CN116949309B - Method for preparing porous superalloy - Google Patents
Method for preparing porous superalloy Download PDFInfo
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- CN116949309B CN116949309B CN202311211727.XA CN202311211727A CN116949309B CN 116949309 B CN116949309 B CN 116949309B CN 202311211727 A CN202311211727 A CN 202311211727A CN 116949309 B CN116949309 B CN 116949309B
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- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 21
- 238000000034 method Methods 0.000 title claims abstract description 20
- 239000000956 alloy Substances 0.000 claims abstract description 79
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 61
- AYJRCSIUFZENHW-UHFFFAOYSA-L barium carbonate Chemical compound [Ba+2].[O-]C([O-])=O AYJRCSIUFZENHW-UHFFFAOYSA-L 0.000 claims abstract description 36
- 238000003723 Smelting Methods 0.000 claims abstract description 17
- 239000002994 raw material Substances 0.000 claims abstract description 11
- 239000011248 coating agent Substances 0.000 claims abstract description 9
- 238000000576 coating method Methods 0.000 claims abstract description 9
- 239000002245 particle Substances 0.000 claims abstract description 7
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 claims description 24
- 229910052759 nickel Inorganic materials 0.000 claims description 23
- 239000000395 magnesium oxide Substances 0.000 claims description 21
- 239000000654 additive Substances 0.000 claims description 18
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 claims description 18
- 238000005245 sintering Methods 0.000 claims description 14
- 230000000996 additive effect Effects 0.000 claims description 13
- 238000007670 refining Methods 0.000 claims description 12
- 239000000203 mixture Substances 0.000 claims description 11
- 239000011230 binding agent Substances 0.000 claims description 10
- 239000000919 ceramic Substances 0.000 claims description 10
- 239000004014 plasticizer Substances 0.000 claims description 10
- 229910052720 vanadium Inorganic materials 0.000 claims description 9
- AYJRCSIUFZENHW-DEQYMQKBSA-L barium(2+);oxomethanediolate Chemical compound [Ba+2].[O-][14C]([O-])=O AYJRCSIUFZENHW-DEQYMQKBSA-L 0.000 claims description 8
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 229910052758 niobium Inorganic materials 0.000 claims description 6
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 4
- 229910052719 titanium Inorganic materials 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 3
- 238000002156 mixing Methods 0.000 claims description 3
- 241000275031 Nica Species 0.000 claims description 2
- 229910052786 argon Inorganic materials 0.000 claims description 2
- 238000002844 melting Methods 0.000 claims description 2
- 230000008018 melting Effects 0.000 claims description 2
- 238000003756 stirring Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 22
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 abstract description 8
- QVQLCTNNEUAWMS-UHFFFAOYSA-N barium oxide Chemical compound [Ba]=O QVQLCTNNEUAWMS-UHFFFAOYSA-N 0.000 abstract description 5
- 229910002092 carbon dioxide Inorganic materials 0.000 abstract description 4
- 239000001569 carbon dioxide Substances 0.000 abstract description 4
- 230000001105 regulatory effect Effects 0.000 abstract description 3
- 238000005728 strengthening Methods 0.000 abstract description 3
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 abstract description 2
- 229910002091 carbon monoxide Inorganic materials 0.000 abstract description 2
- 238000011065 in-situ storage Methods 0.000 abstract description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 17
- 239000011148 porous material Substances 0.000 description 16
- 238000009826 distribution Methods 0.000 description 5
- 239000010955 niobium Substances 0.000 description 5
- 238000002360 preparation method Methods 0.000 description 5
- 238000009864 tensile test Methods 0.000 description 5
- 239000011651 chromium Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000005070 sampling Methods 0.000 description 3
- 239000010936 titanium Substances 0.000 description 3
- 241001391944 Commicarpus scandens Species 0.000 description 2
- 229910018107 Ni—Ca Inorganic materials 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 229920001971 elastomer Polymers 0.000 description 2
- 239000000806 elastomer Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- XQGSVNHIIVBMPX-UHFFFAOYSA-N Improsulfan tosylate Chemical compound CC1=CC=C(S([O-])(=O)=O)C=C1.CS(=O)(=O)OCCC[NH2+]CCCOS(C)(=O)=O XQGSVNHIIVBMPX-UHFFFAOYSA-N 0.000 description 1
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000004220 aggregation Methods 0.000 description 1
- 230000002776 aggregation Effects 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- QDWJUBJKEHXSMT-UHFFFAOYSA-N boranylidynenickel Chemical compound [Ni]#B QDWJUBJKEHXSMT-UHFFFAOYSA-N 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012769 display material Substances 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 229910052735 hafnium Inorganic materials 0.000 description 1
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 230000002147 killing effect Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/10—Sintering only
- B22F3/11—Making porous workpieces or articles
-
- 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%
Abstract
The application belongs to the technical field of alloy materials, and discloses a method for preparing a porous superalloy. The main body of the high-temperature alloy is a high-temperature alloy material with high strength, the barium carbonate material coating is applied by customizing the crucible, smelting of the raw material of the high-temperature alloy is realized, bubbles are released by the barium carbonate coating, the vapor pressure of a smelting chamber is regulated, and the gas overflow amount is controlled, so that the inside of the material is kept in rich holes, and the porous high-temperature alloy material is prepared. The application can release carbon monoxide and/or carbon dioxide gas, and can generate a small amount of barium oxide (alkaline oxide) particles in situ, thereby further improving the second phase strengthening capability of the alloy.
Description
Technical Field
The application relates to the technical field of alloy materials, in particular to a method for preparing a porous superalloy.
Background
The high-temperature alloy is a main material for hot end components in the aviation and aerospace fields, and the previous effort direction is to improve the density and purity of the materials so as to realize the service requirements of high temperature, high strength and long service life. However, the requirements for making warhead materials are different. The materials need to be made into thin-wall materials, the alloy strength and toughness of the materials cannot be too high, otherwise the materials are not easy to crush, and a large-range killing effect is difficult to realize. The elastomer has high temperature bearing capacity including thermal expansion adaptability during high speed flying, and the preparation process of high temperature material with high temperature strength, expansion adaptability and easy crushing under high load needs to be developed.
Disclosure of Invention
The application aims to: aiming at the defects in the prior art, the application provides a porous superalloy and a preparation method thereof, and the main purpose is to form rich porous structures in the material to protectOn the premise of ensuring the high strength of the alloy at the through part, the density of the material is reduced by a porous structure, and the high-temperature alloy material which is easy to break is used under the action of high load. Further, the application provides a preparation method of the porous superalloy, wherein BaCO is adopted in the smelting process of the superalloy 3 CO release by high temperature reaction 2 The internal spherical holes are realized, and meanwhile, the scale of the air holes is regulated and overflow and aggregation growth are prevented by utilizing the control of the protective atmosphere pressure of the smelting chamber, so that the preparation of the alloy material with high-temperature strength and low plasticity and toughness can be realized at lower cost.
The technical scheme is as follows: the method for preparing the porous superalloy comprises the following steps:
step 1, mixing barium carbonate, magnesium oxide and additives, stirring uniformly to form a mixture, coating the mixture on the bottom of a smelting vessel, sintering at 600-700 ℃ for 6-7 hours.
Step 2, putting the raw materials to be smelted of the high-temperature alloy into the treated smelting vessel, wherein the charging mode is as follows: cr and C are located at the bottommost part of the crucible, then Ni and Co are spread, then W is added, then Ni and Co are spread, then Mo is spread, ni and Co are spread, and Nb and V as well as Ni and Co are spread.
And 3, vacuumizing, introducing argon for protection, controlling the atmosphere pressure at 50-200kPa, starting heating, refining at 1350-1380 ℃ for 5-10 minutes after raw materials are melted, adding alloy materials, refining at 1550-1600 ℃ at high temperature for 15-20 minutes, adding intermediate alloy, refining at high temperature for 1-5 minutes, and cooling to obtain alloy ingots.
Specifically, the bottom of the smelting vessel in the step 1 is provided with an uneven structure, and the uneven structure can be in a regular shape or in an irregular shape and can be uniformly distributed as much as possible. Preferably, the structure is of regular shape and is evenly distributed at the bottom of the vessel. The rugged structure may be a protrusion or a recess, preferably a protrusion, more preferably a conical protrusion or a truncated cone protrusion. The contact surface area of the bottom of the smelting vessel is larger than that of a conventional container with the same size, so that the contact area can be increased.
Specifically, in the step 1, the adding amount of barium carbonate, magnesium oxide and additives is calculated according to the parts by weight: 80-85 parts of barium carbonate, 10-12 parts of magnesium oxide and 3-10 parts of additive.
More specifically, the granularity of the barium carbonate is 300+/-50 mu m, and the granularity of the magnesium oxide is 0.3-1mm.
More specifically, the additive is a high-temperature-resistant ceramic binder, a plasticizer and a mineralizer, and in the application, the high-temperature-resistant ceramic binder JR006 and the plasticizer are preferable.
Specifically, in step 2, the cloth mode is: cr and C are located at the bottommost part of the crucible, then 20-30% of Ni and Co are paved, then W is added, then 20-30% of Ni and Co are paved, then Mo is paved, 20-30% of Ni and Co are paved, and Nb and V and the rest of Ni and Co are paved. The material distribution mode is adopted, because the C is distributed at the lower part and is favorable for combining with oxygen of metal elements to form bubbles, the strength and toughness of the metal joint after deoxidation are better, and the weight of the bubbles can be reduced.
Specifically, in the step 3, the alloy materials are Al and Ti, and in the step 3, the alloy materials are added because Al and Ti have large melting heat release capacity, and after enough melt exists, the increase of the heat capacity can reduce the influence of the abrupt temperature rise on the size of bubbles.
Specifically, in the step 3, the intermediate alloy is NiCa and NiB, and in the application, the addition of the intermediate alloy has the effect of improving the shape of residual oxidized inclusions of the alloy by adding Ca and controlling the shape of bubbles by affecting the surface tension of the solid-liquid surface by adding B. Further, the alloy material is preferably nickel-boron intermediate alloy.
The beneficial effects are that: the main body of the high-temperature alloy is a high-temperature alloy material with high strength, the coating is applied by customizing the crucible with large surface area and bottom sawtooth characteristic, the smelting of the raw materials of the high-temperature alloy is realized, and the BaCO of the crucible coating 3 The material can react to release carbon dioxide at high temperature of 1350 ℃ or above, so that the coating BaCO is utilized in the smelting process 3 → BaO + CO 2 Carbon dioxide bubbles released by the chemical reaction are regulated by vapor pressure of the smelting chamber, and the gas overflow amount is controlled, so that the inside of the material is kept rich in holes, and the porous high-temperature alloy material is prepared.
BaCO of the application 3 After the material is decomposed, carbon monoxide and/or carbon dioxide gas can be released, and a small amount of barium oxide (alkaline oxide) particles can be generated in situ, so that the second-phase strengthening capability of the alloy is further improved.
Drawings
Fig. 1 is a schematic structural view of a smelting vessel of the present application.
Fig. 2 is a schematic view of the bottom structure of the smelting vessel of the present application.
FIG. 3 is a schematic diagram of the porous superalloy preparation of the present application.
FIG. 4 is a graph of bubble morphology in a molten superalloy master alloy ingot in example 1.
FIG. 5 is a microscopic distribution of bubbles in a molten superalloy master alloy ingot in example 1.
FIG. 6 is a microscopic distribution of bubbles in a molten superalloy master alloy ingot in example 2.
FIG. 7 shows the fracture after the material fracture in example 1.
Detailed Description
The technical scheme of the present application is described in detail by examples below, but the scope of the present application is not limited to the examples.
Example 1
The high-temperature alloy prepared in the embodiment comprises the following components: carbon, chromium, aluminum, cobalt, titanium, molybdenum, tungsten, niobium, vanadium, hafnium, and zirconium, with the balance being nickel.
The raw materials are mixed according to a certain proportion to be used as raw materials of the high-temperature alloy, and the high-temperature alloy is smelted into master alloy in a vacuum furnace. The smelting master alloy adopts a customized magnesium oxide crucible for a 25 kg furnace. The bottom of the magnesia crucible has an inner diameter of 115mm and an outer diameter of 149mm; the upper edge has an inner diameter of 140mm, an outer diameter of 170mm and a height of 320mm, conical protrusions are uniformly distributed at the bottom, and the diameter of the bottom surface of each protrusion is about 10mm; and a height of about 4mm. The protrusions are arranged in a row. The rows are staggered.
Mixing barium carbonate, magnesium oxide and additives according to mass ratio to obtain a mixture, wherein the barium carbonate is 80 parts, and the granularity of the barium carbonate is 300+/-50 mu m; 12 parts of magnesium oxide with the granularity of 0.3-1mm; 8 parts of additive (high-temperature resistant ceramic binder JR006 and plasticizer). The bottom of the custom magnesium oxide crucible is coated by hand, the thickness of the coating is about 10% of the diameter of the crucible, namely about 10mm, and the coated crucible is sintered in a muffle furnace at 600 ℃ for 6 hours.
During smelting, the raw materials of the high-temperature alloy are placed into a crucible, the charging sequence is the bottommost part of a Cr crucible and a C crucible, then 25% of Ni and Co are paved, then W is added, then 25% of Ni and Co are paved, then Mo is paved, then 25% of Ni and Co are paved, finally Nb and V and the rest of Ni and Co are paved, vacuumizing and heating treatment are carried out, after the raw materials are converted into clear, refining treatment is carried out at 1380 ℃ for 5 minutes, and then Al, ti and other alloy materials are added. Then high-temperature refining treatment is carried out at 1550 ℃ for 15 minutes, then Ni-Ca and Ni-B intermediate alloy is added, high-temperature refining treatment is continued for 2 minutes, and finally alloy liquid is obtained. And cooling to obtain a master alloy ingot of the high temperature alloy.
The morphology of bubbles in the molten superalloy master alloy ingot is shown in FIG. 4. The microscopic distribution of bubbles in the molten superalloy master alloy ingot is shown in FIG. 5. The fracture after the alloy material is broken is shown in fig. 7, and it can be seen that the metal around the air hole has obvious toughness.
Sampling the obtained master alloy ingot of the high temperature alloy to carry out the component and pore, aperture and tensile test. The test results are shown in the following table.
TABLE 1 composition (wt%) of superalloy
TABLE 2 relative porosities, pore sizes, 800 ℃ stretch plasticity of alloy ingots
As can be seen from the data in the table, the high-temperature alloy prepared in the embodiment 1 is similar to the common high-temperature solid solution strengthening high-temperature alloy, and the high-temperature alloy has the advantages of high porosity, high-temperature strength, low plasticity and easiness in breaking.
Example 2
The C content of the alloy was reduced compared to example 1, with a corresponding slightly reduced content of V, W carbide forming elements; the procedure was substantially the same as in example 1, except that the barium carbonate was 85 parts and the barium carbonate particle size was 300.+ -.50. Mu.m; 10 parts of magnesium oxide with the granularity of 0.3-1mm; 5 parts of additive (high temperature resistant ceramic binder JR006, plasticizer). The bottom of the customized magnesia crucible is coated manually, the coated crucible is sintered in a muffle furnace, the sintering treatment temperature is 680 ℃, and the sintering treatment time is 4 hours.
The microscopic distribution of bubbles in the molten superalloy master alloy ingot is shown in FIG. 6.
Sampling the obtained master alloy ingot of the high temperature alloy to carry out the component and pore, aperture and tensile test. The test results are shown in the following table.
TABLE 3 composition (wt%) of superalloy
TABLE 4 relative porosities, pore sizes, 800 ℃ stretch plasticity of alloy ingots
The material prepared by the process has high porosity, but can still keep proper area shrinkage and extensibility due to low matrix strength.
Example 3
The C content of the alloy was reduced compared to example 1, with a corresponding slightly reduced content of V, W carbide forming elements; the procedure was substantially the same as in example 1, except that barium carbonate was 70 parts and the particle size of barium carbonate was 300.+ -.50. Mu.m; 20 parts of magnesium oxide with the granularity of 0.3-1mm; 10 parts of additive (high-temperature resistant ceramic binder JR006 and plasticizer). The bottom of the customized magnesia crucible is coated manually, the coated crucible is sintered in a muffle furnace, the sintering treatment temperature is 600 ℃, and the sintering treatment time is 6 hours.
The master alloy ingots of the high temperature alloys obtained in example 2 and example 3 were sampled and subjected to pore, pore diameter and tensile test. The test results are shown in the following table.
TABLE 5 relative porosities, pore sizes, 800 ℃ stretch plasticity of alloy ingots
As can be seen from the results of examples 1 to 3, the barium carbonate is 80 parts and the granularity of the barium carbonate is 300+ -50 μm; 12 parts of magnesium oxide with the granularity of 0.3-1mm; 8 parts of additive (high-temperature resistant ceramic binder JR006 and plasticizer); the sintering treatment temperature is 600 ℃, the sintering treatment time is 6 hours, the treatment effect is optimal, the strength is moderate, the plasticity is low, and the sintering treatment device is more suitable for serving as a warhead.
Example 4
The alloy composition was the same as in example 1, the procedure was substantially the same as in example 1, except that 50 parts of barium carbonate was used as an additive, and the particle size of barium carbonate was 300.+ -. 50. Mu.m; 40 parts of magnesium oxide with the granularity of 0.3-1mm; 10 parts of additive (high-temperature resistant ceramic binder JR006 and plasticizer); the sintering treatment temperature was 600℃and the sintering treatment time was 6 hours.
Example 5
The alloy composition was the same as in example 1, the procedure was substantially the same as in example 1, except that the additives were: 50 parts of barium carbonate, wherein the granularity of the barium carbonate is 300+/-50 mu m; 25 parts of magnesium oxide with the granularity of 0.3-1mm; 25 parts of additive (high-temperature resistant ceramic binder JR006 and plasticizer); the sintering treatment temperature is 600 ℃, the sintering treatment time is 6 hours, the treatment effect is optimal, and the sintering treatment is mainly characterized by less pores, high strength and high plasticity, and is not suitable for serving as a warhead. The treated pores are less, the strength is high, the plasticity is high, and the method is not suitable for serving as a warhead.
The master alloy ingots of the high temperature alloys obtained in example 4 and example 5 were sampled and subjected to pore, pore diameter and tensile test. The test results are shown in the following table.
TABLE 6 relative porosities, pore sizes, 800 ℃ stretch plasticity of alloy ingots
As can be seen from the test results of examples 1, 4 and 5, the barium carbonate is 80 parts and the granularity of the barium carbonate is 300+/-50 mu m; 12 parts of magnesium oxide with the granularity of 0.3-1mm; 8 parts of additive (high-temperature resistant ceramic binder JR006 and plasticizer) with more treated pores, high strength and low plasticity, and is suitable for serving as a warhead.
Comparative example
The same superalloy as in example 1 was prepared, the starting materials of the superalloy were placed in a common crucible, the charging sequence was the bottommost of the Cr and C crucibles, then 25% of Ni and Co were spread, then W was added, then 25% of Ni and Co were spread, then Mo was spread, then 25% of Ni and Co were spread, finally Nb and V and the remaining Ni and Co were spread, vacuum-pumping and heat treatment were performed, refining treatment was performed at 1380 ℃ for 5 minutes after the raw materials were converted to clear, and then Al, ti and other alloying materials were added. Then high-temperature refining treatment is carried out at 1550 ℃ for 15 minutes, then Ni-Ca and Ni-B intermediate alloy is added, high-temperature refining treatment is continued for 2 minutes, and finally alloy liquid is obtained.
Sampling the obtained master alloy ingot of the high temperature alloy to carry out the component and pore, aperture and tensile test. The test results are shown in the following table.
TABLE 7 composition of superalloy (wt%)
TABLE 8 relative porosities, pore sizes, 800 ℃ stretch plasticity of alloy ingots
As can be seen from the data in the table, when the common crucible is used and the barium carbonate coating is not provided, the obtained alloy material is not a porous material, and has high strength, but the high-temperature elongation can reach 9%, the area reduction rate is 15%, and the display material is not easy to break and is not suitable for being used as a warhead.
In summary, the application is mainly used for maintaining rich holes in the material, thereby preparing the porous high-temperature alloy material, and meeting the requirements of the material for high temperature bearing capacity, including adaptability of thermal expansion and high-temperature material which is easy to crush under a large load during high-speed flight of the elastomer.
The foregoing description is only of the preferred embodiments of the application and is not intended to limit the application.
Claims (7)
1. A method of forming a porous superalloy, comprising the steps of:
step 1, mixing barium carbonate, magnesium oxide and additives, stirring uniformly to form a mixture, coating the mixture on the bottom of a smelting vessel, sintering at 600-700 ℃ for 6-7 hours;
step 2, putting the raw materials of the high-temperature alloy to be smelted into the treated smelting vessel, wherein the charging mode is as follows: cr and C are positioned at the bottommost part of the crucible, then Ni and Co are paved, W is added, then Ni and Co are paved, mo is paved, ni and Co are paved, nb and V are paved, and Ni and Co are paved;
step 3, vacuumizing, introducing argon for protection, controlling the atmosphere pressure at 50-200kPa, starting heating, refining at 1350-1380 ℃ for 5-10 minutes after raw materials are melted, adding alloy materials, refining at 1550-1600 ℃ at high temperature for 15-20 minutes, adding intermediate alloy, refining at high temperature for 1-5 minutes to obtain alloy liquid, and cooling to obtain alloy ingots;
in the step 1, the adding amount of the barium carbonate, the magnesium oxide and the additive is calculated according to the mass parts, and the mixture ratio is as follows: 80-85 parts of barium carbonate, 10-12 parts of magnesium oxide and 3-10 parts of additive;
in the step 1, the additive is a high-temperature resistant ceramic binder JR006 and a plasticizer;
in the step 2, the charging mode is as follows: cr and C are located at the bottommost part of the crucible, then 20-30% of Ni and Co are paved, then W is added, then 20-30% of Ni and Co are paved, then Mo is paved, 20-30% of Ni and Co are paved, and Nb and V and the rest of Ni and Co are paved.
2. The method of claim 1, wherein the melting vessel in step 1 has a rugged structure at the bottom.
3. The method of claim 2, wherein the rugged structure is regular and uniformly distributed at the bottom of the vessel.
4. The method of claim 2, wherein the rugged structure is conical or frustoconical.
5. The method of claim 1, wherein in step 1, the barium carbonate has a particle size of 300±50 μm and the magnesium oxide has a particle size of 0.3 to 1mm.
6. The method of claim 1, wherein in step 3, the alloy material is Al or Ti.
7. The method of claim 1, wherein in step 3, the intermediate alloy is NiCa or NiB.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311211727.XA CN116949309B (en) | 2023-09-20 | 2023-09-20 | Method for preparing porous superalloy |
Applications Claiming Priority (1)
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