EP3366794B1 - Superalliage à base de ni - Google Patents

Superalliage à base de ni Download PDF

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Publication number
EP3366794B1
EP3366794B1 EP18157015.1A EP18157015A EP3366794B1 EP 3366794 B1 EP3366794 B1 EP 3366794B1 EP 18157015 A EP18157015 A EP 18157015A EP 3366794 B1 EP3366794 B1 EP 3366794B1
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Prior art keywords
phase
amount
present
temperature
specific gravity
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EP18157015.1A
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German (de)
English (en)
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EP3366794A1 (fr
Inventor
Kyohei YOKOTA
Yoshinori Sumi
Yoshihiko Koyanagi
Hiroyuki Takabayashi
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Daido Steel Co Ltd
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Daido Steel Co Ltd
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%

Definitions

  • the present invention relates to an Ni-based superalloy suitable for application as a material of high temperature parts such as a turbine wheel.
  • a turbine wheel rotating with receiving an exhaust gas from an engine rotates at a high speed (e. g., the rotation number per minute being hundreds of thousands) under a high temperature (e. g., under a high temperature of about 950°C) and thus, it is required to be excellent in high-temperature strength properties. Therefore, as a material of the turbine wheel, an Ni-based superalloy excellent in high-temperature strength properties, particularly an Ni-based cast alloy including Inconel 713C and MAR-M246 as a representative has been mainly used.
  • the y' phase (a phase of Ni3(Al, Ti, Nb) that is an intermetallic compound) precipitating as a strengthening phase is stable up to a high temperature, it is difficult to produce the turbine wheel by forging and thus, usually, the turbine wheel is mainly produced by casting using an Ni-based cast alloy and is used in a state as cast.
  • the alloy to be used as a material for high temperature parts such as the turbine wheel, it is required to be low in specific gravity and excellent in castability, in addition to the high-temperature strength properties.
  • any Ni-based alloy sufficiently satisfying these requirements yet.
  • Patent Document 1 describes an invention concerning a "nickel-based alloy", and there is disclosed a nickel-based alloy having a composition consisting of, in terms of % by weight, Co: from 14 to 19%, Cr: from 10 to 15%, C: from 0.05 to 0.2%, Mo: from 0 to 3%, and Ti: from 3.1 to 4.5%, with the balance being Ni and unavoidable impurities, and satisfying a Ti/Al ratio of 0.85 or less.
  • this Patent Document 1 there is no disclosure regarding specific means for improving the castability and the component compositions in individual Examples are all different from those of the present invention.
  • Patent Document 1 JP-A-2015-101753
  • the present invention has been made for the purpose of providing an Ni-based superalloy that is low in specific gravity and excellent in high-temperature strength properties and castability.
  • First aspect of the present invention is an Ni-based superalloy having a composition containing, in terms of % by mass, C: from 0.1 to 0.3%, Cr: from 8.0 to 12.0%, Mo: from 1.0 to 5.0%, Co: from 10.0 to 20.0%, Ta: from 0.01 to 1.50%, Ti: from 2.0 to 4.2%, Al: from 5.0 to 8.0%, V: from 0 to 1.5%, B: from 0.005 to 0.030%, and Zr: from 0.05 to 0.15%, with the balance being Ni and unavoidable impurities, and satisfying, in terms of atom%, Ti+Al being from 16.0 to 20.3% and Ti/Al being 0.3 or less.
  • Second aspect of the present invention is the Ni-based superalloy according to the first aspect, having a specific gravity of 7.9 g/cm 3 or less.
  • Third aspect of the present invention is the Ni-based superalloy according to the first or second aspect, in which Ta is from 0.3 to 0.8% by mass.
  • the precipitation temperature of the ⁇ ' phase can be lowered by decreasing a Ti/Al ratio that is a ratio of Ti to Al and in addition, in the case where the Ti/Al ratio is controlled to 0.3 or less, cast cracking can be prevented with suppressing the precipitation of the ⁇ ' phase in a temperature region where cracking due to insufficient ductility may occur during casting.
  • the present invention has been made based on such findings and is characterized in that the addition amount of the solid solution strengthening elements are decreased and, on the other hand, the total amount of Ti+Al that are constituent elements of the ⁇ '-phase is controlled to 16.0% or more and the Ti/Al ratio is controlled to 0.3 or less.
  • a decrease in the specific gravity of the alloy is attained by decreasing the addition amount of the solid solution strengthening elements and, on the other hand, the high-temperature strength properties are secured by increasing the addition amount of Ti and Al that are constituent elements of the ⁇ '-phase.
  • the addition amount of Ti and Al is increased, the cast cracking is prone to occur and there is a concern of inviting deterioration of the castability.
  • the Ni-based superalloy of the present invention is low in the specific gravity and excellent in the high-temperature strength properties and the castability, and hence can be suitably used as a material for high temperature parts such as a turbine wheel.
  • C improves grain boundary strength through formation of carbides. For attaining sufficient high-temperature strength, it is necessary to add C in an amount of 0.1% or more. However, excessive addition of C forms coarse eutectic carbides to cause a decrease in toughness and ductility. Therefore, an upper limit is set to 0.3%.
  • Cr forms a dense oxide film composed of Cr 2 O 3 on a surface to improve oxidation resistance and high-temperature corrosion resistance. For exhibiting such properties, it is necessary to contain Cr in an amount of 8.0% or more.
  • an upper limit is set to 12.0%. More preferable content of Cr is from 9.0 to 10.0%.
  • Mo has an effect of forming a solid solution in the austenite phase to strengthen the matrix through solid solution strengthening.
  • it is necessary to contain Mo in an amount of at least 1.0%. More preferably, the amount of Mo is 3.1% or more. However, its excessive addition lowers phase stability and deteriorates the ductility and the toughness. Therefore, an upper limit is 5.0%.
  • Co has effects of strengthening the austenite phase through solid solution strengthening and also forming a solid solution in the ⁇ ' phase to strengthen the ⁇ ' phase.
  • the amount of Co is 12.0% or more.
  • an upper limit is 20.0%.
  • Ta from 0.01 to 1.50%
  • Ta not only combines with C to form a carbide but also has an effect of forming a solid solution in the ⁇ ' phase to strengthen the ⁇ ' phase.
  • an upper limit is set to 1.50%. More preferable content is from 0.3 to 0.8%.
  • Ti combines with Ni to form the ⁇ ' phase (Ni 3 (Al, Ti) intermetallic compound) that is effective for improving strength, thereby strengthening the alloy through precipitation strengthening.
  • ⁇ ' phase Ni 3 (Al, Ti) intermetallic compound
  • an addition of Ti in a large amount increases an eutectic carbide to lower the ductility. Therefore, an upper limit is set to 4.2%. More preferable content is 3.0% or less.
  • Al is a component that forms the ⁇ ' phase (Ni 3 Al intermetallic compound).
  • Ni 3 Al intermetallic compound Ni 3 Al intermetallic compound.
  • an upper limit is set to 8.0%. More preferable content is from 6.8 to 7.5%.
  • V forms a solid solution in the ⁇ ' phase to achieve solid solution strengthening.
  • its excessive addition lowers the high-temperature strength. Therefore, 1.5% is an upper limit.
  • V is not contained.
  • B strengthens a grain boundary, it is added in an amount of 0.005% or more. However, an excessive addition of B forms a boride to lower properties. Therefore, an upper limit is set to 0.030%.
  • Zr improves the creep strength through grain boundary strengthening similarly to B, Zr is added in an amount of 0.05% or more. However, an excessive addition of Zr lowers the ductility. Therefore, an upper limit is set to 0.15%.
  • Ti+Al from 16.0 to 20.3%
  • the total amount of Ti+Al is an index that indicates the amount of the ⁇ ' phase and, for improving the high-temperature strength properties, it is necessary to contain Ti+Al in an amount of 16% or more in terms of atom %. However, their excessive addition lowers the ductility. Therefore, an upper limit is set to 20.3%.
  • the Ti/Al ratio is an important factor for the precipitation temperature of the ⁇ ' phase and, in the present invention, the Ti/Al ratio is set to 0.3 or less.
  • an Ni-based superalloy that is low in specific gravity and excellent in high-temperature strength properties and castability can be provided.
  • each of alloys having chemical compositions shown in Table 1 was melted in a vacuum melting furnace to cast 50 kg of an ingot. Thereafter, a specimen was prepared from the ingot by machining and, by using the specimen, specific gravity, 0.2% proof strength, elongation, and creep strength were evaluated. Moreover, by using each of the alloys having chemical compositions shown in Table 1, a turbine wheel was prepared to evaluate castability.
  • Measurement of specific gravity was carried out in accordance with JIS Z 8807 (2012) and evaluation was performed according to the following criteria.
  • a specimen having a parallel part diameter of 8 mm and a gauge length of 40 mm was prepared in accordance with JIS G 0567 (2012) and a tensile test was performed at a test temperature of 1,050°C. In this test, 0.2% proof strength and elongation at 1,050°C were measured.
  • the 0.2% proof strength was evaluated according to the following criteria.
  • the elongation was evaluated according to the following criteria.
  • a specimen in accordance with JIS Z 2271 (2010) was prepared, a load stress of 180 MPa was imparted thereto at a test temperature of 1,000°C to measure a life until rupture, and evaluation was performed according to the following criteria.
  • the specimen has a diameter of 6.4 mm at a parallel part.
  • Comparative Example 1 Co and Ta that are solid solution strengthening elements were not added, as compared to the composition of the present invention. Moreover, the amount of Ti that is a constituent element of the ⁇ ' phase was lower than the lower limit of the present invention, while Nb that is not added in the present invention was added. In Comparative Example 1, sufficient high-temperature strength properties were not obtained and the 0.2% proof strength and the creep strength were evaluated as "C”. Furthermore, the specific gravity was evaluated as "B", which is inferior to Examples to be mentioned later.
  • Comparative Example 2 the amount of Ti and the total amount of Ti+Al were lower than the lower limits of the present invention, while a heavy element W that is not added in the present invention was added. Therefore, in Comparative Example 2, the 0.2% proof strength and the creep strength were good as evaluated as "A” but the specific gravity was evaluated as "C".
  • Comparative Example 3 the amount of Ti and the total amount of Ti+Al were lower than the lower limits of the present invention, while heavy elements Hf and W that are not added in the present invention were added. Moreover, the amount of Ta was also higher than the upper limit 1.5% of the present invention. Therefore, in Comparative Example 3, the 0.2% proof strength, elongation and creep strength were good as evaluated as "A” but the specific gravity was evaluated as "C".
  • Comparative Example 4 the total amount of Ti+Al fell within the defined range of the present invention, while the Ti/Al ratio was higher than the upper limit 0.3 of the present invention. Therefore, in Comparative Example 4, the precipitation temperature of the ⁇ ' phase was higher than that in the other examples, so that occurrence of solidification cracking (cast cracking) was observed in the castability evaluation and the evaluation was "C". Moreover, since the precipitation temperature of the ⁇ ' phase was high, the ductility at a high temperature was low and hot elongation was also evaluated as "C".
  • Comparative Example 5 the amount of Al and the total amount of Ti+Al were lower than the lower limits of the present invention. Therefore, sufficient high-temperature strength properties were not obtained, and the 0.2% proof strength and the creep strength were evaluated as "C”. Moreover, the total amount of Ti+Al itself was small in Comparative Example 5 but the Ti/Al ratio was higher than the upper limit 0.3 of the present invention as in Comparative Example 4, so that the occurrence of cast cracking was observed and the castability was evaluated as "B".
  • Comparative Example 8 is different from aforementioned Comparative Examples 6 and 7 and Ta was added so as to fall within the component range defined in the present invention but the total amount of Ti+Al was still lower than the lower limit 16% of the present invention. Therefore, the creep strength was improved as compared to that in Comparative Examples 6 and 7 but was evaluated as "B". In Comparative Example 8, in addition to the creep strength, the 0.2% proof strength, elongation and castability were also evaluated as "B". Thus, properties as a whole were poor as compared to those of Examples to be mentioned later.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (4)

  1. Superalliage à base de Ni ayant une composition, consistant en: en termes de % en masse,
    C: de 0,1 à 0,3 %,
    Cr: de 8,0 à 12,0 %,
    Mo: de 1,0 à 5,0 %,
    Co: de 10,0 à 20,0 %,
    Ta: de 0,01 à 1,50 %,
    Ti: de 2,0 à 4,2 %,
    Al: de 5,0 à 8,0 %,
    V: de 0 à 1,5 %,
    B: de 0,005 à 0,030 %, et
    Zr: de 0,05 à 0,15 %,
    le solde étant Ni et des impuretés inévitables, et satisfaisant, en termes de % atomique,
    Ti + Al étant de 16,0 à 20,3 % et
    Ti/Al étant de 0,3 ou moins.
  2. Superalliage à base de Ni selon la revendication 1, ayant une masse volumique de 7,9 g/cm3 ou moins.
  3. Superalliage à base de Ni selon la revendication 1 ou 2, dans lequel la teneur en Ta est de 0,3 à 0,8 % en masse.
  4. Utilisation du superalliage à base de Ni selon l'une quelconque des revendications 1 à 3, pour fabriquer une roue de turbine.
EP18157015.1A 2017-02-24 2018-02-15 Superalliage à base de ni Active EP3366794B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2017033971A JP6769341B2 (ja) 2017-02-24 2017-02-24 Ｎｉ基超合金

Publications (2)

Publication Number Publication Date
EP3366794A1 EP3366794A1 (fr) 2018-08-29
EP3366794B1 true EP3366794B1 (fr) 2019-06-19

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US (1) US10385426B2 (fr)
EP (1) EP3366794B1 (fr)
JP (1) JP6769341B2 (fr)
CN (1) CN108504903B (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021141690A2 (fr) * 2019-11-22 2021-07-15 Raytheon Technologies Corporation Alliage métallique

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4608094A (en) * 1984-12-18 1986-08-26 United Technologies Corporation Method of producing turbine disks
JP3753143B2 (ja) * 2003-03-24 2006-03-08 大同特殊鋼株式会社 Ｎｉ基超耐熱鋳造合金およびそれを材料とするタービンホイール
US20080260570A1 (en) * 2004-12-02 2008-10-23 Hiroshi Harada Heat-Resistant Superalloy
JP4885530B2 (ja) * 2005-12-09 2012-02-29 株式会社日立製作所 高強度高延性Ｎｉ基超合金と、それを用いた部材及び製造方法
CN100543164C (zh) * 2007-04-25 2009-09-23 中国科学院金属研究所 一种定向凝固抗热腐蚀镍基铸造高温合金及其制备方法
CN101974708A (zh) * 2010-11-05 2011-02-16 钢铁研究总院 一种抗热蚀定向凝固镍基铸造高温合金
US10266926B2 (en) * 2013-04-23 2019-04-23 General Electric Company Cast nickel-base alloys including iron
JP6213185B2 (ja) 2013-11-25 2017-10-18 株式会社Ihi ニッケル基合金
JP6634674B2 (ja) 2014-02-28 2020-01-22 大同特殊鋼株式会社 自動車用ターボチャージャのタービンホイール及びその製造方法

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Publication number Publication date
CN108504903A (zh) 2018-09-07
JP2018138690A (ja) 2018-09-06
US10385426B2 (en) 2019-08-20
JP6769341B2 (ja) 2020-10-14
EP3366794A1 (fr) 2018-08-29
US20180245188A1 (en) 2018-08-30
CN108504903B (zh) 2020-07-28

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