EP1061150B1 - Revêtement comprenant des phases NiAl-beta - Google Patents

Revêtement comprenant des phases NiAl-beta Download PDF

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Publication number
EP1061150B1
EP1061150B1 EP00810410A EP00810410A EP1061150B1 EP 1061150 B1 EP1061150 B1 EP 1061150B1 EP 00810410 A EP00810410 A EP 00810410A EP 00810410 A EP00810410 A EP 00810410A EP 1061150 B1 EP1061150 B1 EP 1061150B1
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EP
European Patent Office
Prior art keywords
weight
coating
phase
nial
alloy
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 - Lifetime
Application number
EP00810410A
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German (de)
English (en)
Other versions
EP1061150A3 (fr
EP1061150A2 (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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
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
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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
    • 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 concerns one Coating, which has large volume fractions, in the range of 20 to 90% by volume of NiAl- ⁇ phase in a ⁇ -matrix.
  • gas turbine components are used.
  • the gas turbine components For example, turbine blades are exposed to high temperatures and should be protected by the coatings from oxidation and corrosion.
  • a coating is described, which is a typical Ni-base superalloy (single crystal alloy) is with addition of yttrium and silicon. Although these elements improve creep resistance and lead also at a low ductile-brittle transition temperature, but the also contained elements W, Mo and the low levels of Cr and Co cause a harmful effect on the oxidation resistance.
  • the ⁇ -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 a sublattice and the Ni atoms the Occupy cube corners of the other subgrid.
  • the ⁇ -phase is coarse and therefore brittle.
  • US Pat. No. 5,116,438 discloses .beta.-phase Ni aluminides which are reacted with gallium are microalloyed. These have a significant at about 0.25 atom% Ga Improvement of ductility at room temperature. A higher proportion of Ga acts are negative.
  • US 4 451 431 describes a corrosion resistant and ductile Coating for turbine components made of a superalloy the coating being of a Ni-based alloy consists of e.g. following composition 18% Cr, 12% Co, 12% Al, 0.6% Y, 1.2% Mo or 2.8% Mo, balance nickel.
  • the invention is based on the object, the ductility of NiAl coatings, which have a high proportion of ⁇ -phase in a ⁇ -matrix to improve.
  • the ⁇ -phase can have a different composition, for example, NiAlCr, NiAlMo.
  • this is achieved by containing the NiAl- ⁇ phase Coating with a content of NiAl- ⁇ in the range of 20 to 90 vol.% In a ⁇ -matrix the following chemical composition (in% by weight): 13 Cr, 24 Co, 12 Al, 0.5 Ta, 1.2 Si, 3 Re, 0.3 Y, 0.1-8 Fe, and optionally 0.0005-0.9 B and / or 0.0005-1 Zr, and / or 0.1-8 Mo and / or 0.1-8 Ga, wherein the Total content Fe, Mo and Ga is 10% maximum, balance Ni and unavoidable Impurities.
  • the advantages of the invention are that the ductility of the coating is significantly improved.
  • micro-alloying with Fe, and optionally with Ga and Mo becomes ensures that the ⁇ -phase is refined and thus the ductility is increased without that the oxidation resistance is reduced. Be the specified Areas exceeded, so the unfavorable effect on the ductility and the resistance to oxidation and corrosion.
  • B (0.001-0.5 wt%), Zr (0.001-0.5 wt%) and / or C 0.5 wt .-%) are added.
  • B, Zr and C consolidate the grain boundaries and the ⁇ / ⁇ phase boundaries.
  • the comparative alloy VL 1 was microalloyed with Zr, B, and Fe.
  • the following alloys data in% by weight
  • the following alloys were prepared, at which the plastic deformation was also determined in a three-point bending test at 200 ° C.:
  • Inventive alloys modified comparative alloys According to Table 1 Zr B Fe L 11 VL 1 0.2 00:05 4 L 12 VL 1 0.2 - 3 L 13 VL 1 0.2 - 4
  • Fig. 1 shows the force-deflection diagram for from the prior Technique known comparative alloy VL 1. The sample showed only a small plastic deflection and went at a force of about 1 kN Fracture.
  • Fig. 2 shows the force-deflection diagram of the inventive Alloy L 11 (comparative alloy VL1, microalloyed with 0.2% by weight Zr, 0.05% Wt .-% B and 4 wt .-% Fe). The sample showed one compared to VL 1 significantly greater plastic deflection and did not increase until about 1.2 kN Fracture.
  • VL 1 has a ductile-brittle transition temperature of greater than 300 ° C alloy
  • L11 has a much lower ductile-brittle transition temperature (200 ° C).
  • the force-deflection diagram shows According to Fig. 3, that in comparison to FIG. 2, the plastic deflection something was lower, but the force at which the sample was broken, with about 1.3 kN was slightly higher.
  • the ductility of the NiAl- ⁇ phase can thus be determined coatings are increased.
  • the microalloying elements refine the coarse ⁇ -phase.
  • B, Zr and C consolidate the grain boundaries and the ⁇ / ⁇ phase boundaries.
  • the plastic deformation and thus the ductility of the coating alloy could thus be crucial be increased by the addition of these additional elements.
  • the Ductilization of the NiAl phase slows crack propagation, i. H. the Rupture toughness is increased, which has a positive effect on the stress behavior of the Coatings affects.
  • C can also be alloyed as a ⁇ / ⁇ phase boundary agent. It is the Addition of 0.0005 to 0.9, preferably 0.001 to 0.5 wt .-% B, 0.0005 to 1.0, preferably 0.001 to 0.5 wt .-% Zr and 0.0005 to 0.8 wt .-% C provided.
  • the phase boundary strengtheners B, C and Zr may be used singly or in combination be added.

Landscapes

  • 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)

Claims (10)

  1. Revêtement constitué d'un alliage à base de Ni, avec une teneur en Al, qui contient une phase β de NiAl avec une fraction de phase β de NiAl dans la plage de 20 à 90% en volume dans une matrice γ, caractérisé par la composition chimique suivante (indications en poids) du revêtement : 13% de Cr, 24% de Co, 12% de Al, 0,5% de Ta, 1,2% de Si, 3% de Re, 0,3% de Y, 0,1 à 8% de Fe, ainsi qu'éventuellement 0,0005 à 0,9% de B et/ou 0,0005 à 1% de Zr et/ou 0,1 à 8% de Mo et/ou 0,1 à 8% de Ga, la fraction totale de Fe, Mo et Ga constituant au maximum 10% et le reste étant formé de Ni et des impuretés inévitables.
  2. Revêtement selon la revendication 1, caractérisé par au maximum 4% en poids de Fe et/ou au maximum 4% en poids de Mo et/ou au maximum 4% en poids de Ga.
  3. Revêtement selon la revendication 1, caractérisé par 0,001 à 0,5% en poids de Zr.
  4. Revêtement selon la revendication 3, caractérisé par 0,2% en poids de Zr.
  5. Revêtement selon la revendication 1, caractérisé par 0,001 à 0,5% en poids de B.
  6. Revêtement selon la revendication 5, caractérisé par 0,2% en poids de B.
  7. Revêtement selon la revendication 1, caractérisé par 0,5 % en poids de C.
  8. Revêtement selon la revendication 1, caractérisé par (indications en poids) 13% de Cr, 24% de Co, 12% de Al, 0,3% de Y, 1,2% de Si, 0,5% de Ta, 3% de Re, 0,2% de Zr, 0,05% de B et 4% de Fe, le reste étant du Ni.
  9. Revêtement selon la revendication 1, caractérisé par (indications en poids) 13% de Cr, 24% de Co, 12% de Al, 0,3% de Y, 1,2% de Si, 0,5% de Ta, 3% de Re, 0,2% de Zr, 4% de Fe, le reste étant du Ni.
  10. Revêtement selon la revendication 1, caractérisé par (indications en poids) 13% de Cr, 24% de Co, 12% de Al, 0,3% de Y, 1,2% de Si, 0,5% de Ta, 3% de Re, 0,2% de Zr et 3% de Fe, le reste étant du Ni.
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 EP1061150A2 (fr) 2000-12-20
EP1061150A3 EP1061150A3 (fr) 2000-12-27
EP1061150B1 true EP1061150B1 (fr) 2005-10-19

Family

ID=7910933

Family Applications (2)

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

Family Applications After (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) EP1061150B1 (fr)
CN (1) CN1250771C (fr)
DE (3) DE19926669A1 (fr)

Families Citing this family (14)

* 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
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
EP1774876B1 (fr) * 2004-07-14 2010-07-07 Raymond Chin Recipient de cuisson comprenant un revetement metallique antiadhesif et son procede de preparation
EP1790743A1 (fr) * 2005-11-24 2007-05-30 Siemens Aktiengesellschaft Alliage, couche de protection et composant
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
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
EP2611949B1 (fr) * 2010-11-02 2016-01-06 Siemens Aktiengesellschaft Alliage a base nickel, couche de protection et élément de construction
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
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
US20230011769A1 (en) * 2019-12-27 2023-01-12 Kubota Corporation Ni-BASED ALLOY, HEAT-RESISTANT AND CORROSION-RESISTANT COMPONENT, AND HEAT TREATMENT FURNACE COMPONENT

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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
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
US5116438A (en) * 1991-03-04 1992-05-26 General Electric Company Ductility NiAl intermetallic compounds microalloyed with gallium
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

Also Published As

Publication number Publication date
CN1280210A (zh) 2001-01-17
DE50011352D1 (de) 2006-03-02
EP1589122B1 (fr) 2008-08-06
CN1250771C (zh) 2006-04-12
EP1061150A3 (fr) 2000-12-27
US6471791B1 (en) 2002-10-29
DE19926669A1 (de) 2000-12-14
EP1589122A1 (fr) 2005-10-26
DE50015301D1 (de) 2008-09-18
EP1061150A2 (fr) 2000-12-20

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