EP3144402A1 - Procédé de fabrication d'un préforme en alliage de aluminiure de titane pour la fabrication d'un composant ayant une capacité de charge elevée pour utilisation dans les moteurs à pistons ou les turbines, notamment des turbines d'avion. - Google Patents

Procédé de fabrication d'un préforme en alliage de aluminiure de titane pour la fabrication d'un composant ayant une capacité de charge elevée pour utilisation dans les moteurs à pistons ou les turbines, notamment des turbines d'avion. Download PDF

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Publication number
EP3144402A1
EP3144402A1 EP16185613.3A EP16185613A EP3144402A1 EP 3144402 A1 EP3144402 A1 EP 3144402A1 EP 16185613 A EP16185613 A EP 16185613A EP 3144402 A1 EP3144402 A1 EP 3144402A1
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EP
European Patent Office
Prior art keywords
forging
blank
stretch
stretching
alloy
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP16185613.3A
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German (de)
English (en)
Inventor
Peter Janschek
Tobias Naumann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Leistritz Turbinentechnik GmbH
Original Assignee
Leistritz Turbinentechnik GmbH
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Filing date
Publication date
Application filed by Leistritz Turbinentechnik GmbH filed Critical Leistritz Turbinentechnik GmbH
Publication of EP3144402A1 publication Critical patent/EP3144402A1/fr
Withdrawn legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • 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
    • 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
    • B21J5/022—Open die forging
    • 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
    • B21J7/00—Hammers; Forging machines with hammers or die jaws acting by impact
    • B21J7/02—Special design or construction
    • B21J7/14—Forging machines working with several hammers
    • 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
    • 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
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • 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
    • C22F1/02—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working in inert or controlled atmosphere or vacuum
    • 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
    • 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
    • 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
    • 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
    • F05D2230/20—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

Definitions

  • the invention relates to a method for producing a preform from an ⁇ + ⁇ -titanium aluminide alloy for producing a heavy-duty component for reciprocating engines and gas turbines, in particular aircraft engines, by forging a blank.
  • TiAl-based alloys belong to the group of intermetallic materials which have been developed for applications in the field of application temperatures of superalloys. Due to its low density of about 4g / cm 3 , this material offers a significant potential for weight savings and to reduce the burden of moving components, such.
  • State of the art is the investment casting of z. B. turbine blades for aircraft engines. For applications with higher load such.
  • the properties of the cast structure are no longer sufficient.
  • thermomechanical treatment by means of plastic forming with a defined degree of deformation and subsequent heat treatment, the static and dynamic properties of TiAl alloys can be increased to the required values.
  • TiAl alloys are not conventionally forgeable because of their high resistance to deformation. Therefore, high temperature forming processes in the region of the ⁇ + ⁇ or ⁇ -phase region must be performed in a protective atmosphere using molybdenum-made tools at very low forming speeds. To achieve the desired final geometry of the forging usually several consecutive forging steps are required.
  • Such a method for producing high-strength components made of ⁇ + ⁇ -TiAl alloys is, for example DE 101 50 674 B4 known.
  • the components, in particular for aircraft engines or stationary gas turbines, are produced here in a two-stage process.
  • a preform is produced from a blank consisting of ⁇ + ⁇ -TiAl alloy.
  • an encapsulated TiAl blank globular structure by isothermal deformation in the ⁇ + ⁇ phase region in the temperature range of 1000 - 1340 ° C or in the ⁇ -phase region in the temperature range of 1340 - 1360 ° C deformed by forging or extrusion.
  • a second, also isothermal secondary forming process with simultaneous dynamic recrystallization in the ⁇ + y or ⁇ -phase region in a temperature range of 1000-1340 ° C the component is formed to the given shape by forging, after which the component for adjusting the microstructure in the ⁇ -phase region solution annealed and then cooled quickly.
  • this method provides the isothermal pre-forging for producing the preform and the isothermal finish forging in the second process step.
  • the formation of a preform is in the components described therein, which have over the longitudinal direction of greatly different cross sections, such. As turbine blades or connecting rods, in view of the required volume distribution required.
  • the invention is therefore based on the problem to provide a method for producing a preform, which is improved in contrast.
  • the invention provides to produce the preform by stretch forging a blank.
  • stretch forging the desired shape is incrementally produced by using multiple tools through multiple action on the workpiece. This forming takes place partially, that means that the blank is only processed locally by means of the stretching forging tool. During this multiple forging operation, a portion of the blank material having the largest cross-sectional area to be found in the later finished part is partially reduced to the cross-sectional area to be found in the finished part at the corresponding location.
  • the forming takes place in such a way that a driven tool, a so-called saddle, exerts a plurality of strokes with a defined path perpendicular to the longitudinal axis of the starting material, wherein the blank is moved by means of the program-controlled manipulator between two strokes by a defined path in the longitudinal direction of the workpiece ,
  • the workpiece is moved by means of the manipulator at least once in one direction by the stretch forging tool and processed here with a corresponding number of strokes. If necessary, a return movement or a repeated repetition of these cycles with a corresponding number of strokes, possibly also with different stroke size done.
  • the stretch forging has a number of advantages compared to the above-mentioned, previously performed way of preforming.
  • a significantly smaller stretching forge can be used compared to the forging presses to be used for the isothermal forming. Because forging forging requires far less force per forging operation, ie per stroke, due to the smaller volume to be reshaped. Therefore, a stretch forge with a forging force of eg 10 t is completely sufficient, to make the transformation.
  • a forging forge with a forging force of about 10 tons is much smaller and simpler.
  • the forging process can also be carried out with particular advantage in air; it does not have to be carried out under protective gas. Because in principle it is possible to use a stretch forging tool, e.g. to use a ceramic material, preferably made of a fiber-reinforced ceramic material, resulting from the significantly lower forging force.
  • the stretch forging itself is preferably carried out in the ⁇ -phase region.
  • the blank is held at a temperature in the range of 1070 - 1300 ° C during stretching forging.
  • a stretch forging tool made of a preferably fiber-reinforced, ceramic material is used, which can be used without difficulty in air.
  • a forging tool made of molybdenum in which case, however, forging must take place under a protective gas atmosphere.
  • the blank and the stretch forging tool itself are preferably heated by means of a radiant heater during stretching forging, wherein preferably an infrared radiator is used.
  • the blank can also be heated by means of electrical current flowing through it. This can be done a targeted temperature during the forging process.
  • the blank is heated before being introduced into the stretch forging tool by means of a radiant heater, inductive heating or by means of electrical current flowing over the blank. Accordingly, so the blank forging is already pre-heated already.
  • the manipulator located immediately adjacent to the stretch forging a corresponding heating device, in which the manipulator moves the blank where it is heated. When it reaches its forging temperature, the blank is fed via the manipulator to the forging shop and moved between the stretching forging tool for forging.
  • the blank is preferably processed by stretch forging in such a way that the elongation is greater than the width.
  • the blank is only partially reshaped.
  • the blank forged between the saddles is reshaped during each stroke.
  • the ratio of the length of the tool or of the calipers in the longitudinal direction of the blank, the so-called “saddle width", to the current width of the blank determines whether the preferred forming is more in the length (elongation) or rather in the width (width) of the blank.
  • a relatively short, for example, cylindrical blank is used which, on the one hand, is widened slightly by stretching for example in the central region until the minimum width that the blade is to have in its final shape is at least approximately reached.
  • the blank undergoes an elongation, so that the stretch-forged shaped section corresponds to the length of the airfoil.
  • the material is correspondingly reshaped, that is displaced, so that the corresponding widths and elongations can be achieved without further ado.
  • the elongation achieved by stretching forging should be between 50-100%, it should be at least 70%.
  • the blank is processed according to an embodiment of the invention only in a central region by stretch forging, so that a first free end portion and a second, held in the manipulator end portion of different geometry or other diameter than the reckgeschmiedete area remain.
  • These two end sections from which the cover strip and the foot are forged on the finished part, are formed into the final shape only after the stretching forging, ie in the second finish forging process. It is conceivable, however, during the stretching forging process, to transform the first free end section, which is not accommodated in the manipulator, to a lesser extent than the central area, ie, for example, to flatten it or the like.
  • the blank is moved by means of the manipulator in such a way by the stretch forging tool that the tool saddles a forged in a previous stroke section z. B. overmolded in half.
  • This means that the blank is moved by the manipulator after each stroke by half the saddle width, so that in the next stroke half of the previously forged area is forged a second time.
  • bite offset the degree of deformation can be adjusted over the cross section of the component and achieve a uniform distribution of the same.
  • the blank can also be rotated about its longitudinal axis by means of the manipulator in order to produce a round cross-section or to introduce a torsion, and the like.
  • ⁇ -phase stabilizing elements are Mo, V or Ta or a mixture thereof.
  • the content of the ⁇ -phase stabilizing element should be 0.1-2%, especially 0.8-1.2%. This in particular when Mo, V and / or Ta are used, since they have a particularly high stabilizing property and therefore their content can be kept relatively low.
  • the invention relates to a preform produced by the method described.
  • the invention relates to a method for producing a high-strength component from an ⁇ + ⁇ -titanium aluminide alloy for reciprocating engines and gas turbines, in particular aircraft engines, which is characterized in that a by the method of the type described above produced preform in a single stage Forming step is formed into a predetermined contour, wherein the preform in the ⁇ -phase region is formed isothermally with a logarithmic deformation rate of 0.01 - 0.5 1 / s.
  • the preform previously prepared according to the invention is formed in a slow, isothermal forming process with a very low forming speed.
  • the forming also takes place at the appropriate temperature in the ⁇ -phase range.
  • the twelve slip planes existing in the cubic-body-centered ⁇ -phase are activated and dynamic recrystallization initiated. By constantly further supplied forming energy, this is maintained over the entire Umformweg. This results in a fine-grained microstructure at lower yield stress. Since the preform has already been forged relatively close to the final contour by the stretch forging, this second forging process can take place sufficiently rapidly despite the low forming speed of 10 -3 s -1 to 10 -1 s -1 .
  • the forming temperature in the ⁇ -phase range is preferably 1070-1250 ° C.
  • a tool made of a highly heat-resistant material is used, preferably of a Mo alloy, wherein the tools are protected in this case during the forming process by an inert atmosphere, so it is working under inert gas.
  • the oxidation can be avoided by working in a vacuum.
  • the preform is expediently heated before the forming, which can be done in an oven, inductive or by resistance heating.
  • a heat treatment of the formed component is expediently carried out in order to set the required service properties and for this purpose to convert the favorable for the transformation ⁇ -phase by a suitable heat treatment in a fine-lamellar ⁇ + ⁇ -structure.
  • the heat treatment may comprise a recrystallization annealing at a temperature of 1230-1270 ° C.
  • the holding time during the recrystallization annealing is preferably 50-100 min.
  • the Rekristallisaitonsglühung takes place in the range of ⁇ - ⁇ -transformation temperature.
  • the component is cooled to a temperature of 900-950 ° C. in 120 s or faster, smaller ⁇ -phase spacings of the ⁇ + ⁇ phase are formed.
  • a second heat treatment step follows, in which the component is first cooled to room temperature and then heated to a stabilizing or relaxation temperature of 850-950 °.
  • the stabilization and relaxation temperature of 850-950 ° C. can also be directly deduced from the temperature of 900 ° -950 ° C. (as described above) obtained after the recrystallization annealing.
  • the preferred holding time at the stabilizing and relaxing temperature, independently of how it was achieved, is preferably 300-360 min.
  • the component temperature is preferably reduced to a temperature below 300 ° C. with a defined cooling rate.
  • the cooling rate is preferably 0.5-2 K / min, that is, the cooling is relatively slow, which serves to stabilize and relax the structure.
  • the cooling rate is preferably 1.5 K / min.
  • the respective cooling can be carried out in a liquid, for. B. in oil, or in air or an inert gas.
  • the invention further relates to a component of an ⁇ + ⁇ -titanium aluminide alloy, in particular for a piston engine, an aircraft engine or a gas turbine, which in a Method of the type described is made.
  • a component may for example be a blade or a disk of a gas turbine or the like.
  • Fig. 1 shows a flowchart for explaining the method according to the invention for preform and for the production of finished parts. Shown is a blank 1 in a cylindrical shape. This consists of an ⁇ + ⁇ -titanium aluminide alloy of a composition as indicated above.
  • the TiAl alloy contains a ⁇ -phase stabilizing element, preferably Mo, V or Ta, since the subsequent forming operations take place in the ⁇ -phase region of the TiAl alloy.
  • the blank 1 is fixed, see step a), in a program-controlled manipulator 2 or robot.
  • step a) it is first fed to a first heating device 3, which may be an infrared radiant heater, an oven or an electric heating device.
  • a heating device 3 In this heating device 3, the blank 1 is heated to a temperature in the range of 1070-1330 ° C, thus, therefore, a temperature in which a ⁇ -phase is formed in the alloy structure.
  • the blank 1 is moved by means of the manipulator 2 in an adjacent to the heater 3 stretching forge 4.
  • This stretching forge 4 has a forging tool 5 comprising a movable forging saddle 6 and a fixed forging saddle 7.
  • the forging saddles 6, 7 are preferably made of a ceramic, in particular fiber-reinforced, material, so that a stretch forging in air is possible.
  • the stretching forge 4 is designed, for example, for a forging force of 10 t.
  • the stretching forge 4 is associated with a heating device 8, preferably an infrared radiator, by means of which it is possible to heat the blank 1 located between the forging saddles 6, 7 as well as the forged saddles 6, 7 even during the forging process, so that in particular the blank on the corresponding forging temperature is maintained.
  • a heating device 8 preferably an infrared radiator
  • the blank 1 is moved through the forging tool 5 in intermittent steps, as indicated by the horizontal double arrow.
  • the forging saddle 6 is raised in individual strokes and lowered forging on the blank 1, the blank is formed between the forging saddles 6, 7.
  • the displacement takes place, for example, by half the width of the same width forging saddles 6, 7, so that with each stroke of the blank 1 in the half, previously forged area is overmolded again.
  • the blank 1 is moved at least once in one direction by the stretching forge 4. If necessary, it is moved in the opposite direction to carry out another forging cycle. During this movement, the blank 1 may also, if necessary, be rotated about its longitudinal axis to forge a twist or curves, etc.
  • the forging saddles 6, 7 used can have a flat forging surface or a three-dimensionally shaped forging surface, for example concave forged surfaces or three-dimensionally twisted forged surfaces, in order to forge targeted geometries.
  • Step c) shows an example of the situation during the forging process.
  • the blank 1 is received between the two forging saddles 6, 7, wherein the forging saddles are closed by way of example.
  • the blank 1 is only partially reshaped, that is to say that a first free end section 9 and a second second end section 10 held in the manipulator 2 or the manipulator tong remain, between which the forged area 11 extends.
  • These end portions 9, 10 serve to form the shroud and the foot of a blade to be produced later, which will be discussed below.
  • the finished forged blank ie the forged preform 12
  • the finished forged blank is shown enlarged by way of example. Shown are the two end portions 9, 10 and the flat-forged central region 11, from which the blade region is formed in the subsequent second forming step. Due to the multiple forging, this area 11 has already been changed in terms of its mechanical properties due to the forming process. It has a very fine microstructure and any pores are necessarily closed. This is expedient for the mechanical properties and also the forming process for the production of the finished component.
  • This preform 12 is then further processed to produce a finished component 13 in the form of a turbine blade in a second isothermal forming step.
  • step d where the preform 12, which may have previously been heated again to the forging temperature in a heater (not shown), is introduced into a shaping second forge 19 with an upper part 14 and a lower part 15.
  • an isothermal forging process takes place in which the upper and lower parts 14, 15 are heated.
  • the forging temperature is also between 1070 - 1250 °, the transformation takes place in the ⁇ phase range.
  • the forming takes place here isothermally with a very slow forming speed, the logarithmic forming speed is in the range of 0.01 - 0.5 1 / s. So there is almost a extrusion.
  • the tools or moldings 14, 15 used here are made of a Mo alloy, which is why the forming takes place in a protective gas atmosphere.
  • the forming tools are actively heated, preferably inductive.
  • the finished component is shown in step e), this being a pure schematic representation.
  • the component 13 is a turbine blade with a shroud 16 and a foot 17, as is well known.
  • the middle region 18, that is to say the actual blade region, is correspondingly arched or twisted in a manner known per se.
  • the secondary forming operation shown in step d) is followed by a heat treatment of the formed component 13, for example a recrystallization annealing at a temperature of 1230-1270 °, with a holding time between 50-100 minutes, after which the component is at a temperature in the range of 900 - 950 ° is cooled relatively quickly.
  • a stabilization and relaxation annealing at a temperature in the range of 850-950 °, to which the component can either be reheated, or the previous cooling takes place already on this temperature range.
  • the holding time here is about 300 to 360 minutes, after which the component is finally cooled to a temperature below 300 ° C with a cooling rate in the range of 0.5 to 2 K / min.
  • Fig. 2 shows in an enlarged schematic representation of the blank, the preform and the finished forged component.
  • the figure part a) of the cylindrical blank is shown directly after introduction into the stretch forging, the two forged saddles begin the forming work.
  • the figure part c) shows the finished stretch forged preform 12 with the end portions 9, 10 and the deformed portion 11. It is apparent that the preform is significantly longer than the blank in the initial state.
  • This preform is then forged in the second forge 19 near net shape isothermally by extrusion. It shows the forged from the area 11 turbine blade 18 with the blade and the shroud 16 and the foot 17, both of which were forged from the end portions 9, 10. Only at the edge are ridges to be separated.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (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)
EP16185613.3A 2015-09-17 2016-08-25 Procédé de fabrication d'un préforme en alliage de aluminiure de titane pour la fabrication d'un composant ayant une capacité de charge elevée pour utilisation dans les moteurs à pistons ou les turbines, notamment des turbines d'avion. Withdrawn EP3144402A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015115683.0A DE102015115683A1 (de) 2015-09-17 2015-09-17 Verfahren zur Herstellung einer Vorform aus einer Alpha+Gamma-Titanaluminid-Legierung zur Herstellung eines hochbelastbaren Bauteils für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke

Publications (1)

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EP3144402A1 true EP3144402A1 (fr) 2017-03-22

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EP16185613.3A Withdrawn EP3144402A1 (fr) 2015-09-17 2016-08-25 Procédé de fabrication d'un préforme en alliage de aluminiure de titane pour la fabrication d'un composant ayant une capacité de charge elevée pour utilisation dans les moteurs à pistons ou les turbines, notamment des turbines d'avion.

Country Status (4)

Country Link
US (1) US20170081751A1 (fr)
EP (1) EP3144402A1 (fr)
JP (1) JP2017094392A (fr)
DE (1) DE102015115683A1 (fr)

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CN111690888A (zh) * 2020-05-28 2020-09-22 河南新开源石化管道有限公司 一种钛合金原料推压挤料装置
CN112899526A (zh) * 2021-01-19 2021-06-04 中国航空制造技术研究院 航空发动机风扇叶片用的α+β型两相钛合金及制备方法
CN113172190A (zh) * 2021-04-15 2021-07-27 沈阳和世泰通用钛业有限公司 锻件成型方法
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CN111690888A (zh) * 2020-05-28 2020-09-22 河南新开源石化管道有限公司 一种钛合金原料推压挤料装置
CN112899526A (zh) * 2021-01-19 2021-06-04 中国航空制造技术研究院 航空发动机风扇叶片用的α+β型两相钛合金及制备方法
CN112899526B (zh) * 2021-01-19 2022-04-29 中国航空制造技术研究院 航空发动机风扇叶片用的α+β型两相钛合金及制备方法
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CN114226613A (zh) * 2021-12-06 2022-03-25 陕西宏远航空锻造有限责任公司 一种7型AerMet100超高强度钢锻件的锻造方法
CN114226613B (zh) * 2021-12-06 2024-05-24 陕西宏远航空锻造有限责任公司 一种“7”型AerMet100超高强度钢锻件的锻造方法
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