US3635068A - Hot forming of titanium and titanium alloys - Google Patents

Hot forming of titanium and titanium alloys Download PDF

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Publication number
US3635068A
US3635068A US822453A US3635068DA US3635068A US 3635068 A US3635068 A US 3635068A US 822453 A US822453 A US 822453A US 3635068D A US3635068D A US 3635068DA US 3635068 A US3635068 A US 3635068A
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forging
die
billet
method defined
titanium
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US822453A
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English (en)
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Thomas Watmough
John A Schey
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IIT Research Institute
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IIT Research Institute
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    • 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
    • B21J5/06—Methods for forging, hammering, or pressing; Special equipment or accessories therefor for performing particular operations
    • B21J5/08—Upsetting
    • 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
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S72/00—Metal deforming
    • Y10S72/70—Deforming specified alloys or uncommon metal or bimetallic work

Definitions

  • the present invention relates to the forming of titanium and titanium alloys. More particularly it relates to an improved method for the bulk plastic deformation of titanium and titanium alloys utilizing elevated deforming temperatures in dies that are heated to or close to the workpiece temperature.
  • Titanium and titanium alloys are becoming popular in the design of structures requiring a high strength-to-weight ratio.
  • titanium alloys are defined to mean the structural alloys of titanium.
  • Typical alloy compositions of this class normally include additions of aluminum and may also contain additions of one or more alloying agents such as tin, zirconium, molybdenum, vanadium, silicon, chromium, manganese and iron.
  • alloying agents such as tin, zirconium, molybdenum, vanadium, silicon, chromium, manganese and iron.
  • titanium alloys is understood to also include industrially pure titanium. Titanium alloys find particular application in the field of aircraft and missile design, though other applications are continually being found where the advantageous properties of titanium alloys are beneficial.
  • the term bulk deformation means the forming of a finished product from an ingot, billet, slug or preform as opposed to bending or drawing sheet material.
  • a commercial forming process for titanium alloys should permit economical forming of the alloy into a desired shape while retaining desirable physical properties. inherently such a process must retain in the alloy the microcrystalline structure necessary for attaining high strength-to-weight ratio.
  • the chief difficulty in the known processes for the bulk deformation of titanium alloys has been in overcoming the very high compressive yield strength of titanium alloys which makes them extremely difficult to form into thin-forged webs and ribs and other configurations requiring extensive flow of material in the die.
  • Die materials for present commercial forming methods are usually selected from the so-called hot-working die steels which possess adequate strength only at temperatures of 1,000 F. or below. For this reason forging proceeds with a substantial temperature gradient between the titanium alloy and the die, and cooling of the workpiece limits the deformation that can be attained in a single operation.
  • lt is a further object of the present invention to provide an improved method of forging titanium and titanium alloys.
  • the present invention relates to a method of forming titanium alloys at elevated temperatures.
  • the process is performed by heating the workpiece to a temperature above l,400 F. and heating the dies to the same or a slightly lower temperature.
  • this process will be referred to herein as isothermal forming.
  • the speed of the press is selected at from 0 to about 100 inches per minute depending on the alloy composition and the forming temperature.
  • Titanium alloys are strain rate sensitive materials. That is, for any substantial deformation at elevated temperatures, the yield strength of the alloy is dependent on the rate of deformation. The higher the rate of deformation, the higher the yield strength.
  • the temperature and press speed are selected so that the resultant yield strength does not exceed approximately one-third of the yield strength of the die material at the same temperature.
  • a strength differential of this magnitude assures that the die material will not deform even when complex workpiece configurations are to be formed. It is by a proper selection of the above-named parameters that bulk deformation of titanium alloys is possible by isothermal forming, using a single die of commercially available material. The particular temperature selected and the particular press speed employed is keyed to the properties of the specific alloy being formed. The difficulty of forming is a function of the particular alloy being worked beginning with industrially pure titanium at the easiest end of the spectrum and extending to the alloys most difficult to work, such as Ti-8Al-1Mo-1V.
  • titanium alloys exhibit a sensitivity to strain rate wherein the yield strength increases with strain rate.
  • the drawing shows this property for three typical titanium alloys at several temperatures and pressing rates.
  • the curves illustrate to a limited extent the variety of strain rate sensitivity exhibited by different alloys of titanium.
  • the curves are labeled in inches per minute of press travel rather than actual strain rate because in forming complex shapes the strain rate varies throughout the forging.
  • the values used to plot the curves were obtained by axially compressing alloy cylinders 1 inch in diameter and 2 inches long. The values plotted are for the compressive yield strengths at which plastic deformation begins.
  • the solid lines represent commercial Ti-6Al-6V-2Sn alloy compressed at press speeds ranging from 0.6 to 50 inches per minute of head travel.
  • This alloy is representative of a titanium alloy which can be worked at a wide variety of pressing speeds and virtually throughout the temperature range from about 1,400 to about 1,950 F. without excessive die pressures.
  • the dash lines represent commercial Ti-8Al-lMo-1V alloy.
  • the press speeds range only from 0.05 to 5.0 inches per minute, yet the strain rate sensitivity of this alloy is much more pronounced.
  • the practical temperature range is at the upper end of the l,400 to 1,950 F. temperature range.
  • the yield strength ranges from 4,000 p.s.i. at 1,900 F. up to 30,000 p.s.i. at l,700 F.
  • Ti-SAl-lMo-IV represents alloys which are at the difficult to work end of the spectrum in the context of the present invention. These alloys should be deformed at temperatures above l,700 F. or at extremely low-strain rates, or both, depending on the die material employed.
  • the dot-dash lines represent Ti-6Al-4V alloy deformed at two press speeds. As can be seen this alloy remains relatively easy to work between l,500 and l,800 F. so long as the pressing speed is low. When the pressing speed is raised to just 5 inches per minute, the stress-temperature relationship becomes similar to, if not as extreme as that of Ti-8Al-1Mo-l V alloy.
  • the values in the drawing are expressed in terms of speed of press head travel rather than actual strain rate because the actual strain rate in a complex three-dimensional shape varies from point to point for a constant press speed and is a function of the press head speed, the shape of the original billet and the final shape. Lowering the strain rate throughout the material lowers the final forging pressure on the die faces. In some cases it may be desirable to deform at a constant total press force and allow the deforming body to select its own optimum strain rate. The need for such a measure is dependent on the alloy and the temperature involved. Obviously, the pressing could also be carried out in multiple steps if desired using the single set of dies and partial forging in each step.
  • a temperature range of between about 1,400 and about l,950 F. is preferred for several reasons.
  • the temperature at which titanium alloys are formed has a relationship to the microcrystalline structure and consequently to the mechanical properties of the finished product. Titanium alloys exhibit a change in crystal structure at some temperature from hexagonal to body-centered cubic. This temperature is called the beta transus and is a welldefined property of each alloy.
  • the beta transus temperatures for most known alloys range from about l,500 to l,900 F.
  • the beta transus temperatures for Ti-6Al-6V-2 Sn, Ti-8Al-lMo-1V and Ti-6Al-4V are approximately 1,735, 1,900 and l,830 F., respectively.
  • Forming alloys above the beta transus results in a final product which retains the body-centered cubic microcrystalline structure and possesses different properties than are provided by forming below the beta transus.
  • the desirability of forming above or below the beta transus depends therefore on the desired properties for the specific application. Accordingly, the temperature for each application is selected based on the specific alloy employed and the microcrystalline structure desired.
  • the primary objective in selecting the material for the forming tool or die is to avoid plastic deformation which would destroy the dies. Therefore the die pressures are to be kept below the yield strength of the die material selected so that only elastic deformation occurs.
  • alloys listed in table I are themselves difficult to form into finished shapes. They are difficult to machine; however, dies of these materials may be produced by commercial processes such as precision casting so that costs of die manufacture are minimized.
  • Lubrication during the forging operation promotes die filling.
  • Several hot forging lubrication techniques such as a combination of glass and graphite, are suitable and prevent both adhesion to the die and oxidation of the billet. As in any forging operation excessive lubricant accumulation prevents complete die filling and should be avoided.
  • a scaled down airplane nosewheel was prepared from a preform of Ti-6Al-6V-2Sn.
  • the preform was in the form of an annular ring having an outside diameter of 7.27 inches, an inside diameter of 2.40 inches and a thickness of 0.54 inches.
  • the preform weighed 3.25 pounds and was coated with a glass lubricant prior to forming.
  • the preform was heated in a furnace of 1,800 F.
  • Suitable dies of IN 100 were inserted in a press and were heated to l,800 F. by external induction heating coils surrounding the dies.
  • the preform was inserted between the dies and was pressed at a pressing speed of 0.1 inches per minute to a final forging load of 250 tons.
  • the forging was completed in a single step to form a finished nosewheel.
  • the forging had a plan area of 37 square inches.
  • the final forging pressure was 13,500 p.s.i.
  • EXAMPLE II A preform having the same composition and dimensions as example I was heated to 1,700 F. and was inserted into the same set of dies which were also preheated to 1,700 F. Pressing was effected at 0.1 inches per minute. At this temperature a forging load of 300 tons was required to close the dies resulting in a final forging pressure of 16,200 p.s.i.
  • EXAMPLE III A preform having the same composition and dimensions as example I was heated to 1,600 F. and was inserted into the same set of dies which were also preheated to 1,600. F. Pressing was again effected at 0.1 inches per minute. At this temperature a forging load of 350 tons was required to close the dies resulting in a final forging pressure of 18,900 p.s.i.
  • a pair of dies weighing 150 pounds each was formed of IN 100 to define a die cavity having an intricate form including corners, thin webs and flanges.
  • a billet in the form of a rectangular block of Ti-6Al-6V-2Sn weighing 2.1 pounds and having dimensions of 2.75 inches by 3 inches by 1.52 inches was heated in a furnace to l,800 F.
  • the dies were also heated to l,800 F. by induction heating coils surrounding the dies.
  • the billet was coated with glass lubricant before forging, was inserted between the dies and was pressed at 1,800 F. at a press speed of 3 inches per minute. Pressing was continued at a constant speed until the die cavity closed at a forging load of 250 tons. Complete die filling was achieved.
  • the plan area of the finished forging was 10.5 square inches giving a final forging pressure of 47,600 p.s.i.
  • the final form of the forging was generally of a rectangular shape and included four sidewalls roughly one-fourth inch in thickness and 2% inches high with a central web spanning the rectangular opening approximately half the distance from the bottom to the top of the rectangular walls.
  • the shape was designed for maximum material displacement during the forging operation.
  • EXAMPLE V A billet having the same dimensions and composition as that of example IV was heated to 1,700 F. and inserted between the same set of dies as in example IV. The dies were preheated to l,'700 F. and pressing was effected at 3 inches per minute to die closure. The resulting shape was identical to that of example IV and required a forging load of 325 tons resulting in a final forging pressure of 61,800 p.s.i.
  • EXAMPLE VI A billet of the same composition and dimensions as in the example IV was heated to 1,800 F. and inserted into the same set of dies. The dies were preheated to 1,800 F. Pressing was effected at 0.1 inches per minute to die closure. The resulting shape was identical to that of example IV and required a forging load of 75 tons for die closure resulting in a final forging pressure of 14,300 p.s.i.
  • EXAMPLE VI A larger set of dies defining a die cavity of the same shape as that of example IV and having scaled up dimensions was formed from IN 100.
  • the dies were also heated to 1,800 F. as in example IV.
  • the billet was coated with glass lubricant and inserted between the dies. Pressing was effected at 3 inches per minute to die closure with a forging load of 350 tons required for die closure.
  • the plan area of the final forged form was 15.5 square inches resulting in a final forging pressure of 45,200 p.s.i.
  • Example 1 to III the only variable is the temperature and the effect on the forging pressure is evident.
  • Examples IV and V show the effect of increased pressing speed at the temperatures illustrated in examples l and II.
  • Example VI differs from example I only in the shape. The values for forging pressure are quite close indicating for given temperature and press speed the final forging pressure can be predicted regardless of the shape of the forging.
  • Example VII is similar to example IV and illustrates that the forging pressure is not appreciably affected by the size of the forging.
  • the present invention has been described with reference to a forging operation, it applies equally to the extrusion of titanium and titanium alloys.
  • the die is manufactured of superalloy and the billet of material is placed in a container and forced through the die.
  • both the billet and the die are heated above 1,400 F. and are maintained at the desired temperature during the extrusion by conventional heating means compared to present processes of extrusion, pressures can be substantially reduced because much slower extrusion speeds can be selected in the absence of cooling thus taking advantage of the strain rate sensitivity of the alloy.
  • the present invention provides a new process for forming finished parts of titanium and titanium alloys either above or below the beta transus with a minimum of difficulty and process steps. The result is better products at a great savings in time and cost.
  • a method for forging complex three-dimensional shapes with strain rate sensitive titanium alloys comprising the steps of:

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US822453A 1969-05-07 1969-05-07 Hot forming of titanium and titanium alloys Expired - Lifetime US3635068A (en)

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Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4023225A (en) * 1974-11-01 1977-05-17 Anatoly Andreevich Tochilkin Method of fabrication of headed-shank parts from high-strength two-phase titanium alloys
US4055975A (en) * 1977-04-01 1977-11-01 Lockheed Aircraft Corporation Precision forging of titanium
US4281528A (en) * 1978-07-27 1981-08-04 Trw Inc. Process for isothermally shaping a titanium-containing metal workpiece
US4991419A (en) * 1988-11-18 1991-02-12 Sumitomo Metal Industries, Ltd. Method of manufacturing seamless tube formed of titanium material
FR2653449A1 (fr) * 1989-10-23 1991-04-26 Cooper Ind Inc Piece en alliage a base de titane et procede de production de celle-ci.
US5118363A (en) * 1988-06-07 1992-06-02 Aluminum Company Of America Processing for high performance TI-6A1-4V forgings
US5141566A (en) * 1990-05-31 1992-08-25 Sumitomo Metal Industries, Ltd. Process for manufacturing corrosion-resistant seamless titanium alloy tubes and pipes
US5242506A (en) * 1990-10-19 1993-09-07 United Technologies Corporation Rheologically controlled glass lubricant for hot metal working
US5244517A (en) * 1990-03-20 1993-09-14 Daido Tokushuko Kabushiki Kaisha Manufacturing titanium alloy component by beta forming
EP1495819A1 (en) * 2003-07-08 2005-01-12 BorgWarner Inc. Process for manufacturing forged titanium compressor wheel
US20050145310A1 (en) * 2003-12-24 2005-07-07 General Electric Company Method for producing homogeneous fine grain titanium materials suitable for ultrasonic inspection
RU2258575C1 (ru) * 2004-01-09 2005-08-20 ОАО Челябинский металлургический комбинат "МЕЧЕЛ" Способ производства труднодеформируемых поковок из высоколегированных сталей и сплавов
US20050257864A1 (en) * 2004-05-21 2005-11-24 Brian Marquardt Metastable beta-titanium alloys and methods of processing the same by direct aging
US20070102493A1 (en) * 2005-11-04 2007-05-10 Cyril Bath Company Titanium stretch forming apparatus and method
USH2227H1 (en) * 2002-02-11 2008-12-02 The United States Of America As Represented By The Secretary Of The Air Force High speed titanium alloy microstructural conversion method
US7611592B2 (en) 2006-02-23 2009-11-03 Ati Properties, Inc. Methods of beta processing titanium alloys
RU2382686C2 (ru) * 2008-02-12 2010-02-27 Государственное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Способ штамповки заготовок из наноструктурных титановых сплавов
US20100071430A1 (en) * 2005-11-04 2010-03-25 Cyril Bath Company Stretch forming apparatus with supplemental heating and method
US20110146854A1 (en) * 2009-12-22 2011-06-23 Spirit Aerosystems, Inc. System and method for forming contoured new and near-net shape titanium parts
US20110180188A1 (en) * 2010-01-22 2011-07-28 Ati Properties, Inc. Production of high strength titanium
US20110232349A1 (en) * 2003-05-09 2011-09-29 Hebda John J Processing of titanium-aluminum-vanadium alloys and products made thereby
US20120096915A1 (en) * 2010-10-25 2012-04-26 General Electric Company System and method for near net shape forging
US8337750B2 (en) 2005-09-13 2012-12-25 Ati Properties, Inc. Titanium alloys including increased oxygen content and exhibiting improved mechanical properties
US8499605B2 (en) 2010-07-28 2013-08-06 Ati Properties, Inc. Hot stretch straightening of high strength α/β processed titanium
US8652400B2 (en) 2011-06-01 2014-02-18 Ati Properties, Inc. Thermo-mechanical processing of nickel-base alloys
US9050647B2 (en) 2013-03-15 2015-06-09 Ati Properties, Inc. Split-pass open-die forging for hard-to-forge, strain-path sensitive titanium-base and nickel-base alloys
US9133539B2 (en) 2011-10-06 2015-09-15 Rolls-Royce Plc Method and equipment for shaping a cast component
US9192981B2 (en) 2013-03-11 2015-11-24 Ati Properties, Inc. Thermomechanical processing of high strength non-magnetic corrosion resistant material
US9206497B2 (en) 2010-09-15 2015-12-08 Ati Properties, Inc. Methods for processing titanium alloys
US9255316B2 (en) 2010-07-19 2016-02-09 Ati Properties, Inc. Processing of α+β titanium alloys
US9777361B2 (en) 2013-03-15 2017-10-03 Ati Properties Llc Thermomechanical processing of alpha-beta titanium alloys
US9869003B2 (en) 2013-02-26 2018-01-16 Ati Properties Llc Methods for processing alloys
US10094003B2 (en) 2015-01-12 2018-10-09 Ati Properties Llc Titanium alloy
US10435775B2 (en) 2010-09-15 2019-10-08 Ati Properties Llc Processing routes for titanium and titanium alloys
US10502252B2 (en) 2015-11-23 2019-12-10 Ati Properties Llc Processing of alpha-beta titanium alloys
US10513755B2 (en) 2010-09-23 2019-12-24 Ati Properties Llc High strength alpha/beta titanium alloy fasteners and fastener stock
US20200094309A1 (en) * 2016-12-21 2020-03-26 Hitachi Metals, Ltd. Method for producing hot-forged material
CN112718429A (zh) * 2020-12-17 2021-04-30 哈尔滨工业大学 一种减少钛基合金热旋压成形过程中氧化缺陷的方法
US11111552B2 (en) 2013-11-12 2021-09-07 Ati Properties Llc Methods for processing metal alloys
CN118492247A (zh) * 2024-07-17 2024-08-16 宝武特冶钛金科技有限公司 一种ta19钛合金前机匣精化锻件的制造方法
US12344918B2 (en) 2023-07-12 2025-07-01 Ati Properties Llc Titanium alloys

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FR2696957B1 (fr) * 1992-10-21 1994-11-25 Snecma Procédé de formage de pièces en alliages à base de titane.
RU2229952C1 (ru) * 2002-11-15 2004-06-10 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "Салют" Способ штамповки заготовок из титановых сплавов
RU2266171C1 (ru) * 2004-06-04 2005-12-20 ОАО Верхнесалдинское металлургическое производственное объединение (ВСМПО) Способ изготовления промежуточной заготовки из (альфа+бета)- титановых сплавов
RU2314362C2 (ru) * 2005-12-09 2008-01-10 Открытое Акционерное Общество "Корпорация Всмпо-Ависма" СПОСОБ ИЗГОТОВЛЕНИЯ ПРОМЕЖУТОЧНОЙ ЗАГОТОВКИ ИЗ α- ИЛИ α+β-ТИТАНОВЫХ СПЛАВОВ
CN103909191B (zh) * 2014-04-10 2016-01-13 西部钛业有限责任公司 一种舰船用STi80两相钛合金板坯的制备方法
JP6966411B2 (ja) * 2018-11-02 2021-11-17 信越化学工業株式会社 付加硬化型シリコーン樹脂組成物、その硬化物、及び光半導体装置
CN114310156B (zh) * 2021-11-18 2023-07-18 上海海隆石油管材研究所 一种钛合金钻杆接头模锻制备方法

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US2814101A (en) * 1953-04-14 1957-11-26 Prex Forgings Corp Forging die and method
US2900715A (en) * 1956-05-28 1959-08-25 Steel Improvement & Forge Co Protection of titanium
US3519503A (en) * 1967-12-22 1970-07-07 United Aircraft Corp Fabrication method for the high temperature alloys

Cited By (76)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4023225A (en) * 1974-11-01 1977-05-17 Anatoly Andreevich Tochilkin Method of fabrication of headed-shank parts from high-strength two-phase titanium alloys
US4055975A (en) * 1977-04-01 1977-11-01 Lockheed Aircraft Corporation Precision forging of titanium
US4281528A (en) * 1978-07-27 1981-08-04 Trw Inc. Process for isothermally shaping a titanium-containing metal workpiece
US5118363A (en) * 1988-06-07 1992-06-02 Aluminum Company Of America Processing for high performance TI-6A1-4V forgings
US4991419A (en) * 1988-11-18 1991-02-12 Sumitomo Metal Industries, Ltd. Method of manufacturing seamless tube formed of titanium material
FR2653449A1 (fr) * 1989-10-23 1991-04-26 Cooper Ind Inc Piece en alliage a base de titane et procede de production de celle-ci.
US5026520A (en) * 1989-10-23 1991-06-25 Cooper Industries, Inc. Fine grain titanium forgings and a method for their production
US5244517A (en) * 1990-03-20 1993-09-14 Daido Tokushuko Kabushiki Kaisha Manufacturing titanium alloy component by beta forming
US5141566A (en) * 1990-05-31 1992-08-25 Sumitomo Metal Industries, Ltd. Process for manufacturing corrosion-resistant seamless titanium alloy tubes and pipes
US5242506A (en) * 1990-10-19 1993-09-07 United Technologies Corporation Rheologically controlled glass lubricant for hot metal working
USH2227H1 (en) * 2002-02-11 2008-12-02 The United States Of America As Represented By The Secretary Of The Air Force High speed titanium alloy microstructural conversion method
US20090133786A1 (en) * 2002-12-26 2009-05-28 General Electric Company Method for producing homogeneous fine grain titanium materials suitable for ultrasonic inspection
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