CN116657001B - Nickel-based superalloy and preparation method thereof - Google Patents
Nickel-based superalloy and preparation method thereof Download PDFInfo
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 140
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 69
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 62
- 238000002360 preparation method Methods 0.000 title abstract description 17
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 26
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 17
- 238000005242 forging Methods 0.000 claims description 63
- 238000010438 heat treatment Methods 0.000 claims description 38
- 238000001816 cooling Methods 0.000 claims description 27
- 238000000034 method Methods 0.000 claims description 25
- 238000002844 melting Methods 0.000 claims description 24
- 230000008018 melting Effects 0.000 claims description 24
- 230000008569 process Effects 0.000 claims description 21
- 229910000831 Steel Inorganic materials 0.000 claims description 20
- 239000010959 steel Substances 0.000 claims description 20
- 239000013078 crystal Substances 0.000 claims description 13
- 230000006698 induction Effects 0.000 claims description 12
- 238000000137 annealing Methods 0.000 claims description 11
- 238000009826 distribution Methods 0.000 claims description 8
- 238000010313 vacuum arc remelting Methods 0.000 claims description 8
- 230000000087 stabilizing effect Effects 0.000 claims description 7
- 150000001247 metal acetylides Chemical class 0.000 claims description 6
- 229910052750 molybdenum Inorganic materials 0.000 claims description 6
- 229910052760 oxygen Inorganic materials 0.000 claims description 6
- 229910001566 austenite Inorganic materials 0.000 claims description 3
- 239000003054 catalyst Substances 0.000 claims description 3
- 230000001550 time effect Effects 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 abstract description 83
- 239000000956 alloy Substances 0.000 abstract description 83
- 239000010936 titanium Substances 0.000 description 35
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 21
- 238000004321 preservation Methods 0.000 description 17
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 15
- 239000006104 solid solution Substances 0.000 description 14
- 239000010941 cobalt Substances 0.000 description 13
- 229910017052 cobalt Inorganic materials 0.000 description 13
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 13
- 230000000052 comparative effect Effects 0.000 description 13
- 230000002045 lasting effect Effects 0.000 description 12
- 239000000463 material Substances 0.000 description 12
- 238000005728 strengthening Methods 0.000 description 12
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 11
- 238000005204 segregation Methods 0.000 description 10
- 230000009467 reduction Effects 0.000 description 9
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 8
- 229910052757 nitrogen Inorganic materials 0.000 description 8
- 239000002893 slag Substances 0.000 description 8
- 238000003723 Smelting Methods 0.000 description 7
- 238000001556 precipitation Methods 0.000 description 7
- 239000011651 chromium Substances 0.000 description 6
- 239000007789 gas Substances 0.000 description 6
- 238000011068 loading method Methods 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 238000010079 rubber tapping Methods 0.000 description 6
- 239000000243 solution Substances 0.000 description 6
- 229910052799 carbon Inorganic materials 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 239000001307 helium Substances 0.000 description 5
- 229910052734 helium Inorganic materials 0.000 description 5
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 5
- 230000007774 longterm Effects 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000007670 refining Methods 0.000 description 5
- 229910018072 Al 2 O 3 Inorganic materials 0.000 description 4
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 4
- 229910010413 TiO 2 Inorganic materials 0.000 description 4
- 229910052786 argon Inorganic materials 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 4
- 238000005266 casting Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 239000006185 dispersion Substances 0.000 description 4
- 238000003756 stirring Methods 0.000 description 4
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 239000011733 molybdenum Substances 0.000 description 3
- 229910052698 phosphorus Inorganic materials 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- 229910052717 sulfur Inorganic materials 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 229910004261 CaF 2 Inorganic materials 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 2
- 229910000990 Ni alloy Inorganic materials 0.000 description 2
- 230000032683 aging Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 2
- 239000000498 cooling water Substances 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 238000007667 floating Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 230000005923 long-lasting effect Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 238000005498 polishing Methods 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 238000004381 surface treatment Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000005303 weighing Methods 0.000 description 2
- 241001062472 Stokellia anisodon Species 0.000 description 1
- UCKMPCXJQFINFW-UHFFFAOYSA-N Sulphide Chemical compound [S-2] UCKMPCXJQFINFW-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 210000001787 dendrite Anatomy 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000010309 melting process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- CSJDCSCTVDEHRN-UHFFFAOYSA-N methane;molecular oxygen Chemical compound C.O=O CSJDCSCTVDEHRN-UHFFFAOYSA-N 0.000 description 1
- 150000004767 nitrides Chemical group 0.000 description 1
- 235000011837 pasties Nutrition 0.000 description 1
- 230000002085 persistent effect Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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- 230000035945 sensitivity Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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
- C22C19/056—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%
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/023—Alloys based on nickel
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a nickel-based superalloy and a preparation method thereof, belongs to the technical field of superalloy, and solves the problem that the nickel-based superalloy in the prior art is difficult to meet the comprehensive requirements of a rotating member on high-temperature durability and low-cycle fatigue performance. The nickel-based superalloy comprises the following components in percentage by mass: c:0.02% -0.04%, cr:18.5 to 20.0 percent, co:13.0 to 14.0 percent, mo:4.0 to 4.90 percent of Al:1.3 to 1.6 percent of Ti:2.80 to 3.25 percent of Ti/Al:2.25 to 2.38, (Al+Ti): 4.35 to 4.58 percent, O: less than or equal to 20PPm, N: less than or equal to 20PPm, less than or equal to 10PPm for S, less than or equal to 80PPm for P, and nickel: the balance. The nickel-based superalloy of the invention ensures the comprehensive requirements of high-temperature durability and low-cycle fatigue performance of the alloy.
Description
Technical Field
The invention relates to the technical field of high-temperature alloy, in particular to a nickel-based high-temperature alloy and a preparation method thereof.
Background
The nickel-based deformation superalloy has good toughness matching, is suitable for manufacturing high-temperature rotating parts such as turbine discs, blades and the like, and is also used for manufacturing non-rotating high-temperature structural parts (such as casings, annular parts and the like) and fasteners and the like. The existing nickel-based deformation superalloy is generally smelted by adopting a vacuum induction and electroslag remelting or vacuum induction and vacuum consumable duplex process, the content of C is relatively high (between 0.05 and 0.1 percent), and the content of O+N+S is generally controlled to be about 90 ppm. The traditional nickel-based deformation superalloy is difficult to control stably in the thermal deformation process, mixed crystals are easy to cause, so that the performance fluctuation of the alloy component is large, and the comprehensive requirements of a rotating piece on high-temperature durability (such as durability above 730 ℃) and low-cycle fatigue performance (such as 500 ℃/strain control 0-0.7%/0.33 Hz low-cycle fatigue performance) are difficult to be met simultaneously.
Disclosure of Invention
In view of the above, the present invention aims to provide a nickel-based superalloy and a preparation method thereof, which are used for solving the problem that the existing nickel-based superalloy is difficult to simultaneously meet the comprehensive requirements of a rotating member on high-temperature durability and low-cycle fatigue performance.
The aim of the invention is mainly realized by the following technical scheme:
in one aspect, the invention provides a nickel-base superalloy, comprising the following components in percentage by mass: c:0.02% -0.04%, cr:18.5 to 20.0 percent, co:13.0 to 14.0 percent, mo:4.0 to 4.90 percent of Al:1.3 to 1.6 percent of Ti:2.80 to 3.25 percent of Ti/Al:2.25 to 2.38, (Al+Ti): 4.35 to 4.58 percent, O: less than or equal to 20PPm, N: less than or equal to 20PPm, less than or equal to 10PPm for S, less than or equal to 80PPm for P, and nickel: the balance.
Further, the nickel-based superalloy comprises the following components in percentage by mass: 0.026% -0.037%, cr:18.5 to 19.7 percent, co:13.0 to 13.98 percent of Mo:4.10 to 4.70 percent of Al:1.3 to 1.45 percent of Ti:2.95 to 3.25 percent of O: less than or equal to 10PPm, N: less than or equal to 20PPm, S less than or equal to 8PPm, P less than or equal to 40PPm, nickel: the balance.
Further, the nickel-based superalloy comprises the following components in percentage by mass: 2.26 to 2.38.
Further, the nickel-based superalloy comprises the following components in percentage by mass (al+ti): 4.36 to 4.58 percent.
Further, the microstructure of the nickel-based superalloy mainly comprises equiaxed austenite grains, evenly distributed carbides and dispersed gamma' -phase; the grain size reaches above 6.5 grade.
Further, the carbide mainly comprises M 23 C 6 And MC; m is M 23 C 6 Is in a short rod shape and is intermittently distributed at the grain boundary; MC is in a block shape and is intermittently distributed in the crystal.
Further, M 23 C 6 The mass percentage of the catalyst is about 0.5% -0.75%.
The invention also provides a preparation method of the nickel-based superalloy, which comprises the following steps:
step 1: sequentially carrying out vacuum induction melting, electroslag remelting and vacuum arc remelting to obtain a steel ingot;
step 2: homogenizing and annealing the steel ingot;
step 3: preparing a bar blank by adopting quick forging and radial forging;
step 4: forging by adopting a die forging press to prepare a forging piece;
step 5: solution treatment;
step 6: stabilizing and treating with time effect to obtain nickel-base superalloy.
In the step 1, a batch distribution mode is adopted in the distribution process of vacuum induction melting.
Further, in step 2, the homogenizing annealing process includes:
s201, heating to 1150-1165 ℃, and preserving heat for 47-49 h;
s202, continuously heating to 1180-1195 ℃, preserving heat for 65-67 h, and then air-cooling.
Compared with the prior art, the invention has the following beneficial effects:
a) According to the nickel-based superalloy, the content of single elements such as C, cr, co, al, ti in the alloy is accurately controlled, so that the solid solution strengthening effect of the alloy and the grain boundary strength of the alloy are improved; and by cooperatively controlling the values of Ti/Al and (Al+Ti), the optimal matching of the content and the size of the gamma' -phase in the alloy is ensured, the content of inclusions in the alloy is reduced by precisely controlling the content of O, N, S, P, the purity, the plasticity and the fatigue performance of the alloy are improved, the uniformity of crystal grains and the precipitation and the distribution of a grain boundary phase are ensured, and the comprehensive requirements of high-temperature durability (such as the durability above 730 ℃) and low-cycle fatigue performance (such as the low-cycle fatigue performance of 500 ℃/strain control 0-0.7%/0.33 Hz) of the alloy are simultaneously ensured.
b) The preparation method of the nickel-based superalloy of the invention prepares the alloy meeting 700 ℃ service aeroengine through controlling the content of key components in the alloy and triple smelting and cogging and die forging processes, and has uniform and fine crystal grains, low crack expansion rate and excellent long-term service comprehensive performance; and the alloy member has small fluctuation in performance.
c) The nickel-based superalloy can meet the requirements of materials for rotating parts of 700 ℃ serving aeroengines, and has the following properties: room temperature tensile properties: tensile strength sigma b More than or equal to 1300 MPa (e.g. 1330-1420 MPa); yield strength sigma 0.2 More than or equal to 1000 MPa (for example, 1010-1050 MPa); elongation after break delta 5 More than or equal to 20.0 percent (for example, 21 percent to 24 percent); the area reduction ratio psi is more than or equal to 24.0 percent (for example, 25-36 percent); 535 ℃ performance: tensile strength sigma b More than or equal to 1200 MPa (e.g. 1210-1320 MPa); yield strength sigma 0.2 More than or equal to 875 MPa (for example, 885-950 MPa); elongation after break delta 5 More than or equal to 19 percent (for example, 19 percent to 22 percent); the area reduction ratio psi is more than or equal to 23 percent (for example, 24-29 percent); 730 ℃/550MPa durability performance: the lasting time tau is more than or equal to 35 h (for example, 41-47 h); 815 ℃/250MPa durability: the lasting time tau is equal to or longer than 115 h (for example, 118-170 h); elongation after break delta 5 More than or equal to 17 percent (for example, 17 percent to 22 percent); 815 ℃/295MPa durability: the lasting time tau is more than or equal to 52 h (for example, 53-70 h); elongation after break delta 5 More than or equal to 12 percent (for example, 13 percent to 18 percent); low cycle fatigue performance: 500 ℃/strain control 0-0.7%/0.33 Hz, > 3 x 10 4 Circumference (e.g., 33884-47323).
d) The nickel-based superalloy of the invention has high forgeability, and can be used for preparing disc ring forgings and fasteners; the processing and forming modes are multiple, and the cast-forging welding can be realized; the cutting processability is good.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims thereof as well as the appended drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, like reference numerals being used to designate like parts throughout the drawings;
FIG. 1 is a grain diagram of example 1 of the present invention;
FIG. 2 is a microstructure chart of example 1 of the present invention;
fig. 3 is a grain diagram of comparative example 4.
Detailed Description
Preferred embodiments of the present invention are described in detail below with reference to the attached drawing figures, which form a part of the present invention and are used in conjunction with embodiments of the present invention to illustrate the principles of the present invention.
The inventor finds that the component control of the existing nickel-based superalloy is too wide, the preparation process window is also wide, in the prior art, the content of C is generally high, the content and the distribution dispersity of a grain boundary phase are large, stable control is difficult in the thermal deformation process, mixed crystals are easy to cause, the performance fluctuation of the alloy component is large, and the comprehensive requirements of a rotating part on high-temperature durability and low-cycle fatigue performance are difficult to meet. Therefore, the inventor has conducted intensive studies to more precisely control the alloy composition and process, and provided a superalloy capable of long-term service at 700 ℃. The high-temperature alloy meets the comprehensive performance of the rotating member in long-term service at 700 ℃.
The invention provides a nickel-based superalloy, which comprises the following components in percentage by mass: c:0.02% -0.04%, cr:18.5 to 20.0 percent, co:13.0 to 14.0 percent, mo:4.0 to 4.90 percent of Al:1.3 to 1.6 percent of Ti:2.80 to 3.25 percent of Ti/Al:2.25 to 2.38, (Al+Ti): 4.35 to 4.58 percent, O: less than or equal to 20PPm, N: less than or equal to 20PPm, less than or equal to 10PPm for S, less than or equal to 80PPm for P, and nickel: the balance.
Specifically, O+N+S is less than or equal to 50PPm.
The following is a specific description of the action and the selection of the amounts of the components contained in the invention:
c: c in nickel-base alloys is mainly formed by MC carbide formation during solidification and M precipitation during heat treatment 23 C 6 、M 6 C and the like affect the mechanical properties of the material. Granular discontinuous carbide M precipitated at grain boundary 23 C 6 Grain boundary sliding and crack propagation can be prevented, the lasting life is prolonged, and the lasting plasticity and toughness are improved; higher C content tends to increase MC, M 23 C 6 And increase grain boundary M 23 C 6 The inventors have intensively studied to find that: m at C content of 0.01%, 0.03%, 0.04%, 0.05%, 0.1%, respectively 23 C 6 The content of (C) is 0.19%, 0.58%, 0.78%, 0.97%, 1.95%, respectively. When the C content is less than 0.04%, carbide is discontinuously distributed at the grain boundary; when the C content is more than 0.04%, carbide starts to be distributed continuously at the grain boundary; when the C content is 0.06%, not only small-sized continuous carbides but also large-sized discrete carbides exist in the grain boundary, the average size thereof is 3 μm, and the long-lasting life of the alloy is also reduced. Therefore, the content of C is controlled to be 0.02% -0.04%.
Cr: cr is an indispensable alloying element in nickel-based superalloy, and has the following main effects: (1) solid solution strengthening: cr in the gamma matrix of the high-temperature alloy causes lattice distortion, generates elastic stress field reinforcement, and improves the gamma solid solution strength; (2) precipitation strengthening: cr dissolved in gamma solid solution can also form a series of carbides with C, mainly M 23 C 6 The carbide is mainly distributed at the grain boundary, and granular discontinuous carbide uniformly distributed at the grain boundary can effectively prevent the grain boundary from sliding and migrating and improve the lasting strength; (3) antioxidant: cr in gamma matrixAn important function is the formation of Cr 2 O 3 The oxide film has good oxidation resistance, and the higher the Cr content is, the better the oxidation resistance is. Considering the cost problem of the alloy, the Cr content is controlled to be 18.5-20.0%.
Co: co is one of main solid solution strengthening elements of the nickel base alloy, and the addition of Co to the gamma base can reduce the stacking fault energy of the base, reduce the stacking fault energy, increase the probability of occurrence of the stacking fault, make the intersection and sliding of dislocation more difficult, so that the deformation requires larger external force and is shown as the improvement of strength; and the stacking fault energy is reduced, the creep rate is reduced, and the creep resistance is increased. In addition, the Co element can also reduce the solubility of the gamma prime forming elements Ti and Al in the matrix, so that the quantity of gamma prime precipitated phases in the alloy is increased, and the service temperature of the alloy is increased. However, co belongs to a scarce resource in China, and the cost factor of the alloy is considered, so that the content of Co element is controlled to be 13.0-14.0%.
Mo: mo enters the nickel-based alloy matrix and mainly plays a role in solid solution strengthening. Particularly, when the cost is reduced and the Co content is reduced to weaken the solid solution strengthening effect, the solid solution strengthening of Mo element is also one of the characteristics of the invention. The invention controls the content of Mo element to be 4.0 percent to 4.9 percent.
Al: al is a main element forming a gamma' phase, and about 20% of Al added into the alloy enters a gamma solid solution to play a role in solid solution strengthening; 80% of Al forms Ni with Ni 3 Al plays a role in precipitation strengthening. In order to ensure that the alloy has a gamma' phase which is necessary for maintaining the high-temperature strength at 700 ℃, the invention limits the Al content of the alloy to 1.3-1.6%.
Ti: about 10% of the Ti added into the nickel-based alloy enters a gamma solid solution to play a certain solid solution strengthening role, and about 90% enters a gamma' phase. Under the condition of a certain Al content, as the quantity of the gamma 'phase increases and the high-temperature strength of the alloy increases along with the increase of the Ti content, in order to ensure that the gamma' phase which is necessary for maintaining the high-temperature strength of 700 ℃ exists in the alloy, the invention limits the Ti content to 2.80-3.25 percent and simultaneously controls the Ti/Al:2.25 to 2.38, (Al+Ti): 4.35 to 4.58 percent.
O: the reduction of the O, N element content can reduce the inclusion quantity in the material, and is beneficial to improving the plasticity and toughness of the alloy. During melting of the alloy, N readily forms Ti (C, N) with Ti, and the increase in Ti (C, N) increases the likelihood of fatigue source formation while also reducing the amount of Ti element required for the gamma prime phase of the strengthening phase. Therefore, in the present invention, it is necessary to control O: less than or equal to 20PPm, N: and the volume of the mixture is less than or equal to 20PPm.
S: higher S content has an effect on the plasticity and long-term properties of the alloy. The higher the S content at the end of alloy smelting solidification, the easier the sulfide is to precipitate. The S element has obvious influence on the nickel-based alloy at the temperature of more than 800 ℃, the S element is obvious in the steel ingot smelting and cogging process, and the inventor finds that in the research: 100 The S-content in ppm fails to smelt, while the S-content in 56 ppm group steel ingot has serious cracking in the cogging process, and after the S-content exceeds 10ppm, the durability and plasticity at 730 ℃ are reduced to different degrees. Therefore, in the present invention, it is necessary to control S: less than or equal to 10PPm.
P: as the P content increases, the long-lasting life of the nickel-base alloy decreases drastically, and the inventors found in the study that: when the P content exceeds 80ppm, the lasting life at 730 ℃ is less than 25 h, and when the P content exceeds 100 ppm, the lasting life is only about 2 h; and after a P content of over 80ppm, the nickel-based alloy has a significant notch sensitivity persisting at 730 ℃. Therefore, in the present invention, control of P is required: less than or equal to 80PPm.
In order to further improve the comprehensive performance of the nickel-base superalloy, the nickel-base superalloy may comprise the following components in percentage by mass: c:0.026% -0.037%, cr:18.5 to 19.7 percent, co:13.0 to 13.98 percent of Mo:4.10 to 4.70 percent of Al:1.3 to 1.45 percent of Ti:2.95 to 3.25 percent of Ti/Al:2.26 to 2.38, (Al+Ti): 4.36 to 4.58 percent, O: less than or equal to 10PPm, N: less than or equal to 20PPm, S less than or equal to 8PPm, P less than or equal to 40PPm, nickel: the balance.
Specifically, O+N+S is less than or equal to 40PPm.
Specifically, the microstructure of the nickel-based superalloy mainly comprises equiaxed austenite grains, evenly distributed carbides and dispersed gamma' -phase; wherein the carbide mainly comprises M 23 C 6 And MC; m is M 23 C 6 Is in a short rod shape, is intermittently distributed on a grain boundary, and has the content of about 0.5-0.75 percent (mass fraction); MC is in block shape, brokenContinuously distributed in the crystal, and the content is less, about 0.1-0.2% (mass fraction); the gamma 'phase is spherical and dispersed in the crystal grain, the particle size of the gamma' phase is about 60-200 nm, the content is 24-26%, the content of the gamma 'phase with the particle size of about 60-100 nm is about 12-16%, and the content of the gamma' phase with the size of more than 100nm is about 8-14%.
Specifically, the grain size of the nickel-base superalloy reaches more than 6.5 levels, for example, 7-8 levels.
The invention also provides a preparation method of the nickel-based superalloy, which comprises the following steps:
step 1: sequentially carrying out vacuum induction melting, electroslag remelting and vacuum arc remelting to obtain a steel ingot;
step 2: homogenizing and annealing the steel ingot;
step 3: preparing a bar blank by adopting quick forging and radial forging;
step 4: forging by adopting a die forging press to prepare a forging piece;
step 5: solution treatment;
step 6: stabilizing and treating with time effect to obtain nickel-base superalloy.
Specifically, the specific steps of the step 1 include:
step 1.1: weighing raw materials according to the proportion of alloy components;
step 1.2: vacuum induction melting, comprising:
s1.2.1 cloth: loading nickel plates, carbon powder, cobalt blocks and molybdenum strips into a furnace in batches; after the furnace burden is completely charged into the furnace, vacuumizing until the vacuum degree is less than or equal to 0.1Pa, and preparing for electrifying;
s1.2.2 melting and refining: maintaining low-power baking at 50-100 kw, evacuating and exhausting, adopting gradient (for example, 200kw, 400kw and 600 kw) to raise power to 1000-1500 kw, adding the residual nickel plate and the residual carbon powder and chromium blocks after the furnace material is completely melted until the furnace material is completely melted, and carrying out electromagnetic stirring on the alloy liquid after the furnace material is melted, so as to promote the rapid reduction of O element and N element; the temperature in the melting stage is controlled to be 1500-1560 ℃, and the temperature in the refining stage is controlled to be 1500-1560 ℃;
and S1.2.3, tapping and casting: reducing power, preserving heat, adding aluminum blocks and titanium sponge in batches, after furnace materials are melted, charging Ar gas into the furnace to 20000 Pa-30000 Pa, adding nickel alloy, applying electromagnetic stirring to promote melting and uniform components, adjusting the power to pouring temperature, tapping, controlling the tapping temperature to 1450-1510 ℃, cooling the furnace for a period of time, and carrying out vacuum induction ingot casting;
s1.2.4 surface treatment: cutting off a riser after the ingot is cooled, and carrying out surface polishing treatment so as to carry out electroslag remelting treatment in a later period;
step 1.3: electroslag remelting, comprising:
s1.3.1 CaF is selected 2 45%~65%，Al 2 O 3 15%~25%，CaO 15%~25%，MgO 2%~8%，TiO 2 0-5% of the slag is used as premelting slag;
after a S1.3.2 electrode is welded and polished into a furnace, argon is introduced, the flow rate of the argon is not lower than 30L/min, slag melting, arcing, remelting and feeding are carried out, after the ingot furnace is cooled for 2 hours, an ESR ingot is obtained after demoulding, the melting speed is controlled to be 3.7 Kg/min-4.2 Kg/min in the remelting stage, and the water temperature in the remelting process is controlled to be 28-35 ℃;
carrying out surface turning treatment on the S1.3.3 cast ingot, wherein the unilateral turning quantity is 5-10 mm, and the diameter is controlled within the range of 400-420 mm, so that vacuum arc remelting treatment is carried out at a later stage;
the adoption of the method for electroslag remelting treatment can effectively reduce the content of S element in the alloy;
step 1.4: vacuum arc remelting:
s1.4.1 cleaning a vacuum arc furnace crystallizer, then adjusting an electrode into the crystallizer, and finishing electrode welding in the furnace after centering treatment;
s1.4.2 vacuum degree is less than 1Pa, and air leakage rate is less than 0.3 Pa/min;
charging helium gas for cooling when S1.4.3 is smelted, and controlling the flow of helium gas to rise from 0ml/min to 110ml/min for the first 0.5h according to the flow, wherein the heat sealing top stage is reduced from 110ml/min to 20ml/min in 0.5 h;
and (5) after the S1.4.4 cast ingot is cooled in the furnace for a certain period of time, breaking the vacuum consumable arc to obtain a steel ingot.
Specifically, in the above-mentioned S1.2.1, the large-size burden is laid on the bottom as much as possible, so as to prevent bridging phenomenon in the melting process.
Specifically, in the S1.2.1, the crucible with the middle heat (more than 10 heats) is adopted for smelting, so that the content of gas elements can be effectively reduced, and the gas release of the crucible wall is serious because of the early heat of the crucible.
Specifically, in the above step s1.2.1, a first portion of nickel plate and a first portion of carbon powder are first loaded into a furnace; then loading the second part of nickel plate, the second part of carbon powder, the first part of cobalt blocks and molybdenum strips into a furnace; and loading the second part of cobalt blocks and the third part of carbon powder into a furnace.
Specifically, in the above S1.2.1, the first part of nickel plate accounts for 1/2 to 2/3 of the total nickel plate mass; the first part of carbon powder accounts for about 1/4 of the total carbon powder mass, the second part of nickel plate accounts for about 1/6 of the total nickel plate mass, the second part of carbon powder accounts for about 1/4 of the total carbon powder mass, the first part of cobalt block accounts for about 1/2 of the total cobalt block mass, the second part of cobalt block accounts for about 1/2 of the total cobalt block mass, and the third part of carbon powder accounts for about 1/4 of the total carbon powder mass.
Specifically, in the above-mentioned S1.2.1, considering that the improvement of the vacuum degree during refining promotes the carbon-oxygen reaction, along with the upward floating and discharge of CO bubbles, the precipitation of H and N, the upward floating of nonmetallic inclusions, the decomposition of nitrides and the volatilization of trace harmful elements are facilitated; however, too high a vacuum level can increase the reaction between the crucible and the metal and the volatilization loss of the alloy element. Therefore, the vacuum pumping is controlled to be less than or equal to 0.1Pa, and the electrification is prepared.
Specifically, in the S1.2.3, the specific steps of adding aluminum blocks and titanium sponge in 3 batches include: firstly, adding a first part of titanium sponge and a first part of aluminum blocks; then adding a second part of titanium sponge and a second part of aluminum blocks; and adding a third part of aluminum blocks after 8-12 min of interval. Wherein the mass ratio of the first portion of titanium sponge to the second portion of titanium sponge is about 1:1, a step of; the mass ratio of the first part aluminum block, the second part aluminum block and the third part aluminum block is about 1:1:1.
specifically, adding Ti to S1.2.3 can reduce Ti inclusions, such as Ti (C, N) formation.
Specifically, al is added in batches in S1.2.3, so that exothermic temperature rise is reduced, and the contents of Al and Ti elements can be controlled simultaneously by feeding Al and Ti in batches.
Specifically, in the S1.4.3, the bottom of the molten pool can be promoted to move upwards by controlling the helium flow to rise from 0ml/min to 110ml/min in the first 0.5h and the heat sealing top stage to fall from 110ml/min to 20ml/min in the 0.5h, so that the bottom of the molten pool is deformed into a flat disc shape from the original back taper; meanwhile, the two-phase area of the pasty area is reduced, the diffusion distance of metal elements in the solidification process is reduced, and the segregation tendency of the alloy is reduced.
Specifically, in S1.4.3, the melting rate of the vacuum consumable remelting affects the micro-porosity amount of the alloy, and in order to reduce the defect, the melting rate control range is as follows: (3.4-4.0) kg/min, and the cooling water temperature is controlled to be 18-28 ℃.
Specifically, in the preparation method, after smelting in the step 1, the components in the molten steel are as follows: c: 0.02-0.04%, cr:18.5 to 20.0 percent, co:13.0 to 14.0 percent, mo:4.0 to 4.90 percent of Al:1.3 to 1.6 percent of Ti:2.80 to 3.25 percent of Ti/Al:2.25 to 2.38, (Al+Ti): 4.35 to 4.58 percent, O: less than or equal to 20PPm, N: less than or equal to 20PPm, less than or equal to 10PPm for S, less than or equal to 80PPm for P, and nickel: the balance.
Specifically, in the step 2, the purpose of the homogenizing annealing is to eliminate the low melting point phase in the steel ingot and to alleviate the element segregation. 2 sections of heat preservation are arranged in the homogenizing annealing, and in the 1 st section of heat preservation, the temperature is lower, and the main function is to eliminate a low-melting-point phase in the alloy; the heat preservation in the 2 nd stage can promote the uniform diffusion of segregation elements. Specifically, the homogenizing annealing process comprises the following steps:
s201, heating to 1150-1165 ℃, and preserving heat for 47-49 h;
s202, continuously heating to 1180-1195 ℃, preserving heat for 65-67 h, and then air-cooling.
Specifically, in S201, the temperature is slowly increased, the furnace temperature is slowly increased from less than or equal to 400 ℃ to 1150-1165 ℃ and the temperature is increased for 10-15 h.
Specifically, in S201, considering that the excessive temperature and the excessive heat preservation time do not play a positive role in the remelting of the low-melting-point phase, and the long-time heat preservation at high temperature can cause deepening of the oxide layer on the surface of the ingot and growth of crystal grains, which is not beneficial to the subsequent forging processing; and the low temperature and the short heat preservation time can not ensure the complete melting back of the low-melting-point phase, and the residual low-melting-point phase is compatible and easy to become a crack source for forging. Therefore, the temperature is controlled to be increased to 1150-1165 ℃, and the heat preservation time and the size of the steel ingot are controlled to be consistent with that of the low-melting-point phase, so that the steel ingot is completely remelted.
Specifically, in S202, the higher the temperature and the longer the holding time, the more sufficient the remelting of the segregation element, but after the temperature and time reach the matching equilibrium point, the remelting of the segregation element will remain stable. The inventors have intensively studied to consider that the homogenization heat treatment can be completed when the residual segregation coefficient reaches 0.2. Therefore, the temperature is too high and the heat preservation time is too long, the positive effect on the remelting of segregation elements is small, the grains are coarse, the energy is wasted, and the production efficiency is reduced; and the low temperature and the short heat preservation time can not ensure that most of segregation elements are remelted, and dendrite segregation reduces the hot working plasticity in the forging process. Therefore, the temperature is controlled to be increased to 1180-1195 ℃, and the heat preservation time and the size of the steel ingot are controlled to be consistent with each other, and the residual segregation coefficient is controlled to be 0.2.
Specifically, in the step 3, the process of preparing the bar blank by adopting quick forging and radial forging is as follows: sequentially upsetting, drawing and radial forging alloy rod blanks with the temperature kept at 1150-1200 ℃; wherein the deformation of each upsetting is 30% -50%, and the deformation of each drawing is 30% -60%; and cooling to 40-50 ℃ after upsetting and drawing out each time, and not cooling again until the heat preservation temperature is reduced to 1050-1120 ℃. If the deformation amount is too large at each time, the alloy has the risk of cracking, and the deformation amount is too large, the alloy grain structure has the risk of mixed crystal in a large deformation area, and if the deformation amount is too small, the alloy deformation is insufficient, and the purposes of grain crushing and recrystallization cannot be achieved.
Specifically, in the step 4, the forging process of the die forging press for preparing the forging piece comprises the following steps: orderly upsetting cakes and die forging the alloy rod blank sections which are insulated at 1030-1060 ℃; the deformation of the upsetting cakes is 50% -60%, and the deformation of the die forging is 50% -60%.
Specifically, in the step 5, the solution treatment process is as follows: heating to 1015-1025 ℃, preserving heat for 3.5-4.5 h, and cooling with oil; considering that the temperature rising speed is too high, the alloy core part does not reach the solid solution temperature, and the heat preservation time is insufficient; therefore, the temperature is slowly increased, the temperature is increased from the temperature of the furnace to be less than or equal to 400 ℃, and the temperature increasing speed is controlled to be 4-6 ℃/min. Too high a temperature or too long a holding time can result in grain growth that is detrimental to alloy performance. The temperature is low or the heat preservation time is too short, and the gamma 'phase cannot be dissolved or partially dissolved, so that preparation is made for obtaining the proper gamma' phase in the subsequent aging process; therefore, the temperature is controlled to be raised to 1015-1025 ℃ and kept for 3.5-4.5 hours.
Specifically, in the step 6, the stabilizing and time-efficient treatment process comprises the following steps: heating to 840-850 ℃, preserving heat for 3-4.5 h, and air cooling; heating to 755-765 ℃, preserving heat for 15-17 h, and then air cooling to room temperature.
Specifically, in the step 6, considering that the temperature rising speed is too high, the alloy core does not reach the stabilization and aging treatment temperature, the heat preservation time is insufficient, the precipitated gamma' phase is insufficient, and the quantity and the size do not reach the optimal matching value; too high a temperature or too long a holding time can lead to larger gamma' -phase size, deviate from the optimal size-to-number ratio and affect the alloy strength. Therefore, the temperature is slowly increased, the temperature is increased from the temperature of the furnace to be less than or equal to 400 ℃, and the temperature increasing speed is controlled to be 4-6 ℃/min.
Specifically, the performance of the nickel-based superalloy obtained in the above step 6 is as follows: room temperature performance: tensile strength sigma b More than or equal to 1300 MPa (e.g. 1330-1420 MPa); yield strength sigma 0.2 More than or equal to 1000 MPa (for example, 1010-1050 MPa); elongation after break delta 5 More than or equal to 20.0 percent (for example, 21 percent to 24 percent); the area reduction ratio psi is more than or equal to 24.0 percent (for example, 25-36 percent); 535 ℃ performance: tensile strength sigma b More than or equal to 1200 MPa (e.g. 1210-1320 MPa); yield strength sigma 0.2 More than or equal to 875 MPa (for example, 885-950 MPa); elongation after break delta 5 More than or equal to 19 percent (for example, 19 percent to 22 percent); the area reduction ratio psi is more than or equal to 23 percent (for example, 24-29 percent); 730 ℃/550MPa durability performance: the lasting time tau is more than or equal to 35 h (for example, 41-47 h); elongation after break delta 5 24% (e.g., 25% -38%); 815 ℃/250MPa durability: the lasting time tau is equal to or longer than 115 h (for example, 118-170 h); elongation after break delta 5 More than or equal to 17 percent (for example, 17 percent to 22 percent); 815 ℃/295MPa durability: the lasting time tau is more than or equal to 52 h (for example, 53-70 h); elongation after break delta 5 More than or equal to 12 percent (for example, 13 to 1)8%); low cycle fatigue performance: 500 ℃/strain control 0-0.7%/0.33 Hz, > 3 x 10 4 Circumference (e.g., 33884-47323).
Compared with the prior art, the nickel-based superalloy of the invention improves the solid solution strengthening effect of the alloy and the grain boundary strength of the alloy by precisely controlling the content of C, cr, co, al, ti and other single elements in the alloy; and by cooperatively controlling the values of Ti/Al and (Al+Ti), the optimal matching of the content and the size of the gamma' phase in the alloy is ensured, the content of inclusions in the alloy is reduced by precisely controlling the content of O, N, S, P, the purity, the plasticity and the fatigue performance of the alloy are improved, the uniformity of crystal grains and the precipitation and the distribution of a grain boundary phase are ensured, and the comprehensive performance of the alloy is ensured.
The preparation method of the nickel-based superalloy of the invention prepares the alloy meeting 700 ℃ service aeroengine rotating parts through controlling the content of key components in the alloy and triple smelting and cogging and die forging processes, and has uniform and fine crystal grains, low crack expansion rate and excellent long-term service comprehensive performance.
The nickel-based superalloy can meet the requirements of materials for rotating parts of 700 ℃ serving aeroengines, and has the following properties: room temperature tensile properties: tensile strength sigma b More than or equal to 1300 MPa (e.g. 1330-1420 MPa); yield strength sigma 0.2 More than or equal to 1000 MPa (for example, 1010-1050 MPa); elongation after break delta 5 More than or equal to 20.0 percent (for example, 21 percent to 24 percent); the area reduction ratio psi is more than or equal to 24.0 percent (for example, 25-36 percent); 535 ℃ performance: tensile strength sigma b More than or equal to 1200 MPa (e.g. 1210-1320 MPa); yield strength sigma 0.2 More than or equal to 875 MPa (for example, 885-950 MPa); elongation after break delta 5 More than or equal to 19 percent (for example, 19 percent to 22 percent); the area reduction ratio psi is more than or equal to 23 percent (for example, 24-29 percent); 730 ℃/550MPa durability performance: the lasting time tau is more than or equal to 35 h (for example, 41-47 h); elongation after break delta 5 24% (e.g., 25% -38%); low cycle fatigue performance: 500 ℃/strain control 0-0.7%/0.33 Hz, > 3 x 10 4 Circumference (e.g., 33884-47323).
The invention also provides application of the nickel-based superalloy, and the nickel-based superalloy can be used for rotating parts of 700 ℃ service aeroengines. Such as for alloy disk shaft integrated turbine disks. The beneficial effects of the nickel-based superalloy of the present invention when used in a rotating member of an aircraft engine are the same as those described above, and are not described here again.
Examples 1 to 5
The following specific examples and comparative examples demonstrate the advantages of the present invention for precise control of the composition and process parameters of the nickel-base superalloys. Embodiments 1-5 of the present invention provide a nickel-base superalloy and a method of making the same.
The composition of the nickel-base superalloys of examples 1-5 is shown in Table 1 below.
The preparation method of the nickel-base superalloy of examples 1 to 5 includes:
example 1
Step 1: sequentially carrying out vacuum induction melting, electroslag remelting and vacuum arc remelting to obtain a steel ingot;
step 1.1: weighing raw materials according to the proportion of alloy components;
step 1.2: vacuum induction melting:
s1.2.1 cloth: firstly, loading a first part of nickel plates and a first part of carbon powder into a furnace; then loading the second part of nickel plate, the second part of carbon powder, the first part of cobalt blocks and molybdenum strips into a furnace; loading the second part of cobalt blocks and the third part of carbon powder into a furnace; after the furnace burden is completely charged into the furnace, vacuumizing until the vacuum degree is less than or equal to 0.1Pa, and preparing for electrifying;
wherein the first part of nickel plate accounts for about 2/3 of the total nickel plate mass; the first part of carbon powder accounts for about 1/4 of the total carbon powder mass, the second part of nickel plate accounts for about 1/6 of the total nickel plate mass, the second part of carbon powder accounts for about 1/4 of the total carbon powder mass, the first part of cobalt block accounts for about 1/2 of the total cobalt block mass, the second part of cobalt block accounts for about 1/2 of the total cobalt block mass, and the third part of carbon powder accounts for about 1/4 of the total carbon powder mass;
s1.2.2 melting and refining: maintaining low-power baking at 50-100 kw, evacuating and exhausting, adopting 200kw, 400kw and 600 kw) to raise power to 1000-1500 kw, adding the residual nickel plate, residual carbon powder and chromium blocks after the furnace material is completely melted until the furnace material is completely melted, and carrying out electromagnetic stirring on the alloy liquid after the furnace material is melted, so as to promote the rapid reduction of O element and N element; the temperature in the melting stage is controlled to be 1500-1560 ℃, and the temperature in the refining stage is controlled to be 1500-1560 ℃;
and S1.2.3, tapping and casting: reducing power, preserving heat, adding aluminum blocks and titanium sponge in batches (adding a first part of titanium sponge and a first part of aluminum blocks firstly, then adding a second part of titanium sponge and a second part of aluminum blocks, and adding a third part of aluminum blocks after 8-12 min intervals, wherein the mass ratio of the first part of titanium sponge to the second part of titanium sponge is about 1:1, and the mass ratio of the first part of aluminum blocks, the second part of aluminum blocks and the third part of aluminum blocks is about 1:1:1), after furnace materials are melted, charging Ar gas into a furnace to 20000 Pa-30000 Pa, adding nickel alloy, applying electromagnetic stirring to promote melting and uniform components, adjusting the power to pouring tapping temperature, controlling the tapping temperature to 1450-1510 ℃, and carrying out vacuum induction ingot casting after furnace cooling for a period of time;
s1.2.4 surface treatment: cutting off a riser after the ingot is cooled, and carrying out surface polishing treatment so as to carry out electroslag remelting treatment in a later period;
step 1.3: electroslag remelting:
s1.3.1 CaF is selected 2 45%~65%，Al 2 O 3 15%~25%，CaO 15%~25%，MgO 2%~8%，TiO 2 0-5% of the slag is used as premelting slag;
after a S1.3.2 electrode is welded and polished into a furnace, argon is introduced, the flow rate of the argon is not lower than 30L/min, slag melting, arcing, remelting and feeding are carried out, after the ingot furnace is cooled for 2 hours, an ESR ingot is obtained after demoulding, the melting speed is controlled to be 3.7 Kg/min-4.2 Kg/min in the remelting stage, and the water temperature in the remelting process is controlled to be 28-35 ℃;
carrying out surface turning treatment on the S1.3.3 cast ingot, wherein the unilateral turning quantity is 5-10 mm, and the diameter is controlled within the range of 400-420 mm, so that vacuum arc remelting treatment is carried out at a later stage;
step 1.4: vacuum arc remelting:
s1.4.1 cleaning a vacuum arc furnace crystallizer, then adjusting an electrode into the crystallizer, and finishing electrode welding in the furnace after centering treatment;
s1.4.2 vacuum degree is less than 1Pa, and air leakage rate is less than 0.3 Pa/min;
s1.4.3 helium is filled for cooling when smelting, and the helium flow is controlled to rise from 0ml/min to 110ml/min for the first 0.5h, and the heat-sealing top stage is reduced from 110ml/min to 20ml/min in 0.5 h. Melting speed control range: (3.6-4.0) kg/min, and controlling the cooling water temperature to be 18-24 ℃;
and (5) after the S1.4.4 cast ingot is cooled in the furnace for a certain period of time, breaking the vacuum consumable arc to obtain a VAR cast ingot with phi 508 mm.
Step 2: homogenizing and annealing the steel ingot: heating from 400 ℃ to 1150 ℃ through 11h, and preserving heat for 47h; continuously heating to 1180 ℃, preserving heat for 65 hours, and then cooling in air;
step 3: preparing a bar blank by adopting quick forging and radial forging: sequentially upsetting and drawing out the alloy rod blank with the temperature of 1200 ℃ for three times, and radially forging; wherein, the deformation amount of upsetting each time is 30 percent, and the deformation amount of drawing each time is 30 percent; cooling to 40 ℃ after upsetting and drawing out each time, and cogging on a radial forging machine for multiple times until the heat preservation temperature is reduced to 1080 ℃ to obtain a finished bar with phi 260 mm;
step 4: forging by adopting a die forging press to prepare a forging piece: orderly upsetting cakes and die forging the alloy rod blank section with the temperature kept at 1060 ℃; the deformation of the upsetting cakes and the forging are respectively 50%, so that a forging piece is obtained;
step 5: solution treatment: heating from the furnace temperature of 400 ℃ at a heating speed of 5 ℃/min to 1015 ℃, preserving heat for 3.5h, and cooling with oil;
step 6: stabilizing and performing time-efficient treatment to obtain a nickel-based superalloy disc member: heating from 400 ℃ to 840 ℃ at a heating speed of 5 ℃/min, preserving heat for 3 hours, and air cooling; heating from the furnace temperature of 400 ℃ at a heating speed of 5 ℃/min, heating to 755 ℃, preserving heat for 15 hours, and then cooling to room temperature by air to obtain the nickel-based superalloy disc.
Example 2
The preparation method of this example is substantially the same as that of example 1, except that:
s1.3.1 the premelted slag component is CaF 2 65%，Al 2 O 3 25%，CaO 25%，MgO 8%，TiO 2 5%；
Step 2: homogenizing and annealing the steel ingot: heating from 400 ℃ to 1165 ℃ through 15h, and preserving heat for 49h; continuously heating to 1195 ℃, preserving heat for 67h, and then cooling in air;
step 3: preparing a bar blank by adopting quick forging and radial forging: sequentially upsetting and drawing out the alloy rod blank with the temperature of 1200 ℃ for three times, and radially forging; wherein, the deformation amount of upsetting each time is 50% and the deformation amount of drawing each time is 60%; cooling to 50 ℃ after upsetting and drawing out each time, and cogging on a radial forging machine for multiple times until the heat preservation temperature is reduced to 1050 ℃ to obtain a finished bar with the diameter of 180 mm;
step 4: forging by adopting a die forging press to prepare a forging piece: orderly upsetting cakes and die forging the alloy rod blank section with the temperature kept at 1060 ℃; the deformation of the upsetting cakes and the forging are respectively 50%, so that a forging piece is obtained;
step 5: solution treatment: heating from the furnace temperature of 400 ℃ at a heating speed of 5 ℃/min to 1025 ℃, preserving heat for 4.5 hours, and cooling with oil;
step 6: stabilizing and performing time-efficient treatment to obtain a nickel-based superalloy disc member: heating from the furnace temperature of 400 ℃ at a heating speed of 5 ℃/min, heating to 850 ℃ and preserving heat for 4.5 hours, and air cooling; heating from the furnace temperature of 400 ℃ at a heating speed of 5 ℃/min, heating to 765 ℃, preserving heat for 17 hours, and then cooling to room temperature to obtain the nickel-based superalloy disc.
Example 3
The preparation method of this example is substantially the same as that of example 1, except that:
s1.3.1 the premelted slag component is CaF 2 55%，Al 2 O 3 20%，CaO 20%，MgO 5%，TiO 2 3%；
Step 2: homogenizing and annealing the steel ingot: raising the temperature from 400 ℃ to 1160 ℃ through 13h, and preserving the heat for 48h; continuously heating to 1190 ℃, preserving heat for 66h, and then cooling in air;
step 3: preparing a bar blank by adopting quick forging and radial forging: sequentially upsetting and drawing out the alloy rod blank with the temperature of 1180 ℃ for three times, and radially forging; wherein, the deformation amount of upsetting each time is 50 percent, and the deformation amount of drawing each time is 50 percent; cooling to 40 ℃ after upsetting and drawing out each time, and cogging on a radial forging machine for multiple times until the heat preservation temperature is reduced to 1060 ℃ to obtain a finished bar with the diameter of 180 mm;
step 4: forging by adopting a die forging press to prepare a forging piece: orderly upsetting cakes and die forging the alloy rod blank section with the temperature of 1050 ℃; the deformation of the upsetting cakes and the forging are 60% respectively, so that a forging piece is obtained;
step 5: solution treatment: heating from the furnace temperature of 400 ℃ at a heating speed of 5 ℃/min to 1020 ℃, preserving heat for 4 hours, and cooling with oil;
step 6: stabilizing and performing time-efficient treatment to obtain a nickel-based superalloy disc member: heating from 400 ℃ to 845 ℃ at a heating speed of 5 ℃/min, preserving heat for 4 hours, and air cooling; heating from the furnace temperature of 400 ℃ at a heating speed of 5 ℃/min, heating to 760 ℃, preserving heat for 16 hours, and then cooling to room temperature by air to obtain the nickel-based superalloy disc.
Examples 4-5 differ from example 3 in that the steel chemistry is different, see table 1, with the remaining parameters being the same.
The invention also provides 5 comparative examples, examples 1-5 and comparative examples 1-5 steel with chemical compositions as shown in Table 1.
Comparative example 4 the same composition as in example 1 was used, and the temperature and deformation amount of the manufactured disc member in step 4 of the manufacturing method were different, wherein the swaging temperature of comparative example 4 was 1090 deg.c and the deformation amounts of the heading cake and the swaging were 30% and 40%, respectively.
Comparative examples 1 to 3 and 5 were identical in preparation with the components of example 3.
The metallographic structures of the examples and comparative examples are shown in Table 2.
Table 3 shows the room temperature mechanical properties of the examples and comparative examples of the present invention, table 4 shows the mechanical properties at 535℃of the examples and comparative examples of the present invention, table 5 shows the durability at 730℃and 550MPa of the examples and comparative examples of the present invention, and Table 6 shows the low cycle fatigue properties at 500℃of the examples and comparative examples of the present invention.
FIG. 1 is a grain diagram of example 1 of the present invention; fig. 2 is a microstructure of example 1 of the present invention, and fig. 3 is a grain diagram of comparative example 4.
The average grain size of the disc forging prepared by adopting the alloy disclosed by the invention is 7.0-7.5, the average grain size is finer than 5 and extremely less than 2, the variation coefficient Cv ranges from 2.33% to 4.33%, the variation coefficient Cv is less than 15%, the data is normal, and the discrete degree is low. The dispersion of the room-temperature tensile strength and the tensile strength at 535 ℃ and the yield strength of the disc forging prepared by the alloy is small, and the variation coefficient Cv value is 2.63% -4.75%; the elongation at break and the area shrinkage Cv are less than 15%, and the dispersion is low in a normal range.
From the analysis, the content of elements in the alloy is precisely controlled; the grain uniformity of the microstructure of the alloy is ensured by cooperatively controlling the values of Ti/Al and (Al+Ti) and combining the accurate control of the preparation method, the grain size reaches more than 6.5 levels, and the content and the size of gamma' phase in the alloy are optimally matched; by accurately controlling the content of O, N, S, P, the content of inclusions in the alloy is reduced, the purity, plasticity and fatigue performance of the alloy are improved, the uniformity of crystal grains and the precipitation and distribution of grain boundary phases are ensured, and the comprehensive performance of the alloy is ensured. The dispersion of the room-temperature tensile strength and the tensile strength at 535 ℃ and the yield strength of the disc forging prepared by the alloy is small, and the variation coefficient Cv value is 2.63% -4.75%; the elongation at break and the area shrinkage Cv are less than 15%, and the dispersion is low in a normal range. The alloy member has small fluctuation in performance.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention.
Claims (8)
1. The nickel-based superalloy is characterized by comprising the following components in percentage by mass: c:0.02% -0.04%, cr:18.5 to 20.0 percent, co:13.0 to 14.0 percent, mo:4.0 to 4.90 percent of Al:1.3 to 1.6 percent of Ti:2.80 to 3.25 percent of Ti/Al:2.25 to 2.38, (Al+Ti): 4.35 to 4.58 percent, O: less than or equal to 20PPm, N: less than or equal to 20PPm, less than or equal to 10PPm for S, less than or equal to 80PPm for P, and nickel: the balance;
the microstructure of the nickel-based superalloy mainly comprises equiaxed austenite grains, evenly distributed carbides and dispersed gamma' -phase; the grain size reaches above 6.5 grade;
the carbide mainly comprises M 23 C 6 And MC; m is M 23 C 6 Is in a short rod shape and is intermittently distributed at the grain boundary; MC is in a block shape and is intermittently distributed in the crystal;
M 23 C 6 the mass percentage of the catalyst is 0.5% -0.75%;
performance of nickel-base superalloy: low cycle fatigue performance: 500 ℃/strain control 0-0.7%/0.33 Hz, > 3 x 10 4 And (3) week(s).
2. The nickel-base superalloy of claim 1, wherein the nickel-base superalloy comprises, in mass percent, C:0.026% -0.037%, cr:18.5 to 19.7 percent, co:13.0 to 13.98 percent of Mo:4.10 to 4.70 percent of Al:1.3 to 1.45 percent of Ti:2.95 to 3.25 percent of O: less than or equal to 10PPm, N: less than or equal to 20PPm, S less than or equal to 8PPm, P less than or equal to 40PPm, nickel: the balance.
3. The nickel-base superalloy of claim 1, wherein the nickel-base superalloy comprises the following components in mass percent: 2.26 to 2.38.
4. The nickel-base superalloy as in claim 1, wherein the nickel-base superalloy comprises the following components in mass percent (al+ti): 4.36 to 4.58 percent.
5. The nickel-base superalloy of claim 1, wherein M is 23 C 6 The mass percentage of the catalyst is 0.57% -0.75%.
6. A method of producing the nickel-base superalloy as in any of claims 1 to 5, comprising:
step 1: sequentially carrying out vacuum induction melting, electroslag remelting and vacuum arc remelting to obtain a steel ingot;
step 2: homogenizing and annealing the steel ingot;
step 3: preparing a bar blank by adopting quick forging and radial forging;
step 4: forging by adopting a die forging press to prepare a forging piece;
step 5: solution treatment;
step 6: stabilizing and treating with time effect to obtain nickel-base superalloy.
7. The method according to claim 6, wherein in the step 1, batch distribution is adopted in the distribution process of vacuum induction melting.
8. The method according to claim 6 or 7, wherein in the step 2, the homogenizing annealing step comprises:
s201, heating to 1150-1165 ℃, and preserving heat for 47-49 h;
s202, continuously heating to 1180-1195 ℃, preserving heat for 65-67 h, and then air-cooling.
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| CN103866163A (en) * | 2014-03-14 | 2014-06-18 | 钢铁研究总院 | Nickel-chromium-cobalt-molybdenum heat resisting alloy and pipe manufacturing process thereof |
| CN104988357A (en) * | 2015-06-17 | 2015-10-21 | 上海大学兴化特种不锈钢研究院 | Nickel base alloy material for ultra-supercritical steam turbine |
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| CN103866163A (en) * | 2014-03-14 | 2014-06-18 | 钢铁研究总院 | Nickel-chromium-cobalt-molybdenum heat resisting alloy and pipe manufacturing process thereof |
| CN104988357A (en) * | 2015-06-17 | 2015-10-21 | 上海大学兴化特种不锈钢研究院 | Nickel base alloy material for ultra-supercritical steam turbine |
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