EP1568794B1 - Ni-BASE SINGLE CRYSTAL SUPERALLOY - Google Patents

Ni-BASE SINGLE CRYSTAL SUPERALLOY Download PDF

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EP1568794B1
EP1568794B1 EP03777308A EP03777308A EP1568794B1 EP 1568794 B1 EP1568794 B1 EP 1568794B1 EP 03777308 A EP03777308 A EP 03777308A EP 03777308 A EP03777308 A EP 03777308A EP 1568794 B1 EP1568794 B1 EP 1568794B1
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single crystal
based single
crystal super
composition
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EP1568794A1 (en
EP1568794A4 (en
Inventor
Toshiharu Nat. Ins. for Mat. Science KOBAYASHI
Yutaka Nat. Inst. for Mat. Science KOIZUMI
Tadaharu Nat. Inst. for Mat. Science YOKOKAWA
Hiroshi Nat. Inst. for Mat. Science HARADA
Yasuhiro Ishikawajima-Harima Heavy Ind. Co. AOKI
Mikiya Ishikawajima-Harima Heavy Ind. Co. ARAI
Shoju Ishikawajima-Harima Heavy Ind. Co. MASAKI
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Independent Administrative Institution National In
IHI Corp
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IHI Corp
National Institute for Materials Science
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    • 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%

Definitions

  • the present invention relates to a Ni-based single crystal super alloy, and more particularly, to a technology employed for improving the creep characteristics of Ni-based single crystal super alloy.
  • Table 1 An example of the typical composition of Ni-based single crystal super alloy developed for use as a material for moving and stationary blades subject to high temperatures such as those in aircraft and gas turbines is shown in Table 1.
  • Table 1 Alloy name Elements (wt%) Al Ti Ta Nb Mo W Re C Zr Hf Cr Co Ru Ni CMSX-2 6.0 1.0 6.0 - 1.0 8.0 - - - - 8.0 5.0 - Rem CMSX-4 5.6 1.0 6.5 - 0.6 6.0 3.0 - - - 6.5 9.0 - Rem Rene'N6 6.0 - 7.0 03 1.0 6.0 5.0 - - 0.2 4.0 13.0 - Rem CMSX-10 K 5.7 0.3 8.4 0.1 0.4 5.5 6.3 - - 0.03 2.3 3.3 - Rem 3B 5.7 0.5 8.0 - - 5.5 6.0 0.05 - 0.15 5.0 12.5 3.0 Rem
  • Ni-based single crystal super alloys after performing solution treatment at a prescribed temperature, aging treatment is performed to obtain an Ni-based single crystal super alloy.
  • This alloy is referred to as a so-called precipitation hardened alloy, and has a from in which the precipitation phase in the form of a ⁇ ' phase is precipitated in a matrix in the form of a ⁇ phase.
  • CMSX-2 Cannon-Muskegon, US Patent No. 4,582,548
  • CMSX-4 Cannon-Muskegon, US Patent No. 4,643,782
  • Rene'N6 General Electric, US Patent No. 5,455,120
  • CMSX-10K Canon-Muskegon, US Patent No. 5,366,695
  • 3B General Electric, US Patent No. 5,151,249
  • CMSX-2 which is a first-generation alloy
  • CMSX-4 which is a second-generation alloy
  • their creep strength is inferior to third-generation alloys.
  • the third-generation alloys of Rene'N6 and CMSX-10 are alloys designed to have improved creep strength at high temperatures in comparison with second-generation alloys, since the composite ratio of Re (5 wt% or more) exceeds the amount of Re that dissolves into the matrix ( ⁇ phase), the excess Re compounds with other elements and as a result, a so-called TCP (topologically close packed) phase precipitates at high temperatures causing the problem of decreased creep strength.
  • the lattice constant of the precipitation phase ( ⁇ ' phase) slightly smaller than the lattice constant of the matrix ( ⁇ phase) is effective in improving the creep strength of Ni-based single crystal super alloys.
  • the lattice constant of each phase fluctuates greatly fluctuated according to the composite ratios of the composite elements of the alloy, it is difficult to make fine adjustments in the lattice constant and as a result, there is the problem of considerable difficulty in improving creep strength.
  • the object of the present invention is to provide a Ni-based single crystal super alloy that makes it possible to improve strength by preventing precipitation of the TCP phase at high temperatures.
  • the Ni-based single crystal super alloy of the present invention has 5.0-7.0 wt % of Al, 4.0-10.0 wt % of Ta, 1.1-4.5 wt.% of Mo, 4.0-10.0 wt % of W, 3.1-8.0 wt % of Re, 0-0.50 wt % of Hf, 2.0-5.0 wt % of Cr, 0.1-9.9 wt % of Co, 4.1-14.0 wt % of Ru, 0-2.0 wt% of Ti, 0-4.0 wt % ofNb, 0-0.05 wt% of B, 0-0.15 wt% of C, 0-0.1 wt % of Si, 0-0.1 wt % of Y, 0-0.1 wt% of La, 0-0.1 wt % of Ce, 0-1 wt % of V and 0-0.1 wt% ofZr in terms of its weight ratio, with the remainder consisting of Ni and unavoidable impurities; and
  • the Ni-based single crystal super alloy of the present invention is characterized by having a composition comprising 5.0-7.0 wt% of al, 4.0-6.0 wt% of Ta, 1.1-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co, and 4.1-14.0 wt% of Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities.
  • the Ni-based single crystal super alloy of the present invention is characterized by having a composition comprising 5.0-7.0 wt% of Al, 4.0-6.0 wt% of Ta, 2.9-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Rc, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co and 4.1-14.0 wt% of Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities.
  • the Ni-based single crystal super alloy of the present invention is preferably having a composition comprising 5.9 wt% of Al, 5.9 wt% of Ta, 3.9 wt% of Mo, 5.9 wt% of W, 4.9 wt% of Re, 0.10 wt% of Hf, 2.9 wt% of Cr, 5.9 wt% of Co and 5.0 wt% of Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities, in the Ni-based single crystal super alloys previously described.
  • the creep endurance temperature at 137 MPa and 1000 hours can be made to be 1344 K (1071°C).
  • the Ni-based single crystal super alloy of the present invention is preferably having a composition comprising 5.8 wt% of Co, 2.9 wt% of Cr, 3.1 wt% of Mo, 5.8 wt% of W, 5.8 wt% of Al, 5.6 wt% of Ta, 5.0 wt% of Ru, 4.9 wt% of Re and 0.10 wt% of Hf in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities, in the Ni-based single crystal super alloys previously described.
  • the creep endurance temperature at 137 MPa and 1000 hours can be made to be 1366 K (1093 °C).
  • the Ni-based single crystal super alloy of the present invention is preferably having a composition comprising 5.8 wt% of Co, 2.9 wt% of Cr, 3.9 wt% of Mo, 5.8 wt% of W, 5.8 wt% of Al, 5.8 wt% (5.82 wt%) or 5.6 wt% of Ta, 6.0 wt% of Ru, 4.9 wt% of, Re and 0.10 wt% of Hf in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities, in the Ni-based single crystal super alloys previously described.
  • the creep endurance temperature at 137 MPa and 1000 hours can be made to be 1375 K (1102°C) or 1379 K(1106°C).
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.0-7.0 wt% of Al, 4.0-10.0 wt% of Ta, 1.1-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co, 10.0-14.0 wt% of Ru, 4.0 wt% or less of Nb, 2.0 wt% or less of Ti, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of Ce, 1 wt% or less of V and 0.1 wt% or less of Zr.
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.8-7.0 wt% of Al, 4.0-5.6 wt% of Ta, 3.3-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.9-4.3 wt% of Cr, 0-9.9 wt% of Co, 4.1-14.0 wt% of Ru, 4.0 wt% or less of Nb, 2.0 wt% or less of Ti, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0,1 wt% or less of Ce, 1 wt% or less of V and 0.1 wt% or less of Zr.
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.0-7.0 wt% of Al, 4.0-10.0 wt% of Ta, 1.1-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.9-5.0 wt% of Cr, 0-9.9 wt% of Co, 6.5-14.0 wt% of Ru, 4.0 wt% or less of Nb, 2.0 wt% or less of Ti, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of Ce, 1 wt% or less of V and 0.1 wt% or less of Zr.
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.0-7.0 wt% of Al, 4.0-6.0 wt% of Ta, 3.3-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co, 4.1-14.0 wt% of Ru, 4.0 wt% or less of Nb, 2.0 wt% or less of Ti, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of Ce, 1 wt% or less of V and 0.1 wt% or less of Zr.
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.0-7.0 wt% of Al, 4.0-5.6 wt% of Ta, 3.3-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 20-5.0 wt% of Cr, 0-9.9 wt% of Co, 4.1-14.0 wt% of Ru, 4.0 wt% or less of Nb, 2.0 wt% or less of Ti, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of Ce, 1 wt% or less of V and 0.1 wt% or less of Zr.
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.0-7.0 wt% of Al, 4.0-10.0 wt% of Ta, 3.1-4.5 wt% of Mo, 4.0-10.0 wt% ofW, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co, 4.1-14.0 wt% of Ru, 4.0 wt% or less of Nb, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of Ce,1 wt% or less of V and 0.1 wt% or less of Zr.
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.8-7.0 wt% of Al, 4.0-10.0 wt% of Ta, 3.1-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co, 4.1-14.0 wt% of Ru, 4.0 wt% or less of Nb, 2.0 wt% or less of Ti, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of o or less of Ce,1 wt% or less of V and 0.1 wt% or less of Zr.
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.0-7.0 wt% of Al, 4.0-10.0 wt% of Ta, 3.1-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0,50 wt% of Hf, 2.9-43 wt% of Cr, 0-9.9 wt% of Co, 4.1-14.0 wt% of Ru, 4.0 wt% or less of Nb, 2.0 wt% or less of Ti, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of Ce, 1 wt% or less of V and 0.1 wt% or less of Zr.
  • the above described Ni-based single crystal super alloy is more preferably having a composition comprising 5.0-7.0 wt% of Al, 4.0-10.0 wt% of Ta+Nb+Ti, 3.3-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co, 4.1-14.0 wt% of Ru, 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of Ce, 1 wt% or less of V and 0.1 wt% or less of Zr.
  • the Ni-based single crystal super alloy of the present invention is characterized by a2 ⁇ 0.999a1 when the lattice constant of the matrix is taken to be a1 and the lattice constant of the precipitation phase is taken to be a2 in the Ni-based single crystal super alloys previously described.
  • the relationship between a1 and a2 is such that a2 ⁇ 0.999a1 when the lattice constant of the matrix is taken to be a1 and the lattice constant of the precipitation phase is taken to be a2, and since the lattice constant a2 of the precipitation phase is -0.1% or less of the lattice constant a1 of the matrix, the precipitation phase that precipitates in the matrix precipitates so as to extent continuously in the direction perpendicular to the direction of the load.
  • strength at high temperatures can be enhanced without dislocation defects moving within the alloy structure under stress.
  • the lattice constant of the crystals of the precipitation phase a2 is 0.9965 or less of the lattice constant of the crystals of the matrix a1
  • Ni-based single crystal super alloy of the present invention is characterized by comprising the feature that the dislocation space of the alloy is 40 nm or less.
  • the present invention comprises an Ni-based single crystal super alloy having a composition comprising 5.0-7.0 wt % of Al, 4.0-10.0 wt % ofTa, 1.1-4.5 wt % of Mo, 4.0-10.0 wt % of W, 3.1-8.0 wt % of Re, 0-0.50 wt % of Hf, 2.0-5.0 wt % of Cr, 0.1-9.9 wt % of Co, 4.1-14.0 wt % of Ru, 0-2.0 wt% of Ti, 0-4.0 wt % ofNb, 0-0.05 wt% of B, 0-0.15 wt% of C, 0-0.1 wt % of Si, 0-0.1 wt % of Y, 0-0.1 wt% of La, 0-0.1 wt % of Ce, 0-1 wt % of V and 0-0.1 wt% of Zr in terms of its weight ratio, with the remainder consisting of Ni and unavoid
  • the above Ni-based single crystal super alloy is an alloy having a composition comprising 5.0-7.0 wt % of Al, 4.0-6.0 wt% of Ta, 1.1-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8-0 wt% of Re, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co and 4.1-14.0 wt% of Ru, with the remainder consisting of Ni and unavoidable impurities.
  • the above Ni-based single crystal super alloy is an alloy having a composition comprising 5.0-7.0 wt % of A1, 4.0-6.0 wt% of Ta, 2.9-4.5 wt% of Mo, 4.0-10.0 wt% of W, 3.1-8.0 wt% of Re, 0-0.50 wt% of Hf, 2.0-5.0 wt% of Cr, 0-9.9 wt% of Co and 4.1-14.0 wt% of Ru, with the remainder consisting of Ni and unavoidable impurities.
  • All of the above alloys have an austernite phase in the form of a ⁇ phase (matrix) and an intermediate regular phase in the form of a ⁇ ' phase (precipitation phase) that is dispersed and precipitated in the matrix.
  • the ⁇ ' phase is mainly composed of an intermetallic compound represented by Ni 3 Al, and the strength of the Ni-based single crystal super alloy at high temperatures is improved by this ⁇ ' phase.
  • the composite ratio of Cr is within the range of 2.0 wt% or more to 5.0 wt% or less, and more preferably 2.9 wt%. This ratio is more preferably within the range of 2.9 wt% or more to 5.0 wt% or less, more preferably within the range of 2.9 wt% or more to 4.3 wt% or less, and most preferably 2.9 wt%. If the composite ratio of Cr is less than 2.0 wt%, the desired high-temperature corrosion resistance cannot be secured, thereby making this undesirable. If the composite ratio of Cr exceeds 5.0 wt%, in addition to precipitation of the ⁇ ' phase being inhibited, harmful phases such as a ⁇ phase or ⁇ phase form that cause a decrease in strength at high temperatures, thereby making this undesirable.
  • Mo In addition to improving strength at high temperatures by dissolving into the matrix in the form of the ⁇ phase in the presence of W and Ta, Mo also improves strength at high temperatures due to precipitation hardening. Furthermore, Mo also improves the aftermentioned lattice misfit and dislocation space of the alloy which relate characteristics of this alloy.
  • the composite ratio of Mo is within the range of 1.1 wt% or more to 45 wt% or less, more preferably within the range of 2.9 wt% or more to 4.5 wt% or less. This ratio is more preferably within the range of 3.1 wt% or more to 4.5 wt% or less, more preferably within the range of 3.3wt% or more to 4.5 wt% or less, and most preferably 3.1 wt% or 39 wt%. If the composite ratio of Mo is less than 1.1 wt%, strength at high temperature cannot be maintained at the desired level, thereby making this undesirable. If the composite ratio of Mo exceeds 4.5 wt%, strength at high temperatures decreases, and corrosion resistance at high temperatures also decreases, thereby making this undesirable.
  • W improves strength at high temperatures due to the actions of solution hardening and precipitation hardening in the presence of Mo and Ta as previously mentioned.
  • the composite ratio of W is within the range of 4.0 wt% or more to 10.0 wt% or less, and most preferably 5.9 wt% or 5.8 wt%. If the composite ratio of W is less than 4.0 wt%, strength at high temperatures cannot be maintained at the desired level, thereby making this undesirable. If the composite ratio of W exceeds 10.0 wt%, high-temperature corrosion resistance decreases, thereby making this undesirable.
  • Ta improves strength at high temperatures due to the actions of solution hardening and precipitation hardening in the presence of Mo and W as previously mentioned, and also improves strength at high temperatures as a result of a portion of the Ta undergoing precipitation hardening relative to the ⁇ ' phase.
  • the composite ratio of Ta is within the range of 4.0 wt% or more to 10.0 wt% or less, more preferably within the range of 4.0 wt% more to 6.0 wt% or less. This ratio is more preferably within the range of 4.0 wt% or more to 5.6 wt% or less, and most preferably 5.6 wt% or 5.82 wt%.
  • the composite ratio of Ta is less than 4.0 wt%, strength at high temperatures cannot be maintained at the desired level, thereby making this undesirable. If the composite ratio of Ta exceeds 10.0 wt%, the ⁇ phase and ⁇ phase form that cause a decrease in strength at high temperatures, thereby making this undesirable.
  • Al improves strength at high temperatures by compounding with Ni to form an intermetallic compound represented by Ni 3 Al, which composes the ⁇ ' phase that finely and uniformly disperses and precipitates in the matrix, at a ratio of 60-70% in terms of volume percent.
  • the composite ratio of Al is within the range of 5.0 wt% or more to 7.0 wt% or less. This ratio is more preferably within the range of 5.8 wt% or more to 7.0 wt% or less, and most preferably 5.9 wt% or 5.8 wt%. If the composite ratio of Al is less than 5.0 wt%, the precipitated amount of the ⁇ ' phase becomes insufficient, and strength at high temperatures cannot be maintained at the desired level, thereby making this undesirable.
  • the composite ratio of Al exceeds 7.0 wt%, a large amount of a coarse ⁇ phase referred to as the eutectic ⁇ ' phase is formed, and this eutectic ⁇ ' phase prevents solution treatment and makes it impossible to maintain strength at high temperatures at a high level, thereby making this undesirable.
  • Hf is an element that segregates at the grain boundary and improves strength at high temperatures by strengthening the grain boundary as a result of being segregated at the grain boundary between the ⁇ phase and ⁇ ' phase.
  • the composite ratio of Hf is preferably within the range of 0.01 wt% or more to 0.50 wt% or less, and most preferably 0.10 wt%, If the composite ratio of Hf is less than 0.01 wt%, the precipitated amount of the ⁇ ' phase becomes insufficient and strength at high temperatures cannot be maintained at the desired level, thereby making this undesirable.
  • the composite ratio of Hf may be within the range of 0 wt% or more to less than 0.01 wt%, if necessary. Furthermore, if the composite ratio of Hf exceeds 0.50 wt%, local melting is induced which results in the risk of decreased strength at high temperatures, thereby making this undesirable.
  • Co improves strength at high temperatures by increasing the solution limit at high temperatures relative to the matrix such as Al and Ta, and dispersing and precipitating a fine ⁇ ' phase by heat treatment.
  • the composite ratio of Co is within the range of 0.1 wt% or more to 9.9 wt% or less, and most preferably 5.8 wt%, If the composite ratio of Co is less than 0.1 wt%, the precipitated amount of the ⁇ ' phase becomes insufficient and the strength at high temperatures cannot be maintained, thereby making this undesirable.
  • the composite ratio of Co may be within the range if 10 wt% or more to less than 0.1 wt%, if necessary.
  • the composite ratio of Re is within the range of 3.1 wt% or more to 8.0 wt% or less, and most preferably 4.9 wt%. If the composite ration of Re is less than 3.1 wt%, solution strengthening of the ⁇ phase becomes insufficient and strength at high temperatures cannot be maintained at the desired level, thereby making this undesirable. If the composite ratio of Re exceeds 8.0%, the TCP phase precipitates at high temperatures and strength at high temperatures cannot be maintained at a high level, thereby making this undesirable.
  • the composite ratio of Ru is within the range of 4.1 wt% or more to 14.0 wt% or less. This ratio is more preferably within the range of 10.0 wt% or more to 14.0 wt% or less, or preferably within the range of 6.5 wt% or more to 14.0 wt% or less, and most preferably 5.0 wt%, 6.0 wt% or 7.0 wt%. If the composite ratio of Ru is less than 1.0 wt%, the TCP phase precipitates at high temperatures and strength at high temperatures cannot be maintained at a high level, thereby making this undesirable.
  • the composite ratio of Ru is less than 4.1 wt%, strength at high temperatures decreases compared to the case when the composite ratio of Ru is 4.1 wt% or more. Furthermore, if the composite ratio of Ru exceeds 14.0 wt%, the ⁇ phase precipitates and strength at high temperatures deceases which is also undesirable.
  • the composite ratios of Al, Ta, Mo, W, Hf, Cr, Co and Ni to the optimum ratios, together with setting the aftermentioned lattice misfit and dislocation space of the alloy which are calculated from the lattice constant of the ⁇ phase and the lattice constant of the ⁇ ' phase within their optimum ranges, strength at high temperatures is improved, and precipitation of the TCP phase can be inhibited by adding Ru.
  • the composite ratios of Al, Cr, Ta and Mo to the aforementioned ratios, the production cost for the alloy can be decreased.
  • relative strength of the alloy can be increased and the lattice misfit and dislocation space of the alloy can be adjusted to the optimum value.
  • lattice constant a2 of the crystals of the precipitation phase is preferably -0.1% or less lattice constant a1 of the crystals of the matrix.
  • the lattice constant of the crystals of the precipitation phase a2 is 0.9965 or less of the lattice constant of the crystals of the matrix a1.
  • the above-described relationship between a1 and a2 becomes a2 ⁇ 0.9965a1.
  • the percentage of the lattice constant a2 relative to the lattice constant a1 is called "lattice misfit".
  • the composition of the composite element that compose the Ni-based single crystal super alloy is suitably adjusted.
  • FIG.1 shows a relationship between the lattice misfit of the alloy and the time until the alloy demonstrates creep rupture (creep rupture life).
  • the preferable value of the lattice misfit is determined to - 0.35 or lower.
  • the composition of Mo is maintained to a high level, and the composition of the other composite elements is suitably adjusted.
  • Ti can be further included in the above Ni-based super crystal super alloy.
  • the composite ratio of Ti is within the range of 0 wt% or more to 2.0 wt% or less. If the composite ratio of Ti exceeds 2.0 wt%, the harmful phase precipitates and the strength at high temperatures cannot be maintained, thereby making this undesirable.
  • Nb can be further included in the above Ni-based super crystal super alloy.
  • the composite ratio of Nb is within the range of 0 wt% or more to 4.0 wt% or less. If the composite ratio of Nb exceeds 4.0 wt%, the harmful phase precipitates and the strength at high temperatures cannot be maintained, thereby making this undesirable.
  • strength at high temperatures can be improved by adjusting the total composite ratio of Ta, Nb and Ti (Ta+Nb+Ti) within the range of 4.0 wt% or more to 10.0 wt% or less.
  • B, C, Si, Y, La, Ce, V and Zr and the like can be included in the above Ni-based super crystal super alloy, for example.
  • the alloy includes at least one of elements selected from B, C, Si, Y, La, Ce, V and Zr
  • the composite ratio of each element is 0.05 wt% or less of B, 0.15 wt% or less of C, 0.1 wt% or less of Si, 0.1 wt% or less of Y, 0.1 wt% or less of La, 0.1 wt% or less of Ca, 1 wt% or less of V and 0.1 wt% or less of Zr. If the composite ratio of each element exceeds the above range, the harmful phase precipitates and the strength at high temperatures cannot be maintained, thereby making this undesirable.
  • a dislocation space of the alloy is 40 nm or less.
  • the reticulated dislocation (displacement of atoms which are connected as a line) in the alloy is called dislocation networks, and a space between adjacent reticulations is called "dislocation space".
  • FIG. 2 shows a relationship between the dislocation space of the alloy and the time until the alloy demonstrates creep rupture (creep rupture life).
  • the preferable value of the dislocation space is determined to 40 nm or lower.
  • the composition of Mo is maintained to a high level, and the composition of the other composite elements is suitably adjusted.
  • FIG. 3 is a transmission electron microgram of the Ni-based single crystal super alloy showing an embodiment (aftermentioned embodiment 3) of the dislocation networks and dislocation space of the Ni-based single crystal super alloy of the present invention. As shown in FIG. 3 , in case of the Ni-based single crystal super alloy of the present invention, the dislocation space is 40 nm or lower.
  • Ni-based single crystal super alloys may cause reverse partitioning, however, in Ni-based single crystal super alloy of the present invention does not cause reverse partitioning.
  • solution treatment and aging treatment were performed on the alloy ingots followed by observation of the state of the alloy structure with a scanning electron microscope (SEM).
  • Solution treatment consisted of holding for 1 hour at 1573K (1300°C) followed by heating to 1613K (1340°C) and holding for 5 hours.
  • aging treatment consisted of consecutively performing primary aging treatment consisting of holding for 4 hours at 1273K-1423K (1000°C -1150°C) and secondary aging treatment consisting of holding for 20 hours at 1143K (870°C).
  • reference example 5 having a composition of 4.0 wt% of Ru, embodiments 1, 2, 4, 9, 10 and 11 having a composition approximately 5.0 wt% of Ru, embodiments 3, 12 and 13 having a composition of 6.0 wt% of Ru, and embodiment 14 having a composition of 7.0 wt% of Ru, were determined to have high strength at high temperature.
  • samples of reference examples 1-6 and embodiments 1-14 were determined to have a high withstand temperature (1356K (1083°C)) equal to or greater than the alloys of the prior art (comparative Examples 1-5).
  • samples of reference examples 1-6 and embodiments 1-14 were determined to have a high withstand temperature (embodiment 1:1344K (1071°C), embodiment 2: 1366K (1093°C), embodiment 3:1375K (1102°C), embodiment 4: 1372K (1099°C), embodiment 5: 1379K (1106°C), embodiment 6: 1349K (1076°C), embodiment 7: 1379K (1106°C), embodiment 8: 1363K (1090°C), embodiment 9: 1358K (1085°C), embodiment 10: 1362K (1089°C), embodiment 11: 1361K (1088°C), embodiment 12: 1363K (1090°C), embodiment 13: 1366K (1093°C) and embodiment 14:1384K (1111°C)).
  • this allow has a higher heat resistance temperature than Ni-based single crystal super alloys of the prior art, and was determined to have high strength even at high temperatures.
  • the composite ratio of Ru is preferably be determined to a range so as to keep the balance against the composition of the other composite elements is suitably adjusted (4.1 wt% or more to 14.0 wt% or less, for example).

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  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat Treatment Of Sheet Steel (AREA)
EP03777308A 2002-12-06 2003-12-05 Ni-BASE SINGLE CRYSTAL SUPERALLOY Expired - Lifetime EP1568794B1 (en)

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CN107034388A (zh) * 2017-03-17 2017-08-11 泰州市金鹰精密铸造有限公司 镍基单晶高温合金涡轮叶片的制备工艺
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CN111961920B (zh) * 2020-08-09 2022-02-11 浙江大学 一种高承温能力的镍基单晶高温合金及其制备方法
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CA2508698A1 (en) 2004-06-24
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JPWO2004053177A1 (ja) 2006-04-13
AU2003289214A1 (en) 2004-06-30
WO2004053177A1 (ja) 2004-06-24
JP3814662B2 (ja) 2006-08-30
EP1568794A4 (en) 2006-11-02
CA2508698C (en) 2012-05-15
AU2003289214A8 (en) 2004-06-30
CN1745186A (zh) 2006-03-08
US20060011271A1 (en) 2006-01-19
DE60326083D1 (de) 2009-03-19

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