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EP1061150A2 - Revêtement comprenant des phases NiAl-beta - Google Patents

Revêtement comprenant des phases NiAl-beta Download PDF

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Publication number
EP1061150A2
EP1061150A2 EP00810410A EP00810410A EP1061150A2 EP 1061150 A2 EP1061150 A2 EP 1061150A2 EP 00810410 A EP00810410 A EP 00810410A EP 00810410 A EP00810410 A EP 00810410A EP 1061150 A2 EP1061150 A2 EP 1061150A2
Authority
EP
European Patent Office
Prior art keywords
weight
coating containing
nial
phase
phase according
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
Application number
EP00810410A
Other languages
German (de)
English (en)
Other versions
EP1061150B1 (fr
EP1061150A3 (fr
Inventor
Dr. Nazmy Mohamed
Hans Joachim Dr. Schmutzler
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.)
GE Vernova GmbH
Original Assignee
ABB Alstom Power Switzerland Ltd
Alstom Schweiz 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 ABB Alstom Power Switzerland Ltd, Alstom Schweiz AG filed Critical ABB Alstom Power Switzerland Ltd
Priority to EP05105696A priority Critical patent/EP1589122B1/fr
Publication of EP1061150A2 publication Critical patent/EP1061150A2/fr
Publication of EP1061150A3 publication Critical patent/EP1061150A3/fr
Application granted granted Critical
Publication of EP1061150B1 publication Critical patent/EP1061150B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process

Definitions

  • the invention relates to the field of materials technology. It affects one Coating which has large volume fractions, preferably in the range of 20 contains up to 90% by volume of NiAl- ⁇ phase in a ⁇ matrix.
  • a large number of alloys are known which are used for coating e.g. B. gas turbine components can be used.
  • the gas turbine components for example turbine blades, are exposed to high temperatures and should be protected against oxidation and corrosion by means of the coatings.
  • the coating material Base material not only protects against oxidation and corrosion, but also that mechanical properties of the base material are not affected.
  • a low ductile-brittle transition temperature ductile brittle Transition Temperature - DBTT
  • a certain ductility at low Temperatures for the coating material can be reached.
  • US Pat. No. 5,943,138 describes a coating which has a typical Ni-based superalloy (single crystal alloy) is with the addition of yttrium and silicon. Although these elements improve the creep resistance and lead also to a low ductile-brittle transition temperature, but the also contain elements W, Mo and the small proportions of Cr and Co cause a harmful effect on the resistance to oxidation.
  • the high-strength NiAl alloys developed in recent years can to some extent compete with the Ni-based superalloys, however, is a Disadvantage compared to the ductile, high-tough Ni-based superalloys low toughness and its high DBT temperature (R. Dariola: NiAl for Turbine Airfoil Application, Structural Intermetallics, The Minerals, Metals & Materials Society, 1993, pp. 495-504), which results in a low ductility of this Alloys reflect at low temperatures.
  • the beta phase of NiAl alloys has an ordered cubic B2 crystal structure (CsCI prototype) and consists of two simple interpenetrating cubic cells, at where the Al atoms are the cube corners of one sublattice and the Ni atoms are the Occupy the cube corners of the other subgrid.
  • the ⁇ phase is rough and therefore brittle
  • the object of the invention is to improve the ductility of NiAl coatings, which have a high proportion of ⁇ phase in a ⁇ matrix.
  • the ⁇ phase can have a different composition, for example NiAl, NiAlCr, NiAlMo, NiAlTi.
  • the phase containing NiAl- ⁇ Coating has the following microalloying elements (data in% by weight) 0.1-8 Fe and / or 0.1-8 Mo and / or 0.1-8 Ga, the total proportion Fe, Mo and Ga is at most 10%.
  • the advantages of the invention are that the ductility of the coating is significantly improved.
  • microalloying with Fe, Ga and Mo achieves that the ⁇ phase is refined and thus the ductility is increased without that the oxidation resistance is reduced.
  • the specified Crossed areas this has an adverse effect on ductility and resistance to oxidation and corrosion.
  • the coating is max. 4% by weight Fe, Ga, Mo contains.
  • B 0.0005-0.9, preferably 0.001-0.5% by weight
  • Zr 0.0005-1.0, preferably 0.001-0.5% by weight
  • C 0.0005-0.8, preferably max. 0.5% by weight
  • the comparative alloys VL 1, VL 2 and VL 3 were microalloyed with Zr, B, and Fe.
  • the following alloys (data in% by weight) were produced, on which the plastic deformation was also determined in a three-point bending test at 200 ° C:
  • Alloys according to the invention modified comparison alloys
  • Table 1 Zr B Fe L 11 VL 1 0.2 0.05 4th L 12 VL 1 0.2 - 3rd L 13 VL 1 0.2 - 4th L 21 VL 2 0.2 - 3rd L 31 VL 3 0.2 - 3rd
  • Fig. 1 shows the force-deflection diagram for the from the prior art Technology known comparison alloy VL 1.
  • the sample showed only a small one plastic deflection and increased with a force of approx. 1 kN Fracture.
  • Fig. 2 shows the force-deflection diagram of the inventive Alloy L 11 (comparative alloy VL1, micro-alloyed with 0.2% by weight Zr, 0.05% % By weight B and 4% by weight Fe).
  • the sample showed one in comparison to VL 1 much greater plastic deflection and only increased at around 1.2 kN Fracture.
  • VL 1 has a ductile-brittle transition temperature of greater than 300 ° C alloy
  • L 11 has a significantly lower ductile-brittle transition temperature (200 ° C).
  • alloy L 12 composition as L 11, but without the addition of boron and with only 3% by weight Fe
  • FIG. 2 shows the force-deflection diagram 3 that compared to Fig. 2, the plastic deflection somewhat was lower, but the force at which the sample broke, at approx. 1.3 kN was slightly higher.
  • microalloying with Fe, Zr and B the ductility of the NiAl- ⁇ phase can be reduced contained coatings can be increased.
  • the microalloying elements refine the rough ⁇ phase.
  • B, Zr and C strengthen the grain boundaries and the ⁇ / ⁇ phase boundaries.
  • the three-point bending test was subjected to a force of about 0.9 kN and a deflection of about 1.65 mm to break.
  • FIGS. 7 and 8 clarifies.
  • the comparative alloy VL 3 went with a force of approx. 2 kN and a deflection of 1.7 mm to break while the Alloy L 31 according to the invention, which differs from VL 3 in that that it is additionally micro-alloyed with 3 wt.% Fe and 0.2 wt.% Zr Fracture had a deflection of approx. 2.2 mm.
  • the plastic deformation and thus the ductility of the coating alloy could be decisive can be increased by adding these additional elements.
  • the Ductilization of the NiAl phase slows crack propagation, i.e. H. the Crack toughness is increased, which has a positive effect on the stress behavior of the Coatings affects.
  • the invention is not limited to that described Embodiments limited. It can be used on all ⁇ -phase NiAls Coatings are applied. Fe, Mo and Ga can each be in the Range of 0.1 to 8, preferably 4 wt .-%, are added. The Elements can be added both individually and in combination, with a Total share of max. 10% by weight should not be exceeded. The mentioned elements refine the ⁇ phase and thus increase ductility, without reducing the resistance to oxidation. Will the specified areas exceeded, this has an unfavorable impact on the ductility and Resistance to oxidation and corrosion.
  • phase boundary hardeners B, C and Zr can be used individually or in combination be added.

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  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
EP00810410A 1999-06-08 2000-05-12 Revêtement comprenant des phases NiAl-beta Expired - Lifetime EP1061150B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05105696A EP1589122B1 (fr) 1999-06-08 2000-05-12 Revêtement comprenant des phases NiAl-beta

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19926669A DE19926669A1 (de) 1999-06-08 1999-06-08 NiAl-beta-Phase enthaltende Beschichtung
DE19926669 1999-06-08

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP05105696A Division EP1589122B1 (fr) 1999-06-08 2000-05-12 Revêtement comprenant des phases NiAl-beta

Publications (3)

Publication Number Publication Date
EP1061150A2 true EP1061150A2 (fr) 2000-12-20
EP1061150A3 EP1061150A3 (fr) 2000-12-27
EP1061150B1 EP1061150B1 (fr) 2005-10-19

Family

ID=7910933

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05105696A Expired - Lifetime EP1589122B1 (fr) 1999-06-08 2000-05-12 Revêtement comprenant des phases NiAl-beta
EP00810410A Expired - Lifetime EP1061150B1 (fr) 1999-06-08 2000-05-12 Revêtement comprenant des phases NiAl-beta

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05105696A Expired - Lifetime EP1589122B1 (fr) 1999-06-08 2000-05-12 Revêtement comprenant des phases NiAl-beta

Country Status (4)

Country Link
US (1) US6471791B1 (fr)
EP (2) EP1589122B1 (fr)
CN (1) CN1250771C (fr)
DE (3) DE19926669A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1260612A1 (fr) * 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd Couche de liason ou revêtement en MCrAlY
EP1790743A1 (fr) * 2005-11-24 2007-05-30 Siemens Aktiengesellschaft Alliage, couche de protection et composant
EP2474414A1 (fr) * 2011-01-06 2012-07-11 Siemens Aktiengesellschaft Alliage, couche de protection et composant
EP2474413A1 (fr) * 2011-01-06 2012-07-11 Siemens Aktiengesellschaft Alliage, couche de protection et composant
WO2012059325A3 (fr) * 2010-11-02 2012-10-11 Siemens Aktiengesellschaft Alliage, couche de protection et élément de construction

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6746783B2 (en) * 2002-06-27 2004-06-08 General Electric Company High-temperature articles and method for making
US7070866B2 (en) * 2004-05-27 2006-07-04 General Electric Company Nickel aluminide coating with improved oxide stability
US7641985B2 (en) * 2004-06-21 2010-01-05 Siemens Energy, Inc. Boron free joint for superalloy component
US7942288B2 (en) * 2004-07-14 2011-05-17 Raymond Qin Cooking utensils with metallic non-stick coating and methods for making the same
KR100911788B1 (ko) * 2007-02-13 2009-08-12 레이몬드 친 금속 비점착 코팅을 갖는 요리 식기 및 이의 제조 방법
US8920937B2 (en) * 2007-08-05 2014-12-30 United Technologies Corporation Zirconium modified protective coating
RU2368682C1 (ru) * 2008-04-08 2009-09-27 Федеральное унитарное государственное предприятие "Центральный научно-исследовательский институт черной металлургии имени И.П. Бардина" (ФГУП "ЦНИИчермет им. И.П. Бардина") ЖАРОПРОЧНЫЙ ПОРОШКОВЫЙ СПЛАВ НА ОСНОВЕ ИНТЕРМЕТАЛЛИДА NiAl И СПОСОБ ЕГО ПОЛУЧЕНИЯ
CN101638376B (zh) * 2008-07-29 2011-04-27 江苏恩华药业股份有限公司 阿戈美拉汀的制备方法及其中间体
RU2371494C1 (ru) * 2008-11-19 2009-10-27 Учреждение Российской академии наук Институт металлургии и материаловедения им. А.А. Байкова РАН (ИМЕТ РАН) ЖАРОПРОЧНЫЙ ПОРОШКОВЫЙ СПЛАВ НА ОСНОВЕ ИНТЕРМЕТАЛЛИДА NiAl И ИЗДЕЛИЕ, ВЫПОЛНЕННОЕ ИЗ НЕГО
CN105624658B (zh) * 2014-10-31 2017-12-15 中国科学院金属研究所 一种活性元素改性铝化物涂层及其制备工艺
KR20220118435A (ko) * 2019-12-27 2022-08-25 구보다코포레이션 Ni기 합금, 내열·내식 부품, 열처리로용 부품

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US2542962A (en) * 1948-07-19 1951-02-20 His Majesty The King In The Ri Nickel aluminum base alloys
JPS5124452B2 (fr) * 1972-12-14 1976-07-24
US4045255A (en) * 1976-06-01 1977-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Directionally solidified eutectic γ+β nickel-base superalloys
US4116723A (en) * 1976-11-17 1978-09-26 United Technologies Corporation Heat treated superalloy single crystal article and process
US4328045A (en) * 1978-12-26 1982-05-04 United Technologies Corporation Heat treated single crystal articles and process
US4451431A (en) * 1982-10-25 1984-05-29 Avco Corporation Molybdenum-containing high temperature coatings for nickel- and cobalt-based superalloys
US4478791A (en) 1982-11-29 1984-10-23 General Electric Company Method for imparting strength and ductility to intermetallic phases
US4612165A (en) 1983-12-21 1986-09-16 The United States Of America As Represented By The United States Department Of Energy Ductile aluminide alloys for high temperature applications
US5043138A (en) 1983-12-27 1991-08-27 General Electric Company Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys
EP0207874B1 (fr) * 1985-05-09 1991-12-27 United Technologies Corporation Revêtements protecteurs pour superalliages, bien adaptés aux substrats
US5116438A (en) * 1991-03-04 1992-05-26 General Electric Company Ductility NiAl intermetallic compounds microalloyed with gallium
US5215831A (en) * 1991-03-04 1993-06-01 General Electric Company Ductility ni-al intermetallic compounds microalloyed with iron
US5116691A (en) * 1991-03-04 1992-05-26 General Electric Company Ductility microalloyed NiAl intermetallic compounds
DE4423118C1 (de) * 1994-07-01 1995-06-01 Max Planck Inst Eisenforschung Nickel-Aluminium-Legierung
US5516380A (en) * 1994-10-14 1996-05-14 General Electric Company NiAl intermetallic alloy and article with improved high temperature strength
IT1294098B1 (it) * 1997-07-10 1999-03-22 Flametal S P A Lega per rivestimenti o riporti resistenti alla corrosione.
US6153313A (en) * 1998-10-06 2000-11-28 General Electric Company Nickel aluminide coating and coating systems formed therewith

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1260612A1 (fr) * 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd Couche de liason ou revêtement en MCrAlY
US6924045B2 (en) 2001-05-25 2005-08-02 Alstom Technology Ltd Bond or overlay MCrAIY-coating
EP1790743A1 (fr) * 2005-11-24 2007-05-30 Siemens Aktiengesellschaft Alliage, couche de protection et composant
WO2012059325A3 (fr) * 2010-11-02 2012-10-11 Siemens Aktiengesellschaft Alliage, couche de protection et élément de construction
CN103189545A (zh) * 2010-11-02 2013-07-03 西门子公司 合金、保护层和构件
EP2474414A1 (fr) * 2011-01-06 2012-07-11 Siemens Aktiengesellschaft Alliage, couche de protection et composant
EP2474413A1 (fr) * 2011-01-06 2012-07-11 Siemens Aktiengesellschaft Alliage, couche de protection et composant
WO2012092997A1 (fr) * 2011-01-06 2012-07-12 Siemens Aktiengesellschaft Alliage, couche protectrice et pièce
WO2012093001A1 (fr) * 2011-01-06 2012-07-12 Siemens Aktiengesellschaft Alliage, couche protectrice et pièce
CN103298607A (zh) * 2011-01-06 2013-09-11 西门子公司 合金、保护层和构件

Also Published As

Publication number Publication date
EP1061150B1 (fr) 2005-10-19
CN1280210A (zh) 2001-01-17
EP1589122A1 (fr) 2005-10-26
EP1061150A3 (fr) 2000-12-27
DE19926669A1 (de) 2000-12-14
DE50015301D1 (de) 2008-09-18
DE50011352D1 (de) 2006-03-02
CN1250771C (zh) 2006-04-12
EP1589122B1 (fr) 2008-08-06
US6471791B1 (en) 2002-10-29

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