EP3198049A1 - Verfahren zur beschichtung einer turbinenschaufel - Google Patents
Verfahren zur beschichtung einer turbinenschaufelInfo
- Publication number
- EP3198049A1 EP3198049A1 EP15797329.8A EP15797329A EP3198049A1 EP 3198049 A1 EP3198049 A1 EP 3198049A1 EP 15797329 A EP15797329 A EP 15797329A EP 3198049 A1 EP3198049 A1 EP 3198049A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- coating
- platform
- layer
- zone
- contact zone
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000011248 coating agent Substances 0.000 title claims abstract description 71
- 238000000576 coating method Methods 0.000 title claims abstract description 71
- 238000000034 method Methods 0.000 title claims abstract description 34
- 229910000601 superalloy Inorganic materials 0.000 claims description 12
- 238000005507 spraying Methods 0.000 claims description 8
- 238000000227 grinding Methods 0.000 claims description 7
- 230000004888 barrier function Effects 0.000 claims description 5
- 239000000463 material Substances 0.000 description 11
- 239000006228 supernatant Substances 0.000 description 11
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 239000010953 base metal Substances 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 230000008092 positive effect Effects 0.000 description 2
- 238000009736 wetting Methods 0.000 description 2
- 241000139306 Platt Species 0.000 description 1
- 229910000946 Y alloy Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- NQLVQOSNDJXLKG-UHFFFAOYSA-N prosulfocarb Chemical compound CCCN(CCC)C(=O)SCC1=CC=CC=C1 NQLVQOSNDJXLKG-UHFFFAOYSA-N 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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
- C23C2/00—Hot-dipping or immersion processes for applying the coating material in the molten state without affecting the shape; Apparatus therefor
- C23C2/26—After-treatment
-
- 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
- C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
-
- 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
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
-
- 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
- C23C4/18—After-treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
Definitions
- the invention relates to a method of coating a turbine blade comprising a blade and at least one platform disposed at one end of the blade, the or each platform having a contact zone and at least one protrusion zone adjacent to the contact zone, and at the Contact zone completes the wing.
- the blading of a turbine stage is subject to particular thermal and mechanical stresses.
- the individual blades of a turbine stage are therefore each made as a single crystalline workpieces to improve the mechanical strength as possible.
- the required heat resistant ⁇ ness, which often can not be ⁇ riding determine the monocrystalline material is then usually achieved via an additional coating. Depending on the requirements, the coating can also be applied in several layers.
- a frequently used method for this purpose is to coat the areas of a blade, in which the highest thermal loads occur, with a thermal barrier layer ("TBC"), which comprises a bond coating. is at the blade held ⁇ th.
- TBC thermal barrier layer
- the bonding layer is in this case usually formed by a superalloy, for example a metal-chromium-aluminum-yttrium alloy (MCrAlY) with nickel and / or cobalt as base metal.
- MrAlY metal-chromium-aluminum-yttrium alloy
- the bonding layer is usually sprayed onto the monocrystalline material of the blade with a defined thickness in several layers. This is intended to improve a ⁇ hand, the adhesion of the TBC to the blade, on the other hand, the bonding layer carries itself also contributes to it ⁇ creased heat resistance of the blade. In areas of moderate thermal stress, the bonding layer alone can also provide sufficient heat protection for the material of the turbine blade.
- a turbine blade When coating, the special structure of a turbine blade should be observed.
- This usually consists of a profiled ⁇ profiled wing which is completed at its two longitudinal ends by a platform.
- the wing is arranged radially in the flow space of the turbine, the platform Men of individual blades of the same turbine stage form an inner or outer ring and close as flush as possible to each other.
- spraying the respective wing-side surface of the platform with the bonding layer there is often also a slight spraying of the respective end face of the platform.
- the remnants of the bonding layer are removed from the faces of the platforms, which is usually done manually, for example by grinding. This is on the one hand consuming, on the other hand endangers the grinding process on the front side of a platform, the wing-side coating.
- the binding layer may break or tear at the edge of the platform. If this occurs at a point where a TBC is to be applied, its liability is impaired.
- the TBC can gradually abblät ⁇ tern in operation. If this occurs at a location where no TBC is provided, the material of the blade is already subject to a higher heat load by the cracks itself.
- the invention is therefore based on the object to provide a method for coating a turbine blade, which is as simple as possible to perform, and in the field of
- the above object is inventively achieved by a method for coating a turbine blade comprising egg NEN wing and at least one at one end of the wing at ⁇ parent platform, the or each platform a contact zone and at least a layer adjacent to the contact zone on ⁇ area Supernatant zone, and at the Kon- tactical zone completes the wing.
- the method has the following method steps:
- the wings may be terminated at both ends of each egg ⁇ ner platform, and in particular the method steps mentioned may be performed on both platforms.
- the invention is based on the following considerations:
- the platform is exposed in all its surface area to the high temperatures encountered during operation in the supernatant zone, while on the other hand, the platform in the contact zone to the places where the wing connects, is not exposed to these Tempe ⁇ tures.
- the platform in the contact zone to the places where the wing connects is not exposed to these Tempe ⁇ tures.
- this means in simple terms is that in the supernatant zone macro ⁇ scopically takes place a greater heat-induced expansion as exposed here all the microscopic surface elements to warmth are, while this is not the case, however, for some micro ⁇ scopic surface elements in the contact zone.
- a platform now expands more in the area of the overhang zone than in the area of the contact zone, which reduces the distance to an adjacent platform.
- the distance between two adjacent platforms ⁇ it can therefore be chosen such that their end faces are in contact in the region of the supernatant zone in operation almost or completely, and thus make it harder a fluidic escape of hot gas. In the region of the contact zone of the two adjacent platforms, the escape is made more difficult by the layers of the coating remaining on the end surfaces.
- the platform merges into the wing in the contact zone to form a concave surface, leaving the at least first layer of the coating on the end face in the region of the contact zone is particularly advantageous.
- the removal of parts of the loading ⁇ coating may lead to tangential forces within a layer of the coating. While such tangential Forces in a position of the coating in the supernatant zone can propagate largely unhindered, they can locally have a normal component on a concave surface in the region of the contact zone. This normal force component promotes local peeling of the respective position of the loading ⁇ coating from the platform in the region of the concave surface and the contact zone.
- the first layer of the coating is applied to the platform on the wing side by spraying.
- the specified method is particularly advantageous because it can easily come to a - possibly unkontrol ⁇ lated - wetting the end face of the platform with a layer of the coating at the wing-side spraying the platform with the coating.
- the conditions for the procedure are given.
- At least the first layer of Beschich ⁇ tion can be applied to the platform by a dip bath.
- a turbine blade whose wings at the ends ⁇ is completed by a respective platform, in this case, it is difficult to prevent a deposition of a layer of the coating on the end faces of the platforms.
- the conditions for the procedure are met here, too.
- a binding layer serves to improve the bonding of a further, later to be applied, layer of the coating to the material of the turbine blade.
- the turbine blade in particular on the platform, with a
- a superalloy is applied to the platform as the bonding layer.
- a superalloy may in particular be a metal-chromium-aluminum-yttrium compound (MCrAlY), it being possible to use nickel and / or cobalt as the base metal.
- MrAlY metal-chromium-aluminum-yttrium compound
- the at least first layer of the coating is removed from the at least one end face of the platform in the region of the projection zone by grinding.
- This type of removal can be controlled very precisely locally compared to, for example, erosive methods, whereby the risk of undesired damage to layers of the coating can be reduced.
- a heat-barrier layer is applied to the platform on the wing side as a further layer of the coating.
- this may be formed as a ceramic thermal barrier layer.
- Thermal barrier layer were applied, especially in sen ⁇ sensitive area of the contact zone can be significantly reduced. This has a particularly positive effect on the adhesion of the thermal barrier layer.
- the invention further identifies a gas turbine comprising Wenig ⁇ least one vane and / or rotor blade, which is coated by the method described above.
- the advantages stated for the method and its developments can be transferred analogously to the gas turbine.
- FIG 1 an oblique view of a platform of a turbine blade with indicated wing Stumpf
- FIG. 3 shows in a block diagram the sequence of a method for coating a turbine blade
- FIG. 4 shows a cross-sectional view of a gas turbine.
- an end ei ⁇ ner turbine blade 1 is shown schematically in an oblique view.
- the turbine blade 1 has a platform 2 and a wing 4, wherein the wing 4 is indicated in this illustration as a wing stump.
- the region of the platform 2, in which it has contact with the wing 4 or merges into it, is defined here as the contact zone 6. This is characterized by a ge ⁇ punctured border.
- a wing 4 projecting supernatant zone 8a, 8b.
- Projection zones 8a, 8b are each characterized by a ge ⁇ dashed border.
- a first layer of a coating by Be ⁇ spray applied it is usually impossible to prevent in the leaf-side spraying the platform 2 that also the end face 10 of the platform 2 is wetted with parts of the coating. These remnants of the first layer of the coating are to be removed from the end face 10a, 10b in the region of the projection zones 8a, 8b.
- the portions of the coating which have reached the end face 10c when the first layer is applied are left there.
- two adjacent platforms 2 of turbine blade 1 are shown schematically in a plan view.
- Each of the two platforms 2 in this case has an end face 10 which lies opposite the end face 10 of the respective other platform. If a layer of a coating is now applied to the turbine blade 1 and parts of this layer of the coating also fall on the respective end face 10 of the platform 2, this can lead to the gap 12, by which the two platforms 2 are spaced apart from one another , no longer has the defined width. To counter this, in the field of
- the platforms 2 expand in the transition zones 8a, 8b due to heat stronger than in the contact zones 6.
- By leaving of residues of a layer of the coating on the end faces 10c in the region of the contact zone 6 can thus prevents ⁇ the that the gap in this area has a too large width 12, which could fluidically lead to an undesired escape of hot gas.
- FIG. 3 schematically shows a block diagram of the sequence of a method 20 for coating a turbine blade.
- a first layer 22 of a coating 24 is first applied by spraying ⁇ hen 26 wing ⁇ side.
- the first layer 22 of the coating 24 is a superalloy 28, for example MCrAlY.
- spraying 26 of the platform 2 of the turbine blade or vane 1 with the superalloy 28 is applied, these also teilwei ⁇ se to the end face 10 of the platform 2.
- Projection zone 8a the applied to the end face 10a first layer 22 of the coating 24 by grinding 30 away from the end face 10a.
- the platform is only wing side after grinding 30, but not coated on the end face 10a with the super alloy ⁇ 28th
- the superalloy 28 also remains there at the end face.
- a further layer of the coating 24 is applied on the wing side.
- This further layer is formed by a ceramic TBC 32.
- FIG. 4 schematically shows, in a cross-sectional illustration, a gas turbine 40 with turbine blades 1, which have been coated according to the method described above.
- the turbine blades 1 can in this case be designed both as guide vanes 42 and as rotor blades 44.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102014224865.5A DE102014224865A1 (de) | 2014-12-04 | 2014-12-04 | Verfahren zur Beschichtung einer Turbinenschaufel |
PCT/EP2015/077062 WO2016087215A1 (de) | 2014-12-04 | 2015-11-19 | Verfahren zur beschichtung einer turbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3198049A1 true EP3198049A1 (de) | 2017-08-02 |
EP3198049B1 EP3198049B1 (de) | 2018-12-26 |
Family
ID=54601790
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15797329.8A Active EP3198049B1 (de) | 2014-12-04 | 2015-11-19 | Verfahren zur beschichtung einer turbinenschaufel |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP3198049B1 (de) |
CN (1) | CN107002214B (de) |
DE (1) | DE102014224865A1 (de) |
WO (1) | WO2016087215A1 (de) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10767501B2 (en) * | 2016-04-21 | 2020-09-08 | General Electric Company | Article, component, and method of making a component |
US11988104B1 (en) * | 2022-11-29 | 2024-05-21 | Rtx Corporation | Removable layer to adjust mount structure of a turbine vane for re-stagger |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1340331A (fr) * | 1962-09-07 | 1963-10-18 | Rateau Soc | Perfectionnements aux dispositifs de liaison des extrémités d'aubes mobiles de turbines |
IL98057A (en) * | 1990-05-14 | 1994-11-28 | United Technologies Corp | Variable thickness coating for turbine blades of airplanes |
EP0475316A1 (de) * | 1990-09-10 | 1992-03-18 | United Technologies Corporation | Vorrichtung zum Zurichten von Flächen an Gasturbinenschaufeln |
DE50211431D1 (de) * | 2001-09-25 | 2008-02-07 | Alstom Technology Ltd | Dichtungsanordnung zur dichtspaltreduzierung innerhalb einer strömungsrotationsmaschine |
US20060051212A1 (en) * | 2004-09-08 | 2006-03-09 | O'brien Timothy | Coated turbine blade, turbine wheel with plurality of coated turbine blades, and process of coating turbine blade |
US20060110254A1 (en) * | 2004-11-24 | 2006-05-25 | General Electric Company | Thermal barrier coating for turbine bucket platform side faces and methods of application |
US7140952B1 (en) * | 2005-09-22 | 2006-11-28 | Pratt & Whitney Canada Corp. | Oxidation protected blade and method of manufacturing |
EP2366488A1 (de) * | 2010-03-19 | 2011-09-21 | Siemens Aktiengesellschaft | Verfahren zum Wiederaufarbeiten einer Turbinenschaufel mit wenigstens einer Plattform |
US8708655B2 (en) * | 2010-09-24 | 2014-04-29 | United Technologies Corporation | Blade for a gas turbine engine |
-
2014
- 2014-12-04 DE DE102014224865.5A patent/DE102014224865A1/de not_active Withdrawn
-
2015
- 2015-11-19 CN CN201580065728.5A patent/CN107002214B/zh active Active
- 2015-11-19 EP EP15797329.8A patent/EP3198049B1/de active Active
- 2015-11-19 WO PCT/EP2015/077062 patent/WO2016087215A1/de active Application Filing
Also Published As
Publication number | Publication date |
---|---|
DE102014224865A1 (de) | 2016-06-09 |
CN107002214A (zh) | 2017-08-01 |
WO2016087215A1 (de) | 2016-06-09 |
EP3198049B1 (de) | 2018-12-26 |
CN107002214B (zh) | 2019-12-27 |
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