WO2004053177A1 - Ni基単結晶超合金 - Google Patents
Ni基単結晶超合金 Download PDFInfo
- Publication number
- WO2004053177A1 WO2004053177A1 PCT/JP2003/015619 JP0315619W WO2004053177A1 WO 2004053177 A1 WO2004053177 A1 WO 2004053177A1 JP 0315619 W JP0315619 W JP 0315619W WO 2004053177 A1 WO2004053177 A1 WO 2004053177A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- weight
- less
- single crystal
- based single
- crystal superalloy
- Prior art date
Links
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%
Definitions
- the present invention relates to a Ni-based single crystal superalloy, and more particularly to an improvement of a Ni-based single crystal superalloy for improving creep characteristics. Ming background technology
- Typical compositions of Ni-based single crystal superalloys that have been developed as materials for moving and stationary blades at high temperatures such as aircraft and gas turbines include those shown in Table 1, for example.
- Ni-based single crystal superalloy after performing a solution treatment at a predetermined temperature, an aging treatment is performed to obtain a Ni-based single crystal superalloy.
- This alloy is called a so-called precipitation hardening type alloy, and has a form in which a ⁇ 'phase as a precipitated phase is precipitated in an a phase as a mother phase.
- CMSX-2 Cannon Muskegon, see US Patent No. 4,582,548 is a first-generation alloy
- CMSX-4 Cannon Muskegon, US Patent No. No. 4, 643, 782
- Rene 'N6 General Electric, U.S. Pat. No. 5,455,120
- CMS X-10K Cannon's Muskegon, U.S. Pat. No. 5,366,695 is a third-generation alloy
- 3B (manufactured by General Electric, U.S. Pat. 1, 249) is called the fourth generation alloy.
- first-generation alloy CMS X-2 and second-generation alloy CMS X-4 have the same cleave strength at low temperatures, but have a eutectic 7 'phase even after high-temperature solution treatment. Remains in large amounts, and its creep strength at high temperatures is inferior to that of third-generation alloys.
- the third-generation Rene 'N6 and CMS X-10K are alloys intended to improve creep strength at higher temperatures than second-generation alloys.
- the composition ratio of Re (5% by weight or more) exceeds the amount of Re dissolved in the parent phase ( ⁇ phase)
- the excess Re combines with other elements to form so-called TCP at high temperatures.
- a phase Topicologically Close Packed phase
- the present invention has been made in view of the above circumstances, and an object of the present invention is to provide a Ni-based single crystal superalloy capable of preventing the precipitation of a TCP phase at a high temperature and improving the strength. . Disclosure of the invention
- the present invention has the following configuration.
- the components are as follows: A1: 5.0% by weight or more 7.
- Ta 4.0% by weight or more and 10.0% by weight or less
- Mo 1.1% by weight or more and 4.5% by weight or less
- W 4.0% by weight or more and 10.0% by weight or less
- Re 3.1% to 8.0% by weight
- Hf 0% to 0.50% by weight
- Cr 2.
- the components are, by weight, A1: 5.0 to 7.0 wt%, Ta: 4.0 to 6.0 wt%, , Mo: 1.1 single % To 4.5 wt% or less, W: 4.0 wt% to 10.0 wt%, Re: 3.1 wt% to 8.0 wt%, Hf: 0 wt% to 0.50 %
- Cr 2.0% by weight or more and 5.0% by weight or less
- Co 0% by weight or more and 9.9% by weight or less
- Ru 4.1% by weight or more and 14.0% by weight or less
- the balance is characterized by having a composition consisting of Ni and unavoidable impurities.
- the components are, by weight, A1: 5.0 to 7.0 wt%, Ta: 4.0 to 6.0 wt%, , Mo: 2.9% by weight or more and 4.5% by weight or less, W: 4.0% by weight or more and 10.0% by weight or less, Re: 3.1% by weight or more and 8.0% by weight or less, Hf: 0% to 0.50% by weight, Cr: 2.0% to 5.0% by weight, Co: 0% to 9.9% by weight, Ru: 4.1% to 14.%
- the composition is characterized by containing 0% by weight or less, with the balance being Ni and unavoidable impurities.
- the addition of Ru suppresses the precipitation of the TCP phase, which causes a decrease in strength, when used at a high temperature.
- the lattice constant of the parent phase ( ⁇ phase) and the lattice constant of the precipitated phase ( ⁇ , phase) can be optimized. . These make it possible to improve the strength at high temperatures.
- the composition ratio of Ru is 4.1% by weight or more and 14.0% by weight or less, the precipitation of the TCP phase, which causes a decrease in creep strength at the time of use at a high temperature, is suppressed.
- the components are expressed by weight as follows: A1: 5.9% by weight, Ta: 5.9% by weight, Mo: 3.9% by weight, W: 5.9% by weight. % By weight, Re: 4.9% by weight, Hf: 0.10% by weight, Cr: 2.9% by weight, Co: 5.9% by weight, Ru: 5.0% by weight, the balance Preferably have a composition consisting of Ni and unavoidable impurities.
- the creep durability temperature at 137 MPa and 1000 hours can be 1344 K (1071 ° C).
- the components are expressed by weight as follows: Co: 5.8% by weight, Cr: 2.9% by weight, Mo: 3.1% by weight, W: 5. 8% by weight, A1: 5.8% by weight, Ta: 5.6% by weight, Ru: 5.0% by weight, Re: 4.9% by weight, Hf: Desirably, the composition contains 0.1% by weight and the balance is composed of Ni and unavoidable impurities. '
- the creep durability temperature at 137 MPa and 1000 hours can be 1366 K (1093 ° C).
- the components are expressed by weight as follows: Co: 5.8% by weight, Cr: 2.9% by weight, Mo: 3.9% by weight, W: 5. 8% by weight, A1: 5.8% by weight, Ta: 5.8% by weight (5.82% by weight) or 5.6% by weight, Ru: 6.0% by weight, Re: 4.9% by weight, It is desirable that Hf: 0.10% by weight be contained and the balance be composed of Ni and unavoidable impurities.
- the creep durability temperature at 137 MPa and 1000 hours can be 1375 K (1102 ° C) or 1379 K (1106 ° C).
- Ni-based single crystal superalloy described above may further contain Ti in a weight ratio of 0% to 2.0% by weight.
- Nb in a weight ratio of 0% to 4.0% by weight may be further contained.
- Ni-based single crystal superalloy may include at least one of B, C, Si, Y, La, Ce, V, and Zr.
- the individual components are, by weight, B: 0.05% by weight or less, C: 0.15% by weight or less, Si: 0.1% by weight or less, Y: 0.1% by weight or less, La: 0.1% by weight or less, Ce: 0.1% by weight or less, V: 1% by weight or less, Zr: 0.1% by weight or less.
- the components are more desirably in a weight ratio: A 1: 5.0% by weight to 7.0% by weight, Ta: 4.0% by weight to 10% by weight. 0.0% by weight or less, Mo: 1.1% by weight or more and 4.5% by weight or less, W: 4.0% by weight or more and 10.0% by weight or less, Re: 3.1% by weight or more and 8.0% by weight or less , Hf: 0% to 0.50% by weight, Cr: 2.0% to 5.0% by weight, Co: 0% to 9.9% by weight, Ru: 10.0% by weight or more 14.0% by weight or less, Nb: 4.0% by weight or less, Ti: 2.0% by weight or less, B: 0.05% by weight or less, C: 0.15% by weight %, S: 0.1% by weight, Y: 0.1% by weight, La: 0.1% by weight, Ce: 0.1% by weight, V: 1% by weight, Z r: has a composition of 0.1% by weight or less.
- the components are more desirably in a weight ratio: A 1: 5.8% by weight to 7.0% by weight, Ta: 4.0% by weight to 5% by weight. 6% by weight or less, Mo: 3.3% by weight or more and 4.5% by weight or less, W: 4.0% by weight or more and 10.0% by weight or less, Re: 3.1% by weight or more and 8.0% by weight or less , Hf: 0% to 0.50% by weight, Cr: 2.9% to 4.3% by weight, Co: 0% to 9.9% by weight, Ru: 4.1% by weight 14.0% by weight or less, Nb: 4.0% by weight or less, Ti: 2.0% by weight or less, B: 0.05% by weight or less, C: 0.15% by weight or less, Si: 0 1 wt% or less, Y: 0.1 wt% or less, La: 0.1 wt% or less, Ce: 0.1 wt% or less, V: 1 wt% or less, Zr:
- the components are more desirably in a weight ratio: A 1: 5.0% by weight to 7.0% by weight, Ta: 4.0% by weight to 10% by weight. 0 wt% or less, Mo: l.
- the components are, by weight, A 1: 5.0% by weight to 7.0% by weight, and Ta: 4.0% by weight to 6% by weight. 0.0% by weight or less, Mo: 3.3% by weight or more and 4.5% by weight or less, W: 4.0% by weight or more and 10.0% by weight or less, Re: 3.1% by weight or more and 8.0% by weight or less , Hf: 0% to 0.50% by weight, Cr: 2.0% to 5.0% by weight, Co: 0% to 9.9% by weight, Ru: 4.1% by weight More than 14.0% by weight, Nb: 4.0 weight %, T: 2.0% by weight or less, B: 0.05% by weight or less, C: 0.15% by weight or less, Si: 0.1% by weight or less, Y: 0.1% by weight or less , La: 0.1% by weight or less, Ce: 0.1% by weight or less, V: 1% by weight or less, Zr: 0.1% by weight or less.
- Ni-based single crystal superalloy described above is more desirably composed of components by weight: A 1: 5.0% by weight to 7.0% by weight, Ta: 4.0% by weight to 5% by weight. 6% by weight or less, Mo: 3.3% by weight or more and 4.5% by weight or less, W: 4.0% by weight or more and 10.0% by weight or less, Re: 3.1% by weight or more and 8.0% by weight or less Hf: 0% to 0.50% by weight, Cr: 2.0% to 5.0% by weight, Co: 0% to 9.9% by weight, Ru: 4.1% by weight % To 14.0% by weight, Nb: 4.0% by weight or less, Ti: 2.0% by weight or less, B: 0.05% by weight or less, C: 0.15% by weight or less, Si: 0.1 wt% or less, Y: 0.1 wt% or less, La: 0.1 wt% or less, Ce: 0.1 wt% or less, V: 1 wt% or less, Zr: 0.1 wt% It
- the components are more desirably in a weight ratio: A 1: 5.0% by weight to 7.0% by weight, Ta: 4.0% by weight to 10% by weight. 0.0 wt% or less, Mo: 3.1 wt% to 4.5 wt%, W: 4.0 wt% to 10.0 wt%, Re: 3.1 wt% to 8.0 wt% , Hf: 0% to 0.50% by weight, Cr: 2.0% to 5.0% by weight, Co: 0% to 9.9% by weight, Ru: 4.1% by weight 14.0% by weight or less, Nb: 4.0% by weight or less, B: 0.05% by weight or less, C: 0.15% by weight or less, Si: 0.1% by weight or less, Y: 0. 1% by weight or less, La: 0.1% by weight or less, Ce: 0.1% by weight or less, V: 1% by weight or less, Zr: 0.1% by weight or less.
- the components are more desirably in a weight ratio: A 1: 5.8% by weight or more and 7.0% by weight or less, Ta: 4.0% by weight or more; L 0.0% by weight or less, Mo: 3.1% by weight or more 4.5% by weight, W: 4.0% by weight or more 10.0% by weight or less, Re: 3.1% by weight or more 8.0% by weight %, Hf: 0% to 0.5% by weight, Cr: 2.0% to 5.0% by weight, Co: 0% to 9.9% by weight, Ru: 4.1% by weight % To 14.0% by weight, Nb: 4.0 weight %, T: 2% by weight, B: 0.05% by weight, C: 0.15% by weight, Si: 0.1% by weight, Y: 0.1% by weight, La: 0.1% by weight or less, Ce: 0.1% by weight or less, V: 1% by weight or less, Zr: 0.1% by weight or less.
- the components are more desirably in a weight ratio: A 1: 5.0% by weight to 7.0% by weight, Ta: 4.0% by weight to 10% by weight. 0.0% by weight or less, Mo: 3.1% by weight or more and 4.5% by weight or less, W: 4.0% by weight or more and 10.0% by weight or less, Re: 3.1% by weight or more and 8.0% by weight or less , Hf: 0% to 0.50% by weight, Cr: 2.9% to 4.3% by weight, Co: 0% to 9.9% by weight, Ru: 4.1% by weight or more 14.0% by weight or less, Nb: 4.0% by weight or less, Ti: 2% by weight or less, B: 0.05% by weight or less, C: 0.15% by weight or less, Si: 0.1 % By weight, Y: 0.1% by weight, La: 0.1% by weight, Ce: 0.1% by weight, V: 1% by weight, Zr: 0.1% by weight or less Have
- the Ni-based single crystal superalloy of the present invention is more desirably composed of components in a weight ratio of A1: 5.0 wt% or more and 7.0 wt% or less, and Ta + Nb + Ti: 4.0. Weight% or more 10.0% by weight or less, Mo: 3.3% by weight or more and 4.5% by weight or less, W: 4.0% by weight or more and 10.0% by weight or less, Re: 3.1% by weight or more 8 0.0% by weight or less, Hf: 0% by weight or more and 0.50% by weight or less, Cr: 2.0% by weight or more and 5.0% by weight or less, Co: 0% by weight or more and 9.9% by weight or less, Ru: 4.
- Ni-base single crystal superalloy of the present invention is the Ni-base single crystal superalloy described above, wherein a2 is a lattice constant of a mother phase and a2 is a lattice constant of a precipitated phase. ⁇ 0.999 al.
- the lattice constant of the mother phase is al and the lattice constant of the precipitated phase is a2
- the relationship between al and a2 is a2 ⁇ 0.999 al. Is less than 0.1% of the lattice constant al of the matrix
- the precipitated phase is precipitated so as to extend continuously in the direction perpendicular to the load direction, and dislocation defects are less likely to move in the alloy structure under stress.
- the strength at high temperatures can be increased as compared with the conventional Ni-based single crystal superalloy.
- the lattice constant a2 of the crystal of the precipitated phase is set to 0.9965 or less, which is the lattice constant al of the crystal of the mother phase.
- the Ni-based single crystal superalloy of the present invention is characterized in that the transition network spacing in the alloy is 40 nm or less.
- FIG. 1 is a diagram showing the relationship between lattice misfit and creep life.
- FIG. 2 is a diagram showing the relationship between the transition network interval and the creep life.
- FIG. 3 is a transmission electron micrograph of the Ni-based single crystal superalloy, illustrating the transition network of the Ni-based single crystal superalloy of the present invention and the spacing therebetween.
- the Ni-based single crystal superalloy of the present invention contains components such as Al, Ta, Mo, W, Re, Hf, Cr, Co, and Ru, and Ni (remainder), and further contains unavoidable impurities. Alloy.
- Ni-based single crystal superalloy has, for example, a composition ratio of A1: 5.0% by weight to 7.0% by weight, Ta: 4.0% by weight to 10.0% by weight, and Mo: 1%. 1 wt% or more 4.5 wt% or less, W: 4.0 wt% or more and 10.0 wt% or less, Re: 3.1 wt% or more 8.0 wt% or less, Hf: 0 wt% Not less than 0.50% by weight, Cr: 2.
- the Ni-based single crystal superalloy described above has, for example, a composition ratio of A1: 5.0 wt% to 7.0 wt%, Ta: 4.0 wt% to 6.0 wt%, : l. 1% by weight or more and 4.5% by weight or less, W: 4.0% by weight or more: L 0.0% by weight or less, Re: 3.1 Hf: 0 to 0.5% by weight, Cr: 2.0 to 5.0% by weight, Co: 0 to 9.9% by weight
- Ru is an alloy containing from 4.1% by weight to 14.0% by weight, with the balance being Ni and unavoidable impurities.
- the Ni-based single crystal superalloy described above has, for example, a composition ratio of A1: 5.0% by weight to 7.0% by weight, Ta: 4.0% by weight to 6.0% by weight, and Mo: : 2.9% by weight or more 4.5% by weight or less, W: 4.0% by weight or more and 10.0% by weight or less, Re: 3.1% by weight or more and 8.0% by weight or less, Hf: 0% by weight or more 0.5% by weight or less, Cr: 2.0% by weight or more and 5.0% by weight or less, Co: 0% by weight or more and 9.9% by weight or less, Ru: 4.1% by weight or more and 14.0% by weight or less Is an alloy containing Ni and inevitable impurities.
- Each of the above alloys has an ⁇ -phase (matrix), which is an austenite phase, and an ⁇ ′ phase (precipitation phase), which is an intermediate ordered phase dispersed and precipitated in the matrix.
- the r ′ phase is mainly composed of an intermetallic compound represented by Ni 3A1, and the high temperature strength of the Ni-based single crystal superalloy is improved by the ⁇ ′ phase.
- Cr is an element having excellent resistance to oxidation and improves the high-temperature corrosion resistance of a Ni-based single crystal superalloy.
- the composition ratio of Cr is preferably Cr: 2.0% by weight or more and 5.0% by weight or less, more preferably 2.9% by weight or more and 5.0% by weight or less, and 2.9% by weight or more.
- the range is more preferably 4.3% by weight or less, and most preferably 2.9% by weight.
- composition ratio of Cr is less than 2.0% by weight, the desired high-temperature corrosion resistance cannot be ensured, which is not preferable. If the composition ratio of Cr exceeds 5.0% by weight, the precipitation of a and phase is suppressed. In addition, harmful phases such as the ⁇ phase and the phase are formed and the high-temperature strength is reduced, which is not preferable.
- Mo in the coexistence with W and Ta, forms a solid solution in the matrix a phase, which increases the high-temperature strength, and also contributes to the high-temperature strength by precipitation hardening. Mo greatly contributes to the lattice misfit and dislocation network spacing (described later), which are characteristics of this alloy.
- the composition ratio of Mo is preferably in the range of 1.1% to 4.5% by weight, more preferably 2.9% to 4.5% by weight, and more preferably 3.1% to 4.5%. weight%
- composition ratio of Mo is less than 1.1% by weight, the desired high-temperature strength cannot be ensured, which is not preferable.
- composition ratio of Mo exceeds 4.5% by weight, the high-temperature strength decreases, and Is not preferred because the high-temperature corrosion resistance also decreases.
- W improves the high-temperature strength by the action of solid solution strengthening and precipitation hardening in the presence of Mo and Ta as described above.
- composition ratio of W is preferably in the range of 4.0% by weight to 10.0% by weight, and most preferably 5.9% by weight or 5.8% by weight.
- composition ratio of W is less than 4.0% by weight, the desired high-temperature strength cannot be ensured, so that it is not preferable. If the composition ratio of W exceeds 10.0% by weight, the high-temperature corrosion resistance is lowered, so that it is preferable. Absent.
- T a improves the high-temperature strength by the action of solid solution strengthening and precipitation hardening in the co-presence of Mo and Mo as described above, and partially precipitates and hardens the ⁇ ′ phase. And improve high temperature strength.
- the composition ratio of Ta is preferably in the range of 4.0% by weight to 10.0% by weight, more preferably in the range of 4.0% by weight to 6.0% by weight, and more preferably 4.0% by weight or more.
- the range of 6% by weight or less is more preferable, and the range of 5.6% by weight or 5.82% by weight is most preferable.
- composition ratio of Ta is less than 4.0% by weight, a desired high-temperature strength cannot be ensured, so that it is not preferable. If the composition ratio of Ta exceeds 10.0% by weight, a ⁇ phase or a phase is generated. This is undesirable because the high-temperature strength is reduced.
- a 1 is combines with N i, ⁇ to finely uniformly dispersed and precipitated in the matrix phase, an intermetallic compound represented by N i 3 A 1) constituting a phase, 60% to 70% by volume fraction To improve high temperature strength.
- composition ratio of A1 is preferably in a range of 5.0% by weight to 7.0% by weight, more preferably in a range of 5.8% by weight to 7.0% by weight, and is preferably 5.9% by weight or 5. Most preferably, it is 8% by weight.
- composition ratio of A1 is less than 5.0% by weight, the precipitation amount of the ⁇ 'phase becomes insufficient. It is not preferable because the desired high-temperature strength cannot be secured. If the composition ratio of A1 exceeds 7.0% by weight, a large number of coarse ⁇ phases called eutectic ⁇ ′ phases are formed, and the solution treatment becomes impossible. However, it is not preferable because high temperature strength cannot be secured.
- Hf is a segregation element at the grain boundaries, and is localized at the grain boundaries of the r phase and the a ′ phase to strengthen the grain boundaries, thereby improving the high-temperature strength.
- composition ratio of Hf is preferably in the range of 0.01% by weight to 0.50% by weight, and most preferably 0.10% by weight.
- the composition ratio of No. 11 is less than 0.01% by weight, the precipitation amount of the ⁇ 'phase becomes insufficient, and the desired high-temperature strength cannot be ensured.
- the composition ratio of Hf may be 0% by weight or more and less than 0.01% by weight.
- the composition ratio of Hf exceeds 0.50% by weight, local melting may be caused to lower the high-temperature strength, which is not preferable.
- Co increases the solid solution limit of Al, Ta, etc. in a parent phase at high temperatures, and disperses and precipitates a fine ⁇ -phase by heat treatment, thereby improving high-temperature strength.
- the Co composition ratio is preferably in the range of 0.1% by weight to 9.9% by weight, and most preferably 5.8% by weight.
- the composition ratio of ⁇ 0 is less than 0.1% by weight, the precipitation amount of the ⁇ 'phase becomes insufficient, and the desired high-temperature strength cannot be ensured.
- the composition ratio of Co may be 0% by weight or more and less than 0.1% by weight. If the Co composition ratio exceeds 9.9% by weight, the balance with other elements such as Al, Ta, Mo, W, Hf, and Cr will be lost, and harmful phases will precipitate to lower the high-temperature strength. Is not preferred.
- Re forms a solid solution in the ⁇ phase, which is a parent phase, and improves high-temperature strength by solid solution strengthening. It also has the effect of improving corrosion resistance.
- a harmful TCP phase may precipitate at high temperatures, and the high-temperature strength may decrease.
- composition ratio of Re is preferably in the range of 3.1% by weight to 8.0% by weight, and most preferably 4.9% by weight.
- composition ratio of Re is less than 3.1% by weight, the solid solution strengthening of the ⁇ phase is insufficient, and the desired high-temperature strength cannot be secured. Exceeding this is preferred because the TCP phase precipitates at high temperatures, making it impossible to ensure high high-temperature strength. Difficult 15619
- Ru suppresses the precipitation of the TCP phase, thereby improving the high-temperature strength.
- composition ratio of Ru is in the range from 4.1% by weight to 14.0% by weight, or in the range from 10.0% by weight to 14.0% by weight, or in the range from 6.5% by weight to 14.0% by weight.
- the following range is preferable, and most preferably 5.0% by weight, 6.0% by weight or 7.0% by weight.
- composition ratio of No. 11 is less than 1.0% by weight, a TCP phase is precipitated at a high temperature, and high high-temperature strength cannot be secured. Further, when the composition ratio of Ru is less than 4.1% by weight, the high-temperature strength is lower than when the composition ratio of Ru is 4.1% by weight or more. On the other hand, if the composition ratio of Ru exceeds 14.0% by weight, the ⁇ phase precipitates and the high-temperature strength decreases, which is not preferable.
- the lattice constant of the a-phase and the lattice constant of the a′-phase can be adjusted.
- the calculated lattice misfit and dislocation network spacing (described below) are set in optimal ranges to improve the high-temperature strength, and by adding Ru, the precipitation of the TCP phase can be suppressed.
- the composition ratio of A1, Cr, Ta, and Mo as described above, the production cost of the alloy can be reduced.
- the lattice constant of the crystal constituting the mother phase, a is defined as al, and the ⁇ 'phase, which is a precipitated phase, is formed.
- the lattice constant of the crystal is a2
- the relationship between al and a2 is a2 ⁇ 0.999 al. That is, it is preferable that the lattice constant a2 of the crystal of the precipitated phase is equal to or less than 0.1% of the lattice constant a1 of the crystal of the mother phase.
- the lattice constant a2 of the crystal of the precipitated phase is not more than 0.9965 which is the lattice constant al of the crystal of the mother phase.
- the relationship between al and a2 described above is a2 ⁇ 0.9955 al.
- the percentage of the lattice constant a2 of the crystal of the precipitated phase to the lattice constant al of the crystal of the mother phase is referred to as “lattice misfit”.
- the lattice constants of the two have such a relationship, when the precipitated phase is precipitated in the parent phase by the heat treatment, the precipitated phase is deposited so as to extend continuously in the direction perpendicular to the load direction. Therefore, dislocation defects are less likely to move in the alloy structure under stress, and the creep strength is increased.
- Figure 1 shows the relationship between lattice misfit and the time until creep rupture of the alloy (creep life).
- a more preferable lattice misfit is set to 0.35 or less. In order to reduce the lattice misfit to less than 0.35, it is necessary to adjust the composition ratio of other constituent elements while keeping the composition ratio of Mo high.
- the addition of Ru suppresses the precipitation of the TCP phase, which causes a decrease in creep strength, when used at high temperatures.
- the lattice constant of the mother phase (r phase) and the lattice constant of the precipitated phase ( ⁇ 'phase) can be set to optimal values. Will be possible. As a result, the cleave strength at high temperatures can be improved.
- the above-mentioned Ni-based single crystal superalloy may further contain Ti.
- the composition ratio of Ti is preferably in a range from 0% by weight to 2.0% by weight. When the composition ratio of Ti exceeds 2.0% by weight, a harmful phase is precipitated and the high-temperature strength is reduced, which is not preferable.
- the above-mentioned Ni-based single crystal superalloy may further contain Nb.
- the composition ratio of Nb is preferably 0% by weight or more and 4.0% by weight or less. If the composition ratio of Nb exceeds 4.0% by weight, it is not preferable because a harmful phase is precipitated and the high-temperature strength is reduced.
- the high-temperature strength can also be improved by setting the composition ratio of Ding &, ⁇ , and 1 ⁇ to be 4.0% by weight or more and 10.0% by weight or less in total (Ta + Nb + Ti). It can be done.
- Ni-based single crystal superalloy may contain, for example, B, C, Si, Y, La, Ce, V, Zr, etc., in addition to the inevitable impurities.
- the composition ratios of the various components are as follows: B: 0.05% by weight or less, C: 0.15% by weight or less, S: i: 0.1% by weight or less, Y: 0.1% by weight or less, La: 0.1% by weight or less, Ce: 0.1% by weight or less, V: 1% by weight or less, Zr: 0 It is preferably at most 1% by weight. If the composition ratio of the individual components exceeds the above range, a harmful phase is precipitated and the high-temperature strength decreases, which is not preferable. In the above-mentioned Ni-based single crystal superalloy, it is desirable that the transition network spacing in the alloy is 40 nm or less.
- the transition network indicates dislocations (displacements of atoms connected in a line) formed in a network in the alloy.
- the spacing between the meshes is defined as a dislocation network spacing.
- Fig. 2 shows the relationship between the transition network spacing and the time until the alloy breaks the clip (creep life).
- the creep life satisfies the required value (the value indicated by the dotted line on the vertical axis of the figure) if the distance between the dislocation networks is approximately 40 nm or less. Therefore, in the present invention, a preferable transition network spacing is set to 40 nm or less. In order to keep the transition network interval at 40 nm or less, it is necessary to adjust the composition ratio of other constituent elements while maintaining the composition ratio of Mo high.
- FIG. 3 is a transmission electron micrograph of the Ni-based single crystal superalloy illustrating the transition network and the interval of the Ni-based single crystal superalloy of the present invention (Example 3 described later).
- FIG. 3 shows that the Ni-based single crystal superalloy of the present invention has a transition network spacing of 40 nm or less.
- the conventional Ni-based single crystal superalloy includes an alloy that causes reverse distribution, but the Ni-based single crystal superalloy according to the present invention does not cause reverse distribution.
- the aging treatment consists of a primary aging treatment at 1273K to 1423K (1000 ° C to 1150 ° C) for 4 hours and a secondary aging treatment at 1143K (870 ° C) for 20 hours. went.
- Reference example 1 209.35 105.67 -0.39 Reference example 2 283.20 158.75 -0.40 Reference example 3 219.37 135.85 -0.56 Reference example 4 274.38 153.15 1 0 58 Reference Example 5 328.00 487.75 -0.58 Reference Example 6 203.15 -0.41
- Example 1 509.95 326.50 -0.60
- Example 2 420.60 753.95 — 0. 42
- Example 6 400.00-1.45
- Example 8 682.00 -0.63
- Example 9 550.00 -0.42
- Example 10 658.50 — 0.45
- Example 11 622.00 -0.48
- Example 12 683.50-1 0. 51
- Example 13 412.7 766.35-1.62
- Example 14 152.00-1.45 Table 4
- Comparative Example 5 (3B)-0.25
- the samples of Reference Examples 1 to 6 and Example 114 were all subjected to high temperature conditions of 1273K (1000 ° C) or higher. It can be seen that these steels also have high strength.
- Reference Example 5 in which the composition ratio of Ru was 4.0% by weight, and Examples 1, 2, 4, 9, 10, and 11, in which the composition ratio of Ru was approximately 5.0% by weight, and the composition of Ru.
- Examples 3 and 12, 13 in which the ratio is 6.0% by weight and Example 14 in which the composition ratio of Ru is 7.0% by weight have high high-temperature strength.
- the lattice misfit of the comparative example is not less than 0.35, whereas the samples of Reference Examples 1 to 6 and Examples 1 to 14 are all It can be seen that the lattice misfit is less than 0.35.
- Examples 1 to 14 all have high service temperatures (Example 1: 1344K (1071 ° C), Example 2: 1368K (1093.C), Example 3: 1375K (1102 ° C), 4: 1372K (1099 ° C), Example 5: 1379K (1106 ° C), Example 6: 1379K (1106 ° C), Example 7: 1379K (1106 ° C), Example 8: 1363K (1090 ° C), Example 9: 1358 K (1085 ° C), Example 10: 1362 K (1089 ° C), Example 11: 136 IK (1088 ° C), Example 12: 1363 K (1090 ° C) ° C), Example 13: 1366 K (1093 ° C :), Example 14: 1384 K (111 ° C.) Accordingly, Examples 1 to 14 show the conventional Ni. It has a higher heat resistance temperature than the base single crystal superalloy, indicating that it has excellent high temperature strength.
- the amount of Ru increases more than necessary, the ⁇ phase precipitates and the high-temperature strength decreases, so that the Ru content is within a range where the balance with other elements is maintained.
- it is preferably set to 4.1% by weight or more and 14.0% by weight or less.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- 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)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2508698A CA2508698C (en) | 2002-12-06 | 2003-12-05 | Ni-based single crystal super alloy |
JP2004558425A JP3814662B2 (ja) | 2002-12-06 | 2003-12-05 | Ni基単結晶超合金 |
DE60326083T DE60326083D1 (de) | 2002-12-06 | 2003-12-05 | Monokristalline nickel-basis-superlegierung |
US10/537,477 US20060011271A1 (en) | 2002-12-06 | 2003-12-05 | Ni-based single crystal superalloy |
AU2003289214A AU2003289214A1 (en) | 2002-12-06 | 2003-12-05 | Ni-BASE SINGLE CRYSTAL SUPERALLOY |
EP03777308A EP1568794B1 (en) | 2002-12-06 | 2003-12-05 | Ni-BASE SINGLE CRYSTAL SUPERALLOY |
US12/900,896 US8968643B2 (en) | 2002-12-06 | 2010-10-08 | Ni-based single crystal super alloy |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2002-355756 | 2002-12-06 | ||
JP2002355756 | 2002-12-06 |
Related Child Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10537477 A-371-Of-International | 2003-12-05 | ||
US12/900,896 Continuation-In-Part US8968643B2 (en) | 2002-12-06 | 2010-10-08 | Ni-based single crystal super alloy |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004053177A1 true WO2004053177A1 (ja) | 2004-06-24 |
Family
ID=32500797
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2003/015619 WO2004053177A1 (ja) | 2002-12-06 | 2003-12-05 | Ni基単結晶超合金 |
Country Status (8)
Country | Link |
---|---|
US (1) | US20060011271A1 (ja) |
EP (1) | EP1568794B1 (ja) |
JP (1) | JP3814662B2 (ja) |
CN (1) | CN100357467C (ja) |
AU (1) | AU2003289214A1 (ja) |
CA (1) | CA2508698C (ja) |
DE (1) | DE60326083D1 (ja) |
WO (1) | WO2004053177A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2008032751A1 (en) * | 2006-09-13 | 2008-03-20 | National Institute For Materials Science | Ni-BASE SINGLE CRYSTAL SUPERALLOY |
CN100482824C (zh) * | 2005-04-30 | 2009-04-29 | 中国科学院金属研究所 | 一种含铼镍基单晶高温合金及其制备工艺 |
Families Citing this family (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1498503B1 (en) * | 2002-03-27 | 2011-11-23 | National Institute for Materials Science | Ni-BASE DIRECTIONALLY SOLIDIFIED SUPERALLOY AND Ni-BASE SINGLE CRYSTAL SUPERALLOY |
US20070044869A1 (en) * | 2005-09-01 | 2007-03-01 | General Electric Company | Nickel-base superalloy |
JP5344453B2 (ja) * | 2005-09-27 | 2013-11-20 | 独立行政法人物質・材料研究機構 | 耐酸化性に優れたNi基超合金 |
EP1997923B1 (en) * | 2006-03-20 | 2016-03-09 | National Institute for Materials Science | Method for producing an ni-base superalloy |
US8696979B2 (en) * | 2006-03-31 | 2014-04-15 | National Institute For Materials Science | Ni-base superalloy and method for producing the same |
CN100460542C (zh) * | 2006-06-14 | 2009-02-11 | 中国科学院金属研究所 | 一种无铼第二代镍基单晶高温合金 |
US8388890B2 (en) * | 2006-09-21 | 2013-03-05 | Tyco Electronics Corporation | Composition and method for applying an alloy having improved stress relaxation resistance |
US7704332B2 (en) * | 2006-12-13 | 2010-04-27 | United Technologies Corporation | Moderate density, low density, and extremely low density single crystal alloys for high AN2 applications |
US9499886B2 (en) | 2007-03-12 | 2016-11-22 | Ihi Corporation | Ni-based single crystal superalloy and turbine blade incorporating the same |
CN101680059B (zh) * | 2007-03-12 | 2011-07-06 | 株式会社Ihi | Ni基单晶超合金及使用其的涡轮叶片 |
CN100557092C (zh) * | 2007-12-17 | 2009-11-04 | 北京航空航天大学 | 采用籽晶法与螺旋选晶法组合制备Ni基单晶高温合金的方法 |
JP5467307B2 (ja) * | 2008-06-26 | 2014-04-09 | 独立行政法人物質・材料研究機構 | Ni基単結晶超合金とそれよりえられた合金部材 |
US8216509B2 (en) * | 2009-02-05 | 2012-07-10 | Honeywell International Inc. | Nickel-base superalloys |
US20100254822A1 (en) * | 2009-03-24 | 2010-10-07 | Brian Thomas Hazel | Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom |
US20110076179A1 (en) * | 2009-03-24 | 2011-03-31 | O'hara Kevin Swayne | Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom |
CN102803528B (zh) | 2009-04-17 | 2015-04-22 | 株式会社Ihi | Ni基单晶超合金及使用其的涡轮叶片 |
WO2012039189A1 (ja) * | 2010-09-24 | 2012-03-29 | 公立大学法人大阪府立大学 | Reが添加されたNi基2重複相金属間化合物合金及びその製造方法 |
US20160214350A1 (en) | 2012-08-20 | 2016-07-28 | Pratt & Whitney Canada Corp. | Oxidation-Resistant Coated Superalloy |
EP2943974B1 (en) | 2013-01-08 | 2021-01-13 | SK Siltron Co., Ltd. | Method of detecting defects in silicon single crystal wafer |
JP6226231B2 (ja) | 2013-09-18 | 2017-11-08 | 株式会社Ihi | 熱遮蔽コーティングしたNi合金部品及びその製造方法 |
CN105506387B (zh) * | 2015-12-21 | 2017-08-08 | 谷月恒 | 一种高比蠕变强度的镍基单晶高温合金及其制备方法和应用 |
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 |
CN109797433B (zh) * | 2019-01-23 | 2021-05-25 | 深圳市万泽中南研究院有限公司 | 单晶高温合金、热端部件及设备 |
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 |
CN112522543A (zh) * | 2020-11-18 | 2021-03-19 | 贵州工程应用技术学院 | 一种高浓度Re/Ru高承温能力高蠕变抗力镍基单晶超合金 |
CN113913942A (zh) * | 2021-01-13 | 2022-01-11 | 中国航发北京航空材料研究院 | 镍基单晶合金、用途和热处理方法 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0208645A2 (en) * | 1985-06-10 | 1987-01-14 | United Technologies Corporation | Advanced high strength single crystal superalloy compositions |
EP0246082A1 (en) * | 1986-05-13 | 1987-11-19 | AlliedSignal Inc. | Single crystal super alloy materials |
EP0848071A1 (en) * | 1996-12-11 | 1998-06-17 | United Technologies Corporation | Superalloy compositions |
JPH10330872A (ja) * | 1997-05-29 | 1998-12-15 | Toshiba Corp | Ni基耐熱超合金及びNi基耐熱超合金部品 |
JPH11256258A (ja) * | 1998-03-13 | 1999-09-21 | Toshiba Corp | Ni基単結晶超合金およびガスタービン部品 |
JPH11310839A (ja) * | 1998-04-28 | 1999-11-09 | Hitachi Ltd | 高強度Ni基超合金方向性凝固鋳物 |
EP0971041A1 (fr) * | 1998-07-07 | 2000-01-12 | ONERA (Office National d'Etudes et de Recherches Aérospatiales) | Superalliage monocristallin à base de nickel à haut solvus phase gamma prime |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4582548A (en) * | 1980-11-24 | 1986-04-15 | Cannon-Muskegon Corporation | Single crystal (single grain) alloy |
US4643782A (en) * | 1984-03-19 | 1987-02-17 | Cannon Muskegon Corporation | Single crystal alloy technology |
US5151249A (en) * | 1989-12-29 | 1992-09-29 | General Electric Company | Nickel-based single crystal superalloy and method of making |
US5455120A (en) * | 1992-03-05 | 1995-10-03 | General Electric Company | Nickel-base superalloy and article with high temperature strength and improved stability |
US5366695A (en) * | 1992-06-29 | 1994-11-22 | Cannon-Muskegon Corporation | Single crystal nickel-based superalloy |
US5482789A (en) * | 1994-01-03 | 1996-01-09 | General Electric Company | Nickel base superalloy and article |
US6190471B1 (en) * | 1999-05-26 | 2001-02-20 | General Electric Company | Fabrication of superalloy articles having hafnium- or zirconium-enriched protective layer |
-
2003
- 2003-12-05 EP EP03777308A patent/EP1568794B1/en not_active Expired - Lifetime
- 2003-12-05 CN CNB2003801095013A patent/CN100357467C/zh not_active Expired - Lifetime
- 2003-12-05 US US10/537,477 patent/US20060011271A1/en not_active Abandoned
- 2003-12-05 DE DE60326083T patent/DE60326083D1/de not_active Expired - Lifetime
- 2003-12-05 CA CA2508698A patent/CA2508698C/en not_active Expired - Lifetime
- 2003-12-05 AU AU2003289214A patent/AU2003289214A1/en not_active Abandoned
- 2003-12-05 JP JP2004558425A patent/JP3814662B2/ja not_active Expired - Lifetime
- 2003-12-05 WO PCT/JP2003/015619 patent/WO2004053177A1/ja active Application Filing
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0208645A2 (en) * | 1985-06-10 | 1987-01-14 | United Technologies Corporation | Advanced high strength single crystal superalloy compositions |
EP0246082A1 (en) * | 1986-05-13 | 1987-11-19 | AlliedSignal Inc. | Single crystal super alloy materials |
EP0848071A1 (en) * | 1996-12-11 | 1998-06-17 | United Technologies Corporation | Superalloy compositions |
JPH10330872A (ja) * | 1997-05-29 | 1998-12-15 | Toshiba Corp | Ni基耐熱超合金及びNi基耐熱超合金部品 |
JPH11256258A (ja) * | 1998-03-13 | 1999-09-21 | Toshiba Corp | Ni基単結晶超合金およびガスタービン部品 |
JPH11310839A (ja) * | 1998-04-28 | 1999-11-09 | Hitachi Ltd | 高強度Ni基超合金方向性凝固鋳物 |
EP0971041A1 (fr) * | 1998-07-07 | 2000-01-12 | ONERA (Office National d'Etudes et de Recherches Aérospatiales) | Superalliage monocristallin à base de nickel à haut solvus phase gamma prime |
Non-Patent Citations (1)
Title |
---|
See also references of EP1568794A4 * |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN100482824C (zh) * | 2005-04-30 | 2009-04-29 | 中国科学院金属研究所 | 一种含铼镍基单晶高温合金及其制备工艺 |
WO2008032751A1 (en) * | 2006-09-13 | 2008-03-20 | National Institute For Materials Science | Ni-BASE SINGLE CRYSTAL SUPERALLOY |
JP5177559B2 (ja) * | 2006-09-13 | 2013-04-03 | 独立行政法人物質・材料研究機構 | Ni基単結晶超合金 |
US8771440B2 (en) | 2006-09-13 | 2014-07-08 | National Institute For Materials Science | Ni-based single crystal superalloy |
Also Published As
Publication number | Publication date |
---|---|
CA2508698C (en) | 2012-05-15 |
CN1745186A (zh) | 2006-03-08 |
AU2003289214A1 (en) | 2004-06-30 |
EP1568794B1 (en) | 2009-02-04 |
EP1568794A1 (en) | 2005-08-31 |
JP3814662B2 (ja) | 2006-08-30 |
CA2508698A1 (en) | 2004-06-24 |
CN100357467C (zh) | 2007-12-26 |
DE60326083D1 (de) | 2009-03-19 |
JPWO2004053177A1 (ja) | 2006-04-13 |
AU2003289214A8 (en) | 2004-06-30 |
US20060011271A1 (en) | 2006-01-19 |
EP1568794A4 (en) | 2006-11-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2004053177A1 (ja) | Ni基単結晶超合金 | |
JP5177559B2 (ja) | Ni基単結晶超合金 | |
EP2305845B1 (en) | Ni-BASED SINGLE CRYSTAL SUPERALLOY AND ALLOY MEMBER USING THE SAME AS BASE | |
CA2729117C (en) | Ni-based single crystal superalloy and component obtained from the same | |
JP4833227B2 (ja) | 高耐熱性,高強度Ir基合金及びその製造方法 | |
JP4557079B2 (ja) | Ni基単結晶超合金及びこれを用いたタービン翼 | |
CA2479774C (en) | Ni-base directionally solidified and single-crystal superalloy | |
EP1262569B1 (en) | Ni-based single crystal super alloy | |
US20040221925A1 (en) | Ni-based superalloy having high oxidation resistance and gas turbine part | |
US6966956B2 (en) | Ni-based single crystal super alloy | |
JP2010507016A (ja) | ニッケル基超合金 | |
RU2518838C2 (ru) | МОНОКРИСТАЛЛИЧЕСКИЙ СУПЕРСПЛАВ НА ОСНОВЕ Ni И ЛОПАТКА ТУРБИНЫ | |
WO2010119709A1 (ja) | Ni基単結晶超合金及びこれを用いたタービン翼 | |
JPWO2007122931A1 (ja) | Ni基超合金とその製造方法 | |
JP5224246B2 (ja) | 耐酸化性の優れたNi基化合物超合金及びその製造方法と耐熱構造材 | |
US8968643B2 (en) | Ni-based single crystal super alloy | |
JPH0310039A (ja) | 高温強度および高温耐食性にすぐれたNi基単結晶超合金 | |
JP2820139B2 (ja) | 高温強度および高温耐食性にすぐれたNi基単結晶超合金 | |
JPH07300639A (ja) | 高耐食性ニッケル基単結晶超合金およびその製造方法 | |
JPH0941058A (ja) | Ni基単結晶合金 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW |
|
AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): BW GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2004558425 Country of ref document: JP |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
ENP | Entry into the national phase |
Ref document number: 2006011271 Country of ref document: US Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2508698 Country of ref document: CA Ref document number: 10537477 Country of ref document: US |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2003777308 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 20038A95013 Country of ref document: CN |
|
WWP | Wipo information: published in national office |
Ref document number: 2003777308 Country of ref document: EP |
|
WWP | Wipo information: published in national office |
Ref document number: 10537477 Country of ref document: US |