EP2316988B1 - 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 PDF

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Publication number
EP2316988B1
EP2316988B1 EP10188806.3A EP10188806A EP2316988B1 EP 2316988 B1 EP2316988 B1 EP 2316988B1 EP 10188806 A EP10188806 A EP 10188806A EP 2316988 B1 EP2316988 B1 EP 2316988B1
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EP
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Prior art keywords
resistant
oxidation
turbine blade
protective coating
coating
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EP10188806.3A
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German (de)
English (en)
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EP2316988A1 (fr
Inventor
Matthias Hoebel
Günter Ambrosy
Felix Reinert
Stephane Barril
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General Electric Technology GmbH
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Alstom Technology AG
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    • 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)

Claims (15)

  1. Aube de turbine (1) pour le rotor (13) d'une turbine, avec une pale (2) s'étendant en direction radiale (r) et présentant une pointe d'aube (9), et qui est configurée à la pointe d'aube (9) soit sous forme de couronne (3) avec un bord de couronne intérieur et extérieur s'étendant en direction radiale (r) soit comme anneau de renforcement (11) avec une nervure (12) s'étendant en direction radiale avec des bords latéraux, dans laquelle la pale (2) est munie sur sa surface au moins dans des zones déterminées d'au moins une première couche de protection (4, 4a) en matériau résistant à l'oxydation, caractérisée en ce que
    - ladite au moins une première couche de protection résistant à l'oxydation (4) est une couche métallique, notamment une couche de MCrAlY,
    - cette première couche de protection (4) est disposée au moins sur le bord de couronne intérieur et/ou extérieur ou sur les bords de nervure,
    - cette première couche de protection (4) n'est pas présente sur la pointe d'aube (9) de l'aube de turbine (1) située radialement à l'extérieur, et
    - la pointe d'aube (9) située radialement à l'extérieur se compose d'une deuxième couche de protection (5) en au moins une couche résistant à l'usure et à l'oxydation déposée au moyen d'un procédé connu de soudage par rechargement au laser, dans laquelle cette deuxième couche de protection (5) sur la pointe d'aube (9) est en recouvrement au moins partiel le long du bord de couronne extérieur et/ou intérieur ou des bords de nervure avec la première couche de protection métallique (4) disposée à ces endroits.
  2. Aube de turbine (1) selon la revendication 1, caractérisée en ce que ladite au moins une couche de protection métallique (4) est recouverte d'une couche céramique d'isolation thermique (4a) et dans laquelle la deuxième couche de protection résistant à l'usure et à l'oxydation (5) déposée par soudage par rechargement au laser est en recouvrement au moins partiel uniquement avec la couche de protection métallique (4) mais pas avec la couche céramique d'isolation thermique (4a) .
  3. Aube de turbine (1) selon la revendication 1 ou 2, caractérisée en ce que la couche de protection résistant à l'usure et à l'oxydation (5) se compose d'un matériau abrasif (6) et d'un matériau liant métallique résistant à l'oxydation (7).
  4. Aube de turbine (1) selon la revendication 3, caractérisée en ce que le matériau abrasif (6) est le nitrure de bore cubique (cBN).
  5. Aube de turbine (1) selon la revendication 3, caractérisée en ce que le matériau liant résistant à l'oxydation (7) présente la composition chimique suivante (en % en poids): 15-30 Cr, 5-10 Al, 0,3-1,2 Y, 0,1-1,2 Si, 0-2 autres, reste Ni, Co.
  6. Aube de turbine (1) selon la revendication 3, caractérisée en ce que la proportion du matériau abrasif (6) dans la couche de protection (5), dans la mesure où celle-ci est en plusieurs couches, augmente en direction radiale (r) vers l'extérieur.
  7. Aube de turbine (1) selon la revendication 1 ou 2, caractérisée en ce qu'une couche intermédiaire (8), qui se compose exclusivement de matériau liant résistant à l'oxydation (7), est disposée entre la première couche de protection métallique (4) et la deuxième couche de protection résistant à l'usure et à l'oxydation (5), dans laquelle la couche intermédiaire (8) recouvre au moins partiellement la première couche de protection (4) et dans laquelle la deuxième couche de protection (5) recouvre de nouveau au moins partiellement la couche intermédiaire (8).
  8. Aube de turbine (1) selon l'une quelconque des revendications 1 à 7, caractérisée en ce que l'aube de turbine (1) est une aube de turbine reconditionnée.
  9. Aube de turbine (1) selon la revendication 8, caractérisée en ce que l'aube de turbine a été utilisée au cours d'un intervalle de fonctionnement précédent de la turbine sans pointe d'aube abrasive (9).
  10. Aube de turbine (1) selon l'une quelconque des revendications 1 à 9, caractérisée en ce que l'aube de turbine (1) est un composant neuf.
  11. Aube de turbine (1) selon l'une quelconque des revendications 1 à 10 avec une longueur (L), caractérisée en ce que la longueur (L) peut être modifiée au moyen des couches (5) déposées par soudage par rechargement au laser.
  12. Procédé de fabrication d'une aube de turbine (1) selon l'une quelconque des revendications 1 à 11, dans lequel, au cours d'une étape de fabrication précédente, on revêt la pale (2) de l'aube de turbine (1) sur sa surface au moins dans des zones déterminées avec la couche de protection métallique résistant à l'usure et à l'oxydation (4), notamment une couche de MCrAlY, et on dépose en option sur cette couche de protection (4) une couche céramique d'isolation thermique résistant à l'oxydation (4a), caractérisé en ce que
    - on enlève ladite au moins une couche de protection résistant à l'oxydation (4, 4a) sur la pointe d'aube (9) située radialement à l'extérieur par usinage mécanique contrôlé et/ou par dégarnissage chimique, et ensuite
    - on dépose la couche de protection résistant à l'usure et à l'oxydation (5) au moyen d'un procédé connu de soudage par rechargement au laser en une seule couche ou en plusieurs couches sur la pointe d'aube (9), de telle manière que, le long du bord de couronne extérieur et/ou intérieur ou des bords de nervure, elle soit en recouvrement au moins partiel avec ladite première couche de protection métallique (4) déposée antérieurement mais pas avec la couche céramique d'isolation thermique (4a) déposée en option antérieurement.
  13. Procédé selon la revendication 12, caractérisé en ce que l'on effectue l'usinage mécanique contrôlé par meulage ou par fraisage CNC.
  14. Procédé selon la revendication 12, caractérisé en ce que, lors de l'étape de soudage par rechargement au laser de la pointe d'aube (9), on mélange un matériau abrasif (6) et un matériau liant résistant à l'oxydation (7) dans une buse de pulvérisation et on les projette ensuite de façon concentrique autour du faisceau laser (10) sous forme de jet de poudre dans le bain fondu produit par le faisceau laser (10) sur la pointe d'aube (9).
  15. Procédé selon la revendication 12 ou 14, caractérisé en ce que l'on détermine en outre en ligne pendant le soudage par rechargement au laser la température ou la répartition de la température dans le bain fondu et en ce que l'on utilise cette information à l'aide d'un système de régulation, pour contrôler la puissance du laser pendant le soudage par rechargement au laser et/ou pour faire varier de façon contrôlée le mouvement relatif entre le faisceau laser (10) et l'aube de turbine (1).
EP10188806.3A 2009-11-02 2010-10-26 Aube de turbine résistant à l'usure et à l'oxydation Active EP2316988B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009051661 2009-11-02

Publications (2)

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EP2316988A1 EP2316988A1 (fr) 2011-05-04
EP2316988B1 true EP2316988B1 (fr) 2015-07-08

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US (1) US8740572B2 (fr)
EP (1) EP2316988B1 (fr)
JP (1) JP5693149B2 (fr)
CA (1) CA2719273C (fr)
DE (1) DE102010049398A1 (fr)

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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)
CN110899695A (zh) * 2019-12-09 2020-03-24 浙江翰德圣智能再制造技术有限公司 一种激光增材制造微弧火花MCrAlY电极的方法

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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
US20150308276A1 (en) * 2012-12-17 2015-10-29 General Electric Company Robust 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
DE102014202457A1 (de) * 2014-02-11 2015-08-13 Siemens Aktiengesellschaft Verbesserte Verschleißbeständigkeit eines Hochtemperaturbauteils durch Kobaltbeschichtung
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US20110103968A1 (en) 2011-05-05
EP2316988A1 (fr) 2011-05-04
US8740572B2 (en) 2014-06-03
JP5693149B2 (ja) 2015-04-01
JP2011099437A (ja) 2011-05-19
CA2719273A1 (fr) 2011-05-02
DE102010049398A1 (de) 2011-05-05

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