EP1214995A2 - Méthode de traitement de matériaux métalliques - Google Patents

Méthode de traitement de matériaux métalliques Download PDF

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Publication number
EP1214995A2
EP1214995A2 EP01127929A EP01127929A EP1214995A2 EP 1214995 A2 EP1214995 A2 EP 1214995A2 EP 01127929 A EP01127929 A EP 01127929A EP 01127929 A EP01127929 A EP 01127929A EP 1214995 A2 EP1214995 A2 EP 1214995A2
Authority
EP
European Patent Office
Prior art keywords
blank
deformation
compression
carried out
heating
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
EP01127929A
Other languages
German (de)
English (en)
Other versions
EP1214995A3 (fr
EP1214995B1 (fr
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
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 GKSS Forshungszentrum Geesthacht GmbH filed Critical GKSS Forshungszentrum Geesthacht GmbH
Publication of EP1214995A2 publication Critical patent/EP1214995A2/fr
Publication of EP1214995A3 publication Critical patent/EP1214995A3/fr
Application granted granted Critical
Publication of EP1214995B1 publication Critical patent/EP1214995B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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 treatment metallic materials, especially for consolidation of the structure of metallic materials, as well as a metallic Blank.
  • Metallic materials such as intermetallic titanium aluminides are very brittle and therefore difficult to form Materials. So far, such metallic materials exclusively via melting metal processes manufactured, predominantly vacuum arc melting, Plasma melting and induction melting applied becomes. Although the melting material is usually two to three times is melted occur significantly in the castings Quality defects, which are mainly due to a coarse-grained Structure with a pronounced preference orientation of the crystals, strong increases (local fluctuations in the composition) and the appearance of Show pores. Such defects do not only occur in the Primary casting, for example of titanium aluminides, but also with many other metallic materials, so that, as mentioned, for a direct Component production from the cast material is not suitable are. The material present as primary casting must therefore be structurally and chemically consolidated. For this, the high temperature forming by forging or extrusion applied regularly, before all a clear refinement of the structure and a Compensate for local fluctuations in composition of the material is sought if it is for example, metallic alloys.
  • the structure of the casting material has been through recrystallization processes and phase transformations that take place during the high temperature forming by the in the material mechanical energy input is initiated, consolidated.
  • the delicacy and homogeneity of the after Forming the existing structure therefore depends on the Forming temperature and speed especially from Degree of deformation, i.e. the extent to which the Plastic deformation reached.
  • Degree of deformation i.e. the extent to which the Plastic deformation reached.
  • the degree of deformation is in conventional single-stage forging through compression mostly to a height reduction of 90 limited to 95%. With such degrees of deformation arise high on the periphery of the forged body secondary tensile stresses that often lead to cracking to lead. This is especially for brittle materials like Titanium aluminides, problematic, which is why mostly only can be formed much weaker.
  • higher Forming degrees require multi-stage forging that very much is complex and also not for everyone Component shapes is applicable.
  • Blank in the sense described above means an element made of metallic material of the type described above, the extent, possibly by multiple melting, has been treated in the same way as for extrusion or forging has been pretreated.
  • the metallic element in this sense can be too scientific
  • it can also be a semi-finished product that is used to produce End products should serve, for example turbine blades for jet engines or connecting rods for drive units of motor vehicles.
  • Blanks are made from the solution according to the invention metallic materials can be produced with which, such as strived for a significantly improved structure consolidation of the metallic material can be reached, whereby also the application of the method to brittle and therefore difficult to form metallic materials results in in relation to the structure achievable according to the method have even the expectations placed in the process have significantly exceeded, i.e. the structural and chemical consolidation of the structure has increased compared to the achievable structural installations by means of known forging and extrusion processes considerably improved.
  • Another significant advantage of the invention Process is that the forming temperature, to which the blank is heated, considerably can be below the temperatures for the previous one known forging and extrusion processes had to be achieved.
  • the deformation is advantageously in the form of a Drilled on the blank. This will make one caused by rotation of the blank plastic deformation generated.
  • the drill angle should there are no geometric restrictions with the result that by twisting the Blank reached very large plastic deformations become. Drilling enables high forming ratios even with small effective lengths of Realize blanks, i.e. very high degrees of deformation of the Achieve material, even when using the Process on materials that are difficult to form. Drilling makes a very large amount more mechanical Energy introduced into the materials through which an even dynamic recrystallization of the Structure of the material is initiated.
  • the compression is advantageously carried out by application of the blank with constant force, but it is it is also preferably possible to apply compression of the blank with a constant rate of deformation to be done.
  • the blank can be heated during the procedural treatment in any way, it is advantageous to heat the blank to control such that the blank as a whole is heated or kept at the forming temperature, when the deformation takes place. In this case the blank is deformed overall, i.e. twisted and / or compressed.
  • the blank is preferably heated by means of an electrical coil that is suitable around the blank is positioned and possibly along the blank is slidable in the sense of the foregoing to heat certain selected areas of the blank.
  • the invention also relates to a blank made of a titanium aluminide treated according to one or more of claims 1 to 11, the titanium aluminide preferably comprising the composition Ti - 47 Al -3.7 (Nb, Cr, Mn, Si) - 0.5 B having.
  • Fig. 2 shows a macro picture of the formed sample.
  • the structural refinement achieved by the forming process is based on light microscopic micrographs in 3 demonstrates.
  • FIG. 3a shows the relatively rough casting structure in the head area the sample in which there is no deformation and therefore no dynamic recrystallization has taken place.
  • Fig. 3b shows the relatively rough casting structure in the head area the sample in which there is no deformation and therefore no dynamic recrystallization has taken place.
  • Fig. 3b shows the relatively rough casting structure in the head area the sample in which there is no deformation and therefore no dynamic recrystallization has taken place.
  • Fig. 3b shows the relatively rough casting structure in the head area the sample in which there is no deformation and therefore no dynamic recrystallization has taken place.
  • Fig. 3b shows the relatively rough casting structure in the head area the sample in which there is no deformation and therefore no dynamic recrystallization has taken place.
  • Fig. 3b shows the relatively rough casting structure in the head area the sample in which there is no deformation and therefore no dynamic recrystallization has taken place.
  • Fig. 3b shows the relatively rough casting structure in the head area the sample in which there is no deformation and therefore no
  • a particular advantage of the method is that the Samples do not need to be heated, therefore there are no special requirements for the High temperature resistance of these materials.
  • the Carrying out the experiment can be the sample to be reshaped homogeneous over the entire length to the desired deformation temperature be heated.
  • the sample is also heated locally by induction heating become.
  • This latter method has the advantage that under otherwise identical conditions, locally very high degrees of deformation and forming speeds can be realized can achieve what with many materials homogeneous recrystallization is advantageous.
  • the induction coil along the longitudinal axis of the sample be moved.
  • the reshaping can like was demonstrated by the available results in Comparison to conventional forging and extrusion processes at relatively low forming temperatures 1000 ° C take place, which is the deformation of corrosion-sensitive Materials, such as titanium aluminides made easier.
  • a particular advantage of the process however, is also that forming operations at extremely high temperatures under protective gas in relative can be easily realized.
  • titanium aluminides are often, for example, forming temperatures above 1350 ° C, as this is special lamellar structural morphologies can be set. Because of this variability in the experimental procedure the forming conditions to a large extent to the deformation and Recrystallization behavior can be set, so that even relatively brittle materials, such as titanium aluminides, can be shaped well.
  • the ones required for deformation Torques and forces can, however, in all Cases initiated via relatively cold samples so that these versions are not made of very expensive ones High temperature materials need to be manufactured.

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  • 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)
  • Investigating And Analyzing Materials By Characteristic Methods (AREA)
  • Manufacture And Refinement Of Metals (AREA)
EP01127929A 2000-12-14 2001-11-23 Méthode de traitement de matériaux métalliques Expired - Lifetime EP1214995B1 (fr)

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 true EP1214995A2 (fr) 2002-06-19
EP1214995A3 EP1214995A3 (fr) 2003-08-06
EP1214995B1 EP1214995B1 (fr) 2006-10-11

Family

ID=7667118

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01127929A Expired - Lifetime EP1214995B1 (fr) 2000-12-14 2001-11-23 Méthode de traitement de matériaux métalliques

Country Status (9)

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

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100505168B1 (ko) * 2000-12-14 2005-08-03 게카에스에스-포르슝스첸트룸 게스트하흐트 게엠베하 금속성 블랭크 및 그 처리방법
CN110014155A (zh) * 2019-04-10 2019-07-16 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
EP3670681A1 (fr) * 2018-12-20 2020-06-24 The Boeing Company Appareils de torsion haute pression et procédés de modification des propriétés de matériaux de pièces utilisant de tels appareils
EP3670679A1 (fr) * 2018-12-20 2020-06-24 The Boeing Company Appareils de torsion haute pression et procédés de modification des propriétés de matériaux de pièces utilisant de tels appareils
EP3670680A1 (fr) * 2018-12-20 2020-06-24 The Boeing Company Appareils de torsion haute pression et procédés de modification des propriétés de matériaux de pièces utilisant de tels appareils

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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 (fr) 2017-12-19 2023-01-04 Ihi Corporation Matériau d'alliage tial, son procédé de production et procédé de forgeage de matériau d'alliage tial
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
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

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US5190603A (en) * 1990-07-04 1993-03-02 Asea Brown Boveri Ltd. Process for producing a workpiece from an alloy containing dopant and based on titanium aluminide
RU2056214C1 (ru) * 1995-01-13 1996-03-20 Открытое акционерное общество "ГАЗ" Способ получения стержней с проушинами на концах

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
DE10062310C2 (de) * 2000-12-14 2002-11-07 Geesthacht Gkss Forschung Verfahren zur Behandlung metallischer Werkstoffe

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5190603A (en) * 1990-07-04 1993-03-02 Asea Brown Boveri Ltd. Process for producing a workpiece from an alloy containing dopant and based on titanium aluminide
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

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
DATABASE WPI Derwent Publications Ltd., London, GB; AN 1985-054318 [09] XP002243457 & SU 1 079 337 A (KURGANSK MASHINO STR), 15. März 1984 (1984-03-15) *
DATABASE WPI Derwent Publications Ltd., London, GB; AN 1986-060428 [09] XP002243458 & SU 1 171 541 A (LUTSKIJ AVTOMOBILNYJ Z), 7. August 1985 (1985-08-07) *
DATABASE WPI Derwent Publications Ltd., London, GB; AN 1988-153312 [25] XP002243459 & SU 1 348 048 A (MO I STALI I SPLAVOV), 30. Oktober 1987 (1987-10-30) *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100505168B1 (ko) * 2000-12-14 2005-08-03 게카에스에스-포르슝스첸트룸 게스트하흐트 게엠베하 금속성 블랭크 및 그 처리방법
EP3670681A1 (fr) * 2018-12-20 2020-06-24 The Boeing Company Appareils de torsion haute pression et procédés de modification des propriétés de matériaux de pièces utilisant de tels appareils
EP3670679A1 (fr) * 2018-12-20 2020-06-24 The Boeing Company Appareils de torsion haute pression et procédés de modification des propriétés de matériaux de pièces utilisant de tels appareils
EP3670680A1 (fr) * 2018-12-20 2020-06-24 The Boeing Company Appareils de torsion haute pression et procédés de modification des propriétés de matériaux de pièces utilisant de tels appareils
US10907228B2 (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
US10907226B2 (en) 2018-12-20 2021-02-02 The Boeing Company Methods of modifying material properties of workpieces using high-pressure-torsion apparatuses
CN110014155A (zh) * 2019-04-10 2019-07-16 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

Also Published As

Publication number Publication date
JP2002241912A (ja) 2002-08-28
CN1380437A (zh) 2002-11-20
DE10062310A1 (de) 2002-07-18
EP1214995A3 (fr) 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
EP1214995B1 (fr) 2006-10-11
DE50111187D1 (de) 2006-11-23
RU2222635C2 (ru) 2004-01-27
ES2269282T3 (es) 2007-04-01
DE10062310C2 (de) 2002-11-07
KR100505168B1 (ko) 2005-08-03

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