• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a titanium-based intermetallic alloy having, in atomic percentages, 16% to 26% Al, 18% to 28% Nb, 0% to 3% of a metal M selected from Mo, W, Hf, and V, 0% to 0.8% Si, 0% to 2% Ta, 0% to 4% Zr, with the Fe + Ni condition ≤ 400 ppm, the remainder being Ti.
    公开号:FR3030577A1
    申请号:FR1463066
    申请日:2014-12-22
    公开日:2016-06-24
    发明作者:Jean-Yves Guedou；Jean-Michel Patrick Maurice Franchet；Jean-Loup Bernard Victor Strudel；Laurent Germann；Dipankar Banerjee；Vikas Kumar；Tapash Nandy
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to titanium-based intermetallic alloys.
    [0002] Titanium-based titanium-based intermetallic alloys are known from the application FR 9716057. Such alloys have a high yield strength up to 650 ° C., high creep resistance at 550 ° C. and good temperature ductility. room. However, these alloys may have creep and high temperature oxidation resistance (650 ° C. and beyond) insufficient for certain applications in turbomachines, such as downstream discs or high pressure compressor wheels. These parts are the hottest rotating parts of the compressor and are usually made of nickel alloy density greater than 8 which can be detrimental to the weight of the machine. There is, therefore, a need for new titanium-based Ti 2 A-base alloys having improved high temperature creep resistance.
    [0003] There is also a need for novel titanium-based alloys of the Ti 2 A-B type having improved high temperature oxidation resistance. There is still a need for new titanium-based alloys of the Ti 2 CANb type.
    [0004] OBJECT AND SUMMARY OF THE INVENTION To this end, the invention proposes, according to a first aspect, a titanium-based intermetallic alloy comprising, in atomic percentages, 16% to 26% of Al, 18% to 28% of Nb. 0% to 3% of a metal M selected from Mo, W, Hf, and V, 0 ° h to 0.8% Si, 0 ° h to 2% Ta, 0 ° h to 4% Zr with the Fe + Ni <400 ppm, the remainder being Ti. Due to the reduced content of Fe and Ni elements, the alloy according to the invention advantageously has improved high temperature creep resistance.
    [0005] Such an alloy may advantageously have a yield strength greater than 850 MPa at a temperature of 550 ° C, a high creep resistance between 550 ° C and 650 ° C and a ductility greater than 3.5 ° A) and a yield strength greater than 1000 MPa at room temperature. By "ambient temperature" it is necessary to understand the temperature of 20 ° C.
    [0006] Unless otherwise stated, if several metals M selected from Mo, W, Hf and V are present in the alloy, it should be understood that the sum of the percent atomic percentages of each of the metals present is within the indicated range of values. For example, if Mo and W are present in the alloy, the sum of the atomic percentage content in Mo and the atomic percentage content in W is between 0 ° h and 3%. Tantalum present in atomic contents of between 0 and 2% advantageously makes it possible to reduce the kinetics of oxidation and to increase the creep resistance of the alloy.
    [0007] In an exemplary embodiment, the alloy can verify, in atomic percentage, the following condition: Fe + Ni 5 350 ppm, for example Fe + Ni 5 300 ppm. In an exemplary embodiment, the alloy can verify, in atomic percentage, the following condition: Fe + Ni + Cr 5 350 ppm, for example Fe + Ni + Cr <300 ppm. Preferably, the alloy can verify, in atomic percentage, the following condition: Fe 200 ppm, for example Fe 150 ppm, for example Fe 5. 100 ppm. Preferably, the atomic percentage ratio Al / Nb may be between 1 and 1.3, for example between 1 and 1.2. Such an Al / Nb ratio advantageously makes it possible to improve the resistance to hot oxidation of the alloy. Preferably, the atomic percentage ratio Al / Nb is between 1.05 and 1.15. Such an Al / Nb ratio makes it possible to give the alloy optimum resistance to hot oxidation.
    [0008] Preferably, the alloy may comprise, in atomic percentage, 20% to 22% of Nb. Such Nb contents advantageously make it possible to give the alloy improved oxidation resistance, ductility and mechanical strength. In an exemplary embodiment, the alloy may comprise, in atomic percentage, 22% to 25% of Al. Such contents advantageously make it possible to give the alloy creep resistance and improved oxidation. Preferably, the alloy may comprise, in atomic percentage, 23% to 24% Al. Such contents advantageously make it possible to confer on the alloy an improved ductility as well as creep resistance and improved oxidation. In an exemplary embodiment, the alloy may comprise, in atomic percentage, 0.1% to 0.8% of Si. Preferably, the alloy may comprise, in atomic percentage, 0.1% to 0.5% of Si.
    [0009] Such Si contents advantageously make it possible to improve the creep resistance of the alloy while giving it good resistance to oxidation. In an exemplary embodiment, the alloy may comprise, in atomic percentage, 0.8% to 3% of M. Preferably, the alloy may comprise, in atomic percentage, 0.8% to 2.5% of M preferably 1% to 2% of M. Such metal contents M advantageously make it possible to improve the heat resistance of the alloy. In an exemplary embodiment, the alloy may comprise, in atomic percentage, 1% to 3% of Zr. Preferably, the alloy may comprise, in atomic percentage, from 1 to 2% of Zr. Such Zr contents advantageously make it possible to improve the creep strength, the mechanical strength above 400 ° C and the oxidation resistance of the alloy.
    [0010] In an exemplary embodiment, the alloy may be such that the following condition is satisfied as an atomic percentage: M + Si + Zr + Ta 0.4%, for example M + Si + Zr + Ta 1%. Such contents advantageously make it possible to improve the hot strength of the alloy.
    [0011] In an exemplary embodiment, the alloy may be such that: the content, in atomic percentage, of Al is between 20% and 25%, preferably between 21% and 24%, the content, as an atomic percentage, in Nb is between 20% and 22%, preferably between 21% and 22%, the atomic percentage ratio Al / Nb is between 1 and 1.3, preferably between 1 and 1.2, more preferably between 1.05 and 1.15, the content, in atomic percentage, in M is between 0.8% and 3%, preferably between 0.8% and 2.5%, more preferably between 1% and 2%; %, and the content, in atomic percentage, in Zr is between 1% and 3%, the alloy being optionally such that the content, as an atomic percentage, of Si is between 0.1% and 0.8%. preferably between 0.1% and 0.5%. Such an alloy advantageously has: - a high mechanical strength at 650 ° C in tension (R = 1050MPa - R0.2 = 900MPa), - a good creep resistance at high temperature (elongation of 1% in 150 hours at 650 ° C. under a stress of 500MPa), - good resistance to hot oxidation, and - good ductility at room temperature (> 3.5%). Table 1 below gives the compositions of examples of alloys Si to S12 according to the invention. All these compositions satisfy, as an atomic percentage, the following condition Fe + Ni 400 ppm. Alloy Al Nb Mo Si Zr Al / Nb density TI3 (° C) Si 22 25 0.88 5.29 1065 S2 22 25 0.5 0.88 5.28 1058 S3 22 25 1 0.88 5.34 1055 S4 22 25 1 0.5 0.88 5.34 1065 S5 24 25 0.96 5.29 1085 S6 22 20 1.10 5.09 1055 S7 22 23 1.5 0.2 0.95 5.39 1060 S8 20 25 1 0.80 5.41 1025 S9 22 25 1.5 2 0.88 5.50 1025 S10 20 23 2 2 0.87 5.43 1000 S11 24.5 20 1.5 0.25 1.21 The invention also relates to a turbomachine equipped with a part comprising a, in particular formed of an alloy such as as defined above. The part can, for example, be a housing or a rotating part. The invention also relates to an engine comprising a turbomachine as defined above. The invention also relates to an aircraft comprising a motor as defined above. BRIEF DESCRIPTION OF THE DRAWINGS Other characteristics and advantages of the invention will emerge from the following description, with reference to the appended drawings, in which: FIG. 1 represents the evolution of the creep resistance of various alloys at 650 ° C. under a stress of 310 MPa; FIG. 2 represents the influence of the Al / Nb ratio on the resistance to hot oxidation; FIGS. 3A to 3D illustrate the results obtained in terms of mechanical properties for a preferred alloy according to FIG. 'invention.
    [0012] EXAMPLES EXAMPLE 1 Manufacture of an alloy according to the invention Starting from raw materials consisting of titanium sponges and master alloy granules, a mixture was produced to obtain the chemical composition S12 described in Table 1 above. This mixture of powders was then homogenized and compressed to form a compact constituting an electrode. This electrode was then remelted under vacuum by creating an electric arc between the consumable electrode and the bottom of the water-cooled crucible (vacuum arc remelting process or "VAR" for "Vacuum Arc Remelting"). ). The ingot obtained is then reduced to a bar by high speed deformation (by forging or extrusion) to reduce the grain size. The last step is an isothermal forging of slices cut in the bar at a temperature just below the transus temperature and at a low rate of deformation (some 10-3).
    [0013] Such an alloy of composition S12 which contains 1.3% of zirconium has a very good resistance to hot oxidation. Indeed, this alloy does not peel after exposure of 1500 hours at 700 ° C in air, a thin layer of very adherent and therefore protective oxide, composed of alumina and zirconia being formed. Alloys containing no zirconium may have a lower resistance to hot oxidation. EXAMPLE 2 Improvement of the Hot Creep Resistance by Using a Limited Fe + Ni Content The creep properties of the three alloy compositions P1, P2 and P3 detailed in Table 2 below were compared. . Composition Ti Al Nb Mo Fe Ni (Atomic%) Alloy P1 55.2 23.9 20.3 0.40 0.09 0.01 Alloy P2 53.9 25.3 20.3 0.40 0.07 0, 01 Alloy P3 55.5 23.8 20.3 0.40 0.01 0.02 Table 2 These alloys contain trace elements Fe and Ni which are present in the form of impurities, and result naturally from the manufacturing process. Fe and Ni elements are impurities from the stainless steel container used to make titanium powders. It is thus preferable to use a high purity titanium powder taken from the center of the volume defined by the container where the pollution coming from the walls is negligible in order to ensure that the Fe + Ni 400 ppm condition is obtained. As shown in FIG. 1, an improvement in the creep resistance at 650 ° C. under a stress of 310 MPa is observed when the trace element contents are reduced in order to satisfy the Fe + Ni 400 ppm relationship. Indeed, as represented in FIG. 1, creep reaches 1% after 250 hours with an alloy according to the invention (P3) whereas this creep value is reached only after 40 hours with an alloy according to the invention. prior art (P1). Example 3: Improvement of the resistance to hot corrosion by implementing an Al / Nb atomic percentage ratio of between 1 and 1.3. The resistance to hot corrosion was compared. various alloys. The results are given in FIG. 2. The compositions of alloys S3, S5, S9 and S11 are given above in Table 1. In this test, the mass variation following peeling of the surface of the alloy is measured . This test shows the resistance to oxidation of alloys at 800 ° C. There is a loss of mass related to the consumption of the metal due to oxidation for the alloys S3, S5 and S9 which do not have an Al / Nb ratio of between 1 and 1.3. On the other hand, this loss of mass does not occur for alloy S11 which has an Al / Nb ratio of between 1 and 1.3.
    [0014] Example 4 Comparison of Performance Between the Alloy Manufactured in Example 1 and Other Types of Alloys The results of the tests grouped together in FIGS. 3A to 3D show that composition S12 has both good results in tension and in creep. More particularly: FIG. 3A shows, for different alloys, the evolution of the yield strength (R0.2) as a function of the temperature; FIG. 3B shows, for different alloys, the evolution of the elongation At break (ductility) versus temperature, FIG. 3C compares creep (time for 1% creep) of different alloys at temperatures of 600 and 650 ° C, and FIG. creep of different alloys at temperatures of 600 and 650 ° C. The expression "containing / containing a" must be understood as "containing / containing at least one". The expression "understood between ... and ..." or "from ... to" must be understood as including boundaries.
    权利要求:
    Claims (13)
    [0001]
    REVENDICATIONS1. A titanium-based intermetallic alloy having, in atomic percentages, 16 ° to 26% Al, 18 to 28% Nb, 0 to 3% of a metal M selected from Mo, W, Hf, and V 0% to 0.8% Si, 0% to 2% Ta, 0 ° h to 4% Zr, with the condition Fe + Ni 5. 400 ppm, the remainder being Ti.
    [0002]
    2. Alloy according to claim 1, characterized in that the atomic percentage ratio Al / Nb is between 1 and 1.3.
    [0003]
    3. Alloy according to claim 2, characterized in that the atomic percentage ratio Al / Nb is between 1.05 and 1.15.
    [0004]
    4. An alloy according to any one of claims 1 to 3, characterized in that it comprises, in atomic percentage, 20% to 22 ° hl of Nb.
    [0005]
    5. An alloy according to any one of claims 1 to 4, characterized in that it comprises, in atomic percentage, 23 ° h at 24 ° h of Al.
    [0006]
    6. An alloy according to any one of claims 1 to 5, characterized in that it comprises, in atomic percentage, 0.1% to 0.8% Si.
    [0007]
    7. An alloy according to any one of claims 1 to 6, characterized in that it comprises, in atomic percentage, 0.8% to 3% of M.
    [0008]
    8. An alloy according to any one of claims 1 to 7, characterized in that it comprises, in atomic percentage, 1% to 3% of Zr.
    [0009]
    9. Intermetallic alloy according to any one of claims 1 to 8, characterized in that: the content, in atomic percentage, of Al is between 20% and 25%, the atomic percentage content in Nb is between 20% and 22%, the atomic percentage ratio Al / Nb being between 1 and 1.3, the content, in atomic percentage, in M is between 0.8% and 3%, and the content as an atomic percentage, Zr is between 1% and 3%. 5
    [0010]
    10.Alloy according to any one of claims 1 to 9, characterized in that the condition M + Si + Zr + Ta 0.4% is further verified.
    [0011]
    11.Turbomachine equipped with a part comprising an alloy according to any one of claims 1 to 10. 10
    [0012]
    12. Motor comprising a turbomachine according to claim 11.
    [0013]
    Aircraft comprising an engine according to claim 12.
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    引用文献:
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    US4716020A|1982-09-27|1987-12-29|United Technologies Corporation|Titanium aluminum alloys containing niobium, vanadium and molybdenum|
    US5032357A|1989-03-20|1991-07-16|General Electric Company|Tri-titanium aluminide alloys containing at least eighteen atom percent niobium|
    EP0539152A1|1991-10-21|1993-04-28|General Electric Company|Titanium niobium aluminide alloys|
    EP0924308A1|1997-12-18|1999-06-23|Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"|Titanium-based intermetallic alloys of the Ti2AlNb type with high yield strength and good creep resistance|
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    RU2405849C1|2009-10-28|2010-12-10|Российская Федерация, от имени которой выступает государственный заказчик - Министерство промышленности и торговли Российской Федерации |Intermetallic titanium-based alloy|
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    CN106854725B|2016-12-23|2019-03-19|西部超导材料科技股份有限公司|A kind of Ti2The preparation method of AlNb based alloy and its ingot casting|
    CN111647771B|2020-04-17|2021-10-15|中国航发北京航空材料研究院|Multi-element composite anti-oxidation Ti2AlNb alloy and preparation method thereof|
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    法律状态:
    2015-12-15| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-24| PLSC| Publication of the preliminary search report|Effective date: 20160624 |
    2016-12-05| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 5 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1463066|2014-12-22|
    FR1463066A|FR3030577B1|2014-12-22|2014-12-22|INTERMETALLIC ALLOY BASED ON TITANIUM|FR1463066A| FR3030577B1|2014-12-22|2014-12-22|INTERMETALLIC ALLOY BASED ON TITANIUM|
    CN201580069975.2A| CN107109540B|2014-12-22|2015-12-14|The mutual alloy of titanium-based|
    CA2971092A| CA2971092A1|2014-12-22|2015-12-14|Intermetallic alloy based on titanium|
    BR112017013328A| BR112017013328A2|2014-12-22|2015-12-14|titanium-based intermetallic alloy, turbocharger, engine, and aircraft.|
    JP2017551367A| JP6805163B2|2014-12-22|2015-12-14|Intermetallic compound alloy containing titanium as the main component|
    US15/538,119| US10119180B2|2014-12-22|2015-12-14|Titanium-based intermetallic alloy|
    PCT/FR2015/053481| WO2016102806A1|2014-12-22|2015-12-14|Intermetallic alloy based on titanium|
    EP15823349.4A| EP3237646B1|2014-12-22|2015-12-14|Intermetallic alloy based on titanium|
    RU2017126060A| RU2730348C2|2014-12-22|2015-12-14|Intermetallic titanium-based alloy|
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