EP0464366B1 - Procédé de fabrication d'une pièce en alliage à base d'aluminiure de titane contenant un matériau de dopage - Google Patents

Procédé de fabrication d'une pièce en alliage à base d'aluminiure de titane contenant un matériau de dopage Download PDF

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Publication number
EP0464366B1
EP0464366B1 EP91108605A EP91108605A EP0464366B1 EP 0464366 B1 EP0464366 B1 EP 0464366B1 EP 91108605 A EP91108605 A EP 91108605A EP 91108605 A EP91108605 A EP 91108605A EP 0464366 B1 EP0464366 B1 EP 0464366B1
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Prior art keywords
atomic
temperature
deformation
cast body
workpiece
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Expired - Lifetime
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EP91108605A
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German (de)
English (en)
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EP0464366A1 (fr
Inventor
Mohamed Dr. Nazmy
Markus Staubli
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ABB Asea Brown Boveri Ltd
ABB AB
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ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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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
    • 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

Definitions

  • the invention is based on a method for producing a workpiece from a dopant-containing alloy based on titanium aluminide.
  • High-temperature alloys for thermal machines based on the intermetallic compound TiAl which are suitable for the production of cast and forged components and which can supplement and partially replace the conventional nickel-based superalloys.
  • the invention relates to the melting and casting of alloys based on the intermetallic compound TiAl and doped with further additives and to the thermal and thermomechanical processing of this alloy into usable workpieces with good mechanical properties.
  • Intermetallic compounds of titanium with aluminum have some interesting properties which make them appear attractive as construction materials in the medium and higher temperature range. Among other things, this includes their low density compared to superalloys, which only reaches approx. 1/2 of the value for Ni superalloys. Their technical usability in the present form stands in the way of their brittleness. The former can be improved by additives, whereby higher strength values are also achieved.
  • intermetallic compounds some of which have already been introduced as construction materials, nickel aluminides, nickel silicides and titanium aluminides are known.
  • the shape of the intermetallic phases based on titanium aluminides presents a certain problem. Because of the high affinity of the elements involved for oxygen, in particular that of titanium, the production of molded parts by casting is difficult. Poor mold filling, porosity and cavities are the consequences. In addition, the properties of the cast structure cannot be improved to the desired extent by subsequent heat treatments. On the other hand, classic hot forming is opposed by the comparatively poor ductility in the lower temperature range.
  • US-A-4 842 819 describes the thermoforming of a blank which was obtained by hot isostatic pressing of a strip produced by melt spinning. After heat treatment, workpieces were obtained from the hot-formed blank by material-removing processing. The hot working was carried out at 975 ° C, the previous hot isostatic pressing at 950 ° C and over 200 MPa.
  • the invention is based on the object of specifying a method for producing a workpiece from a dopant-containing alloy based on titanium aluminide, which leads to a material of high oxidation and corrosion resistance, high heat resistance and sufficient ductility.
  • an alloy with a composition according to claim 8 (each consisting approximately half of Al and Ti and doped) was melted in an induction furnace: The melt was poured into ingots. The ingots were then annealed at a temperature of 1100 ° C for 10 hours in an argon atmosphere. The cast skin and scale layer were then removed mechanically. Then the cylindrical blocks were inserted into suitable capsules made of soft carbon steel and the latter sealed. The encapsulated workpieces were then hot-isostatically pressed at a temperature of 1260 ° C. for 3 hours under a pressure of 120 MPa, cooled, heated to 1100 ° C. at 10 to 50 ° C./min, held and forged at 1100 ° C.
  • the linear rate of deformation (punch speed of the forging press) v was 0.1 mm / s at the beginning of the forging process.
  • the pressing forces required for the upsetting were of medium size. In the present case, they were approximately 750 kN, which corresponded to an initial pressure of approximately 300 MPa.
  • the forging die consisted of the Mo alloy containing small amounts of Ti and Zr.
  • the flow limit of the workpiece was approx. 200 MPa at 1150 ° C.
  • the workpiece had a Vickers hardness HV of an average of 336 kg / mm2.
  • the forging process was carried out essentially isothermally at a temperature of 1120 ° C., a flow limit of 250 MPa being observed on average.
  • the rate of deformation (punch speed) at the start of each forging operation was approximately 0.1 to 0.2 mm / s.
  • the base part was compressed by a further 20% decrease in height in the longitudinal axis of the airfoil.
  • the workpiece was then cooled to below 500 ° C. at a rate of 300 ° C./h and, after cooling, tempered for 1 hour at a temperature of 800 ° C. With this, the almost final shape of the turbine blade was achieved, apart from milling the grooves on the fir tree base.
  • the cast blank was annealed at 1050 ° C, overturned (removal of the cast skin) and encapsulated in an all-round sleeve made of soft steel and hot isostatically pressed according to the previous examples. Then the block was first compressed in the longitudinal direction with a 30% decrease in height at 1150 ° C. and pressed several times in the transverse directions in such a way that an oval cross section was produced in the leaf section. Intermediate annealing was carried out at 1200 ° C. The pre-forged blank with an oval cross-section in the sheet section was placed in the die of a forging press and deformed in several stages until the above sheet profile was reached. The forging process was carried out essentially isothermally at a temperature of 1150 ° C.
  • a flow limit of 200 MPa on average was observed at this temperature.
  • the deformation speed (punch speed) at the beginning of the drop forging operations was approx. 0.2 mm / s.
  • the remaining process steps were analogous to Example 4.
  • the tempering was carried out at a temperature of 750 ° C. for 2 hours.
  • the structure of the finished turbine blade was fine-grained and homogeneous.
  • the Vickers hardness HV was 15% higher than the as-cast state.
  • B generally has a strong toughness-increasing effect in combination with other strength-increasing elements.
  • the loss of ductility caused by alloying W could be practically compensated for by adding only 0.5 at.% B. Additions higher than 1 at.% B are not necessary.
  • polynary systems in which an attempt is made to make up for the negative properties of individual additions by simultaneously alloying other elements.
  • the area of application of the modified titanium aluminides advantageously extends to temperatures between 600 and 1000 ° C.
  • the invention is not restricted to the exemplary embodiments.
  • the workpiece is forged essentially isothermally, and after the isothermal forging it has the shape of a gas turbine blade.
  • the workpiece is essentially forged isothermally and, after the isothermal forging, is subjected to a further hot-forming process with up to 40% reduction in cross-section, the latter advantageously consisting of hot rolling.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Forging (AREA)
  • Press Drives And Press Lines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

  1. Procédé de production d'une pièce à partir d'un alliage contenant un dopant et à base d'aluminure de titane, consistant à réaliser les étapes suivantes:
    - Fusion de l'alliage,
    - Coulage de la masse fondue pour produire un moulage,
    - Refroidissement du moulage à la température ambiante et élimination de sa croûte de moulage et de sa couche de scorie,
    - Compression isostatique à haute température du moulage débarrassé de sa scorie, à une température comprise entre 1 200 et 1 300°C et sous une pression comprise entre 100 et 150 MPa,
    - Refroidissement du moulage compressé de façon isostatique à haute température,
    - Chauffage du moulage refroidi à des températures de 1 050 à 1 200°C,
    - Déformation une ou plusieurs fois à cette température, dans le but d'améliorer le moulage et la structure,
    - Refroidissement du moulage déformé à la température ambiante, et
    - Usinage du moulage déformé pour produire la pièce en éliminant de la matière.
  2. Procédé selon la revendication 1, caractérisé en ce qu'un alliage de TiAl dopé avec l'un au moins des éléments Zr, V, Cr, Si, Y, W, B ou Ge, est soumis aux étapes opératoires supplémentaires suivantes;
    - Faire fondre l'alliage sous vide ou sous une atmosphère de gaz protecteur, dans un four à induction,
    - Effectuer un recuit, sous une atmosphère de gaz protecteur ou sous vide, à une température comprise entre 1 000 et 1 150°C,
    - Insérer le moulage, après avoir éliminé la croûte de moulage et la couche de scorie, dans une capsule en acier doux et sceller hermétiquement la capsule d'acier remplie,
    - Soumettre la capsule d'acier scellée renfermant la moulage à une compression isostatique à haute température,
    - Chauffer à 10-50°C/min jusqu'à 1 050 à 1 150°C,
    - Maintenir cette température pendant 5 à 20 min.
  3. Procédé selon la revendication 1 ou 2, dans lequel la déformation à haute température est réalisée de la façon suivante;
    - Déformation isothermique de l'ensemble dans une gamme de températures comprises entre 1 050 et 1 150°C, à une vitesse de déformation de ε = 5.10⁻⁵s⁻¹
    Figure imgb0010
     à 10⁻²s⁻¹, jusqu'à l'obtention d'une déformation ε = 1,6, où
    Figure imgb0011
     ho = hauteur initiale de la pièce,
    h = hauteur de la pièce après déformation.
  4. Procédé selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la déformation à haute température est réalisée de la manière suivante:
    - Refoulement dans la direction longitudinale à raison de 50% de diminution de hauteur,
    - Refoulement dans une première direction transversale à raison de 30% de diminution de section droite,
    - Refoulement dans une seconde direction transversale à raison de 30% de diminution de section droite,
    - Refoulement dans la direction longitudinale à raison de 20% de diminution de hauteur,
    - Refroidissement à 300°C/h jusqu'à moins de 500°C,
    - Revenu à 800°C pendant 1 h,
    - Refroidissement à la température ambiante.
  5. Procédé selon l'une quelconque des revendications 1 à 4, caractérisé en ce que la pièce est forgée de façon essentiellement isothermique et possède la forme d'une aube de turbine à gaz après le forgeage isothermique.
  6. Procédé selon l'une quelconque des revendications 1 à 5, caractérisé en ce que la pièce est forgée de façon essentiellement isothermique et est, après le forgeage isothermique, soumise à un procédé supplémentaire de déformation à haute température, avec jusqu'à 40% de réduction de la section droite.
  7. Procédé selon la revendication 6, caractérisé en ce que le procédé de déformation à haute température comprend un laminage à chaud.
  8. Procédé selon l'une quelconque des revendications 1 à 7, caractérisé en ce que l'alliage possède l'une des compositions ci-dessous:
       Al = 48% en atomes
       Zr = 3% en atomes
       B = 0,5% en atomes
       Ti = 48,5% en atomes
    ou
       Al = 48% en atomes
       Y = 3% en atomes
       Si = 0,5% en atomes
       Ti = 48,5% en atomes
    ou
       Al = 48% en atomes
       Cr = 3% en atomes
       Ti = 49% en atomes
    ou
       Al = 48% en atomes
       Y = 3% en atomes
       B = 0,5% en atomes
       Ti = 48,5% en atomes
    ou
       Al = 48% en atomes
       Ge = 3% en atomes
       Ti = 49% en atomes
    ou
       Al = 48% en atomes
       W = 3% en atomes
       Ge = 0,5% en atomes
       Ti = 48,5% en atomes
EP91108605A 1990-07-04 1991-05-27 Procédé de fabrication d'une pièce en alliage à base d'aluminiure de titane contenant un matériau de dopage Expired - Lifetime EP0464366B1 (fr)

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EP90112734 1990-07-04
EP90112734 1990-07-04

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EP0464366B1 true EP0464366B1 (fr) 1994-11-30

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US (1) US5190603A (fr)
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JP (1) JPH04232234A (fr)
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EP0464366A1 (fr) 1992-01-08
JPH04232234A (ja) 1992-08-20
DE59103639D1 (de) 1995-01-12
US5190603A (en) 1993-03-02

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