CN117126996B - Heat treatment method for GH2132 alloy blind rivet sleeve - Google Patents
Heat treatment method for GH2132 alloy blind rivet sleeve Download PDFInfo
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- CN117126996B CN117126996B CN202311394477.8A CN202311394477A CN117126996B CN 117126996 B CN117126996 B CN 117126996B CN 202311394477 A CN202311394477 A CN 202311394477A CN 117126996 B CN117126996 B CN 117126996B
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- 239000000956 alloy Substances 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000010438 heat treatment Methods 0.000 title claims abstract description 28
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 26
- 238000001816 cooling Methods 0.000 claims abstract description 45
- 238000000137 annealing Methods 0.000 claims abstract description 43
- 238000004321 preservation Methods 0.000 claims abstract description 12
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 10
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 10
- 229910052786 argon Inorganic materials 0.000 claims description 5
- 229910052757 nitrogen Inorganic materials 0.000 claims description 5
- 239000007789 gas Substances 0.000 claims 1
- 238000012545 processing Methods 0.000 abstract description 10
- 239000002023 wood Substances 0.000 abstract description 3
- 238000007493 shaping process Methods 0.000 abstract description 2
- 238000012360 testing method Methods 0.000 description 21
- 230000000052 comparative effect Effects 0.000 description 19
- 239000003921 oil Substances 0.000 description 9
- 239000000463 material Substances 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 4
- 238000005336 cracking Methods 0.000 description 4
- 238000004140 cleaning Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 239000006104 solid solution Substances 0.000 description 3
- 238000005482 strain hardening Methods 0.000 description 3
- 229910000601 superalloy Inorganic materials 0.000 description 3
- 238000005491 wire drawing Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 238000004806 packaging method and process Methods 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 238000004381 surface treatment Methods 0.000 description 2
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- 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
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 description 1
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 229910052698 phosphorus Inorganic materials 0.000 description 1
- 239000011574 phosphorus Substances 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000005488 sandblasting Methods 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 229910052717 sulfur Inorganic materials 0.000 description 1
- 239000011593 sulfur Substances 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Insertion Pins And Rivets (AREA)
- Heat Treatment Of Articles (AREA)
Abstract
The invention belongs to the technical field of aerospace fastener processing, and particularly relates to a heat treatment method for a GH2132 alloy blind rivet sleeve, which comprises the following steps of carrying out annealing treatment on the cold-headed rivet sleeve, wherein the annealing treatment is carried out in two steps: step one, heating the nail sleeve subjected to cold heading to 940-960 ℃, keeping the temperature for 45-60min, and cooling the nail sleeve in a furnace after the heat preservation is finished; and step two, cooling the nail sleeve in the step one to 590-610 ℃, preserving heat for 10-15min, and cooling to room temperature by air after preserving heat. According to the invention, two sections of annealing treatment are adopted for the blind rivet sleeve after cold heading, the deformation of the product is effectively controlled by selecting the annealing temperature and controlling the rate of annealing heating and cooling, the treated product has uniform structural grains, the nail sleeve has good shaping, the dimensional precision of the product is ensured, the assembly precision is improved, the connection strength of the blind rivet is ensured, and the hardness technical and wood index of the fastener of the aerospace vehicle is met.
Description
Technical Field
The invention relates to a heat treatment method of a GH2132 alloy blind rivet sleeve, and belongs to the technical field of aerospace fastener processing.
Background
The GH2132 (A286) alloy is Fe-25Ni-15Cr phase precipitation strengthening iron-based superalloy, has higher yield strength and lasting and creep strength below 650 ℃, has better processing plasticity and welding performance, and is suitable for manufacturing high Wen Chengli parts of aeroengines which work for a long time below 650 ℃.
The self-plugging rivet is a common fastener of a modern aerospace vehicle, the nail sleeve is a component part of the self-plugging rivet, and according to the use requirement of a nail sleeve product, the main purpose of heat treatment is to eliminate the work hardening of upsetting forming under the condition of no deformation or little deformation in the forming process of the nail sleeve product, so that the nail sleeve is ensured not to crack in a riveting test, and meanwhile, the connection strength is realized.
According to GH2132 alloy material specification GJB3167A-2021 (cold heading superalloy cold wire drawing material specification), the solution heat treatment system of GH2132 alloy is (980-1000) DEG C, and water (oil) cooling is provided. The solid solution state hardness is less than or equal to 194HV. However, after water cooling or oil cooling according to the standard recommended process, the deformation of the nail sleeve is large, and the riveting test cannot be performed. Therefore, in order to ensure the dimensional accuracy requirement of the nail sleeve product, the cooling speed is not required to be too high on the premise of meeting the product performance. In addition, after the nail sleeve is solid-dissolved according to the standard recommended process, the upper limit of the standard regulated hardness is 194HV, but for the nail sleeve product, the nail sleeve is cracked in the riveting test process due to the excessively high hardness, and the effective connecting effect cannot be exerted due to the excessively low hardness. Therefore, after comprehensively considering the requirements of connection performance, the requirements on the upper limit and the lower limit of the hardness control of the nail sleeve are put forward.
The hardness of the existing rivet sleeve for aviation blind rivets after heat treatment needs to meet the requirement of not cracking and guaranteeing the connection strength within the range of 145 HV-175 HV. This requirement cannot be met with the standard heat treatment regime for GH2132 alloy materials described above. Therefore, a heat treatment method for a blind rivet sleeve made of GH2132 alloy material is needed, so that the hardness of the blind rivet sleeve made of the GH2132 alloy material meets the use requirement.
Disclosure of Invention
Aiming at the defect that a rivet sleeve prepared from the existing GH2132 alloy material cannot meet the use requirement of an aerospace vehicle fastener by adopting a product obtained by adopting the existing standard heat treatment, and has cracking and insufficient connection strength in a riveting test, the invention provides a heat treatment method of the GH2132 alloy rivet sleeve.
The technical scheme for solving the technical problems is as follows:
the heat treatment method of GH2132 alloy blind rivet sleeve is characterized by that the cold-headed rivet sleeve is undergone the process of annealing treatment, and the described annealing treatment is implemented in two steps:
step one, heating the nail sleeve subjected to cold heading to 940-960 ℃, keeping the temperature for 45-60min, and cooling the nail sleeve in a furnace after the heat preservation is finished;
and step two, cooling the nail sleeve in the step one to 590-610 ℃, preserving heat for 10-15min, and air-cooling to room temperature after preserving heat.
The GH2132 alloy comprises, by mass, not more than 0.08% of carbon, not more than 1.00% of silicon, 1.00-2.00% of manganese, not more than 0.03% of phosphorus, not more than 0.02% of sulfur, 13.5-16% of chromium, 24-27% of nickel, 1-1.5% of molybdenum, 0.1-0.5% of vanadium, 1.75-2.35% of titanium, not more than 0.4% of aluminum, 0.001-0.01% of boron and the balance of iron.
After cold heading forming of the blind rivet sleeve, the hardness of the sleeve is improved due to work hardening, and the blind rivet requires high assembly precision and better plasticity, so that the work hardening is eliminated by annealing. The traditional process generally adopts oil cooling or water cooling, and the deformation of the cooled product is large, which is not beneficial to assembly. Moreover, if the annealing temperature is too high, the product strength is too low, and the requirement of riveting on strength cannot be met; if the annealing temperature is too low, the hardness of the product is too high, the plasticity is poor, and the product is easy to crack in the riveting test process. The process has the advantages that air cooling is adopted, the dimensional accuracy of the product is ensured, the assembly problem is solved, the proper annealing temperature is selected, the product after annealing treatment has uniform structure grains, the connection strength is ensured, the good plasticity is realized, and the technical wood index of 145 HV-175 HV of hardness can be met.
Based on the technical scheme, the invention can also make the following improvements:
in the first step, the furnace cooling rate after the heat preservation is finished is 5-10 ℃/min.
The beneficial effects of adopting the further technical scheme are as follows: reducing deformation caused by too high cooling speed in the high temperature stage.
Further, the first step is cooled by adopting nitrogen or argon.
In the second step, the air cooling rate after the heat preservation is finished is 15-25 ℃/min.
The beneficial effects of adopting the further technical scheme are as follows: compared with the conventional annealing cooling speed, the cooling speed is higher, the structure is fully transformed through the heat preservation in the second step, the cooling speed is accelerated, and the processing efficiency can be improved.
Further, the second step adopts nitrogen or argon for cooling.
The invention has the beneficial effects that: according to the invention, the cold-headed blind rivet sleeve blank is subjected to two-section annealing treatment, the deformation of the product can be effectively controlled by selecting the annealing temperature and controlling the annealing cooling rate, and the annealed product has uniform structure grains, so that the sleeve has good shaping, the dimensional accuracy of the product is ensured, the assembly accuracy is improved, the connection strength of the blind rivet is ensured, and the hardness technical and wood index of the aerospace vehicle fastener is met.
Drawings
FIG. 1 is a schematic structural view of a blind rivet sleeve for aerospace;
FIG. 2 is a temperature profile of an annealing treatment of a CH2132 alloy staple sleeve of the present invention;
FIG. 3 is a photograph of a metallographic structure of a GH2132 alloy nail sleeve of comparative example 1 after annealing treatment;
FIG. 4 is a photograph showing the metallographic structure of the GH2132 alloy nail sleeve of example 1 after annealing treatment;
FIG. 5 is a photograph of a metallographic structure of the GH2132 alloy nail sleeve of example 2 after annealing treatment;
FIG. 6 is a photograph of a metallographic structure of the GH2132 alloy nail sleeve of example 3 after annealing treatment;
FIG. 7 is a photograph of a metallographic structure of a GH2132 alloy nail sleeve of comparative example 2 after annealing treatment;
fig. 8 is a photograph of metallographic structure of the GH2132 alloy nail of comparative example 3 after annealing treatment.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
In the following embodiments, a schematic structural diagram of a blind rivet sleeve for an aerospace vehicle is shown in fig. 1, and the technical conditions are as follows:
materials/technical conditions: GH2132 alloy/GJB 3167;
and (3) heat treatment: hardness is 145 HV-175 HV;
surface treatment: cleaning; 100% fluorescence flaw detection.
Among them, GJB3167 (cold heading superalloy cold wire drawing material specification) recommends that the heat treatment system for GH2132 cold wire drawing material be solid solution (980-1000) deg.C, water (oil) cold. The solid solution state hardness is less than or equal to 194HV.
The special requirements of the aerospace craft on the hardness of the nail sleeve cannot be met by adopting the heat treatment system, and the rivet test cannot be performed due to the fact that water (oil) cooling is adopted, the cooling speed is high, the deformation amount after cooling is large, the assembly is affected, and the rivet test cannot be performed.
Example 1
The processing method of the GH2132 alloy nail sleeve specifically comprises the following steps:
(1) Preparing a material, and preparing GH2132 wires with the technical condition of GJB 3167.
(2) Cold heading, and heading forming of the nail sleeve, wherein scratches are not required on the surface of the nail sleeve.
(3) Turning, flattening the end face, turning the outer circle, and chamfering the orifice.
(4) Cleaning, and cleaning, drying and oil-free surface.
(5) Annealing is carried out in two steps:
step (1), heating to 940 ℃ in a vacuum furnace, preserving heat for 1h, and cooling to 600 ℃ at a speed of 5 ℃/min;
and (2) preserving heat at 600 ℃ for 12min, and cooling to room temperature at 15 ℃/min after the heat preservation is finished. In furnace cooling or air cooling, in order to prevent the oxidation of the parts, the step (1) and the step (2) are cooled by using nitrogen or argon.
The temperature profile of the annealing treatment is shown in fig. 2.
(6) And (5) dry sand blasting, namely removing oxide skin and dirt on the surface of the part, and keeping the part clean.
(7) Fluorescence flaw detection, 100% fluorescence flaw detection is carried out on parts.
(8) Surface treatment and dry film lubricant coating.
(9) Marking and processing according to the process.
(10) And final inspection and packaging, and inspecting the size and the test, and packaging and warehousing after the inspection is qualified.
Example 2
In this example, the method for processing a GH2132 alloy nail sleeve is the same as in example 1, and differs from example 1 only in the step (5): step (1), heating to 960 ℃ in a vacuum furnace, preserving heat for 45min, and cooling to 590 ℃ at a speed of 10 ℃/min; and (2) preserving heat at 590 ℃ for 15min, and cooling to room temperature at 25 ℃/min after the heat preservation is finished. The other same parts will not be described again.
Example 3
In this example, the method for processing a GH2132 alloy nail sleeve is the same as in example 1, and differs from example 1 only in the step (5): step (1), heating to 950 ℃ in a vacuum furnace, preserving heat for 55min, and cooling to 610 ℃ at a speed of 8 ℃/min; and (2) preserving heat at 610 ℃ for 10min, and cooling to room temperature by air at 20 ℃/min after the heat preservation is finished. The other same parts will not be described again.
Comparative example 1
In this comparative example, the method for processing a GH2132 alloy nail sleeve was the same as in example 1, and the difference from example 1 was only that in step (5): the annealing temperature in the step (1) of the annealing treatment is 980 ℃. The other same parts will not be described again.
Comparative example 2
In this comparative example, the method for processing a GH2132 alloy nail sleeve was the same as in example 1, and the difference from example 1 was only that in step (5): the annealing temperature in the step (1) of the annealing treatment is 850 ℃. The other same parts will not be described again.
Comparative example 3
In this comparative example, the method for processing a GH2132 alloy nail sleeve was the same as in example 1, and the difference from example 1 was only that in step (5): the annealing treatment adopts a standard heat treatment scheme, namely primary annealing treatment, the annealing temperature is 980 ℃, the heat preservation is carried out for 1.5h, and the oil cooling is carried out.
The nail sleeves obtained by the methods of examples 1 to 3 and comparative examples 1 to 3 were subjected to hardness test and riveting test, the standard according to which the tests were GB/T4340.1 to 2009, and the hardness was tested after the surface polishing treatment of the test pieces.
Taking into account the differences in raw materials of different batches, three batches of experiments were performed, 3 samples were spot checked for each batch, and the results are shown in tables 1 to 3.
Table 1 test data for the first example and comparative example
Table 2 test data for the second example and comparative example
TABLE 3 test data for the third example and comparative example
As can be seen from tables 1 to 3, the heat treatment process of the invention is adopted in examples 1 to 3, the hardness after annealing treatment meets the requirements of 145 to 175HV of product hardness, and the maximum value 158HV and the minimum value 149HV of the hardness in three batches of tests are respectively 9HV in hardness fluctuation, the hardness fluctuation range is small, and the quality consistency is good.
The comparative example 3 adopts standard recommended annealing treatment, the hardness after oil cooling is unqualified, the hardness is lower than the hardness requirement of the product, and the deformation amount of the oil cooling product is large, and part of the product cannot be subjected to riveting test due to deformation.
The comparative example 1 adopts the standard recommended annealing temperature, and the oil cooling mode is changed into air cooling, and the product size can meet the riveting test, but only adopts one annealing treatment, so that the hardness of the product is lower and is not qualified.
In the comparative example 2, one annealing treatment is adopted, the annealing temperature is 850 ℃, the air cooling is carried out, the product size can meet the riveting test, but the hardness is higher than the product requirement, and the product has no cracking in the test, but the hardness of the product exceeds the hardness range specified by the standard, and the product still has the risk of cracking in the use process and does not meet the use requirement.
As can be seen from fig. 3, 7 and 8, fig. 3 and 8 are metallographic photographs of the products of comparative examples 1 and 3, respectively, and as can be seen from fig. 3 and 8, after treatment at 980 ℃, the grain size is 5-grade, and the corresponding hardness is lower than the product requirement. Fig. 4-6 are metallographic structure photographs of the product obtained by the heat treatment process of the invention, wherein after two times of annealing, the grain size is 6 grade, the grains are uniform, and the hardness meets the product requirement. FIG. 7 is a photograph of metallographic structure of the product of comparative example 2, wherein the product of comparative example 2 has a grain size of 7 grade, a non-uniform grain size and an annealing hardness higher than the product requirement after annealing treatment at 850 ℃.
According to the analysis, compared with the traditional standard recommended process, namely the comparison example 3, the process can meet the product hardness requirement of the self-plugging rivet sleeve for the aerospace craft, the hardness consistency is obviously improved, the deformation of the processed product is small, and the riveting test is met. All three batches of products in examples 1-3 were tested to be acceptable, and the quality fluctuation of the raw materials was overcome, and the process was stable.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Claims (3)
1. The heat treatment method of the GH2132 alloy blind rivet sleeve is characterized by carrying out annealing treatment on the cold-headed rivet sleeve, wherein the annealing treatment is carried out in two steps:
step one, heating the nail sleeve subjected to cold heading to 940-960 ℃, wherein the heat preservation time is 45-60min, and after the heat preservation is finished, cooling the nail sleeve in a furnace at a speed of 5-10 ℃/min;
and step two, cooling the nail sleeve in the step one to 590-610 ℃, keeping the temperature for 10-15min, and air-cooling to room temperature after the heat preservation is finished, wherein the air-cooling speed is 15-25 ℃/min.
2. The method for heat treatment of a GH2132 alloy blind rivet sleeve according to claim 1, wherein in the first step, nitrogen or argon furnace cooling is adopted.
3. The heat treatment method of GH2132 alloy blind rivet sleeve according to claim 1, wherein in the second step, nitrogen or argon gas cooling is adopted.
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| CN111235434A (en) * | 2020-03-02 | 2020-06-05 | 北京钢研高纳科技股份有限公司 | Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature |
| CN111334727A (en) * | 2020-04-09 | 2020-06-26 | 成都先进金属材料产业技术研究院有限公司 | Preparation method of high-temperature alloy wire for improving yield of high-temperature alloy rivet |
| CN116713415A (en) * | 2023-05-11 | 2023-09-08 | 中国航发四川燃气涡轮研究院 | Preparation method of high-temperature-resistant high-elasticity GH4169 alloy spring |
| CN116657067A (en) * | 2023-06-01 | 2023-08-29 | 中南大学 | Heat treatment method for uniformly refining mixed crystal structure of GH4169 alloy forging and regulating delta phase content |
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