EP3129516B1 - Wärmebehandlung einer aluminium-titan-basis-legierung - Google Patents

Wärmebehandlung einer aluminium-titan-basis-legierung Download PDF

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Publication number
EP3129516B1
EP3129516B1 EP15719501.7A EP15719501A EP3129516B1 EP 3129516 B1 EP3129516 B1 EP 3129516B1 EP 15719501 A EP15719501 A EP 15719501A EP 3129516 B1 EP3129516 B1 EP 3129516B1
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EP
European Patent Office
Prior art keywords
alloy
semi
finished product
casting
mould
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EP15719501.7A
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English (en)
French (fr)
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EP3129516A1 (de
Inventor
Guillaume Martin
Céline Jeanne MARCILLAUD
Marie MINEUR-PANIGEON
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • 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
    • B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D13/00—Centrifugal casting; Casting by using centrifugal force
    • B22D13/02—Centrifugal casting; Casting by using centrifugal force of elongated solid or hollow bodies, e.g. pipes, in moulds rotating around their longitudinal axis
    • B22D13/026—Centrifugal casting; Casting by using centrifugal force of elongated solid or hollow bodies, e.g. pipes, in moulds rotating around their longitudinal axis the longitudinal axis being vertical
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D13/00—Centrifugal casting; Casting by using centrifugal force
    • B22D13/04—Centrifugal casting; Casting by using centrifugal force of shallow solid or hollow bodies, e.g. wheels or rings, in moulds rotating around their axis of symmetry
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D13/00—Centrifugal casting; Casting by using centrifugal force
    • B22D13/10—Accessories for centrifugal casting apparatus, e.g. moulds, linings therefor, means for feeding molten metal, cleansing moulds, removing castings
    • B22D13/107—Means for feeding molten metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D21/00—Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
    • B22D21/002—Castings of light metals
    • B22D21/005—Castings of light metals with high melting point, e.g. Be 1280 degrees C, Ti 1725 degrees C
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
    • B22D27/15—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting by using vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D7/00—Casting ingots, e.g. from ferrous metals
    • B22D7/005—Casting ingots, e.g. from ferrous metals from non-ferrous metals
    • 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
    • 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
    • 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
    • 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
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/42—Heat treatment by hot isostatic pressing

Definitions

  • the present invention relates to the heat treatments of metallurgical alloys and, more particularly, the heat treatments of an alloy based on titanium aluminide (titanium-aluminide alloy in English).
  • Titanium aluminides are a class of alloys whose compositions include at least titanium and aluminum, and typically some additional alloying elements.
  • Titanium aluminides and in particular those of the gamma type (gamma titanium-aluminide alloys in English), have the advantage of low density, good resistance to cyclic deformation at low and intermediate temperature, and good environmental resistance. They find application in aircraft engines, as low pressure turbine blades (stator or rotor), bearing supports, high pressure compressor housings, and sealing supports for low pressure turbine, in particular.
  • Titanium aluminides and in particular those of the gamma type, are typically prepared by melting, molding, then hot isostatic compression in order to reduce the porosity resulting from the casting, followed by at least one heat treatment to obtain a good compromise between mechanical properties in traction, fatigue and creep.
  • This treatment process is characterized by a heat treatment temperature which is between 1045 ° C and 1255 ° C for 10 to 40 hours.
  • This manufacturing process is characterized by a heat treatment at a temperature between 1045 ° C and 1255 ° C and for 10 to 40 hours.
  • this “pressure lower than that of hot isostatic compression” will therefore necessarily be less than 1700 ⁇ 10 5 Pa, and preferably less than 1000 ⁇ 10 5 Pa.
  • a preferred characteristic of the invention moreover provides that the step of obtaining the semi-finished product resulting from the molding by centrifugal casting comprises a casting in said permanent mold which the alloy will then fill in such a way that the size of the internal pores of this alloy is reduced after casting compared to what it was before.
  • the simple shape of the mold (without undercut) will be sought to allow it to be filled quickly with the alloy in such a way as to reduce the size of its internal pores compared to what this pore size would be without casting. in such a mold.
  • a hot spot is typically a zone where the temperature of the alloy cast in the mold is higher and / or the flow of this alloy is higher. less favorable, or the diffusion of heat from the metal to the mold also less favorable, such as at the location of an edge of the mold).
  • a characteristic of the proposed solution moreover provides that the semi-finished product raw molded can be heat treated and then machined directly, without intermediate dimensional control of a blank.
  • a simple geometry of the mold therefore of the blank which comes out of its cavity, (typically having at least one plane of symmetry and / or at most one inflection) will limit the risks of non-conformity (limitation of the rate of porosities by avoiding create hot spots).
  • the fact that the mold is a metal mold will eliminate the risk of obtaining ceramic inclusions from the ceramic shell in the case of the lost wax casting process
  • a simple geometry of the mold, therefore of roughing, will allow easy automation of machining.
  • the figure 1 therefore illustrates the main steps not only of treatment of the alloy concerned, but more generally, as a finished product, for example of a turbine blade made of a titanium aluminide-based alloy.
  • An alloy microstructure comprising gamma grains and / or lamellar grains (alpha2 / gamma).
  • step 13 machine in this form here of one or more turbine blades, the heat-treated semi-finished product (see figure 2 ).
  • a device 15 as illustrated may be used. figure 3 which will make it possible to mold a series of semi-finished blanks 7, each of which can have the shape of a bar as foundry where the finished part (s) will then be machined, here two blades 17 of turbomachine turbine.
  • the device 15 comprises a closed and sealed enclosure 19 in which a partial vacuum can be applied.
  • An ingot 21, here in an alloy based on titanium aluminide, and more precisely on titanium aluminide of the gamma type, is first melted in a crucible 23. When molten, the alloy is then poured into a mold. 25 permanent metal, via a funnel 26.
  • the mold 25 makes it possible to cast the alloy by centrifugation, in order to obtain the blanks 7. For this, it is rotated around an axis A.
  • the mold 25 comprises several cavities 27 which extend radially (axes B1 , B2 ...; figures 3, 4 ) around the axis A, preferably by means of a motor 29. These cavities are preferably regularly spaced angularly around the axis A which is here vertical.
  • the centrifugal forces generated by the rotation of the mold force the molten alloy to enter and fill these cavities.
  • the alloy to be cast brought towards the center of the mold, is distributed radially towards the peripheral cavities.
  • the mold 25 is opened and the molded blanks 7 are extracted.
  • the walls of the mold which surround the cavities 27 for collecting the metal are resistant to centrifugal forces, typically more than 10 g.
  • the particles are subjected to a centrifugal force, which can be increased with the angular speed. This increase is distributed over the entire mass of the liquid metal, uniformly over the entire length of each cavity 27.
  • the mold comprises several shells, such as 150a, 150b which open and close along a surface (here the parting line 152) which is generally transverse to the axis (A) around which the mold rotates.
  • a separable attachment 153 such as a lock, is established between the shells so, once the shells have been separated, to be able to exit the molded blank, through the released opening 154.
  • the lines 152 also materialize a parting line making it possible to close and open the mold in question.
  • the mold shown has first and second sides 33a, 33b opposite along the axis 35 and parallel to each other. These two sides are one the entry side of the casting; It is therefore radially internal and the axis 34 is parallel (or even coincident) with one of the axes B, such as B1.
  • this mold (and therefore the solid, polyhedral blank obtained) has here, between the aforementioned first and second sides, a third and a fourth sides (33c, 33d) which widen together from the first side 33a towards the second side, at a first angle and then, from a break in slope (or inflection) 35, at a second larger angle than the first.
  • this mold (its mold cavity) is defined by a first and a second truncated pyramids 37a, 37b, the second pyramid being the extension of the first pyramid by the large base of the first pyramid which is exactly superimposed on the small base of the second.
  • the mold and its molded blank have a plane of symmetry 39 perpendicular to the first and second sides 33a, 33b and which contains the axis 34.
  • the embodiment of the mold cavity of the figure 6 illustrates a blocky mold cavity having two opposite sides, each of generally trapezoidal shape 37a, 37b.
  • Access to the interior of the cavity can be effected radially by one of the two lateral sides, here the larger 41c.
  • the blank exhibits externally - on a determined side or face - at most one inflection by which the section of the semi-finished blank increases or decreases, with, depending on its axis of elongation, here 34 or 43, a maximum cross section S1 of the blank located at one end, along this axis.
  • the figure 7 shows another interesting mold solution where, individually, the open radially inner end 45a of the alloy casting cavity 27 has a shape tapering in section (zone 47a) towards the center of the cavity, along radial direction B.
  • a truncated cone could be suitable.
  • the shape here is in fact a double funnel (head-to-tail), therefore with a radially outer end part of the cavity, which is stepped, to present an enlarged end part 47b.
  • section S2, S3 of the mold / molded blank towards the (or at) ends there are thus maximums of section S2, S3 of the mold / molded blank towards the (or at) ends, it being specified that the sections S1, S2, S3 are each defined externally, transversely to the axis of elongation concerned, as shown.
  • the form 47a may correspond to the heel area of this blade and the end part 47b to the area of the enlarged foot, or vice versa.
  • VAR Vauum Arc Remelting - Recasting with the vacuum arc
  • PAM Pasma Arc Melting - Fusion by plasma arc
  • step 8 figure 1 After having unmolded these blanks 7, they can be cut (roughly) into semi-finished products (step 8 figure 1 ), according to said form "less complex" than that of the finished products which will finally be machined.
  • the unmolded blank can thus be cut into a shape which does not require dimensional control before the latter.
  • ci is machined according to the expected finished product; see final step 14 of dimensional control after machining, figure 1 .
  • each semi-finished product 7 will have been heat treated, without hot isostatic compression (CIC), in order to obtain an alloy microstructure comprising gamma grains and / or lamellar grains (alpha2 / gamma).
  • CIC hot isostatic compression
  • the figures 10.11 show TiAl 48-2-2 microstructures: 48% Al 2% Cr 2% Nb (at%) obtained respectively with and without hot isostatic compaction (CIC), for the same thermal history.
  • tests 1, in Rm, and 4, in A% show an almost exact agreement (superposition) of the results with hot isostatic compaction (solid diamonds) and without (hollow diamonds). The other results are close, two by two. And when they exist, dispersions are low.
  • test piece (a cylinder) made of TiAl 48-2-2.
  • the comparative case of figure 10 was obtained under the following conditions (see US 5609698 ): first treatment, called PLL treatment, comprising a pre-HIP treatment of 1145 ° C for 5 hours, HIP at 1255 ° C, and heat treatment at 1200 ° C, for 2 hours.
  • the alloy used may in particular be TiAl 48-2-2: 48% Al; 2% Cr; 2% Nb (at%), especially since this intermetallic material is useful for at least partially producing certain stages of a turbomachine turbine aircraft, the invention is more generally applicable in particular to the titanium aluminide alloys mentioned below having a composition capable of forming alpha2 and gamma phases, when the alloy is cooled from a melt.
  • gamma titanium aluminides are typically alloys of titanium, from about 40 to 50 atomic percent (at%) aluminum, with optionally small amounts of other alloying elements such as chromium, niobium, vanadium, tantalum, manganese and / or boron.
  • Preferred compositions are from about 45.0 to about 48.5 atomic percent of aluminum, and therefore are at the high end of the operating range.
  • Ti-48Al-2Cr-2Nb Ti-48Al-2Mn-2Nb, Ti-49Al-1V, Ti-47Al-1 Mn-2Nb-0.5W-0.5Mo- 0.2Si, and Ti-47Al- 5Nb-1W. If the manufacturing conditions (in particular the heat treatment) applied to these specific alloys correspond to the aforementioned case of TiAl 48-2-2, in conjunction with the figures 11-12 , the results provided figure 12 are applicable to them.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
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  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)

Claims (14)

  1. Verfahren zur Behandlung einer Legierung aus Titanaluminid mit 40 bis 50 Atomprozent Aluminium (at%), wobei das Verfahren folgende Schritte umfasst:
    - das Formgießen eines Halbzeugs durch Schleuderguss in eine Dauerform (25), dann
    - die Wärmebehandlung des Halbzeugs bei einem Druck, im Wesentlichen dem atmosphärischen Druck entspricht, bis eine Mikrostruktur der Legierung erzielt wird, die Gammakörner und/oder Lamellenkörner (Alpha2/Gamma) umfasst,
    dadurch gekennzeichnet, dass die Wärmebehandlungstemperatur zwischen 1045°C und 1255°C beträgt und besagte Wärmebehandlung 10 bis 40 Stunden lang dauert.
  2. Verfahren zur Herstellung eines Turbomaschinenteils aus einer Legierung aus Titanaluminid mit 40 bis 50 Atomprozent Aluminium (at%) ohne isostatisches Heißpressen, welches die folgenden Schritte umfasst:
    - das Formgießen durch Schleuderguss in eine Dauerform (25), um ein Halbzeug mit einer weniger komplexeren Form als das Fertigerzeugnis (9, 17) zu erzielen,
    - die Wärmebehandlung des Halbzeugs bei einer Temperatur zwischen 1045°C und 1255°C 10 bis 40 Stunden lang ohne isostatisches Heißpressen bei einem Druck, im Wesentlichen gleich dem atmosphärischen Druck ist, bis eine Mikrostruktur der Legierung erzielt wird, die Gammakörner und/oder Lamellenkörner (Alpha 2/Gamma) umfasst,
    - anschließend die Formbearbeitung des besagten wärmebehandelten Halbzeugs (9, 17).
  3. Verfahren nach Anspruch 1 oder 2, in welchem der Schritt der Herstellung des Halbzeugs durch Formgießen im Schleuderguss das Gießen der Legierung in besagte Dauerform (25) umfasst, wobei die Legierung die Form so füllt, dass die Innenporen dieser Legierung nach dem Guss im Vergleich zu vorher kleiner sind, wobei das Befüllen:
    - der oberen Form mit einer Fließgeschwindigkeit der Legierung erfolgt, die größer ist als die Geschwindigkeit, in der die Legierung in der Form erstarrt, und/oder
    - in weniger als 1 Minute, vorzugsweise aber in 30 Sekunden bzw. in 20 Sekunden erfolgt.
  4. Verfahren nach einem der vorhergehenden Ansprüche, in dem besagte Legierung eine der folgenden Legierungen ist: Ti-48AL-2Cr-2Nb, Ti-48AL-2Mn-2Nb, Ti-49Ai-1V, Ti-47A1-1mn-2Nb-0.5W-0.5MO-0.2Si und Ti-47Al-5nB-1W.
  5. Verfahren nach einem der vorhergehenden Ansprüche, in dem besagte Legierung TiAL 48-2-2:48%AI2%Cr2% Nb (at%) ist.
  6. Verfahren nach einem der vorhergehenden Ansprüche, in dem der Schritt zur Erzielung eines Halbzeugs (7) durch Formgießen folgendes umfasst:
    - das Formgießen der Legierung durch Schleuderguss in eine metallische Form oder,
    - besagtes Formgießen durch Schleuderguss in eine metallische Form, gefolgt vom Schneiden besagter geformter Legierung,
    an einem Rohling (7) entlang, welcher mindestens eine Symmetrieebene (39) aufweist.
  7. Verfahren nach einem der vorhergehenden Ansprüche, indem der Schritt der Erzielung eines Halbzeugs durch Formgießen, wobei das Halbzeug eine Achse und entlang dieser Achse einen veränderlichen Querschnitt aufweist, folgendes umfasst:
    - das Formgießen durch Schleuderguss in eine metallische Form oder,
    - das Formgießen durch Schleuderguss in eine metallische Form, gefolgt vom Schneiden der besagten gegossenen Legierung in Teile,
    an einem Rohling (7) entlang, der an der Außenseite höchstens einen Knickpunkt aufweist, durch welchen sich der Querschnitt des halbfertigen Rohlings vergrößert oder verkleinert, wobei sich entlang dieser Achse:
    - die maximalen Werte des Querschnitts (S2, S3) des Rohlings an den Enden desselben befinden, oder
    - sich ein maximaler Querschnitt (S1) des Rohlings an einem einzigen Ende befindet.
  8. Verfahren entweder nur nach Anspruch 2 oder in Kombination mit einem der Ansprüche 3 bis 7, in dem das Halbzeug (7) wärmebehandelt und direkt ohne Zwischenkontrolle der Größe bearbeitet wird.
  9. Verfahren entweder nur nach Anspruch 2 oder in Kombination mit einem der Ansprüche 3 bis 8, in dem der Schritt zur Erzielung des Halbzeugs (7) folgendes umfasst:
    - ausgehend von dem Guss der besagten, geschmolzenen Legierung die Herstellung eines erstens Blocks aus diesem Material,
    - das Wiedereinschmelzen des ersten Blocks in einem metallischen abgekühlten Tiegel (23) und das Gießen des ersten wiedereingeschmolzenen Blocks in eine metallische Schleuderguss- Dauerform (25), um einen geformten Block zu erhalten,
    - das Herausnehmen des wiedereingeschmolzenen geformten Blocks aus der Form und das Schneiden des Halbzeugs in eine weniger komplexere Form.
  10. Verfahren nach Anspruch 9, in dem:
    - die Herstellung des ersten Blocks durch VAR (Vacuum Arc Remelting - Vakuuminduktionsschmelzen) oder durch PAM (Plasma Arc Melting-Plasmalichtbogenschmelzen), und
    - das Wiedereinschmelzen des ersten Blocks in einem VAR SM (Skull Melter - Kalt-Schmelz-Tiegel) erfolgt.
  11. Verfahren nach einem der vorhergehenden Ansprüche, bei dem das Halbzeug wärmebehandelt wird, indem man es:
    - erst 5 bis 15 Stunden lang bei einem Druck kleiner dem Druck einer isostatischen Heißpressung und im Wesentlichen gleich dem atmosphärischen Druck auf eine Temperatur von 1045°C bis 1145°C erhitzt,
    - dann 3 bis 10 Stunden lang bei einem Druck kleiner dem Druck einer isostatischen Heißpressung und im Wesentlichen gleich dem atmosphärischen Druck auf eine Temperatur von 1135° bis 1235 °C erhitzt,
    - und schließlich 2 bis 15 Stunden lang bei einem Druck kleiner dem Druck einer isostatischen Heißpressung und im Wesentlichen gleich dem atmosphärischen Druck auf eine Temperatur von 1155°C bis 1255°C erhitzt.
  12. Verfahren nach Anspruch 1, oder einem der Ansprüche 3 bis 11, sofern er mit Anspruch 1 verbunden wird, in dem die Behandlung der Legierung ohne isostatische Heißpressung erfolgt.
  13. Verfahren nach Anspruch 2 oder einem der Ansprüche 3 bis 11, sofern er mit Anspruch 2 verbunden wird, in dem das Werkstück eine Turbinenschaufel für ein Luftfahrzeug ist.
  14. Verfahren nach Anspruch 1 oder einem der Ansprüche 3 bis 11, sofern er mit Anspruch 1 verbunden wird, in dem die Legierung für eine Turbinenschaufel eines Luftfahrzeugs bestimmt ist
EP15719501.7A 2014-04-08 2015-04-02 Wärmebehandlung einer aluminium-titan-basis-legierung Active EP3129516B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1453131A FR3019561B1 (fr) 2014-04-08 2014-04-08 Traitement thermique d'un alliage a base d'aluminure de titane
PCT/FR2015/050871 WO2015155448A1 (fr) 2014-04-08 2015-04-02 Traitement thermique d'un alliage a base d'aluminure de titane

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EP3129516A1 EP3129516A1 (de) 2017-02-15
EP3129516B1 true EP3129516B1 (de) 2021-06-09

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US (1) US10329655B2 (de)
EP (1) EP3129516B1 (de)
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DE102016224386A1 (de) * 2016-12-07 2018-06-07 MTU Aero Engines AG Verfahren zum herstellen einer schaufel für eine strömungsmaschine
FR3073163B1 (fr) * 2017-11-07 2022-07-15 Safran Aircraft Engines Dispositif et procede de fabrication d'une ebauche en alliage metallique par coulee centrifuge
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FR3019561A1 (fr) 2015-10-09
WO2015155448A1 (fr) 2015-10-15
US10329655B2 (en) 2019-06-25
FR3019561B1 (fr) 2017-12-08
US20170022594A1 (en) 2017-01-26
EP3129516A1 (de) 2017-02-15

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