EP3077557A1 - Procédé de fabrication de pièces en tial - Google Patents

Procédé de fabrication de pièces en tial

Info

Publication number
EP3077557A1
EP3077557A1 EP14828000.1A EP14828000A EP3077557A1 EP 3077557 A1 EP3077557 A1 EP 3077557A1 EP 14828000 A EP14828000 A EP 14828000A EP 3077557 A1 EP3077557 A1 EP 3077557A1
Authority
EP
European Patent Office
Prior art keywords
forging
component
phase
temperature
feedstock
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.)
Granted
Application number
EP14828000.1A
Other languages
German (de)
English (en)
Other versions
EP3077557B1 (fr
Inventor
Robert Patrick HEMPEL
Patrick Voigt
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.)
Hanseatische Waren Handelsgesellschaft Mbh & Co KG
Original Assignee
Hanseatische Waren Handelsgesellschaft Mbh & Co KG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hanseatische Waren Handelsgesellschaft Mbh & Co KG filed Critical Hanseatische Waren Handelsgesellschaft Mbh & Co KG
Publication of EP3077557A1 publication Critical patent/EP3077557A1/fr
Application granted granted Critical
Publication of EP3077557B1 publication Critical patent/EP3077557B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • 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
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing

Definitions

  • the invention relates to a method for producing a component from a titanium-aluminum base alloy, which can be used as a component for turbocharger units of internal combustion engines.
  • exhaust gas turbochargers Through the use of exhaust gas turbochargers internal combustion engines can be made smaller while maintaining power.
  • an exhaust gas turbocharger formed from a turbine and a compressor the turbine runner is set in rotation with the energy of the exhaust gas flow.
  • a shaft transmits the torque to the compressor wheel, which compresses the air flowing into the combustion chamber and introduces into the engine.
  • the fuel in the engine is almost completely burned and harmful emissions are reduced.
  • the exhaust gases of a diesel engine reach temperatures up to about 850 ° C, while the exhaust gases of gasoline engines even temperatures of about 1050 ° C have.
  • the high temperatures of the exhaust gases lead to a large thermal load of the arranged in the exhaust stream components.
  • titanium-titanium intermetallic alloys also referred to as TiAl alloys or titanium aluminides, based on the ⁇ -TiAl phase with a low density and a high specific strength at high temperature.
  • Titanium aluminides are known from the state of the art as multiphase TiAl alloys whose complex structure consists of ⁇ -TiAl, ⁇ 2- ⁇ 3 ⁇ and a small proportion of ⁇ -TiAl phase. Through a specific combination of heat treatment and hot working, the mechanical properties of the alloys are optimized, which is mainly due to the smaller lamellar distance within the ⁇ 2 / ⁇ - ⁇ .
  • EP 2 386 663 A1 discloses a thermally tempered component and a method for producing the component from a TiAl-based alloy.
  • a thermally tempered component in order to achieve homogeneous mechanical properties, in particular a high ductility and creep resistance with high strength and high temperature of a material, in a first process step, the starting material is hot isostatically pressed.
  • the blank is subjected to rapid solid forming.
  • a fine grain formation takes place with the phases ⁇ , ⁇ , ci2 by annealing in the region of the eutectoid temperature of the alloy.
  • the component is subsequently annealed and / or stabilization annealed to adjust the microstructure and the mechanical material properties in a final step with dimensions close to the final dimensions.
  • the necessary step of hot isostatic pressing also referred to as HIP, serves to reduce or remove internal porosities.
  • the hot isostatic pressing, the annealing for fine grain formation and the subsequent annealing or the stabilizing annealing cause a great deal of time and are associated with increased costs.
  • DE 10 2007 051 499 A1 discloses a titanium-aluminum-base alloy material for a gas turbine component, a method for producing the gas turbine component and a gas turbine component.
  • the material has the phases ⁇ / B2-Ti, ⁇ 2- ⁇ 3 ⁇ and ⁇ -im in the range of room temperature with a proportion of ß / B2-Ti phase of not more than 5 vol .-% and in the eutectoid temperature the phases ß / B2-Ti, ⁇ 2 - ⁇ 3 ⁇ and ⁇ -TiAI with a proportion of ß / B2-Ti phase of at least 10 vol .-% on.
  • the method for producing the gas turbine component comprises the following steps: providing a semifinished product of an aforementioned material and forging or massive forming of the semifinished product at a forming temperature in the range between the reduced by 50 K eutectoid temperature and plus 100 K to the alpha transus temperature of the material.
  • the object of the present invention is to provide a method, which is improved over the prior art, for producing components from a TiAl-based alloy.
  • the component produced by the method should be made of a material having homogeneous mechanical properties, in particular a high creep resistance at high strength, especially in high-temperature applications.
  • the method should be less costly and less time consuming than the methods known in the art, the component with dimensions close to the final dimensions should be economically manufacturable.
  • the object is achieved by an inventive method for producing a component made of a titanium-aluminum base alloy, in particular as components for turbocharger units of internal combustion engines.
  • the method comprises the following steps: heating of cast feed material within the (a + ⁇ )
  • the feed is forged as a semi-finished as cast, with the feed material removed directly from the casting and processed in the forging process. Since no further processing steps or method steps, such as a heat treatment, are required between the cast state of the semifinished product and the process of heating, the process chain of the production of the component is greatly shortened in comparison to the prior art.
  • the rate of change of shape results from the change in the dimensions of the component per unit of time, that is from the ratio of the dimension of the component after each forming operation to the dimension of the component before the forming process per unit time or as average strain rate from the dimension of the forging blank after forging in proportion to measure the component before forging per time.
  • the speed of the forming tool corresponds to the tool speed, which is determined by the forming machine.
  • excess material is forced out of the forging. Subsequently, the burr formed from the excess material is removed, for example by punching. The component is deburred.
  • the flashless forging according to the invention saves in comparison to methods from the prior art, on the one hand, further process steps of the post-processing or the finishing of the forging blanks up to the end product.
  • components made of TiAl materials have strong embrittlement in the transition zone, which continue partially and uncontrollably in the forging.
  • the flashless training of forging blanket thus prevents the other hand, the disadvantage of the emergence of strong embrittlement.
  • the microstructure of the material of the component with the mechanical material properties is already set such that advantageously no further process step to change the microstructure is necessary.
  • uniform cooling is a process step or process to understand in which the forging blank after the process of forging without draft evenly cooled in the atmosphere.
  • the forging blank is exposed only to the air of the atmosphere, instead of being placed in a heated oven or the like.
  • compressed air can also be used for cooling.
  • the forged blank after cooling to room temperature by machining or by other methods, such as chemical removal processes, brought into its final form. It is advantageous that additional process steps between the cooling and the removal of the forging blank can be omitted in its final form.
  • the end product is preferably formed as a rotationally symmetrical component, wherein the ratio of height to largest outer diameter is advantageously in the range of 0.8 to 1, 1.
  • the height of the component preferably has values in the range of 50 mm to 55 mm.
  • the feedstock was cast, isostatically hot pressed and pre-formed.
  • the feed is thus in a cast, isostatically hot pressed and pre-formed state before being fed to the heating step.
  • the feed material powder metallurgy which after sintering is preferably present in rod form and subdivided for further processing in predetermined section lengths and thus shortened.
  • the feedstock advantageously has the following chemical composition in% by weight:
  • Tantalum (Ta) to 10.00
  • Manganese (Mn) up to 2.00
  • the process of forging takes place at a temperature between 1100 ° C and 1400 ° C, wherein the range of temperature between 1260 ° C and 1360 ° C is particularly preferred.
  • the heated feedstock is preferably shaped by means of drop forging to the forging blank.
  • the process of drop forging is advantageously carried out in one stage in a suitably executed die. This process can be done alternatively, but also in several stages.
  • the die has a temperature in the range of 140 ° C to 250 ° C.
  • the die is therefore only moderate heated, wherein the temperature of the die is significantly lower than the temperature usual in Isothermschmieden or hot die forging.
  • the tool or die is heated approximately to the temperature of the forging blank, so that at forging temperatures of about 1,300 ° C and the die has a temperature of about 1,300 ° C.
  • the high temperatures of the tools require the use of high-melting materials for the tools, which makes the process extremely uneconomical.
  • the heated feedstock during the process of drop forging with a force in the range of 140 t to 1,000 t is transformed.
  • the applied force is dependent on the forging geometry.
  • the advantageous embodiment of the invention enables the use of the component produced by the method according to the invention as a component for turbocharger units of internal combustion engines, wherein the component is rotationally symmetrical and has a ratio of height to largest outer diameter of 0.8 to 1, 1.
  • the desired mechanical material properties are set, so that no further heat treatment of the forging blank or of the finished component is more necessary, which leads to a significant saving of energy to be expended compared to methods of the prior art,
  • 1 is a graph of microstructure of titanium-aluminum base alloys depending on the temperature and the aluminum concentration
  • FIG. 2a shows a microstructure of a TiAI component after the forging process with a low rate of change of shape
  • FIG. 2b shows a microstructure of a merely cast and isostatically hot pressed TiAl component
  • FIG. 2c shows a microstructure of a TiAI component after the forging process with a high rate of deformation change
  • 4a, 4b embodiments of a forging component.
  • Fig. 1 is a diagram of a structural formation of titanium-aluminum base alloys depending on the temperature and the aluminum concentration is shown.
  • the feedstock is subjected to forming in the direct casting state.
  • the feedstock can be cast as a rod, which can be turned off after the desired external dimensions. After being cut to a predetermined length, the feed is reformed at a strain rate> 19 l / s.
  • the forging blank is further processed by forging process with a strain rate> 19 1 / s without additional process steps, such as heat treatments, by cutting or chemical processes to the final product.
  • the feed material also referred to as raw material or preform
  • it is preheated in the (a + ⁇ ) -phase field according to FIG.
  • the temperature is adjusted to achieve at least 5% vol. By volume of the beta phase in order to avoid uncontrolled grain coarsening during the preheat time.
  • the feedstock is heated to a temperature> 1.320 ° C.
  • an oxide-based protective layer which is conventionally used to protect the base material from being oxidized during the heating phase, or the like, is omitted since, on the one hand, a protective layer thus formed thermally insulates the base material during the cooling phase, so that the base body can be compared to Training without the protective layer cools much slower.
  • the oxide layer grows only very little by the time-very short process with few steps in comparison to known from the prior art method with about 800 pm and is negligible.
  • the heated to a temperature of about 1 .260 ° C to 1360 ° C feedstock, for example, by impact forming by drop forging is formed.
  • the rate of deformation is in the range of 19 1 / s to 50 1 / s.
  • the process step of drop forging takes place in a suitably executed die, which has a temperature in the range of 140 ° C to 250 ° C.
  • the process of forging takes place in one or more stages.
  • the forging geometry dependent forging force for forming is in the range of 140 1 to 1 000 t.
  • the forging blank is removed from the die and cooled uniformly and controlled in ambient air.
  • the cooling of the forging blank takes place according to FIG. 1 with a constant composition of the material and passes through different phases.
  • the forging blank After the forging blank has cooled to room temperature, it has a structure which is formed of lamellar a2 / y colonies at whose colony boundaries ⁇ -phase is present.
  • the proportion of ß-phase is well below 15 vol .-%.
  • FIGS. 2a and 2c show comparative microstructures of a TiAl component after the forging process.
  • FIG. 2 a shows the structure of a component forged at a low rate of deformation
  • FIG. 2 c discloses the structure of a component forged at a high rate of deformation.
  • the microstructure of Fig. 2a shows a low to no formed texture.
  • the microstructure from FIG. 2 c has a distinct texture.
  • the Occurrence of grain refining processes is not significant. Also, only an insignificantly small amount of globular ⁇ -phase occurs along the o / y colony boundaries.
  • the proportion of ⁇ -phase in the o ⁇ / y colonies as well as in the ⁇ -phase surrounding the colonies and the lamellar spacing in the ⁇ 2 / ⁇ - ⁇ are close to the thermodynamic equilibrium.
  • the microstructure is thermally stable in the component insert.
  • the proportion of globular ⁇ grains at the colony boundaries is not significant with 0 to a maximum of 3% by volume and thus has no negative influence on the creep resistance in high-temperature use.
  • the mechanical properties of the TiAl component produced by the process are determined by the expression and the lamellar spacing of the 02/7 colonies of less than 1 pm and the proportion of beta phase.
  • the value of the creep resistance of the forging blank is, for example, above the value of a cast / HIP starting material.
  • FIG. 2b shows the microstructure of a merely cast and isostatically hot pressed TiAl component.
  • FIG. 3 shows the influence of the microstructure on the static mechanical properties on the basis of the dependence of the yield strength R p o, 2 and the elongation on the temperature.
  • the microstructures correspond on the one hand to the structure after the forging process with a high rate of deformation rate according to FIG. 2c and the structure of the merely cast and isostatically hot pressed TiAl component according to FIG. 2b.
  • FIGS. 4a and 4b show alternative embodiments of the rotationally symmetrical forging component produced by the method according to the invention.
  • the TiAl components are designed as components for turbocharger units of internal combustion engines.
  • the component of Fig. 4a has a largest outer diameter of 48 mm and a height of 53 mm.
  • the component shown in Fig. 4b is formed with a largest diameter of about 66 mm and a height of about 55 mm.
  • the details of the numerical values are to be understood as examples.
  • the production can also be transferred to components with much larger dimensions.

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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)

Abstract

L'invention concerne un procédé de fabrication d'une pièce à partir d'un alliage à base de titane-aluminium. La pièce est en particulier destinée à des ensembles turbocompresseurs de moteurs à combustion interne. Le procédé comprend les étapes suivantes : - le chauffage du matériau de départ coulé à l'intérieur du champ de phases (α+β) à une température à laquelle la phase β présente au moins 5 % en volume ; - le forgeage du matériau de départ chauffé pour obtenir une ébauche forgée par déformation par percussion à une vitesse de déformation ≥ 19 1/s, l'ébauche forgée étant exempte de bavures après le forgeage ; - le retrait de l'ébauche forgée de la matrice et le refroidissement contrôlé et régulier, l'ébauche forgée présentant après le refroidissement à la température de la pièce une part maximale de la phase β/B2-Ti de 10 % en volume ; - le traitement ultérieur de l'ébauche forgée pour obtenir le produit fini.
EP14828000.1A 2013-12-06 2014-11-25 Procédé de fabrication de pièces en tial Active EP3077557B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013020460.7A DE102013020460A1 (de) 2013-12-06 2013-12-06 Verfahren zur Herstellung von TiAl-Bauteilen
PCT/DE2014/000598 WO2015081922A1 (fr) 2013-12-06 2014-11-25 Procédé de fabrication de pièces en tial

Publications (2)

Publication Number Publication Date
EP3077557A1 true EP3077557A1 (fr) 2016-10-12
EP3077557B1 EP3077557B1 (fr) 2017-10-25

Family

ID=52358508

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14828000.1A Active EP3077557B1 (fr) 2013-12-06 2014-11-25 Procédé de fabrication de pièces en tial

Country Status (3)

Country Link
EP (1) EP3077557B1 (fr)
DE (1) DE102013020460A1 (fr)
WO (1) WO2015081922A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017212082A1 (de) * 2017-07-14 2019-01-17 MTU Aero Engines AG Schmieden bei hohen temperaturen, insbesondere von titanaluminiden
CN107604210A (zh) * 2017-11-23 2018-01-19 宁国市华成金研科技有限公司 一种耐高温钛合金板

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5226985A (en) * 1992-01-22 1993-07-13 The United States Of America As Represented By The Secretary Of The Air Force Method to produce gamma titanium aluminide articles having improved properties
US5442847A (en) * 1994-05-31 1995-08-22 Rockwell International Corporation Method for thermomechanical processing of ingot metallurgy near gamma titanium aluminides to refine grain size and optimize mechanical properties
JP4209092B2 (ja) * 2001-05-28 2009-01-14 三菱重工業株式会社 ＴｉＡｌ基合金及びその製造方法並びにそれを用いた動翼
DE102007051499A1 (de) 2007-10-27 2009-04-30 Mtu Aero Engines Gmbh Werkstoff für ein Gasturbinenbauteil, Verfahren zur Herstellung eines Gasturbinenbauteils sowie Gasturbinenbauteil
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

Also Published As

Publication number Publication date
DE102013020460A1 (de) 2015-06-11
EP3077557B1 (fr) 2017-10-25
WO2015081922A9 (fr) 2015-10-22
WO2015081922A1 (fr) 2015-06-11

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