CN105714159B - A kind of airframe alloy - Google Patents
A kind of airframe alloy Download PDFInfo
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- CN105714159B CN105714159B CN201610295926.7A CN201610295926A CN105714159B CN 105714159 B CN105714159 B CN 105714159B CN 201610295926 A CN201610295926 A CN 201610295926A CN 105714159 B CN105714159 B CN 105714159B
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- 239000000956 alloy Substances 0.000 title claims abstract description 143
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 85
- 229910052745 lead Inorganic materials 0.000 claims abstract description 33
- 229910052693 Europium Inorganic materials 0.000 claims abstract description 32
- 229910052689 Holmium Inorganic materials 0.000 claims abstract description 32
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 32
- 229910052692 Dysprosium Inorganic materials 0.000 claims abstract description 31
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 31
- 229910052691 Erbium Inorganic materials 0.000 claims abstract description 30
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 30
- 229910052802 copper Inorganic materials 0.000 claims abstract description 30
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 29
- 229910052744 lithium Inorganic materials 0.000 claims abstract description 20
- 229910052718 tin Inorganic materials 0.000 claims abstract description 18
- 229910052746 lanthanum Inorganic materials 0.000 claims abstract description 17
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 17
- 229910052725 zinc Inorganic materials 0.000 claims abstract description 17
- 229910052771 Terbium Inorganic materials 0.000 claims abstract description 16
- 238000002844 melting Methods 0.000 claims description 40
- 230000008018 melting Effects 0.000 claims description 40
- 238000010304 firing Methods 0.000 claims description 24
- 238000002360 preparation method Methods 0.000 claims description 23
- 229910052782 aluminium Inorganic materials 0.000 claims description 18
- 239000000463 material Substances 0.000 claims description 13
- 239000002994 raw material Substances 0.000 claims description 13
- 238000005496 tempering Methods 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
- 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
- 230000008859 change Effects 0.000 claims description 2
- 239000002826 coolant Substances 0.000 claims description 2
- 238000001816 cooling Methods 0.000 claims description 2
- 238000005260 corrosion Methods 0.000 abstract description 11
- 230000007797 corrosion Effects 0.000 abstract description 10
- 229910052761 rare earth metal Inorganic materials 0.000 abstract description 5
- -1 Sc:0.01% ~ 0.08% Substances 0.000 abstract 1
- 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 28
- 210000001161 mammalian embryo Anatomy 0.000 description 22
- 239000011572 manganese Substances 0.000 description 17
- 239000011135 tin Substances 0.000 description 16
- 229910000838 Al alloy Inorganic materials 0.000 description 12
- 238000000034 method Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- 239000004411 aluminium Substances 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 4
- 238000011161 development Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000012545 processing Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-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
- 230000000694 effects Effects 0.000 description 2
- 230000009931 harmful effect Effects 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000000704 physical effect Effects 0.000 description 2
- 150000002910 rare earth metals Chemical class 0.000 description 2
- 229910052706 scandium Inorganic materials 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
- 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
- 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
- 238000004458 analytical method Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 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
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 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
- 239000000835 fiber Substances 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
- 230000008520 organization Effects 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 230000008569 process 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
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 229910000679 solder Inorganic materials 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 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 present invention provides a kind of airframe alloy, including Sc：0.01% ~ 0.08%, Mn：0.06% ~ 1.5%, Ti：0.03% ~ 0.04%, Li：0.01% ~ 0.04%, Sn：0.05% ~ 0.15%, Cu：0.21% ~ 0.30%, Ni：9.0% ~ 12.0%, Cr：0.18% ~ 0.21%, Y：0.01% ~ 0.03%, 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%, Zn：0.31% ~ 0.42%, Pb：0.10% ~ 0.50%, remaining is Al, with the addition of rare earth element in prepared alloy material, in load under the same conditions, hence it is evident that mitigate structural member weight, and corrosion resistance is good, and hardness is big.
Description
Technical field
The invention belongs to acieral field, and in particular to a kind of airframe alloy.
Background technology
The main related concept of aircraft industry includes aircraft, airborne vehicle, civil aircraft etc..It is any that energy is manufactured by people
Fly away from the object referred to as aircraft for the flight that ground in space controlled by people, the aircraft flown in atmosphere
Referred to as airborne vehicle.Civil aircraft, refers to the airborne vehicle in addition to for performing military affairs, customs, police's aerial mission.21st century
It is aircraft industry and transport service fast-developing century, with the progressively in-depth of China's economic reform, national economy is marched toward
3rd step of strategic development, the demand to aircraft product has come into fast traffic lane, and this is the aircraft industry of development China
Development creates fabulous opportunity.Aircraft industry is the field that new and high technology is most concentrated in technology manufacturing industry, belongs to first system
Make technology.US Airways weekly information network is predicted, between 5 years of 2013 ~ 2017 years, the yield of global commercial aircraft and secondary-line-aircraft
9287 framves are up to, total value is more than 994,000,000,000 dollars.
With the fast development of aerospace industries, ground, which is constantly carried, to be required to aircraft weight, performance, energy resource consumption etc.
Height, tightened up requirement is it is also proposed to material.For reduction weight, performance is improved, generally using reduction aircraft component size
Method, but this method can cause material sensitivity decrease and fatigue life to reduce.Aircraft engineers recognize, develop high-strength
It is maximally effective weight losing method to spend alloy in lightweight.
The aircraft industry developed rapidly proposes higher requirement to the raw material for manufacturing aircraft, and used in airframe
The quality of alloy material will directly influence the service life of flight safety and aircraft, how to improve used in airframe
Alloy mass, be a great problem that industry technical staff is faced.
The Chinese patent of application number 200680047951.8 discloses a kind of high tenacity Solder for Al-Cu Joint Welding-lithium for airframe
Sheet material, with high intensity, high tenacity and high corrosion resistance, contains：2.1 ~ 2.8 weight % Cu, 1.1 ~ 1.7 weight % Li, 0.1
~ 0.8 weight % Ag, 0.2 ~ 0.6 weight % Mg, 0.2 ~ 0.6 weight % Mn, Fe and Si content are both less than or equal to 0.1 weight
% is measured, every kind of inevitable impurity content is less than or equal to 0.05 weight %, and content of impurities is less than or equal to 0.15 weight %,
The alloy is substantially free of zirconium；But, preparation process is complicated, and operating parameter is difficult to accurate control, prepared airframe hardness
It is not good enough.
The Chinese patent of application number 201010146337.5 discloses a kind of skin panel for airframe, the covering
Plate includes the stressed-skin construction being connected with least one metallic stiffening element, and the stressed-skin construction includes adjacent with metallic stiffening element
The polymer matrix that connects, the covering member of fibre reinforced, wherein, the metallic stiffening element is by containing 3.5% to 7% Mg
And the Al-Mg alloys preferably also containing at least 0.05% to 1.5% Sc are made；But, aircraft prepared by this method
Fuselage skin resistance magnetic field, ray ability it is poor.
The content 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 in a kind of airframe
Material, with excellent corrosion resistance, high mechanical strength with the addition of rare earth metal in alloy, can eliminate magnetic field, ray and multiple
Harmful effect of the miscellaneous climatic environment to aircraft, efficiently solves above mentioned problem.
In order to solve the above-mentioned technical problem, the present invention takes following technical scheme：
A kind of airframe alloy, component includes：Scandium, manganese, titanium, lithium, tin, copper, nickel, chromium, lanthanum, terbium, dysprosium, aluminium
Deng, wherein, the mass percent composition of above-mentioned element is：The content that Sc content is 0.01% ~ 0.08%, Mn is 0.06% ~
1.5%th, the content that the content that Ti content is 0.03% ~ 0.04%, Li is 0.01% ~ 0.04%, Sn is containing for 0.05% ~ 0.15%, Cu
The content that the content that the content measured as 0.21% ~ 0.30%, Ni is 9.0% ~ 12.0%, Cr is 0.18% ~ 0.21%, La is 0.10% ~
0.20%th, the content that the content that Tb content is 0.01% ~ 0.02%, Dy is 0.01% ~ 0.02%, Zn is containing for 0.31% ~ 0.42%, Y
The content that the content that the content measured as 0.01% ~ 0.03%, Eu is 0.01% ~ 0.03%, Er is 0.50% ~ 3.0%, Ho is 0.20% ~
0.30%th, Pb content is 0.10% ~ 0.50%, and remaining is Al.
Further, a kind of airframe alloy, Cr and Ni mass percent meet following formula：9.2% ＜ Cr+
Ni ＜ 12.1%.
Further, a kind of airframe alloy, Er mass percent is 0.50% ~ 2.0%, Eu quality hundred
It is 0.25% ~ 0.30% to divide the mass percent that ratio is 0.01% ~ 0.02%, Ho, and Pb mass percent is 0.20% ~ 0.50%, Y's
Mass percent is 0.02% ~ 0.03%.
Further, a kind of airframe alloy, raw material components best in quality percentage is as follows, and Sc is
0.04%th, Mn is that 1.0%, Ti is that 0.03%, Li is that 0.03%, Sn is that 0.11%, Cu is that 0.24%, Ni is that 10.0%, Cr is 0.20%, Y
It is that 0.16%, Tb is that 0.014%, Dy is that 0.016%, Ho is that 0.29%, Eu is that 0.014%, Er is that 1.5%, Zn is for 0.027%, La
0.38%th, Pb is 0.20%, and remaining is Al.
Hereinafter, the restriction reason to the composition composition of the alloy used in the present invention is illustrated, and is related in composition composition
% 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 earths
Element, rare earth element is added in aluminium alloy, it is possible to increase the mechanical strength and corrosion resistance of alloy material, when enabling aluminum alloy to founding
Increase constitutional supercooling, crystal grain thinning reduces secondary intergranular away from reducing the gas in alloy and be mingled with, and constituent phases is tended to ball
Change.Smelt surface tension can be also reduced, increases mobility, is conducive to casting ingot-forming, processing performance is had a significant impact；Make
Elevated temperature strength and term creep resistance energy that the aluminium alloy of preparation has had.La contents in alloy are defined as 0.10% by the present invention ~
0.20%, preferably 0.03%；Sc is 0.01% ~ 0.08%, preferably 0.04%；Tb is 0.01% ~ 0.02%, preferably 0.014%；
Dy is 0.01% ~ 0.02%, preferably 0.016%；Ho is 0.25% ~ 0.30%, preferably 0.29%；Eu is 0.01% ~ 0.02%, excellent
Elect 0.014% as；Er is 0.50% ~ 2.0%, preferably 1.5%；Y is 0.02% ~ 0.03%, preferably 0.025%.Rare earth metal can also
Harmful effect of the climatic environment in magnetic field, cosmic ray and complexity to aircraft is eliminated, what is improved the service life of aircraft from；Together
When in load under the same conditions, hence it is evident that mitigate structural member weight.
Ti is the addition element commonly used in aluminium alloy, titanium and aluminium formation TiAl2Phase, heterogeneous necleus during as crystallization,
Play refinement cast sturcture and seam organization；Alterant effect can also be played, increases nucleus, crystal grain thinning is of the invention by Ti
Content is defined as 0.03% ~ 0.04%, preferably 0.03%.Ni can improve the intensity and hardness of alloy in aluminium alloy, reduce anti-corrosion
Property, it can reduce corrode of the alloy to mould, improve the welding performance of alloy, Ni contents in material are defined as 9.0% by the present invention ~
12.0%, preferably 10.0%.Cr can form intermetallic compound in aluminium, hinder the forming core and growth process of recrystallization, right
Alloy has certain invigoration effect, moreover it is possible to improve alloy ductility and reduction stress corrosion opening cracking maleate sensitivity.But meeting-place increase quenching
Sensitiveness, it is in yellow to make anode oxide film, and Cr contents in aluminum alloy material are defined as 0.18% ~ 0.21% by the present invention, are preferably
0.19%.During Mn is a kind of weak alloy deoxidizer, the corrosion stability of alloy is not only advantageous to, and can also improve the intensity of alloy,
And hot cracking tendency can be reduced, improve the corrosion resistance and welding performance of alloy.With the increase of Mn contents, alloy strength is
Improve, to adapt to aviation condition, Mn contents are defined as 0.06% ~ 1.5%, preferably 1.1% by the present invention.Cu、Sn、Li、Zn、Pb
Mobility can be improved in aluminium alloy, increases red brittleness, corrosion resistance is reduced, low-alloy intensity can be decreased slightly as, but cutting can be improved
Performance, adjust must well can to improve the fragility of alloy, thus the present invention Pb contents in aluminum alloy materials are defined as 0.10% ~
0.50%, preferably 0.20%；Li is defined as 0.01% ~ 0.04%, preferably 0.025%；Sn contents are defined as 0.50% ~ 0.15%, excellent
Elect 0.11% as；Cu contents are defined as 0.21% ~ 0.30%, preferably 0.26%；Zn contents are defined as 0.31% ~ 0.42%, are preferably
For 0.38%.
Another object of the present invention, is to provide the preparation method using airframe alloy as described above, system
Standby step includes：
Step S01：Li, Sn, Pb, Al melting is abundant；
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 20 minutes ~ 30 minutes, is quickly cooled to room temperature using coolant, obtains the thick embryo of alloy；
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 150 DEG C/min ~ 200 DEG C/min
Firing rate be heated to 1900 DEG C ~ 1950 DEG C, after vacuumizing add the thick embryo of alloy, make each component melting fully after, with 150
DEG C/min ~ 200 DEG C/min rate of temperature fall is cooled to room temperature, obtains alloy material；
Step S04：Alloy material described in temperature homogenisation between 480 DEG C ~ 505 DEG C；
Step S05：The extremely permanent deformation 3% ~ 6% of alloy material described in restrained stretching；
Step S06：The alloy material is tempered.
Further, the preparation method of the airframe alloy, in step S01, Li, Sn, Pb, Al melting
Condition is：660 DEG C ~ 700 DEG C are heated to 150 DEG C/min ~ 200 DEG C/min firing rate, is melted 20 minutes ~ 30 minutes.
Further, the preparation method of the airframe alloy, in step S02, the condition quickly cooled down
It is the rate of temperature fall cooling with 150 DEG C/min ~ 200 DEG C/min.
Further, the preparation method of the airframe alloy, in step S04, the time of the homogenizing is 20
Hour ~ 30 hours.
Further, the preparation method of the airframe alloy, in step S06, the mode of the tempering is：
440 DEG C ~ 470 DEG C are heated 5 hours ~ 30 hours.
It is an advantage of the invention that：
Alloy provided by the present invention not only has good mechanical strength, and the anti-of aluminium alloy has been significantly increased
Corrosivity.Ti, Ni, Cr, Mn can improve the hardness and corrosion resistance of alloy, and Cu, Sn, Li, Zn, Pb are carried out to the toughness of material
Strengthen, while not destroying the original hardness of material, La, Tb, Dy, Ho, Eu, Er and Y are rare earth elements, are added to energy in material
Enough corrosion resistancies for further strengthening aluminum alloy materials, increase compression and the shock resistance of material, material is just after one-step forming
It is homogenized 20 hours ~ 30 hours between 480 DEG C ~ 505 DEG C, low melting point in alloy can be promoted to can dissolve eutectic phase completely or nearly
It is completely dissolved, reduces the percentage by volume of the second phase, alloy cast ingot chemical constituents analysis is tended to be uniform, tissue reaches or approached
Poised state, improves the solid solubility of alloying element in the base, while improving the plasticity of alloy, improves the intensity of alloy, finally
Improve the processing characteristics and performance of alloy.3% ~ 6% stretcher strain processing, can make the physical property of material keep fixing,
Average tempering heated 5 hours ~ 30 hours at 440 DEG C ~ 470 DEG C simultaneously under the conditions of can obtain higher elasticity and yield point,
Appropriate toughness, to reconcile the physical property after stretcher strain, makes prepared material more conform to the aircraft machine of aviation operation
Stature matter demand.
Embodiment
Specific embodiment of the invention given below, for being described in further detail to the present invention.
Embodiment 1
A kind of airframe alloy, its raw material components include：
Sc be 0.04%, Mn be 1.0%, Ti be 0.03%, Li be 0.03%, Sn be 0.11%, Cu be 0.24%, Ni be 10.0%,
Cr is that 0.20%, Y is that 0.027%, La is that 0.16%, Tb is that 0.014%, Dy is that 0.016%, Ho is that 0.29%, Eu is that 0.014%, Er is
1.5%th, Zn is that 0.38%, Pb is 0.20%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 670 DEG C with 170 DEG C/min firing rate, melted 23 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 23 minutes, is cooled to room temperature using rate of temperature fall as 170 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 170 DEG C/min firing rate
Be heated to 1910 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, rate of temperature fall be 170 DEG C/
Room temperature is cooled in the case of min, alloy material is obtained.
Step S04：Alloy material 23 hours described in temperature homogenisation between 485 DEG C.
Step S05：The extremely permanent deformation 3.6% of alloy material described in restrained stretching；
Step S06：Tempering in 25 hours is heated at a temperature of 450 DEG C to the alloy material.
Embodiment 2
A kind of airframe alloy, its raw material components include：
Sc be 0.01%, Mn be 0.06%, Ti be 0.03%, Li be 0.01%, Sn be 0.05%, Cu be 0.21%, Ni be 9.0%,
Cr is that 0.18%, Y is that 0.01%, La is that 0.10%, Tb is that 0.01%, Dy is that 0.01%, Ho is that 0.20%, Eu is that 0.01%, Er is
0.50%th, Zn is that 0.31%, Pb is 0.10%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 660 DEG C with 150 DEG C/min firing rate, melted 20 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 20 minutes, is cooled to room temperature using rate of temperature fall as 150 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 150 DEG C/min firing rate
Be heated to 1900 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, rate of temperature fall be 150 DEG C/
Room temperature is down in the case of min, alloy material is obtained.
Step S04：Alloy material 23 hours described in temperature homogenisation between 480 DEG C.
Step S05：The extremely permanent deformation 3% of alloy material described in restrained stretching；
Step S06：Tempering in 5 hours is heated at a temperature of 440 DEG C to the alloy material.
Embodiment 3
A kind of airframe alloy, its raw material components include：
Sc be 0.08%, Mn be 1.5%, Ti be 0.04%, Li be 0.04%, Sn be 0.15%, Cu be 0.20%, Ni be 11.9%,
Cr is that 0.21%, Y is that 0.03%, La is that 0.20%, Tb is that 0.02%, Dy is that 0.01%, Ho is that 0.30%, Eu is that 0.03%, Er is
3.0%th, Zn is that 0.42%, Pb is 0.50%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 685 DEG C with 200 DEG C/min firing rate, melted 30 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 30 minutes, is cooled to room temperature using rate of temperature fall as 200 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 200 DEG C/min firing rate
Be heated to 1950 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, using rate of temperature fall as 200 DEG C/
Min speed is cooled to room temperature, obtains alloy material.
Step S04：Alloy material 30 hours described in temperature homogenisation between 505 DEG C.
Step S05：The extremely permanent deformation 6% of alloy material described in restrained stretching；
Step S06：Tempering in 30 hours is heated at a temperature of 470 DEG C to the alloy material.
Embodiment 4
A kind of airframe alloy, its raw material components include：
Sc is that 0.045%, Mn is that 1.05%, Ti is that 0.035%, Li is that 0.025%, Sn is that 0.10%, Cu is that 0.255%, Ni is
10.5%th, Cr is that 0.195%, Y is that 0.02%, La is that 0.15%, Tb is that 0.015%, Dy is that 0.015%, Ho is that 0.25%, Eu is
0.02%th, Er is that 1.75%, Zn is that 0.365%, Pb is 0.30%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 685 DEG C with 175 DEG C/min firing rate, melted 25 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 25 minutes, is cooled to room temperature using rate of temperature fall as 175 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 175 DEG C/min firing rate
Be heated to 1925 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, using rate of temperature fall as 175 DEG C/
Min speed is cooled to room temperature, obtains alloy material.
Step S04：Alloy material 25 hours described in temperature homogenisation between 493 DEG C.
Step S05：The extremely permanent deformation 4.5% of alloy material described in restrained stretching；
Step S06：Tempering in 18 hours is heated at a temperature of 455 DEG C to the alloy material.
Embodiment 5
A kind of airframe alloy, its raw material components include：
Sc be 0.05%, Mn be 1.1%, Ti be 0.04%, Li be 0.03%, Sn be 0.11%, Cu be 0.26%, Ni be 11.0%,
Cr is that 0.20%, Y is that 0.01%, La is that 0.20%, Tb is that 0.02%, Dy is that 0.02%, Ho is that 0.30%, Eu is that 0.03%, Er is
1.80%th, Zn is that 0.37%, Pb is 0.40%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 680 DEG C with 175 DEG C/min firing rate, melted 21 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 21 minutes, is cooled to room temperature using rate of temperature fall as 180 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 180 DEG C/min firing rate
Be heated to 1930 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, using rate of temperature fall as 180 DEG C/
Min speed is cooled to room temperature, obtains alloy material.
Step S04：Alloy material 21 hours described in temperature homogenisation between 490 DEG C.
Step S05：The extremely permanent deformation 4% of alloy material described in restrained stretching；
Step S06：Tempering in 17 hours is heated at a temperature of 450 DEG C to the alloy material.
Embodiment 6
A kind of airframe alloy, its raw material components include：
Sc be 0.02%, Mn be 1.2%, Ti be 0.03%, Li be 0.02%, Sn be 0.12%, Cu be 0.28%, Ni be 11.5%,
Cr is that 0.19%, Y is that 0.02%, La is that 0.14%, Tb is that 0.01%, Dy is that 0.01%, Ho is that 0.22%, Eu is that 0.02%, Er is
2.80%th, Zn is that 0.41%, Pb is 0.34%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 695 DEG C with 190 DEG C/min firing rate, melted 27 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 27 minutes, is cooled to room temperature using rate of temperature fall as 190 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 190 DEG C/min firing rate
Be heated to 1938 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, using rate of temperature fall as 190 DEG C/
Min speed is cooled to room temperature, obtains alloy material.
Step S04：Alloy material 27 hours described in temperature homogenisation between 500 DEG C.
Step S05：The extremely permanent deformation 5% of alloy material described in restrained stretching；
Step S06：Tempering in 20 hours is heated at a temperature of 465 DEG C to the alloy material.
Embodiment 7
A kind of airframe alloy, its raw material components include：
Sc be 0.07%, Mn be 0.7%, Ti be 0.04%, Li be 0.03%, Sn be 0.14%, Cu be 0.27%, Ni be 11.7%,
Cr is that 0.21%, Y is that 0.01%, La is that 0.12%, Tb is that 0.01%, Dy is that 0.02%, Ho is that 0.27%, Eu is that 0.027%, Er is
1.40%th, Zn is that 0.38%, Pb is 0.35%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 665 DEG C with 165 DEG C/min firing rate, melted 24 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 24 minutes, is cooled to room temperature using rate of temperature fall as 165 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 190 DEG C/min firing rate
Be heated to 1905 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, using rate of temperature fall as 165 DEG C/
Min speed is cooled to room temperature, obtains alloy material.
Step S04：Alloy material 22 hours described in temperature homogenisation between 496 DEG C.
Step S05：The extremely permanent deformation 5.5% of alloy material described in restrained stretching；
Step S06：Tempering in 6 hours is heated at a temperature of 462 DEG C to the alloy material.
Embodiment 8
A kind of airframe alloy, its raw material components include：
Sc is that 0.08%, Mn is that 0.8%, Ti is that 0.032%, Li is that 0.032%, Sn is that 0.08%, Cu is that 0.24%, Ni is
9.6%th, Cr be 0.24%, Y be 0.02%, La be 0.16%, Tb be 0.016%, Dy be 0.016%, Ho be 0.27%, Eu be 0.024%,
Er is that 2.40%, Zn is that 0.32%, Pb is 0.24%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 672 DEG C with 192 DEG C/min firing rate, melted 28 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 28 minutes, is cooled to room temperature using rate of temperature fall as 192 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 192 DEG C/min firing rate
Be heated to 1932 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, using rate of temperature fall as 192 DEG C/
Min speed is cooled to room temperature, obtains alloy material.
Step S04：Alloy material 28 hours described in temperature homogenisation between 491 DEG C.
Step S05：The extremely permanent deformation 3.5% of alloy material described in restrained stretching；
Step S06：Tempering in 7 hours is heated at a temperature of 452 DEG C to the alloy material.
Embodiment 9
A kind of airframe alloy, its raw material components include：
Sc is that 0.05%, Mn is that 1.1%, Ti is that 0.036%, Li is that 0.036%, Sn is that 0.09%, Cu is that 0.29%, Ni is
9.9%th, Cr is that 0.19%, Y is that 0.027%, La is that 0.18%, Tb is that 0.018%, Dy is that 0.018%, Ho is that 0.29%, Eu is
0.029%th, Er is that 2.90%, Zn is that 0.39%, Pb is 0.29%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 689 DEG C with 199 DEG C/min firing rate, melted 29 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 29 minutes, is cooled to room temperature using rate of temperature fall as 199 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 199 DEG C/min firing rate
Be heated to 1939 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, using rate of temperature fall as 199 DEG C/
Min speed is cooled to room temperature, obtains alloy material.
Step S04：Alloy material 29 hours described in temperature homogenisation between 499 DEG C.
Step S05：The extremely permanent deformation 4.5% of alloy material described in restrained stretching；
Step S06：Tempering in 18 hours is heated at a temperature of 459 DEG C to the alloy material.
Embodiment 10
A kind of airframe alloy, its raw material components include：
Sc is that 0.04%, Mn is that 1.4%, Ti is that 0.031%, Li is that 0.031%, Sn is that 0.11%, Cu is that 0.23%, Ni is
11.0%th, Cr is that 0.20%, Y is that 0.023%, La is that 0.19%, Tb is that 0.019%, Dy is that 0.019%, Ho is that 0.26%, Eu is
0.026%th, Er is that 2.81%, Zn is that 0.37%, Pb is 0.39%, and remaining is Al.
Its preparation method comprises the following steps：
Step S01：Li, Sn, Pb, Al are heated to 679 DEG C with 179 DEG C/min firing rate, melted 24 minutes.
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, fully melting is treated
Afterwards, stirring insulation 24 minutes, is cooled to room temperature using rate of temperature fall as 179 DEG C/min speed, obtains the thick embryo of alloy.
Step S03：By Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er with 179 DEG C/min firing rate
Be heated to 1929 DEG C melting, after vacuumizing add the thick embryo of alloy, make each component melting fully after, using rate of temperature fall as 179 DEG C/
Min speed is cooled to room temperature, obtains alloy material.
Step S04：Alloy material 24 hours described in temperature homogenisation between 479 DEG C.
Step S05：The extremely permanent deformation 4.7% of alloy material described in restrained stretching；
Step S06：Tempering in 19 hours is heated at a temperature of 449 DEG C to the alloy material.
Experimental example 1
The alloy material of the embodiment of the present invention 1 ~ 10 is compared with common fuselage with aluminium alloy, its results of property such as following table
1。
The performance comparision of table 1
From above-mentioned test example, the properties of alloy material of the present invention are above the common fuselage aluminium under equal conditions
Alloy, is more suitable for the aluminum alloy materials for airframe.
The preferred embodiments of the present invention and experimental example are these are only, is not intended to limit the invention, for this area
Technical staff for, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made appoints
What modification, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (10)
1. a kind of airframe alloy, it is characterised in that the mass percent including Sc is 0.01% ~ 0.08%, Mn quality
The mass percent that the mass percent that percentage is 0.06% ~ 1.5%, Ti is 0.03% ~ 0.04%, Li is 0.01% ~ 0.04%, Sn
Mass percent be 0.05% ~ 0.15%, Cu mass percent be 0.21% ~ 0.30%, Ni mass percent be 9.0% ~
12.0%th, the mass percent that Cr mass percent is 0.18% ~ 0.21%, La is 0.10% ~ 0.20%, Tb mass percent
It is that 0.01% ~ 0.02%, Zn mass percent is 0.31% ~ 0.42%, Y quality for 0.01% ~ 0.02%, Dy mass percent
The mass percent that the mass percent that percentage is 0.01% ~ 0.03%, Eu is 0.01% ~ 0.03%, Er is 0.50% ~ 3.0%, Ho
Mass percent be 0.20% ~ 0.30%, Pb mass percent be 0.10% ~ 0.50%, remaining is Al.
2. airframe alloy according to claim 1, it is characterised in that under Cr and Ni mass percent is met
Formula：9.2% ＜ Cr+Ni ＜ 12.1%.
3. airframe alloy according to claim 1, it is characterised in that Er mass percent is 0.50% ~
The mass percent that the mass percent that 2.0%, Eu mass percent are 0.01% ~ 0.02%, Ho is 0.25% ~ 0.30%, Pb is
0.20% ~ 0.50%, Y mass percent are 0.02% ~ 0.03%.
4. a kind of airframe alloy, it is characterised in that by mass percentage containing the following raw material component：Sc be 0.04%,
Mn is that 1.0%, Ti is that 0.03%, Li is that 0.03%, Sn is that 0.11%, Cu is that 0.24%, Ni is that 10.0%, Cr is that 0.20%, Y is
0.027%th, La is that 0.16%, Tb is that 0.014%, Dy is that 0.016%, Ho is that 0.29%, Eu is that 0.014%, Er is that 1.5%, Zn is
0.38%th, Pb is 0.20%, and remaining is Al.
5. the preparation method of a kind of airframe alloy as any one of claim 1 ~ 4, it is characterised in that prepare
Step includes：
Step S01：Li, Sn, Pb, Al melting is abundant；
Step S02：Under the molten metal bath liquid level that Zn is added to step S01, not with air contact, after after abundant melting, stir
Insulation 20 minutes ~ 30 minutes is mixed, room temperature is quickly cooled to using coolant, obtains alloy crude green body；
Step S03：Sc, Mn, Ti, Cu, Ni, Cr, Y, La, Tb, Dy, Ho, Eu, Er are heated and melted, alloy is added after vacuumizing
Crude green body, makes after each component melting fully, is cooled to room temperature with 150 DEG C/min ~ 200 DEG C/min rate of temperature fall, obtains alloy material
Material；
Step S04：Alloy material described in temperature homogenisation between 480 DEG C ~ 505 DEG C；
Step S05：The extremely permanent deformation 3% ~ 6% of alloy material described in restrained stretching；
Step S06：The alloy material is tempered.
6. the preparation method of airframe alloy according to claim 5, it is characterised in that described in step S01
Li, Sn, Pb, Al melting condition is：660 DEG C ~ 700 DEG C, melting 20 are heated to 150 DEG C/min ~ 200 DEG C/min firing rate
Minute ~ 30 minutes.
7. the preparation method of airframe alloy according to claim 5, it is characterised in that in step S02, described fast
The mode of quickly cooling but 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 to add
The condition of heat fusing is：1900 DEG C ~ 1950 DEG C are heated to 150 DEG C/min ~ 200 DEG C/min firing rate.
9. the preparation method of airframe alloy according to claim 5, it is characterised in that in step S04, described equal
The time of change is 20 hours ~ 30 hours.
10. the preparation method of airframe alloy according to claim 5, it is characterised in that described in step S06
The mode of tempering is：Heated 5 hours ~ 30 hours at a temperature of 440 DEG C ~ 470 DEG C.
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| JPH01132733A (en) * | 1987-11-17 | 1989-05-25 | Kasei Naoetsu:Kk | High damping aluminum alloy |
| JPH0433860B2 (en) * | 1987-03-10 | 1992-06-04 | Showa Aluminium Co Ltd | |
| CN104178666A (en) * | 2014-09-01 | 2014-12-03 | 浙江工贸职业技术学院 | Alloy for wing skins |
| CN105256176A (en) * | 2015-10-20 | 2016-01-20 | 安徽天祥空调科技有限公司 | High-strength dense light and thin aluminum alloy sheet for air conditioner radiator and manufacturing method for high-strength dense light and thin aluminum alloy sheet |
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| JPH0433860B2 (en) * | 1987-03-10 | 1992-06-04 | Showa Aluminium Co Ltd | |
| JPH01132733A (en) * | 1987-11-17 | 1989-05-25 | Kasei Naoetsu:Kk | High damping aluminum alloy |
| CN104178666A (en) * | 2014-09-01 | 2014-12-03 | 浙江工贸职业技术学院 | Alloy for wing skins |
| CN105256176A (en) * | 2015-10-20 | 2016-01-20 | 安徽天祥空调科技有限公司 | High-strength dense light and thin aluminum alloy sheet for air conditioner radiator and manufacturing method for high-strength dense light and thin aluminum alloy sheet |
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