CN104789817B - Engine turbine ODS high-temperature alloy material and preparation method thereof - Google Patents
Engine turbine ODS high-temperature alloy material and preparation method thereof Download PDFInfo
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Abstract
nullThe present invention relates to engine turbine ODS 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%，Co:6.7 8.2%，Zr:0.12 0.18%，Nb:1.12 1.38%，Composite oxides Y Ti O nano particle: 1.2 2.8%，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 meets standard-required，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 ODS high-temperature alloy material adding composite oxides nano particle and preparation method thereof.
Background technology
High temperature alloy refers to iron, 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, anti-oxidant and corrosion resistance, there is good structure stability and dependability, also known as the strong alloy of heat and heat endurance 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 engine, parts often to be aoxidized and various corrosion, it is therefore desirable to the material used to have the anti-oxidant and 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, communications and transportation, petrochemical industry, mine metallurgy, glass building material, paper-making pulping and seawater operation, oneself becomes one of outstanding feature weighing a national metal material development level.
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.
Oxide dispersion intensifying (Oxide Dispersion Strengthened, ODS) high temperature alloy be by tiny oxide particle Dispersed precipitate in matrix alloy, realize a kind of powder metallurgy superalloy of dispersion-strengtherning, be an important development direction of high temperature alloy.Conventional oxide is the oxide of active metal, such as Y2O3、ThO2Deng, they have high rigidity and good heat endurance and chemical stability, and its strengthening effect can maintain close to alloy melting point temperature (0.9Tm), and these ultra-fine oxides are the optimal disperse phase strengthening matrix under high temperature.
Summary of the invention
It is an object of the invention to provide engine turbine and add the ODS high-temperature alloy material of composite oxides nano particleAnd 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.
nullFor reaching this purpose，The present invention is by the following technical solutions: a kind of engine turbine adds the ODS high-temperature alloy material of composite oxides nano particle，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%，Co:6.7-8.2%，Zr:0.12-0.18%，Nb:1.12-1.38%，Composite oxides Y-Ti-O nano particle: 1.2-2.8%，Surplus is Ni and inevitable impurity.
Further, described composite oxides Y-Ti-O nano particle is Y2Ti2O7 and/or Y2TiO5 nano particle, and nano particle size is 10-100nm.
Further, the manufacture method of above-mentioned engine turbine high-temperature alloy material, comprise the following steps:
(1) raw material prepares: by calculating, alloying component in addition to composite oxides Y-Ti-O nano particle in the ODS high-temperature alloy material adding composite oxides nano particle described in claim 1 is carried out dispensing;
(2) smelting electrode rod, carries out Melting control vacuum 0.05-0.2Pa by raw material, and raw material keeps monitor system constant 35-40 minute after all melting；Improving vacuum to 0.001-0.01Pa, refine 10-15 minute at 1620 DEG C-1640 DEG C, adjusting component complies with requirement, then adjusts to 1530-1580 DEG C and pours 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) ESR ingot is made superalloy powder；
(5) superalloy powder that composite oxides Y-Ti-O nano particle and step 4 prepare is carried out ball milling, prepare ODS superalloy powder；Ball milling condition: under argon gas atmosphere is protected, with the speed ball milling of 750～1200 turns per minute, Ball-milling Time 48-120 hour, ball-milling medium: stainless steel ball, ratio of grinding media to material is 5:1～20:1.
(6) high temperature insostatic pressing (HIP) prepares block ODS high temperature alloy, is first loaded in jacket by prepared ODS superalloy powder, carries out soldering and sealing process after vacuumizing jacket, arranges vacuum less than 10- 3Pa；Then will be equipped with the jacket of ODS superalloy powder to put into hot isostatic apparatus carries out hot-pressing processing, obtain block ODS high temperature alloy；Heat and other static pressuring processes condition: temperature is 900 DEG C～1300 DEG C, and pressure is 100～200MPa, processes time 1～4 hours；
(7) it is heat-treated: the blank preparing (6th) step carries out solution treatment, blank heating to 1100-1200 DEG C 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.
The blank prepared by said method is more than 820MPa the tensile strength of 1000 DEG C, and yield strength is more than 660MPa, 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%, Co:6.81%, Zr:0.16%, Nb:1.21%, Y2Ti2O7 nano particle: 1.35%, 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: by calculating, alloying component in addition to composite oxides Y-Ti-O nano particle in the above-mentioned ODS high-temperature alloy material adding composite oxides nano particle is carried out dispensing;
(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；Improving vacuum to 0.008Pa, refine 12 minutes at 1635 DEG C, adjusting component complies with requirement, then adjusts to 1555 DEG C and pours 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) ESR ingot is made superalloy powder；
(5) superalloy powder that composite oxides Y-Ti-O nano particle and step 4 prepare is carried out ball milling, prepare ODS superalloy powder；Ball milling condition: under argon gas atmosphere is protected, with the speed ball milling of 850 turns per minute, Ball-milling Time 90 hours, ball-milling medium: stainless steel ball, ratio of grinding media to material is 10:1；
(6) high temperature insostatic pressing (HIP) prepares block ODS high temperature alloy, is first loaded in jacket by prepared ODS superalloy powder, carries out soldering and sealing process after vacuumizing jacket, arranges vacuum less than 10- 3Pa；Then will be equipped with the jacket of ODS superalloy powder to put into hot isostatic apparatus carries out hot-pressing processing, obtain block ODS high temperature alloy；Heat and other static pressuring processes condition: temperature is 1050 DEG C, pressure is 180MPa, processes 3 hours time；
(7) it is heat-treated: the blank preparing (6th) step carries out solution treatment, blank heating to 1150 DEG C 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 825MPa the tensile strength of 1000 DEG C, and yield strength is 665MPa, and elongation percentage is 22%.
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 meets standard-required, production efficiency is high, and economic benefit and social benefit are notable.
Claims (3)
- null1. the engine turbine ODS high-temperature alloy material adding composite oxides nano particle，It is characterized in that: 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%，Co:6.7-8.2%，Zr:0.12-0.18%，Nb:1.12-1.38%，Composite oxides Y-Ti-O nano particle: 1.2-2.8%，Surplus is Ni and inevitable impurity.
- 2. the engine turbine ODS high-temperature alloy material adding composite oxides nano particle as claimed in claim 1, it is characterised in that: described composite oxides Y-Ti-O nano particle is Y2Ti2O7And/or Y2TiO5Nano particle, nano particle size is 10-100nm.
- The manufacture method of engine turbine high-temperature alloy material the most according to claim 1 and 2, it is characterised in that comprise the following steps:(1) raw material prepares: by calculating, alloying component in addition to composite oxides Y-Ti-O nano particle in the ODS high-temperature alloy material adding composite oxides nano particle described in claim 1 is carried out dispensing;(2) smelting electrode rod, carries out Melting control vacuum 0.05-0.2Pa by raw material, and raw material keeps monitor system constant 35-40 minute after all melting；Improving vacuum to 0.001-0.01Pa, refine 10-15 minute at 1620 DEG C-1640 DEG C, adjusting component complies with requirement, then adjusts to 1530-1580 DEG C and pours 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%, in slag charge, the percentage by weight sum of each component is 100%, above-mentioned slag charge is heated to molten condition, pour in crystallizer, crystallizer and base plate are all water-cooled, the consutrode rod of preparation in step (2) is slowly declined in the slag charge of electroslag remelting melted, after the energising starting the arc, adjusts 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) ESR ingot is made superalloy powder；(5) superalloy powder that composite oxides Y-Ti-O nano particle and step (4) prepare is carried out ball milling, prepare ODS superalloy powder；Ball milling condition: under argon gas atmosphere is protected, with the speed ball milling of 750～1200 turns per minute, Ball-milling Time 48-120 hour, ball-milling medium: stainless steel ball, ratio of grinding media to material is 5:1～20:1；(6) high temperature insostatic pressing (HIP) prepares block ODS high temperature alloy, is first loaded in jacket by prepared ODS superalloy powder, carries out soldering and sealing process after vacuumizing jacket, arranges vacuum less than 10- 3Pa；Then will be equipped with the jacket of ODS superalloy powder to put into hot isostatic apparatus carries out hot-pressing processing, obtain block ODS high temperature alloy；Heat and other static pressuring processes condition: temperature is 900 DEG C～1300 DEG C, and pressure is 100～200MPa, processes time 1～4 hours；(7) it is heat-treated: the blank preparing (6th) step carries out solution treatment, blank heating to 1100-1200 DEG C 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.
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| CN106676363A (en) * | 2016-12-14 | 2017-05-17 | 张家港市广大机械锻造有限公司 | Novel high-temperature alloy casting production process |
| CN110695360B (en) * | 2019-10-30 | 2022-04-12 | 西安欧中材料科技有限公司 | Method for preparing functionally gradient high-temperature alloy turbine disc |
| CN110983110B (en) * | 2019-12-26 | 2020-10-13 | 南京工程学院 | High-fluidity high-temperature alloy and preparation method thereof |
| TWI732654B (en) * | 2020-08-13 | 2021-07-01 | 國家中山科學研究院 | Methods to improve the stress rupture life of nickel-based super alloys |
| CN112250102A (en) * | 2020-10-27 | 2021-01-22 | 航天特种材料及工艺技术研究所 | Y2Ti2O7Composite nano-particles and preparation method and application thereof |
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| JP2013181213A (en) * | 2012-03-01 | 2013-09-12 | Hokkaido Univ | Oxide dispersion strengthening type nickel-based superalloy |
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