Method for manufacturing semi-circular structural beam aluminum alloy die forgings for aircraft

Abstract

The application relates to a manufacturing method of an aluminum alloy die forging piece of a semicircular structural beam for aviation, and belongs to the technical field of metal materials. The method solves the problems of non-molding, folding defects and substandard mechanical properties in the preparation of the existing semicircular structural beam for aviation. The method comprises the following steps: S1, casting an aluminum alloy ingot; S2, extruding a rod; S3, bending; S4, pre-pressing forming; S5, etching and repairing, and performing one-time die forging forming; S6, etching and repairing, and performing two-time die forging forming; and sequentially performing etching and repairing, pre-fire inspection, quenching treatment and aging treatment, so that the manufacturing of the aluminum alloy die forging piece of the semicircular structural beam for aviation is completed. The aluminum alloy die forging piece of the semicircular structural beam for aviation manufactured by the application not only meets the standard requirements in size, but also is easy to form, has high material utilization rate, is not prone to folding defects, increases the service life of the die forging piece, meets the performance requirements of an aviation engine, and improves the stress deformation characteristics in the machining process and the use process of the user. The application is suitable for manufacturing the aluminum alloy die forging piece of the semicircular structural beam for aviation.

Description

Technical Field

[0001] This invention belongs to the field of metal materials technology, specifically relating to a method for manufacturing aluminum alloy forgings for semi-circular structural beams for aerospace applications. Background Technology

[0002] With the rapid development of the aerospace industry, the performance requirements for ultra-high strength aluminum alloy structural components are becoming increasingly stringent. Structural components are evolving towards higher performance, precision, and complexity. Some load-bearing structural components in carrier-based aircraft, due to the influence of the operating environment, need to be designed as semi-circular shapes. These components not only require high performance but also a defect-free surface to prevent deformation during use, placing even higher demands on these irregularly shaped structural components.

[0003] Existing forged parts of this type have a semi-circular structure. If the blank dimensions are not up to standard, it will result in an incomplete and defective forging after molding. After quenching, the semi-circular shape experiences high stress, often leading to deformation that renders it unworkable. The arc has many reinforcing ribs, and folding defects exist after molding. If these defects are not properly repaired, the forging is prone to breakage along the folds during use, posing a safety hazard to aircraft. This invention solves the problems of incomplete molding and folding defects. By optimizing the process, stress deformation is addressed, mechanical properties meet standards, and a stable supply can be achieved. Summary of the Invention

[0004] The purpose of this invention is to solve the problems of incomplete forming, folding defects and substandard mechanical properties in the existing preparation of semi-circular structural parts for aviation, and to provide a method for manufacturing aluminum alloy forgings of semi-circular structural beams for aviation.

[0005] A method for manufacturing aluminum alloy forgings for semi-circular structural beams for aerospace applications, comprising the following steps:

[0006] I. Casting of Aluminum Alloy Ingots: The aluminum alloy ingots are cylindrical ingots with dimensions of Φ405×900mm; the mass percentage of elements in the aluminum alloy ingots is as follows: Si ≤0.10%~0.25%, Fe ≤0.9%~1.4%, Cu 2.0%~2.6%, Mn ≤0.10%, Mg 1.2%~1.8%, Cr 0.10%, Ni 0.9%~1.4%, Zn 0.10%, Ti ≤0.05%~0.10%, individual impurities ≤0.05%, total impurities ≤0.15%, and the remainder is Al;

[0007] 2. After the above-mentioned aluminum alloy ingots are loaded into the furnace, they are heated to 320℃~350℃, and then extruded into bars. After the extruded bars are cut off at the head and tail and then cut into bars with a length of 1650mm as blanks.

[0008] 3. The above-mentioned blank is heated to 420-450℃, the initial forging temperature of the blank is 430℃, and then it is bent on a 5000-ton vertical free forging hydraulic press. The die temperature is 350℃-400℃. The blank is bent into a blank that is the same as the template according to the bending process.

[0009] IV. Pre-pressing of blanks: The blanks obtained in step three are heated to 420℃~450℃, the first forging temperature is 430℃~440℃, the first final forging temperature is 400℃~430℃, the last forging temperature is 430℃~450℃, the last final forging temperature is 400℃~430℃, and the die temperature is 360℃~380℃ to obtain pre-pressed forgings;

[0010] 5. The pre-pressed forgings obtained in step 4 are subjected to etching and cleaning for repair, and then subjected to one die forging. The heating temperature of the pre-pressed forgings is 420℃~450℃, the initial forging temperature of the first piece is 420℃~440℃, the final forging temperature of the first piece is 400℃~430℃, the initial forging temperature of the last piece is 410℃~430℃, the final forging temperature of the last piece is 400℃~420℃, and the die temperature is 360℃~380℃ to obtain the die forgings.

[0011] VI. The forgings obtained in step 5 are subjected to etching and cleaning for repair, then subjected to two die forging processes, followed by etching and cleaning for repair, pre-fire inspection, quenching treatment and aging treatment in sequence, thus completing the manufacturing of aluminum alloy forgings for semi-circular structural beams for aviation.

[0012] Furthermore, in step two, the aluminum alloy ingots must be cleaned of dust, aluminum shavings, and burrs before being loaded into the furnace; during loading, the aluminum alloy ingots must be placed neatly and stably on the material tray.

[0013] Furthermore, in step two, the extrusion process involves using a 5000-ton horizontal hydraulic press with a Ф420mm extrusion cylinder to extrude bars with a diameter of Φ95mm. The cylinder temperature is 320℃~380℃, the extrusion speed is ≤0.6mm / S, and the extrusion is performed using a reverse extrusion method. The extrusion residue must be less than 25mm.

[0014] Furthermore, the etching and repair process described in steps five and six is ​​the same: the part to be cleaned is placed upright in a stainless steel etching basket, and etched and degreased in an alkaline bath of 15% to 20 wt% NaOH at 50℃ to 70℃ for 10 to 20 minutes. Then, it is washed with alkaline solution in a cold water bath at room temperature, and then neutralized and washed with acid in an acid bath of 30% to 40 wt% HNO3 at room temperature for 5 to 8 minutes. Then, it is washed with acid in a cold water bath at room temperature. Finally, the part is rinsed in a hot water bath at 50 to 70℃. After being taken out, it is placed on a repair area with aluminum pads on the ground for repair. Defects in the forging are checked and removed.

[0015] Furthermore, in step six, the two-stage die forging process is as follows: Before die forging, the impurities in the die cavity are removed with compressed air, the upper and lower dies are installed and lubricated with sand oil, and the forging temperature of the first and last pieces of each horizontal stack is 400℃~450℃ when the die forgings are taken out of the furnace. The die forging is carried out in a 5000-ton vertical free forging hydraulic press. The die forgings are subjected to two die forgings. During the final pressing, the lubrication and pressure are applied twice, then the air is released after lifting the car, and then the pressure is applied again. The first piece is then inspected, and the mark is printed in the specified position. Then the burrs are removed. The residual amount of burrs after cutting is less than or equal to 8mm, and undercut is not allowed.

[0016] Furthermore, the two lubrication processes employ a mixture of abrasive oil and graphite as the lubricant; the mass ratio of the abrasive oil to graphite is 7:(2~3).

[0017] Furthermore, in step six, the quenching process is as follows: the forgings and test samples that have completed the pre-quenching inspection are placed flat in the quenching basket and quenched at 529℃~535℃. The holding time is 150~180min for air holding, and the temperature of the water used for quenching is 40℃~60℃. The quenching transfer time is less than or equal to 15s, and the quenching basket is raised and lowered in the water more than 5 times. After staying in the water for 15min, it is lifted out of the water and the quenching furnace number is marked to the specified position.

[0018] Furthermore, the test sample is obtained by randomly selecting one die forging from the same batch that has completed the pre-fire inspection, cutting and sampling it.

[0019] Furthermore, the aging treatment described in step six involves aging at 191℃~198℃, with a holding time of 12 hours for the metal and a total heating time of 12 hours~18 hours.

[0020] The aluminum alloy forgings for semi-circular structural beams for aviation manufactured by this invention not only meet the standard requirements in terms of dimensions, but also improve the overall performance of the semi-circular forgings. It improves the stress deformation characteristics during the machining and use processes, reduces defects in low-magnification microstructure, improves the load-bearing capacity of the forgings, and extends the service life of the aluminum alloy forgings for semi-circular structural beams, thus meeting the requirements for aluminum alloy forgings for semi-circular structural beams for aviation.

[0021] This invention discloses a method for manufacturing aluminum alloy forgings for semi-circular structural beams used in aviation. Characterized by improved load-bearing capacity of irregularly shaped forgings, the method facilitates easy forming, high material utilization, and minimizes the risk of folding defects, thereby increasing the service life of the forgings and meeting the performance requirements of aero-engines. This invention enables stable production of irregularly shaped structural components, reducing the manufacturing cost of carrier-based aircraft. This technology has broad application value in the aviation field, and can be used in the actual production of similar irregularly shaped forgings to improve their load-bearing capacity and service life. It has significant social implications for strengthening modernization and also offers substantial economic benefits.

[0022] This invention is applicable to the manufacture of aluminum alloy die forgings for semi-circular structural beams for aviation applications. Detailed Implementation

[0023] The technical solution of the present invention is not limited to the specific embodiments listed below, but also includes any combination of the specific embodiments.

[0024] Specific Implementation Method 1: This implementation method describes the manufacturing method of aluminum alloy forgings for semi-circular structural beams used in aviation, which is carried out according to the following steps:

[0025] I. Casting of Aluminum Alloy Ingots: The aluminum alloy ingots are cylindrical ingots with dimensions of Φ405×900mm; the mass percentage of elements in the aluminum alloy ingots is as follows: Si ≤0.10%~0.25%, Fe ≤0.9%~1.4%, Cu 2.0%~2.6%, Mn ≤0.10%, Mg 1.2%~1.8%, Cr 0.10%, Ni 0.9%~1.4%, Zn 0.10%, Ti ≤0.05%~0.10%, individual impurities ≤0.05%, total impurities ≤0.15%, and the remainder is Al;

[0026] 2. After the above-mentioned aluminum alloy ingots are loaded into the furnace, they are heated to 320℃~350℃, and then extruded into bars. After the extruded bars are cut off at the head and tail and then cut into bars with a length of 1650mm as blanks.

[0027] 3. The above-mentioned blank is heated to 420-450℃, the initial forging temperature of the blank is 430℃, and then it is bent on a 5000-ton vertical free forging hydraulic press. The die temperature is 350℃-400℃. The blank is bent into a blank that is the same as the template according to the bending process.

[0028] IV. Pre-pressing of blanks: The blanks obtained in step three are heated to 420℃~450℃, the first forging temperature is 430℃~440℃, the first final forging temperature is 400℃~430℃, the last forging temperature is 430℃~450℃, the last final forging temperature is 400℃~430℃, and the die temperature is 360℃~380℃ to obtain pre-pressed forgings;

[0029] 5. The pre-pressed forgings obtained in step 4 are subjected to etching and cleaning for repair, and then subjected to one die forging. The heating temperature of the pre-pressed forgings is 420℃~450℃, the initial forging temperature of the first piece is 420℃~440℃, the final forging temperature of the first piece is 400℃~430℃, the initial forging temperature of the last piece is 410℃~430℃, the final forging temperature of the last piece is 400℃~420℃, and the die temperature is 360℃~380℃ to obtain the die forgings.

[0030] VI. The forgings obtained in step 5 are subjected to etching and cleaning for repair, then subjected to two die forging processes, followed by etching and cleaning for repair, pre-fire inspection, quenching treatment and aging treatment in sequence, thus completing the manufacturing of aluminum alloy forgings for semi-circular structural beams for aviation.

[0031] In step one of this embodiment, the aluminum alloy ingot is cast using conventional methods.

[0032] Specific Implementation Method Two: This implementation method differs from Specific Implementation Method One in that the mass percentage of elements in the aluminum alloy ingot mentioned in step one is as follows: Si 0.10%, Fe 0.8%, Cu 2.2%, Mn 0.10%, Mg 1.5%, Cr 0.10%, Ni 1.0%, Zn 0.10%, Ti 0.05%, with individual impurities ≤0.05%, total impurities ≤0.15%, and the remainder being Al. Everything else is the same as in Specific Implementation Method One.

[0033] Specific Implementation Method Three: This implementation method differs from Specific Implementation Method One in that, in step two, the aluminum alloy ingots must be cleaned of surface dust, aluminum shavings, and burrs before being loaded into the furnace; during loading, the aluminum alloy ingots must be placed neatly and stably on the material tray. Other steps and parameters are the same as in Specific Implementation Method One.

[0034] Specific Implementation Method Four: This implementation method differs from Specific Implementation Method One in that, in step two, the extrusion process involves using a 5000-ton horizontal hydraulic press with a Ф420mm extrusion cylinder to extrude bars with a diameter of Φ95mm. The cylinder temperature is 320℃~380℃, the extrusion speed is ≤0.6mm / S, and a reverse extrusion method is used. The extrusion residue must be less than 25mm. Other steps and parameters are the same as in Specific Implementation Method One.

[0035] In this embodiment, the extrusion speed is ≤0.6mm / S, the purpose of which is to control the formation of coarse crystal rings.

[0036] In step three of this embodiment, the curvature of the bend must reach the specified dimensions to facilitate the forming and performance of the forging.

[0037] Specific Implementation Method Five: This implementation method differs from Specific Implementation Method One in that the etching and repair process described in steps five and six is ​​the same: The workpiece to be cleaned is placed upright in a stainless steel etching basket and etched and degreased in an alkaline bath of 15%–20wt% NaOH at 50℃–70℃ for 10–20 minutes. Then, it is rinsed in a cold water bath at room temperature to remove the alkaline solution, followed by neutralization and whitening in an acid bath of 30–40wt% HNO3 at room temperature for 5–8 minutes. The acid solution is then rinsed in a cold water bath at room temperature. Finally, the workpiece is rinsed in a hot water bath at 50–70℃. After removal, it is placed in a repair area with aluminum pads on the ground for repair, and any defects in the forging are inspected and removed. Other steps and parameters are the same as in Specific Implementation Method One.

[0038] The side-standing placement described in this embodiment is intended to prevent the etching liquid from flowing in and out of the inner cavity of the forging, thus ensuring incomplete etching.

[0039] The defects in the forgings described in this embodiment refer to defects such as folding and dents.

[0040] In this embodiment, the forgings are placed upright in a special stainless steel etching basket, and care must be taken to prevent them from being bumped or damaged during the process.

[0041] Specific Implementation Method Six: This implementation method differs from Specific Implementation Method One in that step six involves two forging processes: Before forging, compressed air is used to remove impurities from the die cavity. The upper and lower dies are installed and lubricated with sand oil. When the forged parts exit the furnace, the initial forging temperature and final forging temperature of the first and last pieces of each horizontal stack are 400℃~450℃. The die forming is carried out in a 5000-ton vertical free forging hydraulic press. The forged parts undergo two die pressing processes. During the final pressing, lubrication and pressure are applied twice. Then, the machine is lifted to release air before pressing is applied again. The first piece is then inspected, and the mark is printed in the specified position. Then, the burrs are removed. The residual burrs after cutting are less than or equal to 8mm, and undercut is not allowed. Other steps and parameters are the same as in Specific Implementation Method One.

[0042] Specific Implementation Method Seven: This implementation method differs from Specific Implementation Method Six in that the two lubrication processes use a mixture of sand-in-oil and graphite as the lubricant; the mass ratio of the sand-in-oil to graphite is 7:(2~3). Other steps and parameters are the same as in Specific Implementation Method Six.

[0043] In this embodiment, the imprint is printed in the specified position, and the handwriting must be neat and clear.

[0044] Specific Implementation Method Eight: This implementation method differs from Specific Implementation Method One in that, in step six, the quenching process is as follows: The forgings and test samples that have undergone pre-quenching inspection are placed flat in a quenching basket and quenched at 529℃~535℃. The holding time is 150~180min (based on air holding). The temperature of the water used for quenching is 40℃~60℃. The quenching transfer time is less than or equal to 15s, and the quenching basket is raised and lowered in the water at least 5 times. After remaining in the water for 15min, it is lifted out of the water. When marking the quenching furnace number, it must be marked to the specified position. Other steps and parameters are the same as in Specific Implementation Method One.

[0045] Specific Implementation Method Nine: This implementation method differs from Specific Implementation Method Eight in that the test sample is obtained by randomly selecting one die forging from the same batch that has completed pre-fire inspection, cutting and sampling it. Other steps and parameters are the same as in Specific Implementation Method Eight.

[0046] In this embodiment, the workpiece is placed flat in a square quenching basket to facilitate the flow of water through the inner cavity of the forging.

[0047] In this embodiment, the quenching furnace number must be written neatly and clearly.

[0048] Specific Implementation Method Ten: This implementation method differs from Specific Implementation Method One in that the aging treatment in step six is ​​performed at 191℃~198℃, with a holding time of 12 hours for the metal, and a total heating time of 12 hours~18 hours. Other steps and parameters are the same as in Specific Implementation Method One.

[0049] In this embodiment, when loading the material into the aging furnace, the material rack must be arranged to facilitate smooth air circulation, so as to ensure uniform and rapid heating.

[0050] In this embodiment, after aging treatment, the sample is taken for analysis and performance testing.

[0051] The beneficial effects of the present invention are verified through the following embodiments:

[0052] Example:

[0053] A method for manufacturing aluminum alloy forgings for semi-circular structural beams for aerospace applications, comprising the following steps:

[0054] I. Casting of Aluminum Alloy Ingots: The aluminum alloy ingots are cylindrical ingots with dimensions of Φ405×900mm; the mass percentage of elements in the aluminum alloy ingots is as follows: Si 0.10%, Fe 0.8%, Cu 2.2%, Mn 0.10%, Mg 1.5%, Cr 0.10%, Ni 1.0%, Zn 0.10%, Ti 0.05%, with individual impurities ≤0.05%, total impurities ≤0.15%, and the remainder being Al;

[0055] 2. After the above-mentioned aluminum alloy ingots are loaded into the furnace, they are heated to 350°C and then extruded into bars. After the extruded bars are cut off at the head and tail and then cut into low magnification bars, bars with a length of 1650mm are cut into blanks.

[0056] 3. The above-mentioned blank is heated to 440℃, the initial forging temperature of the blank is 430℃, and then it is bent on a 5000-ton vertical free forging hydraulic press. The die temperature is 400℃. The blank is bent into a blank that is the same as the template according to the bending process.

[0057] IV. Pre-pressing of blanks: The blanks obtained in step 3 are heated to 430°C, the first forging temperature is 440°C, the first final forging temperature is 410°C, the last forging temperature is 440°C, the last final forging temperature is 410°C, and the die temperature is 380°C to obtain pre-pressed forgings.

[0058] 5. The pre-pressed forgings obtained in step 4 are subjected to etching and cleaning for repair, and then subjected to one die forging. The heating temperature of the pre-pressed forgings is 440℃, the first forging temperature is 430℃, the first forging temperature is 420℃, the last forging temperature is 410℃, the last forging temperature is 400℃, and the die temperature is 360℃ to obtain the die forgings.

[0059] VI. The forgings obtained in step 5 are subjected to etching and cleaning for repair, then subjected to two die forging processes, followed by etching and cleaning for repair, pre-fire inspection, quenching treatment and aging treatment in sequence, thus completing the manufacturing of aluminum alloy forgings for semi-circular structural beams for aviation.

[0060] In step two of this embodiment, the aluminum alloy ingots must be cleaned of dust, aluminum shavings, and burrs before being loaded into the furnace; when loading into the furnace, the aluminum alloy ingots must be placed neatly and stably on the material tray.

[0061] In step two of this embodiment, the extrusion process involves using a 5000-ton horizontal hydraulic press with a Ф420mm extrusion cylinder to extrude bars with a diameter of Φ95mm. The cylinder temperature is 350℃, the extrusion speed is ≤0.6mm / S, and the extrusion is performed using a reverse extrusion method. The extrusion residue is required to be less than 25mm.

[0062] The etching and repair process described in steps five and six of this embodiment is the same: the part to be cleaned is placed upright in a stainless steel etching basket, etched and degreased in an alkaline bath of 15wt% NaOH at 60℃ for 20 minutes, then washed with alkaline solution in a cold water bath at room temperature, then neutralized and washed with acid in an acid bath of 30wt% HNO3 at room temperature for 5 minutes, then washed with acid in a cold water bath at room temperature, and finally rinsed in a hot water bath at 60℃. After being taken out, it is placed on a repair area with aluminum pads on the ground for repair, and defects in the forging are checked and removed.

[0063] In step six of this embodiment, the two-stage die forging process is as follows: Before die forging, the impurities in the die cavity are removed with compressed air, the upper and lower dies are installed and lubricated with sand oil, and the forging temperature of the first and last pieces of each horizontal tray is 430°C when the die forgings are taken out of the furnace. The die forging is carried out in a 5000-ton vertical free forging hydraulic press. The die forgings are forged twice. During the final pressing, the lubrication and pressure are applied twice. Then the car is lifted to release the air and then the pressure is applied again. The first piece is inspected and the mark is printed in the specified position. Then the burrs are removed. The residual amount of burrs after cutting is equal to 8mm. Undercut is not allowed.

[0064] The two lubrication processes described in this embodiment use a mixture of sand oil and graphite as lubricating oil; the mass ratio of the sand oil to graphite is 7:3.

[0065] The quenching process described in step six of this embodiment is as follows: the forgings and test materials that have completed the pre-quenching inspection are placed flat in the quenching basket and quenched at 530°C. The holding time is 150 minutes based on air holding. The temperature of the water used for quenching is 50°C. The quenching transfer time is less than or equal to 15 seconds, and the quenching basket is raised and lowered in the water 8 times. After staying in the water for 15 minutes, it is lifted out of the water. When marking the quenching furnace number, it must be marked to the specified position.

[0066] The sample material described in this embodiment is obtained by randomly selecting one die forging from the same batch that has completed pre-fire inspection, cutting and sampling it.

[0067] The aging treatment described in step six of this embodiment is as follows: aging treatment is carried out at 195°C, and the heat preservation time is 12 hours for metal, with a total heating time of 16 hours.

[0068] In this embodiment, aluminum alloy die forgings for semi-circular structural beams for aviation use were sampled and analyzed, and their performance was tested, using samples from the same melting batch, the same alloy grade, and the same forging conditions.

[0069] Brinell hardness: Sample height 24.99 mm, indentation diameter 3.55 mm, hardness value 147.

[0070] Metallographic test: conforms to GB / T 3246.2-2012 inspection standard.

[0071] Tensile test: GB / T 228.1-2010 is used as the test standard, which specifies a non-proportional elongation force of 6929.75 N, a specified non-proportional elongation stress of 352.22 MPa, a maximum force of 8499.28 N, a tensile strength of 432.00 MPa, an absolute elongation after fracture of 2.66%, and a relative elongation after fracture of 10.64%.

[0072] The aluminum alloy forging for a semi-circular structural beam manufactured in this embodiment meets the standard requirements in terms of dimensions, and improves the overall performance of the semi-circular forging. It also improves the stress deformation characteristics during the machining and use process, reduces defects in low-magnification microstructure, improves the load-bearing capacity of the forging, and extends the service life of the aluminum alloy forging for the semi-circular structural beam, thus meeting the requirements for aluminum alloy forgings for aerospace applications.

Claims

1. A method for manufacturing aluminum alloy forgings for semi-circular structural beams for aviation applications, characterized in that... It proceeds in the following steps: I. Casting of Aluminum Alloy Ingots: The aluminum alloy ingots are cylindrical ingots with dimensions of Φ405×900mm; the mass percentage of elements in the aluminum alloy ingots is as follows: Si 0.10%, Fe 0.8%, Cu 2.2%, Mn 0.10%, Mg 1.5%, Cr 0.10%, Ni 1.0%, Zn 0.10%, Ti 0.05%, with individual impurities ≤0.05%, total impurities ≤0.15%, and the remainder being Al; 2. After the above-mentioned aluminum alloy ingots are loaded into the furnace, they are heated to 320℃~350℃, and then extruded into bars. After the extruded bars are cut off at the head and tail and then cut into bars with a length of 1650mm as blanks.

3. The above-mentioned blank is heated to 420-450℃, the initial forging temperature of the blank is 430℃, and then it is bent on a 5000-ton vertical free forging hydraulic press. The die temperature is 350℃-400℃. The blank is bent into a blank that is the same as the template according to the bending process. IV. Pre-pressing of blanks: The blanks obtained in step three are heated to 420℃~450℃, the first forging temperature is 430℃~440℃, the first final forging temperature is 400℃~430℃, the last forging temperature is 430℃~450℃, the last final forging temperature is 400℃~430℃, and the die temperature is 360℃~380℃ to obtain pre-pressed forgings; 5. The pre-pressed forgings obtained in step 4 are subjected to etching and cleaning for repair, and then subjected to one die forging. The heating temperature of the pre-pressed forgings is 420℃~450℃, the initial forging temperature of the first piece is 420℃~440℃, the final forging temperature of the first piece is 400℃~430℃, the initial forging temperature of the last piece is 410℃~430℃, the final forging temperature of the last piece is 400℃~420℃, and the die temperature is 360℃~380℃ to obtain the die forgings. VI. The forgings obtained in step 5 are subjected to etching and cleaning for repair, then subjected to two die forgings, and then subjected to etching and cleaning for repair, pre-fire inspection, quenching treatment and aging treatment in sequence to complete the manufacturing of aluminum alloy forgings for semi-circular structural beams for aviation. The extrusion described in step two involves using a 5000-ton horizontal hydraulic press with a Ф420mm extrusion cylinder to extrude bars with a diameter of Φ95mm. The extrusion cylinder temperature is 320℃~380℃, the extrusion speed is ≤0.6mm / S, and the extrusion is carried out using a reverse extrusion method. The extrusion residue is required to be less than 25mm. The etching and repair process described in steps five and six is ​​the same: place the part to be cleaned upright in a stainless steel etching basket, etch and degrease it in an alkaline bath of 15% to 20 wt% NaOH at 50℃ to 70℃ for 10 to 20 minutes, then wash it off the alkaline solution in a cold water bath at room temperature, then neutralize and wash it in an acid bath of 30% to 40 wt% HNO3 at room temperature for 5 to 8 minutes, then wash it off the acid solution in a cold water bath at room temperature, and finally rinse it in a hot water bath at 50 to 70℃. After taking it out, place it on a repair area with aluminum pads on the ground for repair, check and remove any defects in the forging. The quenching process described in step six: The forgings and test pieces that have completed the pre-quenching inspection are placed flat in the quenching basket and quenched at 529℃~535℃. The holding time is 150~180min based on air holding. The temperature of the water used for quenching is 40℃~60℃. The quenching transfer time is less than or equal to 15s, and the quenching basket is raised and lowered in the water more than 5 times. After staying in the water for 15min, it is lifted out of the water. When marking the quenching furnace number, it must be marked to the specified position. The test material is obtained by randomly selecting one die forging from the same batch that has completed the pre-fire inspection, cutting and sampling it. The aging treatment described in step six involves aging at 191℃ to 198℃, with a holding time of 12 hours for the metal and a total heating time of 12 to 18 hours.