CN111424199A - 2-series aluminum alloy section for lower stringer of civil aircraft wing and manufacturing method thereof - Google Patents
2-series aluminum alloy section for lower stringer of civil aircraft wing and manufacturing method thereof Download PDFInfo
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- B21D3/00—Straightening or restoring form of metal rods, metal tubes, metal profiles, or specific articles made therefrom, whether or not in combination with sheet metal parts
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Abstract
A2-series aluminum alloy section for a lower stringer of a civil aircraft wing and a manufacturing method thereof belong to the field of manufacturing of the civil aircraft aluminum alloy section, and the mass percent of all substances in the alloy section is as follows: the alloy comprises, by weight, less than 0.05% of Si, less than 0.06% of Fe, 3.7% -4.1% of Cu, 1.2% -1.4% of Mg, less than 0.4% -0.8% of Mn, less than 0.02% of Cr, 0.02% -0.06% of Ti, 0.08% -0.12% of Zr, less than 0.15% of other impurity elements, and the balance Al. According to the invention, by adopting the technical means of optimizing the layout of the die holes, carrying out isothermal reverse extrusion on the ingot casting step heating, carrying out low-stress step quenching and the like, the transverse performance of the section is improved, and the residual stress of the section is reduced.
Description
Technical Field
The invention belongs to the field of manufacturing of aluminum alloy sections for civil aircrafts, and particularly relates to a 2-series aluminum alloy section for a lower stringer of a civil aircraft wing and a manufacturing method thereof.
Background
The aviation manufacturing industry level is an important sign of national strength, China has obviously advanced since the first large civil aircraft development project is started in 1970, particularly, in more than ten years, along with the rapid development of the economy and civil aviation industry in China, the aviation transportation industry shows huge market demands, the commercial aircraft with independent intellectual property rights is developed as one of the national targets and is promoted, ARJ21 new branch aircraft and large passenger aircraft C919 development project are started successively, ARJ21 aircraft is put into airline operation formally in 2016, the large jet passenger aircraft C919 independently developed in China also realizes perfect first flight at Shanghai Pudong international airport in 5 months and 5 months in 2017, and the national aviation manufacturing industry is shown to advance forward. In the next 20 years, the global commercial aircraft delivery will reach more than 4 million, and the total value will reach 6 trillion dollars, wherein the new aircraft delivery in China will reach more than 9000, which accounts for 22% of the world. The Chinese civilian manner will be welcomed by the rapid development stage and the wide market opportunity.
Since the market for domestic civil aircraft projects, various required aluminum alloy sections always depend on import, so that the manufacturing cost of the whole machine is increased, and the aircraft delivery risk caused by the supply interruption of the sections at any time is also faced. Under the background of comprehensively promoting the localization of civil aircraft materials, the Ministry of industry and belief puts the production of 2-series section bars for the lower stringer of the wing into the national new material production application demonstration platform, brings the production into the upstream and downstream cooperation mechanism of the civil aircraft, and strives to realize the localization of the lower stringer of the civil aircraft. The wing lower stringer of the civil aircraft is usually made of 2 series aluminum alloy sections with high strength, high toughness and high damage tolerance, and the common brands and states comprise: 2026 to T3511, 2224 to T3511 and the like, wherein the 2026 alloy is a novel 2-series aluminum alloy developed by reducing the contents of Fe and Si and adding a small amount of Zr on the basis of 2024 alloy by the aluminum industries of America. The 2026-T3511 section prepared by reasonable hot working and heat treatment has the advantages of high strength, high damage tolerance, good corrosion resistance and the like, is applied to a passenger plane of A320 series on a large scale, and is selected by C919 as a manufacturing material of a lower stringer of a wing.
China also has more process improvements in the production of the 2-series aluminum alloy to improve the performance of the 2-series aluminum alloy.
In 2018, patent CN 108441793 a discloses a heat treatment method for forced sizing of aluminum alloy and an aluminum alloy profile for aviation. Through adopting the quenching frock to carry out the forced sizing, restrained the quenching deformation of section bar in the quenching process, obtained better section bar straightness.
Patent CN 104862561A of Chengdu Chilida science and technology Limited discloses a high-strength aluminum alloy section for an airplane hanger and a preparation method thereof in 2015. By optimizing the refining agent used for ingot production and optimizing the alloy components and the production process, the 2-series aluminum alloy section with the tensile strength of 573 MPa, the yield strength of 459 MPa and the elongation of 15.1% is produced.
Zhejiang emperor aluminum industry, Inc. in 2017, discloses a production process of an environment-friendly high-toughness hard aluminum alloy section in patent CN 104975213B. Horizontal continuous casting and continuous extrusion of the 2-series alloy are realized, and the tensile strength of the section can reach more than 500 MPa.
The technical scheme is that the stress mode of the lower stringer of the wing is complex in the actual use process, and the section used for the lower stringer of the civil aircraft wing needs to meet performance indexes in L T directions besides L-direction performance, particularly indexes such as L T-direction stress corrosion performance and the like.
The reason is that the civil aviation industry starts late in China, the use requirements of the civil aircraft wing lower stringer are lacked, aluminum profile production enterprises cannot fully understand various performances and requirements of the civil aircraft wing lower stringer, and sufficient time and force are not invested for related research and development, so that the section which can fully meet the use requirements of the civil aircraft wing lower stringer cannot be produced for a long time. Secondly, the 2026 alloy is a completely new strange alloy for domestic production enterprises as compared with the common 2-series alloy, the alloy components are greatly adjusted, and Zr element is added.
The Nanshan aluminum industry relies on a demonstration platform created by China, production equipment is reasonably configured according to the production requirements of civil aviation profiles, a sound production management system is established, a powerful research and development team is created, profiles with various performances meeting the use requirements of stringers under wings are produced through years of process research and improvement, and the domestic blank is filled. The related process and the section bar produced by the process are approved by the Chinese commercial airplane Limited liability company and are transferred to the final evidence obtaining stage.
Disclosure of Invention
The invention provides a 2-series aluminum alloy section for a lower stringer of a civil aircraft wing and a manufacturing method thereof, which are used for solving the defects in the prior art. The invention is realized by the following technical scheme:
a2-series aluminum alloy section for a lower stringer of a civil aircraft wing comprises the following substances in percentage by mass: the alloy comprises, by weight, less than 0.05% of Si, less than 0.06% of Fe, 3.7% -4.1% of Cu, 1.2% -1.4% of Mg, less than 0.4% -0.8% of Mn, less than 0.02% of Cr, 0.02% -0.06% of Ti, 0.08% -0.12% of Zr, less than 0.15% of other impurity elements, and the balance Al.
A manufacturing method of a 2-series aluminum alloy section for a lower stringer of a civil aircraft wing comprises the following steps:
the method comprises the following steps: casting an ingot, and carrying out homogenization annealing treatment after the ingot casting is finished.
Step two: and (3) heating and insulating the mould by using a box type mould heating furnace to ensure that the temperature of the core part of the mould reaches 390-410 ℃.
Step three: setting the temperature of an extrusion cylinder to be 400-420 ℃, preserving heat after the temperature is reached, heating the cast ingot, loading the heated cast ingot into the extrusion cylinder with the tail end in the direction with the inner head end outside, loading a die with left and right double-hole layouts into the extrusion cylinder to be close to the head end of the cast ingot, slowly inserting the die into a hollow shaft for reverse extrusion, and pre-stretching and straightening after the extrusion is finished to obtain an aluminum alloy section bar primary product.
Step four: the method comprises the steps of carrying out solution treatment on an aluminum alloy profile primary product by adopting an off-line heat treatment process, wherein the solution treatment temperature is 492-494 ℃, the heat preservation time of the solution treatment is 80-120 min, ensuring full solution, carrying out quenching and cooling after the heat preservation is finished, immediately stretching and straightening the quenched profile, and eliminating quenching residual stress.
Step five: after quenching, cooling, stretching and straightening the section, putting the section straight, and naturally aging for over 96 hours to obtain the aluminum alloy section.
The manufacturing method of the 2-series aluminum alloy section for the lower stringer of the civil aircraft wing is characterized in that the ingot casting heating mode is induction heating, and the step heating method comprises the following steps: the induction heating furnace is equally divided into a plurality of areas along the length direction of the cast ingot, each area adopts an independent induction heating coil, a thermocouple and a temperature control device, and after the temperature and the temperature gradient of the head end of the cast ingot are set, the set temperature of each area is automatically calculated and input by a program.
According to the manufacturing method of the 2-series aluminum alloy section for the lower stringer of the civil aircraft wing, in the third step, the set temperature of the head end of the ingot is 350-430 ℃, the temperature of the ingot from the head end to the tail end is in a gradient descending trend, and the temperature gradient descending trend is 10-30 ℃/m. Heating each area of the cast ingot to the temperature, then loading the cast ingot into an extrusion cylinder, loading the head end of the cast ingot into a die, and extruding.
According to the manufacturing method of the 2-series aluminum alloy section for the lower stringer of the civil aircraft wing, the extrusion shaft speed of backward extrusion in the third step is 1.0-1.5 mm/s, the shaft speed is set to be related to the heating temperature of the cast ingot, and the principle is high temperature, low speed, low temperature and high speed.
According to the manufacturing method of the 2-series aluminum alloy section for the lower stringer of the civil aircraft wing, the deformation amount of the prestretching and straightening in the third step is controlled to be less than 1.2%.
According to the manufacturing method of the 2-series aluminum alloy section for the lower stringer of the civil aircraft wing, the stretching deformation amount of the stretching and straightening in the fourth step is controlled to be 1% -3%.
According to the manufacturing method of the 2-series aluminum alloy section for the lower stringer of the civil aircraft wing, the quenching mode in the fourth step is spray quenching.
The spray quenching operation is that the quenching area is divided into two areas, the area close to the heat treatment furnace is a front area, the area far away from the heat treatment furnace is a rear area, upper and lower water spraying devices of the two areas have independent adjusting capacity, the quenching water quantity process parameters are that the water quantity of a front area upper nozzle is 330-370L/s, the water quantity of a front area lower nozzle is 220-260L/s, the water quantity of a rear area upper nozzle is 160-200L/s, the water quantity of a rear area lower nozzle is 130-170L/s, and the quenching passing speed of the section is 150-250 mm/s.
The manufacturing method of the 2-series aluminum alloy section for the lower stringer of the civil aircraft wing comprises the following steps of:
the method comprises the following steps: according to the mass percentages of all substances in the aluminum alloy ingot and the burning loss in the alloy smelting process and the alloy components and contents in the waste materials, the weights of an aluminum ingot, a copper plate, a magnesium ingot, an aluminum-manganese intermediate alloy, an aluminum-chromium intermediate alloy, an aluminum-titanium intermediate alloy and an aluminum-zirconium intermediate alloy are calculated according to the feeding amount, and various raw materials are weighed according to the calculated result.
Step two: putting the fully dried aluminum ingot into a smelting furnace, and controlling the temperature of a hearth to be 950-1050 ℃ in the melting process; and (4) after the aluminum ingot is completely melted, stirring for 15-35 min by using electromagnetic stirring equipment. And alloying is started after the temperature of the melt reaches 700 ℃, the fluctuation range of the temperature of the melt is controlled to be 700-750 ℃, the copper plate and various intermediate alloys are added in batches, the adding time interval of each batch of alloys is 20 min, the adding weight of each batch of alloys does not exceed 800 kg, an electromagnetic stirrer is used for continuously stirring, and scum on the surface of the melt is completely removed by a skimming car before each batch of materials is added in the alloying process.
Step three: all raw materials are put into a smelting furnace, the melt is transferred into a standing furnace from the smelting furnace after being completely melted for primary refining, the temperature of a hearth of the standing furnace is 850 ℃, the temperature of the melt is controlled to be 725-745 ℃ when the melt is transferred from the smelting furnace to the standing furnace, a rotary ventilation device is adopted for refining, the rotor speed of the rotary ventilation device is 250-350 RPM, mixed gas of argon and chlorine is introduced, the argon flow is 180-220 slpm, the chlorine flow is 5-15 slpm, scum floating out of the melt is timely cleaned in the refining process, the refining time is controlled to be 30 min each time, chemical component analysis is carried out by sampling at a fixed position, and precise regulation and control are carried out on the alloy components of the melt.
Step four: and (3) sending the melt subjected to the primary refining in the standing furnace into a double-rotor two-stage degassing box for secondary refining, wherein the temperature of the double-rotor two-stage degassing box is adjusted to be 735-745 ℃, the temperature of the melt is controlled to be 715-735 ℃ when the melt is transferred from the standing furnace to the double-rotor two-stage degassing box, and a refiner is added into the double-rotor two-stage degassing box.
Step five: the melt of the degassing and deslagging of the secondary refining of the double-rotor degassing box is sent into a double-layer filter box for filtering, 30 ppi of porosity of a first-stage filter plate is used for deslagging for the fourth time, 50 ppi of porosity of a second-stage filter plate is used for deslagging for the fifth time, and the filter plate and the whole set of launder begin to be preheated 40 min in advance during casting each time, but the heating time is not allowed to exceed 2 h.
Step six: the melt filtered by the double-layer filter box is sent into a casting machine for casting, the initial casting speed is 20-25 mm/min, and the water flow is 25-30 m3The method comprises the following steps of (1) starting an automatic lubricating system of a crystallizer at the same time; the casting length is more than 100 mm, the casting speed is adjusted to be 35-40 mm/min, and the water flow is adjusted to be 40-45 m3H, root, keeping constant-speed casting; after the length of the cast ingot exceeds 550 mm, the casting speed is adjusted to be 20-25 mm/min, and the water flow is adjusted to be 25-30 m3H root.
Step seven: and immediately feeding the cast ingot cast by the casting machine into a homogenizing furnace for homogenizing operation, and carrying out homogenizing annealing according to a specific homogenizing process preset by different alloy proportions to prevent cracks from being generated in the residual stress releasing process.
The invention has the advantages that:
1. according to the invention, through a large amount of theoretical researches and actual manufacturing, products are obtained to carry out omnibearing performance detection, and finally the standard-meeting 2-series section is obtained, so that the problem that the 2-series section used for the lower stringer of the wing of the domestic civil aircraft completely depends on import is solved. The 2-series section for the lower stringer of the wing produced by the invention successfully passes the certification of the medium-commercial flying material, and replaces an imported section to realize the use of an installation.
2. In the mold design in the prior art, the influence of the mold design on the microstructure and performance of the profile is not considered, particularly, when the porous mold design is carried out, the influence of the die hole layout on the microstructure and performance of the profile is not considered, but only the effects of the profile forming effect and the reduction of extrusion force are taken as the mold design targets, the die hole layout method in the mold design is the upper and lower double-hole layout in fig. 1, and the die hole layout is not beneficial to the control of the transverse structure and performance of the profile (as shown in fig. 3 (a)).
3. Most of domestic extruders are forward extruders, forward extrusion technology is adopted mostly, and only a small part of domestic extruders adopt backward extrusion technology. In the prior art, the heating temperature of each area of the ingot is the same, and the material is subjected to plastic deformation in the extrusion process to do work, so that the actual extrusion temperature of the head end of the section is lower, and the actual extrusion temperature of the tail end of the section is higher, so that the size, the structure and the performance of the head end and the tail end of the section are different greatly, and the use requirement of the civil airplane lower stringer cannot be met. According to the invention, an isothermal backward extrusion technology is adopted, the large-size ingot is subjected to partitioned electromagnetic induction heating, the temperature gradient control of the ingot is realized, the temperature of the front end of the ingot is high, the temperature of the tail end of the ingot is low, the heat generated by extrusion deformation work can compensate the temperature of the tail end of the ingot, the extrusion temperature difference of the head end and the tail end of the ingot is reduced, the isothermal extrusion is well realized, and the head-tail end difference caused by the increase of the extrusion temperature is reduced.
4. In the prior art, a vertical quenching furnace is mostly adopted for quenching, and the quenched section has large residual stress, so that the stringer is easily scrapped due to obvious plastic deformation in the machining process and cannot pass the machining verification link in the product authentication process. A small amount of prior art adopts a horizontal furnace for quenching, but the quenching process of the section is not deeply developed, the quenched section is taken as the first purpose, the problem of large quenching deformation is faced, the section can be fixedly placed in the horizontal furnace only by adopting a tool, the section with large deformation is clamped, and the quenching residual stress of the section is not reduced by adopting water quantity control. The invention adopts a low-stress step quenching technology, utilizes the characteristic that the water spray quantity of a quenching area of the spray type horizontal furnace is adjustable, adjusts the water spray quantity of a front area at a high position to improve the cooling speed and ensure the quenching effect, and adjusts the water spray quantity of a rear area to reduce the cooling speed and reduce the residual stress. Meanwhile, the warpage of the section in the quenching process is reduced by controlling the upper and lower water amounts in the quenching process, and the problem of water curtain shielding caused by fixture fixing is avoided. The 2026 profile is completely quenched, sufficient strength is guaranteed, the residual stress of the profile is reduced as much as possible, and low machining deformation is guaranteed.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a layout view of upper and lower die holes;
FIG. 2 is a left and right die hole layout of the present invention;
FIG. 3 is a cross-sectional microstructure of an extruded profile with different die hole layouts, wherein FIG. 3(a) is a cross-sectional microstructure of an extruded profile using an upper and lower double-hole die, and FIG. 3(b) is a microstructure of an extruded profile using a left and right double-hole die according to the present invention;
FIG. 4 is a section bar for civil aircraft wing lower stringer produced by the technique of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
The method comprises the following steps: and (3) producing a large-specification 2-series ingot with each index meeting the technical specification by adopting a semi-continuous casting mode, and carrying out homogenization annealing. Carrying out chemical analysis on the cast ingot, wherein the Si content is 0.042%, the Fe content is 0.051%, the Cu content is 3.86%, the Mg content is 1.24%, the Mn content is 0.54%, the Cr content is 0.0072%, the Ti content is 0.044% and the Zr content is 0.113%;
step two: heating and insulating the mould by using a box type mould heating furnace to ensure that the temperature of the core part of the mould reaches 390 ℃;
step three: the temperature of the extrusion cylinder is set to be 400 ℃, extrusion can be carried out after the temperature reaches, the temperature of the head end of the ingot casting is set to be 350 ℃, the temperature of the ingot casting from the head end to the tail end is in a gradient descending trend, and the temperature gradient is 30 ℃/m; putting the ingot heated to the temperature into an extrusion cylinder, putting one side of the head end of the ingot into a left-right double-hole die, carrying out reverse extrusion, wherein the extrusion shaft speed of the reverse extrusion is 1.5mm/s, and carrying out pre-stretching straightening after the extrusion is finished, wherein the deformation is 0.8% to obtain an aluminum alloy section bar primary product;
step four, carrying out solution treatment on the primary aluminum alloy section by adopting an off-line heat treatment process, wherein the solution treatment temperature is 494 ℃, the heat preservation time of the solution treatment is 90 min, and spray quenching cooling is adopted after the heat preservation is finished, wherein the quenching water quantity process parameters comprise that the water quantity of an upper front region nozzle is 330L/s, the water quantity of a lower front region nozzle is 220L/s, the water quantity of an upper rear region nozzle is 160L/s, the water quantity of a lower rear region nozzle is 130L/s, the quenching passing speed of the section is 250 mm/s, and the quenched section is immediately stretched and straightened, and the stretching deformation is 1.4%;
step five: and (4) placing the quenched, stretched and aligned section bar to be straight, and performing natural aging for more than 96 hours to obtain the aluminum alloy section bar.
Example 2
The method comprises the following steps: and (3) producing a large-specification 2-series ingot with each index meeting the technical specification by adopting a semi-continuous casting mode, and carrying out homogenization annealing. The ingot is subjected to chemical analysis, and the Si content is 0.042%, the Fe content is 0.053%, the Cu content is 3.79%, the Mg content is 1.34%, the Mn content is 0.49%, the Cr content is 0.0078%, the Ti content is 0.042%, and the Zr content is 0.103%;
step two: heating and insulating the mould by using a box type mould heating furnace to ensure that the temperature of the core part of the mould reaches 410 ℃;
step three: setting the temperature of an extrusion barrel to be 420 ℃, extruding after the temperature reaches, setting the temperature of the head end of an ingot casting to be 430 ℃, setting the temperature of the ingot casting from the head end to the tail end to be in a gradient descending trend, wherein the temperature gradient is 10 ℃/m, loading the ingot casting heated to the temperature into the extrusion barrel, loading one side of the head end of the ingot casting into a left double-hole die and a right double-hole die, carrying out reverse extrusion, wherein the extrusion shaft speed of the reverse extrusion is 1mm/s, and carrying out pre-stretching straightening after the extrusion is finished, wherein the deformation is 1.1% to obtain an aluminum alloy section;
step four, carrying out solution treatment on the primary aluminum alloy section by adopting an off-line heat treatment process, wherein the solution treatment temperature is 494 ℃, the heat preservation time of the solution treatment is 120 min, spray quenching cooling is adopted after the heat preservation is finished, and the quenching water quantity process parameters comprise 370L/s of water quantity of an upper front region nozzle, 240L/s of water quantity of a lower front region nozzle, 200L/s of water quantity of an upper rear region nozzle, 100L/s of water quantity of a lower rear region nozzle, the quenching passing speed of the section is 150mm/s, and the quenched section is immediately stretched and straightened, and the deformation is 2.4%;
step five: and (4) placing the quenched, stretched and aligned section bar to be straight, and naturally aging for over 96 hours to obtain the aluminum alloy section bar.
Example 3
The method comprises the following steps: and (3) producing a large-specification 2-series ingot with each index meeting the technical specification by adopting a semi-continuous casting mode, and carrying out homogenization annealing. Carrying out chemical analysis on the cast ingot, wherein the Si content is 0.045%, the Fe content is 0.049%, the Cu content is 4.09%, the Mg content is 1.38%, the Mn content is 0.64%, the Cr content is 0.0074%, the Ti content is 0.052%, and the Zr content is 0.103%;
step two: heating and insulating the mould by using a box type mould heating furnace to ensure that the temperature of the core part of the mould reaches 410 ℃;
step three: setting the temperature of an extrusion cylinder to be 420 ℃, setting the temperature of the head end of an ingot to be 410 ℃, setting the temperature of the ingot from the head end to the tail end to be in a gradient descending trend, setting the temperature gradient to be 20 ℃/m, loading the ingot heated to the temperature into the extrusion cylinder, loading one side of the head end of the ingot into a left-right double-hole die, carrying out reverse extrusion, setting the extrusion shaft speed of the reverse extrusion to be 1.2mm/s, carrying out pre-stretching straightening after the extrusion is finished, and obtaining an aluminum alloy section bar primary product with the deformation of 0.3%;
step four, carrying out solution treatment on the primary aluminum alloy section by adopting an off-line heat treatment process, wherein the solution treatment temperature is 494 ℃, the heat preservation time of the solution treatment is 100 min, and spray quenching cooling is adopted after the heat preservation is finished, wherein the quenching water quantity process parameters comprise that the water quantity of an upper front region nozzle is 370L/s, the water quantity of a lower front region nozzle is 240L/s, the water quantity of an upper rear region nozzle is 200L/s, the water quantity of a lower rear region nozzle is 100L/s, the quenching passing speed of the section is 200mm/s, the quenched section is immediately stretched and straightened, and the residual stress of quenching, namely the tensile deformation, is eliminated and is controlled to be;
step five: and (4) placing the quenched, stretched and aligned section bar to be straight, and naturally aging for over 96 hours to obtain the aluminum alloy section bar.
The performance of the aluminum alloy section obtained in the embodiment 1-3 of the invention is detected, and the result is shown in table 1. the section with the performance fully meeting the use requirement of the lower stringer of the wing is produced by a series of technological innovations through a process route of semi-continuous casting and reverse isothermal extrusion, L tensile strength exceeds 550 MPa, L yield strength exceeds 410 MPa, L T tensile strength exceeds 480 MPa, L T yield strength exceeds 340 MPa, L T stress corrosion performance meets the requirement that the corrosion does not occur for 30 days under 250 MPa.
Table 1 results of performance testing of examples
| Performance of | Example 1 | Example 2 | Example 3 |
| L tensile strength | 563.1MPa | 556.4MPa | 565.4MPa |
| L directional yield strength | 415.6MPa | 429.2MPa | 432.2MPa |
| L elongation in the direction of elongation | 21.5% | 21.3% | 20.9% |
| L T tensile Strength | 486.5MPa | 486.3MPa | 496.4MPa |
| L T yield strength | 349.2MPa | 349.2MPa | 351.2MPa |
| L T directional elongation | 22.1% | 22.9% | 21.8% |
| L T-direction stress corrosion performance | The stress corrosion does not occur for 30 days under the stress of 250MPa | The stress corrosion does not occur for 30 days under the stress of 250MPaEtching solution | The stress corrosion does not occur for 30 days under the stress of 250MPa |
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. The utility model provides a long purlin is with 2 series aluminum alloy ex-trusions under civil aircraft wing which characterized in that: the alloy section comprises the following substances in percentage by mass: the alloy comprises, by weight, less than 0.05% of Si, less than 0.06% of Fe, 3.7% -4.1% of Cu, 1.2% -1.4% of Mg, less than 0.4% -0.8% of Mn, less than 0.02% of Cr, 0.02% -0.06% of Ti, 0.08% -0.12% of Zr, less than 0.15% of other impurity elements, and the balance Al.
2. A manufacturing method of a 2-series aluminum alloy section for a lower stringer of a civil aircraft wing is characterized by comprising the following steps: the method comprises the following steps:
the method comprises the following steps: casting an ingot, and after the ingot is cast, carrying out homogenization annealing treatment;
step two: heating and insulating the mould by using a box type mould heating furnace, ensuring that the temperature of the core part of the mould reaches 390-410 ℃;
step three: setting the temperature of an extrusion cylinder to be 400-420 ℃, preserving heat after the temperature is reached, heating the cast ingot, loading the heated cast ingot into the extrusion cylinder with the tail end in the direction with the inner head end outside, loading a die with left and right double-hole layout into the extrusion cylinder to be close to the head end of the cast ingot, slowly inserting the die into a hollow shaft for reverse extrusion, and pre-stretching and straightening after the extrusion is finished to obtain an aluminum alloy section bar primary product;
step four: carrying out solution treatment on the primary aluminum alloy section by adopting an off-line heat treatment process, wherein the solution treatment temperature is 492-494 ℃, the heat preservation time of the solution treatment is 90-120 min, the sufficient solution treatment is ensured, quenching and cooling are carried out after the heat preservation is finished, and then the quenched section is immediately stretched and straightened, so that the quenching residual stress is eliminated;
step five: after quenching, cooling, stretching and straightening the section, placing the section to be straight, and naturally aging for more than 96 hours to obtain the aluminum alloy section.
3. The manufacturing method of the 2-series aluminum alloy section for the civil aircraft wing lower stringer according to claim 2, characterized in that: the ingot casting heating method in the third step comprises the following steps: the temperature of the head end of the ingot is set to be 350-430 ℃, the temperature of the ingot from the head end to the tail end is in a gradient descending trend, and the temperature gradient is 10-30 ℃/m.
4. The manufacturing method of the 2-series aluminum alloy section for the civil aircraft wing lower stringer according to claim 2, characterized in that: the ingot casting heating mode is induction heating.
5. The manufacturing method of the 2-series aluminum alloy section for the civil aircraft wing lower stringer according to claim 4, characterized in that: the heating method of induction heating comprises the following steps: the induction heating furnace is equally divided into a plurality of areas along the length direction of the cast ingot, and each area is provided with an independent induction heating coil, a thermocouple and a temperature control device; after the temperature and the temperature gradient of the head end of the ingot are set, automatically calculating the target heating temperature of each area by a program, and automatically inputting the target heating temperature into a temperature control device of each area for execution; in the heating process, each area executes independent heating and temperature control programs.
6. The manufacturing method of the 2-series aluminum alloy section for the civil aircraft wing lower stringer according to claim 2, characterized in that: and the extrusion shaft speed of the reverse extrusion in the third step is 1.0-1.5 mm/s.
7. The manufacturing method of the 2-series aluminum alloy section for the civil aircraft wing lower stringer according to claim 2, characterized in that: and the deformation amount of the pre-stretching and straightening in the third step is controlled to be less than 1.2 percent.
8. The manufacturing method of the 2-series aluminum alloy section for the civil aircraft wing lower stringer according to claim 2, characterized in that: and controlling the tensile deformation of the stretching and straightening in the step four to be 1-3%.
9. The manufacturing method of the 2-series aluminum alloy section for the civil aircraft wing lower stringer according to claim 2, characterized in that: and the quenching mode of the fourth step adopts spray quenching.
10. The method for manufacturing the 2-series aluminum alloy section for the civil aircraft wing lower stringer according to claim 9, wherein the spray quenching operation is that the quenching area is divided into two areas, the area close to the heat treatment furnace is a front area, the area far away from the heat treatment furnace is a rear area, the upper and lower water spraying devices of the two areas have independent adjusting capability, and the quenching water quantity process parameters are that the water quantity of the front area upper nozzle is 330-370L/s, the water quantity of the front area lower nozzle is 220-260L/s, the water quantity of the rear area upper nozzle is 160-200L/s, the water quantity of the rear area lower nozzle is 130-170L/s, and the section quenching passing speed is 150-250 mm/s.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114309110A (en) * | 2021-12-30 | 2022-04-12 | 山东兖矿轻合金有限公司 | Reverse extrusion forming method of 2XXX hard aluminum alloy seamless special-shaped cavity profile |
| CN114672678A (en) * | 2022-04-21 | 2022-06-28 | 西南铝业（集团）有限责任公司 | Preparation method of Al-Cu-Mg aluminum alloy large round ingot |
| CN115110012A (en) * | 2022-06-20 | 2022-09-27 | 中国航发北京航空材料研究院 | Preparation method of 2024 aluminum alloy sheet for aircraft chemical milling part |
| CN115821131A (en) * | 2022-12-05 | 2023-03-21 | 山东南山铝业股份有限公司 | 2-series aluminum alloy section with low fatigue crack propagation rate and manufacturing method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7604772B2 (en) * | 2000-12-12 | 2009-10-20 | Andrei Anatolyevich Axenov | Aluminum-based material and a method for manufacturing products from aluminum-based material |
| CN101613822A (en) * | 2009-06-23 | 2009-12-30 | 中南大学 | A kind ofly adopt trace zirconium or micro-scandium and Zirconium-micro-alloyed aluminium-cooper-maganesium alloy thin plate and preparation |
| CN103451583A (en) * | 2013-09-12 | 2013-12-18 | 中国商用飞机有限责任公司 | Method for producing profile for aircraft wing stringers |
| EP3052669B1 (en) * | 2013-09-30 | 2019-06-12 | Constellium Issoire | Underwing sheet metal with improved damage tolerance properties |
| CN110863128A (en) * | 2019-12-28 | 2020-03-06 | 东北轻合金有限责任公司 | Preparation method of 640 MPa-grade aluminum alloy extruded material for aviation |
-
2020
- 2020-04-02 CN CN202010255033.6A patent/CN111424199B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7604772B2 (en) * | 2000-12-12 | 2009-10-20 | Andrei Anatolyevich Axenov | Aluminum-based material and a method for manufacturing products from aluminum-based material |
| CN101613822A (en) * | 2009-06-23 | 2009-12-30 | 中南大学 | A kind ofly adopt trace zirconium or micro-scandium and Zirconium-micro-alloyed aluminium-cooper-maganesium alloy thin plate and preparation |
| CN103451583A (en) * | 2013-09-12 | 2013-12-18 | 中国商用飞机有限责任公司 | Method for producing profile for aircraft wing stringers |
| EP3052669B1 (en) * | 2013-09-30 | 2019-06-12 | Constellium Issoire | Underwing sheet metal with improved damage tolerance properties |
| CN110863128A (en) * | 2019-12-28 | 2020-03-06 | 东北轻合金有限责任公司 | Preparation method of 640 MPa-grade aluminum alloy extruded material for aviation |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114309110A (en) * | 2021-12-30 | 2022-04-12 | 山东兖矿轻合金有限公司 | Reverse extrusion forming method of 2XXX hard aluminum alloy seamless special-shaped cavity profile |
| CN114309110B (en) * | 2021-12-30 | 2024-05-07 | 山东兖矿轻合金有限公司 | Backward extrusion molding method of 2XXX hard aluminum alloy seamless special-shaped cavity section bar |
| CN114672678A (en) * | 2022-04-21 | 2022-06-28 | 西南铝业（集团）有限责任公司 | Preparation method of Al-Cu-Mg aluminum alloy large round ingot |
| CN114672678B (en) * | 2022-04-21 | 2023-08-22 | 西南铝业（集团）有限责任公司 | Preparation method of large round ingot of Al-Cu-Mg aluminum alloy |
| CN115110012A (en) * | 2022-06-20 | 2022-09-27 | 中国航发北京航空材料研究院 | Preparation method of 2024 aluminum alloy sheet for aircraft chemical milling part |
| CN115110012B (en) * | 2022-06-20 | 2023-10-20 | 中国航发北京航空材料研究院 | Preparation method of 2024 aluminum alloy sheet for chemically-milled parts of aircraft |
| CN115821131A (en) * | 2022-12-05 | 2023-03-21 | 山东南山铝业股份有限公司 | 2-series aluminum alloy section with low fatigue crack propagation rate and manufacturing method thereof |
| CN115821131B (en) * | 2022-12-05 | 2024-05-14 | 山东南山铝业股份有限公司 | Low fatigue crack growth rate 2-series aluminum alloy section bar and manufacturing method thereof |
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Denomination of invention: The invention relates to a 2-Series aluminum alloy profile for civil aircraft wing lower truss and a manufacturing method thereof Effective date of registration: 20211117 Granted publication date: 20210709 Pledgee: Yantai Donghai aluminum foil Co.,Ltd. Pledgor: Shandong Nanshan Aluminium Co.,Ltd. Registration number: Y2021980012518 |
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