CN102223964A - Method for manufacturing a titanium part through initial forging - Google Patents

Method for manufacturing a titanium part through initial forging Download PDF

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Publication number
CN102223964A
CN102223964A CN2009801467009A CN200980146700A CN102223964A CN 102223964 A CN102223964 A CN 102223964A CN 2009801467009 A CN2009801467009 A CN 2009801467009A CN 200980146700 A CN200980146700 A CN 200980146700A CN 102223964 A CN102223964 A CN 102223964A
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temperature
forging
alloy
phase transition
initial forging
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CN2009801467009A
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Chinese (zh)
Inventor
飞利浦·卡洛伊丝
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Safran Aircraft Engines SAS
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SNECMA SAS
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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

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Forging (AREA)

Abstract

The invention relates to a method for manufacturing a titanium alloy part and comprises: heating the part to a temperature T1 until the temperature of the part is substantially uniform, an operation for the initial forging of the part, immediately followed by tempering the part up to ambient temperature; heating the part to a temperature T2 followed by an operation for the final forging of the part to the temperature T2 then immediately followed by tempering the part, the final forging operation being capable of giving the part the final shape thereof, the temperature T1 being greater than the ss-transus temperature of said alloy, the temperature T2 being lower than the ss-transus temperature, the only heating of the part above the ss-transus temperature being the heating to the temperature T1, the initial forging preceding the final forging, said initial forging being carried out once the temperature of the part is substantially uniform, the method being characterized in that the tempering immediately following the initial forging is carried out at a speed greater than 150 DEG C/minute, and the deformation rate during the initial forging being greater than 0.7.

Description

Make the method for titanium parts by initial β forging
Technical field
The present invention relates to make the method for titanium alloy component.More specifically, the present invention relates to a kind of method, comprising:
Described part is heated to temperature T 1, make that the temperature of described part is roughly even, carry out initial forging operation and deformation rate greater than 0.7 for described part, then at once with described parts quenching to peripheral temperature; With
Described part is heated to temperature T 2, then in described temperature T 2Carry out final forging operation for described part, then at once with described parts quenching, described final forging operation is suitable for giving described part its net shape.
Background technology
Titanium alloy is used for high-tech application, especially for aeroturbine, to make the specific component that at high temperature bears high level stress.Pure titanium exists with two kinds of crystalline phase forms: the α phase, and it is a hexagonal structure, and exists under peripheral temperature; With β mutually, it is a body-centered cubic structure, and exists under the temperature more than the alleged β phase transition temperature, the β phase transition temperature of pure titanium equals 883 ℃.Carry out on the phasor of alloying at titanium and other element, β will occur on the β phase transition temperature mutually, have balance at β and α between mutually on the zone of depending on alloying element under this temperature.α β is made of with β mixture mutually α.Especially, alloying element has the influence that makes that the β phase transition temperature changes about 883 ℃.Develop titanium alloy, particularly comprise: the hot mechanical treatment of selecting alloying element and selecting alloy is carried out with desired performance.
For α β or accurate α alloy, for example TA6V and Ti6242 alloy, described alloy thereby be the β phase on the β phase transition temperature is in poised state at α and β between mutually, or is mainly the α phase under peripheral temperature.
In the following description, term " β zone " is used to represent the temperature range on the β phase transition temperature, and " α β field is used to represent the temperature range a little less than the β phase transition temperature to term, and wherein, α is in balance mutually with β.
By example, a kind of current method of making titanium alloys forging part comprises a plurality of forging processes, and all processes are all carried out (thereby temperature T in α β zone 1And T 2All be lower than the β phase transition temperature).Such forging scope makes that macrostructure can not perfect recrystallization and refinement again.In forging latter stage, still exist from the intrinsic phase of the α in groups tubercle of alloy base substrate (partly finishing form)." α tubercle is used to represent to present one or more tubercles in groups of preferred crystalline phase orientation to term in groups.These groups meeting causes the fatigue resistance of part to reduce.
The another kind of method of making titanium alloy forging part comprises a plurality of forging processes, and these processes are carried out in α β zone, and difference is that big process is carried out (thereby temperature T in the β field 1Be lower than the β phase transition temperature, and temperature T 2Be higher than the β phase transition temperature).This last process under higher temperature makes that part is easier to be shaped.Yet this last forging process is carried out under the temperature that is higher than the β phase transition temperature, thereby the entire microstructure of part corresponding acquisition in process early is eliminated.And it is big that the crystal grain of alloy (microstructure) is easy to become, and the deformation rate of last forging process is crystallization again and the refinement again (this is because part had approached its net shape soon before this last forging process) to impel crystal grain greatly inadequately usually.Because crystal grain is bigger, thereby the mechanical performance of part reduces.
And, in last forging process, complex-shaped (to give part its net shape) of used pattern, this macrostructure that makes part have inhomogeneous (zone that occurs in almost indeformable zone simultaneously and significantly be out of shape).This inhomogeneities produces big mechanical behavior difference in part.
Summary of the invention
The present invention attempts to remedy these shortcomings.
The present invention attempts to provide a kind of method that can obtain titanium alloy component, and described part has more uniform structure and has better mechanical performance, particularly for fatigue resistance.
This purpose realizes by the following fact: temperature T 1Be higher than alloy β phase transition temperature, temperature T 2Be lower than the β phase transition temperature, only work as described part and be heated to temperature T 1In time, is only it and is added into the above time of β phase transition temperature, and initial forging is prior to described final forging, as long as the temperature of described part is evenly just carried out initial forging basically, carries out with the speed faster than 150 ℃/minute and to quench.
Utilize these to be provided with, be used for the intrinsic shape matter of refinement microstructure (to obtain the β crystal grain of smaller szie) and elimination part owing to the high part deformation rate due to the forging under sufficiently high temperature.Below the β phase transition temperature, part is made of the β phase crystal grain that roughly waits axle, and this is that part is not distortion (at this stage part thickness constant) as yet because if this is the operation of forging for the first time.Forging makes these crystal grain distortion, and crystal grain is recrystallised to thin β crystal grain.Itself be recrystallised to thin acicular phase in these little β crystal grain quenching process after forging.Therefore, part does not have under peripheral temperature and does not wish the α phase tubercle that occurs.Part quenches fast enough subsequently and does not get back to subsequently in the β zone, and these facts are kept this fine microstructures, and avoid grain growth.Therefore, alloy microstructure refinement and more even again.The fatigue resistance of part improves thus.
And though by the ultrasonic listening metallurgical imperfection, ambient noise reduces.Such ambient noise is because due to the inhomogeneities of microstructure.Since more even on the structural entity, make ambient noise reduce, thereby can meticulousr and more easily detect any metallurgical imperfection in the part.
The present invention also provides a kind of aviation part, and it adopts the revolving body form, is made by method of the present invention.
Description of drawings
By reading the following detailed description to embodiment that provides according to non-limiting example, the present invention can be better understood, and its advantage is more obvious.Reference will be made to the accompanying drawings, wherein:
Fig. 1 is that example illustrates the schematic diagram that is used to make the method for titanium alloy metal parts of the present invention;
Fig. 2 A is the microphoto that is heated to the following titanium alloy of β phase transition temperature;
Fig. 2 B is the enlarged drawing of the microphoto of Fig. 2 A;
Fig. 3 A is the microphoto that is heated to the above titanium alloy of β phase transition temperature;
Fig. 3 B is the enlarged drawing of the microphoto of Fig. 3 A;
Fig. 4 A is that titanium alloy is heated to the above and microphoto that be out of shape with deformation rate 1 afterwards of β phase transition temperature; With
Fig. 4 B is that titanium alloy is heated to the above and microphoto that be out of shape with deformation rate 2.5 afterwards of β phase transition temperature.
The specific embodiment
Method of the present invention is applicable to the briquet that obtains in the following way on the whole: titanium alloy is melted one or many, described alloy is cast into ingot casting, use given thermodynamic cycle forging then.
Fig. 1 is the schematic diagram that example illustrates each step of the method that is used to make titanium alloy component of the present invention.In the diagram, axis of abscissas is represented the time t (not having scale) that increases, axis of ordinates with degree centigrade expression from peripheral temperature T AThe temperature T that increases.Part temperature as time t function is represented by a curve in this schematic diagram.In step 1, part is heated to above the temperature T of alloy β phase transition temperature 1Part is in this temperature T 1Keep sufficiently long a period of time and make the part temperature roughly evenly and equal T 1(step 1-1).This temperature remains on and is represented as platform in the step 1.Do not need to make part in temperature T 1Keep the long period, because the transformation that α arrives the β phase mutually takes place at once when process is higher than the β phase transition temperature.And part kept long duration can cause crystal grain to become big being higher than the β phase transition temperature, and this is harmful to, because it makes the mechanical performance of final part reduce.Therefore, if the industrial treatment ability allows, in case then the part temperature is roughly evenly and equal T 1Just must carry out forging as quickly as possible.
The titanium alloy that is heated to above the β phase transition temperature shows with Fig. 3 A and 3B by comparison diagram 2A and 2B with the microstructure difference that is heated between the identical titanium alloy that is lower than the β phase transition temperature.
Fig. 2 A is heated to a little less than β phase transition temperature and the microscope that do not experience the titanium alloy (the β phase transition temperature of this alloy is 1001 ℃) of forging to be got photo.Fig. 2 B is the enlarged drawing in the zone that gone out by rectangle frame among Fig. 2 A.In Fig. 2 B, as seen, in alloy, present orientation texture, particularly the orientation fibers that constitutes by almost parallel pin 10 (elongated crystal grain).
The photo that Fig. 3 A is to use microscope to get wherein demonstrates and identical titanium alloy shown in Fig. 2 A, but this titanium alloy is to form after being heated to a little more than the temperature of β phase transition temperature and do not experience forging.Fig. 3 B is the enlarged drawing in the zone of being confined by rectangle of Fig. 3 A.As seen, after process was higher than the β phase transition temperature, orientation fibers disappearance and structure be isotropism more.Alloy temperature one surpasses the β phase transition temperature, and α just changes the β phase into mutually, forms a crystallization again that waits of microstructure thus, and follows the increase with crystallite dimension.The stress that existed in part before heating about the β phase transition temperature is extremely significantly eliminated.The microstructure of alloy and state thereby be more suitable for forging operation.
As previously mentioned, be necessary to make whole part in the forging operating process, to be under the temperature that is higher than the β phase transition temperature, in case this All Ranges at part all roughly is in temperature T 1Shi Fasheng.Then, part is being substantially equal to T 1Temperature under forging, to give the intermediate shape (step 1-2) that part approaches its net shape.
In this initial forging operating process, deformation rate is greater than 0.7.Deformation rate T dBe defined as: the thickness H of part before distortion iWith its thickness H after distortion fThe logarithm of ratio:
T d = Log ( H i H f )
If indeformable (that is H, of part f=H i), deformation rate T then dEqual 0.
Advantageously, deformation rate is greater than 1.Preferably deformation rate is greater than 1.6.More high strain rate produces the refining (reducing crystallite dimension) of bigger microstructure, improves the fatigue resistance of part thus.These microstructure differences are found among Fig. 4 A and the 4B, and it has deformation rate 1 and deformation rate 2.5 respectively for using photo that microscope is got and demonstrating Ti6242 alloy after the regional forging of β.The detection that the inventor carries out these samples demonstrates: equal 78,000 circulations (at 772MPA) of 1 from deformation rate the service life of this Ti6242 alloy and become 130,000 circulations that deformation rate equals 2.5.
Ideally, the initial forging operation more than the β phase transition temperature should use pattern to implement, and makes the shape of part after forging approach the part net shape as far as possible, thereby makes the stress minimum that is produced by final forging operation subsequently.And, can consider to use the pattern (for example the truncated cone shape pattern adopts smooth piling up, or the diabolo shape) of simple shape, make that material can flow freely by mould and prevent that any material is trapped in the chamber in the forging operating process.
For example, after this initial forging, the shape of this part is the shape of truncated cone shape or diabolo at once.
In case part has experienced in β zone forging operation, then the part experience quench (step 1-3) and with faster than the speed of 150 ℃/minute (degrees celsius/minute) from the forging temperature T 1Be reduced to peripheral temperature.This rapid quenching is used to keep the fine microstructures (fine grain) of part, and optimizes the mechanical property, particularly its elastic limit of part thus, as confirming in the mechanical detection process of being undertaken by the inventor.
Advantageously, quenching is carried out under being in 200 ℃/minute to 400 ℃/minute speed in the scope.More advantageously, quench and to carry out being substantially equal under 250 ℃/minute the speed, wherein, the detection of being undertaken by the inventor demonstrates: make mechanical property by optimum optimization under this quenching velocity.Quench and preferably in water, carry out.
After quenching, part is heated to the temperature T that is lower than the β phase transition temperature 2(corresponding to the step 2 among Fig. 1).In temperature T 2, alloy thereby be α β zone, alloy microstructure does not change.Any fiber (needle construction) that in initial forging process, produces thereby kept.In case part has been heated to temperature T 2(step 2-1) then carries out final forging operation (step 2-2).
After this final forging, quench (step 2-3) is reduced to peripheral temperature T AThis quenching is used to optimize the mechanical property of part, particularly its elastic limit.
Under particular environment, method of the present invention can comprise one or more middle forging processes, all middle forging processes are in α β zone (thereby being in the temperature that is lower than the β phase transition temperature) all, and described process can carried out after initial forging and before final forging.
Under particular environment, after final forging, carry out tempering operation and have benefit in α β zone.The forging tempering in this α β zone (step 3) among Fig. 1 thereby under the temperature that is lower than the β phase transition temperature, carry out.Therefore, in case part quenches (step 2) in the latter stage of final forging, then part is heated to temperature T 3(step 3-1) do not had the ground of quenching cooling (step 3-2) afterwards to peripheral temperature.For Ti6242 alloy, temperature T 2Approximate 1000 ℃, temperature T 3Equal 595 ℃.In this tempering operation process, do not have the part forging, thereby this part does not change shape.This tempering also is used for reducing the residual stress that part produces owing to final forging operation.
Part solution annealing between final forging and tempering is (at T 2To T 3Under the temperature in the scope) be insignificant (because final forging is in α β zone, thereby not too serious), perhaps even may be harmful to.
Various titanium alloys can experience said method of the present invention.For example, used titanium alloy is the titanium family alloy of α β or accurate α.Especially, this alloy can be TA6V or Ti6242 (TA6Zr4DE).By example, these alloys can be used in the aeroturbine.
The detection of the Ti6242 alloy being carried out by the inventor demonstrates, and the part that obtains by method of the present invention has better fatigue behaviour than the part that obtains by art methods.
Part by method manufacturing as previously mentioned can be the dish that for example is used for aeroturbine.By example, part can be the drum that is used for aeroturbine.
Under particular environment, according to the character of titanium alloy and the type of processed part, the only part of part is heated to above the β phase transition temperature and experiences method of the present invention.So such forging is called as upset.

Claims (11)

1. method of making titanium alloy component, described method comprises:
Described part is heated to temperature T 1, make that the temperature of described part is roughly even, described part is carried out initial forging operation, then at once with described parts quenching to peripheral temperature; With
Described part is heated to temperature T 2, then in described temperature T 2Described part is carried out final forging operation, and then at once with described parts quenching, described final forging operation is suitable for giving described part its net shape;
Described temperature T 1The β phase transition temperature that is higher than described alloy, described temperature T 2Be lower than described β phase transition temperature, the described temperature T that is heated to 1Be only described part to be heated to more than the described β phase transition temperature, described initial forging is prior to described final forging, in case the temperature of described part is roughly evenly just carried out described initial forging,
Described method is characterised in that the described quenching of carrying out is at once carried out under the speed faster than 150 ℃/minute after described initial forging, the deformation rate in described initial forging process is greater than 0.7.
2. method according to claim 1 is characterized in that described deformation rate is greater than 1.
3. method according to claim 1 is characterized in that described deformation rate is greater than 1.6.
4. according to any one described method in the claim 1 to 3, it is characterized in that described quenching is to carry out being substantially equal under 250 ℃/minute the speed.
5. according to any one described method in the claim 1 to 4, it is characterized in that, carry out α β phase tempering operation after the described final forging.
6. according to any one described method in the claim 1 to 5, it is characterized in that described titanium alloy is α β or accurate α titanium family alloy.
7. according to any one described method in the claim 1 to 6, it is characterized in that described titanium alloy is selected from TA6V alloy and Ti6242 alloy.
8. according to any one described method in the claim 1 to 7, it is characterized in that the shape of the described part that forms at once after the described initial forging is the type of truncated cone or diabolo.
9. according to any one described method in the claim 1 to 8, it is characterized in that described part is the revolving body that is used for aeroturbine.
10. according to any one described method in the claim 1 to 8, it is characterized in that described part is the dish that is used for aeroturbine.
11., it is characterized in that described part is the drum that is used for aeroturbine according to any one described method in the claim 1 to 8.
CN2009801467009A 2008-09-22 2009-09-22 Method for manufacturing a titanium part through initial forging Pending CN102223964A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0856339A FR2936173B1 (en) 2008-09-22 2008-09-22 PROCESS FOR THE MANUFACTURE OF A TITANIUM PIECE WITH INITIAL FORGING IN THE BETA DOMAIN
FR0856339 2008-09-22
PCT/FR2009/051786 WO2010031985A1 (en) 2008-09-22 2009-09-22 Method for manufacturing a titanium part through initial β forging

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CN102223964A true CN102223964A (en) 2011-10-19

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

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