DE20219769U1 - Method for producing titanium alloy components by forging above the beta transition temperature - Google Patents

Method for producing titanium alloy components by forging above the beta transition temperature

Info

Publication number
DE20219769U1
DE20219769U1 DE20219769U DE20219769U DE20219769U1 DE 20219769 U1 DE20219769 U1 DE 20219769U1 DE 20219769 U DE20219769 U DE 20219769U DE 20219769 U DE20219769 U DE 20219769U DE 20219769 U1 DE20219769 U1 DE 20219769U1
Authority
DE
Germany
Prior art keywords
structural
transition temperature
forging
titanium alloy
forged
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
DE20219769U
Other languages
German (de)
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.)
FUCHS FA OTTO
Original Assignee
FUCHS FA OTTO
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 FUCHS FA OTTO filed Critical FUCHS FA OTTO
Priority to DE20219769U priority Critical patent/DE20219769U1/en
Publication of DE20219769U1 publication Critical patent/DE20219769U1/en
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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Thermal Sciences (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Forging (AREA)

Abstract

A method for producing titanium alloy components with reduced material wastage through milling has the preform produced at a temperature above the beta transition temperature followed by forging at above the beta transition temperature. This enables the component to be produced with a minimum of material loss and with a minimum of processing for components with thin wall thickness and with tight curvatures. A typical component has a flat base with support ribs.

Description

Der Beschreibungstext wurde nicht elektronisch erfaßt The description text was not recorded electronically  

Der Beschreibungstext wurde nicht elektronisch erfaßt The description text was not recorded electronically  

Der Beschreibungstext wurde nicht elektronisch erfaßt The description text was not recorded electronically  

Der Beschreibungstext wurde nicht elektronisch erfaßtThe description text was not recorded electronically

Claims (6)

1. Strukturteil aus einer Titanlegierung mit einer oder mehreren, der Längserstreckung des Strukturteils folgenden rippenartigen Struktu­ ren, dadurch gekennzeichnet, dass das Strukturteil ein oberhalb der β-Transus-Temperatur geschmiedetes Strukturschmiedeteil (1) ist.1. Structural part made of a titanium alloy with one or more rib-like structures following the longitudinal extent of the structural part, characterized in that the structural part is a structural forged part ( 1 ) forged above the β-transus temperature. 2. Strukturteil nach Anspruch 1, dadurch gekennzeichnet, dass das Strukturschmiedeteil (1) durch das Schmieden endkonturnah oder endkonturgenau hergestellt ist.2. Structural part according to claim 1, characterized in that the structural forged part ( 1 ) is produced by the forging close to or close to the final contour. 3. Strukturschmiedeteil nach Anspruch 1 oder 2, dadurch gekenn­ zeichnet, dass das Strukturschmiedeteil (1) eine Längserstreckung aufweist, die einem Vielfachen seiner Breite entspricht.3. Structural forging according to claim 1 or 2, characterized in that the structural forging ( 1 ) has a longitudinal extent which corresponds to a multiple of its width. 4. Strukturteil nach einem der Ansprüche 1 bis 3, dadurch gekenn­ zeichnet, dass das Strukturschmiedeteil aus einer Ti6Al4V- Legierung besteht.4. Structural part according to one of claims 1 to 3, characterized indicates that the structural forged part is made of a Ti6Al4V Alloy. 5. Strukturteil nach einem der Ansprüche 1 bis 3, dadurch gekenn­ zeichnet, dass das Strukturschmiedeteil aus einer Ti10V2Fe3Al- Legierung besteht.5. Structural part according to one of claims 1 to 3, characterized indicates that the structural forged part is made of a Ti10V2Fe3Al Alloy. 6. Strukturschmiedeteil nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das Strukturschmiedeteil eine Landeklap­ penführungsschiene ist.6. Structured forged part according to one of claims 1 to 5, characterized characterized that the structural forged part a landing flap pen guide rail is.
DE20219769U 2002-12-20 2002-12-20 Method for producing titanium alloy components by forging above the beta transition temperature Expired - Lifetime DE20219769U1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE20219769U DE20219769U1 (en) 2002-12-20 2002-12-20 Method for producing titanium alloy components by forging above the beta transition temperature

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE20219769U DE20219769U1 (en) 2002-12-20 2002-12-20 Method for producing titanium alloy components by forging above the beta transition temperature

Publications (1)

Publication Number Publication Date
DE20219769U1 true DE20219769U1 (en) 2003-04-17

Family

ID=7978184

Family Applications (1)

Application Number Title Priority Date Filing Date
DE20219769U Expired - Lifetime DE20219769U1 (en) 2002-12-20 2002-12-20 Method for producing titanium alloy components by forging above the beta transition temperature

Country Status (1)

Country Link
DE (1) DE20219769U1 (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2154488A3 (en) * 2008-08-13 2013-10-30 Diehl Aerospace GmbH Flap sensor unit
CN103522007A (en) * 2013-09-26 2014-01-22 贵州航宇科技发展股份有限公司 Method for manufacturing TC25 titanium alloy ring piece
CN104191168A (en) * 2014-08-04 2014-12-10 贵州航宇科技发展股份有限公司 Large specially-shaped titanium alloy forging forming method
CN104191165A (en) * 2014-08-04 2014-12-10 贵州航宇科技发展股份有限公司 Method for forging and forming high temperature alloy large special-shaped ring
DE102017101570A1 (en) 2017-01-26 2018-07-26 Hirschvogel Umformtechnik Gmbh Forged flat product
CN110131563A (en) * 2018-02-08 2019-08-16 中国科学院金属研究所 One kind being suitable for the soft core forging of superhigh temperature and makes with Ingot Type design method

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2154488A3 (en) * 2008-08-13 2013-10-30 Diehl Aerospace GmbH Flap sensor unit
CN103522007A (en) * 2013-09-26 2014-01-22 贵州航宇科技发展股份有限公司 Method for manufacturing TC25 titanium alloy ring piece
CN104191168A (en) * 2014-08-04 2014-12-10 贵州航宇科技发展股份有限公司 Large specially-shaped titanium alloy forging forming method
CN104191165A (en) * 2014-08-04 2014-12-10 贵州航宇科技发展股份有限公司 Method for forging and forming high temperature alloy large special-shaped ring
DE102017101570A1 (en) 2017-01-26 2018-07-26 Hirschvogel Umformtechnik Gmbh Forged flat product
CN110131563A (en) * 2018-02-08 2019-08-16 中国科学院金属研究所 One kind being suitable for the soft core forging of superhigh temperature and makes with Ingot Type design method

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Legal Events

Date Code Title Description
R207 Utility model specification

Effective date: 20030522

R150 Utility model maintained after payment of first maintenance fee after three years

Effective date: 20051027

R151 Utility model maintained after payment of second maintenance fee after six years

Effective date: 20081202

R152 Utility model maintained after payment of third maintenance fee after eight years

Effective date: 20101209

R071 Expiry of right
R071 Expiry of right
R082 Change of representative

Representative=s name: HAVERKAMP PATENTANWAELTE PARTG MBB, DE