promoter layer is present between the base material and the ceramic thermal barrier coating. Part of the primer layer can be achieve secure adhesion of the ceramic thermal insulation coating on the metallic base material.
- the component according to the invention can be designed in particular as a turbine component, for example as a hub component of a turbine.
- a structure of wire or rope-shaped elements is arranged at a distance above the collection surface before the coating is applied. After application of the coating, the structure is then removed again. During coating, the coating will be less intense in the areas covered by the structure than in the uncovered areas. The result is the expansion joints of the coating.
- thermal spraying process for example atmospheric plasma spraying (APS) or high velocity oxygen fuel (HVOF) or a gas phase deposition process, for example a so-called EB-PVD process (US Pat. electron beam physical vapor deposition take place).
- APS atmospheric plasma spraying
- HVOF high velocity oxygen fuel
- EB-PVD process US Pat. electron beam physical vapor deposition take place.
- the coating material is evaporated by means of an electron beam from a supply, the conditions in the environment of the component during coating being adjusted so that the evaporated material from the gas phase can be coated onto the material to be coated Surface attaches.
- FIG. 1 shows a first exemplary embodiment of a component according to the invention with a thermal insulation coating in plan view.
- Figure 2 shows an enlarged section of the component of Figure 1 in a cross section along the line A A.
- FIG. 3 shows a second exemplary embodiment of the component according to the invention with thermal insulation coating in a plan view.
- FIG. 4 shows a third exemplary embodiment of a component according to the invention with thermal insulation layering in a top view.
- FIG. 5 shows a step of the production method according to the invention for a component according to the invention with a thermal insulation layer.
- FIG. 6 shows a step of the production method according to the invention for applying a thermal barrier coating to a hub component of a turbine.
- FIGS. 1 and 2 show a large-area turbine component 1 with a thermal insulation layer 3 . While FIG. 1 shows the turbine component 1 in plan view, FIG. 2 shows the turbine component 1 in a section along the line II-II, wherein the sectional representation is enlarged in comparison to FIG.
- the invention will be explained in more detail using the example of a thermal barrier coating for a coating.
- the turbine component 1 has a metallic base body 2, on which a bonding agent layer 4 is applied.
- the adhesion promoter layer 4 serves to increase the adhesion of the thermal barrier coating 3, which is embodied as a ceramic thermal insulation coating in the exemplary embodiment, to the metallic base body 2.
- the thermal barrier coating 3 is applied flatly to the turbine component 1 and has at regular intervals parallel to each other extending expansion joints 5. In the area of expansion joints, the material thickness of the thermal barrier coating is reduced by about half. Depending on the expected thermal load on the component, it can also have a smaller or greater reduction.
- the surface of the thermal barrier coating 3 is subdivided by the expansion joints 5 into a number of surface regions 7.
- These surface regions 7 are rectangular in the present embodiment, however, they can also be square or honeycomb-shaped, in particular hexagonal, as shown in FIGS. 3 and 4.
- the metallic base material 2 of the turbine component 1, 11, 21 expands more strongly than the coating material of the thermal barrier coating 3, 13, 23, then the expansion joints 5, 15, 25 allow expansion of the thermal barrier coating 3, 13, 23 without that excessive voltages occur.
- the geometry of the expansion joints can be suitably selected. If, for example, stresses preferably occur in one direction, then, as shown in FIG. 1, it is possible to provide the component only with expansion joints running parallel to one another.
- the expansion joints 15, 25 need not be arranged at regular intervals from one another. Rather, the distances may also be irregular or have a periodic course.
- the stresses are not only preferential in one direction, then it may be advantageous if the expansion joints 15, 25 extend in different directions over the surface 8 of the thermal insulation layer 3, 13, 23.
- the expansion joints 5 then form a network structure on the surface 8 of the thermal barrier coating 3, as can be seen in FIGS. 3 and 4.
- the expansion tolerance of the thermal barrier coating 3 can be further improved if it has a porosity.
- FIG. 5 shows an essential method step during application of the thermal barrier coating 3
- FIG. 6 shows a hub component of a turbine prior to application of the thermal barrier coating.
- a wire or rope-shaped structure is arranged above the surface of the base body or, if present, the surface 6 of the adhesion promoter layer 4. In the present embodiment are stretched
- Wires 9 by means of a frame (not shown in Fig. 5) at a distance d above the surface 6 of the Haftvermittler ⁇ layer 4 fixed.
- the distance d is greater than the subsequent thickness of the thermal barrier coating 3.
- the ceramic thermal insulation layer 3 is applied to the adhesion promoter layer 4 by means of an EB-PVD method, ie by deposition from the gas phase.
- an EB-PVD method ie by deposition from the gas phase.
- less ceramic material is deposited than in the areas between the wires 9. In this way, the material thickness is in the shadow of the wires 9
- the areas of reduced material thickness then form the expansion joints 5 in the finished heat insulation layer 3.
- the width and depth of the expansion joints 5 can be varied by, for example, the direction from which The deposition of the ceramic material takes place during the deposition process.
- the expansion joints can be changed.
- the later course of the expansion joints 5 can be determined by the course of the wires 9. If, for example, the honeycomb structure shown in FIG. 4 is to be produced, then by means of the frame not individual wires but a wire mesh with the corresponding structure are applied over the surface to be coated.
- FIG. 6 shows an example of the implementation of the method according to the invention on a hub component 30 of a gas turbine.
- an ⁇ comprising two frame parts 35 and 37, between which wires 9 are stretched.
- these wires 9 then provide for the Ent ⁇ expansion joints.
- the inventive method makes it possible, in particular, to provide large-area components, such as hub components of turbines, with expansion-tolerant heat-insulating coatings.
- the distance d at which the wires 9 are applied over the surface 6 to be coated is at least approximately 0.2 mm in the exemplary embodiment. However, it can be varied, in particular increased, depending on the desired depth and width of the expansion joints.
- an MCrAlY layer that is to say a layer of a metallic alloy which comprises chromium (Cr) and aluminum (Al), and in the Y for yttrium or a rare earth element and M for iron, may be used as adhesion promoter layer 4 (Fe), cobalt (Co) or nickel (Ni) are used.
- adhesion promoter layer 4 Fe
- cobalt Co
- Ni nickel
- a ceramic thermal barrier coating are in particular zirconium (Zr) based coatings, for example a zirconium oxide coating.
Landscapes
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
L'invention concerne un élément (1) comprenant un matériau de base (2) sur lequel est appliqué un revêtement (3). L'invention est caractérisée en ce que des joints de dilatation (6) se trouvent dans le revêtement (3).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP05784519A EP1797215A1 (fr) | 2004-10-05 | 2005-08-29 | Element dote d'un revetement et procede pour realiser un revetement |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04023705A EP1645655A1 (fr) | 2004-10-05 | 2004-10-05 | Substrat revêtu et procédé de revêtement |
PCT/EP2005/054230 WO2006037700A1 (fr) | 2004-10-05 | 2005-08-29 | Element dote d'un revetement et procede pour realiser un revetement |
EP05784519A EP1797215A1 (fr) | 2004-10-05 | 2005-08-29 | Element dote d'un revetement et procede pour realiser un revetement |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1797215A1 true EP1797215A1 (fr) | 2007-06-20 |
Family
ID=34926855
Family Applications (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04023705A Withdrawn EP1645655A1 (fr) | 2004-10-05 | 2004-10-05 | Substrat revêtu et procédé de revêtement |
EP05784519A Withdrawn EP1797215A1 (fr) | 2004-10-05 | 2005-08-29 | Element dote d'un revetement et procede pour realiser un revetement |
EP05776179A Withdrawn EP1797214A1 (fr) | 2004-10-05 | 2005-08-29 | Element dote d'un revetement et procede pour realiser un revetement |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04023705A Withdrawn EP1645655A1 (fr) | 2004-10-05 | 2004-10-05 | Substrat revêtu et procédé de revêtement |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05776179A Withdrawn EP1797214A1 (fr) | 2004-10-05 | 2005-08-29 | Element dote d'un revetement et procede pour realiser un revetement |
Country Status (2)
Country | Link |
---|---|
EP (3) | EP1645655A1 (fr) |
WO (2) | WO2006037699A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20110164981A1 (en) * | 2010-01-04 | 2011-07-07 | General Electric Company | Patterned turbomachine component and method of forming a pattern on a turbomachine component |
FR2962447B1 (fr) * | 2010-07-06 | 2013-09-20 | Snecma | Barriere thermique pour aube de turbine, a structure colonnaire avec des colonnes espacees |
EP2431572A1 (fr) * | 2010-09-21 | 2012-03-21 | Siemens Aktiengesellschaft | Revêtement de barrière thermique pour un élément de turbine à vapeur |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS58190892A (ja) * | 1982-04-28 | 1983-11-07 | Nippon Carbon Co Ltd | シリコン単結晶引上げ用黒鉛るつぼ |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2745326B2 (ja) * | 1989-05-29 | 1998-04-28 | 昭和飛行機工業株式会社 | 溶射被膜構造 |
EP0573879A3 (en) * | 1992-06-12 | 1994-08-24 | Siemens Ag | Manufacturing process of a structured phosphor layer |
US5558922A (en) * | 1994-12-28 | 1996-09-24 | General Electric Company | Thick thermal barrier coating having grooves for enhanced strain tolerance |
JP3316418B2 (ja) * | 1997-06-12 | 2002-08-19 | 三菱重工業株式会社 | ガスタービン冷却動翼 |
US6528118B2 (en) * | 2001-02-06 | 2003-03-04 | General Electric Company | Process for creating structured porosity in thermal barrier coating |
US6551061B2 (en) * | 2001-03-27 | 2003-04-22 | General Electric Company | Process for forming micro cooling channels inside a thermal barrier coating system without masking material |
-
2004
- 2004-10-05 EP EP04023705A patent/EP1645655A1/fr not_active Withdrawn
-
2005
- 2005-08-29 EP EP05784519A patent/EP1797215A1/fr not_active Withdrawn
- 2005-08-29 WO PCT/EP2005/054227 patent/WO2006037699A1/fr active Application Filing
- 2005-08-29 EP EP05776179A patent/EP1797214A1/fr not_active Withdrawn
- 2005-08-29 WO PCT/EP2005/054230 patent/WO2006037700A1/fr active Application Filing
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS58190892A (ja) * | 1982-04-28 | 1983-11-07 | Nippon Carbon Co Ltd | シリコン単結晶引上げ用黒鉛るつぼ |
Non-Patent Citations (1)
Title |
---|
See also references of WO2006037700A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2006037699A1 (fr) | 2006-04-13 |
EP1645655A1 (fr) | 2006-04-12 |
WO2006037700A1 (fr) | 2006-04-13 |
EP1797214A1 (fr) | 2007-06-20 |
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Legal Events
Date | Code | Title | Description |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
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17P | Request for examination filed |
Effective date: 20070316 |
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AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): CH DE FR GB IT LI NL |
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DAX | Request for extension of the european patent (deleted) | ||
RBV | Designated contracting states (corrected) |
Designated state(s): CH DE FR GB IT LI NL |
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17Q | First examination report despatched |
Effective date: 20080606 |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 20120301 |