EP2018246A1 - Verfahren zum vorbereiten eines bauteils aus einem elektrisch leitenden basismaterial auf das durchführen eines erodierprozesses - Google Patents
Verfahren zum vorbereiten eines bauteils aus einem elektrisch leitenden basismaterial auf das durchführen eines erodierprozessesInfo
- Publication number
- EP2018246A1 EP2018246A1 EP07728082A EP07728082A EP2018246A1 EP 2018246 A1 EP2018246 A1 EP 2018246A1 EP 07728082 A EP07728082 A EP 07728082A EP 07728082 A EP07728082 A EP 07728082A EP 2018246 A1 EP2018246 A1 EP 2018246A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- coating
- base material
- component
- cooling air
- electrically insulating
- 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- Withdrawn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
Definitions
- the present invention relates to a method for Vorbe ⁇ riding a component of electrically conductive base material on performing an erosion process.
- Highly thermally stressed components are often provided with a heat-insulating coating to keep the heat load of the components low.
- cooling air holes are incorporated in such devices frequently to the Erzeu ⁇ gene of a cooling air film over the component to enable. The cooling air film leads to a further cooling and thus to a further reduction of the thermal load.
- gas turbine blades so running or Leitschau ⁇ blades of gas turbines, have such cooling air holes and thermal barrier coatings on.
- the existing cooling air holes are closed when applying the thermal barrier coating, they must be opened again after applying the thermal barrier coating.
- the opening can be done, for example, by means of a high-pressure fluid, which is blown from the inside of the turbine blades through the cooling air holes.
- a high-pressure fluid which is blown from the inside of the turbine blades through the cooling air holes.
- the object of the present invention is to provide an advantageous method of preparing a component of an electrically conductive base material to performing a Erodierpro ⁇ zesses available.
- a further object is to provide an advantageous method for producing a component from an electrically conductive base material with an electrically insulating coating and recesses introduced into the base material. to make available.
- the surface of the base material is kept from the outset by the coating material where the erosion process is to be carried out for forming recesses, such as cooling air openings, it is no longer necessary to remove excess coating material after application of the coating. The risk of damaging the already applied coating by removing coating material is thereby eliminated. In addition, the number of working steps can be so when erosive inputs bring decrease of recesses since the removal of the coating is removed, which has a cost-len the herstel ⁇ of components can affect.
- a template can be arranged over the component surface being ⁇ .
- This template can also be designed in three dimensions. It then has, for example, a structure which is inverse to the erosive recess and which is arranged relative to the component surface and to the injection direction such that the resulting spray shadow corresponds to the opening surface of the recess in the surface.
- the template is provided with a geeig ⁇ Neten shape and is arranged in such a way check on the component surface that a spray shadow is produced by the geometry of the diffuser.
- the ⁇ ff ⁇ tion of a later to be produced cooling air hole in the electrically insulating coating can be formed as a diffuser.
- the inventive method is particularly suitable for the manufacture of turbine blades, so as runners or vanes of gas turbines to which a thermal barrier coating is applied as an electrically insulating coating and in the means of the erosion process cooling air holes as
- Recesses are to be introduced. Since it nenschaufeln at Gasturbi ⁇ arrives particularly dependent on the integrity of the thermal barrier coating, United ⁇ the invention makes driving a valuable contribution, the production of gas-turbine binenschaufein improve with cooling air holes.
- pins can be used as inverse structures of a three-dimensional template for generating the spray shadow at the locations where the cooling air holes are to be introduced. These pins may have the inverse shape of a diffuser at their abutting end portions of the component.
- Suitable spraying methods for applying the electrically insulating coating are, in particular, thermal spraying methods. But also non-thermal spray methods, such as. Cold gas spraying, can be used in principle.
- the method according to the invention for preparing a component from an electrically conductive base material for performing an erosion process can be made into a production method for producing a component from an electrically insulating base material with an electrically insulating coating applied to the surface of the base material and at least one into the base material Erosion after the application of the electrically insulating coating in the base material introduced recess be expanded if after preparing the component according to the preparation method according to the invention at least one recess is introduced by means of an erosion process where the component surface has been kept free of the coating material.
- Fig. 1 shows schematically a section of a blade of a gas turbine.
- Fig. 2 shows a template for generating a spray shadow during the molding on a thermal insulation coating to the turbine blade in a plan view of the leading edge of the turbine show ⁇ fel.
- Fig. 3 shows the turbine blade of Fig. 2 in one
- FIG. 4 shows a detail of Fig. 3 in an enlarged view.
- FIG. 5 shows the turbine blade of FIG. 3 during the FIG
- FIG. 6 shows a perspective view of a moving blade or guide vane of a turbomachine.
- FIG. 6 shows a perspective view of a rotor 120 or guide vane 130 of a turbomachine that extends along a longitudinal axis 121.
- the turbomachine may be a gas turbine of an aircraft or a power plant for electricity generation, a steam turbine or a compressor.
- the blade 120, 130 has along the longitudinal axis 121 to each other, a securing region 400, an adjoining blade or vane platform 403 and a blade 406 and a blade tip 415.
- the blade 130 may have at its blade tip 415 another platform (not shown).
- a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
- the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
- the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the airfoil 406.
- blades 120, 130 in all regions 400, 403, 406 of the blade 120, 130, for example, massive metallic materials, in particular superalloys, are used.
- superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These writings are with respect.
- the chemical composition of the alloy part of the disclosure can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
- Workpiece consists of a single crystal. In these processes, one must avoid the transition to globulitic (polycrystalline) solidification, since non-directional growth necessarily produces transverse and longitudinal grain boundaries which negate the good properties of the directionally solidified or monocrystalline component.
- the blades 120, 130 may have coatings against corrosion or oxidation, e.g. M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
- M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
- X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
- Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which should be part of this disclosure with regard to the chemical composition of the alloy.
- the density is preferably 95% of the theoretical density.
- thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially ⁇ or fully stabilized by yttria and / or calcium oxide and / or magnesium oxide.
- the thermal barrier coating covers the entire MCrAlX ⁇ layer.
- EB-PVD Electron beam evaporation
- APS atmospheric plasma spraying
- LPPS LPPS
- VPS VPS
- CVD chemical vapor deposition
- the thermal barrier coating may have porous, micro- or grain-contaminated grains for better thermal shock resistance.
- the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
- Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, will also
- the blade 120, 130 may be hollow or solid.
- the blade 120 is to be cooled 130, it is hollow and, if necessary, has film cooling holes 418 (indicated by dashed lines) on.
- the running ⁇ blade 1 shows a schematic representation of a section of a rotor blade of a gas turbine.
- the running ⁇ blade 1 consists of a metallic base material, and has a leading edge 3 and a trailing edge 5 on, Zvi ⁇ rule which extend a pressure side and a suction side 7.
- the turbine blade 1 is provided with a thermal barrier coating for thermal insulation against the hot exhaust gases flowing around it during operation of the gas turbine plant.
- the heat dämmbe Anlagenung is introduced by means of an injection process up ⁇ .
- atmosphäri ⁇ ULTRASONIC plasma spraying for the application which is a particular thermal spraying process comes.
- layer applied before the cooling air holes 11, 13, 15 are introduced by means of Erodierbohrens in the metallic base material of the turbine blade 1 turbine blade featured in preparing the Darge in Fig. 1 ⁇ first the ceramic thermal barrier ⁇ . Since EDM drilling requires a counter electrode to the erosion electrode, the ceramic thermal barrier coating can not be drilled through this method.
- a template 17 is placed over the surface 27 of the turbine blade 1, as shown in FIGS. 2 to 4.
- the template 17 is equipped with a number of pins 19 fixed to a carrier 21.
- the carrier passes into a holder 23, to which the template 17 is held during spraying.
- the template 17 is stopped before the start of spraying to the surface of the uncoated turbine blade 1 that the tips 25 of the pins are located at a very small distance above the surface 27 of the turbine blade 1 (see Fig.4).
- the spattering of the ceramic material takes place with the aid of a spray nozzle 29, from which the ceramic material is sprayed in an injection direction 33.
- the spray tip 29 ver ⁇ transmitting ceramic material forms a spray cone 31, which is a to the spray direction 33 of the spray nozzle 29 substantially symmetrical material distribution. Due to the large ⁇ SEN spatial proximity of the pins 19 to the surface 27 of the turbo binenschaufel of the pins 19 and certain areas of an injection shade 37 is formed between the tips 25 of the surface 27 from 35. In the area 35 of the surface 27 covered by the spray shadow, the spilled ceramic material can not reach the surface 27. This area is therefore not coated during the spraying process.
- Injection direction 33 oriented relative to each other so that the uncoated areas 35 in shape exactly correspond to the shape of the exit surfaces of the cooling air holes 11, 13, 15 to be formed in the component surface.
- a template 17 with a ten geeigne ⁇ form and to arrange in such a way relative to the spraying device 33 on the turbine blade 1, that Spray shadow with the geometry of a diffuser who ⁇ shows the.
- the resting on the turbine blade 1 end portions of the pins 19 of the template 17 may have the inverse form of a diffuser.
- the shape of the pins 19 must be deviating from the shape of an ideal inverse diffuser.
- the erosion electrodes 41 are brought to the uncoated regions 35 and the erosion drilling is started.
- the Ero ⁇ be commanding electrodes 41 (s. Figure 5) is continually updated in the base material 43 so long reach this broken and a central cavity 45 of the turbine blade 1. After reaching the central cavity 45, the corresponding cooling air hole is completed.
- cooling air bores can be introduced into the turbine blades after the application of a ceramic thermal barrier coating.
- the removal of ceramic thermal barrier coating at the locations where the cooling air holes are to be introduced, is not necessary.
- the ceramic thermal barrier coating 39 thus remains unchanged after application, so that the risk of damaging the thermal barrier coating by local removal does not exist.
- the method according to the invention has been described using the example of the preparation of turbine blades for the introduction of cooling air bores by EDM drilling. However, it can also be used for introducing other recesses, for example grooves. These can then be introduced by means of a sinking process as the erosion process in the component surface.
- the component does not need to be a turbine blade.
- the invention can basically be used for preparing and make use of such components, which consist of an electrically conductive base material and after completion should have an electrically insulating surface coating and recesses in the base material. As recesses are blind or through holes, grooves, etc. into consideration.
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07728082A EP2018246A1 (de) | 2006-05-19 | 2007-04-13 | Verfahren zum vorbereiten eines bauteils aus einem elektrisch leitenden basismaterial auf das durchführen eines erodierprozesses |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/EP2006/004786 WO2007134620A1 (de) | 2006-05-19 | 2006-05-19 | Verfahren zum vorbereiten eines bauteils aus einem elektrisch leitenden basismaterial auf das durchführen eines erodierprozesses |
EP07728082A EP2018246A1 (de) | 2006-05-19 | 2007-04-13 | Verfahren zum vorbereiten eines bauteils aus einem elektrisch leitenden basismaterial auf das durchführen eines erodierprozesses |
PCT/EP2007/053616 WO2007134916A1 (de) | 2006-05-19 | 2007-04-13 | Verfahren zum vorbereiten eines bauteils aus einem elektrisch leitenden basismaterial auf das durchführen eines erodierprozesses |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2018246A1 true EP2018246A1 (de) | 2009-01-28 |
Family
ID=40149843
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07728082A Withdrawn EP2018246A1 (de) | 2006-05-19 | 2007-04-13 | Verfahren zum vorbereiten eines bauteils aus einem elektrisch leitenden basismaterial auf das durchführen eines erodierprozesses |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP2018246A1 (de) |
-
2007
- 2007-04-13 EP EP07728082A patent/EP2018246A1/de not_active Withdrawn
Non-Patent Citations (1)
Title |
---|
See references of WO2007134916A1 * |
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RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: REICH, GERHARD Inventor name: MALOW, THOMAS Inventor name: LADRU, FRANCIS-JURJEN Inventor name: GEORGIEV, VIKTOR |
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