EP1529123B1 - Materiau intermetallique et son utilisation - Google Patents

Materiau intermetallique et son utilisation Download PDF

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Publication number
EP1529123B1
EP1529123B1 EP20030739941 EP03739941A EP1529123B1 EP 1529123 B1 EP1529123 B1 EP 1529123B1 EP 20030739941 EP20030739941 EP 20030739941 EP 03739941 A EP03739941 A EP 03739941A EP 1529123 B1 EP1529123 B1 EP 1529123B1
Authority
EP
European Patent Office
Prior art keywords
intermetallic
felt
turbine blade
intermetallic felt
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.)
Expired - Fee Related
Application number
EP20030739941
Other languages
German (de)
English (en)
Other versions
EP1529123A1 (fr
Inventor
Andreas KÜNZLER
Mohamed Nazmy
Markus E. Staubli
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1529123A1 publication Critical patent/EP1529123A1/fr
Application granted granted Critical
Publication of EP1529123B1 publication Critical patent/EP1529123B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Classifications

    • 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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
    • Y10T428/249962—Void-containing component has a continuous matrix of fibers only [e.g., porous paper, etc.]
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
    • Y10T428/249967—Inorganic matrix in void-containing component
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
    • Y10T428/249967—Inorganic matrix in void-containing component
    • Y10T428/24997—Of metal-containing material

Definitions

  • the invention relates to an intermetallic material according to claims 1 and 2 and the use of this material as a felt and as a high-temperature protective layer according to claims 3 and 4.
  • the guide vanes and rotor blades of gas turbines are exposed to heavy loads.
  • the impeller of the gas turbine is fitted with a very small clearance to the stator, so that it comes to rub against.
  • a honeycomb structure is attached on the stator of the gas turbine.
  • the honeycomb structure is made of a heat-resistant metal alloy.
  • Another type are smooth, coated or uncoated thermal damper segments (WSS), which radially face the rotating blade at the outer radius. The blade tip then rubs against these heat dam segments.
  • WSS thermal damper segments
  • the coating has only a limited liability to the turbine blade.
  • cooling air bores with which either the heat spreader segment and / or the blade can be provided, are clogged during rubbing.
  • EP 132,667 or DE-C2-32 03 869 It is known to use metal felts at various points of gas turbine components, such as at the tip of a turbine blade ( DE-C2-32 03 869 ), between a metal core or a ceramic outer skin ( DE-C2 32 35 230 ) or as a shell of the turbine blade ( EP-B1-132 667 ).
  • these embodiments have the disadvantage that the metal felt used has insufficient oxidation resistance. Increases in hot-gas temperatures, for example in gas turbines today, mean that the materials used must always meet higher requirements. However, the metal felts in the mentioned documents no longer meet the requirement of today's standards, in particular with regard to a necessary degree of oxidation resistance.
  • EP-A2-0 916 897 and EP-A2-1 076 157 are metal felts, which are composed of an intermetallic alloy, known. These felts are made of sintered and pressed intermetallic fibers and have by the intermetallic phases compared to the above materials significantly improved material properties in terms of strength, oxidation resistance, ductility and abradability. Metallic high temperature fibers have also been described in VDI Report 1151, 1995 (Metallic High Temperature Fibers by Melt Extraction - Fabrication, Properties, Applications).
  • US 3,928,026 is a coating for Ni and Co base superalloys known with the following chemical composition (in wt .-%): 11-48 Co, 10-40 Cr, 9-15 Al, 0.1-1.0 reactive metal from the group of Y, Sc, Th, La and other rare earths, balance Ni, with the Ni content being at least 15%.
  • the invention solves the problem of further improving the material properties of intermetallic alloys, so that they as a felt or as a high-temperature protective layer of thermal heavily loaded gas turbine components can be used.
  • a suitable choice of the composition of the intermetallic alloy it should have sufficient strength, oxidation resistance, deformability, abradability and sufficient vibration damping properties.
  • the present invention also relates to an intermetallic material consisting of the following composition (wt .-%) 12 Al, 22 Cr, 36 Co, 0.2 Y, 0.2 Hf, 3 Fe, balance Ni and unavoidable impurities or from 10 Al, 22 Cr , 36 Co, 0.2 Y, 0.2 Hf, 2 Ta, 3 Fe, balance Ni and unavoidable impurities.
  • Such an intermetallic material can be used advantageously as a high-temperature coating of, for example, the turbine blades or other components due to the material properties.
  • intermetallic felt on frictional components in thermal turbomachinery is conceivable.
  • This may be, for example, the rotor or stator, the tip of a turbine blade, the turbine blades arranged opposite heat accumulation segments or the platform of the turbine blade.
  • a further advantage arises when the intermetallic felt is coated with a ceramic material, since a very good adhesion of the ceramic material is achieved on the rough surface of the intermetallic felt. This gives, for example, the tip of the guide or blade good protection against thermal and friction-induced mechanical effects.
  • Another advantage arises from the fact that cooling air holes are not clogged by the abrasion during operation, since it is a porous material.
  • the intermetallic felt also has sufficient vibration-absorbing properties.
  • a turbine blade 1 with a tip 11, an airfoil 14, a platform 12 and a blade root 13 is shown. It may be, for example, a guide or a blade of a gas turbine or a compressor.
  • an intermetallic felt 2 according to the invention is arranged at the tip 11 of this turbine blade 1.
  • the intermetallic felt 2 was made on the basis of a Ni-Co aluminide. To ensure adequate strength, oxidation resistance and to achieve ductility, the elements Ta, Cr, Y are added. Table 1 shows the composition according to the invention of the Ni-Co aluminide (designation IM 28 and IM 29).
  • the advantage of the intermetallic felts 2 is the significantly improved oxidation resistance. From the Fig. 7 and 8th For example, the oxidation of various materials can be seen in comparison with the commercial nickel base alloys Hastelloy X, Haynes 230, Haynes 214, and the alloy SV349. Tab. 1 shows the composition of the experimental alloys.
  • FIG. 8 shows the increase in weight given in Tab. 2 in [mg / cm 2 ] over a period of 12 hours at a temperature of 1200 ° C.
  • the weight gain is representative of the oxidation of the materials applied. From the Fig. 8 It can be seen that the comparative alloy Hastelloy X already after a short time of about 100 min. up to approx. 300 min. has a double weight gain. As the time progresses, Hastelloy X's weight gain continues to increase, while the IM14 and IM15 intermetallic felts are set to a constant between 0.6 - 0.8 mg / cm 2 , while the IM 28 and 29 alloys are even lower.
  • the oxidation resistance in the intermetallic felts is significantly improved, since a constant oxide layer has formed.
  • the two alloys IM 28 and 29 differ from the alloys IM 14 and IM 15 by a Co content of 36%. This further increases the oxidation resistance of the intermetallic material.
  • the Fig. 7 shows one with the Fig. 8 comparable presentation, but the experiments were carried out at a temperature of 1050 ° C.
  • the intermetallic felt 2 can be coated with a ceramic material 3, for example with a TBC (Thermal Barrier Coating).
  • TBC is a Y stabilized Zr oxide.
  • Equivalent materials are also conceivable.
  • the ceramic material 3 can be sprayed onto the intermetallic felt 2, it has by the uneven surface of the intermetallic felt 2 a very good grip on it and a good oxidation resistance.
  • the ceramic material 3 is a good protection against thermal and mechanical, for example, frictional effects.
  • cooling air holes which may be present in the turbine blade 1 or on the rotor / stator 4, do not clog, since the intermetallic felt 2 is a porous material.
  • FIG. 2 schematically shows a representation of a gas turbine with a rotor 4a, a stator 4b.
  • blades 6, on the stator 7 vanes 7 are attached.
  • heat guide segments 8 are usually arranged opposite the guide vanes 6, 7.
  • these heat barrier segments 8 may also consist wholly or partly of an intermetallic felt. Due to the porous properties improved cooling at this point is also possible if it has come to an abrasion, as the porous structure of the intermetallic felt prevents clogging.
  • the abrasion can be reduced as already described by a layer of TBC.
  • the component may also be cooled below the TBC layer, since the cooling medium can escape laterally through the porous felt.
  • the FIG. 5 shows a heat recovery segment according to the invention 8 according to the section V in the FIG. 2 ,
  • the intermetallic felt 2 was attached to a supporting base structure 5.
  • the supporting base structure 5 has fastening means 9, which for attachment to in the FIG. 5 not shown rotor 4a and stator 4b are used.
  • the lateral fastening means 9 are interconnected by struts 10. Between the struts 10 is on the side which faces the turbine blades, the intermetallic felt 2 is used and mechanically connected thereto. This can be done for example by soldering, welding or pouring. For reasons of durability, the felt should be firmly bonded to the supporting base structure 5.
  • FIG. 6 shows the section VI-VI of FIG. 5 ,
  • the struts 10 connecting the two fastening means 9 do not penetrate the intermetallic felt 2, but the intermetallic felt 2 is merely attached to them.
  • the intermetallic felt 2 can in turn be coated with a ceramic material 3, for example with a TBC (Thermal Barrier Coating). Equivalent materials are also conceivable.
  • a cooling effect is maintained even with abrasion, since there is no clogging of the intermetallic felt 2.
  • the intermetallic felt in the embodiment in the FIG. 3 mounted on the platform 12 of the turbine blade 1 of the thermal turbomachinery. Again, it makes sense, as with the Figure 1,2 . 5 and 6 described to coat the felt 2 with a ceramic material 3.
  • This has the advantage that the TBC adheres particularly well to the intermetallic felt and the felt is oxidation resistant. There is no additional binding layer (eg MCrA-IY) needed. In the FIG. 3 this is shown next to the right turbine blade 1.
  • the TBC also serves as protection against wear.
  • FIG. 4 shows a second variant of the embodiment of the detail IV of Figure 3.
  • a supporting base structure 5 consisting of a casting or other metal attached.
  • the supporting basic structure 5 may also consist of different chambers in order to ensure an optimal air supply to the intermetallic felt 2.
  • the intermetallic felt can also be used at points within the gas turbine that are subject to vibration, since the felt in addition to the aforementioned oxidation resistance also has very good vibration damping properties.
  • an intermetallic material according to the invention can advantageously also be used as a high-temperature coating 15 on the turbine blades or other components.
  • the two alloys also have improved oxidation properties, unlike the SV 349 alloy.
  • various prior art coating methods are known for applying the protective layer, for example, a plasma spray method.
  • a plasma spray method In this case, an existing of the material to be applied, metallic powder is introduced into a flame or a plasma jet. This powder melts on the spot and is sprayed against the surface to be coated, where the material solidifies and forms a continuous layer.
  • a physical (or chemical) vapor deposition process is also possible.
  • solid coating material is heated in block form and evaporated (eg with a laser or an electron beam). The vapor settles on the base material and forms a coating there after an adequate time.
  • Other, equivalent coating methods are also conceivable.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un matériau intermétallique de la composition suivante : 8-15 % en poids d'aluminium, 15-25 % en poids de chrome, 20-40 % en poids de cobalt, 0-5 % de tantale, 0-0.03 % en poids de lanthane, 0-0.5 % en poids d'yttrium, 0-1.5 % en poids de silicium, 0-1 % en poids de hafnium, 0-0.2 % en poids de zirconium, 0-0.2 % en poids de bore, 0-0.1 % en poids de carbone, 0-4 % en poids de fer, le reste étant du nickel et les inévitables impuretés. L'invention concerne également l'utilisation de ce matériau comme couche protectrice haute température et aux endroits de turbomachines thermiques affectés de frottement ou vibrations.

Claims (10)

  1. Matériau intermétallique de composition suivante (en % en poids) : 12 Al, 22 Cr, 36 Co, 0,2 Y, 0,2 Hf, 3 Fe, et le reste Ni et des impuretés inévitables.
  2. Matériau intermétallique de composition suivante (en % en poids) : 10 Al, 22 Cr, 36 Co, 0,2 Y, 0,2 Hf, 2 Ta, 3 Fe, et le reste Ni et des impuretés inévitables.
  3. Utilisation d'un matériau intermétallique selon l'une quelconque des revendications 1 ou 2, en tant que revêtement haute température (15) dans des turbomachines thermiques.
  4. Utilisation d'un matériau intermétallique selon l'une quelconque des revendications 1 ou 2, en tant que feutre sur des composants sujets à la friction dans des turbomachines thermiques.
  5. Utilisation d'un feutre intermétallique selon la revendication 4,
    caractérisée en ce que le feutre intermétallique est disposé sur un rotor (4, 4a) ou un stator (4, 4b).
  6. Utilisation d'un feutre intermétallique selon la revendication 4,
    caractérisée en ce que le composant (1, 8) est une aube de turbine (1) et la pointe (11) de l'aube de turbine (1) est munie d'un feutre intermétallique (2).
  7. Utilisation d'un feutre intermétallique selon la revendication 4,
    caractérisée en ce que le composant (1, 8) est une aube de turbine (1) et la plate-forme (12) de l'aube de turbine (1) est munie d'un feutre intermétallique (2).
  8. Utilisation d'un feutre intermétallique selon la revendication 4,
    caractérisée en ce que le composant (1, 8) est un segment accumulateur de chaleur (8) et le segment accumulateur de chaleur (8) se compose en totalité ou en partie d'un feutre intermétallique (2).
  9. Utilisation d'un feutre intermétallique selon l'une quelconque des revendications 4 à 7,
    caractérisée en ce que le feutre intermétallique (2) est revêtu d'un matériau céramique (3).
  10. Utilisation d'un feutre intermétallique selon la revendication 4,
    caractérisée en ce que le feutre est utilisé sur des composants sujets à des vibrations dans des turbomachines thermiques.
EP20030739941 2002-08-16 2003-07-24 Materiau intermetallique et son utilisation Expired - Fee Related EP1529123B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH140602 2002-08-16
CH14062002 2002-08-16
PCT/CH2003/000503 WO2004016819A1 (fr) 2002-08-16 2003-07-24 Materiau intermetallique et son utilisation

Publications (2)

Publication Number Publication Date
EP1529123A1 EP1529123A1 (fr) 2005-05-11
EP1529123B1 true EP1529123B1 (fr) 2011-10-05

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP20030739941 Expired - Fee Related EP1529123B1 (fr) 2002-08-16 2003-07-24 Materiau intermetallique et son utilisation

Country Status (5)

Country Link
US (1) US7141128B2 (fr)
EP (1) EP1529123B1 (fr)
CN (1) CN100430499C (fr)
AU (1) AU2003285270A1 (fr)
WO (1) WO2004016819A1 (fr)

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US7378132B2 (en) * 2004-12-14 2008-05-27 Honeywell International, Inc. Method for applying environmental-resistant MCrAlY coatings on gas turbine components
JP2006291307A (ja) * 2005-04-12 2006-10-26 Mitsubishi Heavy Ind Ltd 回転機械の部品及び回転機械
EP1818419A1 (fr) * 2006-01-16 2007-08-15 Siemens Aktiengesellschaft Alliage, couche de protection et composant
GB0807008D0 (en) * 2008-04-17 2008-05-21 Advanced Interactive Materials Helicoidal motors for use in down-hole drilling
US8273148B2 (en) 2009-01-30 2012-09-25 Untied Technologies Corporation Nickel braze alloy composition
EP2374909B1 (fr) * 2010-03-30 2015-09-16 United Technologies Corporation Composition améliorée d'alliage de brasage au nickel
CN107663605A (zh) * 2016-07-29 2018-02-06 泰州市艾瑞克新型材料有限公司 单晶涡轮叶片锯齿冠阻尼面耐磨涂层及其制备工艺
EP3985138A1 (fr) * 2020-10-14 2022-04-20 Siemens Energy Global GmbH & Co. KG Alliage à base de nicocral, poudre, revêtement et composant
US11426822B2 (en) * 2020-12-03 2022-08-30 General Electric Company Braze composition and process of using
CN115747607B (zh) * 2023-01-10 2023-04-14 西安稀有金属材料研究院有限公司 一种用于纤维金属层板的高熵合金薄板及其制备方法

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KR100372482B1 (ko) * 1999-06-30 2003-02-17 스미토모 긴조쿠 고교 가부시키가이샤 니켈 베이스 내열합금
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Also Published As

Publication number Publication date
US20060127660A1 (en) 2006-06-15
US7141128B2 (en) 2006-11-28
AU2003285270A1 (en) 2004-03-03
CN1708598A (zh) 2005-12-14
EP1529123A1 (fr) 2005-05-11
WO2004016819A1 (fr) 2004-02-26
CN100430499C (zh) 2008-11-05

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