CN100482824C - Single crystal high temperature nickel base alloy containing rhenium and its preparing process - Google Patents
Single crystal high temperature nickel base alloy containing rhenium and its preparing process Download PDFInfo
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 60
- 239000000956 alloy Substances 0.000 title claims abstract description 60
- 239000013078 crystal Substances 0.000 title claims description 47
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims description 14
- 229910052759 nickel Inorganic materials 0.000 title claims description 7
- 229910052702 rhenium Inorganic materials 0.000 title claims description 7
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 title claims description 6
- 238000000034 method Methods 0.000 title description 6
- 238000002360 preparation method Methods 0.000 claims abstract description 10
- 230000032683 aging Effects 0.000 claims abstract description 6
- 238000005275 alloying Methods 0.000 claims description 12
- 239000000470 constituent Substances 0.000 claims description 9
- 238000001816 cooling Methods 0.000 claims description 9
- 238000005516 engineering process Methods 0.000 claims description 9
- 230000006698 induction Effects 0.000 claims description 6
- 238000002844 melting Methods 0.000 claims description 5
- 230000008018 melting Effects 0.000 claims description 5
- 238000012545 processing Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 11
- 238000003723 Smelting Methods 0.000 abstract description 2
- 239000006104 solid solution Substances 0.000 abstract description 2
- 230000001939 inductive effect Effects 0.000 abstract 1
- 229910000601 superalloy Inorganic materials 0.000 description 11
- 238000010438 heat treatment Methods 0.000 description 7
- 238000007669 thermal treatment Methods 0.000 description 6
- 230000005496 eutectics Effects 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 238000007711 solidification Methods 0.000 description 4
- 230000008023 solidification Effects 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 3
- 239000011651 chromium Substances 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000018109 developmental process Effects 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 239000010955 niobium Substances 0.000 description 3
- 229910052721 tungsten Inorganic materials 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009415 formwork Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000012528 membrane Substances 0.000 description 2
- 229910052750 molybdenum Inorganic materials 0.000 description 2
- 239000011733 molybdenum Substances 0.000 description 2
- 229910052758 niobium Inorganic materials 0.000 description 2
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 2
- 238000007670 refining Methods 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 229910052715 tantalum Inorganic materials 0.000 description 2
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 2
- 239000010937 tungsten Substances 0.000 description 2
- 229910018138 Al-Y Inorganic materials 0.000 description 1
- 229910000995 CMSX-10 Inorganic materials 0.000 description 1
- 229910001257 Nb alloy Inorganic materials 0.000 description 1
- 241001062472 Stokellia anisodon Species 0.000 description 1
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 description 1
- 239000005864 Sulphur Substances 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- QDWJUBJKEHXSMT-UHFFFAOYSA-N boranylidynenickel Chemical compound [Ni]#B QDWJUBJKEHXSMT-UHFFFAOYSA-N 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
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- 210000000795 conjunctiva Anatomy 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- PTVDYARBVCBHSL-UHFFFAOYSA-N copper;hydrate Chemical compound O.[Cu] PTVDYARBVCBHSL-UHFFFAOYSA-N 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 229910052593 corundum Inorganic materials 0.000 description 1
- 239000010431 corundum Substances 0.000 description 1
- 238000002425 crystallisation Methods 0.000 description 1
- 230000008025 crystallization Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- MCWXGJITAZMZEV-UHFFFAOYSA-N dimethoate Chemical compound CNC(=O)CSP(=S)(OC)OC MCWXGJITAZMZEV-UHFFFAOYSA-N 0.000 description 1
- YGANSGVIUGARFR-UHFFFAOYSA-N dipotassium dioxosilane oxo(oxoalumanyloxy)alumane oxygen(2-) Chemical compound [O--].[K+].[K+].O=[Si]=O.O=[Al]O[Al]=O YGANSGVIUGARFR-UHFFFAOYSA-N 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229910052627 muscovite Inorganic materials 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
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- 230000035882 stress Effects 0.000 description 1
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
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Abstract
The present invention relates to high temperature monocrystal alloy containing Re, and is especially high temperature nickel-base monocrystal alloy containing Re and its preparation process. The high temperature nickel-base monocrystal alloy containing Re consists of C 0.12-0.18 (in wt%, the same below),Cr 4.3-5.6,Al 5.6-6.3,Co 8.0-10.0,Mo 0.8-1.4,W 7.7-9.3,Nb 1.4-1.8,Ta 3.5-4.5, Re 3.5-4.5,Y 0.001-0.005,RE 0.005-0.025,and Ni for the rest. The preparation process of the high temperature nickel-base monocrystal alloy containing Re includes smelting of mother alloy in a vacuum inducing furnace, growing monocrystal at temperature gradient of 60-100 K/cm and growing speed of 2-10 mm/min in a monocrystal furnace, solid solution homogenizing treatment, high temperature ageing and low temperature ageing. The material of the present invention has high endurance limit and creep limit, high heat stability and other excellent performance.
Description
Technical field
The present invention relates to technologies of preparing such as rhenium-containing single crystal super alloy and thermal treatment, a kind of creep strength height, the long rhenium-containing of high-temperature duration life (Re) nickel-based monocrystal high-temperature turbine working-blade material are provided especially and have prepared the process system of this material.
Background technology
Along with the raising of temperature before the engine turbine, to turbine blade, particularly high temperature resistant the and strength property level of high-pressure turbine blade has proposed more and more higher requirement.Since the eighties in 20th century, the development of single crystal super alloy turbine blade has become modern aeroengine design and one of key technology of making.At present, thrust-weight ratio is that 10 aircraft engine F119 (U.S.), F120 (U.S.), GE90 (U.S.), EJ200 (English, moral, meaning, west), M88-2 (method), P2000 (Russia) etc. have selected for use single crystal alloy as blade material.The s-generation of studying in succession and using, third generation single crystal alloy improve about 30 ℃ and 60 ℃ than the warm ability of holding of first-generation single crystal super alloy respectively.The warm ability of holding of the 4th generation single crystal alloy RR3010 of Chu Xianing reaches 1180 ℃ in recent years, is used on the Trent engine of the up-to-date development of Britain RR company.
The Howmet company of the U.S., GE company, PCC company, Allison company and Britain RR company, the CNECMA company of France, manufacturer's equal mass production monocrystalline parts such as Muscovite SALUT engine shop, kind comprises moving turbine blade, turning vane, blade inner and outer ring, nozzle fan-shaped section, the piece of obturaging, nozzle burner etc., is used for military and commercial aircraft, tank, naval vessel, industry gas turbine, guided missile, rocket, space shuttle etc.The range of application of single crystal super alloy more and more widely, particularly adopting single crystal alloy to prepare moving turbine blade has become advanced aircraft engine main development tendency.
Thermal treatment has tangible influence to the creep rupture strength of single crystal alloy, and for example in the MC2 single crystal alloy, as long as solution treatment is 1300 ℃ of insulations 3 hours, and first-generation single crystal super alloy all is easier to homogenizing and handles except PWA1480.And in the third generation single crystal super alloy owing to contain a large amount of alloying elements, particularly Ta and W promotes the formation of (γ+γ ') eutectic phase, therefore without containing considerable (γ+γ ') eutectic in the heat treated solidified structure.Experiment shows: adopts simple isothermal solution heat treatment can not eliminate these eutectic phases, must adopt complicated heat treatment technology, and could the basically eliminate eutectic phase.For example: the CMSX-10M single crystal super alloy carries out 1337 ℃/3h of pre-treatment earlier in order to eliminate these (γ+γ ') eutectics fully, is raised to 1367 ℃ with 3 ℃/h temperature rise rate then, is incubated 3 hours air coolings.Erikson adopts 1366 ℃ of soaking times to reach 30～35h when the CMSX-10 solution heat treatment.Therefore, must scrutinize the heat treating regime of single crystal alloy, to give full play to the potentiality of alloy.Correct heat treating regime will make a cube γ ' be on good terms and obtain the ideal creep strength, and reason is to promote a uniform distressed structure, to guarantee low creep speed.
Summary of the invention
The object of the present invention is to provide a kind of Re of containing single crystal super alloy and preparation technology thereof, be used for the long high-temperature turbine working-blade material of requirement creep strength height, high-temperature duration life and prepare the process system of this material.
Technical scheme of the present invention is:
The present invention contains Re nickel-base high-temperature single crystal alloy (being designated hereinafter simply as DD32) and comprises following alloying constituent (weight percent):
C 0.12～0.18, and Cr 4.3～5.6, and Al 5.6～6.3, and Co 8.0～10.0, and Mo 0.8～1.4, and W 7.7～9.3, and Nb 1.4～1.8, and Ta 3.5～4.5, and Re 3.5～4.5, and Y 0.001～0.005, and Ni is surplus.
Also comprise and add 0.005～0.025%RE (mishmetal).Alloy of the present invention allows the impurity and the gas content scope of existence, and is as shown in table 1.
Table 1 DD32 monocrystalline foreign matter content (wt%)
Principle of design of the present invention is as follows:
The present invention mainly is that the γ ' that adds more aluminium formation high-volume fractional improves its intensity mutually; The adding of Re still all has great role to the raising of the temperature resistant capability of directionally solidified alloy to single crystal alloy.Re mainly enters in the γ matrix, forms to be of a size of～the Re atomic group of the short range order of 1nm, can hinder dislocation motion effectively, and its reduces alloying element rate of diffusion, stops the alligatoring of γ ' phase, and improves γ/γ ' mismatch.In addition, there is 20% Re to enter γ ' phase approximately, directly strengthens γ ' phase.The adding of Re helps to reduce the crystal grain defective and the surperficial recrystallize of single crystal casting, and also beneficial to the anti-environmental performance of alloy.Re joins the alligatoring that can hinder γ ' phase in the superalloy effectively, improves the alligatoring intensity of activation of γ ' phase, thereby can improve the mechanical behavior under high temperature of single crystal super alloy.Further increase γ ' phase amount by adding niobium, improved the lattice misfit degree of γ-γ ', strengthened the strengthening effect of γ ' phase, also form γ simultaneously and " strengthen its room temperature and middle temperature mechanical property mutually; Add a certain amount of carbon, strengthen on the one hand crystal boundary, come reinforced alloys with the more carbide of formation such as tantalum, niobium, chromium on the other hand; Alloying element such as tungsten, molybdenum mainly plays the vital role of solid solution strengthened alloy, and W+Mo content is the important parameter that increases creep life, along with the increase of their content increases creep life thereupon.Co is little to the influence of the heat resistance of alloy, but can significantly improve the plasticity of alloy, and Co can improve the creep life under heavily stressed.The adding of Y (200ppm) can obviously improve the antioxidant property of single crystal alloy, and also beneficial to thermal fatigue property.Add RE in the alloy and carry out microalloying, crystal boundary is strengthened in the refinement that helps dendritic structure, and sulphur content in the control alloy improves creep rupture life.Alloy sample of the present invention adopts current in the world directional solidification technique preparation, has eliminated horizontal and vertical crystal boundary, has improved the initial melting temperature of alloy.
The present invention contains the preparation technology of Re nickel-base high-temperature single crystal alloy, adopts the vacuum induction melting mother alloy, and the monocrystal growing furnace thermograde is in 60K/cm～100K/cm scope, and single crystal growth rate prepares single crystal blade or coupon in 2～10mm/min scope; Air cooling is carried out in solution treatment in 2～6 hours in 1270～1300 ℃ of scopes then subsequently, then carries out homogenizing in 2～6 hours in 1260～1290 ℃ of scopes and handles, and carries out air cooling subsequently; In 1100～1150 ℃ of scopes, carry out high-temperature aging then in 3～6 hours and handle, then in 850～890 ℃ of scopes, carry out low temperature aging processing in 16～36 hours, carry out air cooling subsequently.
The present invention has following advantage:
1, the material that adopts the present invention to obtain has high stress-rupture strength limit and creeping limit.
2, the material that adopts the present invention to obtain has high-temperature oxidation resistant and excellent thermal corrosion resistance, the thermostability height.
3, the material that adopts the present invention to obtain have stretch and rupture ductility good.
4, the material that adopts the present invention to obtain has good thermal fatigue resistance and mechanical fatigue performance.
5, heat treatment window of the present invention is wide, and solution treatment is easy to control.
6, preparation technology of the present invention is reasonable, the production efficiency height.
7, adopt heat treating regime of the present invention that as cast condition γ ' more than 99% is dissolved, the cubes γ ' that separates out uniform distribution and regularly arranged tiny (0.4～0.5 μ m) mutually, and on the γ matrix, separate out the γ ' phase of thinner (～0.3 μ m), and make this single crystal organization stable, be easy to control the effect of strengthening hindering dislocation motion, improve creep strength.
Description of drawings
Fig. 1 is Larson-Miller (Larsen-Miller) curve.Map parameter P is a relational expression, does not have concrete implication, and T is temperature (K), t be the time (hour).
Embodiment
Below by embodiment in detail the present invention is described in detail.
The present invention tests and uses mother alloy through ZG-0.025B type vacuum induction melting, and the Ni-Re prefabricated section that sinters is put into crucible bottom, puts into other elements more successively.Vacuumize before the intensification up to maximum vacuum, be warming up to and turn off the vacuum pump applying argon gas about 1300 ℃, continue to heat up, vacuumize again, refining, come out of the stove until fusing fully.Be cast into the master alloy ingot that is of a size of φ 80 * 500mm, the scale removal of polishing then is cut into suitable piece material and is used to prepare the monocrystalline sample.
Monocrystalline sample of the present invention is prepared on ZGG-0.02 type vacuum induction furnace with the spiral crystal separation method.The power of the heating system of directional solidification furnace is 30KW, adopts low-voltage and high-current, the heating of high purity graphite induction heating element.Adopt the SCR control withdrawing rate, the crystallizer withdrawing rate is stepless adjustable in the 0.1-1000mm/min scope.Vacuum system is made up of diffusion pump and preposition mechanical pump, and pumping speed is 30mm/min, and the working vacuum degree is 10
-5Torr.The preparation of directional freeze sample is carried out on directional solidification furnace, experiment is the corundum shell with formwork, and formwork is placed on the copper water crystallization device, and the mother alloy for preparing is packed in the CaO crucible, the directional solidification furnace state that is evacuated, send electrically heated, treat alloy melting after, measure the alloy melt temperature with the W-Re galvanic couple, in the time of 1600 ℃, cast, be incubated after 10 minutes, carry out pull, prepare oriented specimen with set rate.
Embodiment 1
The present embodiment composition sees Table 2, monocrystal growing furnace temperature gradient 80K/cm, single crystal growth rate is 4mm/min, and sample is through 1295 ℃/4h AC. (AC. is an air cooling)+AC.+850 ℃/24h of AC.+1150 ℃/4h of 1285 ℃/4h AC. thermal treatment, the performance of single crystal alloy such as table 3 and shown in Figure 1.The present invention quotes wherein the mechanical performance data of alloys such as DZ4, DZ22, Rene N4, DD3, SRR99 and DD6 and publishes.
Table 2 alloying constituent, wt%
| C | Cr | Al | Co | Mo | Nb | W | Ta | Re | Y | RE | Ni |
| 0.16 | 4.4 | 5.65 | 9.4 | 1.3 | 1.4 | 8.8 | 4.0 | 3.8 | 0.003 | 0.008 | The balance surplus |
100 hours creep rupture strength/MPa of table 3
| Alloy | 760℃ | 980℃ | 1100℃ |
| DD6 | 807 | 303 | 148 |
| DD32 | 785 | 315 | 160 |
According to shown in Figure 1, DD32 single crystal alloy high temperature drag of the present invention has 30 ℃ advantage than first-generation single crystal alloy SRR99 under low-stress, has 60 ℃ of advantages under heavily stressed.Exceed about 10MPa 980 ℃～1100 ℃ present domestic typical s-generation single crystal alloy DD6 creep rupture strengths of internal ratio.
Embodiment 2
Difference from Example 1 is, the alloying constituent of present embodiment (shown in the table 4).Monocrystal growing furnace temperature gradient 70K/cm, single crystal growth rate is 6mm/min.Through 1285 ℃/4hAC.+1275 ℃/4hAC.+1100 ℃/4hAC.+870 ℃/24h AC. thermal treatment.Do the creep rupture strength contrast with DZ4, DZ22, Rene N4 and DD3 alloy, the results are shown in Table 5.
Table 4 alloying constituent, wt%
| C | Cr | Al | Co | Mo | Nb | W | Ta | Re | Y | RE | Ni |
| 0.18 | 4.8 | 5.6 | 9.5 | 1.2 | 1.6 | 8.0 | 3.6 | 4.0 | 0.005 | 0.005 | Surplus |
100 hours creep rupture strength/MPa of some alloys of table 5
| Alloy | 760 |
800℃ | 900℃ | 980℃ | 1000℃ | 1040℃ |
| DZ4 | 804 | 677 | 353 | 206 | 181 | 142 |
| DZ22 | 804 | 653 | 375 | 213 | 181 | 137 |
| ReneN4 | 853 | 709 | 415 | 247 | 215 | 161 |
| DD3 | 814 | 706 | 368 | 226 | 201 | 177 |
| DD32 | 785 | 620 | 420 | 310 | 280 | 200 |
As shown in Table 5, the creep rupture strength of DD32 single crystal alloy of the present invention more than 900 ℃ has very remarkable advantages than typical directed superalloy (DZ4, DZ22) and first-generation single crystal alloy (DD3, ReneN4).
Embodiment 3
Difference from Example 1 is, the alloying constituent of present embodiment is shown in Table 6, monocrystal growing furnace temperature gradient 70K/cm, single crystal growth rate is 6mm/min, after AC.+1280 ℃ of 1290 ℃/4h/4hAC.+1100 ℃/4hAC.+870 ℃/24h AC. thermal treatment, the tensile property comparing result of DD32 monocrystalline and each representative temperature of SRR99 is as shown in table 7.The DD32 monocrystalline is more or less the same at each representative temperature tensile property and SRR99 below 900 ℃, but has remarkable advantages 1000 ℃ and 1100 ℃ of tensile strengths.
Table 6 alloying constituent, wt%
| C | Cr | Al | Co | Mo | Nb | W | Ta | Re | Y | RE | Ni |
| 0.14 | 5.0 | 5.65 | 9.4 | 0.98 | 1.8 | 7.8 | 4.4 | 3.6 | 0.006 | 0.02 | The balance surplus |
The tensile property contrast of table 7 DD32 monocrystalline and each representative temperature of SRR99
Embodiment 4
Difference from Example 1 is, the alloying constituent of present embodiment is shown in Table 8, the about 80K/cm of monocrystal growing furnace temperature gradient, after AC.+1100 ℃ of AC.+1280 ℃/4h of 1290 ℃/4h/4hAC.+890 ℃/16h AC. thermal treatment, the creep result is as shown in table 9 during 1000 ℃ of DD32 monocrystalline; Table 10 is the creep strength of 1000 ℃ of some first-generation monocrystalline.
Table 8 alloying constituent, wt%
| C | Cr | Al | Co | Mo | Nb | W | Ta | Re | Y | RE | Ni |
| 0.12 | 5.2 | 5.6 | 9.6 | 1.4 | 1.6 | 9.2 | 3.6 | 4.2 | 0.001 | 0.01 | The balance surplus |
Adopt vacuum induction furnace smelting experiment mother alloy, smelt crucible and select the CaO crucible for use, temp measuring system is W-Re galvanic couple and JH-5 type infrared ray optical direction temperature/vacuum degree measuring instrument, and the thermometric protective casing is the outer ZrO of coating
2The Mo-Al of (CeO is stable) and BN
2O
3Metal ceramic tube.Operating process is: carbon, nickel boron master alloy, chromium, tungsten, molybdenum, niobium alloy element and nickel plate are packed in the crucible; Vacuumize, get rid of for little electric current baking crucible and adhere to gas, when vacuum tightness reaches 10
-3During Pa, increase the power melted alloy; After fusing finished, at 1600 ℃ of refining 5～7min, power failure, conjunctiva, rupture of membranes added Al and Al-Y master alloy and mishmetal RE, and back power failure cooling is stirred in high-power then stirring, and the heavy current impact rupture of membranes is cast into master alloy ingot at 1450 ℃.
Table 9 DD32 monocrystalline is the creep under the different stress conditions in the time of 1000 ℃
| t(h) | 152.1MPa | t(h) | 186.4MPa | t(h) | 215.8MPa | t(h) | 245.3MPa | t(h) | 343.4MPa |
| 10 | 0.70 | 20 | 0.25 | 10 | 0.25 | 6 | 0.90 | 2 | 1.00 |
| 20 | 0.85 | 50 | 0.40 | 20 | 0.50 | 10 | 1.2 | 3 | 2.00 |
| 50 | 1.00 | 100 | 0.55 | 50 | 1.8 | 20 | 1.65 | 4 | 3.00 |
| 100 | 1.20 | 150 | 0.80 | 70 | 2.00 | 30 | 2.15 | 6 | 4.00 |
| 200 | 1.50 | 200 | 1.20 | 100 | 3.60 | 40 | 3.10 | 7 | 5.00 |
| 300 | 1.85 | 250 | 1.70 | 110 | 5.00 | 50 | 5.00 | 8 | 6.00 |
| 400 | 2.20 | 300 | 2.40 | 124 | 7.50 | 55 | 7.00 | 10 | 8.75 |
Some single crystal alloys of table 10 are creep strength in the time of 1000 ℃
| Alloy | σ 0.1/100/MPa | σ 0.2/100/MPa | σ 1.0/100/MPa |
| DD402 | 88 | 115 | 208 |
| Alloy | σ 0.2/100/MPa | - | σ 1.0/100/MPa |
| DD3 | 78.5 | - | 196 |
By table 9 and table 10 as can be known, the DD32 single crystal alloy has very remarkable advantages than first-generation single crystal alloy, the creep-resistant property excellence.
Claims (2)
1, a kind of single crystal high temperature nickel base alloy containing rhenium, it is characterized in that by weight percentage, alloying constituent comprises: C 0.12～0.18, Cr 4.3～5.6, and Al 5.6～6.3, and Co 8.0～10.0, Mo 0.8～1.4, W 7.7～9.3, and Nb 1.4～1.8, and Ta 3.5～4.5, Re 3.5～4.5, Y 0.001～0.003, and RE 0.005～0.020%, and Ni is surplus.
2, according to the preparation technology of claim 1 single crystal high temperature nickel base alloy containing rhenium, adopt the vacuum induction melting mother alloy, it is characterized in that: at monocrystal growing furnace temperature gradient 60K/cm～100K/cm, single crystal growth rate is preparation single crystal blade or a coupon in 2～10mm/min scope; Air cooling is carried out in solution treatment in 2～6 hours in 1270～1300 ℃ of scopes then subsequently, then carries out homogenizing in 2～6 hours in 1260～1290 ℃ of scopes and handles, and carries out air cooling subsequently; In 1100～1150 ℃ of scopes, carry out high-temperature aging then in 3～6 hours and handle, then in 850～890 ℃ of scopes, carry out low temperature aging processing in 16～36 hours, carry out air cooling subsequently.
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| CN108588498B (en) * | 2018-05-30 | 2020-04-07 | 哈尔滨理工大学 | Nickel-based gradient material and method for preparing nickel-based gradient material by selective laser melting method |
| CN109014215B (en) * | 2018-07-18 | 2019-12-03 | 西安交通大学 | A kind of heat treatment method of increasing material manufacturing monocrystal nickel-base high-temperature alloy |
| CN110777284B (en) * | 2019-11-26 | 2021-08-03 | 中国科学院金属研究所 | High-defect-tolerance single-crystal high-temperature alloy component and preparation method thereof |
| CN113512669A (en) * | 2020-04-09 | 2021-10-19 | 辽宁红银金属有限公司 | Hydrogen embrittlement resistant high-temperature alloy and preparation method thereof |
| CN114250518B (en) * | 2021-12-30 | 2023-01-31 | 苏州高晶新材料科技有限公司 | Nickel-based single crystal superalloy and preparation method thereof |
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