EP1797214A1 - Element dote d'un revetement et procede pour realiser un revetement - Google Patents

Element dote d'un revetement et procede pour realiser un revetement

Info

Publication number
EP1797214A1
EP1797214A1 EP05776179A EP05776179A EP1797214A1 EP 1797214 A1 EP1797214 A1 EP 1797214A1 EP 05776179 A EP05776179 A EP 05776179A EP 05776179 A EP05776179 A EP 05776179A EP 1797214 A1 EP1797214 A1 EP 1797214A1
Authority
EP
European Patent Office
Prior art keywords
coating
component
expansion joints
base material
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Withdrawn
Application number
EP05776179A
Other languages
German (de)
English (en)
Inventor
Thomas Dobener
Milan Schmahl
Werner Stamm
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP05776179A priority Critical patent/EP1797214A1/fr
Publication of EP1797214A1 publication Critical patent/EP1797214A1/fr
Withdrawn legal-status Critical Current

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 7.
  • 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 joints are distributed like a net over the surface of the coating.
  • Adapt coating to the geometry of the component In order to further increase the elongation tolerance of the coating, it may have a porosity.
  • the expansion tolerance of the coating can be increased.
  • large-area components for example hub components of gas turbines
  • flaking and bulging of a thermal insulation coating can thus be avoided.
  • 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 coating can be designed as a ceramic coating for thermal insulation. If, in addition, the
  • Base material is a metallic base material, it is advantageous if between the base material and the kerami ⁇ 's thermal insulation coating a bonding agent layer before is present. By virtue of the adhesion promoter layer, a secure adherence of the ceramic thermal insulation coating to the metallic base material can be achieved.
  • 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 barrier coating mentioned by way of example can be carried out in particular by means of a thermal spraying method, for example atmospheric plasma spraying (APS) or high velocity oxygen spraying (HVOF) or a gas phase precipitation 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 spraying
  • EB-PVD gas phase precipitation process
  • the coating material is evaporated by means of a Elek ⁇ tronenstrahls from a store, the Bedin ⁇ conditions in the environment of the component during coating are so ein ⁇ made that accumulates the evaporated material from the gas phase on the surface to be coated.
  • 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.
  • Figure 3 shows a second embodiment of the erfin ⁇ Dungswe component with compensatedämmbeSichtung in a Drauf ⁇ view.
  • FIG. 4 shows a third exemplary embodiment of a component according to the invention with thermal insulation layering in a plan view.
  • FIG. 5 shows a step of the production method according to the invention for a component according to the invention with thermal insulation coating.
  • 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 As a first exemplary embodiment of a component according to the invention with coating, a large-area turbine component 1 with a thermal insulation coating 3 is shown schematically in FIGS. 1 and 2.
  • 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.
  • wires 9 When the ceramic thermal barrier coating is applied, these wires 9 then cause the expansion joints to open.
  • 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, can 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).
EP05776179A 2004-10-05 2005-08-29 Element dote d'un revetement et procede pour realiser un revetement Withdrawn EP1797214A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05776179A EP1797214A1 (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
EP05776179A EP1797214A1 (fr) 2004-10-05 2005-08-29 Element dote d'un revetement et procede pour realiser un revetement
PCT/EP2005/054227 WO2006037699A1 (fr) 2004-10-05 2005-08-29 Element dote d'un revetement et procede pour realiser un revetement

Publications (1)

Publication Number Publication Date
EP1797214A1 true EP1797214A1 (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 (2)

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

Country Status (2)

Country Link
EP (3) EP1645655A1 (fr)
WO (2) WO2006037699A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
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

Family Cites Families (7)

* Cited by examiner, † Cited by third party
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
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2006037699A1 *

Also Published As

Publication number Publication date
EP1645655A1 (fr) 2006-04-12
EP1797215A1 (fr) 2007-06-20
WO2006037700A1 (fr) 2006-04-13
WO2006037699A1 (fr) 2006-04-13

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