EP2641984A2 - Verfahren zur Verarbeitung von intermetallischen Titanaluminidzusammensetzungen - Google Patents

Verfahren zur Verarbeitung von intermetallischen Titanaluminidzusammensetzungen Download PDF

Info

Publication number
EP2641984A2
EP2641984A2 EP20130159885 EP13159885A EP2641984A2 EP 2641984 A2 EP2641984 A2 EP 2641984A2 EP 20130159885 EP20130159885 EP 20130159885 EP 13159885 A EP13159885 A EP 13159885A EP 2641984 A2 EP2641984 A2 EP 2641984A2
Authority
EP
European Patent Office
Prior art keywords
titanium aluminide
aluminide intermetallic
intermetallic composition
temperature
tial
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
EP20130159885
Other languages
English (en)
French (fr)
Other versions
EP2641984A3 (de
EP2641984B1 (de
Inventor
Thomas Joseph Kelly
Bernard Patrick Bewlaw
Michael James Weimer
Richard Kenneth Whitacre
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.)
General Electric Co
Original Assignee
General Electric Co
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=47913098&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2641984(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by General Electric Co filed Critical General Electric Co
Priority to EP15184357.0A priority Critical patent/EP2995695B1/de
Publication of EP2641984A2 publication Critical patent/EP2641984A2/de
Publication of EP2641984A3 publication Critical patent/EP2641984A3/de
Application granted granted Critical
Publication of EP2641984B1 publication Critical patent/EP2641984B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • 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
    • 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

Definitions

  • the present invention generally relates to compositions containing titanium and aluminum and the processing thereof. More particularly, this invention relates to methods of processing cast titanium aluminide intermetallic compositions that entail hot isostatic pressing and heat treatment to close porosity and yield a desirable microstructure.
  • Titanium-based alloy systems are well known in the art as having mechanical properties that are suitable for relatively high temperature applications.
  • High temperature capabilities of titanium-based alloys has increased through the use of titanium intermetallic systems based on the titanium aluminide compounds Ti 3 Al (alpha-2 ( ⁇ -2) alloys) and TiAl (gamma ( ⁇ ) alloys).
  • These titanium aluminide intermetallic compounds are generally characterized as being relatively light weight, yet are known to be capable of exhibiting high strength, creep strength and fatigue resistance at elevated temperatures.
  • Additions of chromium and niobium are known to promote certain properties of TiAl intermetallics, such as oxidation resistance, ductility, strength, etc.
  • U.S. Patent No. 4,879,092 to Huang discloses a titanium aluminide intermetallic composition having an approximate formula of Ti 46-50 Al 46-50 Cr 2 Nb 2 , or nominally about Ti-48Al-2Cr-2Nb.
  • This alloy, referred to herein as the 48-2-2 alloy is considered to have a nominal temperature capability of up to about 1400°F (about 760°C), with useful but diminishing capabilities up to about 1500°F (about 815°C).
  • the 48-2-2 alloy is well suited for low pressure turbine blade (LPTB) applications.
  • Hot isostatic pressing is commonly performed to eliminate internal voids and microporosity in titanium aluminide intermetallic castings. Because uncontrolled cooling rates typically performed following HIP are not effective to generate a desired microstructure, responsiveness to post-HIP heat treatments is another desirable characteristic in order to achieve microstructures and mechanical properties needed for specific applications.
  • HIP cycles are typically separate from the heat treatment cycle in the processing of castings.
  • desired microstructures and mechanical properties have been obtained in castings of the 48-2-2 alloy using a process represented in FIG. 3 .
  • a pre-HIP heat treatment is performed at a temperature within a range of about 1800 to about 2000°F (about 980 to about 1090°C) and for a duration of about five to twelve hours.
  • the casting is cooled and transferred to a HIP chamber and then subjected to a high pressure HIP step (for example, 25 ksi (about 1720 bar) or more) at about 2165°F for a duration of about three hours.
  • a high pressure HIP step for example, 25 ksi (about 1720 bar) or more
  • the HIPed casting is then cooled, removed from the HIP chamber, and then subjected to a post-HIP solution treatment at a temperature of about 2200°F for a duration of about two hours.
  • This sequence requires the use of at least two different vessels and loading and unloading the casting three times from these vessels. In addition to incurring additional cost and cycle time, this process has been associated with the loss of aluminum from the casting surface, which leads to reduced environmental and/or mechanical properties.
  • FIGS. 1 and 2 are photomicrographs showing desirable duplex microstructures present in two conventional TiAl castings.
  • a method is needed that is capable of processing TiAl intermetallics, including but not limited to net-shape geometries of the 48-2-2 alloy, to yield a duplex microstructure containing equiaxed and lamellar morphologies. It would be further desirable if such a method did not require a sequence in which a casting is not required to be transferred between multiple different vessels.
  • the present invention provides methods capable of processing compositions containing titanium and aluminum, and especially titanium aluminide intermetallic compositions (TiAl intermetallics) based on the TiAl (gamma) intermetallic compound, to yield desirable microstructures.
  • the methods have the further capability of being performed in a single vessel, resulting in a less complicated process than conventional methods used to produce compositions that require void closure (for example, by HIPing) and heat treatment.
  • a method of processing a titanium aluminide intermetallic composition includes hot isostatic pressing the composition at a temperature of at least 1260°C (about 2300°F), cooling the composition to a temperature of not less than 1120°C (about 2050°F), heat treating the composition at a temperature of about 1150 to about 1200°C (about 2100 to about 2200°F), and then cooling the composition to room temperature.
  • the titanium aluminide intermetallic composition exhibits a desirable duplex microstructure containing equiaxed and lamellar morphologies of the gamma TiAl phase.
  • an alternative method of processing a titanium aluminide intermetallic composition includes hot isostatic pressing the titanium aluminide intermetallic composition, cooling the composition, heat treating the composition at a temperature of at least 1260°C (about 2300°F) for about 2.5 to about 5 hours, cooling the composition to a temperature of not less than 1120°C (about 2050°F), holding the composition at a hold temperature of about 1150 to about 1200°C (about 2100 to about 2200°F) for a duration of about two to about six hours, and then cooling the composition to room temperature.
  • the titanium aluminide intermetallic composition exhibits a desirable duplex microstructure containing equiaxed and lamellar morphologies of the gamma TiAl phase.
  • a beneficial effect of the invention is the ability to produce desirable duplex microstructures in TiAl intermetallics that may otherwise be difficult to obtain, particularly if produced by net-shape casting methods such as spin casting and possibly certain other casting techniques.
  • Another beneficial effect is the ability to take advantage of the energy available for phase equilibration during cool down from a HIP step to assist in a subsequent heat treatment, which has been determined to eliminate the requirement for conventional pre- and post-heat treatment cycles that may cause aluminum to be lost from the casting surface as well as incur additional cost and cycle time.
  • FIGS. 4 and 5 contain flow charts that represent two related methods by which TiAl intermetallic compositions, including but not limited to the 48-2-2 alloy, can be processed to yield a desirable duplex microstructure, with the additional benefit of avoiding the disadvantages of the prior art process summarized in FIG. 3 .
  • the methods of FIGS. 4 and 5 avoid the pre- and post-HIP vacuum heat treatments that are believed to promote the loss of aluminum in TiAl intermetallic compositions.
  • the invention also takes advantage of the high gas pressures and protective (inert) atmospheres used during HIP, the combination of which is believed to be capable of reducing the loss of aluminum in a TiAl intermetallic composition.
  • FIG. 4 and 5 provide for interrupted cooling from a HIP step ( FIG. 4 ) or a temperature that is believed to take advantage of the non-equilibrium phase distribution in TiAl intermetallic compositions following HIP ( FIG. 5 ) to generate (during a subsequent heat treatment) microstructures that are capable of providing desirable mechanical properties, especially if the TiAl intermetallic composition is a cast using a net-shape casting process, such as spin casting or other means.
  • FIGS. 4 and 5 are believed to be particularly beneficial to the 48-2-2 alloy, whose composition is based on the gamma (TiAl) intermetallic compound. Castings of the 48-2-2 alloy exhibit improved ductility and other desirable properties if they contain a duplex microstructure containing equiaxed and lamellar gamma phase morphologies.
  • FIGS. 6 and 7 are representative of LPTB castings produced from the 48-2-2 alloy. Both castings were produced by spin casting, the casting in FIG. 6 was processed by a HIP and heat treatment procedure corresponding to that represented in FIG. 3 , and the casting in FIG. 7 was processed by a modified HIP and heat treatment procedure corresponding to that represented in FIG. 4 .
  • the microstructure of the heat treated casting shown in FIG. 6 possesses an excessive amount of equiaxed gamma phase and an inadequate amount of the lamellar phase (less than 10% volume fraction of the lamellar phase). Such a microstructure would yield a component with insufficiently high temperature creep strength.
  • the microstructure of the heat treated casting shown in FIG. 7 has acceptable amounts of the equiaxed gamma phase and the lamellar phase (about 20% volume fraction of the lamellar phase), the sole exception being at the outermost surface of the casting where titanium levels are depleted. However, the outermost surface can be removed by conventional techniques, such as abrasive blasting or chemical milling, with the result that the entire remaining casting would contain acceptable amounts of the equiaxed gamma phase and lamellar phase.
  • the invention has been shown to yield particularly advantageous results with the 48-2-2 alloy, the invention is believed to be more generally applicable to titanium aluminide intermetallic compositions, particularly TiAl (gamma) intermetallic compositions modified with elements that are intended to promote various properties.
  • the invention has also been shown to be effective with TiAl intermetallic compositions that contain tantalum.
  • Particular compositions that have been successfully evaluated include TiAl compositions that contain chromium, niobium and/or tantalum, for example, about 1.8 to about 2 atomic percent chromium, up to about 2 atomic percent niobium, and up to about 4 atomic percent tantalum.
  • compositions that were successfully evaluated contained, in atomic percent: about 47.3% aluminum, about 1.9% chromium, about 1.9% niobium and the balance titanium and incidental impurities (roughly corresponding to the 48-2-2 alloy); or about 47.3% aluminum, about 1.8% chromium, about 0.85% niobium, about 1.7% tantalum and the balance titanium and incidental impurities; or about 47.3% aluminum, about 2.0% chromium, about 4.0% tantalum and the balance titanium and incidental impurities. More generally, the levels of titanium and aluminum in these TiAl intermetallic compositions are selected to yield a casting whose predominant constituent is the TiAl (gamma) intermetallic compound.
  • compositions evaluated all contained about 47.3 atomic percent aluminum and about 46.7 to 48.9 atomic percent titanium, those skilled in the art will appreciate that aluminum and titanium levels beyond these amounts can be used to yield a casting that is entirely or predominantly the TiAl intermetallic compound, and such variations are within the scope of the invention. Furthermore, those skilled in the art will recognize that other alloy constituents could be included to modify the properties of the TiAl intermetallic compound, and such variations are also within the scope of the invention.
  • the process of FIG. 4 generally entails preparing a TiAl intermetallic composition.
  • a preferred but not limiting example entails spin casting an appropriate melt containing the desired constituents of the TiAl intermetallic composition.
  • the composition (casting) is then loaded in a suitable HIP chamber and heated in a protective atmosphere (for example, argon or another inert gas) to a temperature at which the casting is to undergo HIPing.
  • the HIP temperature (T HIP1 ) is at least 2300°F (about 1260°C), more preferably at least 2350°F (about 1290°C), and most preferably in a range of about 2375 to about 2425°F (about 1300 to about 1330°C).
  • the pressure applied to the casting during the HIP cycle is intended to eliminate internal voids and microporosity in the castings.
  • pressures of at least 15 ksi (about 1030 bar) are believed to be sufficient, with pressures of about 18 ksi (about 1240 bar) and higher believed to be particularly preferred.
  • the duration of the HIP cycle may vary depending on the particular composition and pressure used, but suitable results are believed to be obtained with HIP cycles having durations of about 2.5 to about 5 hours, and particularly about 2.5 to about 3.5 hours.
  • the casting is cooled to a temperature of not less than 2050°F (about 1120°C), more preferably not less than 2100°F (about 1150°C), and most preferably about 2100 to about 2150°F (about 1150 to about 1175°C).
  • the cooling rate may vary, but rates of about 5 to about 20°F/minute (about 3 to about 11 °C/minute) have been found to be acceptable.
  • the casting then undergoes a heat treatment at a temperature of about 2100 to about 2200°F (about 1150 to about 1200°C), for example, about 2100 to about 2150°F (about 1150 to about 1175°C).
  • the duration of this heat treatment may vary depending on the particular composition and HIP treatment used, but suitable results are believe to be obtained with heat treatment cycles having durations of about two to about six hours, and especially about 4.5 to about 5.5 hours.
  • the casting can be cooled directly to room temperature (about 20 to about 25°C) at any desired rate.
  • the TiAl intermetallic casting preferably exhibits a duplex microstructure of the type seen in FIG. 7 . From the above, it should be evident that the casting is not required to be removed from the HIP chamber during the steps identified in FIG. 4 , and that the casting can be continuously exposed to the inert atmosphere of the HIP chamber throughout the process represented in FIG. 4 .
  • the process set forth in FIG. 5 differs from that set forth in FIG. 4 by the allowance of a full cool down (to room temperature) between the HIP cycle and the heat treatment.
  • the process of FIG. 5 additionally involves heating the casting to the T HIP1 temperature prior to the heat treatment. This process is believed to allow more flexibility in the temperature used for the HIP cycle, in that HIPing is not required to be performed at the T HIP1 temperature of FIG. 4 , but instead can be at a temperature (designated as T HIP2 ) that can be higher or lower than the temperatures within the ranges stated above for T HIP1 .
  • the process set forth in FIG. 5 generally entails HIPing a TiAl intermetallic composition (typically a casting) at a suitable temperature (T HIP2 ), which can be followed by cooling the casting to essentially any temperature (including room temperature).
  • T HIP2 a suitable temperature
  • the casting is heat treated at the T HIP1 temperature (for example, at least 2300°F (about 1260°C)) for a duration sufficient to ensure the entire casting is at T HIP1 .
  • the casting can then be cooled at a suitable rate (for example, about 5 to about 20°F/minute (about 3 to about 11°C/minute)) to a temperature of not less than 2050°F (about 1120°C), more preferably not less than 2100°F (about 1150°C), and most preferably about 2100 to about 2150°F (about 1150 to about 1175°C).
  • the casting can then be subjected to the same heat treatment as described for the process of FIG.
  • the TiAl intermetallic casting preferably exhibits a duplex microstructure of the type seen in FIG. 7 .
  • the casting is not required to be removed from the HIP chamber for any step of FIG. 5 , and that the casting can be continuously exposed to the inert atmosphere of the HIP chamber throughout the process represented in FIG. 5 .

Landscapes

  • 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)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Manufacture Of Metal Powder And Suspensions Thereof (AREA)
EP13159885.6A 2012-03-23 2013-03-19 Verfahren zur Verarbeitung von intermetallischen Titanaluminidzusammensetzungen Active EP2641984B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15184357.0A EP2995695B1 (de) 2012-03-23 2013-03-19 Verfahren zur verarbeitung von intermetallischen titanaluminidzusammensetzungen

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201261614751P 2012-03-23 2012-03-23
US13/459,420 US20130248061A1 (en) 2012-03-23 2012-04-30 Methods for processing titanium aluminide intermetallic compositions

Related Child Applications (2)

Application Number Title Priority Date Filing Date
EP15184357.0A Division-Into EP2995695B1 (de) 2012-03-23 2013-03-19 Verfahren zur verarbeitung von intermetallischen titanaluminidzusammensetzungen
EP15184357.0A Division EP2995695B1 (de) 2012-03-23 2013-03-19 Verfahren zur verarbeitung von intermetallischen titanaluminidzusammensetzungen

Publications (3)

Publication Number Publication Date
EP2641984A2 true EP2641984A2 (de) 2013-09-25
EP2641984A3 EP2641984A3 (de) 2014-03-12
EP2641984B1 EP2641984B1 (de) 2015-10-21

Family

ID=47913098

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13159885.6A Active EP2641984B1 (de) 2012-03-23 2013-03-19 Verfahren zur Verarbeitung von intermetallischen Titanaluminidzusammensetzungen
EP15184357.0A Active EP2995695B1 (de) 2012-03-23 2013-03-19 Verfahren zur verarbeitung von intermetallischen titanaluminidzusammensetzungen

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP15184357.0A Active EP2995695B1 (de) 2012-03-23 2013-03-19 Verfahren zur verarbeitung von intermetallischen titanaluminidzusammensetzungen

Country Status (6)

Country Link
US (1) US20130248061A1 (de)
EP (2) EP2641984B1 (de)
JP (1) JP6200666B2 (de)
CN (1) CN103320647B (de)
BR (1) BR102013006917A2 (de)
CA (1) CA2809444C (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021152274A1 (fr) 2020-01-31 2021-08-05 Safran Aircraft Engines Traitement thermique à compression isostatique à chaud de barreaux en alliage d'aluminure de titane pour aubes de turbine basse pression de turbomachine

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8858697B2 (en) 2011-10-28 2014-10-14 General Electric Company Mold compositions
US9011205B2 (en) 2012-02-15 2015-04-21 General Electric Company Titanium aluminide article with improved surface finish
US8932518B2 (en) 2012-02-29 2015-01-13 General Electric Company Mold and facecoat compositions
US10597756B2 (en) * 2012-03-24 2020-03-24 General Electric Company Titanium aluminide intermetallic compositions
US8906292B2 (en) 2012-07-27 2014-12-09 General Electric Company Crucible and facecoat compositions
US8708033B2 (en) 2012-08-29 2014-04-29 General Electric Company Calcium titanate containing mold compositions and methods for casting titanium and titanium aluminide alloys
US8992824B2 (en) 2012-12-04 2015-03-31 General Electric Company Crucible and extrinsic facecoat compositions
US9192983B2 (en) 2013-11-26 2015-11-24 General Electric Company Silicon carbide-containing mold and facecoat compositions and methods for casting titanium and titanium aluminide alloys
US9511417B2 (en) 2013-11-26 2016-12-06 General Electric Company Silicon carbide-containing mold and facecoat compositions and methods for casting titanium and titanium aluminide alloys
CN103710606B (zh) * 2013-12-16 2016-07-06 北京工业大学 一种含Cr高Nbβ-γ TiAl金属间化合物材料及其制备方法
US10391547B2 (en) 2014-06-04 2019-08-27 General Electric Company Casting mold of grading with silicon carbide
CN104005023B (zh) * 2014-06-06 2016-05-25 江苏大学 在钛金属表面制备Ti-Al-Nb合金涂层的方法
EP2990141B1 (de) * 2014-09-01 2019-04-03 MTU Aero Engines GmbH Herstellungsverfahren für TiAl-Bauteile
FR3027921A1 (fr) * 2014-10-31 2016-05-06 Snecma Alliages a base de titane presentant des proprietes mecaniques ameliorees
CN111975003B (zh) * 2020-08-14 2022-12-27 西北工业大学 一种钛铝合金全片层组织的调控方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4879092A (en) 1988-06-03 1989-11-07 General Electric Company Titanium aluminum alloys modified by chromium and niobium and method of preparation

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5149497A (en) * 1991-06-12 1992-09-22 General Electric Company Oxidation resistant coatings of gamma titanium aluminum alloys modified by chromium and tantalum
JPH06228685A (ja) * 1993-02-01 1994-08-16 Honda Motor Co Ltd 高強度高延性ＴｉＡｌ系金属間化合物およびその製造方法
US5350466A (en) * 1993-07-19 1994-09-27 Howmet Corporation Creep resistant titanium aluminide alloy
US5634992A (en) * 1994-06-20 1997-06-03 General Electric Company Method for heat treating gamma titanium aluminide alloys
US6231699B1 (en) * 1994-06-20 2001-05-15 General Electric Company Heat treatment of gamma titanium aluminide alloys
US5609698A (en) * 1995-01-23 1997-03-11 General Electric Company Processing of gamma titanium-aluminide alloy using a heat treatment prior to deformation processing
US5545265A (en) * 1995-03-16 1996-08-13 General Electric Company Titanium aluminide alloy with improved temperature capability
CN1055323C (zh) * 1997-11-03 2000-08-09 冶金工业部钢铁研究总院 钛铝合金铸件的组织均匀细化方法
JP3784363B2 (ja) * 2002-10-10 2006-06-07 株式会社神戸製鋼所 Ａｌ合金鋳造品の改質法
DE102007060587B4 (de) * 2007-12-13 2013-01-31 Helmholtz-Zentrum Geesthacht Zentrum für Material- und Küstenforschung GmbH Titanaluminidlegierungen

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4879092A (en) 1988-06-03 1989-11-07 General Electric Company Titanium aluminum alloys modified by chromium and niobium and method of preparation

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021152274A1 (fr) 2020-01-31 2021-08-05 Safran Aircraft Engines Traitement thermique à compression isostatique à chaud de barreaux en alliage d'aluminure de titane pour aubes de turbine basse pression de turbomachine
FR3106851A1 (fr) * 2020-01-31 2021-08-06 Safran Aircraft Engines Traitement thermique à compression isostatique à chaud de barreaux en alliage d’aluminure de titane pour aubes de turbine basse pression de turbomachine

Also Published As

Publication number Publication date
CN103320647A (zh) 2013-09-25
EP2641984A3 (de) 2014-03-12
JP2013199705A (ja) 2013-10-03
EP2641984B1 (de) 2015-10-21
CA2809444A1 (en) 2013-09-23
BR102013006917A2 (pt) 2015-07-07
CA2809444C (en) 2021-05-18
CN103320647B (zh) 2017-11-07
EP2995695A1 (de) 2016-03-16
EP2995695B1 (de) 2017-11-22
JP6200666B2 (ja) 2017-09-20
US20130248061A1 (en) 2013-09-26

Similar Documents

Publication Publication Date Title
EP2641984B1 (de) Verfahren zur Verarbeitung von intermetallischen Titanaluminidzusammensetzungen
EP2657358B1 (de) Titanaluminidzusammensetzungen
EP2532762B1 (de) Aluminiumoxid ausbildende legierung auf kobalt-nickelbasis und herstellungsverfahren dafür
EP2112239B1 (de) Verfahren zur herstellung von hochfeste aluminiumlegierungen mit l12-ausscheidungeng
EP2112243B1 (de) L12-Aluminium-Legierungen mit hoher Festigkeit
Xu et al. Progress in application of rare metals in superalloys
EP2110452A1 (de) L12-Aluminium-Legierungen mit hoher Festigkeit
US8435362B2 (en) Process for producing a single-crystal component made of a nickel-based superalloy
EP3822007A1 (de) Verfahren zur herstellung eine artikels aus einer titanlegierung
JP7073051B2 (ja) 超合金物品及び関連物品の製造方法
US5908516A (en) Titanium Aluminide alloys containing Boron, Chromium, Silicon and Tungsten
JP6833029B2 (ja) チタンを含まない超合金、粉末、方法および部品
Erickson Polycrystalline cast superalloys
US7704339B2 (en) Method of heat treating titanium aluminide
EP2520678B1 (de) Legierungen auf Nickelbasis
JP6721289B2 (ja) 物品及び物品の製造方法
CN103320648B (zh) 铝化钛金属间组合物
EP1760164A1 (de) Nickel-Superlegierung
SE461987B (sv) Foerfarande foer vaermebehandling av foeremaal av hoeghaallfasta legeringar foere varmisostatisk pressning
RU2361012C1 (ru) Способ обработки отливок из жаропрочных никелевых сплавов для монокристального литья
JP2000345259A (ja) 耐クリープ性γ型チタン・アルミナイド
WO2017123186A1 (en) Tial-based alloys having improved creep strength by strengthening of gamma phase
JP2015165048A (ja) 物品及び物品の製造方法
RU2361011C1 (ru) Способ обработки отливок из жаропрочного никелевого сплава для монокристального литья

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: C22C 14/00 20060101AFI20140131BHEP

Ipc: C22F 1/18 20060101ALI20140131BHEP

17P Request for examination filed

Effective date: 20140912

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150513

RIN1 Information on inventor provided before grant (corrected)

Inventor name: BEWLAY, BERNARD PATRICK

Inventor name: WEIMER, MICHAEL JAMES

Inventor name: WHITACRE, RICHARD KENNETH

Inventor name: KELLY, THOMAS JOSEPH

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Ref country code: NL

Ref legal event code: MP

Effective date: 20151021

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 756663

Country of ref document: AT

Kind code of ref document: T

Effective date: 20151115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602013003505

Country of ref document: DE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 756663

Country of ref document: AT

Kind code of ref document: T

Effective date: 20151021

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 4

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160221

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160121

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160122

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160222

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602013003505

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160331

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

26N No opposition filed

Effective date: 20160722

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160319

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160331

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160319

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160331

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20130319

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160331

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151021

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230222

Year of fee payment: 11

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230414

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240220

Year of fee payment: 12

Ref country code: GB

Payment date: 20240220

Year of fee payment: 12