EP2316988A1 - Aube de turbine résistant à l'usure et à l'oxydation - Google Patents
Aube de turbine résistant à l'usure et à l'oxydation Download PDFInfo
- Publication number
- EP2316988A1 EP2316988A1 EP10188806A EP10188806A EP2316988A1 EP 2316988 A1 EP2316988 A1 EP 2316988A1 EP 10188806 A EP10188806 A EP 10188806A EP 10188806 A EP10188806 A EP 10188806A EP 2316988 A1 EP2316988 A1 EP 2316988A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- protective layer
- blade
- oxidation
- resistant
- turbine blade
- 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
- 230000003647 oxidation Effects 0.000 title claims abstract description 63
- 238000007254 oxidation reaction Methods 0.000 title claims abstract description 63
- 239000011241 protective layer Substances 0.000 claims abstract description 87
- 239000010410 layer Substances 0.000 claims abstract description 47
- 238000000034 method Methods 0.000 claims abstract description 28
- 238000004519 manufacturing process Methods 0.000 claims abstract description 24
- 239000000463 material Substances 0.000 claims abstract description 23
- 239000011230 binding agent Substances 0.000 claims abstract description 17
- 239000000919 ceramic Substances 0.000 claims abstract description 17
- 239000003082 abrasive agent Substances 0.000 claims abstract description 13
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 7
- 239000000126 substance Substances 0.000 claims abstract description 7
- 229910052582 BN Inorganic materials 0.000 claims abstract description 4
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims abstract description 4
- 239000000203 mixture Substances 0.000 claims abstract description 4
- 239000012720 thermal barrier coating Substances 0.000 claims description 23
- 238000003466 welding Methods 0.000 claims description 19
- 230000008021 deposition Effects 0.000 claims description 16
- 238000000227 grinding Methods 0.000 claims description 5
- 238000003801 milling Methods 0.000 claims description 4
- 239000000843 powder Substances 0.000 claims description 4
- 239000002356 single layer Substances 0.000 claims description 4
- 238000009826 distribution Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 2
- 230000000284 resting effect Effects 0.000 claims description 2
- 230000004888 barrier function Effects 0.000 abstract description 3
- 229910052751 metal Inorganic materials 0.000 abstract description 2
- 239000002184 metal Substances 0.000 abstract description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 abstract 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 abstract 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 abstract 1
- 229910052782 aluminium Inorganic materials 0.000 abstract 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract 1
- 229910052804 chromium Inorganic materials 0.000 abstract 1
- 239000011651 chromium Substances 0.000 abstract 1
- 229910017052 cobalt Inorganic materials 0.000 abstract 1
- 239000010941 cobalt Substances 0.000 abstract 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 abstract 1
- 229910052710 silicon Inorganic materials 0.000 abstract 1
- 239000010703 silicon Substances 0.000 abstract 1
- 229910052727 yttrium Inorganic materials 0.000 abstract 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 abstract 1
- 238000000576 coating method Methods 0.000 description 15
- 239000011248 coating agent Substances 0.000 description 10
- 239000007789 gas Substances 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 238000013461 design Methods 0.000 description 4
- 238000007750 plasma spraying Methods 0.000 description 4
- 238000005524 ceramic coating Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 239000012159 carrier gas Substances 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000000873 masking effect Effects 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 238000009420 retrofitting Methods 0.000 description 2
- 240000006829 Ficus sundaica Species 0.000 description 1
- 241001295925 Gegenes Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000001311 chemical methods and process Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004140 cleaning 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
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 150000004767 nitrides Chemical class 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 238000007712 rapid solidification Methods 0.000 description 1
- 238000009877 rendering Methods 0.000 description 1
- 238000005488 sandblasting Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 238000004901 spalling Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 239000002347 wear-protection layer Substances 0.000 description 1
Images
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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
-
- 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
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
-
- 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
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F01D5/284—Selection of ceramic materials
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49337—Composite blade
Definitions
- the invention relates to the field of power plant and materials technology. It relates to a wear and oxidation resistant turbine blade and a manufacturing method for such a wear and oxidation resistant turbine blade.
- the aim of the invention is to avoid the disadvantages of the known prior art.
- the invention has for its object to develop a wear and oxidation resistant turbine blade, which is applicable both for the manufacture of new parts, as well as for reconditioning (retrofit) and for their production of the existing manufacturing process must be minimally adjusted.
- the advantages of the invention are that the main body of the turbine blade is protected against oxidation on all critical surfaces that are exposed to the hot gas and at the same time the blade tip is tolerant to frictional contacts with the heat shield, which is a reduction of the hot gas gap and thus a reduction of leakage losses allowed. In this way, the efficiency of the turbine can be significantly increased.
- the blade according to the invention can be produced by a cost-effective and easily implementable method.
- the turbine blade can be scooped into the rotor of the turbine directly after laser deposition welding (LMF step) without further heat treatment and thus used for turbine operation.
- LMF step laser deposition welding
- the metallic protective layer may be covered by a ceramic thermal barrier coating and the second oxidation and wear resistant protective layer applied by laser deposition welding at least partially overlaps only with the metallic protective layer, but not with the ceramic thermal barrier coating. This achieves optimal oxidation protection and does not adversely affect the integrity of the TBC, i. a spalling of the TBC is prevented.
- the wear-resistant and oxidation-resistant protective layer consists of an abrasive material, which is preferably cubic boron nitride (cBN), and of an oxidation-resistant metallic binder material, in particular having the following chemical composition (in% by weight): 30 Cr, 5-10 Al, 0.3-1.2 Y, 0.1-1.2 Si, 0-2 others, balance Ni, Co.
- cBN cubic boron nitride
- the invention can be used for all blade types of a turbine.
- the abrasive layer is applied to the crown (or part of the crown).
- the method for better wear protection of the shroud web can be used.
- the described realization of the turbine blade is applicable both for the manufacture of new parts, as well as for the reconditioning (retrofit). In doing so, the existing production process has to be adapted only minimally.
- Fig. 1 shows a perspective view of a turbine blade 1 for a (here only schematically indicated) rotor 13 of a gas turbine, while in Fig. 2 a section along the line II-II in Fig. 1 is shown enlarged.
- the turbine blade 1 has an airfoil 2 which extends in the radial direction r (relative to the rotor) and which is formed on the blade tip 9 as a crown 3 with inner and outer crown edges extending in the radial direction.
- the base material of the airfoil is, for example, a nickel-base superalloy.
- the surface of the airfoil is at least on the crown edges (s. Fig.
- the radially outer blade tip is constructed from a second wear and oxidation resistant protective layer 5 constructed by known laser deposition welding, this second protective layer 5 at least partially on the blade tip 9 along the outer and / or inner crown edge overlaps with the first metallic protective layer 4 arranged there.
- the protective layer 5 can be single-layer or multi-layered. In particular, with multilayer overlapping protective layers 5, which are applied by means of LMF, a variation of the length L of the turbine blade 1 can be realized well.
- the protective layer 5 consists of an abrasive material 6, which is preferably cubic boron nitride (cBN), and an oxidation-resistant binder material which preferably has the following chemical composition (in% by weight): 15-30 Cr, 5-10 Al, 0.3- 1.2 Y, 0.1-1.2 Si, 0-2 others, balance Ni, Co.
- cBN cubic boron nitride
- a concretely used suitable binder material is z.
- Fig. 3a and 3b This is especially good on the Fig. 3a and 3b to see the photos of coated according to the invention blade tips.
- the wear-resistant and oxidation-resistant protective layer 5 one can very well recognize the pointed cBN particles as abrasive material 6 which are embedded in the binder material 7.
- This protective layer 5 was by LMF using a fiber-coupled high-power diode laser with max. 1000W output power realized.
- Fig. 3a (left) partially overlaps the new coating with an MCrAIY protective layer 4 previously applied by plasma spraying Fig. 3b the turbine blade 1 on the MCrAIY layer 4 has an additional ceramic thermal barrier coating (TBC) 4a.
- TBC ceramic thermal barrier coating
- Fig. 4 schematically shows a further embodiment of a turbine blade 1 according to the invention with a shroud 11, which is arranged radially outward on the blade tip and a web 12 has.
- a shroud 11 which is arranged radially outward on the blade tip and a web 12 has.
- the special feature of the approach described here is the special design of such a wear-resistant protective layer 5.
- the single-layer or multi-layer 5 is applied so that it at least partially overlaps with other existing protective layers 4.
- a ceramic insulating layer TBC, Thermal Barrier Coating
- TBC Thermal Barrier Coating
- the abrasive layer is applied as the last step in the process chain by laser deposition welding.
- a simple and cost-effective implementation is to remove the radially outwardly located MCrAlY (possibly also TBC) layer (s) by milling or grinding or by chemical process by a defined amount completely.
- the wear-resistant layer is applied by LMF to the now exposed base material.
- the decisive factor here is the locally very limited action of the laser beam, which keeps the effects on the adjacent areas of the blade very low in the case of controlled process control. It is thus possible to apply such a wear-resistant layer in the immediate vicinity of a TBC protective layer without damaging it (see, for example, US Pat Fig. 4b ).
- the surfaces of the turbine blade 1 (eg the blade root) which are not to be coated need not be protected by a masking method.
- the LMF process is a welding process and produces a stable metallurgical bond with the main body of the blade without additional diffusion heat treatment. Due to the low local heat input, the local hardening is kept small despite the rapid solidification process. Thus, the component immediately after the application of the Wear-resistant protective layer can be installed without further subsequent steps.
- Fig. 5 shows various implementation options.
- the wear-resistant MCrAlY protective layer 4 is first applied to the blade 1, for example by plasma spraying. Subsequently, this protective layer 4 is locally removed at the blade tip, for example by milling or grinding ( Fig. 5b ).
- the wear and oxidation resistant protective layer 5 is applied by the LMF method. The last applied protective layer 5 overlaps at least partially with the previously applied oxidation-resistant MCrAlY protective layer 4 (FIG. Fig. 5c ). As a result, the entire blade body is protected against oxidation at high operating temperatures.
- the wear-resistant and oxidation-resistant protective layer 5 overlaps with the previously applied MCrAlY protective layer 4 in order to ensure optimum protection of the airfoil 1 against oxidation. Due to the localized and minimized heat input, the LMF method can be performed in close proximity to the ceramic thermal barrier coating 4a, without the TBC flaking off.
- FIG. 6 Another embodiment is in Fig. 6
- This variant can be used, for example, when the crown 3 of the turbine blade 1 is so wide that the wear-resistant and oxidation-resistant protective layer 5 can not be applied with a single welding track.
- initially at least one multilane, overlapping intermediate layer 8 of oxidation-resistant binder material 7 can be applied.
- at least one further track is applied with combined supply of binder material 7 and abrasive material 6 to the first deposited layer (s). It is not necessary that the abrasive particles 6 are distributed over the entire width of the blade tip 9.
- the in Fig. 6 shown variant cost-optimized production of oxidation and wear resistant blade tip.
- Fig. 7 shows by way of example a coating device 14 for carrying out the last step of the inventive method.
- the device 14 is in EP 1 476 272 B1 described in detail, the content of this document is part of the present application.
- abrasive material 6 and oxidation-resistant binder material 7 are mixed in a powder nozzle, transported by means of a carrier gas 15 and then injected concentrically around the laser beam 10 as a focused powder jet into the melt pool 16 produced by the laser beam 10 at the blade tip 9.
- the temperature or temperature distribution in the molten bath is recorded online (optical temperature signal 17) and this information is not recorded with the help of a Fig. 7 used to control the laser power during laser deposition welding and / or to control the relative movement between the laser beam 10 and the turbine blade 1 controlled.
- the invention can be used in many ways for deckless turbine blades, but also for components with shroud. Attention must be paid to the service life of the abrasive coating, which depends on the respective operating conditions (temperature, fuel). By a good distribution and complete embedding of Abrasivteilchen in the oxidation-resistant binder matrix lifetime optimization is achieved. Nevertheless, the main object of the invention is to protect the turbine blade tip, especially during the break-in period. This corresponds to a duration of several tens to several hundred operating hours.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laser Beam Processing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009051661 | 2009-11-02 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2316988A1 true EP2316988A1 (fr) | 2011-05-04 |
EP2316988B1 EP2316988B1 (fr) | 2015-07-08 |
Family
ID=43402110
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10188806.3A Active EP2316988B1 (fr) | 2009-11-02 | 2010-10-26 | Aube de turbine résistant à l'usure et à l'oxydation |
Country Status (5)
Country | Link |
---|---|
US (1) | US8740572B2 (fr) |
EP (1) | EP2316988B1 (fr) |
JP (1) | JP5693149B2 (fr) |
CA (1) | CA2719273C (fr) |
DE (1) | DE102010049398A1 (fr) |
Cited By (7)
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WO2014099814A1 (fr) * | 2012-12-17 | 2014-06-26 | General Electric Company | Aubes de turbine robustes |
WO2015120994A1 (fr) * | 2014-02-11 | 2015-08-20 | Siemens Aktiengesellschaft | Résistance à l'usure d'un composant à haute température améliorée par un revêtement au cobalt |
EP3093371A3 (fr) * | 2015-05-12 | 2017-01-11 | MTU Aero Engines GmbH | Combinaison de blindage d'extremite d'aubes et de couche de protection contre l'erosion et son procede de fabrication |
EP3357630A1 (fr) * | 2017-02-02 | 2018-08-08 | MTU Aero Engines GmbH | Procédé et dispositif de réparation d'un bout d'aube endommagée d'une aube de turbine avec un revêtement dur et pourvue d'un revêtement d'aube |
EP3366886A1 (fr) * | 2017-02-27 | 2018-08-29 | Rolls-Royce Corporation | Structure de pointe pour aube de turbine avec côté pression et rails latéraux d'aspiration |
EP3546702A1 (fr) * | 2018-03-29 | 2019-10-02 | Siemens Aktiengesellschaft | Aube mobile de turbine pour une turbine à gaz |
EP3546703A1 (fr) * | 2018-03-29 | 2019-10-02 | Siemens Aktiengesellschaft | Aube mobile de turbine pour une turbine à gaz |
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FR2978931B1 (fr) * | 2011-08-10 | 2014-05-09 | Snecma | Procede de realisation d'un renfort de protection du bord d'attaque d'une pale |
EP2604797B1 (fr) * | 2011-12-13 | 2020-01-22 | MTU Aero Engines GmbH | Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif |
US20140010663A1 (en) * | 2012-06-28 | 2014-01-09 | Joseph Parkos, JR. | Gas turbine engine fan blade tip treatment |
US8858873B2 (en) | 2012-11-13 | 2014-10-14 | Honeywell International Inc. | Nickel-based superalloys for use on turbine blades |
US9909428B2 (en) * | 2013-11-26 | 2018-03-06 | General Electric Company | Turbine buckets with high hot hardness shroud-cutting deposits |
CN103659024B (zh) * | 2013-12-31 | 2016-03-30 | 无锡透平叶片有限公司 | 用于汽轮机叶片进气边激光熔覆的坡口结构 |
US9358663B2 (en) | 2014-04-16 | 2016-06-07 | General Electric Company | System and methods of removing a multi-layer coating from a substrate |
US20160237832A1 (en) * | 2015-02-12 | 2016-08-18 | United Technologies Corporation | Abrasive blade tip with improved wear at high interaction rate |
DE102015208783A1 (de) | 2015-05-12 | 2016-11-17 | MTU Aero Engines AG | Abdeckverfahren zur Herstellung einer Kombination von Schaufelspitzenpanzerung und Erosionsschutzschicht |
US10415579B2 (en) | 2016-09-28 | 2019-09-17 | General Electric Company | Ceramic coating compositions for compressor blade and methods for forming the same |
EP3301260A1 (fr) * | 2016-09-30 | 2018-04-04 | Siemens Aktiengesellschaft | Aube de turbine à extrémité à durée de vie prolongée et procédé de fabrication de ladite aube de turbine |
RU2645631C1 (ru) * | 2016-12-07 | 2018-02-26 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева-КАИ" (КНИТУ-КАИ) | Способ нанесения покрытия на образец (варианты) и устройство для его осуществления (варианты) |
US11346232B2 (en) * | 2018-04-23 | 2022-05-31 | Rolls-Royce Corporation | Turbine blade with abradable tip |
US10933469B2 (en) | 2018-09-10 | 2021-03-02 | Honeywell International Inc. | Method of forming an abrasive nickel-based alloy on a turbine blade tip |
US20200157953A1 (en) * | 2018-11-20 | 2020-05-21 | General Electric Company | Composite fan blade with abrasive tip |
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- 2010-10-26 EP EP10188806.3A patent/EP2316988B1/fr active Active
- 2010-10-26 DE DE102010049398A patent/DE102010049398A1/de not_active Withdrawn
- 2010-11-01 JP JP2010245232A patent/JP5693149B2/ja not_active Expired - Fee Related
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GB2075129A (en) * | 1980-05-01 | 1981-11-11 | Gen Electric | Tip cap for a rotor blade and method of replacement |
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EP1245787A2 (fr) * | 2001-03-27 | 2002-10-02 | General Electric Company | Refroidissement d'une extrémité d'aube revêtu |
EP1476272B1 (fr) | 2002-02-20 | 2007-03-28 | Alstom Technology Ltd | Procede de refusion ou de formage de metaux au laser commandes sur la surface d'un article |
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CN104838092A (zh) * | 2012-12-17 | 2015-08-12 | 通用电气公司 | 耐用涡轮叶片 |
WO2014099814A1 (fr) * | 2012-12-17 | 2014-06-26 | General Electric Company | Aubes de turbine robustes |
US10100651B2 (en) | 2014-02-11 | 2018-10-16 | Siemens Aktiengesellschaft | Wear resistance of a high-temperature component imparted by a cobalt coating |
WO2015120994A1 (fr) * | 2014-02-11 | 2015-08-20 | Siemens Aktiengesellschaft | Résistance à l'usure d'un composant à haute température améliorée par un revêtement au cobalt |
RU2655397C2 (ru) * | 2014-02-11 | 2018-05-28 | Сименс Акциенгезелльшафт | Улучшенная износостойкость высокотемпературной конструкционной детали, придаваемая кобальтовым покрытием |
EP3093371A3 (fr) * | 2015-05-12 | 2017-01-11 | MTU Aero Engines GmbH | Combinaison de blindage d'extremite d'aubes et de couche de protection contre l'erosion et son procede de fabrication |
EP3357630A1 (fr) * | 2017-02-02 | 2018-08-08 | MTU Aero Engines GmbH | Procédé et dispositif de réparation d'un bout d'aube endommagée d'une aube de turbine avec un revêtement dur et pourvue d'un revêtement d'aube |
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US10533429B2 (en) | 2017-02-27 | 2020-01-14 | Rolls-Royce Corporation | Tip structure for a turbine blade with pressure side and suction side rails |
EP3546702A1 (fr) * | 2018-03-29 | 2019-10-02 | Siemens Aktiengesellschaft | Aube mobile de turbine pour une turbine à gaz |
EP3546703A1 (fr) * | 2018-03-29 | 2019-10-02 | Siemens Aktiengesellschaft | Aube mobile de turbine pour une turbine à gaz |
WO2019185713A1 (fr) | 2018-03-29 | 2019-10-03 | Siemens Aktiengesellschaft | Pale de turbine pour turbine à gaz |
WO2019185526A1 (fr) | 2018-03-29 | 2019-10-03 | Siemens Aktiengesellschaft | Pale de turbine pour turbine à gaz |
Also Published As
Publication number | Publication date |
---|---|
JP2011099437A (ja) | 2011-05-19 |
CA2719273A1 (fr) | 2011-05-02 |
CA2719273C (fr) | 2017-03-28 |
US8740572B2 (en) | 2014-06-03 |
DE102010049398A1 (de) | 2011-05-05 |
EP2316988B1 (fr) | 2015-07-08 |
JP5693149B2 (ja) | 2015-04-01 |
US20110103968A1 (en) | 2011-05-05 |
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