EP3266889A1 - Amélioration de la ductilité d'alliages de titane aluminium gamma par réduction de teneurs interstitielles - Google Patents

Amélioration de la ductilité d'alliages de titane aluminium gamma par réduction de teneurs interstitielles Download PDF

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Publication number
EP3266889A1
EP3266889A1 EP17179909.1A EP17179909A EP3266889A1 EP 3266889 A1 EP3266889 A1 EP 3266889A1 EP 17179909 A EP17179909 A EP 17179909A EP 3266889 A1 EP3266889 A1 EP 3266889A1
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EP
European Patent Office
Prior art keywords
alloy
tial
recited
tnm
utilizing
Prior art date
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EP17179909.1A
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German (de)
English (en)
Inventor
Gopal Das
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP3266889A1 publication Critical patent/EP3266889A1/fr
Withdrawn legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon

Definitions

  • the present disclosure relates to Enhance ductility of gamma-TiAl alloys.
  • Two-phase ⁇ -TiAl alloys are attractive for high temperature structural applications due to their low density, good elevated temperature mechanical properties, and oxidation and burn resistance. This class of material has the potential to withstand the demanding conditions to which aircraft engines, space vehicles, and automotive engines are exposed. Two-phase ⁇ -TiAl alloys in transport technologies may also contribute to a marked reduction in fuel consumption and pollution.
  • TNM beta-stabilized ⁇ -TiAl alloy
  • LPT low pressure turbine
  • the TNM alloy has the chemical composition Ti- (42-44) Al-5 (Nb, Mo)-0.1B (all in at%) with oxygen at about 800 wppm and solidifies through the beta solidification path yielding a fine cast microstructure with low segregation and minor texture.
  • Vacuum Arc Melting (VAM) cast microstructure is characterized by predominantly lamellar colonies with small amount of gamma and about 10 volume fraction of b/B2 (co) phase.
  • the strength of as-cast TNM and other conventional cast gamma alloys is too low to fulfill the strength needed for the certain components such as high speed LPT blades.
  • the TNM alloy can meet the strength goal.
  • the cast structure is commonly broken down by extrusion/and isothermal forging or by isothermal forging alone which is followed by heat treatments to produce microstructures ranging from a duplex microstructure consisting of ⁇ phase and lamellar colonies (alpha2 + ⁇ ) to a fully lamellar microstructure with varying amounts of b/B2 (co).
  • the high speed LPT blades require a room temperature ductility of about 1.5 -3% and tensile strength of about 130-140 ksi along with creep resistance at about 1400F.
  • Suitable heat treatment of optimum duplex microstructure can fulfill ductility, strength and creep requirements for the high speed LPT blade application. It has been determined that in the wrought condition the maximum use temperature for TNM alloy is 1400F.
  • a process to increase ductility can include utilizing ⁇ -TiAl alloy (e.g. an alloy or alloy composition as herein described) as a base alloy; and reducing at least one interstitial of the base alloy to create an alloy compositions (e.g. as described herein) with extremely low interstitials (Eli).
  • ⁇ -TiAl alloy e.g. an alloy or alloy composition as herein described
  • Eli extremely low interstitials
  • a further embodiment of the present disclosure may include, reducing the at least one interstitial of the base alloy to less than about 200 wppm.
  • a further embodiment of the present disclosure may include, wherein utilizing ⁇ -TiAl alloy as a base alloy includes utilizing a beta stabilized gamma ⁇ -TiAl alloy
  • a further embodiment of the present disclosure may include, wherein utilizing ⁇ -TiAl alloy as a base alloy includes utilizing TNM.
  • a further embodiment of the present disclosure may include, wherein the TNM has a composition of Ti-43.5Al-4Nb-1Mo-0.2B (all in at %).
  • a further embodiment of the present disclosure may include, wherein utilizing ⁇ -TiAl alloy as a base alloy includes utilizing cast and Hot Isostatic Pressing (HIP'd) TNM ⁇ -TiAl alloys.
  • HIP'd Hot Isostatic Pressing
  • An alloy composition (e.g. produced by the process described herein) according to one disclosed non-limiting embodiment of the present disclosure can include a ⁇ -TiAl alloy with at least one reduced interstitial of the base alloy to create an alloy compositions with extremely low interstitials (Eli).
  • a further embodiment of the present disclosure may include, wherein the at least one reduced interstitial is less than about 200 wppm.
  • a further embodiment of the present disclosure may include, wherein utilizing ⁇ -TiAl alloy as a base alloy includes utilizing a beta stabilized gamma ⁇ -TiAl alloy
  • a further embodiment of the present disclosure may include, wherein the ⁇ -TiAl alloy is TNM.
  • a further embodiment of the present disclosure may include, wherein the TNM has a composition of Ti-43.5Al-4Nb-1Mo-0.2B (all in at %).
  • a further embodiment of the present disclosure may include, wherein the ⁇ -TiAl alloy includes a cast and Hot Isostatic Pressing (HIP'd) TNM ⁇ -TiAl alloy.
  • HIP'd Hot Isostatic Pressing
  • ductility improvement in ⁇ -TiAl alloys may be effectuated by additions of substitutional solute elements such as chromium, manganese, and vanadium, as well as interstitials such as oxygen, nitrogen and carbon.
  • substitutional solute elements such as chromium, manganese, and vanadium
  • interstitials such as oxygen, nitrogen and carbon.
  • ductility in ⁇ -TiAl alloys at room temperature increases with decreasing oxygen content in cast ⁇ -TiAl. For example, a reduction of oxygen from 1500 wppm to 500 wppm leds to a significant improvement in ductility from 0.5% to 1.5% at room temperature.
  • TNM beta stabilized gamma ⁇ -TiAl alloy
  • This alloy has a composition of Ti-43.5Al-4Nb-1Mo-0.2B (all in %).
  • This alloy solidifies through a beta solidification path which leads to moderate to mild chemical and microstructural segregations.
  • the resultant microstructure consists mainly of lamellar colonies ( ⁇ 2/ ⁇ ) with gamma and ⁇ /B2 phases located primarily at the colony boundaries.
  • HIP Cast and Hot Isostatic Pressing
  • a ⁇ -TiAl alloy utilizes an existing, mature, ⁇ -TiAl alloy (step 110) such as TNM, gamma TiAl, Ti-48Al-2Cr-2Nb, 47 XD alloy, alloy 7, etc., as the base alloys.
  • step 110 such as TNM, gamma TiAl, Ti-48Al-2Cr-2Nb, 47 XD alloy, alloy 7, etc.
  • interstitials such as oxygen, nitrogen and carbon are reduced to a low level (step 120).
  • the interstitials are reduced to less than about 200 wppm to create new alloy compositions with extremely low interstitials (Eli).
  • LPT blades are made with gamma TiAl for aircraft engines.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Forging (AREA)
  • Powder Metallurgy (AREA)
EP17179909.1A 2016-07-07 2017-07-06 Amélioration de la ductilité d'alliages de titane aluminium gamma par réduction de teneurs interstitielles Withdrawn EP3266889A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/204,092 US20180010213A1 (en) 2016-07-07 2016-07-07 Enhance ductility of gamma titanium aluminum alloys by reducing interstitial contents

Publications (1)

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EP3266889A1 true EP3266889A1 (fr) 2018-01-10

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EP17179909.1A Withdrawn EP3266889A1 (fr) 2016-07-07 2017-07-06 Amélioration de la ductilité d'alliages de titane aluminium gamma par réduction de teneurs interstitielles

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EP (1) EP3266889A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3326746A1 (fr) * 2016-11-25 2018-05-30 Helmholtz-Zentrum Geesthacht Zentrum für Material- und Küstenforschung GmbH Procédé pour assembler et/ou réparer des substrats d'alliages d'aluminure de titane

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110277891A1 (en) * 2010-05-12 2011-11-17 Boehler Schmiedetechnik Gmbh & Co Kg Method for producing a component and components of a titanium-aluminum base alloy
EP2620517A1 (fr) * 2012-01-25 2013-07-31 MTU Aero Engines GmbH Alliage TiAl thermostable
US20140202601A1 (en) * 2011-08-11 2014-07-24 MTU Aero Engines AG FORGED TiAl COMPONENTS, AND METHOD FOR PRODUCING SAME
EP2851445A1 (fr) * 2013-09-20 2015-03-25 MTU Aero Engines GmbH Alliage TiAl résistant au fluage
EP3109337A1 (fr) * 2015-06-24 2016-12-28 MTU Aero Engines GmbH Procédé et dispositif destinés a la fabrication de composants forgés en tial

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8876992B2 (en) * 2010-08-30 2014-11-04 United Technologies Corporation Process and system for fabricating gamma TiAl turbine engine components

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110277891A1 (en) * 2010-05-12 2011-11-17 Boehler Schmiedetechnik Gmbh & Co Kg Method for producing a component and components of a titanium-aluminum base alloy
US20140202601A1 (en) * 2011-08-11 2014-07-24 MTU Aero Engines AG FORGED TiAl COMPONENTS, AND METHOD FOR PRODUCING SAME
EP2620517A1 (fr) * 2012-01-25 2013-07-31 MTU Aero Engines GmbH Alliage TiAl thermostable
EP2851445A1 (fr) * 2013-09-20 2015-03-25 MTU Aero Engines GmbH Alliage TiAl résistant au fluage
EP3109337A1 (fr) * 2015-06-24 2016-12-28 MTU Aero Engines GmbH Procédé et dispositif destinés a la fabrication de composants forgés en tial

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
B. P. BEWLAY ET AL: "TiAl alloys in commercial aircraft engines", MATERIALS AT HIGH TEMPERATURES., vol. 33, no. 4-5, 28 June 2016 (2016-06-28), GB, pages 549 - 559, XP055425624, ISSN: 0960-3409, DOI: 10.1080/09603409.2016.1183068 *

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