EP1407056A2 - Piece moulee realisee en matiere gamma-ti-al intermetallique - Google Patents

Piece moulee realisee en matiere gamma-ti-al intermetallique

Info

Publication number
EP1407056A2
EP1407056A2 EP02759850A EP02759850A EP1407056A2 EP 1407056 A2 EP1407056 A2 EP 1407056A2 EP 02759850 A EP02759850 A EP 02759850A EP 02759850 A EP02759850 A EP 02759850A EP 1407056 A2 EP1407056 A2 EP 1407056A2
Authority
EP
European Patent Office
Prior art keywords
intermetallic
atom
part made
alloy according
molded part
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
EP02759850A
Other languages
German (de)
English (en)
Other versions
EP1407056B1 (fr
Inventor
Andreas Dr. Hoffmann
Heinrich Dr. Kestler
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.)
Plansee SE
Original Assignee
Plansee SE
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 Plansee SE filed Critical Plansee SE
Priority to AT02759850T priority Critical patent/ATE305526T1/de
Publication of EP1407056A2 publication Critical patent/EP1407056A2/fr
Application granted granted Critical
Publication of EP1407056B1 publication Critical patent/EP1407056B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • C22C1/12—Making non-ferrous alloys by processing in a semi-solid state, e.g. holding the alloy in the solid-liquid phase
    • 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
    • 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • Y10T428/12743—Next to refractory [Group IVB, VB, or VIB] metal-base 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12806—Refractory [Group IVB, VB, or VIB] metal-base component

Definitions

  • the invention relates to a molded part made of an intermetallic ⁇ -TiAl
  • ⁇ -TiAl materials are often also referred to as "near- ⁇ -titanium aluminides”.
  • the metal structure of these consists mainly of TiAl phase ( ⁇ phase) with a small proportion of Ti 3 Al ( ⁇ 2 phase).
  • Multi-component alloys can also still have a small proportion of ⁇ -phase, this phase being composed of elements such as chromium, tungsten or
  • Molybdenum is stabilized.
  • intermetallic ⁇ -TiAI materials are of interest for a large number of applications. These include, for example, turbine components as well as engine or transmission components of automobiles. The prerequisite for large-scale application of ⁇ -TiAl is
  • US Pat. No. 5,429,796 describes a cast molded part made of a titanium aluminide material, consisting of 44-52 atom% of aluminum, 0.05-8 atom% of one or more elements from the group consisting of chromium, carbon, gallium, molybdenum, manganese and niobium , Nickel, silicon, tantalum, vanadium and tungsten and at least 0.5% by volume of a boride phase which has a yield strength of 55 ksi and an elongation at break of at least 0.5%.
  • cast pores / blowholes also adversely affect the mechanical properties of ⁇ -TiAl manufactured using casting technology, so that post-compression processes such as e.g. hot isostatic pressing or forming processes must be used.
  • ⁇ -TiAl alloys are therefore usually made from VAR (Vacuum Arc Remeiting) raw material, which is converted into a fine-grained state by means of forming and annealing, the actual shaping following the hot working using complex mechanical, predominantly Machining is carried out.
  • VAR Vauum Arc Remeiting
  • a molded part made of an intermetallic ⁇ -TiAl alloy with 41-49 atom% AI, which has a grain size d ⁇ 5 ⁇ 300 ⁇ m and a pore volume ⁇ 0.2 vol.%
  • Process steps include: - Manufacture of a semi-finished product including a forming process, the degree of deformation being> 65%, - Forming of the semi-finished product in the solidus-liquidus phase state
  • Processing an alloy in the solidus-liquidus phase state is a semi-solid process.
  • Partially liquid masses are usually processed in a thixotropic state in a semi-solid process.
  • Thixotropy is the property of a material to behave highly viscous in the absence of external forces, but to assume a viscosity that is several orders of magnitude lower under the action of shear forces.
  • Thixotropic behavior is limited to certain alloy compositions and those temperature ranges in which both solid and liquid phase components are present in the alloy.
  • the aim is to achieve a semi-solid phase in which there are regular, i.e. globular grains in the solid phase that are evenly surrounded by the melt.
  • the shaping of an alloy using the semi-solid process is known as such.
  • molten alloys are usually slowly cooled to a temperature in the solidus-liquidus two-phase range using one of the known stirring techniques, such as MHD (Magneto-Hydrodynamic-Stirring) or mechanical stirring. Stirring dendrites are destroyed by stirring. The material is given thixotropic properties and the formation of globular primary crystals in the solid phase is promoted.
  • MHD Magnetic-Hydrodynamic-Stirring
  • the achievable grain size was> 50 ⁇ m.
  • ⁇ -TiAl alloys formed into semifinished products in a first hot-forming process section after heating to a temperature in the solidus-liquidus phase region, exhibit thixotropic behavior for the further shaping processing.
  • a degree of deformation of> 65% is a prerequisite, this value being defined as follows:
  • Degree of deformation ⁇ (cross-sectional area before forming - cross-sectional area in the deformed state) / cross-sectional area before forming ⁇ x 100 [%].
  • the thixotropic behavior is unsatisfactory at lower degrees of deformation.
  • ⁇ -TiAl primary material produced by means of VAR Vacuum Are Remelting
  • VAR Vauum Are Remelting
  • the semi-finished product was inductively heated to a temperature between solidus and liquidus in the form of a roughly shaped bolt.
  • the semifinished product had a sufficiently high "handling" strength to be shaped by thixo casting. For this purpose, it was placed in the filling chamber of a die casting machine and pressed into the adjacent mold with the casting piston.
  • the resulting shear stress formed the alloy as a flowable suspension that could be used to form complex components to be free of flow turbulence in the material so that the material spreads free of pores and voids in the mold.
  • This shaping process made it possible to dispense with mechanical machining, or to greatly reduce it, so that, in addition to excellent structural and mechanical properties, the molded parts according to the invention were also highly economical to manufacture. Compared to molded parts cast directly from the melt into a final shape, the advantage according to the invention lies in the much more fine-grained structure and the high degree of pore freedom.
  • the Grain size distribution determined using the line cutting method and the dgs value This means that 95% of the grains evaluated have a diameter that is smaller than the specified value. It should be noted that the dg grain size results in a significantly higher numerical value than is the case in the form of the average grain size. However, the dg 5 value is the more meaningful value, especially for structures with a large grain size range. Depending on the composition of the ⁇ -TiAl material and the applied semi-solid process, the achievable dg 5 grain sizes are between ⁇ 100 ⁇ m and ⁇ 300 ⁇ m. Such molded parts produced for comparison purposes by means of investment casting and not further processed by hot forming have a structure which is at least 5 times coarser than the molded parts produced according to the invention.
  • the grain size difference is particularly pronounced if, according to a preferred embodiment of the invention, alloys with a niobium content of between 1.5 and 12 atom% are used. These alloys show a micro-fine structure by a factor of 7 up to a factor of 16 compared to conventional investment casting.
  • Thixo forging and thixo cross extrusion each a technique that is already known and tried and tested, have proven to be useful alternative forming or shaping processes for the ⁇ -TiAl alloys according to the invention in the solidus-liquidus phase state.
  • thixo forging the partially liquid bolt is inserted into an open tool or die tool.
  • the shaping is carried out by a subsequent tool movement, for example in a forging press.
  • Thixo cross extrusion is a modification of thixo casting. The bolt pushed by a punch is deflected by an angle of 90 ° on its way from the casting chamber to the mold or to the forming tool.
  • the primary casting of an alloy with the composition titanium - 46.5 atom% Al - 2 atom% Cr - 1, 5 atom% Nb - 0.5 atom% Ta - 0.1 atom% boron was carried out using vacuum arc melting (VAR) , The casting block was remelted twice in order to achieve satisfactory homogeneity.
  • the ingot diameter was 210 mm, the ingot length 420 mm.
  • the ingot was extruded in the known state according to previously known process conditions, the degree of deformation being 83%.
  • a bolt section with a length of 110 mm was then heated to a temperature in the solidus-liquidus phase range of the alloy from 1460 to 1470 ° C. and in this state was pressed in a servo-hydraulic press into a closed die-casting tool made of a molybdenum alloy.
  • the molded part produced in this way, a cylindrical component with an average diameter of 40 mm, a length of 100 mm, a flange on the side and a recess of 35 mm x 35 mm x 35 mm in the cylindrical part was examined metallographically.
  • the grain size ds was 120 ⁇ m.
  • the relative density was determined using the buoyancy method and was 99.98%.
  • the grain size dg 5 of the remelted investment casting was 1400 ⁇ m.
  • an ingot of the alloy composition titanium - 45 atom% Al - 5 atom% Nb - 0.2 atom% C - 0.2 atom% boron was produced by vacuum arc melting (VAR) and remelted twice.
  • the ingot diameter was 210 mm, the ingot length 420 mm.
  • the ingot was extruded in the known state by conventional methods, the degree of deformation being 83%.
  • a bolt section with a length of 110 mm was heated to a temperature of 1460 - 1480 ° C, the alloy was brought into the solidus-liquidus phase area and in this state pressed into a closed die-casting tool made of a molybdenum alloy in a servo-hydraulic press.
  • the molded part produced in this way, a cylindrical component with an average diameter of 40 mm, a length of 100 mm, a flange on the side and a depression of 35 mm x 35 mm x 35 mm in the cylindrical part was examined metallographically.
  • the grain size dgs was 75 ⁇ m.
  • the relative density was 99.99%.
  • the grain size dg 5 of the investment casting produced at the beginning had been 1200 ⁇ m.
  • a primary casting blank of the alloy titanium - 46.5 atom% Al - 2 atom% Cr - 0.5 atom% Ta - 0.1 atom% boron was produced by vacuum arc melting (VAR) and remelted twice.
  • the ingot diameter was 170 mm, the ingot length 420 mm.
  • the ingot was extruded in the known state, the degree of deformation being 83%.
  • a bolt section with the length of 110 mm was heated to a temperature of 1440-1470 ° C and in a servo-hydraulic Press pressed into a closed die casting tool made of a molybdenum alloy.
  • the molded part produced in this way a cylindrical component with an average diameter of 40 mm, a length of 100 mm, a flange on the side and a depression of 35 mm x 35 mm x 35 mm in the cylindrical part was examined metallographically.
  • the grain size dgs was 220 ⁇ m.
  • the relative density was 99.99%.
  • the grain size dg of the investment casting had been 1500 ⁇ m.
  • Example 4 A primary casting block of the alloy titanium -46.5 atom% Al - 10 atom% Nb was produced in accordance with the process steps of Example 1 using vacuum arc melting (VAR) and remelted twice.
  • the ingot diameter was 170 mm, the ingot length 420 mm.
  • the ingot was extruded in the known state, the degree of deformation being 83%.
  • a bolt section with a length of 110 mm was heated to a temperature of 1440-1470 ° C and pressed in a servo-hydraulic press into a closed die-casting tool made of a molybdenum alloy.
  • the molded part produced in this way a cylindrical component with an average diameter of 40 mm, a length of 100 mm, a flange on the side and a depression of 35 mm x 35 mm x 35 mm in the cylindrical part was examined metallographically.
  • the grain size dgs was 90 ⁇ m.
  • the relative density was 99.98%.
  • the grain size dg 5 of the investment casting had been 1300 ⁇ m.
  • the primary casting block of the alloy titanium - 46.5 atom% Al - 10 atom% Nb was produced in accordance with Example 1 by means of vacuum arc melting (VAR) and remelted twice.
  • the ingot diameter was 170 mm, the ingot length 420 mm.
  • the ingot was extruded in the known state, the degree of deformation being 72%.
  • a bolt section with the length of 110 mm was heated to a temperature of 1440-1470 ° C and in a servo-hydraulic Press pressed into a closed die casting tool made of a molybdenum alloy.
  • the molded part produced in this way a cylindrical component with an average diameter of 40 mm, a length of 100 mm, a flange on the side and a depression of 35 mm x 35 mm x 35 mm in the cylindrical part was examined metallographically.
  • the grain size d g5 was 170 ⁇ m.
  • the relative density was 99.98%.
  • the grain size dg 5 of the investment casting had been 1300 ⁇ m.
  • Automotive industry e.g. Transmission and engine parts, but also parts for stationary gas turbines and for aerospace, e.g. Turbine components.

Landscapes

  • 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)
  • Extrusion Of Metal (AREA)

Abstract

L'invention concerne une pièce moulée réalisée dans une sélection d'alliages η-Ti-Al aux propriétés mécaniques exceptionnelles. Cette pièce moulée est produite de manière particulièrement économique selon une série d'opérations conformément à l'invention.
EP02759850A 2001-07-19 2002-07-12 Procede de production d'une piece moulee realisee en matiere gamma-ti-al intermetallique Expired - Lifetime EP1407056B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT02759850T ATE305526T1 (de) 2001-07-19 2002-07-12 Verahren zur herstellung eines formteiles aus einem intermetallischen gamma-ti-al-werkstoff

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
AT5732001 2001-07-19
AT0057301U AT5199U1 (de) 2001-07-19 2001-07-19 Formteil aus einem intermetallischen gamma-ti-al-werkstoff
PCT/AT2002/000205 WO2003008655A2 (fr) 2001-07-19 2002-07-12 Piece moulee realisee en matiere gamma-ti-al intermetallique

Publications (2)

Publication Number Publication Date
EP1407056A2 true EP1407056A2 (fr) 2004-04-14
EP1407056B1 EP1407056B1 (fr) 2005-09-28

Family

ID=3494171

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02759850A Expired - Lifetime EP1407056B1 (fr) 2001-07-19 2002-07-12 Procede de production d'une piece moulee realisee en matiere gamma-ti-al intermetallique

Country Status (5)

Country Link
US (1) US6805759B2 (fr)
EP (1) EP1407056B1 (fr)
AT (1) AT5199U1 (fr)
DE (1) DE50204409D1 (fr)
WO (1) WO2003008655A2 (fr)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE393699T1 (de) * 2004-02-26 2008-05-15 Geesthacht Gkss Forschung Verfahren zur herstellung von bauteilen oder halbzeugen, die intermetallische titanaluminid- legierungen enthalten, sowie mittels des verfahrens herstellbare bauteile
DE102004056582B4 (de) * 2004-11-23 2008-06-26 Gkss-Forschungszentrum Geesthacht Gmbh Legierung auf der Basis von Titanaluminiden
DE102005022506B4 (de) * 2005-05-11 2007-04-12 Universität Stuttgart Verfahren zum Schmieden eines Bauteils aus einer Titanlegierung
FR2913898B1 (fr) * 2007-03-23 2009-05-08 Alcan Rhenalu Sa Element structural en alliage d'aluminium incluant un capteur optique.
TW200900541A (en) * 2007-06-29 2009-01-01 Jun-Yen Uan Method for making lithium-aluminum compound with high lithium content
AT509768B1 (de) * 2010-05-12 2012-04-15 Boehler Schmiedetechnik Gmbh & Co Kg Verfahren zur herstellung eines bauteiles und bauteile aus einer titan-aluminium-basislegierung
US9061351B2 (en) * 2011-11-10 2015-06-23 GM Global Technology Operations LLC Multicomponent titanium aluminide article and method of making
US9992917B2 (en) 2014-03-10 2018-06-05 Vulcan GMS 3-D printing method for producing tungsten-based shielding parts
FR3019561B1 (fr) * 2014-04-08 2017-12-08 Snecma Traitement thermique d'un alliage a base d'aluminure de titane
CN108034857A (zh) * 2017-11-23 2018-05-15 中国航发北京航空材料研究院 一种防钛火阻燃涂层及其制备方法
CN108559872B (zh) * 2018-06-05 2020-06-30 中国航发北京航空材料研究院 一种TiAl合金及其制备方法
JP7233659B2 (ja) * 2019-03-18 2023-03-07 株式会社Ihi 熱間鍛造用のチタンアルミナイド合金材及びチタンアルミナイド合金材の鍛造方法並びに鍛造体
CN110643877A (zh) * 2019-09-09 2020-01-03 中国航发北京航空材料研究院 一种含W、Mn、Si、B、C及稀土元素的TiAl金属间化合物
CN116607048B (zh) * 2022-02-09 2024-11-22 中国科学院金属研究所 一种用于精密铸造的γ-TiAl合金及其制备方法

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5015534A (en) * 1984-10-19 1991-05-14 Martin Marietta Corporation Rapidly solidified intermetallic-second phase composites
US4917858A (en) * 1989-08-01 1990-04-17 The United States Of America As Represented By The Secretary Of The Air Force Method for producing titanium aluminide foil
US5284620A (en) * 1990-12-11 1994-02-08 Howmet Corporation Investment casting a titanium aluminide article having net or near-net shape
US5204058A (en) * 1990-12-21 1993-04-20 General Electric Company Thermomechanically processed structural elements of titanium aluminides containing chromium, niobium, and boron
US5131959A (en) 1990-12-21 1992-07-21 General Electric Company Titanium aluminide containing chromium, tantalum, and boron
US5226985A (en) * 1992-01-22 1993-07-13 The United States Of America As Represented By The Secretary Of The Air Force Method to produce gamma titanium aluminide articles having improved properties
JP3839493B2 (ja) * 1992-11-09 2006-11-01 日本発条株式会社 Ｔｉ−Ａｌ系金属間化合物からなる部材の製造方法
US5768679A (en) * 1992-11-09 1998-06-16 Nhk Spring R & D Center Inc. Article made of a Ti-Al intermetallic compound
US5358687A (en) * 1993-06-21 1994-10-25 Agency Of Industrial Science And Technology Processes for manufacturing intermetallic compounds, intermetallic alloys and intermetallic matrix composite materials made thereof
JP3626507B2 (ja) 1993-07-14 2005-03-09 本田技研工業株式会社 高強度高延性ＴｉＡｌ系金属間化合物
US5424027A (en) * 1993-12-06 1995-06-13 The United States Of America As Represented By The Secretary Of The Air Force Method to produce hot-worked gamma titanium aluminide articles
US6231699B1 (en) * 1994-06-20 2001-05-15 General Electric Company Heat treatment of gamma titanium aluminide alloys
US5634992A (en) * 1994-06-20 1997-06-03 General Electric Company Method for heat treating gamma titanium aluminide alloys
US5609698A (en) * 1995-01-23 1997-03-11 General Electric Company Processing of gamma titanium-aluminide alloy using a heat treatment prior to deformation processing
US5653828A (en) * 1995-10-26 1997-08-05 National Research Council Of Canada Method to procuce fine-grained lamellar microstructures in gamma titanium aluminides
US5823243A (en) * 1996-12-31 1998-10-20 General Electric Company Low-porosity gamma titanium aluminide cast articles and their preparation
GB9714391D0 (en) * 1997-07-05 1997-09-10 Univ Birmingham Titanium aluminide alloys
AT2881U1 (de) * 1998-06-08 1999-06-25 Plansee Ag Verfahren zur herstellung eines tellerventiles aus gamma-tial-basislegierungen

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO03008655A2 *

Also Published As

Publication number Publication date
WO2003008655A3 (fr) 2003-10-30
DE50204409D1 (de) 2006-02-09
US6805759B2 (en) 2004-10-19
EP1407056B1 (fr) 2005-09-28
WO2003008655A2 (fr) 2003-01-30
US20040094242A1 (en) 2004-05-20
AT5199U1 (de) 2002-04-25

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