CN111440967B - High-thermal-stability high-strength Re-free nickel-based single crystal superalloy and preparation process thereof - Google Patents
High-thermal-stability high-strength Re-free nickel-based single crystal superalloy and preparation process thereof Download PDFInfo
- Publication number
- CN111440967B CN111440967B CN202010381269.4A CN202010381269A CN111440967B CN 111440967 B CN111440967 B CN 111440967B CN 202010381269 A CN202010381269 A CN 202010381269A CN 111440967 B CN111440967 B CN 111440967B
- Authority
- CN
- China
- Prior art keywords
- alloy
- single crystal
- temperature
- strength
- based single
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 54
- 239000013078 crystal Substances 0.000 title claims abstract description 48
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 28
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 24
- 238000002360 preparation method Methods 0.000 title claims abstract description 7
- 239000000956 alloy Substances 0.000 claims abstract description 105
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 104
- 239000000126 substance Substances 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims abstract description 10
- 238000010438 heat treatment Methods 0.000 claims description 27
- 230000032683 aging Effects 0.000 claims description 10
- 238000003723 Smelting Methods 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 6
- 239000006104 solid solution Substances 0.000 claims description 6
- 239000002994 raw material Substances 0.000 claims description 5
- 238000007711 solidification Methods 0.000 claims description 5
- 230000008023 solidification Effects 0.000 claims description 5
- 238000005266 casting Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 230000006698 induction Effects 0.000 claims description 3
- 239000000243 solution Substances 0.000 claims description 3
- 229910052797 bismuth Inorganic materials 0.000 claims description 2
- 239000012535 impurity Substances 0.000 claims description 2
- 229910052745 lead Inorganic materials 0.000 claims description 2
- 229910052757 nitrogen Inorganic materials 0.000 claims description 2
- 229910052698 phosphorus Inorganic materials 0.000 claims description 2
- 238000010187 selection method Methods 0.000 claims description 2
- 238000005303 weighing Methods 0.000 claims description 2
- 230000003647 oxidation Effects 0.000 abstract description 11
- 238000007254 oxidation reaction Methods 0.000 abstract description 11
- 229910001173 rene N5 Inorganic materials 0.000 abstract description 8
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 229910000510 noble metal Inorganic materials 0.000 abstract description 2
- 238000005728 strengthening Methods 0.000 description 10
- 238000001556 precipitation Methods 0.000 description 9
- 230000000694 effects Effects 0.000 description 8
- 229910052702 rhenium Inorganic materials 0.000 description 7
- 238000012360 testing method Methods 0.000 description 6
- 229910052782 aluminium Inorganic materials 0.000 description 5
- 230000035882 stress Effects 0.000 description 5
- 229910052715 tantalum Inorganic materials 0.000 description 5
- 229910052719 titanium Inorganic materials 0.000 description 5
- 238000011161 development Methods 0.000 description 4
- 230000018109 developmental process Effects 0.000 description 4
- 229910052750 molybdenum Inorganic materials 0.000 description 4
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 description 4
- 229910052804 chromium Inorganic materials 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000007774 longterm Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 229910052721 tungsten Inorganic materials 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000006866 deterioration Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000001739 density measurement Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000010970 precious metal Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910052707 ruthenium Inorganic materials 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- 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%
-
- 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
- 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
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Crystallography & Structural Chemistry (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Inorganic Chemistry (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a high-thermal stability high-strength Re-free nickel-based single crystal superalloy and a preparation process thereof, belonging to the field of nickel-based single crystal superalloys. The alloy comprises the following chemical components in percentage by weight: 7.1-11% of Cr, 7.5-14% of Co, 0.5-3% of Mo, 7-10% of W, 4.5-7% of Al, 5-9% of Ta, 0.5-3% of Ti and the balance of Ni. The alloy has excellent thermal stability, high-temperature strength, oxidation resistance and cold and hot fatigue performance, the mechanical property of the alloy is still maintained at a higher level after the alloy is subjected to long-time thermal exposure at high temperature, a noble metal element Re is not contained, the durability of the alloy is equivalent to that of a typical Rene N5 alloy containing 3% of Re, and the cost is reduced by more than 50%. The method is particularly suitable for manufacturing hot-end high-temperature components with long service life and high reliability in the fields of aviation, aerospace, energy sources and the like.
Description
Technical Field
The invention relates to the technical field of nickel-based single crystal superalloy, in particular to a high-thermal-stability high-strength Re-free nickel-based single crystal superalloy and a preparation process thereof.
Background
With the development of the industrial fields of aviation, aerospace, energy and the like, the requirement on the temperature bearing capacity of high-temperature alloy materials is continuously improved. In order to meet the requirements of advanced equipment power propulsion systems, the high-temperature alloy undergoes several development processes from isometric crystal to directional columnar crystal and single crystal, and the temperature bearing capacity of the high-temperature alloy is remarkably improved. Since the advent of nickel-based single crystal alloys, nickel-based single crystal alloys have become the preferred material for hot end components of advanced aircraft engines and industrial gas turbines due to their high temperature-bearing capacity, superior creep resistance, and good oxidation and corrosion resistance. So far, single crystal alloys have been developed for many generations, and with the increasing generations of single crystal high temperature alloys, the total amount of refractory elements such as W, Mo and Cr is gradually increased, and the high temperature strength is gradually improved. However, with the increase of the total amount of the refractory elements, the tendency of separating out the TCP harmful phase in the alloy is obviously enhanced, the TCP harmful phase can become a crack initiation position, and meanwhile, the strengthening effect of the refractory elements is also reduced, so that the mechanical property of the alloy is obviously reduced, and the long-term service life of parts is damaged. Therefore, it is a future development trend to obtain high-thermal stability and high-strength nickel-based single crystal superalloy. In addition, from the second generation of single crystal superalloys, the refractory element rhenium (Re) is almost added to strengthen the alloy, but rhenium is a rare element and has very little reserve in the crust. In addition, rhenium is expensive, and the addition of rhenium to the single crystal alloy not only greatly increases the cost of the alloy, but also tends to cause the precipitation of a TCP phase, which is detrimental to the thermal stability of the alloy. With the urgent need of high strength, low cost and high reliability alloy in the industrial field, especially in the aviation industry field, it is necessary to develop a second generation high temperature single crystal Ni-based alloy with high thermal stability and high strength without adding rare noble metal element Re.
Disclosure of Invention
In order to solve the problems of poor high-temperature structure stability, low strength, high cost and the like of the nickel-based single crystal superalloy in the prior art, the invention aims to provide a high-heat-stability high-strength Re-free nickel-based single crystal superalloy and a preparation process thereof, wherein the alloy has excellent medium-temperature and high-temperature strength, high structure heat stability, strong oxidation resistance, no precious metal element Re, equivalent durability to the performance of a typical Rene N5 alloy containing 3 wt.% of Re, and the cost is reduced by more than 50%. Is particularly suitable for manufacturing hot-end high-temperature components in the fields of aviation, aerospace, energy sources and the like.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a high-thermal-stability high-strength Re-free second-generation nickel-based single crystal superalloy (DD98m) comprises the following chemical components in percentage by weight:
7.1-11% of Cr, 7.5-14% of Co, 0.5-3% of Mo, 7-10% of W, 4.5-7% of Al, 5-9% of Ta, 0.5-3% of Tis and the balance of Ni.
The alloy comprises the following preferred chemical components in percentage by weight:
7.5-9.5% of Cr, 7.8-11% of Co, 1.8-3% of Mo, 7.5-9.5% of W, 4.5-6.5% of Al, 5-9% of Ta, 1.0-2.5% of Ti, and the balance of Ni.
In the chemical components of the nickel-based single crystal superalloy, the weight ratio of Ti to Al is controlled to be 0.25-0.4.
In the nickel-based single crystal superalloy, impurity elements meet the following requirements:
O≤0.003wt.％，N≤0.002wt.％，S≤0.003wt.％，P≤0.002wt.％，Si≤0.2wt.％，Pb≤0.0003wt.％，Bi≤0.00005wt.％。
the alloy chemical composition design of the invention is mainly based on the following:
the excellent high-temperature strength of the nickel-based single crystal superalloy comes from the solid solution strengthening effect of alloy elements and the precipitation strengthening effect of a precipitation phase. In order to obtain excellent high-temperature endurance/creep performance, a large amount of alloy elements are generally required to be added for improving the strength of the whole system, for example, elements such as Re, Ru, W and Mo are added for improving the solid solution strengthening effect of a matrix, and elements such as Al, Ti and Ta are added for improving the volume fraction of a precipitation phase and improving the particle strengthening effect of the precipitation phase. However, while the strength of the alloy is considered sufficiently, problems such as structural deterioration caused by excessive alloying and difficulty in forming parts must be considered, and these problems tend to increase the tendency of harmful phases to appear in the single crystal alloy or the tendency of the parts to have mixed crystals, resulting in deterioration of alloy properties or poor engineering applicability. In addition, effective control of the alloy manufacturing cost is one of the factors that must be considered in order to achieve sustainable development in important industrial fields such as aircraft engines. Based on the design concept, the influence of various factors is fully considered in the alloy of the invention at the beginning of design. More W, Mo, Cr and other elements are added into the alloy, so that the solid solution strengthening effect of an alloy matrix is improved, the elements such as Re, Ru and the like are effectively replaced, the alloy strength is improved, and the manufacturing cost is reduced; on the other hand, in order to avoid the problem of increasing the tendency of harmful phase precipitation caused by the increase of solid solution strengthening elements, more Co element is added into the alloy, so that the stability of an alloy system is improved similarly to Ru element, and the stability of a high-temperature structure of the alloy is improved. Meanwhile, in order to obtain a better precipitation strengthening effect, a large amount of Al, Ti, Ta and other precipitation phase forming elements need to be added into the alloy, but the durability of the alloy tends to increase firstly and then decrease along with the increase of the Al, Ti and Ta, and researches show that the atomic percentages of the precipitation phase forming elements and the solid solution strengthening elements are more suitable between 15 and 16 percent, and the ratio of Ti to Al is more suitable between 0.25 and 0.4; therefore, the contents of Al, Ti and Ta should be controlled to be 4.7-6.7% of Al, 5-9% of Ta and 0.5-3% of Ti, respectively.
Firstly, weighing alloy raw materials (pure metal simple substances of elements such as Ni, Co, Cr, W, Mo, Ta, Al, Ti and the like are used as raw materials) according to required alloy components, smelting in a vacuum induction smelting furnace, and then casting into a master alloy; remelting a mother alloy by adopting directional solidification equipment, and directionally solidifying and casting the mother alloy into a single crystal rod by adopting a spiral crystal selection method or a seed crystal method; the single crystal rod needs to be heat treated before use. The single crystal rod is subjected to heat treatment by adopting a vacuum or common muffle furnace, and the heat treatment system is carried out according to the following steps:
(1) high-temperature solution treatment: the temperature is gradually increased from 1240 ℃ to 1300 ℃ by adopting a staged temperature increasing method, and the specific process flow is as follows: heating from room temperature to 1240 ℃ and preserving heat for 1h, then heating to 1270 ℃ and preserving heat for 1h, then heating to 1280 ℃ and preserving heat for 1h, then heating to 1290 ℃ and preserving heat for 2h, then heating to 1300 ℃ and preserving heat for 4h, and then taking out and cooling to room temperature in the air.
(2) High-temperature aging treatment: keeping the temperature at 1050-.
(3) And (3) low-temperature aging treatment: keeping the temperature at 850-900 ℃ for 20-28 hours, and taking out the product to be cooled to room temperature in the air.
The invention has the following beneficial effects:
(1) the invention develops a high-thermal-stability and high-strength Re-free nickel-based single crystal superalloy based on a synergistic coupling action mechanism of strengthening elements between high-temperature structural stability and high-temperature strength, and the superalloy has excellent durability and high-temperature oxidation resistance, wherein the durability of the superalloy reaches 190h at 1093 ℃/137MPa, the durability of the superalloy reaches 280h at 1038 ℃/172MPa, the durability of the superalloy reaches 108h at 1010 ℃/235MPa, and the durability of the superalloy reaches 281h at 800 ℃/750 MPa.
(2) The alloy of the invention has complete oxidation resistance at 1010 ℃ and good hot corrosion resistance at 900 DEG C
(3) The alloy of the invention has the endurance life equivalent to the performance of a typical second generation single crystal superalloy Rene N5 containing 3% Re, but the cost is more than 50% lower than that of the Rene N5 alloy because of no element Re.
(4) After the alloy of the invention is subjected to heat exposure experiments for 1000 hours at 950 ℃ and 1050 ℃, the alloy still has high-temperature strength and good structural stability.
(5) The alloy of the invention has a density of 8.57g/cm3And the density is lower than that of the foreign mature alloy Rene N5.
Drawings
FIG. 1 is an as-cast structure of an alloy of example 1 of the present invention;
FIG. 2 is the as-cast structure of the alloy of example 2 of the present invention;
FIG. 3 is a heat treated structure of the alloy of example 3 of the present invention;
FIG. 4 is a heat treated structure of the alloy of example 4 of the present invention;
FIG. 5 is a creep deformation curve for the alloy of example 6;
FIG. 6 is a graph of isothermal oxidation kinetics for the alloy of example 6;
FIG. 7 is the structure of the alloy of example 6 after 500h of heat exposure;
FIG. 8 is the structure of the alloy of example 6 after 1000h of thermal exposure;
FIG. 9 is the structure of example 6 alloy after 2000h of heat exposure;
FIG. 10 is a comparison of the cold-hot cycle fatigue crack length test for the alloy of example 6 of the present invention.
Detailed Description
The following examples further illustrate the invention and are not intended to limit the invention thereto.
The following specific preparation method requirements for each example and comparative alloy: the method comprises the steps of smelting raw materials by using a vacuum induction smelting furnace, casting the raw materials into a master alloy with chemical components meeting requirements, preparing a single crystal rod by using a directional solidification furnace, and carrying out heat treatment before use.
Preparing single crystal alloy on an industrial directional solidification furnace, wherein the temperature gradient range of the directional solidification furnace is 40-80 ℃/cm, the pouring temperature is 1480-1550 ℃, the temperature of a mold shell is consistent with the pouring temperature, and a single crystal test bar is prepared within the growth rate of 3-8 mm/min.
The heat treatment system of the single crystal alloy of the invention is as follows:
(1) high-temperature solution treatment, keeping the temperature at 1240-1300 ℃ for 4-10 hours, and air cooling to room temperature, wherein the specific process comprises the following steps: firstly heating to 1240 ℃ and preserving heat for 1h, then heating to 1270 ℃ and preserving heat for 1h, then heating to 1280 ℃ and preserving heat for 1h, then heating to 1290 ℃ and preserving heat for 2h, finally heating to 1300 ℃ and preserving heat for 4h, and air cooling to room temperature.
(2) High-temperature aging treatment, namely preserving the heat for 4 to 6 hours at 1050-;
(3) and (4) low-temperature aging treatment, keeping the temperature at 850-900 ℃ for 20-28 hours, and air cooling to room temperature.
Examples 1 to 6:
the chemical compositions of the nickel-based single crystal superalloys of inventive examples 1-6 are shown in table 1.
Table 1 list of chemical composition (wt.%) of the alloys of the invention (examples 1-6)
| Alloy (I) | Cr | Co | W | Al | Ti | Ta | Mo | Re | Ni |
| Example 1 | 7.8 | 8.0 | 8.0 | 5.2 | 1.56 | 5.5 | 1.8 | 0 | Surplus |
| Example 2 | 7.8 | 8.5 | 8.0 | 6.5 | 2.0 | 8.5 | 1.8 | 0 | Surplus |
| Example 3 | 9.1 | 10.0 | 9.2 | 5.5 | 1.45 | 5.5 | 2.5 | 0 | Surplus |
| Example 4 | 9.2 | 10.2 | 9.0 | 6.3 | 2.3 | 8.5 | 2.5 | 0 | Surplus |
| Example 5 | 8 | 10.5 | 8.5 | 6 | 2.0 | 8.5 | 2.2 | 0 | Surplus |
| Example 6 | 8.5 | 11 | 8.5 | 5 | 1.5 | 8.0 | 2 | 0 | Surplus |
| Rene N5 | 7.0 | 7.5 | 5.0 | 6.2 | 0 | 6.5 | 1.5 | 3 | Surplus |
The alloy in the above example was subjected to performance testing, with the following results:
1. the density measurement of the alloy of example 6 was 8.57g/cm3。
2. The alloy of example 5 was subjected to a durability test after heat treatment and machining, and the results are shown in table 2.
TABLE 2 example 5 alloy durability
| Temperature/degree | stress/MPa | Long life/h | Elongation/percent |
| 1093 | 137 | 190 | 7 |
| 1038 | 172 | 280 | 13 |
| 1010 | 235 | 108 | 21 |
| 1100 | 190 | 153 | 14 |
| 980 | 250 | 210 | 14 |
| 800 | 750 | 281 | 15 |
3. The durability data for the alloy of example 6 of the invention and the comparative alloy Rene N5 under several test conditions are shown in Table 3.
TABLE 3 permanence of the alloy of example 6 and the comparative alloy Rene N5
4. The as-cast structure of the alloy of example 1 of the present invention is shown in FIG. 1.
5. The as-cast structure of the alloy of example 2 of the present invention is shown in FIG. 2.
6. The structure of the alloy of example 3 of the present invention after heat treatment is shown in FIG. 3.
7. The structure of the alloy of example 4 of the present invention after heat treatment is shown in FIG. 4.
8. The strain-time creep curve of the alloy of example 6 of the present invention is shown in FIG. 5. It can be seen that the creep life of the alloy decreases significantly with increasing stress. Under the three stress conditions, the initial stage of creep is not obvious, and the creep acceleration stage is obvious. The time for steady state creep gradually decreases with increasing stress. This indicates that the stress has a significant effect on the change in creep rate under high temperature conditions.
9. The constant temperature oxidation kinetics curve of the alloy of example 6 of the present invention at 1010 ℃ is shown in FIG. 6. It can be seen that the weight of the sample tends to increase with the oxidation time, the weight gain increasing rapidly in the initial phase and then decreasing in magnitude. The average oxidation rate of the alloy at 1010 ℃ for 50h-100h is 0.035g/m2·h-1The alloy is determined according to HB5258-2000 "test method for measuring oxidation resistance of Steel and high temperature alloyThe temperature of 1010 ℃ is the complete oxidation resistance level.
10. The microstructure of the alloy of the embodiment 6 of the invention after long-term aging for 1000h, 500h, 1000h and 2000h is shown in figures 7-9, and no harmful TCP phase is precipitated. This indicates that the structure of the alloy of the present invention has excellent thermal stability.
11. The room temperature and high temperature tensile properties of the alloy of example 6 of the invention after 100h of thermal exposure at 950 ℃ and 1050 ℃ are shown in table 4. It can be seen that the strength of the alloy is reduced, but the high temperature strength is maintained at a high level.
TABLE 4 tensile Properties at 100h ageing at two temperatures
12. The room temperature and high temperature tensile properties of the alloy of example 6 of the invention after 500h of thermal exposure at 950 ℃ and 1050 ℃ are shown in table 5. It can be seen that the strength of the alloy is reduced, but the high temperature strength is maintained at a high level.
TABLE 5 tensile Properties at two temperatures over 500h
13. The room temperature and high temperature tensile properties of the alloy of example 6 of the invention after 1000h of thermal exposure at 950 ℃ and 1050 ℃ are shown in table 6. It can be seen that the strength of the alloy is reduced, but the high temperature strength is maintained at a high level.
TABLE 6 tensile Properties at 1000h ageing at two temperatures
14. The high temperature durability of the alloy of example 6 of the present invention after different time thermal exposures at 950 ℃ and 1050 ℃ is shown in Table 7. It can be seen that the endurance life is gradually reduced with the extension of the heat exposure time and the increase of the temperature, but the alloy still has higher endurance performance after 1000h of heat exposure.
TABLE 7 permanence of the alloys after long term aging at 1010 ℃/235MPa
15. The comparison of the fatigue crack length test results of the alloy of example 6 of the present invention and other alloys under the cold and hot cycle at room temperature to 1000 ℃ is shown in FIG. 10, which shows that the alloy of the present invention (DD98m) has excellent thermal crack resistance.
Claims (4)
1. A high-thermal stability high-strength Re-free nickel-based single crystal superalloy is characterized in that: the alloy comprises the following chemical components in percentage by weight:
7.1-11% of Cr, 10.2-14% of Co, 0.5-3% of Mo, 7-10% of W, 4.5-7% of Al, 8.0-9% of Ta, 0.5-3% of Ti and the balance of Ni; the weight ratio of Ti to Al is controlled to be 0.25-0.4;
the preparation process of the high-thermal stability high-strength Re-free nickel-based single crystal superalloy comprises the steps of firstly weighing alloy raw materials according to required alloy components, and casting a master alloy after smelting in a vacuum induction smelting furnace; remelting a mother alloy by adopting directional solidification equipment, and directionally solidifying into a single crystal rod by adopting a spiral crystal selection method or a seed crystal method; carrying out heat treatment on the single crystal rod before use; the single crystal rod is subjected to heat treatment by adopting a vacuum or common muffle furnace, and the heat treatment system is carried out according to the following steps:
(1) high-temperature solution treatment: adopting a staged heating method, and gradually heating the temperature from 1240 ℃ to 1300 ℃;
(2) high-temperature aging treatment: preserving the heat for 4-6 hours at 1050-;
(3) and (3) low-temperature aging treatment: keeping the temperature at 850-900 ℃ for 20-28 hours, and cooling to room temperature in air.
2. A high thermal stability high strength Re-free nickel based single crystal superalloy as in claim 1, wherein: the alloy comprises the following chemical components in percentage by weight:
7.5-9.5% of Cr, 10.2-11% of Co, 1.8-3% of Mo, 7.5-9.5% of W, 4.5-6.5% of Al, 8.9-9% of Ta, 1.0-2.5% of Ti and the balance of Ni.
3. A high thermal stability high strength Re-free nickel based single crystal superalloy according to claim 1 or 2, wherein: in the nickel-based single crystal superalloy, the components of impurities meet the following requirements:
O≤0.003wt.%，N≤0.002wt.%，S≤0.003wt.%，P≤0.002wt.%，Si≤0.2wt.%，Pb≤0.0003wt.%，Bi ≤0.00005wt.%。
4. a high thermal stability high strength Re-free nickel based single crystal superalloy as in claim 1, wherein: the specific process of the high-temperature solid solution treatment comprises the following steps: heating to 1240 ℃ and preserving heat for 1h, then heating to 1270 ℃ and preserving heat for 1h, then heating to 1280 ℃ and preserving heat for 1h, then heating to 1290 ℃ and preserving heat for 2h, finally heating to 1300 ℃ and preserving heat for 4h, and air cooling to room temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010381269.4A CN111440967B (en) | 2020-05-08 | 2020-05-08 | High-thermal-stability high-strength Re-free nickel-based single crystal superalloy and preparation process thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010381269.4A CN111440967B (en) | 2020-05-08 | 2020-05-08 | High-thermal-stability high-strength Re-free nickel-based single crystal superalloy and preparation process thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111440967A CN111440967A (en) | 2020-07-24 |
| CN111440967B true CN111440967B (en) | 2021-12-31 |
Family
ID=71655105
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010381269.4A Active CN111440967B (en) | 2020-05-08 | 2020-05-08 | High-thermal-stability high-strength Re-free nickel-based single crystal superalloy and preparation process thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111440967B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114196854B (en) * | 2020-09-02 | 2022-07-15 | 宝武特种冶金有限公司 | High-strength and difficult-to-deform nickel-based high-temperature alloy and preparation method thereof |
| CN112593122B (en) * | 2020-12-09 | 2023-02-03 | 中国科学院金属研究所 | Long-life high-strength hot-corrosion-resistant single crystal high-temperature alloy |
| CN112828310B (en) * | 2020-12-31 | 2023-01-24 | 湖北三江航天红阳机电有限公司 | Method for improving toughness of 3D printing nickel-based high-temperature alloy part |
| CN114606413B (en) * | 2022-03-17 | 2023-02-21 | 广州赛隆增材制造有限责任公司 | High-temperature alloy for additive manufacturing and application thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4639280A (en) * | 1983-12-29 | 1987-01-27 | Association Pour La Recherche Et Le Developpement Des Methodes Et Processus Industriels "A.R.M.I.N.E.S." | Monocrystalline alloy with a nickel matrix basis |
| US5435861A (en) * | 1992-02-05 | 1995-07-25 | Office National D'etudes Et De Recherches Aerospatiales | Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production |
| CN103966671A (en) * | 2014-03-31 | 2014-08-06 | 中国科学院金属研究所 | High-strength hot-corrosion-resistant Ni-based single crystal superalloy and preparation method |
| CN105200521A (en) * | 2014-05-28 | 2015-12-30 | 中国科学院金属研究所 | Rhenium-free low-density high-performance nickel-based monocrystalline high-temperature alloy and heat treatment technology thereof |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104975248B (en) * | 2015-06-30 | 2017-01-25 | 西北工业大学 | Solution treatment method of third generation nickel-base single crystal high temperature alloy |
| CN111004944A (en) * | 2019-12-31 | 2020-04-14 | 长安大学 | High-molybdenum second-generation nickel-based single crystal superalloy and preparation method thereof |
-
2020
- 2020-05-08 CN CN202010381269.4A patent/CN111440967B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4639280A (en) * | 1983-12-29 | 1987-01-27 | Association Pour La Recherche Et Le Developpement Des Methodes Et Processus Industriels "A.R.M.I.N.E.S." | Monocrystalline alloy with a nickel matrix basis |
| US5435861A (en) * | 1992-02-05 | 1995-07-25 | Office National D'etudes Et De Recherches Aerospatiales | Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production |
| CN103966671A (en) * | 2014-03-31 | 2014-08-06 | 中国科学院金属研究所 | High-strength hot-corrosion-resistant Ni-based single crystal superalloy and preparation method |
| CN105200521A (en) * | 2014-05-28 | 2015-12-30 | 中国科学院金属研究所 | Rhenium-free low-density high-performance nickel-based monocrystalline high-temperature alloy and heat treatment technology thereof |
Non-Patent Citations (3)
| Title |
|---|
| Effect of carbon addition on the creep properties in a;L.R. Liu etal.;《aterials Science and Engineering》;20041231;参见实验方法部分 * |
| Formation of carbides and their effects on stress rupture;L.R. Liu etal.;《Materials Science and Engineering》;20031231;参见实验方法部分 * |
| Microstructural evolution of a single crystal nickel-base superalloy;L.R. Liu etal.;《Materials Letters》;20031231;参见实验方法部分 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111440967A (en) | 2020-07-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111440967B (en) | High-thermal-stability high-strength Re-free nickel-based single crystal superalloy and preparation process thereof | |
| Sato et al. | A 5th generation SC superalloy with balanced high temperature properties and processability | |
| CN114032481B (en) | Method for homogenizing high-alloying high-temperature alloy material | |
| US8551265B2 (en) | Cobalt-base alloy with high heat resistance and high strength and process for producing the same | |
| JP2778705B2 (en) | Ni-based super heat-resistant alloy and method for producing the same | |
| CN113106299B (en) | Method for producing Ni-based wrought alloy material | |
| JP5867991B2 (en) | Heat treatment method and product for Ni-base superalloy article | |
| CN106636759B (en) | A kind of high thermal stability high-strength nickel based single-crystal high-temperature alloy that platinum family element is strengthened | |
| CN103966476B (en) | A kind of nickel base superalloy of the anti-fused salt corrosion of excellent performance | |
| CN106337145B (en) | Nickel-chromium-molybdenum alloy and method for producing same | |
| JP6315319B2 (en) | Method for producing Fe-Ni base superalloy | |
| CN114182139B (en) | Precipitation strengthening nickel-based high-temperature alloy and preparation method thereof | |
| CN103173865A (en) | Low-cost nickel-base single crystal high-temperature alloy and preparation method thereof | |
| CN110106397B (en) | High-temperature-resistant bolt alloy material and manufacturing method of bolt | |
| CN111074101A (en) | High-strength low-specific-ratio reorientation solidification nickel-based high-temperature alloy and preparation method and application thereof | |
| EP2730670B1 (en) | Ni-based casting alloy and steam turbine casting part using the same | |
| CN114672696A (en) | Ni-Co based high-temperature alloy and preparation method and application thereof | |
| CN114164357B (en) | Low-cost low-density nickel-based single crystal superalloy | |
| CN109536781B (en) | High-purity low-inclusion nickel-based powder high-temperature alloy and preparation method and application thereof | |
| CN114231767B (en) | Method for controlling sigma phase precipitation of hot corrosion resistant nickel-based superalloy | |
| CN111254317B (en) | Nickel-based casting alloy and preparation method thereof | |
| CN113913942A (en) | Nickel-based single crystal alloy, use and heat treatment method | |
| CN112176224A (en) | High-strength nickel-based single crystal superalloy with excellent comprehensive performance | |
| TWI657147B (en) | A HIGH STRENGH Ni-BASE ALLOY | |
| CN115874085B (en) | Nanophase reinforced tungsten-free cobalt-nickel-based superalloy and preparation method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |