EP2788518B1 - Super-alliage sans ou à faible teneur en rhénium - Google Patents

Super-alliage sans ou à faible teneur en rhénium Download PDF

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Publication number
EP2788518B1
EP2788518B1 EP12787636.5A EP12787636A EP2788518B1 EP 2788518 B1 EP2788518 B1 EP 2788518B1 EP 12787636 A EP12787636 A EP 12787636A EP 2788518 B1 EP2788518 B1 EP 2788518B1
Authority
EP
European Patent Office
Prior art keywords
content
rhenium
weight
nickel
tungsten
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.)
Not-in-force
Application number
EP12787636.5A
Other languages
German (de)
English (en)
Other versions
EP2788518A1 (fr
Inventor
Robert F. Singer
Ernst Affeldt
Michael Weiss
Thomas GÖHLER
Ralf RETTIG
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2788518A1 publication Critical patent/EP2788518A1/fr
Application granted granted Critical
Publication of EP2788518B1 publication Critical patent/EP2788518B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • 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
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/177—Ni - Si alloys

Definitions

  • the present invention relates to a nickel-base superalloy with little or no rhenium content.
  • nickel-based superalloys are used, which can be used as single crystals or as directionally solidified alloys. These alloys have high strength due to their alloying components due to solid solution and / or precipitation or particle hardening.
  • nickel-based superalloys are optimized so that the particle hardening is maintained by the excretion of so-called ⁇ '-phases even at high temperatures and long periods of use.
  • nickel base superalloys such as CMSX-4, PWA-1484 or René N5.
  • Such alloys all contain a rhenium content of more than 3% by weight.
  • a nickel-base superalloy for gas turbine components which, in addition to nickel, contain chromium with a content of 7-9% by weight, titanium with a content of 0.5-1.5% by weight, molybdenum with a content of 5-7% by weight. 7% by weight, tungsten containing 0-1% by weight, tantalum containing 4-5% by weight, aluminum containing 5.5-5.6% by weight, cobalt containing 8-12% by weight, boron containing 0.01-0.02% by weight, zirconium containing 0.02-0.1% by weight, containing carbon from 0.05-0.15% by weight, hafnium at a level of 0-1.5% by weight.
  • nickel-base superalloy for gas turbine components which in addition to nickel molybdenum at a content of 2.0 wt .-%, tungsten with a content of 5.0 wt .-%, tantalum with a content of 6.3 wt .-% , Rhenium at a level of 2.0% by weight, aluminum at a level of 5.5% by weight, titanium at a level of 1.5% by weight, chromium at a level of 5.0% by weight. % and cobalt with a content of 10.0% by weight.
  • a nickel-based superalloy is proposed, the aluminum with a content of 4 to 6 wt .-%, cobalt with a content of 8 to 10 wt .-%, chromium containing 5 to 8 wt % Molybdenum, containing from 2 to 5.5% by weight, tantalum containing from 4 to 6% by weight, rhenium containing from 0 to 1.5% by weight, titanium having a content of Content of 3 to 5.5 wt .-% and tungsten with a content of 3.5 to 6 wt .-% and the balance nickel and unavoidable impurities.
  • the nickel-based superalloy may have an aluminum content of 4.5 to 5.5% by weight, a cobalt content of 8.5 to 9.5% by weight, a chromium content of 6 to 7, 5 wt .-%, a molybdenum content of 2 to 4 wt -%, a tantalum content from 4 to 5.5% by weight, a rhenium content of 0 to 1% by weight, a titanium content of 3.5 to 5.5% by weight and a tungsten content of 4 to 5, 5 wt .-% have.
  • the rest is again formed by nickel and unavoidable impurities.
  • a nickel base superalloy comprising aluminum at a content of 4.5 to 5.5% by weight, cobalt at a content of 8.5 to 9.5% by weight, chromium with a content of 6 to 7.5% by weight, tantalum with a content of 6 to 8% by weight, rhenium with a content of 0 to 2% by weight, titanium with a content of 1.5 to 3 Wt .-% and tungsten with a content of 6 to 8 wt .-% and the remainder comprises nickel and unavoidable impurities.
  • Such alloys can be used in various forms, for example as a directionally solidified alloy or as single crystals for components in gas turbines and in particular aircraft engines.
  • the alloys for turbine blades and in particular blades of low-pressure turbines can be used.
  • the present invention can be realized in particular by alloys having the following compositions: Elemental proportion [wt .-%], balance nickel Short-Bez. al Co Cr Not a word re Ta Ti W Alloy 1 5 9 7 2.5 1 5 4.25 4.5 Alloy 2 5 9 6.5 3.5 1 5 3.75 4.5 Alloy 3 5 9 6.5 3.5 0 4.5 4.5 5 Alloy 4 5 9 6.5 0 2 6 1.5 8th Alloy 5 5 9 6.5 0 1.5 7 2 7 Alloy 6 5 9 6.5 0 1 8th 3 6
  • the alloys 4 to 6 are better castable or heat treatable compared to the alloys 1 to 3.

Landscapes

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

Claims (4)

  1. Superalliage à base de nickel, contenant de l'aluminium avec une teneur de 4 à 6 % en poids, du cobalt avec une teneur de 8 à 10 % en poids, du chrome avec une teneur de 5 à 8 % en poids, du molybdène avec une teneur de 2 à 5,5 % en poids, du tantale avec une teneur de 4 à 6 % en poids, du rhénium avec une teneur de 0 à 1,5 % en poids, du titane avec une teneur de 3 à 5, 5 % en poids et du tungstène avec une teneur de 3,5 à 6 % en poids et le reste contenant du nickel et des impuretés inévitables.
  2. Superalliage à base de nickel selon la revendication 1,
    caractérisé en ce que
    l'alliage contient de l'aluminium avec une teneur de 4,5 à 5,5 % en poids, du cobalt avec une teneur de 8,5 à 9,5 % en poids, du chrome avec une teneur de 6 à 7,5 % en poids, du molybdène avec une teneur de 2 à 4 % en poids, du tantale avec une teneur de 4 à 5,5 % en poids, du rhénium avec une teneur de 0 à 1 % en poids, du titane avec une teneur de 3,5 % à 5 % en poids et du tungstène avec une teneur de 4 à 5,5 % en poids et le reste contenant du nickel et des impuretés inévitables.
  3. Superalliage à base de nickel, contenant de l'aluminium avec une teneur de 4,5 à 5,5 % en poids, du cobalt avec une teneur de 8,5 à 9,5 % en poids, du chrome avec une teneur de 6 à 7,5 % en poids, du tantale avec une teneur de 6 à 8 % en poids, du rhénium avec une teneur de 0 à 2 % en poids, du titane avec une teneur de 1,5 à 3 % en poids et du tungstène avec une teneur de 6 à 8 % en poids et le reste contenant du nickel et des impuretés inévitables.
  4. Composant d'une turbine à gaz, en particulier d'un moteur d'avion, de préférence une aube de turbine pour turbine basse pression, fabriqué avec un alliage selon l'une quelconque des revendications précédentes.
EP12787636.5A 2011-12-07 2012-10-17 Super-alliage sans ou à faible teneur en rhénium Not-in-force EP2788518B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011120388 2011-12-07
PCT/DE2012/001009 WO2013083101A1 (fr) 2011-12-07 2012-10-17 Superalliage à base de nickel exempt de rhénium ou à teneur de rhénium réduite

Publications (2)

Publication Number Publication Date
EP2788518A1 EP2788518A1 (fr) 2014-10-15
EP2788518B1 true EP2788518B1 (fr) 2018-04-25

Family

ID=47191456

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12787636.5A Not-in-force EP2788518B1 (fr) 2011-12-07 2012-10-17 Super-alliage sans ou à faible teneur en rhénium

Country Status (4)

Country Link
US (1) US9850765B2 (fr)
EP (1) EP2788518B1 (fr)
ES (1) ES2670877T3 (fr)
WO (1) WO2013083101A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2927336A1 (fr) 2014-04-04 2015-10-07 MTU Aero Engines GmbH Alliage à base de nickel à propriétés matricielles optimisées
EP3091095B1 (fr) 2015-05-05 2018-07-11 MTU Aero Engines GmbH Superalliage à base de nickel sans rhénium à faible densité
DE102016203724A1 (de) * 2016-03-08 2017-09-14 Siemens Aktiengesellschaft SX-Nickel-Legierung mit verbesserten TMF-Eigenschaften, Rohmaterial und Bauteil

Family Cites Families (13)

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Publication number Priority date Publication date Assignee Title
US6054096A (en) * 1982-12-27 2000-04-25 United Technologies Corporation Stable heat treatable nickel superalloy single crystal articles and compositions
US4765850A (en) 1984-01-10 1988-08-23 Allied-Signal Inc. Single crystal nickel-base super alloy
WO1997038144A1 (fr) * 1996-04-10 1997-10-16 The Penn State Research Foundation Superalliages perfectionnes a resistance a l'oxydation et a soudabilite ameliorees
WO1999031365A1 (fr) * 1997-12-15 1999-06-24 Hitachi, Ltd. Turbine a gaz utilisee pour produire de l'energie et systeme mixte de production d'energie
US20130230405A1 (en) 2007-08-31 2013-09-05 Kevin Swayne O'Hara Nickel base superalloy compositions being substantially free of rhenium and superalloy articles
US8876989B2 (en) 2007-08-31 2014-11-04 General Electric Company Low rhenium nickel base superalloy compositions and superalloy articles
US20090185944A1 (en) * 2008-01-21 2009-07-23 Honeywell International, Inc. Superalloy compositions with improved oxidation performance and gas turbine components made therefrom
US20100135846A1 (en) 2008-12-01 2010-06-03 United Technologies Corporation Lower cost high strength single crystal superalloys with reduced re and ru content
US20100254822A1 (en) * 2009-03-24 2010-10-07 Brian Thomas Hazel Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom
JP5558050B2 (ja) * 2009-08-25 2014-07-23 株式会社日立製作所 強度及び耐酸化特性に優れた一方向凝固用ニッケル基超合金
US20110076180A1 (en) 2009-09-30 2011-03-31 General Electric Company Nickel-Based Superalloys and Articles
US9138963B2 (en) 2009-12-14 2015-09-22 United Technologies Corporation Low sulfur nickel base substrate alloy and overlay coating system
US9108266B2 (en) * 2011-04-19 2015-08-18 General Electric Company Welded component, a welded gas turbine component, and a process of welding a component

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP2788518A1 (fr) 2014-10-15
ES2670877T3 (es) 2018-06-01
US20140356183A1 (en) 2014-12-04
WO2013083101A1 (fr) 2013-06-13
US9850765B2 (en) 2017-12-26

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