CN111304503A - Low-density damage-resistant aluminum-lithium alloy for aircraft wheel and preparation method thereof - Google Patents

Low-density damage-resistant aluminum-lithium alloy for aircraft wheel and preparation method thereof Download PDF

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CN111304503A
CN111304503A CN202010169445.8A CN202010169445A CN111304503A CN 111304503 A CN111304503 A CN 111304503A CN 202010169445 A CN202010169445 A CN 202010169445A CN 111304503 A CN111304503 A CN 111304503A
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forging
less
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die
temperature
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郭明伟
王嘉
钟孝贤
范曦
孙洋
张豪
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Jiangsu Haoran Spray Forming Alloy Co ltd
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Jiangsu Haoran Spray Forming Alloy Co ltd
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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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/115—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by spraying molten metal, i.e. spray sintering, spray casting
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    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/17—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by forging
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    • B22—CASTING; POWDER METALLURGY
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    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/20—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by extruding
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    • B22—CASTING; POWDER METALLURGY
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    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • 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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    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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    • C22C21/00—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
    • 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
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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
    • C22F1/057—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 copper as the next major constituent
    • 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
    • C22F3/00—Changing the physical structure of non-ferrous metals or alloys by special physical methods, e.g. treatment with neutrons
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    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/17—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by forging
    • B22F2003/175—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by forging by hot forging, below sintering temperature
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/20—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by extruding
    • B22F2003/208—Warm or hot extruding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
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    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
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    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps

Abstract

The invention discloses a low-density damage-resistant aluminum-lithium alloy for an aircraft wheel and a preparation method thereof, wherein the preparation method comprises smelting and degassingSmelting, spray forming and the like, and further processing the alloy through a four-fire forging process to obtain Si with the mass fraction of less than or equal to 0.06%, Fe with the mass fraction of less than or equal to 0.6%, and H with the content of less than 0.15cm3The alloy per 100g has 12% improvement of specific strength, 12% improvement of specific modulus and 6% improvement of fracture toughness compared with 7050, 34% improvement of specific strength, 12% improvement of specific modulus and 14% improvement of fracture toughness compared with LD 10.

Description

Low-density damage-resistant aluminum-lithium alloy for aircraft wheel and preparation method thereof
Technical Field
The invention relates to a low-density damage-resistant aluminum-lithium alloy for an aircraft wheel and a preparation method thereof.
Background
In the face of complex international political, economic and military battle environments, the properties of heavy load, long distance, high speed, safety, reliability and the like are the development direction of aviation military aircrafts. In terms of military aircraft design concept and design criteria, the single static strength design criteria is developed to the damage safety design criteria, and then the damage tolerance design criteria is developed.
The structural material is the basis for the performance guarantee of the weapon equipment. For a long time, 2xxx, 7xxx aluminum alloys have been the most prominent lightweight structural materials for military aircraft. In order to realize further light weight of the structure and simultaneously improve the processing technical performance, the stress corrosion resistance and the safety of the material, the application and the development of the aluminum-lithium alloy in the military machine are rapid, and a series of alloy grades are developed to meet different structural application requirements. In particular, in the last decade, a new generation of low-density and high-damage-resistance aluminum-lithium alloy (such as 2050 and 2055 in the aluminum industry in the united states, for example) has been developed, and has been widely applied to wing/body joints, ports, top frames, spars, ribs, and the like of advanced warplanes such as F-22 and F-35, and has a tendency to gradually replace 7050 aluminum alloy.
The aircraft wheels are key airborne equipment for ensuring the safety of take-off and landing of the aircraft, and are installed on an aircraft frame to bear comprehensive complex alternating loads of take-off, landing, ground sliding, shutdown, turning, braking and the like of the aircraft along with each take-off and landing.
Along with the development of airplanes such as heavy load, short-distance take-off and landing, the requirement on the performance of the airplane wheel is higher and higher, under the condition that the weight of the airplane wheel is required to be as light as possible, higher and higher load bearing, longer and longer service life and lower damage structure danger are realized. According to the statistics of aviation faults, faults of the airplane in the takeoff and landing stage account for about 40% of the total fault frequency, wherein each landing instantaneous impact and long-term fatigue and rolling are main causes of damage and destruction of the airplane wheel, and therefore the specific strength, specific rigidity, durability and damage resistance of the airplane wheel are main lifting directions of the airplane wheel.
Taking a certain type of airplane wheel as an example, the design requires that the unit mass bearing capacity of the airplane wheel is improved by about 25%, the service life of the airplane wheel is prolonged by about 200%, the weight is reduced by 5%, and the technical requirements are difficult to meet by using the aluminum alloy of the conventional airplane wheel. There is a pressing need to apply new aluminum alloys with high specific strength, high modulus, high damage tolerance and thermal stability. However, the development of the aluminum lithium alloy in China has a large gap with foreign countries, stable energy conservation capacity cannot be formed, and the application of the low-density high-damage aluminum lithium alloy in the weapon equipment in China is still blank.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a low-density damage-resistant aluminum-lithium alloy for an aircraft wheel and a preparation method thereof.
A low-density damage-resistant aluminum-lithium alloy for an aircraft wheel comprises Cu, Li, Zn, Ti, Mg, Zr and Al, wherein the mass fraction of Cu is 2.5-4.2%, the mass fraction of Li is 0.7-1.35%, the mass fraction of Zn is 0.13-0.2%, the mass fraction of Mg is 0.25-0.65%, the mass fraction of Zr is 0.11-0.25%, the mass fraction of Ag is 0.4-0.8%, the mass fraction of Ti is 0.08-0.12%, the mass fraction of Si is less than or equal to 0.06%, the mass fraction of Fe is less than or equal to 0.6%, and the balance of Al.
Preferably, the solid H content is less than or equal to 0.15cm3/100g。
The preparation method of the low-density damage-resistant aluminum-lithium alloy for the aircraft wheel comprises the following steps:
①, batching according to the alloy mass percentage;
②, melting the prepared metal material, melting at 730-780 ℃, and adding high-purity lithium ingots under the protection of inert gas;
③, degassing and refining the melt;
④, preparing alloy ingot blank by spray forming, cooling the ingot blank to 280-350 ℃ in a deposition chamber after the spray is finished, taking out and air cooling;
⑤, extruding the alloy, heating and preserving heat in an air furnace, wherein the heat preservation temperature is 400-480 ℃, the heat preservation time is more than or equal to 15 hours, the mold temperature is 420-460 ℃, the extrusion cylinder temperature is 420-460 ℃, and the speed of the main push rod is 0.1-1 mm/s;
⑥, performing die forging on the blank by using a die forging press and a die forging tool, sawing an extrusion rod into a certain length, and heating an aluminum lithium alloy ingot blank and a flat anvil and a hub die for forging and cogging, wherein the heating temperature range of the aluminum lithium alloy and the die is 440-470 ℃, the heat preservation time is not less than 8 hours, the heating temperature range of the flat anvil is 400-470 ℃, and the heating time is not less than 12 hours;
⑦ heat treatment:
1) solution treatment: slowly heating to 450-490 ℃, keeping the temperature for 30-90 min, wherein the heating rate is less than or equal to 1 ℃/min, then quickly heating to 505-520 ℃, the heating rate is more than or equal to 4 ℃/min, keeping the temperature for 120-360 min, water quenching, wherein the quenching water temperature is 50-80 ℃, the quenching transfer time is less than or equal to 20s, and the cooling time in water is not less than 10 min;
2) and transferring to an aging stage within 6 hours after the solution treatment, wherein the aging temperature is 120-130 ℃, the aging time is 10-20 hours, the temperature is raised to 150-175 ℃, and the temperature is kept for 15-40 hours.
Preferably, after the heat treatment in the step ⑧, the method further comprises stress relief vibration aging, and the specific process is that the hub blank is subjected to vibration aging with the vibration frequency of 50-90HZ and kept for 10-25 min.
Preferably, in step ②, when the high-purity lithium ingot is added, an inert gas is used for protection, and the inert gas is high-purity argon or nitrogen.
Preferably, in step ②, the melting crucible material is 304L stainless steel, graphite or MgO-based refractory.
Preferably, in the step ③, the degassing extraction is performed by simultaneously using a vacuum standing degassing process and an argon degassing process.
Preferably, step ⑥ further comprises forging the heated blank using a four-fire forging process, comprising the steps of:
1) first hot upsetting and lengthening: quickly taking out the forging stock from the resistance furnace, placing the forging stock in the middle of a flat anvil, starting pressurizing and upsetting, then drawing to 3/4 of the original height, and finally performing a rolling process; the initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃;
2) second fire die forging and punching: placing the forging blank into a forging die for centering, starting to pressurize by a forging press, wherein the pressing speed of the press is less than or equal to 15mm/s, the initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃; after demoulding, returning to the furnace and continuing heating and heat preservation: the heating temperature range is 400-470 ℃, and the heating time is not less than 4 hours; after forging and pressing 1 forged piece, additionally brushing a lubricant at the bottom of the cavity;
3) performing third fire die forging: putting the second hot forging blank into a forging die for centering, starting to pressurize by a forging press, wherein the pressing speed of the forging press is less than or equal to 12mm/s, the initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃; after demoulding, returning to the furnace and continuing heating and heat preservation: the heating temperature range is 400-470 ℃, and the heating time is not less than 4 hours; after forging and pressing 1 forged piece, additionally brushing a lubricant at the bottom of the cavity;
4) fourth hot die forging forming: taking the forging stock out of the resistance furnace, putting the forging stock into a forging die, leveling the forging die, and starting pressurizing; punching the punch in place for three times, wherein the punching depth of the punch for the first time is 60 +/-10 mm, and graphite sawdust is supplemented for lubrication after each punching depth; third stamping until die assembly; the pressing speed of the forging press is less than or equal to 12 mm/s; the dwell time is 5-20 seconds.
Has the advantages that:
the airplane hub is an extremely important bearing part of the airplane. With the development of heavy load, short-distance rise and fall and other models, not only higher and higher requirements on light weight, safety, fatigue life and stress corrosion resistance are provided, but also durability and damage tolerance become one of design criteria.
For the last 30 years, wheel materials of domestic military aircraft have been used for LD5 and LD10, and the application of the new materials is far behind other components. And the foreign airplane wheels are made of a large amount of aluminum alloy such as 7050, 7085 and the like. In recent years, the U.S. aluminum industry has developed a new aluminum-lithium alloy wheel with significantly better bearing capacity, fracture toughness, thermal stability, fatigue performance, and corrosion resistance than 2014-T6 and 2040-T6.
Take a certain type of airplane wheel hub as an example. The hub has the main functions of bearing and fatigue rolling, is in direct proportion to strength and damage tolerance indexes, and the design and material selection parameters mainly comprise specific strength, specific stiffness (specific modulus), fracture toughness and the like. According to the design requirements of the model on the hub, the bearing capacity needs to be increased by 25%, the weight is reduced by 5%, and the service life is prolonged by 100%.
The alloy has obvious performance advantages in six aspects of density, elastic modulus, tensile property, specific strength, specific modulus and fracture toughness.
Compared with 7050, the alloy of the invention has the advantages of 12% improvement of specific strength, 12% improvement of specific modulus and 6% improvement of fracture toughness.
Compared with LD10, the alloy of the invention has 34% higher specific strength, 12% higher specific modulus and 14% higher fracture toughness.
The requirements of bearing capacity, weight reduction and service life are integrated, and preliminary design calculation shows that: 7050 it is difficult to meet the required weight reduction and life targets. The alloy of the invention has greatly improved damage resistance due to the simultaneous improvement of specific strength, specific modulus and fracture toughness, has obvious effects of comprehensive weight reduction, prolonged service life, structural damage resistance and safety improvement, and can meet the design requirements of the model on the hub.
Drawings
FIG. 1 is a table comparing LD10, 7050, and performance parameters of the present aluminum lithium alloy.
Detailed Description
For the purpose of enhancing the understanding of the present invention, the present invention will be further described in detail with reference to the following examples and the accompanying drawings, which are only used for explaining the present invention and are not to be construed as limiting the scope of the present invention.
The aluminum-lithium alloy for the low-density damage-resistant airplane wheel consists of 2.5-4.2% by mass of Cu, 0.7-1.35% by mass of Li, 0.13-0.2% by mass of Zn, 0.25-0.65% by mass of Mg, 0.11-0.25% by mass of Zr, 0.4-0.8% by mass of Ag, 0.08-0.12% by mass of Ti, 0.06% by mass of Si, less than or equal to 0.6% by mass of Fe and the balance of Al.
The impurity contents of Fe and Si elements in the alloy are strictly controlled. At the same time, the solid H content is strictly controlled, and the solid H content is less than or equal to 0.15cm3/100g。
1. Preparing materials according to the requirement of alloy mass percentage, wherein Al 99.95 high-purity aluminum ingots are preferentially used as the aluminum ingots;
2. melting the prepared metal material at 730-780 ℃. Adding high-purity lithium ingots under the protection of inert gas to provide the quality of the aluminum lithium alloy, wherein the inert gas is high-purity argon or nitrogen. In order to better control the content of impurity elements such as alkali metals Na, K, Ga and the like, 304L stainless steel, graphite or MgO-based refractory materials are selected as the materials of the smelting crucible, and the MgO-based refractory materials are preferentially recommended from the viewpoint of thermodynamic stability;
3. degassing and refining the melt. The melt can be effectively degassed by vacuum standing degassing or argon gas is introduced into the melt, and the most effective method is to adopt vacuum standing degassing and argon gas degassing processes at the same time;
4. and (3) preparing an alloy ingot blank by spray forming, cooling the ingot blank to 280-350 ℃ in a deposition chamber after the spray is finished, and taking out for air cooling. Preparation of an Al-Li alloy ingot blank by spray forming technique, H2Further overflow in the melt spray forming atomization process, and the H content of the prepared aluminum lithium alloy ingot blank is less than or equal to 0.15cm3100g, which is obviously lower than the level of the ingot blank prepared by the traditional semi-continuous method, and the low H is beneficial to improving the damage resistance of the alloy;
5. extruding, heating and preserving heat in an air furnace, wherein the heat preservation temperature is 400-480 ℃, the heat preservation time is more than or equal to 15h, and the mold temperature is as follows: 420-460 ℃, extrusion cylinder temperature: 420-460 ℃, main push rod speed: 0.1 mm/s-1 mm/s;
6. and performing die forging on the aluminum lithium alloy blank by using a die forging press and a die forging tool. The method comprises the steps of sawing an extrusion rod into a certain length, heating an aluminum lithium alloy ingot blank and a flat anvil and a hub die for forging and cogging, wherein the heating temperature range of the aluminum lithium alloy and the die is 440-470 ℃, the heat preservation time is not less than 8 hours, the heating temperature range of the flat anvil is 400-470 ℃, and the heating time is not less than 12 hours.
Forging the heated blank by adopting a four-fire forging process:
1) first hot upsetting and lengthening: and (3) quickly taking the forging stock out of the resistance furnace, placing the forging stock in the middle of a flat anvil, starting pressurizing and upsetting, then drawing to 3/4 of the original height, and finally performing a rounding process. The initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃;
2) second fire die forging and punching: placing the forging blank into a forging die for centering, starting to pressurize by a forging press, wherein the pressing speed of the press is less than or equal to 15mm/s, the initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃; after demoulding, returning to the furnace and continuing heating and heat preservation: the heating temperature range is 400-470 ℃, and the heating time is not less than 4 hours; after forging and pressing 1 forged piece, additionally brushing a lubricant on the bottom of the cavity;
3) performing third fire die forging: putting the second hot forging blank into a forging die for centering, starting to pressurize by a forging press, wherein the pressing speed of the forging press is less than or equal to 12mm/s, the initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃; after demoulding, returning to the furnace and continuing heating and heat preservation: the heating temperature range is 400-470 ℃, and the heating time is not less than 4 hours; after forging and pressing 1 forged piece, additionally brushing a lubricant on the bottom of the cavity;
4) fourth hot die forging forming: and taking the forging stock out of the resistance furnace, putting the forging stock into a forging die, leveling the forging die, and starting pressurizing. The punch is punched in place for three times, the punching depth of the first time and the punching depth of the second time are 60 +/-10 mm, and graphite sawdust is supplemented for lubrication after each punching depth. And punching for the third time until the die is closed. The pressing speed of the forging press is less than or equal to 12 mm/s. The dwell time is 5-20 seconds.
7. Thermal treatment
Solid solution system: slowly heating to 450-490 ℃, keeping the temperature for 30-90 min, wherein the heating rate is less than or equal to 1 ℃/min, then quickly heating to 505-520 ℃, the heating rate is more than or equal to 4 ℃/min, keeping the temperature for 120-360 min, water quenching, wherein the quenching water temperature is 50-80 ℃, the quenching transfer time is less than or equal to 20s, and the cooling time in water is not less than 10 min.
And transferring to an aging stage within 6 hours after the solution treatment, wherein the aging system is 120-130 ℃, the aging is 10-20 hours, the temperature is raised to 150-175 ℃, and the temperature is kept for 15-40 hours.
8. Stress relief vibration aging
And (3) carrying out vibration aging on the hub blank, wherein the vibration frequency is 50-90HZ, and keeping for 10-25 min.
The comparison shows that: the alloy has obvious performance advantages in six aspects of density, elastic modulus, tensile property, specific strength, specific modulus and fracture toughness.
Compared with 7050, the alloy of the invention has the advantages of 12% improvement of specific strength, 12% improvement of specific modulus and 6% improvement of fracture toughness.
Compared with LD10, the alloy of the invention has 34% higher specific strength, 12% higher specific modulus and 14% higher fracture toughness.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims (8)

1. The low-density damage-resistant aluminum-lithium alloy for the aircraft wheel is characterized by comprising 2.5-4.2% by mass of Cu, 0.7-1.35% by mass of Li, 0.13-0.2% by mass of Zn, 0.25-0.65% by mass of Mg, 0.11-0.25% by mass of Zr, 0.4-0.8% by mass of Ag, 0.08-0.12% by mass of Ti, 0.06% by mass of Si, less than or equal to 0.6% by mass of Fe and the balance of Al.
2. A low density wear resistant aircraft wheel as claimed in claim 1The aluminum-lithium alloy is characterized in that the solid H content is less than or equal to 0.15cm3/100g。
3. A method for preparing a low-density damage-resistant aluminum-lithium alloy for an aircraft wheel as claimed in claims 1-2, comprising the steps of:
①, batching according to the alloy mass percentage;
②, melting the prepared metal material, melting at 730-780 ℃, and adding high-purity lithium ingots under the protection of inert gas;
③, degassing and refining the melt;
④, preparing alloy ingot blank by spray forming, cooling the ingot blank to 280-350 ℃ in a deposition chamber after the spray is finished, taking out and air cooling;
⑤, extruding the alloy, heating and preserving heat in an air furnace, wherein the heat preservation temperature is 400-480 ℃, the heat preservation time is more than or equal to 15 hours, the mold temperature is 420-460 ℃, the extrusion cylinder temperature is 420-460 ℃, and the speed of the main push rod is 0.1-1 mm/s;
⑥, performing die forging on the blank by using a die forging press and a die forging tool, sawing an extrusion rod into a certain length, and heating an aluminum lithium alloy ingot blank and a flat anvil and a hub die for forging and cogging, wherein the heating temperature range of the aluminum lithium alloy and the die is 440-470 ℃, the heat preservation time is not less than 8 hours, the heating temperature range of the flat anvil is 400-470 ℃, and the heating time is not less than 12 hours;
⑦ heat treatment:
1) solution treatment: slowly heating to 450-490 ℃, keeping the temperature for 30-90 min, wherein the heating rate is less than or equal to 1 ℃/min, then quickly heating to 505-520 ℃, the heating rate is more than or equal to 4 ℃/min, keeping the temperature for 120-360 min, water quenching, wherein the quenching water temperature is 50-80 ℃, the quenching transfer time is less than or equal to 20s, and the cooling time in water is not less than 10 min;
2) and transferring to an aging stage within 6 hours after the solution treatment, wherein the aging temperature is 120-130 ℃, the aging time is 10-20 hours, the temperature is raised to 150-175 ℃, and the temperature is kept for 15-40 hours.
4. The method for preparing the low-density damage-resistant aluminum-lithium alloy for the airplane wheel according to claim 3, wherein the stress-relief vibration aging is further performed after the step ⑧ of heat treatment, and the specific process is that the hub blank is subjected to vibration aging with the vibration frequency of 50-90HZ and is kept for 10-25 min.
5. The method as claimed in claim 3, wherein in step ②, when adding high purity lithium ingot, inert gas is used for protection, and the inert gas is high purity argon or nitrogen.
6. The method for preparing the low-density damage-resistant aluminum-lithium alloy for the airplane wheel according to claim 3, wherein in the step ②, the melting crucible material is 304L stainless steel, graphite or MgO-based refractory material.
7. The method for preparing a low-density damage-resistant aluminum-lithium alloy for an aircraft wheel according to claim 3, wherein in the step ③, a vacuum standing degassing process and an argon degassing process are simultaneously adopted during degassing refining.
8. The method for preparing the low-density damage-resistant aluminum-lithium alloy for the airplane wheel according to claim 3, wherein the step ⑥ is further performed by forging the heated blank by a four-fire forging process, and the method comprises the following steps:
1) first hot upsetting and lengthening: quickly taking out the forging stock from the resistance furnace, placing the forging stock in the middle of a flat anvil, starting pressurizing and upsetting, then drawing to 3/4 of the original height, and finally performing a rolling process; the initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃;
2) second fire die forging and punching: placing the forging blank into a forging die for centering, starting to pressurize by a forging press, wherein the pressing speed of the press is less than or equal to 15mm/s, the initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃; after demoulding, returning to the furnace and continuing heating and heat preservation: the heating temperature range is 400-470 ℃, and the heating time is not less than 4 hours; after forging and pressing 1 forged piece, additionally brushing a lubricant at the bottom of the cavity;
3) performing third fire die forging: putting the second hot forging blank into a forging die for centering, starting to pressurize by a forging press, wherein the pressing speed of the forging press is less than or equal to 12mm/s, the initial forging temperature range is 420-470 ℃, and the final forging temperature is not less than 380 ℃; after demoulding, returning to the furnace and continuing heating and heat preservation: the heating temperature range is 400-470 ℃, and the heating time is not less than 4 hours; after forging and pressing 1 forged piece, additionally brushing a lubricant at the bottom of the cavity;
4) fourth hot die forging forming: taking the forging stock out of the resistance furnace, putting the forging stock into a forging die, leveling the forging die, and starting pressurizing; punching the punch in place for three times, wherein the punching depth of the punch for the first time is 60 +/-10 mm, and graphite sawdust is supplemented for lubrication after each punching depth; third stamping until die assembly; the pressing speed of the forging press is less than or equal to 12 mm/s; the dwell time is 5-20 seconds.
CN202010169445.8A 2020-03-12 2020-03-12 Low-density damage-resistant aluminum-lithium alloy for aircraft wheel and preparation method thereof Pending CN111304503A (en)

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CN113416872A (en) * 2021-05-27 2021-09-21 江苏豪然喷射成形合金有限公司 High-strength high-toughness aluminum lithium alloy for aerospace and preparation method thereof
US20220307118A1 (en) * 2021-03-29 2022-09-29 Citic Dicastal Co., Ltd. Method for manufacturing special vehicle wheels with 7000 series aluminum alloy

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CN106702237A (en) * 2016-12-20 2017-05-24 江苏豪然喷射成形合金有限公司 Spray forming method for aluminum-lithium alloy
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CN102459671A (en) * 2009-06-25 2012-05-16 法国肯联铝业 Aluminium-copper-lithium alloy having improved mechanical strength and improved toughness
CN105814223A (en) * 2013-12-13 2016-07-27 伊苏瓦尔肯联铝业 Extruded products for aeroplane floors made of an aluminium-copper-lithium alloy
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CN113416872A (en) * 2021-05-27 2021-09-21 江苏豪然喷射成形合金有限公司 High-strength high-toughness aluminum lithium alloy for aerospace and preparation method thereof

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