CN112375880A - Aging treatment method for high-temperature alloy for turbine disk - Google Patents
Aging treatment method for high-temperature alloy for turbine disk Download PDFInfo
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- CN112375880A CN112375880A CN202011250214.6A CN202011250214A CN112375880A CN 112375880 A CN112375880 A CN 112375880A CN 202011250214 A CN202011250214 A CN 202011250214A CN 112375880 A CN112375880 A CN 112375880A
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- 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
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/74—Methods of treatment in inert gas, controlled atmosphere, vacuum or pulverulent material
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/46—Ferrous alloys, e.g. steel alloys containing chromium with nickel with vanadium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/50—Ferrous alloys, e.g. steel alloys containing chromium with nickel with titanium or zirconium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/54—Ferrous alloys, e.g. steel alloys containing chromium with nickel with boron
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Abstract
The invention relates to the field of alloy heat treatment methods, in particular to a high-temperature alloy aging treatment method for a turbine disc, which has the advantages of uniform structure, reasonable size and distribution of precipitated phases, improved high-temperature comprehensive mechanical properties, safe and simple operation and lower operation cost, and comprises the following steps: putting the iron-based high-temperature alloy material to be treated into a high-temperature furnace, heating to 650-750 ℃ for aging treatment for at least 10 hours, continuously introducing inert gas into the high-temperature furnace during the aging treatment, opening the furnace body after the aging treatment is finished, and taking out the material. The invention is especially suitable for the production of high-temperature alloys such as high-quality turbine disks, compressor disks, rotor blades, fasteners and the like.
Description
Technical Field
The invention relates to the field of alloy heat treatment methods, in particular to a high-temperature alloy aging treatment method for a turbine disc.
Background
The microstructure and properties of certain metallic materials such as superalloys are sensitive to fluctuations in heating temperature, and when aging is performed, it is required that the temperature be accurate and stable throughout the aging process, and that the quality be guaranteed only by preventing oxidation at high temperatures. GH2132 is Fe-25Ni-15 Cr-based high-temperature alloy, is added with molybdenum, titanium, aluminum, vanadium and trace boron for comprehensive reinforcement, has good processability and weldability, and is suitable for manufacturing high-temperature bearing parts of an aircraft engine working for a long time at the temperature of below 650 ℃, such as a turbine disc, a compressor disc, a rotor blade, a fastener and the like. The delivery state is (980-1000 ℃, 1-2 h of oil cooling + 700-720 ℃ aging for 16h, air cooling), and in order to research the comprehensive use performance of the product under the high-temperature condition, the high-temperature aging treatment is carried out for 10-24 h at 650-750 ℃.
Because the quality requirement of the iron-based wrought superalloy on heat treatment is very high, a satisfactory alloy structure cannot be obtained in the heating process if the temperature is not well controlled, and the quality of the material is adversely affected. The aging treatment of common domestic high-temperature alloys is carried out in a common heat treatment furnace (or an experimental furnace), the temperature fluctuation is usually about +/-3 ℃ under the long-time heat preservation condition of 650-750 ℃ (the experimental furnace), the temperature fluctuation range of the large-scale industrial heat treatment furnace is larger, and the high-temperature oxidation of the surface of an alloy test piece cannot be prevented usually. Meanwhile, high-temperature long-time aging treatment is time-consuming and energy-consuming, and the comprehensive cost of the aging treatment is high.
The patent CN111424159A, named GH4780 alloy welded joint aging treatment method, adopts the scheme that the GH4780 alloy welded joint is firstly insulated for 6-10h at 790-850 ℃, then insulated for 6-10h at 730-760 ℃ and finally insulated for 6-10h at 610-660 ℃. The method can ensure that elements in the welding seam of the GH4780 alloy welding joint are distributed more uniformly, reasonably regulate and control the size and distribution of precipitated phases, effectively reduce the residual stress in the welding joint and improve the mechanical property of the welding joint. The method describes the aging treatment of the GH4780 alloy welding joint, uses a conventional heating furnace for the aging treatment, is suitable for the alloy welding joint, and does not relate to the application of precise temperature control and inert gas protection technology. The temperature precision, stability and anti-oxidation performance which are suitable for the method are higher in requirement. Patent CN107523767A, entitled an aging treatment method for aluminum alloy, which is characterized in that the aluminum alloy workpiece is put into a heating furnace with a first preset temperature; cutting off the power supply of the heating furnace; the aluminum alloy workpiece is cooled to a second preset temperature in the heating furnace along with the furnace; maintaining the aluminum alloy workpiece at a second predetermined temperature for a predetermined period of time; taking out the aluminum alloy workpiece to naturally cool the aluminum alloy workpiece to room temperature in air; wherein the first predetermined temperature is in the range of 210-240 ℃, and the aluminum alloy is ZL 104. The method can shorten the process time to obtain the aluminum alloy workpiece with good tissue uniformity, high elongation and higher toughness requirement, the aging treatment method is ZL104 aluminum alloy, the aging temperature is not high (< 300 ℃), and the method is suitable for aluminum alloy workpieces, and the method is suitable for high-temperature aging of iron-based wrought high-temperature alloy, and the heating process is completely different.
Disclosure of Invention
The invention aims to solve the technical problem of providing the high-temperature alloy aging treatment method for the turbine disc, which has the advantages of uniform structure of the alloy, reasonable size and distribution of precipitated phases, improved high-temperature comprehensive mechanical properties, safe and simple operation and lower operation cost.
The technical scheme adopted by the invention for solving the technical problems is as follows: the aging treatment method of the high-temperature alloy for the turbine disk comprises the following steps: putting the iron-based high-temperature alloy material to be treated into a high-temperature furnace, heating to 650-750 ℃ for aging treatment for at least 10 hours, continuously introducing inert gas into the high-temperature furnace during the aging treatment, opening the furnace body after the aging treatment is finished, and taking out the material.
Furthermore, the time range of the aging treatment is 10-24 hours.
Further, the inert gas is high-purity argon.
Further, the high purity argon gas is supplied at a rate of 50 ml/min.
Furthermore, after the aging treatment is finished, the furnace body is opened again to take out the materials when the furnace temperature is reduced to below 150 ℃.
Further, the continuous and uninterrupted introduction of the inert gas into the high-temperature furnace is performed in the following manner: the tube cavity in the high temperature furnace is repeatedly evacuated and replaced with inert gas.
Further, the high-temperature furnace is a corundum tubular furnace.
Further, the material to be treated is put into a high temperature furnace and then heated to 650-750 ℃ at a heating rate of 10 ℃/min.
Further, the temperature is kept stable after the heating is carried out to the temperature of 650-750 ℃, wherein the temperature fluctuation is within +/-1.0 ℃.
Further, the material to be treated is GH2132 iron-based high-temperature alloy, and the material to be treated mainly comprises the following components in percentage by mass: less than or equal to 0.08 percent of carbon, 13.5 to 16.0 percent of chromium, 24.0 to 27.0 percent of nickel, 1.0 to 1.5 percent of molybdenum, 1.9 to 2.35 percent of titanium, 0.1 to 0.5 percent of vanadium, 0.003 to 0.01 percent of boron, less than or equal to 0.35 percent of silicon, less than or equal to 0.35 percent of manganese, less than or equal to 0.015 percent of phosphorus, less than or equal to 0.002 percent of sulfur, less than or equal to 0.35 percent of aluminum, and the balance of iron.
The invention has the beneficial effects that: the whole aging process of the invention can well ensure the accurate control of the treatment process and simultaneously can be convenient for stably controlling the temperature. Because the inert gas is continuously introduced for protection, the surface oxidation of the test piece is effectively prevented. The method can ensure that the GH2132 alloy has uniform structure, the size and the distribution of precipitated phases are reasonable, and the high-temperature comprehensive mechanical property of the GH2132 alloy is improved. The method is safe and simple to operate, has low operation cost, and really realizes high-precision, high-quality, high-efficiency, low-cost and high-temperature aging treatment of alloy materials represented by GH2132 iron-based high-temperature alloy. The invention is especially suitable for the production of high-temperature alloys such as high-quality turbine disks, compressor disks, rotor blades, fasteners and the like.
Detailed Description
The aging treatment method of the high-temperature alloy for the turbine disk comprises the following steps: putting the iron-based high-temperature alloy material to be treated into a high-temperature furnace, heating to 650-750 ℃ for aging treatment for at least 10 hours, continuously introducing inert gas into the high-temperature furnace during the aging treatment, opening the furnace body after the aging treatment is finished, and taking out the material. For the practical application object, the material to be treated is preferably GH2132 iron-based high-temperature alloy, and the main components of the alloy are as follows by mass percent: less than or equal to 0.08 percent of carbon, 13.5 to 16.0 percent of chromium, 24.0 to 27.0 percent of nickel, 1.0 to 1.5 percent of molybdenum, 1.9 to 2.35 percent of titanium, 0.1 to 0.5 percent of vanadium, 0.003 to 0.01 percent of boron, less than or equal to 0.35 percent of silicon, less than or equal to 0.35 percent of manganese, less than or equal to 0.015 percent of phosphorus, less than or equal to 0.002 percent of sulfur, less than or equal to 0.35 percent of aluminum, and the balance of iron.
In order to obtain better treatment effect, the following scheme is preferred: firstly, the time range of the aging treatment is 10-24 hours, so that a better aging treatment effect is obtained. Secondly, the inert gas is high-purity argon gas, so that a better effect of preventing the surface of the test piece from being oxidized by the inert gas is ensured, and the gas feeding speed of the high-purity argon gas is generally preferably 50 ml/min. And thirdly, after the aging treatment is finished, opening the furnace body to take out the material when the furnace temperature is reduced to be below 150 ℃, thereby ensuring that the aging treatment is ensured to be necessary in time and temperature. Fourthly, the mode of continuously and uninterruptedly introducing inert gas into the high-temperature furnace is as follows: the tube cavity in the high-temperature furnace is repeatedly vacuumized and replaced by inert gas, so that the surface oxidation of the test piece is better prevented.
In addition, preferably, the material to be treated is placed in a high-temperature furnace and then heated to 650-750 ℃ at a heating rate of 10 ℃/min, so that the temperature is improved better, and the aging treatment effect is ensured. The temperature is preferably kept stable after heating to a temperature ranging from 650 ℃ to 750 ℃, wherein the temperature fluctuation is within +/-1.0 ℃.
The feasibility of the protocol of the present application was tested by the following test method: firstly, a high-precision atmosphere protection tube furnace is utilized, wherein a GH2132 iron-based high-temperature alloy to be treated is manufactured into a phi 30 x 50mm test piece, a hearth is a phi 80 x 600mm corundum tube, a heating element is an inlet HRE electric heating wire, and a precise temperature control and measurement system is matched. Under the long-time aging treatment condition of 650-750 ℃, the temperature fluctuation can be accurately controlled within +/-1.0 ℃, the temperature drift is small, the stability is high, the influence of the change of the environmental temperature is avoided, and the test accuracy is obviously improved; the whole process can also continuously introduce high-purity argon inert protective gas to prevent the oxidation reaction of the test piece at high temperature; the equipment power of the high-precision atmosphere protection tube furnace (the highest temperature can reach 1200 ℃) is only about 3 KW. The invention has safe and simple operation and lower operation cost, and really realizes high-precision, high-quality, high-efficiency and low-cost high-temperature aging treatment.
Examples
Example 1
Example 1 is a method for aging a high-temperature alloy for a turbine disk according to the present invention. The invention adopts a phi 30X 50mm test piece made of GH2132 iron-based high-temperature alloy, the test piece is divided into three groups before heating, the test piece is heated to 650 ℃ for heat preservation, then the three groups of test pieces are aged for 10, 16 and 24 hours respectively, the temperature is stabilized at 650 +/-1.0 ℃ in the whole aging process, high-purity argon protective gas is continuously and uninterruptedly introduced, after the test is finished, all the three groups of test pieces are observed, the surfaces of the test pieces have no oxidation phenomenon, and the metallographic structure of the test piece under each aging treatment process is detected and analyzed. After solution treatment and aging, the GH2132 iron-based high-temperature alloy has a structure comprising gamma', MC and mu phases besides an austenite matrix. The observation result of the metallographic microstructure after the high-temperature aging treatment at 650 ℃ is as follows: the internal and external structures of the test piece are uniform, and because the aging temperature is lower, the gamma' phase which is uniform, fine and more in quantity is separated out, and the formed twin crystal lath is thin, small and more in quantity. With the prolonging of the aging time, the precipitation amount is increased, but the growth is not obvious.
Example 2
In example 2, the aging treatment method for the high-temperature alloy for the turbine disk of the invention is applied, and a test piece of phi 30 x 50mm made of the GH2132 iron-based high-temperature alloy is invented. The test pieces are divided into three groups before heating, the test pieces are heated to 700 ℃ for heat preservation, then the three groups of test pieces are aged for 10 hours, 16 hours and 24 hours respectively, the temperature is stabilized at 700 +/-1.0 ℃ in the whole aging process, high-purity argon protective gas is continuously and uninterruptedly introduced, after the test is finished, all the test pieces are observed, the surfaces of the test pieces are free of oxidation, and metallographic structure detection and analysis are carried out on the test pieces under each process. GH2132 iron-based high-temperature alloy, a metallographic microstructure observation result after high-temperature aging treatment at 700 ℃ is as follows: the crystal grains are fine and uniform inside and outside, the crystal boundary is round and smooth, a small amount of twin crystals exist in the crystal grains, the size of the crystal grains is not changed along with the prolonging of the aging time, the number of the twin crystals is increased, and the number of the twin crystals is reduced after 24 hours of aging.
Example 3
In example 3, the aging treatment method for the high-temperature alloy for the turbine disk of the present invention is applied, and a test piece of phi 30 × 50mm made of GH2132 iron-based high-temperature alloy is invented. Dividing the test pieces into three groups before heating, firstly heating the test pieces to 750 ℃ for heat preservation, then aging the three groups of test pieces for 10 hours, 16 hours and 24 hours respectively, stabilizing the temperature in the whole aging process at 750 +/-1.0 ℃, continuously introducing high-purity argon protective gas, observing all the test pieces after the test is finished, wherein the surfaces of the test pieces have no oxidation phenomenon, and carrying out metallographic structure detection and analysis on the test pieces under each process. GH2132 iron-based high-temperature alloy, a metallographic microstructure observation result after high-temperature aging treatment at 750 ℃ is as follows: the internal and external structures of the test piece are uniform, the quantity of twin crystals in the crystal is reduced, the twin crystal lath is widened, the three groups of test pieces are aged for 10 hours, 16 hours and 24 hours respectively, the microscopic structures of the test pieces are basically consistent, and the relation with the aging time is not large.
The embodiment can obtain that the invention not only can ensure that the alloy has uniform structure, reasonable precipitated phase size and distribution, improved high-temperature comprehensive mechanical property, but also has safe and simple operation, very obvious technical advantages and very wide market popularization prospect.
Claims (10)
1. The aging treatment method of the high-temperature alloy for the turbine disk is characterized by comprising the following steps of: putting the iron-based high-temperature alloy material to be treated into a high-temperature furnace, heating to 650-750 ℃ for aging treatment for at least 10 hours, continuously introducing inert gas into the high-temperature furnace during the aging treatment, opening the furnace body after the aging treatment is finished, and taking out the material.
2. The method for aging a high temperature alloy for a turbine disk as claimed in claim 1, wherein: the time range of the aging treatment is 10-24 hours.
3. The aging treatment method for a high-temperature alloy for a turbine disk according to claim 1 or 2, wherein: the inert gas is high-purity argon.
4. The method for aging a high temperature alloy for a turbine disk as claimed in claim 3, wherein: the gas feeding speed of the high-purity argon is 50 ml/min.
5. The aging treatment method for a high-temperature alloy for a turbine disk according to claim 1 or 2, wherein: after the aging treatment is finished, opening the furnace body to take out the material when the furnace temperature is reduced to below 150 ℃.
6. The aging treatment method for the high-temperature alloy for the turbine disk as set forth in claim 1 or 2, wherein the inert gas is continuously and uninterruptedly introduced into the high-temperature furnace in a manner that: the tube cavity in the high temperature furnace is repeatedly evacuated and replaced with inert gas.
7. The aging treatment method for a high-temperature alloy for a turbine disk according to claim 1 or 2, wherein: the high-temperature furnace is a corundum tubular furnace.
8. The aging treatment method for a high-temperature alloy for a turbine disk according to claim 1 or 2, wherein: after the material to be treated is put into a high-temperature furnace, the material is heated to 650-750 ℃ at a heating rate of 10 ℃/min.
9. The aging treatment method for a high-temperature alloy for a turbine disk according to claim 1 or 2, wherein: the temperature is kept stable after the temperature is raised to the range of 650-750 ℃, wherein the temperature fluctuation is within +/-1.0 ℃.
10. The aging treatment method for a high-temperature alloy for a turbine disk according to claim 1 or 2, wherein: the material to be treated is GH2132 iron-based high-temperature alloy, and comprises the following main components in percentage by mass: less than or equal to 0.08 percent of carbon, 13.5 to 16.0 percent of chromium, 24.0 to 27.0 percent of nickel, 1.0 to 1.5 percent of molybdenum, 1.9 to 2.35 percent of titanium, 0.1 to 0.5 percent of vanadium, 0.003 to 0.01 percent of boron, less than or equal to 0.35 percent of silicon, less than or equal to 0.35 percent of manganese, less than or equal to 0.015 percent of phosphorus, less than or equal to 0.002 percent of sulfur, less than or equal to 0.35 percent of aluminum, and the balance of iron.
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| CN202011250214.6A CN112375880A (en) | 2020-11-10 | 2020-11-10 | Aging treatment method for high-temperature alloy for turbine disk |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114686662A (en) * | 2022-03-28 | 2022-07-01 | 江西宝顺昌特种合金制造有限公司 | GH2132 high-temperature alloy and heat treatment method for improving hardness of GH2132 high-temperature alloy |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5370838A (en) * | 1993-12-07 | 1994-12-06 | Hitachi Metals, Ltd. | Fe-base superalloy |
| JP2000273597A (en) * | 1999-03-19 | 2000-10-03 | Japan Steel Works Ltd:The | MANUFACTURE OF PRECIPITATION STRENGTHENING TYPE Ni-Fe- BASE SUPERALLOY |
| US20070169860A1 (en) * | 2006-01-25 | 2007-07-26 | General Electric Company | Local heat treatment for improved fatigue resistance in turbine components |
| CN104775043A (en) * | 2014-10-28 | 2015-07-15 | 中国航空工业集团公司北京航空材料研究院 | GH742y alloy turbine disk blank preparation method |
| CN105734241A (en) * | 2016-03-18 | 2016-07-06 | 贵州航天精工制造有限公司 | Heat treatment method for improving high-temperature endurance property of GH2132 bolt |
| CN107201431A (en) * | 2016-03-18 | 2017-09-26 | 贵州航天精工制造有限公司 | A kind of aging treatment method of raising GH2132 bolt high temperature endurance performances |
| CN110408846A (en) * | 2019-08-30 | 2019-11-05 | 贵州航天新力铸锻有限责任公司 | A kind of aerospace big specification high-tenacity GH2132 bar and preparation method thereof |
| CN110592507A (en) * | 2019-10-30 | 2019-12-20 | 成都先进金属材料产业技术研究院有限公司 | Test method for high-temperature aging treatment of nickel-based alloy |
-
2020
- 2020-11-10 CN CN202011250214.6A patent/CN112375880A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5370838A (en) * | 1993-12-07 | 1994-12-06 | Hitachi Metals, Ltd. | Fe-base superalloy |
| JP2000273597A (en) * | 1999-03-19 | 2000-10-03 | Japan Steel Works Ltd:The | MANUFACTURE OF PRECIPITATION STRENGTHENING TYPE Ni-Fe- BASE SUPERALLOY |
| US20070169860A1 (en) * | 2006-01-25 | 2007-07-26 | General Electric Company | Local heat treatment for improved fatigue resistance in turbine components |
| CN104775043A (en) * | 2014-10-28 | 2015-07-15 | 中国航空工业集团公司北京航空材料研究院 | GH742y alloy turbine disk blank preparation method |
| CN105734241A (en) * | 2016-03-18 | 2016-07-06 | 贵州航天精工制造有限公司 | Heat treatment method for improving high-temperature endurance property of GH2132 bolt |
| CN107201431A (en) * | 2016-03-18 | 2017-09-26 | 贵州航天精工制造有限公司 | A kind of aging treatment method of raising GH2132 bolt high temperature endurance performances |
| CN110408846A (en) * | 2019-08-30 | 2019-11-05 | 贵州航天新力铸锻有限责任公司 | A kind of aerospace big specification high-tenacity GH2132 bar and preparation method thereof |
| CN110592507A (en) * | 2019-10-30 | 2019-12-20 | 成都先进金属材料产业技术研究院有限公司 | Test method for high-temperature aging treatment of nickel-based alloy |
Non-Patent Citations (3)
| Title |
|---|
| 李园春等: "国内粉末高温合金涡轮盘件制造技术的发展现状", 《稀有金属》 * |
| 胡隆伟 等: "《紧固件材料手册》", 31 December 2014, 中国宇航出版社 * |
| 邰清安等: "热处理制度对GH2132合金组织性能的影响", 《材料热处理学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114686662A (en) * | 2022-03-28 | 2022-07-01 | 江西宝顺昌特种合金制造有限公司 | GH2132 high-temperature alloy and heat treatment method for improving hardness of GH2132 high-temperature alloy |
| CN114686662B (en) * | 2022-03-28 | 2023-09-19 | 江西宝顺昌特种合金制造有限公司 | GH2132 high-temperature alloy and heat treatment method for improving hardness of GH2132 high-temperature alloy |
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Application publication date: 20210219 |