US20110240181A1 - Method for manufacturing a titanium part through initial beta forging - Google Patents

Method for manufacturing a titanium part through initial beta forging Download PDF

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Publication number
US20110240181A1
US20110240181A1 US13/120,243 US200913120243A US2011240181A1 US 20110240181 A1 US20110240181 A1 US 20110240181A1 US 200913120243 A US200913120243 A US 200913120243A US 2011240181 A1 US2011240181 A1 US 2011240181A1
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Prior art keywords
temperature
forging
alloy
quenching
transus
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Abandoned
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US13/120,243
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English (en)
Inventor
Philippe Gallois
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Safran Aircraft Engines SAS
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SNECMA SAS
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Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GALLOIS, PHILIPPE
Publication of US20110240181A1 publication Critical patent/US20110240181A1/en
Abandoned legal-status Critical Current

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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
    • B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium

Definitions

  • the present invention relates to a method of fabricating a part out of titanium alloy. More particularly, it relates to a method comprising:
  • Titanium alloys are used in high-tech applications, in particular for aviation turbines, in order to fabricate certain parts that are subjected to high levels of stress at high temperatures.
  • Pure titanium exists in two crystallographic forms: the ⁇ phase, which is hexagonal and exists at ambient temperature, and the ⁇ phase, which is body-centered cubic and exists at temperatures above the so-called ⁇ -transus temperature, which is equal to 883° C. for pure titanium.
  • the ⁇ phase On phase diagrams for titanium alloyed with other elements, the ⁇ phase is to be found above the ⁇ -transus temperature, and below that temperature there is equilibrium between the ⁇ phase and the ⁇ phase over an area that depends on the elements of the alloy.
  • the ⁇ phase is constituted by a mixture of ⁇ phase and ⁇ phase.
  • the alloying elements have the effect of causing the ⁇ -transus temperature to vary around 883° C.
  • Developing a titanium alloy that possesses desired properties consists, in particular, in selecting alloying elements and in selecting the thermomechanical treatment to which the alloy is to be subjected.
  • the alloy is thus in the ⁇ phase above the ⁇ -transus temperature, and respectively in a state of equilibrium between the ⁇ and ⁇ phases, or essentially in the ⁇ phase at ambient temperature.
  • ⁇ domain is used to designate the range of temperatures above the ⁇ -transus temperature
  • ⁇ domain is used to designate the range of temperatures immediately below the ⁇ -transus temperature in which the ⁇ and ⁇ phases are in equilibrium.
  • one present method of fabricating forged parts made of titanium alloys comprises a plurality of forging passes, all of which are performed in the ⁇ domain (the temperatures T 1 and T 2 are then both lower than the ⁇ -transus temperature).
  • Such a forging range does not enable the macrostructure to be fully recyrstallized and refined.
  • colonies of ⁇ phase nodules that are inherited from the alloy billet (semi-finished form).
  • colony of ⁇ nodules is used to designate a group of one or more nodules presenting a preferred crystallographic orientation. These colonies contribute to reducing the ability of the part to withstand fatigue.
  • Another method of fabricating forged parts out of titanium alloys comprises a plurality of forging passes, these passes being performed in the ⁇ domain, with the exception of the large pass, which is performed in the ⁇ domain (the temperature T 1 is then lower than the ⁇ -transus temperature, while the temperature T 2 is higher than the ⁇ -transus temperature).
  • This last pass at a higher temperature makes the part easier to shape. Nevertheless, this last forging pass takes place at a temperature higher than the ⁇ -transus temperature, so the entire microscopic structure of the part as obtained voluntarily during the earlier passes is erased.
  • alloy grains tend to become larger and the deformation ratio of the last forging pass is often not sufficiently great to encourage recrystallization, and thus refining, of the grains (since the part immediately prior to this last forging pass is already close to its final shape). Since the grains are larger, the mechanical properties of the part are diminished.
  • the dies that are used are complex in shape (in order to give the part its final shape), which gives rise to the part having a macrostructure that is not uniform (presence both of zones that are deformed little and of zones that are deformed considerably). This non-uniformity gives rise to large variations in mechanical behavior within the part.
  • the present invention seeks to remedy those drawbacks.
  • the invention seeks to propose a method of enabling a titanium alloy part to be obtained that possesses a structure that is more uniform and that possesses better mechanical properties, in particular in terms of ability to withstand fatigue.
  • the temperature T 1 is higher than the ⁇ -transus temperature of the alloy, that the temperature T 2 is lower than the ⁇ -transus temperature, that the only time said part is heated above the ⁇ -transus temperature is when it is heated to the temperature T 1 , that the initial forging precedes said final forging, the initial forging being performed as soon as the temperature of said part is substantially uniform, and that the quenching is performed at a speed faster than 150° C./min.
  • the high deformation ratio of the part due to forging at a temperature that is sufficiently high serves to refine the microstructure (to obtain ⁇ grains of smaller size) and to erase the heredity of the part.
  • the part is constituted by ⁇ phase grains that are substantially equi-axial, since the part has not yet been deformed, given this is the first forging operation (the thickness of the part at this stage is substantially constant). Forging deforms those grains, which recrystallize into fine ⁇ grains. These small ⁇ grains themselves recrystallize into a fine needled a phase during quenching after forging. The part therefore does not have undesirable nodules of ⁇ phase at ambient temperature.
  • the facts of subsequently quenching the part sufficiently fast and of subsequently not going back into the ⁇ domain enable this refined microstructure to be conserved, and avoids the grains growing.
  • background noise is reduced.
  • Such background noise is generated by non-uniformities in the microstructure. Since the structure is generally more uniform, it follows that background noise is diminished, and thus that any metallurgical defects in the part can be detected more finely and more easily.
  • the invention also provides an aviation part in the form of a body of revolution fabricated by a method of the invention.
  • FIG. 1 is a schematic diagram illustrating the method of the invention for fabricating a metal part out of titanium alloy
  • FIG. 2A is a microphotograph of a titanium alloy heated to below the ⁇ -transus temperature
  • FIG. 2B is an enlargement of the FIG. 2A microphotograph
  • FIG. 3A is a microphotograph of a titanium alloy heated to above the ⁇ -transus temperature
  • FIG. 3B is an enlargement of the FIG. 3 microphotograph
  • FIG. 4A is a microphotograph of a titanium alloy heated to above the ⁇ -transus temperature and then deformed with a deformation ratio of 1;
  • FIG. 4B is a microphotograph of a titanium alloy heated to above the ⁇ -transus temperature and then deformed with a deformation ratio of 2.5.
  • the method of the invention applies in general to a billet obtained by one or more melts of a titanium alloy, casting said alloy as an ingot, and then forging using a given thermodynamic cycle.
  • FIG. 1 is a diagram showing the steps of the method of the invention for fabricating a part out of titanium alloy.
  • the abscissa axis represents increasing time t (no scale), and the ordinate axis represents temperature T in degrees Celsius, increasing from ambient temperature T A .
  • the temperature of the part as a function of time t is represented in this diagram by a curve.
  • step 1 the part is heated to a temperature T 1 that is higher than the ⁇ -transus temperature for the alloy.
  • the part is maintained at this temperature T 1 for a length of time that is long enough for the temperature of the part to be substantially uniform and equal to T 1 (step 1 - 1 ). This maintaining of temperature is represented by the plateau in step 1 .
  • FIGS. 2A and 2B The microstructure difference between a titanium alloy heated to above the ⁇ -transus temperature and the same alloy heated to below the ⁇ -transus temperature is shown by comparing FIGS. 2A and 2B with FIGS. 3A and 3B .
  • FIG. 2A is a photograph taken by a microscope of a titanium alloy heated to a temperature that is immediately below the ⁇ -transus temperature, and without being subjected to forging (the ⁇ -transus temperature for this alloy is 1001° C.).
  • FIG. 2B is an enlargement of the zone in FIG. 2A that is outlined by a rectangle. In FIG. 2B , it can be seen that oriented structures are present in the alloy, specifically oriented fibers constituted by substantially parallel needles 10 (elongate grains).
  • FIG. 3A is a photograph taken using a microscope showing the same titanium alloy as that shown in FIG. 2A , but after heating to a temperature immediately above the ⁇ -transus temperature, and without being subjected to forging.
  • FIG. 3B is an enlargement of the zone of FIG. 3A that is outlined by a rectangle. It can be seen that after passing above the ⁇ -transus temperature, the oriented fibers disappear and the structure is more isotropic. As soon as the alloy temperature exceeds the ⁇ -transus temperature, a phase is transformed into ⁇ phase, thereby giving rise to equi-axial recrystallization of the microstructure, accompanied by an increase in grain size. The stresses that exist in the part prior to heating about the ⁇ -transus temperature are very largely eliminated. The microstructure and the state of the alloy is thus more appropriate for being subjected to the forging operation.
  • the entire part is at a temperature that is higher than the ⁇ -transus temperature during the forging operation, as happens once all of the zones of the part are substantially at the temperature T 1 .
  • the part is then forged at a temperature that is substantially equal to T 1 so as to give it an intermediate shape that approaches its final shape (step 1 - 2 ).
  • the deformation ratio T d is defined as being the logarithm of the ratio of the thickness H i of the part prior to deformation and its thickness H f after deformation:
  • the deformation ratio is greater than 1. Preferably it is greater than 1.6.
  • a higher deformation ratio gives rise to greater refining of the microstructure (reduction of grain size), thereby improving the resistance of the part to fatigue.
  • FIGS. 4A and 4B are photographs taken using a microscope and which show a Ti6242 alloy after forging in the p domain with a deformation ratio of 1 and with a deformation ratio of 2.5, respectively. Tests performed by the inventors on these samples have shown that the lifetime of such a Ti6242 alloy goes from 78,000 cycles (at 772 MPA) for a deformation ratio equal to 1, to 130,000 cycles for a deformation ratio equal to 2.5.
  • the initial forging operation above the ⁇ -transus temperature should be implemented using dies such that the shape of the part after forging is as close as possible to the final shape of the part, so as to minimize the stresses generated by the subsequent final forging operation. Furthermore, care can be taken to use dies that are of simple shape (e.g. a frustoconical die, in a flat stack, or of a diabolo shape) so as to enable material to flow freely throughout the mold and prevent any material becoming trapped in cavities during the forging operation.
  • simple shape e.g. a frustoconical die, in a flat stack, or of a diabolo shape
  • the shape of the part is of the frustoconical or diabolo type.
  • step 1 - 3 the part has been subjected to the forging operation in the ⁇ domain, it is subjected to quenching (step 1 - 3 ) from the forging temperature T 1 down to ambient temperature at a speed faster than 150° C./min (degrees Celsius per minute).
  • This rapid quenching serves to conserve a fine microstructure for the part (fine grains) and thus to optimize the mechanical characteristics of the part, in particular its elastic limit, as has been verified during mechanical testing undertaken by the inventor.
  • the quenching is performed at a speed lying in the range 200° C./min to 400° C./min. Even more advantageously, the quenching is performed at a speed substantially equal to 250° C./min, where tests carried out by the inventors have shown that the mechanical characteristics are best optimized at this quenching speed. Quenching is preferably performed in water.
  • the part After quenching, the part is heated to a temperature T 2 that is lower than the ⁇ -transus temperature (corresponding to step 2 in FIG. 1 ). At the temperature T 2 , the alloy is thus in the ⁇ domain, and the microstructure of the alloy is not modified. Any fibers (needle structures) produced during initial forging are thus conserved.
  • the final forging operation is performed (step 2 - 2 ).
  • step 2 - 3 This final forging is followed by quenching (step 2 - 3 ) down to ambient temperature T A .
  • This quenching serves to optimize the mechanical characteristics of the part, and in particular its elastic limit.
  • the method of the invention may include one or more intermediate forging passes, all in the ⁇ domain (and thus at a temperature lower than the ⁇ -transus temperature), which passes are performed after the initial forging and before the final forging.
  • the final forging may be followed by a tempering operation in the ⁇ domain.
  • This forging tempering (step 3 in FIG. 1 ) in the ⁇ domain is thus performed at a temperature that is lower than the ⁇ -transus temperature.
  • the part is heated to a temperature T 3 (step 3 - 1 ), and is then cooled without quenching (step 3 - 2 ) down to ambient temperature.
  • the temperature T 2 is approximately equal to 1000° C.
  • the temperature T 3 is equal to 595° C.
  • This tempering also serves to reduce the residual stresses generated in the part by the final forging operation.
  • Solution annealing of the part between final forging and tempering (at a temperature lying in the range T 2 and T 3 ) is pointless (since the final forging is in the domain and is therefore less severe), or might even be harmful.
  • the titanium alloy used is an alloy of the ⁇ or quasi- ⁇ titanium family.
  • the alloy may be TA6V or Ti6242 (TA6Zr4DE).
  • these alloys are used in aviation turbines.
  • Tests performed by the inventors on Ti6242 alloys show that a part obtained by a method of the invention possesses better fatigue properties than does a part obtained by a prior art method.
  • the part fabricated by a method as described above may be a disk for an aviation turbine, for example.
  • the part may be a drum for an aviation turbine.
  • upset forging a portion only of the part is heated to above the ⁇ -transus temperature and is subjected to the method of the invention. Such forging is then referred to as upset forging.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Forging (AREA)
US13/120,243 2008-09-22 2009-09-22 Method for manufacturing a titanium part through initial beta forging Abandoned US20110240181A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0856339A FR2936173B1 (fr) 2008-09-22 2008-09-22 Procede pour la fabrication d'une piece en titane avec forgeage initial dans le domaine beta
FR0856339 2008-09-22
PCT/FR2009/051786 WO2010031985A1 (fr) 2008-09-22 2009-09-22 PROCEDE POUR LA FABRICATION D'UNE PIECE EN TITANE AVEC FORGEAGE INITIAL DANS LE DOMAINE β

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US (1) US20110240181A1 (fr)
EP (1) EP2346629A1 (fr)
JP (1) JP2012503098A (fr)
CN (1) CN102223964A (fr)
BR (1) BRPI0919278A2 (fr)
CA (1) CA2738007A1 (fr)
FR (1) FR2936173B1 (fr)
IL (1) IL211876A0 (fr)
RU (1) RU2011115833A (fr)
WO (1) WO2010031985A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160060729A1 (en) * 2013-06-05 2016-03-03 Kabushiki Kaisha Kobe Seiko Sho (Koke Steel, Ltd.) Forged titanium alloy material and method for producing same, and ultrasonic inspection method
CN107824731A (zh) * 2017-09-28 2018-03-23 湖南金天钛业科技有限公司 一种Ti55钛合金大规格棒材锻造方法
CN109234568A (zh) * 2018-09-26 2019-01-18 西部超导材料科技股份有限公司 一种Ti6242钛合金大规格棒材的制备方法
CN113182476A (zh) * 2021-04-28 2021-07-30 西部钛业有限责任公司 一种高强tc11钛合金锻件的制备方法
CN117000926A (zh) * 2023-08-10 2023-11-07 陕西鼎益科技有限公司 一种提高钛合金棒材组织均匀性的锻造成型方法

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* Cited by examiner, † Cited by third party
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FR2979702B1 (fr) * 2011-09-05 2013-09-20 Snecma Procede de preparation d'eprouvettes de caracterisation mecanique d'un alliage de titane
FR2982279B1 (fr) * 2011-11-08 2013-12-13 Snecma Procede de fabrication d'une piece realisee dans un alliage de titane ta6zr4de
NO2975028T3 (fr) * 2013-03-15 2018-07-21
RU2635595C1 (ru) * 2016-09-23 2017-11-14 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" СПОСОБ ПОЛУЧЕНИЯ ДЕТАЛЕЙ ГАЗОТУРБИННЫХ ДВИГАТЕЛЕЙ ИЗ ТИТАНОВОГО ПСЕВДО -β - СПЛАВА С ЛИГАТУРОЙ Ti-Al-Mo-V-Cr-Fe
RU2660461C1 (ru) * 2017-04-25 2018-07-06 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" СПОСОБ ИЗГОТОВЛЕНИЯ ДЕТАЛЕЙ ИЗ ТИТАНОВЫХ ПСЕВДО - α - СПЛАВОВ
CN112222341A (zh) * 2020-10-16 2021-01-15 中国第二重型机械集团德阳万航模锻有限责任公司 Tc17钛合金模锻件的制造方法
CN114346141A (zh) * 2022-01-17 2022-04-15 太原理工大学 一种制备弱α织构钛合金锻件的多段热加工方法

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US6913436B2 (en) * 2003-01-16 2005-07-05 Rolls-Royce Plc Gas turbine engine blade containment assembly
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160060729A1 (en) * 2013-06-05 2016-03-03 Kabushiki Kaisha Kobe Seiko Sho (Koke Steel, Ltd.) Forged titanium alloy material and method for producing same, and ultrasonic inspection method
US10604823B2 (en) * 2013-06-05 2020-03-31 Kobe Steel, Ltd. Forged titanium alloy material and method for producing same, and ultrasonic inspection method
CN107824731A (zh) * 2017-09-28 2018-03-23 湖南金天钛业科技有限公司 一种Ti55钛合金大规格棒材锻造方法
CN109234568A (zh) * 2018-09-26 2019-01-18 西部超导材料科技股份有限公司 一种Ti6242钛合金大规格棒材的制备方法
CN113182476A (zh) * 2021-04-28 2021-07-30 西部钛业有限责任公司 一种高强tc11钛合金锻件的制备方法
CN117000926A (zh) * 2023-08-10 2023-11-07 陕西鼎益科技有限公司 一种提高钛合金棒材组织均匀性的锻造成型方法

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FR2936173A1 (fr) 2010-03-26
IL211876A0 (en) 2011-06-30
WO2010031985A1 (fr) 2010-03-25
CN102223964A (zh) 2011-10-19
JP2012503098A (ja) 2012-02-02
FR2936173B1 (fr) 2012-09-21
RU2011115833A (ru) 2012-10-27
EP2346629A1 (fr) 2011-07-27
CA2738007A1 (fr) 2010-03-25
BRPI0919278A2 (pt) 2015-12-15

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