WO2014024734A1 - Ni基単結晶超合金 - Google Patents
Ni基単結晶超合金 Download PDFInfo
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- WO2014024734A1 WO2014024734A1 PCT/JP2013/070613 JP2013070613W WO2014024734A1 WO 2014024734 A1 WO2014024734 A1 WO 2014024734A1 JP 2013070613 W JP2013070613 W JP 2013070613W WO 2014024734 A1 WO2014024734 A1 WO 2014024734A1
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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%
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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
- C22C19/056—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%
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
- C30B29/10—Inorganic compounds or compositions
- C30B29/52—Alloys
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B11/00—Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B33/00—After-treatment of single crystals or homogeneous polycrystalline material with defined structure
- C30B33/02—Heat treatment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/132—Chromium
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/175—Superalloys
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/607—Monocrystallinity
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a Ni-based single crystal superalloy suitably used for members used under high stress and high stress, such as turbine blades and turbine vanes such as jet engines and gas turbines. More specifically, the present invention has improved thermo-mechanical fatigue characteristics, creep characteristics, and environmental resistance characteristics, and the orientation dependence of the creep characteristics is small. The present invention relates to a Ni-based single crystal superalloy excellent in performance.
- Ni-based single crystal superalloys are used for members used under high stress and high stress, such as turbine blades and turbine vanes for jet engines and gas turbines.
- the inlet gas temperature of the turbine has been further increased in order to improve output and efficiency. Therefore, the turbine blades and turbine vanes of the gas turbine have a hollow blade structure in order to maintain high temperature strength, and the temperature of the base material is prevented from rising by forced cooling inside the blade.
- the surface temperature of the blades of the turbine blade and the turbine vane exceeds 900 ° C.
- the internal temperature of the blade is about 600 ° C., and the temperature difference between the surface and the inside of the blade generates TMF.
- the turbine blade rotates at a high speed while being exposed to a high-temperature combustion gas, and a centrifugal force is applied. Therefore, the turbine blade must withstand high stress creep. Similar to the TMF characteristic, the creep characteristic is also an important characteristic for the Ni-based single crystal superalloy. As a cause of deterioration of the creep characteristics and TMF characteristics, for example, precipitation of a TCP phase (Topologically Close Packed phase) can be mentioned, and the problem becomes apparent particularly when used at a high temperature for a long time.
- Ni-based single crystal superalloys PWA1480 (trademark) or those described in the following Patent Documents 1, 2, 3, 4 and 5 are known.
- the creep characteristics are not sufficient to increase the efficiency by increasing the combustion gas temperature of the turbine. Therefore, Ni-based single crystal superalloys described in the following Patent Documents 6, 7 and 8 containing expensive Re have appeared, but Ni-based single crystal superalloys containing Re are applicable to large-sized members. In this case, the problem that the material cost is too high is pointed out.
- orientation dependency that the angle shift in the ⁇ 001> crystal orientation greatly affects the strength under high stress is also a problem.
- Small orientation dependence means less wasted manufacturing parts, and for this reason, small orientation dependence is more advantageous for larger parts and is considered to be superior in cost performance in practical terms. It is done.
- the present invention improves the first generation Ni-based single crystal superalloy that does not contain Re, has excellent TMF characteristics, creep characteristics and environmental resistance characteristics, and has low creep orientation dependence and practical cost performance.
- An object of the present invention is to provide a Ni-based single crystal superalloy excellent in the above.
- the Ni-based single crystal superalloy of the present invention is Cr: 6% by mass or more and 12% by mass or less, Mo: 0.4 mass% or more and 3.0 mass% or less, W: 6 mass% or more and 10 mass% or less, Al: 4.0 mass% or more and 6.5 mass% or less, Nb: 0% by mass or more and 1% by mass or less, Ta: 8% by mass or more and 12% by mass or less, Hf: 0% by mass to 0.15% by mass, Si: 0.01% by mass or more and 0.2% by mass or less, and Zr: 0% by mass or more and 0.04% by mass or less, Containing Inclusion of at least one element of B, C, Y, La, Ce or V is permitted, The balance is made of Ni and inevitable impurities.
- the Ni-based single crystal superalloy of the present invention is Cr: 7% by mass or more and 12% by mass or less, Mo: 0.4 mass% or more and 2.5 mass% or less, W: 7 mass% or more and 10 mass% or less, Al: 4.0 mass% or more and 6.5 mass% or less, Nb: 0% by mass or more and 1% by mass or less, Ta: 9 mass% or more and 11 mass% or less, Hf: 0% by mass to 0.15% by mass, Si: 0.01% by mass or more and 0.2% by mass or less, and Zr: 0% by mass or more and 0.04% by mass or less, Containing Inclusion of at least one element of B, C, Y, La, Ce or V is permitted, The balance is made of Ni and inevitable impurities.
- the Ni-based single crystal superalloy of the present invention is Cr: 8% by mass or more and 10% by mass or less, Mo: 0.4 mass% or more and 2.0 mass% or less, W: 7 mass% or more and 9 mass% or less, Al: 4.0 mass% or more and 6.5 mass% or less, Nb: 0% by mass or more and 1% by mass or less, Ta: 10 mass% or more and 11 mass% or less, Hf: 0% by mass to 0.15% by mass, Si: 0.01% by mass or more and 0.2% by mass or less, and Zr: 0% by mass or more and 0.04% by mass or less, Containing Inclusion of at least one element of B, C, Y, La, Ce or V is permitted, The balance is made of Ni and inevitable impurities.
- the composition ratio of the elements allowed to be contained is B: 0.05 mass% or less, C: 0.15 mass% or less, Y: 0.1 mass% or less, La: 0.1% by mass or less, Ce: 0.1% by mass or less, V: 1% by mass or less, It is preferable that
- ⁇ (h) is creep life (hours)
- X Co , X Cr , X Mo , X W , X Al , X Ti , X Nb , and X Ta are cobalt, chromium, molybdenum, tungsten, and aluminum, respectively.
- Titanium, niobium, tantalum composition ratio (% by mass) It is preferable that ⁇ (h) ⁇ 120.
- the creep life ⁇ (h) is preferably 200 or more.
- the Ni-based single crystal superalloy of the present invention is excellent in environmental resistance characteristics such as TMF characteristics, creep characteristics and high-temperature oxidation resistance, has low orientation dependency of creep characteristics, and has excellent cost performance in practical use.
- composition component and the composition ratio in the Ni-based single crystal superalloy having the characteristics as described above are based on the following viewpoints.
- the composition ratio of Cr improves the high temperature corrosion resistance and high temperature oxidation resistance of the Ni-based single crystal superalloy.
- the composition ratio of Cr is 6% by mass or more and 12% by mass or less. When the composition ratio is less than 6% by mass, it is difficult to ensure high temperature corrosion resistance and high temperature oxidation resistance. When the composition ratio exceeds 12% by mass, harmful phases such as ⁇ phase and ⁇ phase are generated and the high temperature strength decreases. To do.
- the composition ratio of Cr is preferably 7% by mass or more and 12% by mass or less, and more preferably 8% by mass or more and 10% by mass or less.
- Mo molybdenum
- Mo has a negative gamma / gamma prime misfit value and promotes the Raft effect, which is one of the strengthening mechanisms at high temperatures.
- Mo is dissolved in the substrate and contributes to an increase in high-temperature strength by precipitation hardening.
- the composition ratio of Mo is 0.4 mass% or more and 3.0 mass% or less. When the composition ratio is less than 0.4% by mass, the high-temperature strength decreases, and when it exceeds 3.0% by mass, a harmful phase is generated and the high-temperature strength decreases.
- the composition ratio of Mo is preferably 0.4% by mass or more and 2.5% by mass or less, and more preferably 0.4% by mass or more and 2.0% by mass or less.
- W tungsten
- the composition ratio of W is 6 mass% or more and 10 mass% or less. When the composition ratio is less than 6% by mass, the TMF characteristics and creep characteristics are lowered, and when it exceeds 10% by mass, a harmful phase is generated and the TMF characteristics and creep characteristics are degraded.
- the composition ratio of W is preferably 7% by mass or more and 10% by mass or less, and more preferably 7% by mass or more and 9% by mass or less.
- Al combines with Ni to form an intermetallic compound represented by Ni 3 Al constituting a gamma prime phase that precipitates in the gamma matrix, and particularly TMF characteristics and creep on the low temperature side below 1000 ° C. Improve properties.
- the composition ratio of Al is not less than 4.0% by mass and not more than 6.5% by mass. When the composition ratio is less than 4% by mass, the amount of gamma prime phase is small and the required TMF characteristics and creep characteristics cannot be obtained. When the composition ratio exceeds 6.5% by mass, the required TMF characteristics and creep characteristics are not obtained. I can't get it.
- the composition ratio of Nb (niobium) is 0% by mass or more and 1% by mass or less. When the composition ratio exceeds 1% by mass, a harmful phase is generated at a high temperature, and TMF characteristics and creep characteristics are deteriorated.
- Ta (tantalum) strengthens the gamma prime phase and improves the creep properties.
- the composition ratio of Ta is 8% by mass or more and 12% by mass or less. When the composition ratio is less than 8% by mass, the required TMF characteristics and creep characteristics cannot be obtained. When the composition ratio exceeds 12% by mass, formation of a eutectic gamma prime phase is promoted, and solution heat treatment becomes difficult.
- the composition ratio of Ta is preferably 9% by mass or more and 11% by mass or less, and more preferably 10% by mass or more and 11% by mass or less.
- Hf (hafnium) may improve oxidation resistance and improve TMF characteristics.
- the composition ratio of Hf is 0% by mass or more and 0.15% by mass or less. When the composition ratio exceeds 0.15% by mass, generation of a harmful phase is promoted, and TMF characteristics and creep characteristics are deteriorated.
- Si may improve oxidation resistance, improve TMF characteristics, and reduce the orientation dependency of single crystals.
- the composition ratio of Si is 0.01% by mass or more and 0.2% by mass or less. When the composition ratio is less than 0.01% by mass, effects such as improvement in oxidation resistance, improvement in TMF characteristics, and reduction in orientation dependency of a single crystal cannot be obtained. On the other hand, if the composition ratio exceeds 0.2% by mass, the solid solubility limit of other elements is lowered, so that the required TMF characteristics and creep characteristics cannot be obtained.
- Zr zirconium
- the composition ratio of Zr is 0% by mass or more and less than 0.04% by mass.
- the Ni-based single crystal superalloy having such a composition can further contain, for example, at least one of B, C, Y, La, Ce or V in addition to the inevitable impurities.
- the individual ingredients are B: 0.05 mass% or less, C: 0.15 mass% or less, Y: 0.1 mass% or less, La: 0.1% by mass or less, Ce: 0.1% by mass or less, V: 1% by mass or less, It is preferable that
- the Ni-based single crystal superalloy does not contain Co (cobalt) as described above. This is to improve TMF characteristics. When Co is contained, stacking faults are easily generated, and it is considered that TMF characteristics are deteriorated. Further, the Ni-based single crystal superalloy particularly contains Hf, Si and Zr for improving TMF characteristics (however, the composition ratio of Hf and Zr may be 0% by mass). Even in a Ni-base superalloy that does not contain Co, it is considered that twins are formed on the surface of the metal crystal 111 and the dislocation progresses to break. In a Ni-based single crystal superalloy containing Hf, Si, and Zr, since Hf, Si, and Zr are components that segregate at the interface, the progress of dislocation may be suppressed, and TMF characteristics may be improved.
- ⁇ (h) is creep life (hours)
- X Co , X Cr , X Mo , X W , X Al , X Ti , X Nb , and X Ta are cobalt, chromium, molybdenum, tungsten, and aluminum, respectively.
- Titanium, niobium, tantalum composition ratio (% by mass)) ⁇ (h) ⁇ 120 is preferable, and ⁇ (h) ⁇ 200 is more preferable.
- the above formula (1) is a parameter that defines the creep life of the Ni-based single crystal superalloy. Regarding the existing Ni-based superalloy that does not contain Re, its composition and creep life under the condition of 392 MPa at 900 ° C. Is newly derived by multiple regression analysis. The predicted value of the creep life predicted by the equation (1) is in good agreement with the measured value of the creep life at 392 MPa at 900 ° C. for the Ni-based superalloy not containing Re.
- the Ni-based single crystal alloy can be manufactured by subjecting a single crystal casting having a predetermined composition to the following heat treatment. That is, the heat treatment is Solution treatment for holding at 1280 ° C to 1360 ° C for 2 hours to 40 hours ⁇ Air cooling at 200 ° C / min to 400 ° C / min or cooling in an inert gas atmosphere ⁇ 1000 ° C to 1200 ° C for 2 hours to 5 hours Primary aging treatment that cools in air or inert gas atmosphere after holding ⁇ Secondary aging treatment that cools in air or inert gas atmosphere after holding at 850 ° C to 950 ° C for 10 to 30 hours .
- the heat treatment is Solution treatment for holding at 1280 ° C to 1360 ° C for 2 hours to 40 hours ⁇ Air cooling at 200 ° C / min to 400 ° C / min or cooling in an inert gas atmosphere ⁇ 1000 ° C to 1200 ° C for 2 hours to 5 hours
- Primary aging treatment that cools in air or inert gas atmosphere after
- a Ni-base superalloy having the composition (mass%) shown in Table 1 is melted using a vacuum melting furnace, cast with a heated and held lost wax mold, and the mold is pulled down at a solidification rate of 200 mm / h, A crystal casting was obtained.
- the obtained single crystal casting was preheated in vacuum at 1300 ° C. for 1 hour, then the temperature was raised, held at 1330 ° C. for 10 hours, and then subjected to a solution treatment that was air-cooled at about 300 ° C./min. . Thereafter, a primary aging treatment was performed in which air was cooled at 1100 ° C. for 4 hours in vacuum and a secondary aging treatment in which air cooling was performed at 870 ° C. for 20 hours in vacuum.
- the temperature range of the solution treatment of the Ni-based single crystal superalloys of Examples 1 to 7 is 1310 ° C. to 1360 ° C., and the temperature range of the primary aging treatment is 1000 ° C. to 1150 ° C.
- the known PWA 1480 cited as Reference Example 1 is kept at 1288 ° C. for 4 hours and then air cooled, then kept at 1080 ° C. for 4 hours and then air cooled, and then kept at 871 ° C. for 32 hours and air cooled. Heat treatment was applied.
- the single crystal alloy cast after the heat treatment was processed into a creep test piece having a parallel part diameter of 4 mm and a length of 20 mm, and subjected to a creep test under the conditions of 392 MPa at 900 ° C. and 245 MPa at 1100 ° C.
- the TMF test was performed by heating a test piece having a parallel part diameter of 5 mm and a length of 15 mm with high frequency.
- the temperature range was changed from the lower limit of 400 ° C. to the upper limit of 900 ° C., and a strain of ⁇ 0.64% was applied in conjunction with this temperature change.
- the frequency was 66 min in one cycle, the waveform was a triangular wave, and 60 min was maintained during compression.
- test conditions simulated the operating conditions of the gas turbine, and the surface temperature of the turbine blade was assumed to be 900 ° C. during steady state and 400 ° C. during stoppage.
- the temperature raising / lowering rate was 166.7 ° C./min.
- the TMF characteristic is evaluated by the number of repetitions until the test piece breaks.
- Table 2 shows the calculated value of the creep life ⁇ (h) and the measured value of the creep test under the conditions of 392 MPa at 900 ° C. and 245 MPa at 1100 ° C. As is apparent from Table 2, it is confirmed that all of the Ni-based single crystal superalloys of Examples 1 to 6 have creep characteristics superior to those of PWA1480 as Reference Example 1. .
- the LMP taken on the horizontal axis in FIG. 1 is a Larson-Miller parameter, which is known as a parameter for organizing the rupture time under different temperature conditions.
- T in the equation defining LMP indicates temperature (K)
- tr indicates fracture time (h).
- 1% creep strain time defining LMP indicates 1% creep strain arrival time (h). Larger LMP means that it can withstand creep at higher temperatures or longer.
- Ni-based single crystal superalloys of Examples 1 to 7 are superior in creep characteristics to PWA1480 of Reference Example 1.
- Table 3 shows the results of the TMF test.
- PWA1480 Reference Example 1
- the Ni-based single crystal superalloys of Examples 1 to 6 have an excellent TMF of 130 to 288 times. It is confirmed that it has characteristics.
- the oxidation test was conducted under two conditions: electric furnace heating and kerosene burner rig. In electric furnace heating, heating to 1100 ° C. in an atmospheric furnace and holding at this temperature for 1 hour was taken as one cycle, 50 cycles were performed, and the change in mass of the sample was measured. In the burner rig, the mass change of the sample was measured after heating to 1100 ° C. and holding at this temperature for 1 hour.
- the results of the oxidation test are as shown in Table 4.
- Ni-based single crystal superalloys of Examples 2 and 3 the glossy metallic surface was maintained as it was, whereas PWA1480 (Reference Example 1) was covered with a gray oxide film. From these results, the Ni-based single crystal superalloys of Examples 1 to 7 are evaluated to be excellent in oxidation resistance.
- the creep strength decreases as the tilt angle from the growth direction of the single crystal increases. From the viewpoint of improving the yield when cast on a turbine blade, even if the tilt angle of the crystal in the longitudinal direction increases, it is required that the creep strength does not deteriorate significantly within 15 ° from the ⁇ 001> crystal orientation. Therefore, the orientation dependence of the creep characteristics of the Ni-based single crystal superalloy of Example 1 was examined in detail.
- the creep conditions were 392 MPa at 900 ° C. and 245 MPa at 1000 ° C.
- the creep life when the difference in orientation from the ⁇ 001> crystal orientation, which is the growth direction of the single crystal, is 1.5 ° to a maximum of 12.5 ° is 230 hours to 330 hours under the creep condition of 900 ° C.
- Example 1 has little orientation dependency of creep characteristics.
- the manufacturing process of the Ni-based single crystal superalloy is as follows: solution treatment for holding a single crystal cast at 1320 ° C. for 5 hours ⁇ primary aging treatment holding at 1100 ° C. for 4 hours ⁇ holding at 870 ° C. for 20 hours A series of heat treatment called secondary aging treatment is performed.
- the most excellent creep characteristics when the cooling rate is 300 ° C./min in any of the creep conditions of 392 MPa at 900 ° C. and 245 MPa at 1000 ° C. Is obtained. Since the Ni-based single crystal superalloy of the present invention does not contain Re in the composition, it is confirmed that it is easily affected by the cooling rate. In addition, if the cooling rate at the time of air cooling after solution treatment is 200 degreeC / min, it will be thought that the required creep characteristic is implement
- the temperature of the primary aging treatment was changed to 1100 ° C., 1125 ° C., 1150 ° C., and 1175 ° C., and the influence of the temperature of the primary aging treatment on the creep characteristics was examined. .
- the results are shown in FIGS. 4 (a) and 4 (b).
- the manufacturing process of the Ni-based single crystal superalloy is as follows: solution treatment for 5 hours at 1310 ° C. ⁇ first aging treatment for 4 hours at each temperature ⁇ 20 hours at 870 ° C. A series of heat treatment called secondary aging treatment is performed.
- Ni-based single crystal superalloy was produced in the same manner as described above except that the solution treatment was changed to 1340 ° C., and the influence of the temperature of the primary aging treatment on the creep characteristics was examined. The results are shown in FIGS. 5 (a) and 5 (b).
- the temperature of the primary aging treatment is any of the creep conditions of 392 MPa at 900 ° C. and 245 MPa at 1000 ° C.
- the lower one is excellent in creep characteristics, and the best is at 1100 ° C.
- the temperature of the primary aging treatment is 1175 ° C., it is considered that the required creep characteristics are realized.
- the Ni-based single crystal superalloy of the present invention is excellent in environmental resistance characteristics such as TMF characteristics, creep characteristics and high-temperature oxidation resistance, has a small orientation dependency of creep characteristics, and has excellent cost performance in practical use. Therefore, it is effective for a member used under high temperature and high stress, such as a turbine blade or a turbine vane such as a jet engine or a gas turbine.
Abstract
Description
すなわち、本発明のNi基単結晶超合金は、
Cr:6質量%以上12質量%以下、
Mo:0.4質量%以上3.0質量%以下、
W:6質量%以上10質量%以下、
Al:4.0質量%以上6.5質量%以下、
Nb:0質量%以上1質量%以下、
Ta:8質量%以上12質量%以下、
Hf:0質量%以上0.15質量%以下、
Si:0.01質量%以上0.2質量%以下、および
Zr:0質量%以上0.04質量%以下、
を含有し、
B、C、Y、La、CeまたはVの少なくとも一つの元素の含有が許容され、
残部がNiおよび不可避的不純物からなることを特徴としている。
Cr:7質量%以上12質量%以下、
Mo:0.4質量%以上2.5質量%以下、
W:7質量%以上10質量%以下、
Al:4.0質量%以上6.5質量%以下、
Nb:0質量%以上1質量%以下、
Ta:9質量%以上11質量%以下、
Hf:0質量%以上0.15質量%以下、
Si:0.01質量%以上0.2質量%以下、および
Zr:0質量%以上0.04質量%以下、
を含有し、
B、C、Y、La、CeまたはVの少なくとも一つの元素の含有が許容され、
残部がNiおよび不可避的不純物からなることを特徴としている。
Cr:8質量%以上10質量%以下、
Mo:0.4質量%以上2.0質量%以下、
W:7質量%以上9質量%以下、
Al:4.0質量%以上6.5質量%以下、
Nb:0質量%以上1質量%以下、
Ta:10質量%以上11質量%以下、
Hf:0質量%以上0.15質量%以下、
Si:0.01質量%以上0.2質量%以下、および
Zr:0質量%以上0.04質量%以下、
を含有し、
B、C、Y、La、CeまたはVの少なくとも一つの元素の含有が許容され、
残部がNiおよび不可避的不純物からなることを特徴としている。
含有が許容される前記元素の組成比が、
B:0.05質量%以下、
C:0.15質量%以下、
Y:0.1質量%以下、
La:0.1質量%以下、
Ce:0.1質量%以下、
V:1質量%以下、
であることが好ましい。
τ(h)= -3208+11XCo+40XCr+139XMo+93XW+327XAl+146XTi+45XNb+53XTa (1)
(ただし、τ(h)はクリープ寿命(時間)、XCo、XCr、XMo、XW、XAl、XTi、XNb、XTaは、それぞれ、コバルト、クロム、モリブデン、タングステン、アルミニウム、チタン、ニオブ、タンタルの組成比(質量%))を示す)
で示されるとき、τ(h)≧120であることが好ましい。
B:0.05質量%以下、
C:0.15質量%以下、
Y:0.1質量%以下、
La:0.1質量%以下、
Ce:0.1質量%以下、
V:1質量%以下、
であることが好ましい。
τ(h)= -3208+11XCo+40XCr+139XMo+93XW+327XAl+146XTi+45XNb+53XTa (1)
(ただし、τ(h)はクリープ寿命(時間)、XCo、XCr、XMo、XW、XAl、XTi、XNb、XTaは、それぞれ、コバルト、クロム、モリブデン、タングステン、アルミニウム、チタン、ニオブ、タンタルの組成比(質量%))を示す)
で示されるとき、τ(h)≧120であることが好ましく、τ(h)≧200であることがより好ましい。上記式(1)は、Ni基単結晶超合金のクリープ寿命を規定するパラメータであり、Reを含有しない既存のNi基超合金について、その組成と、900℃で392MPaの条件下でのクリープ寿命との関係を重回帰分析して新たに導出したものである。式(1)により予測されるクリープ寿命の予測値は、Reを含有しないNi基超合金の900℃で392MPaにおけるクリープ寿命の実測値とよく一致している。
1280℃~1360℃に2時間~40時間保持する溶体化処理→200℃/min~400℃/minでの空冷または不活性ガス雰囲気中での冷却→1000℃~1200℃で2時間~5時間保持後に空冷または不活性ガス雰囲気中で冷却する1次時効処理→850℃~950℃で10時間~30時間保持後に空冷または不活性ガス雰囲気中で冷却する2次時効処理
という一連のものである。
Claims (6)
- Cr:6質量%以上12質量%以下、
Mo:0.4質量%以上3.0質量%以下、
W:6質量%以上10質量%以下、
Al:4.0質量%以上6.5質量%以下、
Nb:0質量%以上1質量%以下、
Ta:8質量%以上12質量%以下、
Hf:0質量%以上0.15質量%以下、
Si:0.01質量%以上0.2質量%以下、および
Zr:0質量%以上0.04質量%以下、
を含有し、
B、C、Y、La、CeまたはVの少なくとも一つの元素の含有が許容され、
残部がNiおよび不可避的不純物からなることを特徴とするNi基単結晶超合金。 - Cr:7質量%以上12質量%以下、
Mo:0.4質量%以上2.5質量%以下、
W:7質量%以上10質量%以下、
Al:4.0質量%以上6.5質量%以下、
Nb:0質量%以上1質量%以下、
Ta:9質量%以上11質量%以下、
Hf:0質量%以上0.15質量%以下、
Si:0.01質量%以上0.2質量%以下、および
Zr:0質量%以上0.04質量%以下、
を含有し、
B、C、Y、La、CeまたはVの少なくとも一つの元素の含有が許容され、
残部がNiおよび不可避的不純物からなることを特徴とするNi基単結晶超合金。 - Cr:8質量%以上10質量%以下、
Mo:0.4質量%以上2.0質量%以下、
W:7質量%以上9質量%以下、
Al:4.0質量%以上6.5質量%以下、
Nb:0質量%以上1質量%以下、
Ta:10質量%以上11質量%以下、
Hf:0質量%以上0.15質量%以下、
Si:0.01質量%以上0.2質量%以下、および
Zr:0質量%以上0.04質量%以下、
を含有し、
B、C、Y、La、CeまたはVの少なくとも一つの元素の含有が許容され、
残部がNiおよび不可避的不純物からなることを特徴とするNi基単結晶超合金。 - 含有が許容される前記元素の組成比が、
B:0.05質量%以下、
C:0.15質量%以下、
Y:0.1質量%以下、
La:0.1質量%以下、
Ce:0.1質量%以下、
V:1質量%以下、
であることを特徴とする請求項1から3のいずれか一項に記載のNi基単結晶超合金。 - クリープ寿命τ(h)が、
τ(h)= -3208+11XCo+40XCr+139XMo+93XW+327XAl+146XTi+45XNb+53XTa (1)
(ただし、τ(h)はクリープ寿命(時間)、XCo、XCr、XMo、XW、XAl、XTi、XNb、XTaは、それぞれ、コバルト、クロム、モリブデン、タングステン、アルミニウム、チタン、ニオブ、タンタルの組成比(質量%))を示す)
で示されるとき、τ(h)≧120であることを特徴とする請求項1から4のいずれか一項に記載のNi基単結晶超合金。 - 前記クリープ寿命τ(h)が200以上であることを特徴とする請求項5に記載のNi基単結晶超合金。
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US14/419,765 US9816161B2 (en) | 2012-08-09 | 2013-07-30 | Ni-based single crystal superalloy |
DE112013003971.0T DE112013003971T5 (de) | 2012-08-09 | 2013-07-30 | Nickelbasierte einkristalline Superlegierung |
KR1020157002347A KR101687320B1 (ko) | 2012-08-09 | 2013-07-30 | Ni기 단결정 초합금 |
CN201380041423.1A CN104520457B (zh) | 2012-08-09 | 2013-07-30 | Ni基单晶超合金 |
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JP2012177573A JP6016016B2 (ja) | 2012-08-09 | 2012-08-09 | Ni基単結晶超合金 |
JP2012-177573 | 2012-08-09 |
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JP (1) | JP6016016B2 (ja) |
KR (1) | KR101687320B1 (ja) |
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US9816161B2 (en) | 2017-11-14 |
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CN104520457A (zh) | 2015-04-15 |
JP2014034720A (ja) | 2014-02-24 |
KR20150044879A (ko) | 2015-04-27 |
DE112013003971T5 (de) | 2015-06-25 |
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