CN111604463A - Preparation method of near-net-shape die forging for hub of civil aircraft - Google Patents
Preparation method of near-net-shape die forging for hub of civil aircraft Download PDFInfo
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- CN111604463A CN111604463A CN202010267690.2A CN202010267690A CN111604463A CN 111604463 A CN111604463 A CN 111604463A CN 202010267690 A CN202010267690 A CN 202010267690A CN 111604463 A CN111604463 A CN 111604463A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K1/00—Making machine elements
- B21K1/28—Making machine elements wheels; discs
- B21K1/40—Making machine elements wheels; discs hubs
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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
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Abstract
A preparation method of a near-net-shape die forging for a hub of a civil aircraft comprises the following steps: the method comprises the following steps: forging the cast ingot; step two: sawing and blanking; step three: flaw detection treatment; step four: molding a blank by using the tire; step five: pre-forging treatment; step six: finish forging treatment; step seven: and (6) heat treatment. According to the method for preparing the airplane hub near-net-shape die forging, the shapes of the pre-forging pieces are reasonably designed, and the processes of ingot casting forging changing, die forging forming and heat treatment are reasonably formulated, so that the forging pieces are enabled to be formed without folding, and flow lines are smoothly distributed along the outer contours of the forging pieces; the grain size of each part of the whole forge piece is uniformly controlled within the range of 9-9.5 grades, the structure is uniform, no surface coarse grains exist, the surface quality of the forge piece finished product is excellent, the near-net-shape forging is realized, and the forge piece can be directly installed for use without machining.
Description
Technical Field
The invention belongs to the field of manufacturing of civil aircraft hubs, and particularly relates to a preparation method of a near-net-shape die forging of a civil aircraft hub.
Background
At the end of the last 60 s, with the rapid development of the international civil aviation industry, an era of jet airliners replacing propeller airliners has come. In 1970, in 8 months, the project for developing the first large civil aircraft in China is formally started, and Shanghai aircraft manufacturers are responsible for manufacturing the aircraft, and the code of the aircraft is fortune ten. After ten years of arduous struggle, 9/26/1980, the first jet airliner developed by Chinese independently was successfully transported for ten years. The success of Yun Ten's development has made a miracle under the economic conditions and the state of the art in China at that time, but then the Yun Ten's project was set aside in 1985 for various reasons. In the later last 80 and 90 s, our country has performed several international cooperations to develop civilian aircraft, but eventually these attempts have not been continuously pushed forward.
With the rapid growth of the Chinese economy and the continuous development of the civil aviation industry, the aviation transportation industry shows huge market demands. The development of commercial aircraft with proprietary intellectual property is again being pursued. In 2002, ARJ21 new branch aircraft project of China is established, and in 2007, C919 development projects of large passenger aircraft are started. After more than ten years of efforts, ARJ21 eventually completed the whole process of development, test and operation of a commercial aircraft, and was formally put into airline operation in 2016. Next, in 2017, 5 months and 5 days, the first self-developed type in China fully adopts advanced technology and has completely independent intellectual property right, and the large jet airliner C919 realizes perfect first flight at Pudong international airport in Shanghai, which indicates that China really has the core capability of developing modern trunk aircrafts.
In 2019, 8, 1 month and 8 days, the fourth test flight aircraft of the domestic C919 large passenger plane finishes the first flight at Pudong international airport in Shanghai, and C919 takes one step towards the goal of putting into airline operation. It is predicted that in the next 20 years, the global commercial aircraft will deliver up to 4 million, with a total value of nearly 6 trillion dollars, with the Chinese new aircraft delivering up to 9000 more, accounting for 22% of the world. The way of large civil aircrafts in China is accelerating to meet the future.
The airplane wheel is an important component of an airplane landing system, and carries impact load of hundreds of tons of airplanes during takeoff high-speed running and hundreds of tons of airplanes during landing. The hub of airplane is an important part of airplane wheel, its external tyre and internal brake device are matched, and various loads produced when the airplane is landed and ground operation can be transferred into the hub by means of tyre, so that it is a main bearing component for plane sliding, taking-off and landing, and can play an important role for safety of airplane.
The landing speed and the weight of the airplane are continuously increased, the landing speed of the modern advanced airplane exceeds 350km/h, and the takeoff weight of the large-scale transport airplane is up to 600000 kg. At present, in one-time emergency braking, the airplane wheel braking device needs to absorb kinetic energy of an airplane exceeding 1500MJ to stop the airplane, and huge thermal shock is brought to the hub of the airplane.
Because of the severe working environment, the root of the rim of the hub of the airplane, the root of the hub adapter and the root of the fixed rim and the like are easy to generate fatigue cracks, and the generation of the fatigue cracks has great harm to the safety of the airplane. Therefore, the requirements on the mechanical strength, the fatigue strength, the tissue uniformity, the residual stress, the streamline distribution, the surface quality and the like of the airplane hub forging are extremely high.
The aluminum alloy airplane hub has the structural characteristics of high-rib thin-wall convex lugs and the like, and is complex in shape and difficult to form. Because large civil aircrafts start late in China and the technology is relatively laggard, the hub forged piece obtained by the existing preparation method of the aircraft hub forged piece in China often has the molding defects of folding, insufficient filling of lugs and fillets and the like; the forging piece has the structural defects of uneven structure, coarse crystals on the surface and the like; the forging has the defects of rough surface, large machining allowance, low material utilization rate, poor dimensional precision and the like. Therefore, the reasonable blank shape, the pre-forging shape, the near-net-shape forging process and the heat treatment process need to be researched and determined, the near-net-shape die forging product meeting various index requirements of the hub of the civil aircraft can be stably produced in batches at low cost, and the development of the manufacturing industry of the large civil aircraft in China is assisted.
Disclosure of Invention
The invention provides a preparation method of a near-net-shape die forging for a hub of a civil aircraft, which is used for overcoming the defects in the prior art.
The invention is realized by the following technical scheme:
a preparation method of a near-net-shape die forging for a hub of a civil aircraft comprises the following steps:
the method comprises the following steps: forging the cast ingot: heating the ingot casting blank, and upsetting and drawing on a free forging press to obtain a forging rod with fine and uniform tissues;
step two: sawing and blanking: precisely sawing and blanking a forging rod to obtain a forging stock with the height-diameter ratio of 2-2.5;
step three: flaw detection treatment: performing circumferential surface flaw detection on the forging stock with the height-diameter ratio of 2-2.5, and checking internal defects of the forging stock;
step four: blank molding by using a tire: upsetting the forging stock with the height-diameter ratio of 2-2.5 and qualified for flaw detection into a cake-shaped blank by using a blank die;
step five: pre-forging treatment: forging the cake blank into a pre-forging piece by using a pre-forging die, wherein the pre-forging piece is in a revolving body structure;
step six: and (3) finish forging treatment: forging and pressing the pre-forging piece by using a finish forging die to obtain a finish forging piece;
step seven: and (3) heat treatment: the final forging piece is firstly subjected to solid solution and quenching treatment processes, so that a second phase in a forging piece material is dissolved in an alloy matrix as much as possible to obtain a supersaturated solid solution, an aging treatment process is performed after the final forging piece is quenched and cooled, the supersaturated alloy matrix obtained after the solid solution treatment is decomposed in the aging process, fine and dispersed strengthening phases are precipitated, the mechanical property of the forging piece is improved, and the airplane hub die forging piece is obtained after the aging treatment.
The preparation method of the near-net-shape forming die forging piece for the hub of the civil aircraft comprises the steps that in the step one, the initial forging temperature of the cast ingot is 400-460 ℃, and the final forging temperature is 350-400 ℃. In the process, the upsetting ratio is kept between 2.0 and 3.0, the drawing ratio is kept between 6.0 and 8.0, and the forging is followed by air cooling to room temperature.
In the method for preparing the near-net-shape die forging for civil aircraft hub, the upsetting and drawing operation in the first step needs to be repeated for 2-3 times, and a heating operation is needed before each upsetting and drawing operation.
In the fourth step, the forging starting temperature of the forging stock is 400-460 ℃, the finish forging temperature is 350-400 ℃, and the upsetting speed is 7-12 mm/s. The deformation amount in this step is kept at 70-80%, and the steel sheet is air-cooled to room temperature after forging.
In the fifth step, the initial forging temperature of the cake blank is 400-.
In the sixth step, the forging starting temperature of the pre-forged piece is 400-.
The preparation method of the near-net forming die forging for the hub of the civil aircraft comprises the following specific operations of the solid solution and quenching treatment process in the seventh step: heating the final forging to 495-505 ℃, preserving heat for 155-175min, discharging from the furnace, cooling by water, wherein the quenching water temperature is 60-80 ℃, and the quenching transfer time is not more than 15 s.
The preparation method of the near-net forming die forging for the hub of the civil aircraft comprises the following specific operations in the seventh step: and heating the final forging after the solution treatment to 174 ℃ and 180 ℃, preserving heat for 579 and 609min, discharging and air cooling to room temperature.
According to the preparation method of the near-net forming die forging for the hub of the civil aircraft, the concrete structure of the rotary body pre-forging in the fifth step is as follows: the barrel bottom of the preforging piece is a plane, the wall thickness and the drawing gradient are similar to those of the final forging piece, but the depth of the barrel is shallower than that of the final forging piece, and the outer brim of the barrel is a curved surface with a concave-convex structure.
In the fourth step and the fifth step, the lower die of the tire die and the lower die of the pre-forging die are both designed with positioning structures so as to ensure that the blank is positioned at the center of the die during forging and realize uniform deformation of all parts of the blank during forging.
According to the preparation method of the near-net forming die forging for the civil aircraft hub, in the fifth step and the sixth step, the pre-forging die and the finish-forging die are both designed with anti-sticking structures, so that smooth demolding and no damage to the surface of the forging are guaranteed.
According to the preparation method of the near-net-shape forming die forging piece for the civil aircraft hub, in the fifth step and the sixth step, the pre-forging die and the finish-forging die are both provided with the lock catch guide mechanisms, so that the workpiece is prevented from being shifted in the forging process.
According to the preparation method of the near-net forming die forging for the civil aircraft hub, in the fifth step and the sixth step, the lubricant with the HYKOGEEN AL2931 MBA-C type is selected in the pre-forging process and the final forging process, so that a good lubricating effect is ensured, and excellent surface quality is obtained.
The invention has the advantages that:
1. aiming at the problems of folding, underfilling, uneven forging structure, coarse grain on the surface, rough surface, poor dimensional precision, large machining allowance, low material utilization rate, poor process applicability, poor stability and the like in the preparation of the existing airplane hub die forging, the preparation method of the airplane hub near-net forming die forging provided by the invention reasonably formulates the processes of ingot casting forging changing, die forging forming and heat treatment through reasonably designing the shape of a pre-forging, and ensures that the forging is formed without folding and streamline is smoothly distributed along the outer contour of the forging; the grain size of each part of the whole forge piece is uniformly controlled within the range of 9-9.5 grades, the structure is uniform, no surface coarse grains exist, the surface quality of the finished product of the forge piece is excellent, the near-net-shape forging is realized, and the forge piece can be directly installed for use without machining; in addition, the tensile strength level of the finished product of the forged piece is 10% higher than the international universal standard, the fatigue strength meets the enterprise standard of international aviation manufacturers, and the residual stress level is low. The method for preparing the airplane hub near-net forming die forging is in the leading level of the international airplane hub preparation process; in addition, the preparation method has good stability and high production efficiency, and the mass stable production of the finished product of the forged piece is realized at present.
2. The invention has realized the near net shaping is made, this forging belongs to the deep tubiform mould forging, the depth of cavity is 300mm, and the thin rib of high muscle has lugs, the forging shaping is difficult, the sticking tendency is large, the near net shaping mould forging preparation method of wheel hub of civil aircraft that the invention provides, guarantee the surface is bright and clean through the rational material selection of the mould, designed the special anti-sticking structure at the same time, guaranteed the forging is demolded smoothly, the surface is not damaged; by selecting the special lubricant, good lubricating effect is ensured, the final forged piece has excellent surface quality, all the forged pieces leaving the factory are subjected to surface fluorescence permeation detection and meet the requirement of secondary sensitivity, and can be directly installed and used without machining, so that the small-allowance-free near-net-shape forming of the forged piece is realized, and the method belongs to the highest level of the international airplane hub forging process;
3. the invention realizes fine grain control, and the airplane hub forged piece is easy to have coarse grains on the surface and uneven structure performance, so that the performance weak points of the forged piece are increased, and the service reliability is reduced;
4. the method for preparing the near-net forming die forging of the civil aircraft hub provided by the invention has the advantages that firstly, deformation is reasonably distributed through stages of ingot casting forging changing, blank molding, die forging forming and the like, so that the material is ensured to obtain a sufficient and uniform forging ratio; secondly, by reasonably designing the preforging die, the material flows strictly according to the appearance of the forging piece in the forming process, and the streamline reinforcement is realized; and finally, a reasonable heat treatment process system is selected, the precipitation strengthening effect is ensured, the fatigue strength of the final forged piece finished product meets the enterprise standard of international aviation manufacturers, and the tensile strength is 10% higher than the international universal standard.
5. The forging forming numerical simulation technology is adopted, the Deform forming simulation technology is fully utilized in the product development process, and a large amount of simulation analysis is carried out on a temperature field and a strain field, so that the optimal deformation degree, temperature and speed process parameter combination is determined, and powerful theoretical support is provided for mastering the technical means without surface coarse grains; meanwhile, the simulation of streamline, pressing force, forging ratio, die stress analysis and the like in material flow provides the most direct and reliable basis for die design, blank/pre-forging design, equipment selection and the like, the product development is completed quickly and efficiently, and the batch production is realized.
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 three-dimensional structure view of a near-net-shape die forging of a hub of a civil aircraft according to the invention;
FIG. 2 is a cross-sectional view of the three-dimensional structure of the near-net-shape die forging of the civil aircraft hub of the invention;
FIG. 3 is a schematic flow chart of a method for manufacturing a near-net-shape die forging for a hub of a civil aircraft, provided by the invention;
FIG. 4 is a schematic flow chart of a forging process of a near-net-shape die forging for a hub of a civil aircraft provided by the invention;
FIG. 5 is a grain structure diagram of a finish forged part provided by the present invention after heat treatment;
FIG. 6 is a finished product diagram of the near-net forming die forging of the civil aircraft hub.
Reference numerals: 1. ingot casting blank; 2. forging a rod; 3. forging a blank; 4. a cake-shaped blank; 5. pre-forging; 6. and (5) finishing the forged piece.
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: forging the cast ingot: heating the ingot blank 1 to 430 ℃, upsetting the ingot blank for two times on a free forging press, wherein the initial forging temperature of the ingot blank 1 is 410 ℃, the final forging temperature is 350 ℃, the upsetting ratio is 2.3, drawing the ingot blank 1 after upsetting is carried out, the drawing ratio is 6.6, and air cooling to room temperature after drawing to obtain a forging rod 2 with fine and uniform tissue;
step two: sawing and blanking: precisely sawing and blanking the forging rod 2 to obtain a forging stock 3 with the height-diameter ratio of 2.2, and preparing a blank for a blank die blank;
step three: flaw detection treatment: performing circumferential surface flaw detection on the forging stock 3 with the height-diameter ratio of 2.2 obtained in the step two, and checking internal defects of the forging stock;
step four: blank molding by using a tire: heating a qualified forging blank 3 with a height-diameter ratio of 2.2 to 430 ℃, upsetting the forging blank 3 on a forging press by using a blank die, wherein the upsetting starting forging temperature is 410 ℃, the final forging temperature is 350 ℃, the upsetting speed is 8mm/s, and the deformation is kept at 75%, meanwhile, the lower die of the blank die is provided with a positioning structure to ensure that the forging blank 3 is positioned at the central position of the die during forging, so that the uniform deformation of all parts of the blank during forging is realized, and the blank is air-cooled to room temperature after forging to obtain a cake-shaped blank 4;
step five: pre-forging treatment: heating a cake-shaped blank 4 to 440 ℃, forging and pressing the cake-shaped blank 4 on a forging press by using a pre-forging die, coating a lubricant on the surface of the cake-shaped blank 4 and the inner surface of the pre-forging die before forging and pressing, simultaneously arranging a positioning structure on the lower die of the pre-forging die, arranging an anti-sticking structure on the inner surface of the pre-forging die, arranging a lock catch guide mechanism on the pre-forging die to ensure that the blank is positioned at the central position of the die during forging, realizing uniform deformation of all parts of the blank during forging, leading a forge piece to be smooth in die stripping and free of surface damage, preventing the workpiece from shifting in the forging process, effectively improving the qualification rate and performance of the pre-forging piece, wherein the forging starting temperature is 420 ℃, the final forging temperature is 360 ℃, the die temperature is 360 ℃, the forging speed is 3mm/s, air cooling to room temperature after forging, and processing burrs;
step six: and (3) finish forging treatment: heating a pre-forging piece 5 to 440 ℃, forging and pressing the pre-forging piece 5 on a forging press by using a finish forging die, coating a lubricant on the surface of the pre-forging piece 5 and the inner surface of the finish forging die before forging and pressing, simultaneously arranging an anti-sticking die structure on the inner surface of the finish forging die, arranging a lock catch guide mechanism on the finish forging die so as to ensure that a forging piece is smoothly demoulded and has no surface damage, preventing the workpiece from being displaced in the forging process, effectively improving the qualification rate and the performance of the finish forging piece, cooling the forging start forging temperature to 420 ℃, the finish forging temperature to 360 ℃, the die temperature to 360 ℃, the forging speed to 3mm/s, cooling the forging piece to room temperature after forging, and treating the inner and outer rough surfaces to obtain a finish forging piece;
step seven: and (3) heat treatment: placing the final forging 6 into a heating furnace, preserving heat at 495-505 ℃ for 155-175min, taking out of the furnace, cooling by water, wherein the quenching water temperature is 60-80 ℃, and the quenching transfer time is not more than 15 s; and (3) placing the final forging after the solid solution and quenching treatment into a heating furnace, preserving heat for 579-609min at the temperature of 174-180 ℃, taking out of the furnace, and air-cooling to room temperature to obtain a civil engine hub finished product.
Verification experiment
And (3) detecting the fatigue strength, the tensile strength, the elongation after fracture, the grain size, the residual stress, the surface quality and the like of the civil airplane hub die forging finished product. The surface quality is detected by adopting a fluorescence penetration method, the residual stress is detected on 3 specific parts by adopting a blind hole method, and the result is as follows: the fatigue strength is 61971N when the stress level is 400 MPa; the fatigue strength is 186426N when the stress level is 350 MPa; at a stress level of 320MPa, a fatigue strength of 107N is not broken. The axial tensile strength is 478MPa, the axial yield strength is 426MPa, the elongation after axial fracture is 9.1 percent, the chord direction tensile strength is 472MPa, the chord direction yield strength is 415MPa, and the elongation after chord direction fracture is 4.2 percent. No surface coarse grains exist, the grain size of each part of the whole forging is uniformly controlled within the range of 9-9.5 grades, and the structure is uniform. The three-point residual stress test result is-100 MPa, -99MPa and-97 MPa. The surface quality meets the requirement of secondary sensitivity.
The qualified standard of the product is as follows: the fatigue test is carried out by the client in the internal laboratory, and is automatically judged according to the internal indexes. The axial tensile strength is more than 440MPa, the axial yield strength is more than 390MPa, and the elongation after axial fracture is more than 8%; the chord-direction tensile strength is more than 440MPa, the chord-direction yield strength is more than 380MPa, and the elongation after chord-direction fracture is more than 3%. The grain size is not less than 5 grade, and the depth of the surface coarse grain layer is not more than 1.6 mm. The residual stress index is in the range of-120 MPa to 50 MPa. Surface quality requires secondary sensitivity of fluorescence detection.
The data show that the finished product of the forging provided by the invention has the advantages that the tensile property is higher than the index by about 10%, the fatigue strength is high, the residual stress level is low, the crystal grains of the whole forging are fine and uniform, no coarse grains are on the surface, the surface quality is excellent, the near-net-shape forging is realized, the forging can be directly installed for use without machining, the product quality is in the international leading position, and a high-quality hub can be provided for civil engineering manufacture, so that a powerful support can be provided for the manufacturing industry of large civil engineering in China.
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. A preparation method of a near-net-shape die forging for a hub of a civil aircraft is characterized by comprising the following steps of: the method comprises the following steps:
the method comprises the following steps: forging the cast ingot: heating the ingot casting blank, and upsetting and drawing on a free forging press to obtain a forging rod with fine and uniform tissues;
step two: sawing and blanking: precisely sawing and blanking a forging rod to obtain a forging stock with the height-diameter ratio of 2-2.5;
step three: flaw detection treatment: performing circumferential surface flaw detection on the forging stock with the height-diameter ratio of 2-2.5, and checking internal defects of the forging stock;
step four: blank molding by using a tire: upsetting the forging stock with the height-diameter ratio of 2-2.5 and qualified for flaw detection into a cake-shaped blank by using a blank die;
step five: pre-forging treatment: forging the cake blank into a pre-forging piece by using a pre-forging die, wherein the pre-forging piece is in a revolving body structure;
step six: and (3) finish forging treatment: forging and pressing the pre-forging piece by using a finish forging die to obtain a finish forging piece;
step seven: and (3) heat treatment: the final forging piece is firstly subjected to solid solution and quenching treatment processes, so that a second phase in a forging piece material is dissolved in an alloy matrix as much as possible to obtain a supersaturated solid solution, an aging treatment process is performed after the quenching treatment of the final forging piece is completed, the supersaturated alloy matrix obtained after the solid solution treatment is decomposed in the aging process, fine and dispersed strengthening phases are precipitated, the mechanical property of the forging piece is improved, and an airplane hub die forging piece finished product is obtained after the aging treatment is completed.
2. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps: in the first step, the initial forging temperature of the ingot is 400-460 ℃, and the final forging temperature is 350-400 ℃. In the process, the upsetting ratio is kept between 2.0 and 3.0, the drawing ratio is kept between 6.0 and 8.0, and the forging is followed by air cooling to room temperature.
3. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps: in the first step, the upsetting and drawing operation needs to be repeated for 2-3 times, and heating operation is needed before each upsetting and drawing operation.
4. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps: in the fourth step, the initial forging temperature of the forging stock is 400-460 ℃, the final forging temperature is 350-400 ℃, and the upsetting speed is 7-12 mm/s. The deformation amount in this step is kept at 70-80%, and the steel sheet is air-cooled to room temperature after forging.
5. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps: in the fifth step, the initial forging temperature of the cake blank is 400-400 ℃, the final forging temperature is 350-400 ℃, the die temperature is 350-400 ℃, the forging speed is 1-5mm/s, and the cake blank is air-cooled to the room temperature after forging.
6. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps: in the sixth step, the initial forging temperature of the pre-forging piece is 400-460 ℃, the final forging temperature is 350-400 ℃, the die temperature is 350-400 ℃, the forging speed is 1-5mm/s, and the pre-forging piece is air-cooled to the room temperature after being forged.
7. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps:
the solid solution and quenching treatment process in the seventh step comprises the following specific operations: heating the final forging to 495-;
the aging treatment process in the seventh step comprises the following specific operations: and heating the final forging after the solution treatment to 174 ℃ and 180 ℃, preserving heat for 579 and 609min, discharging and air cooling to room temperature.
8. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps: the concrete structure of the revolving body pre-forging in the step five is as follows: the barrel bottom of the preforging piece is a plane, the wall thickness and the drawing gradient are similar to those of the final forging piece, but the depth of the barrel is shallower than that of the final forging piece, and the outer brim of the barrel is a curved surface with a concave-convex structure.
9. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps: in the fourth step and the fifth step, the lower die of the tire die and the lower die of the pre-forging die are both provided with positioning structures so as to ensure that the blank is positioned at the center of the die during forging and realize uniform deformation of all parts of the blank during forging.
10. The method for preparing the near-net-shape die forging for the hub of the civil aircraft as claimed in claim 1, wherein the method comprises the following steps:
in the fifth step and the sixth step, the pre-forging die and the finish-forging die are both designed with anti-sticking structures, so that the smooth demolding and surface damage prevention of the forge piece are ensured;
in the fifth step and the sixth step, the pre-forging die and the finish forging die are both provided with lock catch guide mechanisms to prevent the workpiece from shifting in the forging process;
in the fifth step and the sixth step, the pre-forging process and the final forging process both adopt a lubricant with the model of HYKOGEEN AL2931 MBA-C, so that a good lubricating effect is ensured, and excellent surface quality is obtained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010267690.2A CN111604463A (en) | 2020-04-08 | 2020-04-08 | Preparation method of near-net-shape die forging for hub of civil aircraft |
Applications Claiming Priority (1)
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