EP1214995B1 - Verfahren zur Behandlung metallischer Werkstoffe - Google Patents

Verfahren zur Behandlung metallischer Werkstoffe Download PDF

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Publication number
EP1214995B1
EP1214995B1 EP01127929A EP01127929A EP1214995B1 EP 1214995 B1 EP1214995 B1 EP 1214995B1 EP 01127929 A EP01127929 A EP 01127929A EP 01127929 A EP01127929 A EP 01127929A EP 1214995 B1 EP1214995 B1 EP 1214995B1
Authority
EP
European Patent Office
Prior art keywords
blank
deformation
compression
heating
sample
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
EP01127929A
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German (de)
English (en)
French (fr)
Other versions
EP1214995A3 (de
EP1214995A2 (de
Inventor
Fritz Dr. Appel
Stephan Eggert
Uwe Lorenz
Michael Dr. Oehring
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.)
GKSS Forshungszentrum Geesthacht GmbH
Original Assignee
GKSS Forshungszentrum Geesthacht GmbH
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Publication date
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Publication of EP1214995A2 publication Critical patent/EP1214995A2/de
Publication of EP1214995A3 publication Critical patent/EP1214995A3/de
Application granted granted Critical
Publication of EP1214995B1 publication Critical patent/EP1214995B1/de
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
    • B21J1/02—Preliminary treatment of metal stock without particular shaping, e.g. salvaging segregated zones, forging or pressing in the rough
    • B21J1/025—Preliminary treatment of metal stock without particular shaping, e.g. salvaging segregated zones, forging or pressing in the rough affecting grain orientation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J9/00—Forging presses
    • B21J9/02—Special design or construction
    • B21J9/06—Swaging presses; Upsetting presses
    • B21J9/08—Swaging presses; Upsetting presses equipped with devices for heating the work-piece
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D7/00—Modifying the physical properties of iron or steel by deformation
    • C21D7/13—Modifying the physical properties of iron or steel by deformation by hot working
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • 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 invention relates to a method for the treatment of difficult-to-form metallic materials for the consolidation of the structure of the metallic materials. Such a method is e.g. in US-A-5 039 356.
  • Previously used conventional treatment or forming techniques for metallic materials show consolidation results that do not meet the desired results regularly.
  • Special metallic materials for example the group of titanium aluminides or magnesium materials, according to the previously used conventional treatment or forming techniques, for example by forging or extrusion, still considerable chemical and structural inhomogeneity of their structure, which does not tolerate certain technical applications can be.
  • the known treatment or forming techniques lack, first of all, that with these only relatively low degrees of deformation can be achieved. This is, for example, if the metallic materials are to be used in thermally and mechanically highly stressed areas, such as turbine blades of jet engines for aircraft or connecting rods for drive assemblies of automobiles unacceptable.
  • Metallic materials such as intermetallic titanium aluminides are very brittle and thus difficult to form materials.
  • such metallic materials have been produced exclusively by melt-metallographic processes, predominantly employing vacuum arc melting, plasma melting and induction melting.
  • the melt is usually melted two to three times, occur in the castings considerable quality deficiencies, which are mainly by a coarse-grained texture with a pronounced preference of the crystals, strong increases (local variations in the composition) and the appearance of pores.
  • Such deficiencies occur not only in the primary casting, for example, of titanium aluminides, but also in many other metallic materials, so that they, as mentioned, are not suitable for direct component production from the casting material.
  • the primary casting material must therefore be structurally and chemically consolidated.
  • the high-temperature forming by forging or extrusion is used regularly, in particular, a significant refinement of the structure and a balance of local variations in the composition of the material is sought, for example, it is metallic alloys.
  • the fineness and homogeneity of the structure present after the forming process therefore depends, in addition to the forming temperature and the forming speed, above all, on the degree of deformation, ie. the extent of the plastic deformation achieved during the deformation of the material.
  • This degree of deformation is usually limited to a height reduction of 90 to 95% in conventional single-stage forging by compression. At such degrees of deformation arise at the periphery of the forging high secondary tensile stresses, which often lead to cracking. This is particularly problematic for brittle materials, such as titanium aluminides, which therefore usually can only be converted much less.
  • Higher degrees of deformation require multi-stage forging, which is very expensive and is also not applicable to all desired component shapes.
  • Blank in the above sense means an element of metallic material of the type described above, which has been treated so far, possibly by multiple melting, as it has been previously pretreated for extrusion or forging.
  • the metallic element in this sense may be a suitable sample for scientific purposes, but it may also be a semi-finished product intended for the production of end products, for example turbine blades for jet engines or connecting rods for drive units of motor vehicles.
  • blanks of metallic materials can be produced with which, as desired, a significantly improved microstructural consolidation of the metallic material can be achieved, wherein the application of the method to brittle and thus difficult to deform metallic materials results with respect to the procedurally achievable structure shown have even exceeded the expectations placed in the process considerably, ie the structural and chemical consolidation of the structure has significantly improved over the achievable microstructures by known forging and extrusion processes.
  • Another significant advantage of the method according to the invention is that the forming temperature to which the blank is heated, can be significantly lower than the temperatures that had to be achieved for the previous known forging and extrusion process.
  • the deformation is applied in the form of a twist as well as a simultaneous compression, i. a superimposition of both types of deformation takes place, wherein the shearing cracks which possibly occur during the deformation of the metallic material due to the twisting are closed again at a very early stage, so that they can not grow into macro-cracks. Due to the superimposition of twisting and compression, moreover, a more homogeneous deformation of the material is achieved, since the shearing operations associated with the two deformation processes are strongly inclined with respect to each other with a suitable geometric structure of the blank.
  • the compression is carried out by loading the blank with a constant force, but it is also preferably possible to carry out the compression by applying the blank at a constant rate of deformation.
  • the heating of the blank in the process-related treatment can take place in any desired manner, it being advantageous to control the heating of the blank such that the blank as a whole is heated or held at forming temperature when the deformation takes place.
  • the blank is deformed in total, ie twisted and compressed.
  • the heating so as to purposefully heat the selected portion of the blank whose deformation is to be effected, i. in the broadest sense stepwise deformation of the blank depending on the relative to the blank positioned heater or heat.
  • the heating of the blank is preferably carried out by means of an electric coil which is suitably positioned around the blank and optionally displaceable along the blank in order to heat certain selected areas of the blank in the sense of the preceding paragraph.
  • the method described here was carried out on a laboratory scale on a TiAl alloy of the composition (in atomic percent) Ti - 47 Al - 3.7 (Nb, Cr, Mn, Si) - 0.5 B tested.
  • the experiments were carried out in air.
  • threaded head samples were installed in a compression apparatus in which the sample holders could be rotated against each other to rotate the sample (FIG. 1).
  • the samples were heated by an induction coil to different deformation temperatures between 1000 and 1100 ° C.
  • the sample temperature was determined with a thermocouple. Due to the geometric structure of the coil, the hot sample zone was about 6 mm in length, which was considered to be the effective sample length for evaluation.
  • Fig. 2 shows a macro photograph of the reshaped sample. The texture refinement achieved by the forming process is demonstrated on the basis of light micrographs in Fig. 3.
  • Fig. 3a shows the relatively coarse cast structure in the head region of the sample, in which no deformation and thus no dynamic recrystallization has taken place.
  • Fig. 3b shows the central sample area deformed by the compression and twist.
  • d 800 ⁇ m
  • the method described here can be easily extended to technical standards, since the components required for this purpose, such as induction heaters or forming machines, belong to the standard equipment of the metallurgical industry.
  • a particular advantage of the method is that the sample holders need not be heated, so there are no special requirements for the high temperature strength of these materials.
  • the sample to be reshaped can be heated homogeneously over the entire length to the desired deformation temperature.
  • the sample may also be locally heated by induction heating. This latter method has the advantage that locally very high degrees of deformation and forming speeds can be realized under otherwise identical conditions can, which is advantageous in many materials for achieving a homogeneous recrystallization.
  • the induction coil For the total deformation of the sample must, as indicated in Fig. 1, the induction coil to be moved along the sample longitudinal axis.
  • Forming can be done at 1000 ° C at relatively low forming temperatures compared to conventional forging and extrusion processes, which greatly simplifies the transformation of corrosion sensitive materials such as titanium aluminides.
  • a particular advantage of the method is that forming operations at extremely high temperatures under protective gas can be realized in a relatively simple manner.
  • forming temperatures of more than 1350.degree. C. are often necessary, since in this way special lamellar microstructure morphologies can be set.
  • the forming conditions can be adjusted to a high degree to the deformation and recrystallization behavior, so that even relatively brittle materials, such as titanium aluminides, can be well formed.
  • the torques and forces required for the deformation can be initiated in all cases on relatively cold sample holders, so that these versions need not be made of very expensive high-temperature materials.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Forging (AREA)
  • Manufacture And Refinement Of Metals (AREA)
  • Investigating And Analyzing Materials By Characteristic Methods (AREA)
EP01127929A 2000-12-14 2001-11-23 Verfahren zur Behandlung metallischer Werkstoffe Expired - Lifetime EP1214995B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10062310 2000-12-14
DE10062310A DE10062310C2 (de) 2000-12-14 2000-12-14 Verfahren zur Behandlung metallischer Werkstoffe

Publications (3)

Publication Number Publication Date
EP1214995A2 EP1214995A2 (de) 2002-06-19
EP1214995A3 EP1214995A3 (de) 2003-08-06
EP1214995B1 true EP1214995B1 (de) 2006-10-11

Family

ID=7667118

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01127929A Expired - Lifetime EP1214995B1 (de) 2000-12-14 2001-11-23 Verfahren zur Behandlung metallischer Werkstoffe

Country Status (9)

Country Link
US (1) US7115177B2 (ru)
EP (1) EP1214995B1 (ru)
JP (1) JP3859504B2 (ru)
KR (1) KR100505168B1 (ru)
CN (1) CN1237196C (ru)
AT (1) ATE342142T1 (ru)
DE (2) DE10062310C2 (ru)
ES (1) ES2269282T3 (ru)
RU (1) RU2222635C2 (ru)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10062310C2 (de) * 2000-12-14 2002-11-07 Geesthacht Gkss Forschung Verfahren zur Behandlung metallischer Werkstoffe
KR101014639B1 (ko) * 2002-09-30 2011-02-16 유겐가이샤 리나시메타리 금속 가공 방법 및 그 금속 가공 방법을 이용한 금속체와그 금속 가공 방법을 이용한 금속 함유 세라믹체
KR101140918B1 (ko) * 2003-03-10 2012-07-03 유겐가이샤 리나시메타리 금속체의 가공 방법 및 금속체의 가공 장치
US7313691B2 (en) * 2003-11-18 2007-12-25 International Business Machines Corporation Internet site authentication service
TWI457431B (zh) * 2008-01-30 2014-10-21 Chemetall Gmbh 將金屬表面施以一種潤滑劑組成物的方法
SG155788A1 (en) * 2008-03-18 2009-10-29 Turbine Overhaul Services Pte Methods and apparatuses for correcting twist angle in a gas turbine engine blade
RU2471002C1 (ru) * 2011-11-28 2012-12-27 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Способ повышения сопротивления усталости конструкционных металлических материалов
US9527109B2 (en) * 2013-06-05 2016-12-27 General Electric Company Coating process and coated article
CN103480789B (zh) * 2013-10-18 2015-11-18 核工业理化工程研究院 铝合金碟形工件压扭成型方法
FR3036640B1 (fr) * 2015-05-26 2017-05-12 Snecma Procede de fabrication d'une aube de turbomachine en tial
EP3730666B1 (en) 2017-12-19 2023-01-04 Ihi Corporation TiAl ALLOY MEMBER, METHOD OF MANUFACTURING THE SAME, AND METHOD OF FORGING TiAl ALLOY MEMBER
US10907228B2 (en) * 2018-12-20 2021-02-02 The Boeing Company Methods of modifying material properties of workpieces using high-pressure-torsion apparatuses
US10907226B2 (en) * 2018-12-20 2021-02-02 The Boeing Company Methods of modifying material properties of workpieces using high-pressure-torsion apparatuses
US10907227B2 (en) * 2018-12-20 2021-02-02 The Boeing Company Methods of modifying material properties of workpieces using high-pressure-torsion apparatuses
CN109518124B (zh) * 2019-01-09 2021-03-26 西南大学 一种轴承滚动体的表面改性方法
CN110014155B (zh) * 2019-04-10 2021-08-06 厦门理工学院 一种高纯高致密粉末冶金制品的压扭锻成型方法
CN111519147B (zh) * 2020-03-18 2022-03-11 赣州有色冶金研究所有限公司 一种择优取向的钽靶材及其制备方法

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SU1079337A1 (ru) * 1982-07-15 1984-03-15 Курганский машиностроительный институт Способ формировани булатного узора в стальной заготовке
SU1171541A1 (ru) * 1983-04-19 1985-08-07 Луцкий Автомобильный Завод Способ изготовлени торсионных валов
SU1348048A1 (ru) * 1985-11-18 1987-10-30 Московский институт стали и сплавов Способ изготовлени пресс-изделий
JP2586023B2 (ja) * 1987-01-08 1997-02-26 日本鋼管株式会社 ＴｉＡ１基耐熱合金の製造方法
JPH03285757A (ja) * 1990-04-02 1991-12-16 Sumitomo Light Metal Ind Ltd アルミナイド製内燃機関用吸、排気バルブの製造方法
US5262123A (en) * 1990-06-06 1993-11-16 The Welding Institute Forming metallic composite materials by urging base materials together under shear
DE59103639D1 (de) * 1990-07-04 1995-01-12 Asea Brown Boveri Verfahren zur Herstellung eines Werkstücks aus einer dotierstoffhaltigen Legierung auf der Basis Titanaluminid.
US5039356A (en) * 1990-08-24 1991-08-13 The United States Of America As Represented By The Secretary Of The Air Force Method to produce fatigue resistant axisymmetric titanium alloy components
RU2056214C1 (ru) * 1995-01-13 1996-03-20 Открытое акционерное общество "ГАЗ" Способ получения стержней с проушинами на концах
DE10062310C2 (de) * 2000-12-14 2002-11-07 Geesthacht Gkss Forschung Verfahren zur Behandlung metallischer Werkstoffe

Also Published As

Publication number Publication date
JP2002241912A (ja) 2002-08-28
CN1380437A (zh) 2002-11-20
DE10062310A1 (de) 2002-07-18
EP1214995A3 (de) 2003-08-06
JP3859504B2 (ja) 2006-12-20
KR20020047012A (ko) 2002-06-21
US20020157740A1 (en) 2002-10-31
CN1237196C (zh) 2006-01-18
US7115177B2 (en) 2006-10-03
ATE342142T1 (de) 2006-11-15
DE50111187D1 (de) 2006-11-23
RU2222635C2 (ru) 2004-01-27
EP1214995A2 (de) 2002-06-19
ES2269282T3 (es) 2007-04-01
DE10062310C2 (de) 2002-11-07
KR100505168B1 (ko) 2005-08-03

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