CN109136654A - A kind of low rhenium corrosion and heat resistant long-life high intensity second generation nickel-base high-temperature single crystal alloy and its heat treatment process - Google Patents
A kind of low rhenium corrosion and heat resistant long-life high intensity second generation nickel-base high-temperature single crystal alloy and its heat treatment process Download PDFInfo
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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
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- 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
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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Abstract
本发明公开了一种低铼抗热腐蚀长寿命高强度第二代镍基单晶高温合金及其热处理工艺，属于抗热腐蚀镍基单晶高温合金技术领域。按重量百分含量计，该合金化学成分为：Cr：8.0～11.0％，Co：7.0～11.0％，Mo：0.1～0.5％，W：3.0～6.0％，Ta：4.0～7.0％，Al：3.8～5.2％，Ti：0～3.0％，Re：1.0～3.0％，C：0～0.2％，其余为Ni；6.0wt.％≤Al+Ti≤8.0wt.％，Al/Ti>1。该合金具备与典型第二代高强单晶合金相当的高温力学性能，并且具有良好的抗热腐蚀性能和长期组织稳定性。The invention discloses a second-generation nickel-based single crystal superalloy with low rhenium, anti-hot corrosion, long life and high strength and a heat treatment process thereof, belonging to the technical field of hot-corrosion-resistant nickel-based single crystal superalloy. By weight percentage, the chemical composition of the alloy is: Cr: 8.0-11.0%, Co: 7.0-11.0%, Mo: 0.1-0.5%, W: 3.0-6.0%, Ta: 4.0-7.0%, Al: 3.8～5.2%, Ti: 0～3.0%, Re: 1.0～3.0%, C: 0～0.2%, the rest are Ni; 6.0wt.%≤Al+Ti≤8.0wt.%, Al/Ti>1. The alloy has high-temperature mechanical properties comparable to typical second-generation high-strength single-crystal alloys, as well as good hot corrosion resistance and long-term microstructure stability.
Description
Technical field
The invention belongs to corrosion and heat resistant nickel-base high-temperature single crystal alloy technical fields, and in particular to a kind of low rhenium corrosion and heat resistant is long
Service life high intensity second generation nickel-base high-temperature single crystal alloy and its heat treatment process, are primarily adapted for use in and hold under the conditions of High Temperature Hot-corrosion Behaviorof
By the components of higher stress, it is on active service under high temperature turbine parts and all kinds of marine environment including ground industry gas turbine
The high temperature turbine parts on naval vessel and carrier-borne aircraft.
Background technique
With the development of aero-engine and gas turbine technology, intake air temperature is constantly promoted, to material temperature capability
It is required that it is higher and higher, for the high-temperature turbine portion on the naval vessel and carrier-borne aircraft applied under ground industry gas turbine and marine environment
Part does not require nothing more than it and has higher mechanical behavior under high temperature, mechanical behavior under high temperature when especially long, while requiring to have excellent
Hot corrosion resistance.In addition, for the high temperature turbine parts of long life serve, alloy must also have both good chronic tissue with
Stability.Currently, the corrosion and heat resistant single crystal super alloy that European and American developed countries develop mainly includes PWA1483, CMSX-
The corrosion and heat resistant single crystal super alloy of the alloys such as 11B, CMSX-11C, domestic development mainly has the alloys such as DD8, DD10 and DD413,
Cr element is the main alloy element for improving alloy hot corrosion resistance, these corrosion and heat resistant single crystal alloys generally contain higher contain
The Cr element of amount, therefore these alloys have excellent hot corrosion resistance, but a large amount of additions of Cr content will increase alloy TCP
The precipitation of phase is inclined to, and limits the addition content of other refractory elements (Re+W+Mo+Ta), directly results in the height of these alloys
The level of domestic and international second generation corrosion-resistant superalloy is far not achieved in warm intensity.Currently, with aero-engine and combustion gas wheel
The continuous promotion of machine inlet temperature, in the G/H grade gas turbine introduced to the market, the companies such as U.S. GE have been used containing 3%Re member
The second generation single crystal superalloy (such as Ren é N5 and CMSX-4 alloy) of element is widely used in the system of single crystal turbine blade
It is standby.However, the alloys such as high-strength single crystal alloy Ren é N5 and CMSX-4 of the typical second generation, although having excellent high-temperature mechanics
Performance, but since the corrosion and heat resistant element Cr content in alloy is lower (being lower than 8%), the hot corrosion resistance of alloy is caused to reach
Less than the requirement under heat erosion Service Environment, for it is long when the ground gas turbine be on active service under heat erosion environmental condition with
And the high temperature turbine parts of naval vessel, carrier-borne aircraft, it falls off once damage occurs in protective coating, high temperature turbine parts will face serious
Heat erosion damage even Fracture Failure Risk.Currently, mechanical behavior under high temperature with higher, and have both good corrosion and heat resistant
The type of energy and the single crystal super alloy of chronic tissue stability at home and abroad is more rare.
For above-mentioned background, domestic and international high temperature alloy area research person expects that obtaining one kind has good corrosion and heat resistant
Can, mechanical behavior under high temperature is suitable with the external typical high-strength single crystal alloy of the second generation, and has good chronic tissue stability
Low rhenium corrosion and heat resistant long-life high-strength nickel based single-crystal high-temperature alloy.
Summary of the invention
The purpose of the present invention is to provide a kind of low rhenium corrosion and heat resistant long-life high-strength nickel based single-crystal high-temperature alloy and its
Heat treatment process, which has and the comparable mechanical behavior under high temperature of the typical high-strength single crystal alloy of the second generation, and has good
Hot corrosion resistance and chronic tissue stability.
To achieve the above object, the technical solution adopted in the present invention is as follows:
A kind of low rhenium corrosion and heat resistant long-life high-strength nickel based single-crystal high-temperature alloy, weight percentage, the alloy
Chemical component is as follows:
Cr:8.0~11.0%, Co:7.0~11.0%, Mo:0.1~0.5%, W:3.0~6.0%, Ta:4.0~
7.0%, Al:3.8~5.2%, Ti:0~3.0%, Re:1.0~3.0%, C:0~0.2%, remaining is Ni；Wherein: 6.0%
≤ Al+Ti≤8.0%, Al/Ti > 1.
The preferred chemical component of nickel-base high-temperature single crystal alloy of the present invention is following (wt.%):
Cr:9.0~10.0%, Co:8.0~10.0%, Mo:0.1~0.5%, W:3.5~5.0%, Ta:5.0~
6.5%, Al:4.0~5.0%, Ti:0.5~3.0%, Re:1.5~3.0%, C:0~0.1%, remaining is Ni；Wherein:
6.5%≤Al+Ti≤7.5%, Al/Ti > 1.
In nickel-base high-temperature single crystal alloy provided by the invention, the ingredient and mass percentage of impurity meet following requirements: O
≤ 0.003%, N≤0.0015%, S≤0.004%, P≤0.018%, Si≤0.2%, Pb≤0.0005%, Bi≤
0.00005%.
The Design of Chemical Composition of alloy (alloy designations are named as DD421) of the present invention is based primarily upon following reason:
Re is very effective solution strengthening element in high temperature alloy, and can reduce the body diffusion coefficient of other elements, is mentioned
The roughening activation energy of high γ ' phase, delays the growth rate of γ ' phase.Re also segregation forms elementide in γ matrix, hinders
Dislocation motion significantly improves the mechanical behavior under high temperature of alloy.More importantly for alloy of the present invention, the addition of Re element
Remarkable effect has been played to the raising of the hot corrosion resistance of alloy, and can overcome the disadvantages that the appropriate reduction confrontation of Cr element in this alloy
It is influenced brought by hot corrosion resistance.And Re element generates very the antioxygenic property of alloy, especially structure stability
Detrimental effect.In addition, abundance of the Re in the earth's crust is very low, it is lower than 0.001g/t, the reserves in China are more rare, therefore
On the basis of acquisition higher mechanical property and good hot corrosion resistance, it should which the use of Re element contains in alloy less as far as possible
Amount.Therefore, the content of Re is controlled 1.0~3.0% in this alloy.
Cr is the main element for improving nickel base superalloy hot corrosion resistance, Cr in traditional corrosion-resistant superalloy
Content is generally higher than 12% (mass fraction, similarly hereinafter), and to guarantee alloy in heat erosion environment, it is rotten to be capable of forming continuous heat resistanceheat resistant
Lose Cr2O3Protective film, but a large amount of additions of Cr will increase the precipitation tendency of TCP phase in alloy, and limiting Mo, W, Re etc., other are strong
Change the addition of element, this is also the main reason for current corrosion and heat resistant single crystal alloy mechanical behavior under high temperature is generally relatively low.The present invention
A possibility that alloy improves alloy hot corrosion resistance by addition Re element, and realization suitably reduces Cr content in alloy (8~
11%), both guaranteed the hot corrosion resistance of alloy, also for increase alloy in intensified element (Mo, W, Re, Ta) and γ ' formation
Element (Al, Ti, Ta) content provides possibility, improves alloy solid solution and strengthens and precipitation strength level.
Co can reduce the stacking fault energy of alloy substrate, and to the structure stability of alloy, there is also certain beneficial effect, Co
Added be conducive to heat treatment when alloying element homogenization, alloy heat treatment window, but excessively high Co content meeting can be expanded
Low-alloyed solid solubility temperature is dropped, and drops low-alloyed breaking strength and antioxygenic property.Therefore the high temperature power in order to guarantee alloy
Performance is learned, Co content is controlled 7~11%.
Mo, W are most important solution strengthening elements in high temperature alloy, especially Mo other than having solution strengthening effect,
It also can increase γ/γ ' mismatch, improve alloy high-temp mechanical property.However, being excessively added for Mo, W element will increase dramatically
The precipitation of TCP phase is inclined to, and the addition content of especially Mo element is more sensitive for the precipitation of TCP phase, in alloy development process
Middle discovery, when the addition content of Mo element is more than 1%, microstructure stability cannot obtain effective guarantee, when relatively short
Between heat exposure test after the TCP such as a large amount of μ and σ tissue is precipitated in alloy.Especially in heat erosion environment, Mo is easy to draw
Acid frit reaction is played, very detrimental effect is generated to the hot corrosion resistance of alloy.On the other hand, Mo, W in alloy are reduced
Content low-alloyed density can also drop, control alloy density will be extremely important for large size single crystal alloy vane material.Cause
This controls the content of Mo, W respectively in 0.5% and 6% or less.
Al, Ti are most important γ ' formation elements in nickel-base high-temperature single crystal alloy, generate important shadow to alloy elevated temperature strength
It rings.Al element can significantly improve the antioxygenic property of alloy, and Ti element may react to form stable solid-state vulcanization with S
Object, delays the formation of metal-metal sulphide liquid eutectic, to delay heat erosion reaction process, the heat resistanceheat resistant for improving alloy is rotten
Corrosion energy, but Ti element is unfavorable to the antioxygenic property of alloy, and casting of the Ti as extremely strong normal segregation element, to alloy
Performance is brought a negative impact, and the cancellation band of a large amount of eutectics carrys out great difficulty when for alloy solid solution heat treatment.In addition, in alloy
Al, Ti's is excessively added the structure stability that can significantly reduce alloy.Therefore, it is necessary to which the Al+Ti rationally controlled in alloy always contains
Amount and Ti/Al ratio.In general, the volume fraction of γ ' is higher in aero-engine single crystal turbine blade, γ '/γ mismatch also compared with
Greatly, thus alloy it is relatively short when mechanical behavior under high temperature it is higher.Compared to aero engine turbine blades, industry gas turbine
The military service period of turbo blade is longer, and total service life reaches 50000 hours, alloy it is long when mechanical behavior under high temperature for blade
Safety be on active service and service life it is more important.In general, second generation aero-engine single crystal blade material (such as Ren é N5,
CMSX-4 etc.) γ ' volume fraction (65~70%) with higher, and there is very high γ '/γ mismatch, lead to alloy
Microscopic structure and performance degradation rate are very fast, though lead to alloy short time high temperature mechanical property with higher, mechanical property when long
It can be even horizontal not as good as generation corrosion and heat resistant single crystal alloy.Therefore, develop it is a kind of have medium γ ' volume fraction (50~
60%), lower γ '/γ mismatch corrosion and heat resistant single crystal alloy for improve combustion engine blade it is long when mechanical behavior under high temperature and
Structure stability will have potentiality very much.Therefore, to guarantee that alloy has both good high-temperature oxidation resistance and corrosion and heat resistant
Can, at the same guarantee alloy it is long when tissue and stability, Al/Ti > 1 in this alloy, Al content control 3.8~5.2%,
Ti content controls the overall control in 0~3.0%, Al+Ti, two kinds of elements 6.0~8.0%.
Ta, which mainly passes through, increases γ ' phase amount, improves γ ' phase intensity and thermal stability to improve the elevated temperature strength of alloy,
Has the function of solution strengthening simultaneously.Ta is other than having the heat resistance for improving alloy, also for the corrosion and heat resistant for improving alloy
Performance and antioxygenic property generate positive effect.Other than above-mentioned effect, since Ta is in interdendritic segregation, it can also pass through tune
The density of mushy zone interdendritic liquid in whole directional solidification, reduce casting in freckle the defects of formability.In addition, Ta is not
The formation element of TCP phase, it is little compared to solution strengthening elements, the influences to microstructure stability such as Mo, W, Re.But it is excessively high to contain
The Ta of amount will lead to the eutectic too high levels in alloy, so that the heat treatment of alloy becomes very difficult.In conjunction with factors above, originally
Ta content in invention alloy is controlled 4.0~7.0%.
The intensity of inevitable low angle boundary in single crystal alloy can be strengthened by adding suitable C, improve the casting of alloy
Low-alloyed recrystallization tendency drops in performance, but excess C can reduce alloy initial melting temperature, reduce alloy heat treatment window, and right
The mechanical property and structure stability of alloy have an adverse effect.Therefore, the C content in alloy should control C:0~
0.2%.
Nickel-base high-temperature single crystal alloy of the present invention is using elements such as pure Ni, Cr, Co, W, Mo, Al, Ti, Ta, Re, C true
Melting in empty induction furnace, and the satisfactory master alloy of chemical component is poured into, then pass through apparatus for directional solidification (high rapid hardening again
Gu method or liquid metal cooling method) remelting, using spiral crystal selector or seed-grain method directional solidification at monocrystalline coupon, and suitable
Heat treating regime under be heat-treated.Heat treating regime carries out in accordance with the following steps:
(1) solution heat treatment: 1~4 hour is kept the temperature at 1240~1260 DEG C；Then raise temperature to 1270~1290 DEG C of heat preservations 2
~8 hours, then it is air-cooled to room temperature；Wherein solution heat treatment successively using being warming up to air-cooled effect after certain temperature twice
Be: low temperature is dissolved first, by low melting point phased soln, improves the initial melting temperature of alloy, is next used higher temperature solid solution, will be closed
The precipitated phases such as γ/γ ' eutectic are farthest dissolved in gold；
(2) high-temperature aging is heat-treated: being kept the temperature 2~6 hours at 1080~1160 DEG C, is then air-cooled to room temperature；
(3) low temperature aging is heat-treated: being kept the temperature 20~28 hours at 850~930 DEG C, is then air-cooled to room temperature.
Wherein, it is using the effect of high-temperature aging heat treatment after aging strengthening model successively uses low temperature aging to be heat-treated: logical
Different aging time and temperature are crossed, the size and shape of γ ' phase in alloy is adjusted, improves alloy mechanical property.
For prior art background, the present invention has developed a kind of low rhenium corrosion and heat resistant long-life high intensity nickel-based monocrystal high temperature
Alloy, hot corrosion resistance is suitable with M38 alloy, 1050 DEG C it is below at use temperature, mechanical behavior under high temperature is much higher than
First generation single crystal super alloy, reach or close to the high-strength single crystal alloy Ren é N5 of the second generation level.
Advantages of the present invention and beneficial effect are described as follows:
(1) compared with other existing nickel-base high-temperature single crystal alloys, alloy of the present invention has excellent hot corrosion resistance,
900 DEG C and 950 DEG C of hot corrosion resistances it is suitable with M38 alloy.
(2) enduring quality of alloy of the present invention is much higher than first generation corrosion and heat resistant single crystal alloy, high close to typical case's second generation
Strong single crystal super alloy is horizontal, and the average creep rupture life under the conditions of 982 DEG C/273MPa is close to 70h, 1038 DEG C/172MPa condition
Under average creep rupture life be more than 100h, the average life span under the conditions of 982 DEG C/172MPa is more than 1000h, therefore, the present invention close
Gold is high-strength corrosion and heat resistant single crystal super alloy.
(3) alloy of the present invention Long-term Aging tissue stabilization under the conditions of 900 DEG C and 1000 DEG C.
Detailed description of the invention
Fig. 1 is the as-cast microstructure of 1 alloy of the embodiment of the present invention.
Fig. 2 is 2 alloy of embodiment by+870 DEG C of 1250 DEG C/2h+1260 DEG C/6h (AC)+1130 DEG C/4h (AC)/for 24 hours
(AC) the typical heat-treated microstructure after being heat-treated
Fig. 3 is 2 alloy of embodiment by+870 DEG C of 1250 DEG C/2h+1270 DEG C/6h (AC)+1130 DEG C/4h (AC)/for 24 hours
(AC) the typical heat-treated microstructure after being heat-treated
Fig. 4 is 2 alloy of embodiment by+870 DEG C of 1250 DEG C/2h+1280 DEG C/6h (AC)+1130 DEG C/4h (AC)/for 24 hours
(AC) the typical heat-treated microstructure after being heat-treated
Fig. 5 is the γ ' tissue in alloy after 2 alloy standard heat treatment of the embodiment of the present invention.
Fig. 6 is 3-6 of embodiment of the present invention alloy and first generation single crystal super alloy PWA1483 and the second generation in the prior art
The Larson-Miller curve of single crystal super alloy Ren é N5 and CMSX-4 alloy compares figure.
Fig. 7 is the test result of 6 900 DEG C of hot corrosion resistances of alloy of the embodiment of the present invention.
Fig. 8 is the test result of 6 950 DEG C of hot corrosion resistances of alloy of the embodiment of the present invention.
Fig. 9 is antioxygenic property of 7 alloy of embodiment of the present invention at a temperature of 900 DEG C, 1000 DEG C and 1100 DEG C.
Figure 10 is the microscopic structure that 3 alloy of embodiment of the present invention dendrite after 900 DEG C of prolonged heat exposure 6500h does region
(universal microscopic structure).
Figure 11 is the microscopic structure that 3 alloy of embodiment of the present invention dendrite after 900 DEG C of prolonged heat exposure 6500h does region
(more serious region is precipitated in a small amount of TCP phase).
Figure 12 is the microscopic structure of 3 alloy of embodiment of the present invention interdendritic regions after 900 DEG C of prolonged heat exposure 6500h.
Figure 13 is the microscopic structure that 3 alloy of embodiment of the present invention dendrite after 1000 DEG C of prolonged heat exposure 5000h does region.
Figure 14 is the microscopic structure of 3 alloy of embodiment of the present invention interdendritic regions after 1000 DEG C of prolonged heat exposure 5000h.
Specific embodiment
The present invention is described in detail below in conjunction with drawings and examples.
For the deficiencies in the prior art, it is Ni-based that the present invention has developed a kind of low rhenium corrosion and heat resistant long-life high intensity
Single crystal super alloy, the alloy composition are following (wt.%):
Cr:8.0~11.0%, Co:7.0~11.0%, Mo:0.1~0.5%, W:3.0~6.0%, Ta:4.0~
7.0%, Al:3.8~5.2%, Ti:0~3.0%, Re:1.0~3.0%, C:0~0.2%, remaining is Ni.
The specific preparation method requirement of the alloy: vacuum induction melting is used, and it is satisfactory to pour into chemical component
Then master alloy recycles high speed freezing method directional solidification processes or liquid metal cooling directional solidification process (LMC), using spiral shell
Rotation crystal selector is legal to being frozen into monocrystalline coupon.
The hot corrosion resistance of alloy of the present invention is suitable with M38 alloy, 1050 DEG C it is below at use temperature, high temperature power
Learn performance be much higher than first generation single crystal super alloy, reach or close to the high-strength single crystal alloy Ren é N5 of the second generation level.
In the following, being described in further details in conjunction with accompanying drawings and embodiments 1-7 to the present invention.
1-7 alloying component of the embodiment of the present invention is specifically shown in Table 1, for the ease of comparison, also lists typical first in table 1
For the chemical component of corrosion and heat resistant single crystal super alloy PWA1483 and typical the second generation single crystal superalloy Ren é N5.
The typical as-cast microstructure of 1 alloy of embodiment is as shown in Figure 1.
Embodiment alloy carry out after following heat treatment the hot corrosion resistance, antioxygenic property, mechanical property of alloy with
And chronic tissue stability study, wherein the standard heat treatment system of embodiment 1-7 alloy is as follows: 1250 ± 10 DEG C/2h+
1270 ± 10 DEG C/6h+870 ± 10 DEG C of (AC)+1130 ± 10 DEG C/4h (AC)/for 24 hours (AC), within the scope of the heat treating regime, together
The performance that one alloying component is tested is almost the same.
Wherein, 2 alloy of embodiment by+870 DEG C of 1250 DEG C/2h+1270 ± 10 DEG C/6h (AC)+1130 DEG C/4h (AC)/
Typical heat-treated microstructure for 24 hours after (AC) standard heat treatment is as in Figure 2-4, γ ' of the alloy after standard heat treatment
Tissue is as shown in Figure 5.
According to alloy composition range, it is prepared for the monocrystalline coupon of alloy of the present invention, coupon is through Overheating Treatment and machinery
Persistence testing experiment is carried out after processing, experimental result is shown in Table 2.3-6 of embodiment of the present invention alloy and the Ni-based list of the typical first generation
The Larson- of brilliant high temperature alloy PWA1483 and typical second generation nickel-base high-temperature single crystal alloy Ren é N5, CMSX-4 alloy
Miller curve comparison is shown in Fig. 6.The short time high temperature enduring quality of alloy of the present invention is much higher than PWA1483 alloy, close to Ren é N5
Level of alloy, wherein alloy it is long when high temperature endurance performance (980 DEG C/172MPa, 1000h or more) reach the second generation monocrystalline conjunction
Golden CMSX-4 is horizontal, or even slightly better than typical second generation single crystal alloy.
Hot corrosion resistance and hot-corrosion-resistant alloy of 6 alloy of the embodiment of the present invention at a temperature of 900 DEG C and 950 DEG C
Fig. 7 and Fig. 8 are shown in the hot corrosion resistance comparison of PWA1483 and M38 alloy, wherein 900 DEG C of corrosion and heat resistants of alloy of the present invention
Can be suitable with PWA1483 and M38 alloy, 950 DEG C of hot corrosion resistances are better than M38 alloy.
Oxidation behavior of 7 alloy of embodiment of the present invention at a temperature of 900 DEG C, 1000 DEG C and 1100 DEG C is shown in Fig. 9.
3 alloy of embodiment carries out prolonged heat exposure in 900 DEG C and 1000 DEG C of Long-term Aging furnaces respectively after Overheating Treatment
Experiment.Only doing individual local locations in dendrite in 900 DEG C of alloys after prolonged heat exposure 6500 hours, there are a small amount of TCP phases to be precipitated
(see Figure 10 and 11), and interdendritic regions have no that (as shown in figure 12) is precipitated in harmful TCP phase.1000 DEG C of prolonged heat exposures 5000 are small
When after have no that harmful TCP phase is precipitated in alloy, 1000 DEG C of prolonged heat exposure microscopic structures are shown in Figure 13 (dendrite does region) and 14 (branches
Intergranular region).
1 embodiment of the present invention of table and the chemical component of PWA1483, Ren é N5 alloy form list (wt.%)
| Alloy | Cr | Co | Mo | W | Al | Ti | Ta | Re | C | Ni | Nv |
| Embodiment 1 | 9.0 | 8.5 | 0.35 | 4.7 | 4.2 | 2.9 | 6.0 | 2.40 | 0.07 | Surplus | 2.07 |
| Embodiment 2 | 10.0 | 8.3 | 0.4 | 4.4 | 4.0 | 2.8 | 5.5 | 2.44 | 0.05 | Surplus | 2.07 |
| Embodiment 3 | 9.70 | 8.67 | 0.49 | 4.45 | 4.2 | 2.9 | 5.65 | 2.56 | 0.05 | Surplus | 2.15 |
| Embodiment 4 | 9.31 | 8.94 | 0.45 | 4.5 | 4.12 | 2.96 | 5.73 | 2.51 | 0.04 | Surplus | 2.11 |
| Embodiment 5 | 9.70 | 8.7 | 0.44 | 4.47 | 4.56 | 2.19 | 5.78 | 2.49 | 0.06 | Surplus | 2.10 |
| Embodiment 6 | 9.36 | 8.63 | 0.40 | 4.61 | 4.32 | 2.60 | 5.58 | 2.48 | 0.05 | Surplus | 2.08 |
| Embodiment 7 | 9.16 | 8.56 | 0.1 | 4.9 | 4.18 | 2.88 | 5.62 | 2.51 | 0.06 | Surplus | 2.06 |
| PWA1483 | 12.0 | 9.0 | 1.9 | 4.0 | 3.4 | 4.0 | 5.0 | - | 0.06 | Surplus | 2.27 |
| René N5 | 7.0 | 7.5 | 1.5 | 5.0 | 6.2 | - | 6.5 | 3.0 | 0.05 | Surplus+0.15Hf | 2.12 |
The creep rupture life of 2 embodiment 3-6 alloy of table
Claims (6)
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| CN201710463755.9A Pending CN109136654A (en) | 2017-06-19 | 2017-06-19 | A kind of low rhenium corrosion and heat resistant long-life high intensity second generation nickel-base high-temperature single crystal alloy and its heat treatment process |
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| CN111398333A (en) * | 2020-04-13 | 2020-07-10 | 中国科学院金属研究所 | Differential thermal analysis method for measuring primary melting temperature of single crystal superalloy |
| CN111926217A (en) * | 2020-08-13 | 2020-11-13 | 煜工(南通)环保设备制造有限公司 | High-temperature-resistant, corrosion-resistant and high-strength 1200-type alloy material and preparation method and application thereof |
| CN112593121A (en) * | 2020-12-08 | 2021-04-02 | 中国科学院金属研究所 | High-strength high-temperature-oxidation-resistant rhenium-free second-generation nickel-based single crystal high-temperature alloy and heat treatment process thereof |
| CN113075053A (en) * | 2021-03-31 | 2021-07-06 | 华能国际电力股份有限公司 | Method and system for rapidly predicting long-term thermal exposure tensile strength of Ni3Al strengthened alloy |
| CN114310033A (en) * | 2021-12-30 | 2022-04-12 | 东方电气集团东方汽轮机有限公司 | Activating diffusion agent and application thereof |
| CN116083752A (en) * | 2022-11-01 | 2023-05-09 | 中国科学院金属研究所 | Low-cost and high-strength second-generation nickel-based single crystal superalloy DD515 and its preparation process |
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| CN103436739A (en) * | 2013-06-20 | 2013-12-11 | 中国科学院金属研究所 | Rhenium-containing high-strength heat-corrosion-resistant nickel-base single-crystal high-temperature alloy |
| 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 |
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| CN111398333A (en) * | 2020-04-13 | 2020-07-10 | 中国科学院金属研究所 | Differential thermal analysis method for measuring primary melting temperature of single crystal superalloy |
| CN111398333B (en) * | 2020-04-13 | 2021-10-29 | 中国科学院金属研究所 | A Differential Thermal Analysis Method for Measuring the Initial Melting Temperature of Single Crystal Superalloys |
| CN111926217A (en) * | 2020-08-13 | 2020-11-13 | 煜工(南通)环保设备制造有限公司 | High-temperature-resistant, corrosion-resistant and high-strength 1200-type alloy material and preparation method and application thereof |
| CN112593121A (en) * | 2020-12-08 | 2021-04-02 | 中国科学院金属研究所 | High-strength high-temperature-oxidation-resistant rhenium-free second-generation nickel-based single crystal high-temperature alloy and heat treatment process thereof |
| CN113075053A (en) * | 2021-03-31 | 2021-07-06 | 华能国际电力股份有限公司 | Method and system for rapidly predicting long-term thermal exposure tensile strength of Ni3Al strengthened alloy |
| CN113075053B (en) * | 2021-03-31 | 2023-02-17 | 华能国际电力股份有限公司 | Method and system for rapidly predicting long-term thermal exposure tensile strength of Ni3Al reinforced alloy |
| CN114310033A (en) * | 2021-12-30 | 2022-04-12 | 东方电气集团东方汽轮机有限公司 | Activating diffusion agent and application thereof |
| CN116083752A (en) * | 2022-11-01 | 2023-05-09 | 中国科学院金属研究所 | Low-cost and high-strength second-generation nickel-based single crystal superalloy DD515 and its preparation process |
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