CN105714159A - Fuselage alloy - Google Patents
Fuselage alloy Download PDFInfo
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- CN105714159A CN105714159A CN201610295926.7A CN201610295926A CN105714159A CN 105714159 A CN105714159 A CN 105714159A CN 201610295926 A CN201610295926 A CN 201610295926A CN 105714159 A CN105714159 A CN 105714159A
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- 239000000956 alloy Substances 0.000 title claims abstract description 126
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 80
- 229910052692 Dysprosium Inorganic materials 0.000 claims description 28
- 229910052804 chromium Inorganic materials 0.000 claims description 28
- 229910052759 nickel Inorganic materials 0.000 claims description 28
- 229910052691 Erbium Inorganic materials 0.000 claims description 27
- 229910052693 Europium Inorganic materials 0.000 claims description 27
- 229910052689 Holmium Inorganic materials 0.000 claims description 27
- 229910052802 copper Inorganic materials 0.000 claims description 27
- 229910052745 lead Inorganic materials 0.000 claims description 27
- 229910052727 yttrium Inorganic materials 0.000 claims description 27
- 229910052719 titanium Inorganic materials 0.000 claims description 26
- 238000002360 preparation method Methods 0.000 claims description 25
- 238000010304 firing Methods 0.000 claims description 24
- 210000001161 mammalian embryo Anatomy 0.000 claims description 24
- 239000000463 material Substances 0.000 claims description 24
- 229910052782 aluminium Inorganic materials 0.000 claims description 16
- 229910052744 lithium Inorganic materials 0.000 claims description 16
- 238000005496 tempering Methods 0.000 claims description 15
- 229910052771 Terbium Inorganic materials 0.000 claims description 14
- 229910052746 lanthanum Inorganic materials 0.000 claims description 14
- 229910052718 tin Inorganic materials 0.000 claims description 14
- 229910052725 zinc Inorganic materials 0.000 claims description 14
- 229910052748 manganese Inorganic materials 0.000 claims description 13
- 239000002994 raw material Substances 0.000 claims description 13
- 238000000265 homogenisation Methods 0.000 claims description 12
- 238000009413 insulation Methods 0.000 claims description 12
- 239000007788 liquid Substances 0.000 claims description 12
- 239000000155 melt Substances 0.000 claims description 12
- 229910052751 metal Inorganic materials 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 12
- 238000003756 stirring Methods 0.000 claims description 12
- 238000002844 melting Methods 0.000 claims description 3
- 230000008018 melting Effects 0.000 claims description 3
- 239000002826 coolant Substances 0.000 claims description 2
- 238000001816 cooling Methods 0.000 claims description 2
- 230000007797 corrosion Effects 0.000 abstract description 12
- 238000005260 corrosion Methods 0.000 abstract description 12
- 229910052761 rare earth metal Inorganic materials 0.000 abstract description 6
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 30
- 239000011651 chromium Substances 0.000 description 28
- 239000010949 copper Substances 0.000 description 28
- 239000010936 titanium Substances 0.000 description 27
- 239000011572 manganese Substances 0.000 description 17
- 229910000838 Al alloy Inorganic materials 0.000 description 13
- 238000010438 heat treatment Methods 0.000 description 10
- 238000011161 development Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 239000000470 constituent Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 230000009931 harmful effect Effects 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 230000000704 physical effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 150000002910 rare earth metals Chemical class 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229910018134 Al-Mg Inorganic materials 0.000 description 1
- 229910018182 Al—Cu Inorganic materials 0.000 description 1
- 229910018467 Al—Mg Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 241001062472 Stokellia anisodon Species 0.000 description 1
- 229910010038 TiAl Inorganic materials 0.000 description 1
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical compound [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- JJWKPURADFRFRB-UHFFFAOYSA-N carbonyl sulfide Chemical compound O=C=S JJWKPURADFRFRB-UHFFFAOYSA-N 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 238000002425 crystallisation Methods 0.000 description 1
- 230000008025 crystallization Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- KBQHZAAAGSGFKK-UHFFFAOYSA-N dysprosium atom Chemical compound [Dy] KBQHZAAAGSGFKK-UHFFFAOYSA-N 0.000 description 1
- 230000005496 eutectics Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 description 1
- VZCYOOQTPOCHFL-UPHRSURJSA-N maleic acid Chemical compound OC(=O)\C=C/C(O)=O VZCYOOQTPOCHFL-UPHRSURJSA-N 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
- 239000011159 matrix material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 238000001953 recrystallisation Methods 0.000 description 1
- 229910052706 scandium Inorganic materials 0.000 description 1
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 229910000679 solder Inorganic materials 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000004781 supercooling Methods 0.000 description 1
- GZCRRIHWUXGPOV-UHFFFAOYSA-N terbium atom Chemical compound [Tb] GZCRRIHWUXGPOV-UHFFFAOYSA-N 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- VZCYOOQTPOCHFL-UHFFFAOYSA-N trans-butenedioic acid Natural products OC(=O)C=CC(O)=O VZCYOOQTPOCHFL-UHFFFAOYSA-N 0.000 description 1
- 230000003442 weekly effect Effects 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
-
- 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
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Powder Metallurgy (AREA)
- Heat Treatment Of Steel (AREA)
- Manufacture Of Metal Powder And Suspensions Thereof (AREA)
Abstract
The invention provides a fuselage alloy which comprises 0.01-0.08% of Sc, 0.06-1.5% of Mn, 0.03-0.04% of Ti, 0.01-0.04% of Li, 0.05-0.15% of Sn, 0.21-0.30% of Cu, 9.0-12.0% of Ni, 0.18-0.21% of Cr, 0.01-0.03% of Y, 0.10-0.20% of La, 0.01-0.02% of Tb, 0.01-0.02% of Dy, 0.20-0.30% of Ho, 0.01-0.03% of Eu, 0.50-3.0% of Er, 0.31-0.42% of Zn, 0.10-0.50% of Pb and the balance of Al. Since rare earth elements are added into the prepared alloy material, in the case of same force bearing, the weight of structural parts is obviously reduced, the corrosion resistance is good, and the hardness is high.
Description
Technical field
The invention belongs to acieral field, be specifically related to a kind of airframe alloy.
Background technology
The concept that aircraft industry is mainly correlated with includes aircraft, airborne vehicle, civil aircraft etc..Any object that can fly away from the flight that ground carries out being controlled by people in space that manufactured by people is called aircraft, and the aircraft carrying out flying in atmosphere is called airborne vehicle.Civil aircraft, refers to except for the airborne vehicle except performing military affairs, customs, police's aerial mission.21 century is aircraft industry and the century of transport service fast development, progressively in-depth along with China's economic reform, national economy has marched toward the 3rd step of strategic development, and the demand of aircraft product has been come into fast traffic lane, and this is that the development of aircraft industry of development China creates fabulous opportunity.Aircraft industry is the field that in technology manufacturing industry, new and high technology is concentrated most, belongs to advanced manufacturing technology.US Airways weekly information network is predicted, between 5 years of 2013 ~ 2017 years, the yield of whole world commercial aircraft and secondary-line-aircraft is up to 9287 framves, and total value is more than 994,000,000,000 dollars.
Along with the fast development of aerospace industries, aircraft weight, performance, energy resource consumption etc. are improved constantly with requiring, material be it is also proposed tightened up requirement.For reducing weight, improving performance, generally adopt the way reducing aircraft component size, but the method can cause that material sensitivity decrease and fatigue life reduce.Aircraft engineers recognize, development of high strength alloy in lightweight is maximally effective weight losing method.
The raw material manufacturing aircraft is had higher requirement by the aircraft industry developed rapidly, and the quality of the alloy material used by airframe will directly influence the service life of flight safety and aircraft, how to improve the alloy mass used by airframe, be the encountered a great problem of industry technical staff.
The Chinese patent of application number 200680047951.8 discloses a kind of high tenacity Solder for Al-Cu Joint Welding-lithium sheet material for airframe, there is high intensity, high tenacity and high corrosion resistance, contain: the Cu of 2.1 ~ 2.8 weight %, the Li of 1.1 ~ 1.7 weight %, the Ag of 0.1 ~ 0.8 weight %, the Mg of 0.2 ~ 0.6 weight %, the Mn of 0.2 ~ 0.6 weight %, Fe and Si content be both less than or equal to 0.1 weight %, every kind of inevitable impurity content is less than or equal to 0.05 weight %, content of impurities is less than or equal to 0.15 weight %, and this alloy is substantially free of zirconium；But, preparation process is complicated, and operating parameter is difficult to accurate control, and prepared airframe hardness is not good enough.
The Chinese patent of application number 201010146337.5 discloses a kind of skin panel for airframe, described skin panel includes the stressed-skin construction being connected with at least one metallic stiffening element, described stressed-skin construction includes the polymer-matrix adjacent with metallic stiffening element, carbon fiber reinforced covering member, wherein, described metallic stiffening element by containing 3.5% to 7% Mg and preferably Al-Mg alloy possibly together with the Sc of at least 0.05% to 1.5% make；But, aircraft fuselage skin opposing magnetic field, the ability of ray prepared by the method are poor.
Summary of the invention
In order to overcome above-mentioned prior art defect, it is an object of the invention to provide the alloy material used by a kind of airframe, there is excellent corrosion resistance, mechanical strength is high, alloy with the addition of rare earth metal, the climatic environment harmful effect to aircraft of magnetic field, ray and complexity can be eliminated, efficiently solve the problems referred to above.
In order to solve above-mentioned technical problem, the present invention takes following technical scheme:
A kind of airframe alloy, component includes: scandium, manganese, titanium, lithium, stannum, copper, nickel, chromium, lanthanum, terbium, dysprosium, aluminum etc., wherein, the weight portion of above-mentioned element consists of: the content of Sc is 0.01% ~ 0.08%, the content of Mn is 0.06% ~ 1.5%, the content of Ti is 0.03% ~ 0.04%, the content of Li is 0.01% ~ 0.04%, the content of Sn is 0.05% ~ 0.15%, the content of Cu is 0.21% ~ 0.30%, the content of Ni is 9.0% ~ 12.0%, the content of Cr is 0.18% ~ 0.21%, the content of La is 0.10% ~ 0.20%, the content of Tb is 0.01% ~ 0.02%, the content of Dy is 0.01% ~ 0.02%, the content of Zn is 0.31% ~ 0.42%, the content of Y is 0.01% ~ 0.03%, the content of Eu is 0.01% ~ 0.03%, the content of Er is 0.50% ~ 3.0%, the content of Ho is 0.20% ~ 0.30%, the content of Pb is 0.10% ~ 0.50%, all the other are Al.
Further, described a kind of airframe alloy, the amount of Cr and Ni meets following formula: 9.2% < Cr+Ni < 12.1%.
Further, described a kind of airframe alloy, the content of Er is 0.50% ~ 2.0%, and the content of Eu is 0.01% ~ 0.02%, and the content of Ho is 0.25% ~ 0.30%, and the content of Pb is 0.20% ~ 0.50%, and the content of Y is 0.02% ~ 0.03%.
Further, described a kind of airframe alloy, raw material components optimum weight percentage ratio is as follows, Sc is 0.04%, Mn is 1.0%, Ti is 0.03%, Li is 0.03%, Sn is 0.11%, Cu is 0.24%, Ni is 10.0%, Cr is 0.20%, Y is 0.027%, La is 0.16%, Tb is 0.014%, Dy is 0.016%, Ho is 0.29%, Eu is 0.014%, Er is 1.5%, Zn is 0.38%, Pb is 0.20%, and all the other are Al.
Hereinafter, the restriction reason that the one-tenth of the alloy of employing in the present invention is grouped into illustrates, and becomes the % related in being grouped into refer to quality %.
Sc:0.01% ~ 0.08%, La:0.10% ~ 0.20%, Tb:0.01% ~ 0.02%, Dy:0.01% ~ 0.02%, Ho:0.20% ~ 0.30%, Eu:0.01% ~ 0.03%, Er:0.50% ~ 3.0%, Y:0.01% ~ 0.03%.La, Tb, Dy, Ho, Eu, Er and Y are rare earth elements, rare earth element adds in aluminium alloy, mechanical strength and the corrosion resistance of alloy material can be improved, constitutional supercooling is increased when enabling aluminum alloy to founding, crystal grain thinning, reduce secondary intergranular from, reduce the gas in alloy and be mingled with, and making constituent phases tend to nodularization.Also can reduce smelt surface tension, increase mobility, be conducive to casting ingot-forming, processing performance is had obvious impact；Make elevated temperature strength and term creep resistance energy that the aluminium alloy of preparation had.La content in alloy is defined as 0.10% ~ 0.20% by the present invention, it is preferred to 0.03%；Sc is 0.01% ~ 0.08%, it is preferred to 0.04%；Tb is 0.01% ~ 0.02%, it is preferred to 0.014%；Dy is 0.01% ~ 0.02%, it is preferred to 0.016%；Ho is 0.25% ~ 0.30%, it is preferred to 0.29%；Eu is 0.01% ~ 0.02%, it is preferred to 0.014%；Er is 0.50% ~ 2.0%, it is preferred to 1.5%；Y is 0.02% ~ 0.03%, it is preferred to 0.025%.Rare earth metal can also eliminate the climatic environment harmful effect to aircraft of magnetic field, cosmic ray and complexity, and what improves the service life of aircraft from；Simultaneously when load is identical, hence it is evident that alleviate structural member weight.
Ti is addition element conventional in aluminium alloy, and titanium forms TiAl with aluminum2Phase, becomes heterogeneous necleus during crystallization, plays the effect of refinement cast sturcture and seam organization；Can also playing alterant effect, increase nucleus, Ti content is defined as 0.03% ~ 0.04% by the crystal grain thinning present invention, it is preferred to 0.03%.Ni can put forward heavy alloyed intensity and hardness in aluminium alloy, reduces corrosion resistance, can reduce the alloy corrode to mould, put forward heavy alloyed welding performance, and Ni content in material is defined as 9.0% ~ 12.0% by the present invention, it is preferred to 10.0%.Cr can form intermetallic compound in aluminum, hinders forming core and the growth process of recrystallization, and alloy has certain invigoration effect, moreover it is possible to improves alloy ductility and reduces stress corrosion opening cracking maleate sensitivity.But meeting-place increases quenching sensitive, and making anode oxide film is yellow, and Cr content in aluminum alloy material is defined as 0.18% ~ 0.21% by the present invention, it is preferred to 0.19%.Mn is in a kind of weak alloy deoxidizer, is not only advantageous to the corrosion stability of alloy, and the intensity of alloy can also be made to improve, and can reduce hot cracking tendency, improve corrosion resistance and the welding performance of alloy.Along with Mn content increases, alloy strength increases, and for adapting to aviation condition, Mn content is defined as 0.06% ~ 1.5% by the present invention, it is preferred to 1.1%.Cu, Sn, Li, Zn, Pb can improve mobility in aluminium alloy, increase red brittleness, reduce corrosion resistance, low-alloy intensity can be decreased slightly as, but cutting ability can be improved, regulate well can to improve the fragility of alloy, therefore Pb content in aluminum alloy materials is defined as 0.10% ~ 0.50% by the present invention, it is preferred to 0.20%；Li is defined as 0.01% ~ 0.04%, it is preferred to 0.025%；Sn content is defined as 0.50% ~ 0.15%, it is preferred to 0.11%；Cu content is defined as 0.21% ~ 0.30%, it is preferred to 0.26%；Zn content is defined as 0.31% ~ 0.42%, it is preferred to be 0.38%.
Another object of the present invention, is in that to provide the preparation method adopting airframe alloy as above, and preparation process includes:
Step S01: by melted to Li, Sn, Pb, Al abundant；
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 20 minutes ~ 30 minutes, use coolant to be quickly cooled to room temperature, obtain the thick embryo of alloy；
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are heated to 1900 DEG C ~ 1950 DEG C with the firing rate of 150 DEG C/min ~ 200 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the rate of temperature fall of 150 DEG C/min ~ 200 DEG C/min, obtains alloy material；
Step S04: alloy material described in the temperature homogenisation between 480 DEG C ~ 505 DEG C；
Step S05: sheet material described in restrained stretching is to permanent deformation 3% ~ 6%；
Step S06: described alloy material is carried out tempering.
Further, the preparation method of described airframe alloy, in step S01, described Li, Sn, Pb, Al melting condition is: heat to 660 DEG C ~ 700 DEG C with the firing rate of 150 DEG C/min ~ 200 DEG C/min, melted 20 minutes ~ 30 minutes.
Further, the preparation method of described airframe alloy, in step S02, the condition of described quick cooling is to lower the temperature with the rate of temperature fall of 150 DEG C/min ~ 200 DEG C/min.
Further, the preparation method of described airframe alloy, in step S04, the time of described homogenizing is 20 hours ~ 30 hours.
Further, the preparation method of described airframe alloy, in step S06, the mode of described tempering is: heat 5 hours ~ 30 hours at 440 DEG C ~ 470 DEG C.
The invention have the advantage that
Alloy provided by the present invention not only has good mechanical strength, and the corrosion resistance of aluminium alloy has been significantly increased.Ti, Ni, Cr, Mn can put forward heavy alloyed hardness and corrosion resistance, Cu, Sn, Li, Zn, the toughness of material is strengthened by Pb, do not destroy the original hardness of material simultaneously, La, Tb, Dy, Ho, Eu, Er and Y is rare earth element, join the corrosion resistance that can strengthen aluminum alloy materials in material further, increase pressurized and the shock resistance of material, after material just one-step forming between 480 DEG C ~ 505 DEG C homogenizing 20 hours ~ 30 hours, can promote that in alloy, low melting point solubilized eutectic phase is completely or nearly completely dissolved, reduce the percentage by volume of second-phase, alloy cast ingot chemical constituents analysis is made to tend to uniform, tissue reaches or close to poised state, improve alloying element solid solubility in the base, improve the plasticity of alloy simultaneously, put forward heavy alloyed intensity, finally improve processing characteristics and the serviceability of alloy.The stretcher strain of 3% ~ 6% processes, the physical property that can make material keeps fixing, higher elasticity and yield point can be obtained at 440 DEG C ~ 470 DEG C average temperings heated under 5 hours ~ 30 hours conditions simultaneously, suitable toughness, to be in harmonious proportion the physical property after stretcher strain, prepared material is made to more conform to the airframe material demand of aviation operation.
Detailed description of the invention
Specific embodiments of the invention given below, are used for the present invention is described in further detail.
Embodiment 1
A kind of airframe alloy, its raw material components includes:
Sc is 0.04%, Mn is 1.0%, Ti is 0.03%, Li is 0.03%, Sn is 0.11%, Cu is 0.24%, Ni is 10.0%, Cr is 0.20%, Y is 0.027%, La is 0.16%, Tb is 0.014%, Dy is 0.016%, Ho is 0.29%, Eu is 0.014%, Er is 1.5%, Zn is 0.38%, Pb is 0.20%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 670 DEG C with the firing rate of 170 DEG C/min, melted 23 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 23 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 170 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1910 DEG C with the firing rate heating of 170 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature when rate of temperature fall is 170 DEG C/min, obtains alloy material.
Step S04: alloy material 23 hours described in the temperature homogenisation between 485 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 3.6%；
Step S06: described alloy material is heated tempering in 25 hours at 450 DEG C of temperature.
Embodiment 2
A kind of airframe alloy, its raw material components includes:
Sc is 0.01%, Mn is 0.06%, Ti is 0.03%, Li is 0.01%, Sn is 0.05%, Cu is 0.21%, Ni is 9.0%, Cr is 0.18%, Y is 0.01%, La is 0.10%, Tb is 0.01%, Dy is 0.01%, Ho is 0.20%, Eu is 0.01%, Er is 0.50%, Zn is 0.31%, Pb is 0.10%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 660 DEG C with the firing rate of 150 DEG C/min, melted 20 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 20 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 150 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1900 DEG C with the firing rate heating of 150 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, drop to room temperature in the situation that rate of temperature fall is 150 DEG C/min, obtain alloy material.
Step S04: alloy material 23 hours described in the temperature homogenisation between 480 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 3%；
Step S06: described alloy material is heated tempering in 5 hours at 440 DEG C of temperature.
Embodiment 3
A kind of airframe alloy, its raw material components includes:
Sc is 0.08%, Mn is 1.5%, Ti is 0.04%, Li is 0.04%, Sn is 0.15%, Cu is 0.20%, Ni is 11.9%, Cr is 0.21%, Y is 0.03%, La is 0.20%, Tb is 0.02%, Dy is 0.01%, Ho is 0.30%, Eu is 0.03%, Er is 3.0%, Zn is 0.42%, Pb is 0.50%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 685 DEG C with the firing rate of 200 DEG C/min, melted 30 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 30 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 200 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1950 DEG C with the firing rate heating of 200 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the speed that rate of temperature fall is 200 DEG C/min, obtains alloy material.
Step S04: alloy material 30 hours described in the temperature homogenisation between 505 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 6%；
Step S06: described alloy material is heated tempering in 30 hours at 470 DEG C of temperature.
Embodiment 4
A kind of airframe alloy, its raw material components includes:
Sc is 0.045%, Mn is 1.05%, Ti is 0.035%, Li is 0.025%, Sn is 0.10%, Cu is 0.255%, Ni is 10.5%, Cr is 0.195%, Y is 0.02%, La is 0.15%, Tb is 0.015%, Dy is 0.015%, Ho is 0.25%, Eu is 0.02%, Er is 1.75%, Zn is 0.365%, Pb is 0.30%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 685 DEG C with the firing rate of 175 DEG C/min, melted 25 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 25 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 175 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1925 DEG C with the firing rate heating of 175 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the speed that rate of temperature fall is 175 DEG C/min, obtains alloy material.
Step S04: alloy material 25 hours described in the temperature homogenisation between 493 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 4.5%；
Step S06: described alloy material is heated tempering in 18 hours at 455 DEG C of temperature.
Embodiment 5
A kind of airframe alloy, its raw material components includes:
Sc is 0.05%, Mn is 1.1%, Ti is 0.04%, Li is 0.03%, Sn is 0.11%, Cu is 0.26%, Ni is 11.0%, Cr is 0.20%, Y is 0.01%, La is 0.20%, Tb is 0.02%, Dy is 0.02%, Ho is 0.30%, Eu is 0.03%, Er is 1.80%, Zn is 0.37%, Pb is 0.40%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 680 DEG C with the firing rate of 175 DEG C/min, melted 21 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 21 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 180 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1930 DEG C with the firing rate heating of 180 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the speed that rate of temperature fall is 180 DEG C/min, obtains alloy material.
Step S04: alloy material 21 hours described in the temperature homogenisation between 490 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 4%；
Step S06: described alloy material is heated tempering in 17 hours at 450 DEG C of temperature.
Embodiment 6
A kind of airframe alloy, its raw material components includes:
Sc is 0.02%, Mn is 1.2%, Ti is 0.03%, Li is 0.02%, Sn is 0.12%, Cu is 0.28%, Ni is 11.5%, Cr is 0.19%, Y is 0.02%, La is 0.14%, Tb is 0.01%, Dy is 0.01%, Ho is 0.22%, Eu is 0.02%, Er is 2.80%, Zn is 0.41%, Pb is 0.34%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 695 DEG C with the firing rate of 190 DEG C/min, melted 27 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 27 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 190 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1938 DEG C with the firing rate heating of 190 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the speed that rate of temperature fall is 190 DEG C/min, obtains alloy material.
Step S04: alloy material 27 hours described in the temperature homogenisation between 500 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 5%；
Step S06: described alloy material is heated tempering in 20 hours at 465 DEG C of temperature.
Embodiment 7
A kind of airframe alloy, its raw material components includes:
Sc is 0.07%, Mn is 0.7%, Ti is 0.04%, Li is 0.03%, Sn is 0.14%, Cu is 0.27%, Ni is 11.7%, Cr is 0.21%, Y is 0.01%, La is 0.12%, Tb is 0.01%, Dy is 0.02%, Ho is 0.27%, Eu is 0.027%, Er is 1.40%, Zn is 0.38%, Pb is 0.35%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 665 DEG C with the firing rate of 165 DEG C/min, melted 24 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 24 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 165 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1905 DEG C with the firing rate heating of 190 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the speed that rate of temperature fall is 165 DEG C/min, obtains alloy material.
Step S04: alloy material 22 hours described in the temperature homogenisation between 496 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 5.5%；
Step S06: described alloy material is heated tempering in 6 hours at 462 DEG C of temperature.
Embodiment 8
A kind of airframe alloy, its raw material components includes:
Sc is 0.08%, Mn is 0.8%, Ti is 0.032%, Li is 0.032%, Sn is 0.08%, Cu is 0.24%, Ni is 9.6%, Cr is 0.24%, Y is 0.02%, La is 0.16%, Tb is 0.016%, Dy is 0.016%, Ho is 0.27%, Eu is 0.024%, Er is 2.40%, Zn is 0.32%, Pb is 0.24%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 672 DEG C with the firing rate of 192 DEG C/min, melted 28 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 28 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 192 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1932 DEG C with the firing rate heating of 192 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the speed that rate of temperature fall is 192 DEG C/min, obtains alloy material.
Step S04: alloy material 28 hours described in the temperature homogenisation between 491 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 3.5%；
Step S06: described alloy material is heated tempering in 7 hours at 452 DEG C of temperature.
Embodiment 9
A kind of airframe alloy, its raw material components includes:
Sc is 0.05%, Mn is 1.1%, Ti is 0.036%, Li is 0.036%, Sn is 0.09%, Cu is 0.29%, Ni is 9.9%, Cr is 0.19%, Y is 0.027%, La is 0.18%, Tb is 0.018%, Dy is 0.018%, Ho is 0.29%, Eu is 0.029%, Er is 2.90%, Zn is 0.39%, Pb is 0.29%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 689 DEG C with the firing rate of 199 DEG C/min, melted 29 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 29 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 199 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1939 DEG C with the firing rate heating of 199 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the speed that rate of temperature fall is 199 DEG C/min, obtains alloy material.
Step S04: alloy material 29 hours described in the temperature homogenisation between 499 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 4.5%；
Step S06: described alloy material is heated tempering in 18 hours at 459 DEG C of temperature.
Embodiment 10
A kind of airframe alloy, its raw material components includes:
Sc is 0.04%, Mn is 1.4%, Ti is 0.031%, Li is 0.031%, Sn is 0.11%, Cu is 0.23%, Ni is 11.0%, Cr is 0.20%, Y is 0.023%, La is 0.19%, Tb is 0.019%, Dy is 0.019%, Ho is 0.26%, Eu is 0.026%, Er is 2.81%, Zn is 0.37%, Pb is 0.39%, and all the other are Al.
Its preparation method comprises the following steps:
Step S01: Li, Sn, Pb, Al are heated to 679 DEG C with the firing rate of 179 DEG C/min, melted 24 minutes.
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 24 minutes, it is cooled to room temperature with the speed that rate of temperature fall is 179 DEG C/min, obtains the thick embryo of alloy.
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are melted to 1929 DEG C with the firing rate heating of 179 DEG C/min, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the speed that rate of temperature fall is 179 DEG C/min, obtains alloy material.
Step S04: alloy material 24 hours described in the temperature homogenisation between 479 DEG C.
Step S05: sheet material described in restrained stretching is to permanent deformation 4.7%；
Step S06: described alloy material is heated tempering in 19 hours at 449 DEG C of temperature.
Experimental example 1
By the embodiment of the present invention 1 ~ 10 alloy material compared with common fuselage aluminium alloy, its results of property such as table 1 below.
Table 1 Performance comparision
From above-mentioned test example, the properties of alloy material of the present invention is above the common fuselage aluminium alloy under equal conditions, is more suitable for the aluminum alloy materials for airframe.
These are only the preferred embodiments of the present invention and experimental example, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.All within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (10)
1. an airframe alloy, it is characterized in that, content including Sc is 0.01% ~ 0.08%, the content of Mn is 0.06% ~ 1.5%, the content of Ti is 0.03% ~ 0.04%, the content of Li is 0.01% ~ 0.04%, the content of Sn is 0.05% ~ 0.15%, the content of Cu is 0.21% ~ 0.30%, the content of Ni is 9.0% ~ 12.0%, the content of Cr is 0.18% ~ 0.21%, the content of La is 0.10% ~ 0.20%, the content of Tb is 0.01% ~ 0.02%, the content of Dy is 0.01% ~ 0.02%, the content of Zn is 0.31% ~ 0.42%, the content of Y is 0.01% ~ 0.03%, the content of Eu is 0.01% ~ 0.03%, the content of Er is 0.50% ~ 3.0%, the content of Ho is 0.20% ~ 0.30%, the content of Pb is 0.10% ~ 0.50%, all the other are Al.
2. airframe alloy according to claim 1, it is characterised in that the amount of Cr and Ni meets following formula: 9.2% < Cr+Ni < 12.1%.
3. airframe alloy according to claim 1, it is characterised in that the content of Er is 0.50% ~ 2.0%, the content of Eu is 0.01% ~ 0.02%, and the content of Ho is 0.25% ~ 0.30%, and the content of Pb is 0.20% ~ 0.50%, and the content of Y is 0.02% ~ 0.03%.
4. an airframe alloy, it is characterized in that, by weight percentage containing, for example lower raw material components: Sc is 0.04%, Mn is 1.0%, Ti is 0.03%, Li is 0.03%, Sn is 0.11%, Cu is 0.24%, Ni is 10.0%, Cr is 0.20%, Y is 0.027%, La is 0.16%, Tb is 0.014%, Dy is 0.016%, Ho is 0.29%, Eu is 0.014%, Er is 1.5%, Zn is 0.38%, Pb is 0.20%, and all the other are Al.
5. the preparation method of an airframe alloy, it is characterised in that preparation process includes:
Step S01: by melted to Li, Sn, Pb, Al abundant；
Step S02: Zn is added under the molten metal bath liquid level of step S01, not with air contact, after fully melted, stirring insulation 20 minutes ~ 30 minutes, use coolant to be quickly cooled to room temperature, obtain the thick embryo of alloy；
Step S03: Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are added heat fusing, the thick embryo of alloy is added after evacuation, after making each component melts fully, it is cooled to room temperature with the rate of temperature fall of 150 DEG C/min ~ 200 DEG C/min, obtains alloy material；
Step S04: alloy material described in the temperature homogenisation between 480 DEG C ~ 505 DEG C；
Step S05: sheet material described in restrained stretching is to permanent deformation 3% ~ 6%；
Step S06: described alloy material is carried out tempering.
6. the preparation method of airframe alloy according to claim 5, it is characterized in that, in step S01, described Li, Sn, Pb, Al melting condition is: heat to 660 DEG C ~ 700 DEG C with the firing rate of 150 DEG C/min ~ 200 DEG C/min, melted 20 minutes ~ 30 minutes.
7. the preparation method of airframe alloy according to claim 5, it is characterised in that in step S02, the mode of described quick cooling is: rate of temperature fall is 150 DEG C/min ~ 200 DEG C/min.
8. the preparation method of airframe alloy according to claim 5, it is characterised in that in step S03, described in add the condition of heat fusing and be: heat to 1900 DEG C ~ 1950 DEG C with the firing rate of 150 DEG C/min ~ 200 DEG C/min.
9. the preparation method of airframe alloy according to claim 5, it is characterised in that in step S04, the time of described homogenizing is 20 hours ~ 30 hours.
10. the preparation method of airframe alloy according to claim 5, it is characterised in that in step S06, the mode of described tempering is: heat 5 hours ~ 30 hours at 440 DEG C ~ 470 DEG C temperature.
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