EP3372700B1 - Procédé de fabrication d'éléments structuraux en tial forgés - Google Patents

Procédé de fabrication d'éléments structuraux en tial forgés Download PDF

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Publication number
EP3372700B1
EP3372700B1 EP17160397.0A EP17160397A EP3372700B1 EP 3372700 B1 EP3372700 B1 EP 3372700B1 EP 17160397 A EP17160397 A EP 17160397A EP 3372700 B1 EP3372700 B1 EP 3372700B1
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EP
European Patent Office
Prior art keywords
forging
blank
deformation
forged
alloy
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EP17160397.0A
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German (de)
English (en)
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EP3372700A1 (fr
Inventor
Falko Dr. Heutling
Claudia Kunze
Ulrike Dr. Habel
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MTU Aero Engines AG
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MTU Aero Engines AG
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Priority to ES17160397T priority Critical patent/ES2753242T3/es
Priority to EP17160397.0A priority patent/EP3372700B1/fr
Priority to US15/915,290 priority patent/US10737314B2/en
Publication of EP3372700A1 publication Critical patent/EP3372700A1/fr
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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
    • B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
    • B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
    • B21J5/025—Closed die forging
    • 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
    • B21J1/06—Heating or cooling methods or arrangements specially adapted for performing forging or pressing operations
    • 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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • F05D2230/41—Hardening; Annealing
    • 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
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl

Definitions

  • titanium aluminides or TiAl alloys Due to their low specific weight and their mechanical properties, components made of titanium aluminides or TiAl alloys are of interest for use in gas turbines, in particular aircraft turbines.
  • Titanium aluminides or TiAl alloys are hereby understood as meaning alloys which contain titanium and aluminum as main constituents, so that their chemical composition has constituents with the highest proportions of aluminum and titanium.
  • TiAl alloys are characterized by the formation of intermetallic phases, such as y - TiAl or ⁇ 2 - Ti 3 Al, which give the material good strength properties.
  • TiAl alloys are not easy to process and the microstructures of TiAl materials need to be precisely adjusted to achieve the desired mechanical properties.
  • the invention proposes that, in the case of a forging process for the production of a forged component from a TiAl alloy, the forming by forging be carried out in such a way that a homogeneous deformation takes place for the entire component. It has been shown that with a uniform deformation over the entire component, in a simple manner a homogeneous microstructure of the forged component can be achieved, so that the property profile of the forged component over the entire component is homogeneous. Accordingly, a blank is provided for the forging, the shape of which is selected such that the deformation over the entire volume of the blank or of the blank forged from the blank is substantially the same.
  • a forged semi-finished product can thus be understood in particular to be a forged upper part or forged intermediate product, which can be processed via one or more processing steps to form a finished component, for example a turbine blade.
  • Under a blank can be understood in particular a forging material, which can be processed by a forging process to the semifinished product.
  • the degree of deformation ⁇ is defined as the natural logarithm of the ratio of final dimension x 1 after deformation to initial dimension x 0 in the case of a one-dimensional dimensional change in a Cartesian reference system.
  • the blank can now be shaped in such a way that the degree of deformation has a defined value in one of the directions of the reference system, for example the x, y or z direction of a Cartesian reference system, in one of the directions of the reference system, and only within that or that the degree of deformation in several directions of the reference system or in each direction, in particular each main direction of the reference system has a defined value and deviates from this only within the allowable fluctuation range.
  • the shape of the blank can be chosen so that the transformation to be performed has a defined degree of deformation, which is within the usable volume of the forged Semifinished from the defined value of the degree of deformation by a maximum of ⁇ 0.5, in particular ⁇ 0.25 deviates.
  • the defined value of the degree of deformation may in particular be greater than or equal to 0.7, so that a minimum deformation takes place to that extent.
  • the degree of deformation of 0.7 within the usable volume is not exceeded, so that the entire material of the forged semi-finished product undergoes a minimum deformation by forging.
  • the defined value of the degree of deformation can be kept as low as possible in order to keep the cost of forming low. Accordingly, the value of the degree of deformation may be less than or equal to 2.5, in particular less than or equal to 2.0.
  • the shape of the blank can be selected so that along the longitudinal axis of the blank, so the axis with the largest dimension, the mass is distributed so that more mass is present at the two ends than in the middle of the blank.
  • the blank can be divided along its longitudinal axis into three equally long regions or sections, namely a first and second end region and a central region wherein the mass of the blank is distributed in the regions so that there is more mass in the end regions than in the central region , Accordingly, the blank may be formed such that M M ⁇ M E1 ⁇ M E2 where M M is the mass of the blank in the central region, M E1 is the mass of the blank in the first end region and M E2 is the mass of the blank in the second end region.
  • the blank can satisfy the condition: M M ⁇ M E2 / 1.25.
  • alloyed titanium aluminide alloys which are especially suitable for niobium and molybdenum can be used.
  • Such alloys are also referred to as TNM alloys.
  • an alloy of 27 to 30 weight percent aluminum, 8 to 10 weight percent niobium, and 1 to 3 weight percent molybdenum may be used, the remainder being titanium.
  • the aluminum content may be selected in the range of 28.1 to 29.1 weight percent aluminum, while 8.5 to 9.6 weight percent niobium and 1.8 to 2.8 weight percent molybdenum may be added.
  • the alloy may be alloyed with boron in the range of 0.01 to 0.04 weight percent boron, more preferably 0.019 to 0.034 weight percent boron.
  • the alloy may include unavoidable impurities such as carbon, oxygen, nitrogen, hydrogen, chromium, silicon, iron, copper, nickel and yttrium, the content of which is ⁇ 0.05% by weight of chromium, ⁇ 0.05% by weight of silicon, ⁇ 0.08 wt% oxygen, ⁇ 0.02 wt% carbon, ⁇ 0.015 wt% nitrogen, ⁇ 0.005 wt% hydrogen, ⁇ 0.06 wt% iron, ⁇ 0.15 wt% copper, ⁇ 0.02 wt% nickel and ⁇ 0.001 wt% yttrium , Further constituents may be contained individually in the range of 0 to 0.05 percent by weight or in total from 0 to 0.2 percent by weight.
  • unavoidable impurities such as carbon, oxygen, nitrogen, hydrogen, chromium, silicon, iron, copper, nickel and yttrium, the content of which is ⁇ 0.05% by weight of chromium, ⁇ 0.05% by weight of silicon,
  • the forging of the blank can be carried out in particular as isothermal forging, wherein only a single-stage forming, so only one forming step preferably can be carried out in only one forging without a further forming or forging takes place in another forging die. In this way, the cost of forming can be kept low.
  • one-stage means both that the forming process takes place in a single continuous process, and that only a single transformation takes place in the production process.
  • the forming of the cast, for example, not yet formed blank for semi-finished can be done in a single forging step, without further transformation to the finished component is necessary. So it does not have to be pressed several times and from different directions, but it is only a press or a die with two forms required between which the blank is inserted and formed during pressing of the two forms against each other. The forged part does not have to be moved or moved between different forging steps.
  • the forging of the corresponding components can be carried out by drop forging in the temperature range of the ⁇ + ⁇ + ⁇ phase region, wherein the forging temperature in the range of 1150 ° C to 1200 ° C can lie.
  • a corresponding die can be kept at the temperature by heating during the forging process.
  • an inert ambient atmosphere may be adjusted during forging.
  • the forged semi-finished products may be subjected to a two-stage heat treatment, wherein the first stage of the heat treatment provides for recrystallization annealing below the ⁇ / ⁇ transformation temperature for a period of 50 to 100 minutes.
  • the annealing at a temperature below the ⁇ / ⁇ transformation temperature, where ⁇ -titanium is converted to ⁇ -TiAl in accordance with the phase diagram for the TiAl alloy used can be as close as possible to the ⁇ / ⁇ transformation temperature, with a temperature of 8%, in particular 4%, below the ⁇ / ⁇ - conversion temperature should not be fallen below.
  • the recrystallization annealing may preferably be carried out for 60 to 90 minutes, especially 70 to 80 minutes.
  • the first stage of the heat treatment with the recrystallization annealing may be followed by a second stage of heat treatment with stabilizing annealing in the temperature range of 800 ° C to 950 ° C for 5 to 7 hours.
  • the stabilization annealing can be carried out in particular in the temperature range from 825 ° C. to 925 ° C., preferably from 850 ° C. to 900 ° C., with a holding time of from 345 minutes to 375 minutes.
  • the cooling in the recrystallization annealing can be done by air cooling, wherein in the temperature range between 1300 ° C and 900 ° C, the cooling rate ⁇ 3 ° C per second should be to set a fine-lamellar microstructure of ⁇ 2 -Ti 3 Al and ⁇ -TiAl, which required mechanical properties guaranteed.
  • the cooling in the second heat treatment stage, so the stabilization annealing, can be done with correspondingly lower cooling rates in the oven.
  • the heat treatment steps are carried out as accurately as possible at the corresponding selected temperature.
  • an increasingly accurate adjustment of the temperature and keeping the components at the appropriate temperatures with increasing Expenses connected so that for an economically meaningful processing a compromise must be found.
  • a temperature adjustment with a deviation in the range of 5 ° C to 10 ° C up and down from the setpoint temperature has proven to be advantageous.
  • the selected target temperature for the heat treatment steps of the present invention can be set and held up and down in a corresponding temperature window of 5 ° C to 10 ° C deviation from the target temperature.
  • the precursor material may also be made by metal injection molding (MIM), powder metallurgy, additive processes (e.g., 3D printing, cladding), or combinations thereof.
  • MIM metal injection molding
  • the blanks or the starting material can be hot-isostatically pressed before forging. It may be advantageous to machine the starting material before forging on all sides or locally with a material-removing machining process in order to work off surface edge zones and / or to give the blank the desired shape for the subsequent shaping. Any suitable method can be used as the material-removing machining method, in particular metal-cutting methods or electrochemical machining methods.
  • the blanks can be produced by melting in vacuo or inert gas with self-consumable electrodes or in the cooled crucible by means of plasma arc melting, wherein a single or multiple remelting of the alloy can be performed.
  • the remelting may be by vacuum induction melting or vacuum arc remelting (VIM vacuum induction melting), and the cast material may be hot isostatically pressed using temperatures ⁇ 1200 ° C at a pressure ⁇ 100 MPa and a holding time ⁇ 4 hours can.
  • the forged semi-finished product can be post-processed with a material-removing machining process to produce the finished component.
  • a material-removing machining process Any suitable method can be used as the material-removing machining method, in particular metal-cutting methods or electrochemical machining methods.
  • FIGS. 1a and 1b show the sequence of process steps in the implementation of an embodiment of the method according to the invention.
  • a blank 5 is produced by filling a molten TiAl alloy into a mold 1 having a cavity 2 corresponding to the shape of the blank 5 to be produced.
  • the casting blank 4 After pouring the TiAl alloy in the mold 1 and solidifying the TiAl alloy, the casting blank 4 can be correspondingly pressed in a system 3 for hot isostatic pressing in order to compact the green cast iron 4 and to close possible cast blanks or the like.
  • the hot - isostatic pressing thus does not serve the transformation of the casting blank 4, but only the material compression.
  • the blank 5 can be additionally subjected to a material-removing post-processing, for example by machining or by electrochemical machining.
  • the correspondingly produced blank 5 is forged in a drop forging 6 to a near net shape, forged semi-finished 9, wherein the drop forge 6 has two Gesenkhohlformen 7 and 8, which define between them a cavity corresponding to the shape of the forged semi-finished product 9, as in the dashed representation of the FIG. 1b is shown.
  • the TiAl alloy is formed into the forged semifinished product 9.
  • the deformation of the blank 5 for the forged semi-finished product 9 can be carried out by isothermal forging at a temperature which is as constant as possible.
  • the compression of the Gesenkhohlformen 7 and 8 is indicated by the arrows in the FIG. 1b shown.
  • a finished turbine blade 10 with an airfoil 13, a blade root 11 and a shroud 12 is present.
  • results in the process of the invention can be prepared by a single forming step by isothermal forging in a drop forging 6 a near net shape of the component to be produced, so that the post-processing can be minimized.
  • FIG. 2 shows in Examples 1 to 3 different courses of the mass distribution over the longitudinal axis of a blank 5, as they can be used in the present invention.
  • FIG. 2 shows that a blank 5 can be divided into equal sections along the longitudinal axis of the blank 5, wherein within these sections different masses of the blank are present, namely at the two ends of the longitudinal axis respectively more mass than in a central region.
  • the mass of the respective areas at the ends can be the same or different sizes.
  • FIG. 3 shows a so-called quasibinary state diagram of a TiAl alloy as can be used in the present invention.
  • Quasi-binary means that in the state shown only the proportions of two components, in the present case Ti and Al change, and the other alloying constituents, in this case Nb and Mo, remain constant.
  • the dashed working field 14 lies in the ⁇ + ⁇ + ⁇ phase region and indicates the temperature range in which isothermal forging can be carried out with the corresponding composition of the TiAl alloy.

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  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
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  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
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Claims (19)

  1. Procédé de fabrication d'un élément structural forgé (10) en un alliage TiAl, en particulier d'une aube de turbine, dans lequel une ébauche (5) est réalisée à partir d'un alliage TiAl et déformée par forgeage pour obtenir un produit semi-fini forgé (9), un volume utilisable étant défini dans le produit semi-fini forgé, lequel volume correspond à l'élément structural forgé à fabriquer, caractérisé en ce que la forme de l'ébauche (5) est choisie de sorte que le taux de déformation ϕg à l'intérieur du volume utilisable du produit semi-fini forgé par forgeage présente une valeur définie qui s'écarte de la valeur définie d'un maximum de ± 1 au-dessus du volume utilisable, dans lequel ϕg = ½(| ϕx | + | ϕy | + | ϕz |), dans lequel ϕx, ϕy, ϕz sont les taux de déformation dans la direction x-, y- et z-, et sont chacun défini comme le logarithme naturel du rapport entre la dimension finale respective dans la direction x-, y- ou z- après la déformation et la dimension initiale respective dans la direction x-, y- ou z-.
  2. Procédé selon la revendication 1, caractérisé en ce que le taux de déformation à l'intérieur du volume utilisable du produit semi-fini forgé (9) s'écarte de la valeur définie d'au maximum ± 0,5, en particulier de ± 0,25.
  3. Procédé selon l'une des revendications précédentes, caractérisé en ce que la valeur définie du taux de déformation est supérieure ou égale à 0,7, le taux de déformation n'étant en particulier pas inférieur à 0,7 à l'intérieur du volume utilisable.
  4. Procédé selon l'une des revendications précédentes, caractérisé en ce que la valeur définie du taux de déformation est inférieure ou égale à 2,5, en particulier inférieure ou égale à 2,0.
  5. Procédé selon l'une des revendications précédentes, caractérisé en ce que la vitesse de déformation est comprise entre 0,01 et 0,5 1/s, en particulier entre 0,025 et 0,25 1/s.
  6. Procédé selon l'une des revendications précédentes, caractérisé en ce que la forme de l'ébauche (5) est choisie de sorte que, le long de l'axe longitudinal de l'ébauche, l'ébauche est divisée en trois régions égales, à savoir une première et une seconde région d'extrémité ainsi qu'une région centrale, dans lequel MM < ME1 ≤ ME2, MM étant la masse de l'ébauche dans la région centrale, ME1 étant la masse de l'ébauche dans la première région d'extrémité et ME2 étant la masse de l'ébauche dans la seconde région d'extrémité.
  7. Procédé selon la revendication 7, caractérisé en ce que MM est ≤ ME2/1,25.
  8. Procédé selon l'une des revendications précédentes, caractérisé en ce quel'on utilise un alliage TiAl avec du niobium et du molybdène, en particulier un alliage contenant 27 à 30 % en poids d'aluminium, 8 à 10 % en poids de niobium et 1 à 3 % en poids de molybdène.
  9. Procédé selon la revendication 8, caractérisé en ce quel'on utilise un alliage contenant 0,01 à 0,04 % en poids de bore.
  10. Procédé selon la revendication 8 ou 9, caractérisé en ce quel'on utilise on utilise un alliage qui présente, en plus des impuretés inévitables, au moins un autre constituant du groupe comprenant le carbone, l'oxygène, l'azote, l'hydrogène, le chrome, le silicium, le fer, le cuivre, le nickel et l'yttrium, leur teneur pouvant être ≤ 0,05 % en poids de chrome, ≤ 0,05 % en poids de silicium, ≤ 0,08 % en poids d'oxygène, ≤ 0,02 % en poids de carbone, ≤ 0,015 % en poids d'azote, ≤ 0,005 % en poids d'hydrogène, ≤ 0,06 % en poids de fer, ≤ 0,15 % en poids de cuivre, ≤ 0,02 % en poids de nickel et ≤ 0,001 % en poids d'yttrium.
  11. Procédé selon l'une des revendications 8 à 10, caractérisé en ce quel'on utilise un alliage dont la composition chimique comprend du titane en une quantité telle que l'alliage, avec les constituants restants selon les revendications 8 à 10, soit porté à 100 % en poids.
  12. Procédé selon l'une des revendications précédentes, caractérisé en ce que la déformation par forgeage isotherme, en particulier par estampage, a lieu dans la plage de température de la zone de phase α+γ+β- de l'alliage TiAl, en particulier à une température de forgeage comprise entre 1150 °C et 1200 °C.
  13. Procédé selon l'une des revendications précédentes, caractérisé en ce que l'alliage TiAl est soumis à un traitement thermique en deux étapes après la déformation par forgeage isotherme, la première étape du traitement thermique comprenant un recuit de recristallisation pendant 50 à 100 minutes à une température inférieure à la température de transformation γ/α et la seconde étape du traitement thermique comprend un recuit de stabilisation dans la plage de température de 800 °C à 950 °C pendant 5 à 7 heures, et la vitesse de refroidissement à la première étape du traitement thermique dans la plage de température de 1300 °C à 900 °C étant supérieure ou égale à 3 °C/s.
  14. Procédé selon la revendication 13, caractérisé en ce que le recuit de recristallisation est effectué pendant 60 à 90 minutes, en particulier pendant 70 à 80 minutes, et/ou le recuit de stabilisation est effectué dans la plage de température de 825 °C à 925 °C, en particulier de 850 °C à 900 °C, et/ou pendant 345 à 375 minutes.
  15. Procédé selon l'une des revendications précédentes, caractérisé en ce que la température pendant le traitement thermique est réglée vers le haut et vers le bas et maintenue avec une précision de 5 °C à 10 °C d'écart par rapport à la température de consigne.
  16. Procédé selon l'une des revendications précédentes, caractérisé en ce que l'on utilise comme matière première pour le forgeage, des ébauches (5) fabriquées par au moins l'un des procédés choisis dans le groupe comprenant la coulée, le moulage par injection de poudres métalliques (MIM), le procédé de la métallurgie des poudres, des procédés additifs, l'impression 3D, le soudage par superposition, le pressage isostatique à chaud et un procédé d'usinage par enlèvement de matériau.
  17. Procédé selon l'une des revendications précédentes, caractérisé en ce que le forgeage isotherme et/ou la déformation a lieu lors d'une étape de déformation en une étape, en particulier dans une matrice de forgeage, et/ou le forgeage isotherme est réalisé sous forme d'estampage avec une matrice chauffée.
  18. Procédé selon l'une des revendications précédentes, caractérisé en ce que l'ébauche (5) prévue n'est pas forgée et est déformée en une seule étape de forgeage pour former un produit semi-fini, l'unique étape de forgeage étant effectuée en particulier en pressant deux formes d'une matrice chacune dans une seule direction et l'une contre l'autre afin de déformer ainsi l'ébauche située entre les formes pour obtenir le produit semi-fini (9).
  19. Procédé selon l'une des revendications précédentes, caractérisé en ce que le produit semi-fini forgé (9), qui a notamment été déformé en une seule étape de forgeage, est à nouveau usiné par un procédé d'usinage par enlèvement de matériau, notamment par usinage par enlèvement de copeaux, de préférence par fraisage et/ou par usinage électrochimique, afin de produire l'élément structural forgé, en particulier sans autre déformation, et/ou en ce que l'élément structural forgé est une aube d'une turbomachine, notamment une aube de turbine, de préférence une turbine à basse pression.
EP17160397.0A 2017-03-10 2017-03-10 Procédé de fabrication d'éléments structuraux en tial forgés Active EP3372700B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES17160397T ES2753242T3 (es) 2017-03-10 2017-03-10 Procedimiento para fabricar componentes de TiAl forjados
EP17160397.0A EP3372700B1 (fr) 2017-03-10 2017-03-10 Procédé de fabrication d'éléments structuraux en tial forgés
US15/915,290 US10737314B2 (en) 2017-03-10 2018-03-08 Method for producing forged TiAl components

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17160397.0A EP3372700B1 (fr) 2017-03-10 2017-03-10 Procédé de fabrication d'éléments structuraux en tial forgés

Publications (2)

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EP3372700A1 EP3372700A1 (fr) 2018-09-12
EP3372700B1 true EP3372700B1 (fr) 2019-10-09

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EP17160397.0A Active EP3372700B1 (fr) 2017-03-10 2017-03-10 Procédé de fabrication d'éléments structuraux en tial forgés

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EP (1) EP3372700B1 (fr)
ES (1) ES2753242T3 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018209315A1 (de) 2018-06-12 2019-12-12 MTU Aero Engines AG Verfahren zur Herstellung eines Bauteils aus Gamma - TiAl und entsprechend hergestelltes Bauteil
DE102018209881A1 (de) * 2018-06-19 2019-12-19 MTU Aero Engines AG Verfahren zur Herstellung eines geschmiedeten Bauteils aus einer TiAl-Legierung
CN109365731B (zh) * 2018-12-11 2020-10-20 陕西宏远航空锻造有限责任公司 一种高温合金精锻叶片的模锻方法
DE102020214700A1 (de) 2020-11-23 2022-05-25 MTU Aero Engines AG Verfahren zur herstellung eines bauteils aus einer tial – legierung und entsprechend hergestelltes bauteil
CN113043648B (zh) * 2021-03-08 2024-01-26 洛阳航辉新材料有限公司 一种平板类铸件的热等静压方法
CN115679231B (zh) * 2022-09-16 2024-03-19 中南大学 一种提高钛铝基合金高温强塑性的工艺
CN115846559A (zh) * 2022-11-27 2023-03-28 陕西宏远航空锻造有限责任公司 一种多向锻造制备钛铝合金叶片方法
CN117684109A (zh) * 2023-12-13 2024-03-12 陕西创信金属科技有限公司 一种消除纯钛锻件加工应力形变的方法
CN118905244B (zh) * 2024-07-04 2025-05-09 北京科技大学 一种TiAl合金3D打印坯料等温锻造成形航空零件的制备方法
CN119681185B (zh) * 2024-12-18 2025-10-10 武汉理工大学 一种钛铝合金叶片高性能锻造方法
CN120920639B (zh) * 2025-08-14 2026-04-21 中国机械总院集团北京机电研究所有限公司 一种基于热换模技术的真空等温锻造TiAl合金叶片方法

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AT509768B1 (de) 2010-05-12 2012-04-15 Boehler Schmiedetechnik Gmbh & Co Kg Verfahren zur herstellung eines bauteiles und bauteile aus einer titan-aluminium-basislegierung
DE102011110740B4 (de) 2011-08-11 2017-01-19 MTU Aero Engines AG Verfahren zur Herstellung geschmiedeter TiAl-Bauteile
DE102015103422B3 (de) 2015-03-09 2016-07-14 LEISTRITZ Turbinentechnik GmbH Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer Alpha+Gamma-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke

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Publication number Publication date
US10737314B2 (en) 2020-08-11
ES2753242T3 (es) 2020-04-07
EP3372700A1 (fr) 2018-09-12
US20180257127A1 (en) 2018-09-13

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