CN104862533B - engine turbine high-temperature alloy material and preparation method thereof - Google Patents
engine turbine high-temperature alloy material and preparation method thereof Download PDFInfo
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Abstract
nullThe present invention relates to a kind of engine turbine high-temperature alloy material，The composition of described high-temperature alloy material includes by weight percentage: C:0.22 0.28%，Mn:2.1 2.2%，Si:0.45 0.61%，Cr:18.3 19.2%，Mo:8.25 10.4%，W:3.50 3.80%，Al:0.05 0.35%，Cu:0.18 0.27%，Fe:5.0 9.2%，B:1.0‑1.1%，Ti:3.15‑3.45%，Co:6.7 8.2%，Zr:0.12 0.18%，Nb:1.12 1.38%，Surplus is Ni and inevitable impurity，And provide the preparation method matched with this material，The batch components of preparation is reasonable in design，Coordinate rational heat processing technique、Organization of production is convenient、On-the-spot workable、The feature of equipment highly versatile，The high temperature alloy large-scale turbine disk product quality produced is high，Structure property conformance with standard requirement，Production efficiency is high，Economic benefit and social benefit are notable.
Description
Technical field
The invention belongs to high temperature alloy field, be specially a kind of high temperature alloy and preparation method thereof, be primarily adapted for use in engine turbine high-temperature alloy material and preparation method thereof.
Background technology
High temperature alloy refers to ferrum, brill, nickel as base, can be on active service and the metalloid material developed under 600 DEG C of high temperature above.High temperature alloy is single austenitic matrix tissue, have higher elevated temperature strength, antioxidation and corrosion resistance, there is good structure stability and dependability, also known as the strong alloy of heat and heat stability high temperature alloy, the most often referred to as superalloy (Superalloy).
High temperature alloy can have different sorting techniques according to alloying component, tissue and moulding process are different.Classify by matrix element, mainly have nickel base superalloy, cobalt-base superalloy and iron-base superalloy, additionally Ling Youyige branch nickel one iron-base superalloy.Divide by preparation technology, wrought superalloy, cast superalloy and powder metallurgy superalloy can be divided into.Solid solution strengthened alloy and aging precipitation enhanced type alloy, different enhanced type alloys can be divided into have different heat treating regimes by schedule of reinforcement classification.
The motive force of development of high temperature alloy derives from the needs of high-temperature fuel gas turbine, gas turbine engine, especially aeroengine thrust and efficiency growing, improving constantly of engine operating temperature, and this just requires that material must possess a higher resistance to temperature ability.In the running of electromotor, parts often to be aoxidized and various corrosion, it is therefore desirable to the material used to have antioxidation and the corrosion and heat resistant ability of excellence.Along with smelting, process, the progress of the Technology such as protection, vigorous growth and application period have been stepped in the research of high temperature alloy and application.Utilize high temperature alloy high-intensity performance, high-temperature wearable and decay resistance, high temperature alloy is in addition to applying in Aeronautics and Astronautics field at present, also being widely used in the fields such as atomic energy, energy source and power, transportation, petrochemical industry, mine metallurgy, glass building material, paper-making pulping and sea water operation, oneself becomes one of outstanding feature weighing a national metal material level of development.
The development of high temperature alloy is closely related with the progress of aero-engine.From the later stage thirties 20th century, the country such as English, moral, U.S. begins to researching high-temperature alloy.The development of the development of aero-engine and high temperature alloy advances side by side, inseparable, the former is the major impetus of the latter, and the latter is the former important guarantee.In aero-engine, temperature is the highest, and the casting turbo blade alloy development of the position that stress is the most complicated is the most so.The beginning of the forties, in Britain due to the appearance of Whittle jet engine at that time, it is desirable to sheet material more more preferable than austenitic stainless steel croop property and bar.Mond company of Britain produces and adds the Nimonic75 alloy having lacked C and Ti (Xian Cheng International nickel Co. Ltd. Inco. Ltd.) nineteen forty-one, it is used as the blade material used in short-term, added Al later and increased Ti content, soon Nimonic80 alloy has been developed, and the blade material of turbojet it is used successfully as in nineteen forty-two, this be develop the earliest with Ni:(Al, Ti) the turbo blade material strengthened.Hereafter the said firm adds B the most in the alloy, and adjusts Al, Ti content, succeeds in developing Nimonic80A alloy, for improving creep and enduring quality further, with C.Substitute part Ni in matrix, developed Nimonic90 alloy, add again Mo and obtain the alloys such as Nimoniel00, form Nimonie system.
From the beginning of China successfully melted out the first stove GH4030 alloy from 1956, eighties of last century have developed GH4037, K406 etc. the sixties in succession.By the development of nearly 60 years, the development of antioxidant high temperature alloy and exploitation currently mainly concentrated on Ni-based or iron-base superalloy.The course of its development is in line with international standards, i.e. defers to deforming alloy, casting alloy and the road for development of oriented monocrystalline alloy, makes China become the 4th country forming independent high temperature alloy system in the world after the U.S. and Russia, English.
As fixing blade and the core component that connects blade and turbine wheel shaft, reliability and the serviceability of the turbine disk are most important, and this just production to the turbine disk, especially hot-working proposes high requirement.For putting forward heavy alloyed temperature capability, use at present and reduce Cr, raising refractory element total amount (W, Nb, Ta, Re, Mo etc.) and the alloy design method of precipitation phase γ ' content.Along with the alloying level of the turbine disk improves constantly, serious segregation makes hot-working character deteriorate, and low cycle fatigue property reduces, and fatigue crack easily extends.
Summary of the invention
It is an object of the invention to provide a kind of high temperature alloy and preparation method thereof, there is the processability of excellence and high temperature capability, the aero-engine needs to turbine disk material can be met.
The complete one of technical scheme, each parameter is all to control through strict so that product quality is guaranteed.
For reaching this purpose, the present invention is by the following technical solutions: a kind of engine turbine high-temperature alloy material, the composition of described high-temperature alloy material includes by weight percentage: C:0.22-0.28%, Mn:2.1-2.2%, Si:0.45-0.61%, Cr:18.3-19.2%, Mo:8.25-10.4%, W:3.50-3.80%, Al:0.05-0.35%, Cu:0.18-0.27%, Fe:5.0-9.2%, B:1.0-1.1%, Ti:3.15-3.45%, Co:6.7-8.2%, Zr:0.12-0.18%, Nb:1.12-1.38%, surplus is Ni and inevitable impurity.
Further, it is provided that the manufacture method of a kind of above-mentioned engine turbine high-temperature alloy material, comprise the following steps:
(1) raw material prepares: carry out dispensing by above-mentioned alloying component;
(2) smelting electrode rod, carries out melting by raw material, controls vacuum 0.05-0.2Pa, and raw material keeps monitor system constant 35-40 minute after all melting；Improve vacuum to 0.001-0.01Pa, 1620 DEG C of-1640 DEG C of refines 10-15 minute, adjusting component complied with requirement, then adjust to 1530-1580 DEG C pour into consutrode rod；
(3) electroslag remelting: the slag charge proportioning of electroslag remelting is by weight: CaF2:45-55%, Al2O3:18-23%；CaO:15.5-18%；SiO2:16.5-19.2%, above-mentioned slag charge is heated to molten condition, pour in crystallizer, crystallizer and base plate are all water-cooled, in in step 2, the consutrode rod of preparation is slowly declined to the slag charge of electroslag remelting melted, after the energising starting the arc, adjustment remelting voltage to 35-65V, electric current 3000-8000A；Consutrode rod is slowly melted by resistance heat, and the consutrode rod drop after fusing reacts with slag charge through melted slag material layer and purified, and recrystallizes in the bottom of crystallizer, obtains dense structure, uniform, pure, the ESR ingot of any surface finish；
(4) forging: the heating furnace that ESR ingot is put into initial temperature 450-480 DEG C heats, is warming up to 1100-1230 DEG C, again at 1000-1050 DEG C after insulation 3-4h, is incubated 10-20h, then forges, be forged into alloy preform, be cooled to room temperature；
(5) hot rolling: be heated to 1000 DEG C-1035 DEG C and carry out hot rolling, is cooled to room temperature in atmosphere after hot rolling；
(6) heat treatment: the blank after hot rolling is carried out solution treatment, hot rolling blank is heated to 1100-1200 DEG C and is incubated 9-12 hour, then air cooling is carried out, carry out progressive aging process the most again: first stage Ageing Treatment: put into by blank in heat-treatment heater, isothermal holding is carried out to 900-1000 DEG C by room temperature, temperature retention time is 12-28h, it is cooled to 720-800 DEG C with 30 DEG C/min and carries out second stage Ageing Treatment: 720-800 DEG C of temperature retention time 24-36h, it is cooled to 650-700 DEG C with 20 DEG C/min and carries out phase III Ageing Treatment: be incubated 10-12h at 650-700 DEG C, finally by blank air cooling to room temperature.
Further, the composition of described high-temperature alloy material includes by weight percentage: C:0.24-0.256%, Mn:2.15-2.18%, Si:0.48-0.59%, Cr:18.45-19.15%, Mo:9.15-10.05%, W:3.65-3.78%, Al:0.18-0.32%, Cu:0.21-0.245%, Fe:5.8-8.2%, B:1.05-1.08%, Ti:3.22-3.43%, Co:6.93-7.98%, Zr:0.14-0.16%, Nb:1.18-1.31%, surplus is Ni and inevitable impurity.
Further, it is provided that the manufacture method of a kind of above-mentioned engine turbine high-temperature alloy material, comprise the following steps:
(1) raw material prepares: carry out dispensing by above-mentioned alloying component;
(2) smelting electrode rod, carries out melting by raw material, controls vacuum 0.07Pa, and raw material keeps monitor system constant 38 minutes after all melting；Improve vacuum to 0.008Pa, 1630 DEG C of refines 12 minutes, adjusting component complied with requirement, then adjust to 1550 DEG C pour into consutrode rod；
(3) electroslag remelting: the slag charge proportioning of electroslag remelting is by weight: CaF2:46.6%, Al2O3:20.2%；CaO:15.8%；SiO2:17.4%, is heated to molten condition by above-mentioned slag charge, pours in crystallizer, crystallizer and base plate are all water-cooled, in the consutrode rod of preparation is slowly declined to the slag charge of electroslag remelting melted in step 2, after the energising starting the arc, adjust remelting voltage to 40V, electric current 4500A；Consutrode rod is slowly melted by resistance heat, and the consutrode rod drop after fusing reacts with slag charge through melted slag material layer and purified, and recrystallizes in the bottom of crystallizer, obtains dense structure, uniform, pure, the ESR ingot of any surface finish；
(4) forging: the heating furnace that ESR ingot is put into initial temperature 465 DEG C heats, is warming up to 1175 DEG C, again at 1025 DEG C after insulation 3.5h, is incubated 12h, then forges, be forged into alloy preform, be cooled to room temperature；
(5) hot rolling: be heated to 1020 DEG C and carry out hot rolling, is cooled to room temperature in atmosphere after hot rolling；
(6) heat treatment: the blank after hot rolling is carried out solution treatment, hot rolling blank is heated to 1150 DEG C and is incubated 10 hours, then air cooling is carried out, carry out progressive aging process the most again: first stage Ageing Treatment: put into by blank in heat-treatment heater, isothermal holding is carried out by room temperature to 950 DEG C, temperature retention time is 15h, it is cooled to 760 DEG C with 30 DEG C/min and carries out second stage Ageing Treatment: 760 DEG C of temperature retention times 30h, it is cooled to 670 DEG C with 20 DEG C/min and carries out phase III Ageing Treatment: be incubated 11h at 670 DEG C, finally by blank air cooling to room temperature.
The blank prepared by said method is more than 800MPa the tensile strength of 1000 DEG C, and yield strength is more than 650MPa, and elongation percentage is more than 20%.
Effect of the invention is that:
The high-temperature alloy material of the present invention, has excellent processability and excellent high-temperature behavior, especially has the room temperature of excellence to high temperature tensile strength, and structure stability is good, and enduring quality is suitable with high-performance casting forging high temperature alloy TMW.Simultaneously by specific parameter optimization, technique coordinates, it is provided that preparation method reliably, produces satisfactory product, meanwhile, greatly improves product quality and yield rate, reduce production cost, create great economic benefit.Follow-up slightly complicated Technology for Heating Processing so that the quality of foundry goods and performance obtain stronger guarantee.
Detailed description of the invention
Embodiment
1
A kind of engine turbine high-temperature alloy material, the composition of described high-temperature alloy material includes by weight percentage: C:0.265%, Mn:2.18%, Si:0.54%, Cr:18.7%, Mo:9.3%, W:3.68%, Al:0.28%, Cu:0.21%, Fe:6.5%, B:1.05%, Ti:3.33%, Co:6.81%, Zr:0.16%, Nb:1.21%, surplus is Ni and inevitable impurity, the manufacture method of described engine turbine high-temperature alloy material, comprises the following steps:
(1) raw material prepares: carry out dispensing by above-mentioned alloying component;
(2) smelting electrode rod, carries out Melting control vacuum 0.1Pa by raw material, and raw material keeps monitor system constant 37 minutes after all melting；Improve vacuum to 0.008Pa, 1635 DEG C of refines 12 minutes, adjusting component complied with requirement, then adjust to 1555 DEG C pour into consutrode rod；
(3) electroslag remelting: the slag charge proportioning of electroslag remelting is by weight: CaF2:47.1%, Al2O3:20.0%；CaO:16.2%；SiO2:16.7%, is heated to molten condition by above-mentioned slag charge, pours in crystallizer, crystallizer and base plate are all water-cooled, in the consutrode rod of preparation is slowly declined to the slag charge of electroslag remelting melted in step 2, after the energising starting the arc, adjust remelting voltage to 40V, electric current 4000A；Consutrode rod is slowly melted by resistance heat, and the consutrode rod drop after fusing reacts with slag charge through melted slag material layer and purified, and recrystallizes in the bottom of crystallizer, obtains dense structure, uniform, pure, the ESR ingot of any surface finish；
(4) forging: the heating furnace that ESR ingot is put into initial temperature 465 DEG C heats, is warming up to 1200 DEG C, again at 1025 DEG C after insulation 3.5h, is incubated 15h, then forges, be forged into alloy preform, be cooled to room temperature；
(5) hot rolling: be heated to 1020 DEG C and carry out hot rolling, is cooled to room temperature in atmosphere after hot rolling；
(6) heat treatment: the blank after hot rolling is carried out solution treatment, hot rolling blank is heated to 1150 DEG C and is incubated 11 hours, then air cooling is carried out, carry out progressive aging process the most again: first stage Ageing Treatment: put into by blank in heat-treatment heater, isothermal holding is carried out by room temperature to 950 DEG C, temperature retention time is 15h, it is cooled to 730 DEG C with 30 DEG C/min and carries out second stage Ageing Treatment: 730 DEG C of temperature retention times 15h, it is cooled to 660 DEG C with 20 DEG C/min and carries out phase III Ageing Treatment: be incubated 11h at 660 DEG C, finally by blank air cooling to room temperature.
The blank prepared by said method is 805MPa the tensile strength of 1000 DEG C, and yield strength is 665MPa, and elongation percentage is 23%.
It is reasonable in design that the present invention has composition, coordinate rational heat processing technique, organization of production workable, the feature of equipment highly versatile convenient, on-the-spot, the high temperature alloy large-scale turbine disk product quality produced is high, structure property conformance with standard requirement, production efficiency is high, and economic benefit and social benefit are notable.
Claims (3)
1. the manufacture method of an engine turbine high-temperature alloy material, it is characterised in that comprise the following steps:
(1) raw material prepares: carry out dispensing by high temperature alloy composition, the composition of described high-temperature alloy material includes by weight percentage: C:0.22-0.28%, Mn:2.1-2.2%, Si:0.45-0.61%, Cr:18.3-19.2%, Mo:8.25-10.4%, W:3.50-3.80%, Al:0.05-0.35%, Cu:0.18-0.27%, Fe:5.0-9.2%, B:1.0-1.1%, Ti:3.15-3.45%, Co:6.7-8.2%, Zr:0.12-0.18%, Nb:1.12-1.38%, surplus is Ni and inevitable impurity；
(2) smelting electrode rod, carries out melting by raw material, controls vacuum 0.05-0.2Pa, and raw material keeps monitor system constant 35-40 minute after all melting；Improve vacuum to 0.001-0.01Pa, 1620 DEG C of-1640 DEG C of refines 10-15 minute, adjusting component complied with requirement, then adjust to 1530-1580 DEG C pour into consutrode rod；
(3) electroslag remelting: the slag charge proportioning of electroslag remelting is by weight percentage: CaF2: 45-55%, Al2O3: 18-23%；CaO:15.5-18%；SiO2: 16.5-19.2%, in described slag charge, each component sum is 100%, above-mentioned slag charge is heated to molten condition, pour in crystallizer, crystallizer and base plate are all water-cooled, in the consutrode rod of preparation is slowly declined to the slag charge of electroslag remelting melted in step 2, after the energising starting the arc, adjust remelting voltage to 35-65V, electric current 3000-8000A；Consutrode rod is slowly melted by resistance heat, and the consutrode rod drop after fusing reacts with slag charge through melted slag material layer and purified, and recrystallizes in the bottom of crystallizer, obtains dense structure, uniform, pure, the ESR ingot of any surface finish；
(4) forging: the heating furnace that ESR ingot is put into initial temperature 450-480 DEG C heats, is warming up to 1100-1230 DEG C, again at 1000-1050 DEG C after insulation 3-4h, is incubated 10-20h, then forges, be forged into alloy preform, be cooled to room temperature；
(5) hot rolling: be heated to 1000 DEG C-1035 DEG C and carry out hot rolling, is cooled to room temperature in atmosphere after hot rolling；
(6) heat treatment: the blank after hot rolling is carried out solution treatment, hot rolling blank is heated to 1100-1200 DEG C and is incubated 9-12 hour, then air cooling is carried out, carry out progressive aging process the most again: first stage Ageing Treatment: put into by blank in heat-treatment heater, isothermal holding is carried out to 900-1000 DEG C by room temperature, temperature retention time is 12-28h, it is cooled to 720-800 DEG C with 30 DEG C/min and carries out second stage Ageing Treatment: 720-800 DEG C of temperature retention time 24-36h, it is cooled to 650-700 DEG C with 20 DEG C/min and carries out phase III Ageing Treatment: be incubated 10-12h at 650-700 DEG C, finally by blank air cooling to room temperature.
2. the manufacture method of high-temperature alloy material as claimed in claim 1, it is characterised in that: C:0.24-0.256%, Mn:2.15-2.18%, Si:0.48-0.59%, Cr:18.45-19.15%, Mo:9.15-10.05%, W:3.65-3.78%, Al:0.18-0.32%, Cu:0.21-0.245%, Fe:5.8-8.2%, B:1.05-1.08%, Ti:3.22-3.43%, Co:6.93-7.98%, Zr:0.14-0.16%, Nb:1.18-1.31%, surplus is Ni and inevitable impurity.
The manufacture method of engine turbine high-temperature alloy material the most according to claim 2, it is characterised in that comprise the following steps:
(1) raw material prepares: carry out dispensing by above-mentioned alloying component;
(2) smelting electrode rod, carries out melting by raw material, controls vacuum 0.07Pa, and raw material keeps monitor system constant 38 minutes after all melting；Improve vacuum to 0.008Pa, 1630 DEG C of refines 12 minutes, adjusting component complied with requirement, then adjust to 1550 DEG C pour into consutrode rod；
(3) electroslag remelting: the slag charge proportioning of electroslag remelting is by weight percentage: CaF2: 46.6%, Al2O3: 20.2%；CaO:15.8%；SiO2: 17.4%, above-mentioned slag charge is heated to molten condition, pours in crystallizer, crystallizer and base plate are all water-cooled, in the consutrode rod of preparation is slowly declined to the slag charge of electroslag remelting melted in step 2, after the energising starting the arc, adjust remelting voltage to 40V, electric current 4500A；Consutrode rod is slowly melted by resistance heat, and the consutrode rod drop after fusing reacts with slag charge through melted slag material layer and purified, and recrystallizes in the bottom of crystallizer, obtains dense structure, uniform, pure, the ESR ingot of any surface finish；
(4) forging: the heating furnace that ESR ingot is put into initial temperature 465 DEG C heats, is warming up to 1175 DEG C, again at 1025 DEG C after insulation 3.5h, is incubated 12h, then forges, be forged into alloy preform, be cooled to room temperature；
(5) hot rolling: be heated to 1020 DEG C and carry out hot rolling, is cooled to room temperature in atmosphere after hot rolling；
(6) heat treatment: the blank after hot rolling is carried out solution treatment, hot rolling blank is heated to 1150 DEG C and is incubated 10 hours, then air cooling is carried out, carry out progressive aging process the most again: first stage Ageing Treatment: put into by blank in heat-treatment heater, isothermal holding is carried out by room temperature to 950 DEG C, temperature retention time is 15h, it is cooled to 760 DEG C with 30 DEG C/min and carries out second stage Ageing Treatment: 760 DEG C of temperature retention times 30h, it is cooled to 670 DEG C with 20 DEG C/min and carries out phase III Ageing Treatment: be incubated 11h at 670 DEG C, finally by blank air cooling to room temperature.
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| CN108165708A (en) * | 2017-12-27 | 2018-06-15 | 大连透平机械技术发展有限公司 | The heat treatment method of 25Cr2Ni3Mo materials |
| CN111074100A (en) * | 2019-12-31 | 2020-04-28 | 江苏新华合金有限公司 | Nickel-based high-temperature alloy bar and preparation method thereof |
| CN111378873B (en) * | 2020-04-23 | 2021-03-23 | 北京钢研高纳科技股份有限公司 | Deformed high-temperature alloy, preparation method thereof, hot-end rotating part of engine and engine |
| CN112708788B (en) * | 2020-11-18 | 2022-06-17 | 北京钢研高纳科技股份有限公司 | Method for improving plasticity of K403 alloy, die material and product |
| CN112522545B (en) * | 2020-11-27 | 2021-12-14 | 成都先进金属材料产业技术研究院股份有限公司 | Nickel-chromium high-resistance electrothermal alloy |
| CN113430392B (en) * | 2021-06-18 | 2022-07-01 | 山西太钢不锈钢股份有限公司 | Efficient arc striking method for large-end-face electrode blank for electroslag smelting |
| CN113846247A (en) * | 2021-09-24 | 2021-12-28 | 成都先进金属材料产业技术研究院股份有限公司 | W-Mo-Co reinforced high-temperature alloy hot-rolled bar and preparation method thereof |
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| US20060051234A1 (en) * | 2004-09-03 | 2006-03-09 | Pike Lee M Jr | Ni-Cr-Co alloy for advanced gas turbine engines |
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