CN108385003A - A kind of aerospace high-ductility corrosion aluminium alloy extrusions and preparation method thereof - Google Patents
A kind of aerospace high-ductility corrosion aluminium alloy extrusions and preparation method thereof Download PDFInfo
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- CN108385003A CN108385003A CN201810505728.8A CN201810505728A CN108385003A CN 108385003 A CN108385003 A CN 108385003A CN 201810505728 A CN201810505728 A CN 201810505728A CN 108385003 A CN108385003 A CN 108385003A
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- 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
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/026—Alloys based on aluminium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
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- 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
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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- 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
- C22F1/053—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 of alloys with zinc as the next major constituent
Abstract
A kind of aerospace high-ductility corrosion aluminium alloy extrusions and preparation method thereof, the present invention relates to a kind of aerospace high-ductility corrosion aluminium alloy extrusions and preparation method thereof, the problem of aerospace requirement being cannot be satisfied the purpose of the present invention is to solve existing aluminium alloy extrusions, aluminium alloy extrusions of the present invention includes that the melting raw material of Cu, Mg, Zn, Zr and Al are made, be by aluminium ingot, tough cathode, primary magnesium ingot, zinc ingot metal, aluminium zircaloy ingot be smelting, casting, homogenizing annealing, hot extrusion, quenching, stretching, timeliness are fabricated.The present invention is optimized by alloying component, ingot quality controls, multistage uniform treatment technology, extrusion forming technology, the twin-stage quenching of strenthen-toughening mechanizm and three-step aging technology, high-ductility corrosion aluminium alloy extrusions is produced, effectively cut down proximate matter residual stress by increasing tension aligning amount, improves the follow-up machining accuracy of proximate matter.Present invention application aluminium alloy extrusions preparation field.
Description
Technical field
The present invention relates to a kind of aerospace high-ductility corrosion aluminium alloy extrusions and preparation method thereof.
Background technology
With the fast development of China's aerospace cause, harsher requirement is proposed to basic material.It is requiring
Extrudate sectional dimension increases, while cut lengths lengthens, it is desirable that extrudate performance is matched with more high-strength tenacity.It needs
Develop tensile strength >=650MPa, yield strength >=610MPa, compression yield strength >=620MPa, elongation percentage >=8% breaks
Split toughness >=33KIC/MPam1/2, sectional area >=50cm of the high overall target of conductivity >=37%IACS2, length >=12m
Proximate matter, and form stabilized production technology, tensile strength, toughness and the corrosion resistance of existing aluminium alloy extrusions are difficult simultaneous
It cares for, if tensile strength is high, toughness and corrosion resistance are relatively poor, and if toughness and excellent anti-corrosion performance, tension are strong
It spends low.In order to solve the contradiction between intensity and anti-stress corrosion performance, the Cina of Aircraft Company of Israel in 1974 is proposed
A kind of three-step aging technique --- regression and re-ageing (RRA) treatment process.Alloy has crystalline substance similar with T6 states after RRA is handled
Inner tissue and crystal boundary structure similar with T7X states.But since the characteristics of this technique is that second level aging temp is higher, when recurrence
Between it is very short, thus be difficult applied in actual industrial.
Invention content
The purpose of the present invention is to solve existing aluminium alloy extrusions cannot be satisfied aerospace requirement, can not be simultaneously
The problem of meeting high-tensile, high tenacity and corrosion resistance and good, provides a kind of aerospace high-ductility corrosion aluminium alloy
Proximate matter and preparation method thereof.
It is Cu that a kind of aerospace of the present invention, which is by element mass percentage with high-ductility corrosion aluminium alloy extrusions,：1.9%
~2.2%, Mg：2.2%~2.6%, Zn：9.2%~9.8%, Zr：0.10%~0.13% and surplus be Al melting raw material
It is made.
A kind of aerospace of the present invention is followed the steps below with the preparation method of high-ductility corrosion aluminium alloy extrusions：
One, it is Cu that aluminium alloy extrusions, which is by element mass percentage,：1.9%~2.2%, Mg：2.2%~2.6%,
Zn：9.2%~9.8%, Zr：0.10%~0.13% and surplus be Al ratio weigh aluminium ingot, tough cathode, primary magnesium ingot, zinc
Ingot, aluminium zircaloy ingot are as raw material, and then the melting raw material in smelting furnace, obtains molten aluminium alloy；
Two, the molten aluminium alloy that step 1 obtains is cast as round ingot casting；
Three, the casting oxide skin for removing circle ingot casting at ambient temperature, obtains the aluminium alloy round cast ingot of scale removal；
Four, the aluminium alloy round cast ingot of scale removal is kept the temperature into 12h under conditions of temperature is 420 DEG C~440 DEG C, then
60h is kept the temperature under conditions of being warming up to 470 DEG C, cooled to room temperature after coming out of the stove, the circle ingot casting after being annealed；
Five, the circle ingot casting after annealing is put into induction heater, is heated to 420 DEG C~440 DEG C, obtains hot extruded shapes
Blank；
Six, under conditions of temperature is 420 DEG C~440 DEG C, the hot extruded shapes base that is obtained step 5 using extruder
Material is squeezed into proximate matter, obtains hot extruded shapes；
Seven, hot extruded shapes are put into resistance-heated furnace, at 450~460 DEG C keep the temperature 2h, be warming up to 470 DEG C heat preservation 2~
6h, quenching treatment, water cooling of coming out of the stove to room temperature；
Eight, step 7 treated aluminium alloy extrusions is subjected to stretching-machine stretcher leveling, obtains the conjunction of the aluminium after stretcher leveling
Metal type material；
Nine, the aluminium alloy extrusions after stretcher leveling is subjected to roll straightening, obtains the aluminium alloy extrusions after roll straightening；
Ten, the aluminium alloy extrusions after roll straightening is put into the resistance-heated furnace that temperature is 120 DEG C and heats 29h~31h,
Level-one ageing treatment is carried out, cooled to room temperature of coming out of the stove obtains the proximate matter after level-one timeliness；
11, the proximate matter after level-one timeliness is put into 24 meters of roller-bottom type glowing furnaces that temperature is 175 DEG C and keeps the temperature 120min
~200min carries out secondary time effect processing, and then water cooling to room temperature, obtains the proximate matter after secondary time effect；
12, the proximate matter after secondary time effect is put by section material frame in the resistance-heated furnace that temperature is 120 DEG C and heats 29h
~31h carries out three-step aging processing, and water cooling to room temperature obtains the proximate matter after three-step aging, that is, completes；
The section material frame includes ladder shape frame body and grid body；The ladder shape frame body is by two vertical rectangle steels
Pipe and more lateral rectangular steel pipes are constituted；The both ends of lateral rectangular steel pipe weld together with vertical rectangular steel pipe respectively；Vertically
Multiple through-holes are offered on rectangular steel pipe and lateral rectangular steel pipe；
The grid body is rectangular configuration, and grid body end face is welded on one of lateral rectangular steel pipe lower surface,
Other end is welded on lateral rectangular steel pipe lower surface adjacent thereto；It is arranged with per another adjacent lateral rectangular steel pipe more
A grid body.
The present invention utilizes 24 meters of roller-bottom type glowing furnaces of aluminum alloy plate materials quenching, designs the material rack special of proximate matter, into
The secondary time effect of row proximate matter is handled, that is, meets the regression effect of secondary time effect, and ensures that proximate matter is not sent out after two level high-temperature water cooling
Raw apparent deformation.The material rack special of proximate matter is designed to the hollow out form of many places punching, by proximate matter from first to last many places thin wire
It is fixed on rack, it is unlikely after top and bottom all can fully carry out water cooling, and guarantee proximate matter is water cooled when ensureing that proximate matter is come out of the stove
In the apparent deformation of generation.
The present invention is optimized by alloying component and three-step aging, has produced while having had tensile strength height and rotproofness
The excellent aluminium alloy extrusions of energy, the endwise tensile strength 670-682N/mm of proximate matter produced by the present invention2；Provide Non-proportional extension
Intensity 644-647N/mm2, elongation after fracture 11.3-13.9%；Compressive yield strength 652-661MPa is surveyed according to GB/T 4161
The fracture toughness for trying proximate matter is 33.2MPam1/2, according to GB/T 12966-2008 37.2~38.2%IACS of testing conductivity,
Peeling Corrosion, which is tested, according to HB 5455 is not less than EB grades.
Description of the drawings
Fig. 1 is metallograph of 1 aluminium alloy round cast ingot of embodiment in 200nm；
Fig. 2 is metallograph of 1 aluminium alloy round cast ingot of embodiment in 100nm；
Fig. 3 is SEM organization chart of 1 aluminium alloy cast ingot of embodiment at 20 μm；
Fig. 4 is SEM organization chart of 1 aluminium alloy cast ingot of embodiment at 10 μm；
Fig. 5 is the SEM photograph that 1 aluminium alloy cast ingot of embodiment homogenizes circle ingot casting after annealing；
Fig. 6 is the TEM photos that 1 aluminium alloy cast ingot of embodiment homogenizes circle ingot casting after annealing；
Fig. 7 is SEM photograph of 1 hot extruded shapes of embodiment at 10 μm；
Fig. 8 is SEM photograph of 1 hot extruded shapes of embodiment at 2 μm；
Fig. 9 is 1 proximate matter of embodiment through double_stage guide treated metallograph；
Figure 10 is 1 proximate matter of embodiment through double_stage guide treated SEM photograph；
Figure 11 be 1 proximate matter of embodiment after solution treatment in 1 μm of TEM photos；
Figure 12 is for 1 proximate matter of embodiment in the TEM photos of 50nm after solution treatment；
Figure 13 is 1 proximate matter secondary time effect shove charge photo of embodiment；
Figure 14 is 1 proximate matter secondary time effect material rack special photo of embodiment；
Figure 15 is the TEM photos of proximate matter crystal boundary after 1 three-step aging of embodiment；
Figure 16 is the transgranular TEM photos of proximate matter after 1 three-step aging of embodiment；
Figure 17 is the material rack special structural schematic diagram of proximate matter of the present invention.
Specific implementation mode
Technical solution of the present invention is not limited to the specific implementation mode of act set forth below, further include each specific implementation mode it
Between arbitrary combination.
Specific implementation mode one：A kind of aerospace of present embodiment is by element quality with high-ductility corrosion aluminium alloy extrusions
Percentage composition is Cu：1.9%~2.2%, Mg：2.2%~2.6%, Zn：9.2%~9.8%, Zr：0.10%~0.13% He
Surplus is made of the melting raw material of Al.
The impurity elements such as Fe and Si in present embodiment derive from aluminium ingot, impurity F e≤0.08% in aluminium alloy extrusions,
Fe≤0.10%, other single impurity≤0.05%, the impurity within the scope of this do not influence the performance of aluminium alloy foil material.
The endwise tensile strength 670-682N/mm of the proximate matter of present embodiment manufacture2；Proof strength of non-proportional 644-
647N/mm2, elongation after fracture 11.3-13.9%；Compressive yield strength 652-661MPa tests proximate matter according to GB/T 4161
Fracture toughness is 33.2MPam1/2, according to GB/T 12966-2008 37.2~38.2%IACS of testing conductivity, according to HB
5455 test Peeling Corrosions are not less than EB grades.
Specific implementation mode two：A kind of aerospace of present embodiment is pressed with the preparation method of high-ductility corrosion aluminium alloy extrusions
It is carried out according to following steps：
One, it is Cu that aluminium alloy extrusions, which is by element mass percentage,：1.9%~2.2%, Mg：2.2%~2.6%,
Zn：9.2%~9.8%, Zr：0.10%~0.13% and surplus be Al ratio weigh aluminium ingot, tough cathode, primary magnesium ingot, zinc
Ingot, aluminium zircaloy ingot are as raw material, and then the melting raw material in smelting furnace, obtains molten aluminium alloy；
Two, the molten aluminium alloy that step 1 obtains is cast as round ingot casting；
Three, the casting oxide skin for removing circle ingot casting at ambient temperature, obtains the aluminium alloy round cast ingot of scale removal；
Four, the aluminium alloy round cast ingot of scale removal is kept the temperature into 12h under conditions of temperature is 420 DEG C~440 DEG C, then
60h is kept the temperature under conditions of being warming up to 470 DEG C, cooled to room temperature after coming out of the stove, the circle ingot casting after being annealed；
Five, the circle ingot casting after annealing is put into induction heater, is heated to 420 DEG C~440 DEG C, obtains hot extruded shapes
Blank；
Six, under conditions of temperature is 420 DEG C~440 DEG C, the hot extruded shapes base that is obtained step 5 using extruder
Material is squeezed into proximate matter, obtains hot extruded shapes；
Seven, hot extruded shapes are put into resistance-heated furnace, at 450~460 DEG C keep the temperature 2h, be warming up to 470 DEG C heat preservation 2~
6h, quenching treatment, water cooling of coming out of the stove to room temperature；
Eight, step 7 treated aluminium alloy extrusions is subjected to stretching-machine stretcher leveling, obtains the conjunction of the aluminium after stretcher leveling
Metal type material；
Nine, the aluminium alloy extrusions after stretcher leveling is subjected to roll straightening, obtains the aluminium alloy extrusions after roll straightening；
Ten, the aluminium alloy extrusions after roll straightening is put into the resistance-heated furnace that temperature is 120 DEG C and heats 29h~31h,
Level-one ageing treatment is carried out, cooled to room temperature of coming out of the stove obtains the proximate matter after level-one timeliness；
11, the proximate matter after level-one timeliness is put into 24 meters of roller-bottom type glowing furnaces that temperature is 175 DEG C and keeps the temperature 120min
~200min carries out secondary time effect processing, and then water cooling to room temperature, obtains the proximate matter after secondary time effect；
12, the proximate matter after secondary time effect is put by section material frame in the resistance-heated furnace that temperature is 120 DEG C and heats 29h
~31h carries out three-step aging processing, and water cooling to room temperature obtains the proximate matter after three-step aging, that is, completes；
The section material frame includes ladder shape frame body 1 and grid body 2；The ladder shape frame body 1 is by two vertical squares
Shape steel pipe 3 and Duo Gen transverse directions rectangular steel pipe 4 are constituted；The both ends of lateral rectangular steel pipe 4 are welded on one with vertical rectangular steel pipe 3 respectively
It rises；Multiple through-holes 5 are offered on vertical rectangular steel pipe 3 and lateral rectangular steel pipe 4；
The grid body 2 is rectangular configuration, and 2 end face of grid body is welded on 4 following table of one of lateral rectangular steel pipe
Face, other end are welded on 4 lower surface of lateral rectangular steel pipe adjacent thereto；It is divided into per another adjacent lateral rectangular steel pipe 4
It is equipped with multiple grid bodies 2.
Present embodiment utilizes 24 meters of roller-bottom type glowing furnaces of aluminum alloy plate materials quenching, designs the PP Pipe Compound of proximate matter
Frame carries out the secondary time effect processing of proximate matter, that is, meets the regression effect of secondary time effect, and ensures proximate matter after two level high-temperature water cooling
Do not occur obviously to deform.The material rack special of proximate matter is designed to the hollow out form of many places punching, and by proximate matter, from first to last many places are used carefully
Iron wire is fixed on rack, when ensureing that proximate matter is come out of the stove, after top and bottom all can fully carry out water cooling, and guarantee proximate matter is water cooled,
It is unlikely to occur obviously to deform.
Present embodiment is optimized by alloying component, ingot quality controls, multistage uniform treatment technology, extrusion forming skill
Art, strenthen-toughening mechanizm technology have produced high-ductility corrosion aluminium alloy extrusions, longitudinal tension of the proximate matter of present embodiment manufacture
Intensity 670-682N/mm2；Proof strength of non-proportional 644-647N/mm2, elongation after fracture 11.3-13.9%；Resistance to compression is surrendered
Intensity 652-661MPa, the fracture toughness that proximate matter is tested according to GB/T 4161 are 33.2MPam1/2, according to GB/T 12966-
2008 37.2~38.2%IACS of testing conductivity test Peeling Corrosion according to HB 5455 and are not less than EB grades.
Specific implementation mode three：Present embodiment is unlike specific implementation mode two：Aluminium alloy extrusions is by element
Mass percentage is Cu：2.0%, Mg：2.5%, Zn：9.6%, Zr：0.12% and surplus be Al ratio weigh aluminium
Ingot, tough cathode, primary magnesium ingot, zinc ingot metal, aluminium zircaloy ingot are as raw material.Other are the same as one or two specific embodiments.
Specific implementation mode four：Unlike one of present embodiment and specific implementation mode two or three：Step 1 is in temperature
Degree is melting raw material 5h~9h in 720 DEG C~760 DEG C of smelting furnace.Other are identical as specific implementation mode two or three.
Specific implementation mode five：Unlike one of present embodiment and specific implementation mode two to four：Step 2 is being cast
Make that temperature is 720 DEG C~760 DEG C, casting speed is 30mm/min~70mm/min, cooling water temperature is 10 DEG C~20 DEG C and cold
But water intensity is 20m3/ h~60m3Molten aluminium alloy is cast as round ingot casting under conditions of/h.Other and specific implementation mode two
It is identical to one of four.
Specific implementation mode six：Unlike one of present embodiment and specific implementation mode one to five：In step 5
Temperature is squeezed under conditions of being 430 DEG C.Other are identical as one of specific implementation mode one to five.
Specific implementation mode seven：Unlike one of present embodiment and specific implementation mode two to six：In step 7
2h is kept the temperature under the conditions of 450 DEG C, is warming up to 470 DEG C of heat preservation 4h.Other are identical as one of specific implementation mode two to six.
Specific implementation mode eight：Unlike one of present embodiment and specific implementation mode two to seven：By aluminium in step
Alloy profile carries out stretching-machine stretcher leveling, and control amount of tension is 2.7%~3.2%；Other and specific implementation mode two to seven
One of it is identical.
Specific implementation mode nine：Unlike one of present embodiment and specific implementation mode two to eight：Add in step 10
Hot 30h carries out level-one ageing treatment.Other are identical as one of specific implementation mode two to eight.
Specific implementation mode ten：Unlike one of present embodiment and specific implementation mode two to nine：In step 11
160min is kept the temperature, secondary time effect processing is carried out.Other are identical as one of specific implementation mode two to nine.
Specific implementation mode 11：Unlike one of present embodiment and specific implementation mode two to ten：Step 12
Middle heating 30h carries out three-step aging processing.Other are identical as one of specific implementation mode two to ten.
Beneficial effects of the present invention are verified using following embodiment：
Embodiment one：A kind of aerospace is followed the steps below with the preparation method of high-ductility corrosion aluminium alloy extrusions：
One, it is Cu to press element mass percentage：2.0%, Mg：2.6%, Zn：9.8%, Zr：0.12% and surplus be Al
Ratio weigh aluminium ingot, tough cathode, primary magnesium ingot, zinc ingot metal, aluminium zircaloy ingot as raw material, be then 750 DEG C molten in temperature
Melting raw material 8h, obtains molten aluminium alloy in furnace；
Two, casting temperature is 740 DEG C, casting speed 50mm/min, cooling water temperature are 15 DEG C and cooling water intensity
For 40m3Molten aluminium alloy is cast as round ingot casting under conditions of/h；
Three, the casting oxide skin for removing circle ingot casting at ambient temperature, obtains the aluminium alloy round cast ingot of scale removal；
Four, the aluminium alloy round cast ingot of scale removal is kept the temperature into 12h under conditions of temperature is 440 DEG C, then heated to
60h is kept the temperature under conditions of 470 DEG C, cooled to room temperature after coming out of the stove, the circle ingot casting after being annealed；
Five, the circle ingot casting after annealing is put into induction heater, is heated to 420 DEG C~440 DEG C, obtains hot extruded shapes
Blank；
Six, under conditions of temperature is 430 DEG C, the hot extruded shapes blank that step 5 obtains is squeezed into using extruder
Proximate matter obtains hot extruded shapes；
Seven, hot extruded shapes are put into resistance-heated furnace, 2h is kept the temperature under the conditions of 450 DEG C, be warming up to 470 DEG C of heat preservations
4h, quenching treatment, water cooling of coming out of the stove to room temperature；
Eight, step 7 treated aluminium alloy extrusions is subjected to stretching-machine stretcher leveling, obtains the conjunction of the aluminium after stretcher leveling
The amount of tension control of metal type material, stretcher leveling is 2.7%~3.2%；
Nine, the aluminium alloy extrusions after stretcher leveling is subjected to roll straightening, obtains the aluminium alloy extrusions after roll straightening；
Ten, the aluminium alloy extrusions after roll straightening is put into the resistance-heated furnace that temperature is 120 DEG C and heats 30h, carried out
Level-one ageing treatment, cooled to room temperature of coming out of the stove obtain the proximate matter after level-one timeliness；
11, the proximate matter after level-one timeliness is put into 24 meters of roller-bottom type glowing furnaces that temperature is 175 DEG C and keeps the temperature 180min,
Secondary time effect processing is carried out, then water cooling to room temperature, obtains the proximate matter after secondary time effect；
12, the proximate matter after secondary time effect is put by section material frame in the resistance-heated furnace that temperature is 120 DEG C and heats 29h
~31h carries out three-step aging processing, and water cooling to room temperature obtains the proximate matter after three-step aging, that is, completes；
The section material frame includes ladder shape frame body 1 and grid body 2；The ladder shape frame body 1 is by two vertical squares
Shape steel pipe 3 and Duo Gen transverse directions rectangular steel pipe 4 are constituted；The both ends of lateral rectangular steel pipe 4 are welded on one with vertical rectangular steel pipe 3 respectively
It rises；Multiple through-holes 5 are offered on vertical rectangular steel pipe 3 and lateral rectangular steel pipe 4；
The grid body 2 is rectangular configuration, and 2 end face of grid body is welded on 4 following table of one of lateral rectangular steel pipe
Face, other end are welded on 4 lower surface of lateral rectangular steel pipe adjacent thereto；It is divided into per another adjacent lateral rectangular steel pipe 4
It is equipped with multiple grid bodies 2.
By the superpower high-ductility corrosion aluminium alloy extrusions of aerospace manufactured in the present embodiment, according to GB/T228《Metal material
Room temperature tensile properties test method》The endwise tensile strength 670N/mm of the experimental test proximate matter2, it is specified that nonproportional cyclic straining
644N/mm2, elongation after fracture 13.9%, compressive yield strength 652N/mm2, the fracture of test proximate matter is provided according to GB/T 4161
Toughness 34.2Pam1/2, according to 12,966 37.4~38.2%IACS of testing conductivity of GB/T, test is provided according to HB5455
The exfoliation Corrosion of material is not less than EB grades.
Embodiment two：A kind of aerospace is followed the steps below with the preparation method of high-ductility corrosion aluminium alloy extrusions：
One, it is Cu to press element mass percentage：2.0%, Mg：2.5%, Zn：9.6%, Zr：0.12% and surplus be Al
Ratio weigh aluminium ingot, tough cathode, primary magnesium ingot, zinc ingot metal, aluminium zircaloy ingot as raw material, be then 750 DEG C molten in temperature
Melting raw material 8h, obtains molten aluminium alloy in furnace；
Two, casting temperature is 740 DEG C, casting speed 50mm/min, cooling water temperature are 15 DEG C and cooling water intensity
For 40m3Molten aluminium alloy is cast as round ingot casting under conditions of/h；
Three, the casting oxide skin for removing circle ingot casting at ambient temperature, obtains the aluminium alloy round cast ingot of scale removal；
Four, the aluminium alloy round cast ingot of scale removal is kept the temperature into 12h under conditions of temperature is 430 DEG C, then heated to
60h is kept the temperature under conditions of 470 DEG C, cooled to room temperature after coming out of the stove, the circle ingot casting after being annealed；
Five, the circle ingot casting after annealing is put into induction heater, is heated to 430 DEG C, obtain hot extruded shapes blank；
Six, under conditions of temperature is 430 DEG C, the hot extruded shapes blank that step 5 obtains is squeezed into using extruder
Proximate matter obtains hot extruded shapes；
Seven, hot extruded shapes are put into resistance-heated furnace, 2h is kept the temperature under the conditions of 450 DEG C, be warming up to 470 DEG C of heat preservations
4h, quenching treatment, water cooling of coming out of the stove to room temperature；
Eight, step 7 treated aluminium alloy extrusions is subjected to stretching-machine stretcher leveling, obtains the conjunction of the aluminium after stretcher leveling
The amount of tension control of metal type material, stretcher leveling is 2.7%~3.2%；
Nine, the aluminium alloy extrusions after stretcher leveling is subjected to roll straightening, obtains the aluminium alloy extrusions after roll straightening；
Ten, the aluminium alloy extrusions after roll straightening is put into the resistance-heated furnace that temperature is 120 DEG C and heats 30h, carried out
Level-one ageing treatment, cooled to room temperature of coming out of the stove obtain the proximate matter after level-one timeliness；
11, the proximate matter after level-one timeliness is put into 24 meters of roller-bottom type glowing furnaces that temperature is 175 DEG C and keeps the temperature 160min,
Secondary time effect processing is carried out, then water cooling to room temperature, obtains the proximate matter after secondary time effect；
12, the proximate matter after secondary time effect is put by section material frame in the resistance-heated furnace that temperature is 120 DEG C and heats 29h
~31h carries out three-step aging processing, and water cooling to room temperature obtains the proximate matter after three-step aging, that is, completes；
The section material frame includes ladder shape frame body 1 and grid body 2；The ladder shape frame body 1 is by two vertical squares
Shape steel pipe 3 and Duo Gen transverse directions rectangular steel pipe 4 are constituted；The both ends of lateral rectangular steel pipe 4 are welded on one with vertical rectangular steel pipe 3 respectively
It rises；Multiple through-holes 5 are offered on vertical rectangular steel pipe 3 and lateral rectangular steel pipe 4；
The grid body 2 is rectangular configuration, and 2 end face of grid body is welded on 4 following table of one of lateral rectangular steel pipe
Face, other end are welded on 4 lower surface of lateral rectangular steel pipe adjacent thereto；It is divided into per another adjacent lateral rectangular steel pipe 4
It is equipped with multiple grid bodies 2.
Aerospace manufactured in the present embodiment is with superpower high-ductility corrosion aluminium alloy extrusions according to GB/T228《Metal material room
Warm Erichsen test method》The endwise tensile strength 682N/mm of experimental test proximate matter2；Proof strength of non-proportional 647N/
mm2, elongation after fracture 11.3%；Compressive yield strength 661MPa, the fracture toughness that proximate matter is tested according to GB/T 4161 are
33.2MPa·m1/2, according to GB/T 12966-2008 37.2~37.8%IACS of testing conductivity, tested and shelled according to HB 5455
It falls corrosion and is not less than EB grades.
The metallograph of the present embodiment aluminium alloy round cast ingot is as illustrated in fig. 1 and 2, by Fig. 1 and 2 it is found that as cast condition sample metallographic
There are a degree of segregation phenomena, the interior decorative pattern pattern that white is presented of crystal grain, the few transgranular regions of the second phase segregation in tissue
Corrode shallow white, the close grain boundaries of segregation heavy corrosion depth are grey, and there are a large amount of second phases to be corroded as black for grain boundaries.Through
Statistics, as cast condition sample average crystallite dimension are wide 76.8 ± 7.5 μm, grow 77.9 ± 7.4 μm, and crystal grain is relatively fine.
The SEM tissues of aluminium alloy cast ingot are as shown in Figure 3 and Figure 4, it can be found that being corresponding with metallographic structure, in crystal boundary
Place is dispersed with the second phase, and high power close to the position of crystal boundary the results show that have a large amount of tiny acicular second distributed mutuallies, this and metallographic
It is consistent to there is white decorative pattern for intra-die in tissue, i.e., due near crystal boundary the second phase segregation be corroded gray, do not analyse
It is white to go out or less interior zone is precipitated.The EDS analyses of the second phase of typical case are as shown in table 1 in Fig. 4, it is found that as cast condition is closed
Second phase present in payment organization is mainly Al-Zn-Mg-Cu eutectic phases, S (Al2CuMg) phase, η (MgZn2) phase.Use Image
200 times of pictures of J softwares pair count, it is found that the second phase accounting is 10.87 ± 0.35%.
1 cast alloy the second phase EDS analysis results (at%) of table
7000 be that the purposes of alloy Homogenization Treatments is to promote coarse primary solidification precipitated phase back dissolving, this external demand is in height
Temperature is lower to promote Al3The disperse educt of Zr particles, this mutually in subsequent deformation processing and heat treatment process can pinning crystal boundary, suppression
System recrystallization, improves alloy property.Al3The higher temperature range of Zr nucleation rates is 420~450 DEG C.Therefore Al in order to balance3Zr
The back dissolving of the disperse educt of particle and a solidifying phase carries out the first order homogenizing annealing of 420 DEG C~440 DEG C heat preservation 12h
After processing, the high-temperature process of 470 DEG C of heat preservation 60h, cooled to room temperature after coming out of the stove are carried out.Circle ingot casting after homogenizing annealing
SEM photograph such as Fig. 5, TEM photos are as shown in fig. 6, as shown in Figure 5, precipitated phase back dissolving is abundant in being organized after Homogenization Treatments, as cast condition
The eutectic structure of alloy sheet stratiform completely disappears only fragmentary white phase residual, shows that it is richness Fe phases by energy spectrum analysis,
The quantity of rich Fe phases with distribution not as extending with for homogenization time significantly changes, after homogenizing annealing, the crystalline substance of alloy
Significant changes do not occur for particle size.As seen from Figure 6, a large amount of Al are precipitated during ingot homogenization3Zr spheroidal particles, it is total with matrix
Lattice, strong pinning dislocation and crystal boundary hinder dislocation motion and crystal boundary migration, with what is recrystallized in strong inhibition hot procedure
Effect improves the comprehensive performance of proximate matter end-state.
The SEM photograph of hot extruded shapes is as shown in Figure 7 and Figure 8, by Fig. 7 and Fig. 8 it is found that existing in As-extruded alloy big
The second phase being distributed along the direction of extrusion is measured, typical case's the second phase EDS analyses are as shown in table 2.Existing Main Second Phase has, and A is η+S
Mixed phase, B are Al7Cu2Fe phases, C is η phases.It is counted using 500 times of pictures of Image J softwares pair, finds the second phase accounting
It is 8.35 ± 0.49%.
The EDS analysis results (at%) of 2 the second phase of extrudate of table
Using twin-stage quenching technical, first order solid solubility temperature is relatively low, can discharge more deformation energy storage, and it is solid to reduce high temperature
The recrystallization driving force of molten processing makes proximate matter retain the Deformation structure of higher proportion, and the second level uses high-temperature process, ensures alloy
The abundant back dissolving of second phase improves the intensity and fracture toughness of proximate matter to matrix, the recrystallized structure accounting after single-stage is dissolved
It is 33%~45%, the recrystallized structure accounting after double_stage guide is 13%~25%, hence it is evident that is reduced.It is handled through double_stage guide
Metallograph and SEM photograph such as Fig. 9 and Figure 10 afterwards.From Fig. 9 and Figure 10 it is found that being handled through double_stage guide, the second phase back dissolving is filled
Point, only remaining a small amount of richness the second phases of Fe.
As is illustrated by figs. 11 and 12, even tissue, intra-die has Al to TEM photos after solution treatment3Zr、Al3Ti disperses
Phase, size about 10~15nm.Al3Zr、Al3Ti plays the role of strong pinning dislocation, effectively improves the intensity of alloy.
It needs to carry out tension force stretching after proximate matter quenching, be controlled according to conventional amount of tension 1.5%~3.0%, the remnants of proximate matter are answered
Power is larger, unfavorable to subsequent machining, and the present invention controls the amount of tension of proximate matter 2.7%~3.2%, and residual stress obtains
Effectively control, by original maximum stress 98MPa, is reduced to maximum stress 53MPa.
7000 line aluminium alloys are typical precipitation strengthening alloys, are one of primary structural materials of aircraft industry.7000 systems
After the processing of 6 peak timeliness of aluminum alloy T, transgranular precipitated phase is that the tiny areas GP and η ' phases is precipitated, and obtains maximum reinforcing effect, but T6 shapes
The anti-stress corrosion performance of alloy is poor under state.Although anti-stress corrosion performance, meeting can be improved using two-stage time effect system
Make the strength reduction 10%~15% of alloy.The present embodiment utilizes 24 meters of roller-bottom type glowing furnaces of aluminum alloy plate materials quenching, if
The material rack special of proximate matter is counted out, the secondary time effect processing of proximate matter is carried out, that is, meets the regression effect of secondary time effect, and ensure proximate matter
Do not occur obviously to deform after two level high-temperature water cooling.The material rack special pictorial diagram of proximate matter is as shown in figure 14, and structural schematic diagram is as schemed
Shown in 17, rack is designed to the hollow out form of many places punching, and by proximate matter, from first to last many places are fixed on thin wire on rack, protects
When card proximate matter is come out of the stove, after top and bottom all can fully carry out water cooling, and guarantee proximate matter is water cooled, it is unlikely to occur obviously to deform.
After three-step aging shown in TEM photos Figure 15 and Figure 16 of proximate matter, as shown in Figure 15, grain boundaries precipitated phase is and matrix
η phases in non-symbiosis and epibiosis, in interrupted chainlike distribution avoid forming anodic attack channel at grain boundary sites, improve alloy
Corrosion resistance.
Transgranular there is the corynebacterium of even dispersion and discoid precipitated phase as shown in Figure 16, size is in 10nm or less.It is main
If the η phases and η ' phases of even dispersion, can greatly improve alloy strength.
Performance (intensity highest state) test result after the present embodiment level-one timeliness is as shown in table 3, as shown in Table 3,
After level-one timeliness, the tensile strength of proximate matter is very high, has reached 756MPa, but fracture toughness and corrosion resistance are slightly weak, therefore
The application has carried out secondary time effect and three-step aging again, has finally obtained while having met high-tensile, high tenacity and corrosion-resistant
The good proximate matter of performance.
The performance of 3 proximate matter peak timeliness of table
The present embodiment is optimized by alloying component and three-step aging, has produced while having had tensile strength high and rotproofness
The aluminium alloy extrusions haveing excellent performance, the endwise tensile strength 670-682N/mm of the proximate matter of the present embodiment manufacture2；Provide disproportional
Extension strength 644-647N/mm2, elongation after fracture 11.3-13.9%；Compressive yield strength 652-661MPa, according to GB/T
The fracture toughness of 4161 test proximate matters is 33.2MPam1/2, according to GB/T 12966-2008 testing conductivities 37.2~
38.2%IACS tests Peeling Corrosion according to HB 5455 and is not less than EB grades.
Claims (10)
1. a kind of aerospace high-ductility corrosion aluminium alloy extrusions, it is characterised in that the aluminium alloy extrusions is by element quality percentage
Content is Cu：1.9%~2.2%, Mg：2.2%~2.6%, Zn：9.2%~9.8%, Zr：0.10%~0.13% and surplus
It is made of the melting raw material of Al.
2. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions as described in claim 1, it is characterised in that
The preparation method follows the steps below：
One, it is Cu that aluminium alloy extrusions, which is by element mass percentage,：1.9%~2.2%, Mg：2.2%~2.6%, Zn：
9.2%~9.8%, Zr：0.10%~0.13% and surplus be Al ratio weigh aluminium ingot, tough cathode, primary magnesium ingot, zinc ingot metal,
Aluminium zircaloy ingot is as raw material, and then the melting raw material in smelting furnace, obtains molten aluminium alloy；
Two, the molten aluminium alloy that step 1 obtains is cast as round ingot casting；
Three, the casting oxide skin for removing circle ingot casting at ambient temperature, obtains the aluminium alloy round cast ingot of scale removal；
Four, the aluminium alloy round cast ingot of scale removal is kept the temperature into 12h under conditions of temperature is 420 DEG C~440 DEG C, then heated up
60h is kept the temperature under conditions of to 470 DEG C, cooled to room temperature after coming out of the stove, the circle ingot casting after being annealed；
Five, the circle ingot casting after annealing is put into induction heater, is heated to 420 DEG C~440 DEG C, obtains hot extruded shapes base
Material；
Six, under conditions of temperature is 420 DEG C~440 DEG C, the hot extruded shapes blank that step 5 obtains is squeezed using extruder
It is pressed into proximate matter, obtains hot extruded shapes；
Seven, hot extruded shapes are put into resistance-heated furnace, 2h are kept the temperature at 450~460 DEG C, be warming up to 470 DEG C of 2~6h of heat preservation,
Quenching treatment, water cooling of coming out of the stove to room temperature；
Eight, step 7 treated aluminium alloy extrusions is subjected to stretching-machine stretcher leveling, obtains the aluminium alloy type after stretcher leveling
Material；
Nine, the aluminium alloy extrusions after stretcher leveling is subjected to roll straightening, obtains the aluminium alloy extrusions after roll straightening；
Ten, the aluminium alloy extrusions after roll straightening is put into the resistance-heated furnace that temperature is 120 DEG C and heats 29h~31h, carried out
Level-one ageing treatment, cooled to room temperature of coming out of the stove obtain the proximate matter after level-one timeliness；
11, by the proximate matter after level-one timeliness be put into temperature be heat preservation 120min in 175 DEG C of 24 meters of roller-bottom type glowing furnaces~
200min carries out secondary time effect processing, and then water cooling to room temperature, obtains the proximate matter after secondary time effect；
12, by the proximate matter after secondary time effect by section material frame be put into temperature be heating 29h in 120 DEG C of resistance-heated furnace~
31h carries out three-step aging processing, and water cooling to room temperature obtains the proximate matter after three-step aging, that is, completes；
The section material frame includes ladder shape frame body (1) and grid body (2)；The ladder shape frame body (1) is vertical by two
Rectangular steel pipe (3) and more lateral rectangular steel pipes (4) are constituted；The both ends of lateral rectangular steel pipe (4) respectively with vertical rectangular steel pipe
(3) weld together；Multiple through-holes (5) are offered on vertical rectangular steel pipe (3) and lateral rectangular steel pipe (4)；
The grid body (2) is rectangular configuration, and grid body (2) end face is welded under one of lateral rectangular steel pipe (4)
Surface, other end are welded on lateral rectangular steel pipe (4) lower surface adjacent thereto；Per another adjacent lateral rectangular steel pipe
(4) multiple grid bodies (2) are arranged with.
3. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions according to claim 2, feature exist
In aluminium alloy extrusions be by element mass percentage be Cu：2.0%, Mg：2.5%, Zn：9.6%, Zr：0.12% and surplus
Aluminium ingot, tough cathode, primary magnesium ingot, zinc ingot metal, aluminium zircaloy ingot are weighed as raw material for Al.
4. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions according to claim 2, feature exist
In step 1 in temperature is 720 DEG C~760 DEG C of smelting furnace melting raw material 5h~9h.
5. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions according to claim 2, feature exist
In step 2 casting temperature is 720 DEG C~760 DEG C, casting speed is 30mm/min~70mm/min, cooling water temperature 10
DEG C~20 DEG C and cooling water intensity is 20m3/ h~60m3Molten aluminium alloy is cast as round ingot casting under conditions of/h.
6. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions according to claim 2, feature exist
2h is kept the temperature at 450 DEG C in step 7, is warming up to 470 DEG C of heat preservation 4h.
7. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions according to claim 2, feature exist
The amount of tension control of stretcher leveling in step 8 is 2.7%~3.2%.
8. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions according to claim 2, feature exist
30h is heated in step 10, carries out level-one ageing treatment.
9. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions according to claim 2, feature exist
160min is kept the temperature in step 11, carries out secondary time effect processing.
10. a kind of preparation method of aerospace high-ductility corrosion aluminium alloy extrusions according to claim 2, feature exist
30h is heated in step 12, carries out three-step aging processing.
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