Forming process and forming tool for deep-cylinder thin-wall part of aero-engine

Abstract

The invention discloses an aero-engine deep-cylinder thin-wall part forming process and a forming tool, and belongs to the technical field of high-temperature alloy annular part forging. The aero-engine deep-cylinder thin-wall part forming process comprises the following steps that 1, a blank is placed in a heating furnace to be heated to the initial forging temperature of the material; 2, upsetting, square drawing-out, rounding, upsetting, punching and chambering are carried out on the blank on a forging hammer; 3, performing rough turning on the blank; and 4, the blank is remelted and heated. And 5, the remelted and heated blank is subjected to chambering on a forging hammer, and the GH4169 bearing cylinder forged piece is obtained. And 6, the forge piece is subjected to solid solution heat treatment. And 7, sampling the forge piece subjected to solid solution, and carrying out physical and chemical test. And 8, roughly turning the forged piece qualified in the physical and chemical test. And 9, carrying out ultrasonic inspection on the forged piece subjected to rough turning. Aiming at the GH4169 deep-cylinder thin-wall part, the upper limit of the forming weight of the GH4169 deep-cylinder thin-wall part can be improved by optimizing the forming process, meanwhile, the forging deformation is uniform through the steps of upsetting, square drawing-out, rolling and upsetting, and the uniformity of the grain structure of the forging is effectively ensured.

Description

Technical Field

[0001] The present application relates to the technical field of forging high-temperature alloy ring parts, and in particular, to a forming process for a deep-barrel thin-walled part of an aircraft engine. In addition, the present application also relates to a forming tooling applied to the forming process for the deep-barrel thin-walled part of an aircraft engine. Background Art

[0002] The information provided in this section is for the purpose of generally presenting the background of the present application. To the extent described in this section, the work of the presently named inventors and aspects of the description that may not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present application.

[0003] GH4169 alloy is widely used in aviation and aerospace fields due to its excellent high temperature performance. The bearing cylinder of an aircraft engine is made of GH4169 alloy. It is a deep thin-walled part with thin wall thickness and high height. The total weight of a single forging is large. Due to the large height of the forging and the high deformation resistance of GH4169, it is difficult to form the inner hole. It is difficult to ensure the inner hole size during punching and folding defects are likely to occur. It is also easy to deform unevenly and produce mixed crystals. Please refer to the attached manual for details. Figure 1 , which is a schematic diagram of the high-magnification mixed crystal structure of the load-bearing cylinder formed by the existing process.

[0004] In order to improve the upper limit of GH4196 alloy deep barrel thin wall forging equipment and ensure uniform grain structure of forgings, we provide an optimized forming process and cooperate with improved forming tooling to effectively improve the final product quality.

[0005] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0006] In view of at least one of the above technical problems, the present application provides a forming process for deep-barrel thin-walled parts of aircraft engines. For GH4169 deep-barrel thin-walled parts, the upper limit of the forming weight of GH4169 deep-barrel thin-walled parts can be increased by optimizing the forming process. At the same time, in view of the uneven deformation characteristics of the upsetting process, upsetting, square drawing, rounding and upsetting steps are performed to make the deformation of the forgings uniform, effectively ensuring the uniformity of the grain structure of the forgings.

[0007] At the same time, the present application also provides a molding tool used in the above-mentioned aircraft engine deep barrel thin-walled parts molding process.

[0008] According to one aspect of the present application, a forming process for a deep barrel thin-walled part of an aircraft engine is provided, comprising the following steps:

[0009] S100, according to the size requirements of the deep tube thin-walled parts to be processed and formed, select the diameter and length of the GH4169 bar blank;

[0010] S200, placing the blank in a heating furnace for preheating at a temperature of 800±10°C, and keeping the temperature for 168 to 212 minutes;

[0011] S300, heating the preheated and heat-insulated blank to (980-1030)±20°C, and then heat-insulating for 101-228 minutes;

[0012] S400, the heated blank is subjected to upsetting, square drawing, rounding, upsetting and punching in sequence on a free forging hammer device;

[0013] S500, rough turning the inner hole of the blank to a preset forming size;

[0014] S600, the rough-turned blank is heated in the furnace, first preheated at 800±10℃, and kept warm for 64-104min, then heated at 960-1050℃, and kept warm for 39-95min;

[0015] S700, the blank that has been reheated is expanded on a free forging hammer to obtain a GH4169 bearing cylinder forging;

[0016] S800, performing solution heat treatment on the forging after hole expansion;

[0017] S900. Take samples of forgings that have completed solution heat treatment for physical and chemical tests. Forgings that pass the physical and chemical tests are then rough turned to specified dimensions. After rough turning, the forgings are ultrasonically inspected to see if they are qualified.

[0018] In some embodiments of the present application, in step S400, the striking energy or tonnage of the free forging equipment is selected according to the deformation work required for forging forming, and the calculation formula of the upsetting deformation work A required for billet upsetting is as follows:

[0019]

[0020] Where: S is the true flow stress at the corresponding deformation temperature and speed, in MPa; D1, H1 are the diameter and height of the billet, in mm; D2, H2 are the diameter and height of the billet after upsetting, in mm; V is the volume of the forging, in mm 3 .

[0021] In some embodiments of the present application, in step S400, during upsetting, the calculation formula of the striking energy E of the free forging equipment is as follows:

[0022]

[0023] Where: E is the striking energy required by the free forging equipment, unit is J; η is the striking efficiency, usually η = 0.7 ~ 0.9.

[0024] In some embodiments of the present application, in step S400, during upsetting, the calculation formula for the forging hammer tonnage G of the free forging equipment is as follows:

[0025]

[0026] Where: g is the acceleration due to gravity, g = 9.8 / s 2 ; v is the striking speed of the forging hammer, usually v=5~6m / s.

[0027] In some embodiments of the present application, in step S400, the blank is transferred from the heating furnace to the free forging equipment for forging, and the transfer time shall not exceed 15S.

[0028] In some embodiments of the present application, in step S400, attention should be paid to the temperature of the forging during the forging process on the free forging hammer equipment, and the temperature of the forging should be detected with an optical pyrometer or an infrared thermometer, and the final forging temperature of the forging should not be lower than 900°C.

[0029] In some embodiments of the present application, in step S400, the blank should be continuously rotated around the blank axis during the upsetting process, and the blank should be turned upside down when the upsetting process is halfway through.

[0030] In some embodiments of the present application, in step S800, the forging enters the heating furnace when the temperature is ≤780°C, the heating temperature is (770°C~790°C)±10°C, and it is kept warm for 2h~4h, and the temperature is raised with the furnace to (960°C~980°C)±10°C, and it is kept warm for 2h~2.5h, and then the forging is oil-cooled.

[0031] According to another aspect of the present application, a deep-barrel thin-walled parts forming tool for aircraft engines is also provided, which is applied to the above-mentioned deep-barrel thin-walled parts forming process for aircraft engines. The deep-barrel thin-walled parts forming tool for aircraft engines includes a forward punch and a recoil punch. The forward punch is used to connect to a punching device to punch holes in the deep-barrel thin-walled parts blank through the forward punch, and the recoil punch is used to connect to a punching device to punch out the negative film of the punched deep-barrel thin-walled parts blank through the recoil punch.

[0032] In some embodiments of the present application, both the forward punch and the recoil punch are truncated cone structures that are wide at the top and narrow at the bottom, and the bottom and top surfaces of the forward punch and the recoil punch are chamfered at the same angle. The minimum diameter of the recoil punch is smaller than the diameter of the forward punch, and the height of the recoil punch is higher than that of the forward punch.

[0033] This application has the following beneficial effects:

[0034] The forming process of deep-barrel thin-walled parts for aircraft engines in this application is aimed at GH4169 deep-barrel thin-walled parts. By optimizing the forming process steps and process parameters, the upper limit of the forming weight of GH4169 deep-barrel thin-walled parts can be increased by more than 30%. At the same time, in view of the uneven deformation characteristics of the upsetting process, upsetting, square drawing, rounding, and upsetting steps are performed to make the forgings deform evenly, effectively ensuring the uniformity of the grain structure of the forgings. The purpose of square drawing and rounding is to make the forgings bear forces in all directions. In addition, this application also provides a method for selecting and calculating the striking energy or tonnage of free forging equipment, which can further improve the forging accuracy and effectively improve the production quality of the product. This application overcomes the difficulties in punching and forming forgings in existing processes, and the problem of easily generating mixed crystals, and has significant economic benefits.

[0035] The aircraft engine deep barrel thin-walled parts forming tooling of the present application also has the above beneficial effects. At the same time, the forming tooling of the present application can also achieve the effect of easier punching of the punching plate. The tooling structure is simple and efficient, and it is very convenient to use, which is conducive to further improving the processing efficiency.

[0036] Of course, any product implementing this application does not necessarily need to achieve all the advantages described above at the same time. In addition to the purposes, features and advantages described above, this application also has other purposes, features and advantages. The following will further describe this application in detail with reference to the figures. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0038] Figure 1 It is a schematic diagram of the high-magnification mixed crystal structure of the bearing cylinder formed by the existing process;

[0039] Figure 2 It is a schematic diagram of the process flow of a preferred embodiment of the present application;

[0040] Figure 3 It is a structural schematic diagram of a positive punch of a preferred embodiment of the present application;

[0041] Figure 4 It is a structural schematic diagram of a recoil punch of a preferred embodiment of the present application;

[0042] Figure 5 It is a force diagram of a deep tube thin-walled member of a preferred embodiment of the present application;

[0043] Figure 6 This is a 100X organization diagram of the physical and chemical test microstructure of the forging of Example 1 of the present application;

[0044] Figure 7 This is a 500X organization diagram of the physical and chemical test microstructure of the forging of Example 1 of the present application;

[0045] Figure 8 This is a 100X organization diagram of the physical and chemical test microstructure of the forging of Example 2 of the present application;

[0046] Fig. 9 This is a 500X organization diagram of the physical and chemical test microstructure of the forging of Example 2 of the present application;

[0047] Fig.10 This is a 100X organization diagram of the physical and chemical test microstructure of the forging of Example 3 of the present application;

[0048] Fig.11 This is a 500X microstructure diagram of the physical and chemical test microstructure of the forging of Example 3 of the present application;

[0049] Legend: 1. Forward punch; 2. Recoil punch. DETAILED DESCRIPTION

[0050] The embodiments of the present application are described in detail below in conjunction with the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0051] Figure 1 It is a schematic diagram of the high-magnification mixed crystal structure of the bearing cylinder formed by the existing process; Figure 2 It is a schematic diagram of the process flow of a preferred embodiment of the present application; Figure 3 It is a structural schematic diagram of a positive punch of a preferred embodiment of the present application;

[0052] Figure 4 It is a structural schematic diagram of a recoil punch of a preferred embodiment of the present application; Figure 5 It is a force diagram of a deep tube thin-walled member of a preferred embodiment of the present application; Figure 6 This is a 100X organization diagram of the physical and chemical test microstructure of the forging of Example 1 of the present application; Figure 7 This is a 500X organization diagram of the physical and chemical test microstructure of the forging of Example 1 of the present application; Figure 8 This is a 100X organization diagram of the physical and chemical test microstructure of the forging of Example 2 of the present application; Fig. 9 This is a 500X organization diagram of the physical and chemical test microstructure of the forging of Example 2 of the present application; Fig.10 This is a 100X organization diagram of the physical and chemical test microstructure of the forging of Example 3 of the present application; Fig.11 This is a 500X microstructure diagram of the physical and chemical test microstructure of the forging of Example 3 of the present application.

[0053] A forming process for a deep-barrel thin-walled part of an aircraft engine comprises the following steps:

[0054] S100, according to the size requirements of the deep tube thin-walled parts to be processed and formed, select the diameter and length of the GH4169 bar blank;

[0055] S200, placing the blank in a heating furnace for preheating at a temperature of 800±10°C, and keeping the temperature for 168 to 212 minutes;

[0056] S300, heating the preheated and heat-insulated blank to (980-1030)±20°C, and then heat-insulating for 101-228 minutes;

[0057] S400, the heated blank is subjected to upsetting, square drawing, rounding, upsetting and punching in sequence on a free forging hammer device;

[0058] S500, rough turning the inner hole of the blank to a preset forming size;

[0059] S600, the rough-turned blank is heated in the furnace, first preheated at 800±10℃, and kept warm for 64-104min, then heated at 960-1050℃, and kept warm for 39-95min;

[0060] S700, the blank that has been reheated is expanded on a free forging hammer to obtain a GH4169 bearing cylinder forging;

[0061] S800, performing solution heat treatment on the forging after hole expansion;

[0062] S900. Take samples of forgings that have completed solution heat treatment for physical and chemical tests. Forgings that pass the physical and chemical tests are then rough turned to specified dimensions. After rough turning, the forgings are ultrasonically inspected to see if they are qualified.

[0063] The forming process of deep-barrel thin-walled parts for aircraft engines in this application is aimed at GH4169 deep-barrel thin-walled parts. By optimizing the forming process steps and process parameters, the upper limit of the forming weight of GH4169 deep-barrel thin-walled parts can be increased by more than 30%. At the same time, in view of the uneven deformation characteristics of the upsetting process, upsetting, square drawing, rounding, and upsetting steps are performed to make the forgings deform evenly, effectively ensuring the uniformity of the grain structure of the forgings. The purpose of square drawing and rounding is to make the forgings bear forces in all directions. In addition, this application also provides a method for selecting and calculating the striking energy or tonnage of free forging equipment, which can further improve the forging accuracy and effectively improve the production quality of the product. This application overcomes the difficulties in punching and forming forgings in existing processes, and the problem of easily generating mixed crystals, and has significant economic benefits.

[0064] Please note that, please refer to Figure 5When forgings are upset, they can be divided into three zones according to the degree of deformation: zone I is a difficult deformation zone with the smallest deformation degree, zone II is a large deformation zone with the largest deformation degree, and zone III is a small deformation zone with a medium deformation degree. Due to the uneven deformation of the forgings, the grains in zone II with the largest deformation degree are small new grains, while zones I and IIII with smaller deformation degrees may be in the critical deformation zone, with different degrees of grain crushing, resulting in coarse grains in some parts. During upsetting, the forgings are mainly subjected to axial compressive stress, while the four-way stretching and rolling cause the forgings to be subjected to compressive stress in all directions, so that all areas of the forgings are deformed in zone II, thereby making the forgings deform evenly.

[0065] Preferably, in step S400, the striking energy or tonnage of the free forging equipment is selected according to the deformation work required for forging forming, and the calculation formula of the upsetting deformation work A required for billet upsetting is as follows:

[0066]

[0067] Where: S is the true flow stress at the corresponding deformation temperature and speed, in MPa; D1, H1 are the diameter and height of the billet, in mm; D2, H2 are the diameter and height of the billet after upsetting, in mm; V is the volume of the forging, in mm 3 .

[0068] It should be noted that the tonnage of equipment required for free forging is mainly related to factors such as deformation area, forging material, and deformation temperature. The contact area between the forging and the tool during upsetting is much larger than that of other deformation steps, and many forging processes are related to upsetting. Therefore, the size of the upsetting force is often used to select free forging equipment. On the forging hammer, since the striking force is uncertain, the striking energy or tonnage of the free forging equipment should be selected based on the deformation work required for forging formation. The present application can know the work required for forging through formula (1), and thus select the corresponding forging equipment.

[0069] Preferably, in step S400, during upsetting, the calculation formula of the striking energy E of the free forging equipment is as follows:

[0070]

[0071] Where: E is the striking energy required by the free forging equipment, unit is J; η is the striking efficiency, usually η = 0.7 ~ 0.9.

[0072] It can be understood that by combining formula (2) with formula (1), the impact energy E of the free forging equipment can be calculated, which facilitates the precise control of the free forging equipment, improves the processing accuracy, and ensures the quality of the product.

[0073] Preferably, in step S400, during upsetting, the calculation formula for the forging hammer tonnage G of the free forging equipment is as follows:

[0074]

[0075] Where: g is the acceleration due to gravity, g = 9.8 / s 2 ; v is the striking speed of the forging hammer, usually v=5~6m / s.

[0076] It can be understood that by combining formula (3) with formula (1), the forging hammer tonnage of the free forging equipment can be calculated, and the key operating parameters of the free forging equipment can be obtained to ensure the high quality forging of the product.

[0077] It should be noted that, through formula (3) and formula (1), the relationship between the forging hammer tonnage G and the forging weight m of the free forging equipment under different working conditions can also be derived. For example, when the forging hammer striking speed is v = 5.5 m / s and the striking efficiency is η = 0.8, then

[0078]

[0079] It can be deduced that the relationship between the forging hammer tonnage G and the forging weight m is as follows:

[0080]

[0081] Where: ρ is the density of the material corresponding to the forging.

[0082] Therefore, the larger the forging weight m, the larger the forging hammer tonnage G required for upsetting the forging. Since the diameter D2 and height H2 of the billet after upsetting remain unchanged, the flow stress σ S It is a constant value at a constant deformation temperature and speed. When the tonnage G of the forging hammer remains unchanged, the weight m of the forging increases with the decrease of H1 and increases with the increase of D1. Therefore, if you want to increase the weight of the forging under the condition of fixed forging equipment, you can increase the billet diameter D1 and reduce the billet height, that is, reduce the billet height-to-diameter ratio.

[0083] The aspect ratio of GH4169 forgings is generally 1.0 to 2.0. In order to increase the upper limit of forging forming weight by 30%, the present application further optimizes the aspect ratio of GH4169 forgings to 1.0 to 1.5.

[0084] For example, the size of the blank is Φ160mm*288mm, and the size of the forged part after upsetting is Φ234mm*135mm. Substituting into formula (5) we get:

[0085]

[0086] After optimizing the billet height-to-diameter ratio, the billet size is Φ180mm*228mm. The forging size after upsetting is Φ234mm*135mm. Substituting into formula (5), we get:

[0087]

[0088] m2 is increased by 32.8% compared with m1. It can be seen that under the condition of unchanged forging quality, the upper limit of the forming weight of GH4169 deep tube thin-walled parts can be increased by more than 30% by optimizing the height-to-diameter ratio (height-to-diameter ratio is 1.0-1.5).

[0089] Preferably, in step S400, the blank is transferred from the heating furnace to the free forging equipment for forging, and the transfer time shall not exceed 15 seconds.

[0090] It is understandable that in order to minimize the heat loss of the blank, the transfer time between the blank from the heating furnace and the free forging equipment should be as short as possible to ensure that the blank is forged within a suitable temperature range. This application stipulates that the transfer time is less than 15s, which can ensure that the heat loss of the blank is within an acceptable range, which is convenient for workers to operate.

[0091] Preferably, in step S400, during the forging process on the free forging hammer equipment, attention should be paid to the temperature of the forging, and the temperature of the forging should be detected by an optical pyrometer or an infrared thermometer, and the final forging temperature of the forging should not be lower than 900°C.

[0092] It is understandable that in order to ensure the forging effect and reduce the impact of billet temperature loss or temperature instability on the performance of the final product, this application stipulates that an optical pyrometer or infrared thermometer is used to detect the forging temperature during the forging process to ensure that the final forging temperature of the forging is not lower than 900°C to ensure the final forging quality.

[0093] Preferably, in step S400, the blank should be continuously rotated around the blank axis during the upsetting process, and the blank should be turned upside down when the upsetting process is halfway completed.

[0094] It is understandable that the blank should be rotated around the blank axis during the upsetting process, and turning it upside down once during the upsetting process can improve the uniformity of product processing and help improve the consistency of product performance. The reason why the blank is turned upside down once again in the middle of the upsetting process is that it takes into account the deformation characteristics of GH4169 and prevents the lower head from absorbing heat and cooling too quickly, which will increase the deformation resistance.

[0095] Preferably, in step S800, the forging enters the heating furnace when the temperature is ≤780°C, is heated to (770°C-790°C)±10°C, is kept warm for 2h-4h, is heated with the furnace to (960°C-980°C)±10°C, is kept warm for 2h-2.5h, and then the forging is oil-cooled.

[0096] It is understandable that extending the holding time of each heating stage in step S800 to at least 2 hours can ensure the stability of the forging performance and reduce the impact of rapid temperature changes on its performance.

[0097] Embodiment 1

[0098] 1. The bar size is Φ160mm*288mm, the weight is m=47.8kg, the height-to-diameter ratio is 1.8, and the size of the forging after upsetting is Φ234mm*135mm. Substituting these data into formula (1) yields: A=6283.5σ S , thus the work required for forging upsetting can be obtained. S Substituting into equation (4) we get: G = 510.9σ S , thereby determining the corresponding forging equipment tonnage.

[0099] The bar size is Φ180mm*228mm, the weight is m=47.8kg, the height-to-diameter ratio is 1.27, and the size of the forging after upsetting is Φ234mm*135mm. Substituting these data into formula (1) yields: A=4731σ S , and thus determine the corresponding forging equipment tonnage. S Substituting into equation (4) we can get: G = 385σ S , thus obtaining the work required for forging and upsetting.

[0100] σ S Because the flow stress is a constant under the same conditions, the upsetting deformation work of the forging is reduced by 32.8% after the upsetting ratio of the forging is reduced from 1.8 to 1.27.

[0101] 2. Place the blank in a heating furnace for heating.

[0102] The bar material is heated in the furnace at ≤800℃. Preheating: heating temperature 800±10℃, holding time 188~232min, then heating to: (980~1030)±20℃, holding time 113~258min.

[0103] 3. The heated blank is subjected to upsetting, square drawing, rounding, upsetting and punching on the free forging hammer.

[0104] Among them, upsetting: the blank is upset to a forming height of 135±3mm. During the upsetting process, the blank should be continuously rotated around the blank axis. When the upsetting reaches 182±5mm, it should be turned upside down once, that is, it should be turned upside down once halfway through the upsetting process to prevent the lower head from absorbing heat and cooling too quickly, which will increase the deformation resistance;

[0105] Punching: Use a Φ90 punch with a taper of 3° to punch first with a forward punch (L=100) and then a back punch (L=130).

[0106] 4. Rough turn the inner hole of the blank to the specified size

[0107] Rough turn the inner hole size to Φ120±1mm.

[0108] 5. The blank is returned to the furnace for heating.

[0109] Billet ≤ 800℃ enters the furnace for heating, preheating: heating temperature 800±10℃, holding time 64~104min, then heating to: (980~1030)±20℃, holding time 39~95min

[0110] 6. Expand the hole of the reheated billet on the free forging hammer.

[0111] Use a Φ110 core rod to expand the hole. Pay attention to correcting the deviation and rotating evenly during the expansion process. Pay attention to the minimum wall thickness of the forging when expanding the hole. Air cool after expansion.

[0112] 6. Perform solution heat treatment on the forgings.

[0113] Forgings enter the furnace at ≤780℃, (770℃~790℃)±10℃, keep warm for 2h~4h, rise to (960℃~980℃±10℃) with the furnace, keep warm for 2h~2.5h, and oil cool the forgings

[0114] 8. Take samples of forgings after solution treatment for physical and chemical tests

[0115] 9. Rough turning shall be carried out on forgings that have passed the physical and chemical tests.

[0116] 10. Perform ultrasonic inspection on forgings after rough turning.

[0117] At this point, the preparation of the GH4169 load-bearing cylinder is completed.

[0118] The high-magnification organization diagram of the forgings subjected to the traditional forming process is shown in Figure 1 The grain size of the forging is uneven, and there are obvious mixed crystals.

[0119] Forging, square drawing, rounding, upsetting, punching, rough turning, hole expansion process steps of forging physical and chemical testing high-magnification organization diagram see Figure 6 and Figure 7 , the forging has uniform grain structure.

[0120] Embodiment 2

[0121] 1. The bar size is Φ160mm*228mm, the height-to-diameter ratio is 1.43, the weight is m=37.8kg, and the size of the forging after upsetting is Φ204mm*140mm. Substituting these data into formula ①, we get: A=2620σ S , thus the work required for forging upsetting can be obtained. S Substituting into formula ④, we can get: G = 213σ S , thereby determining the corresponding forging equipment tonnage.

[0122] 2. Place the blank in a heating furnace for heating.

[0123] The bar material is heated in the furnace at ≤800℃. Preheating: heating temperature 800±10℃, holding time 168~212min, then heating to: (980~1030)±20℃, holding time 101~228min.

[0124] 3. The heated blank is subjected to upsetting, square drawing, rounding, upsetting and punching on the free forging hammer.

[0125] Upsetting: Upset the blank to 140±3mm. During the upsetting process, the blank should be rotated around the blank axis continuously. When the upsetting reaches 180±5, it should be turned upside down once;

[0126] Punching: Use a Φ90 punch with a taper of 3° (special punch), first punch forward (L=100) and then back punch (L=130).

[0127] 4. Rough turn the inner hole of the blank to the specified size

[0128] The inner hole size is Φ120±1mm.

[0129] 5. The blank is returned to the furnace for heating.

[0130] The billet is heated in the furnace at ≤800℃. Preheating: heating temperature 800±10℃, holding time 51~105min, then heating to: (980~1030)±20℃, holding time 31~87min.

[0131] 6. The reheated billet is expanded on the free forging hammer.

[0132] Use a Φ110 core rod to expand the hole. Pay attention to correcting the deviation and rotating evenly during the expansion process. Pay attention to the minimum wall thickness of the forging when expanding the hole. Air cool after expansion.

[0133] 7. Solution heat treatment of forgings.

[0134] Forgings enter the furnace at ≤780℃, (770℃~790℃)±10℃, keep warm for 2h~3h, then raise the temperature to (960℃~980℃)±10℃ with the furnace, keep warm for 2h~2.5h, and then oil cool the forgings.

[0135] 8. Take samples of forgings after solution treatment for physical and chemical tests.

[0136] 9. Rough turning shall be carried out on forgings that have passed the physical and chemical tests.

[0137] 10. Perform ultrasonic inspection on forgings after rough turning.

[0138] At this point, the preparation of the GH4169 load-bearing cylinder is completed.

[0139] Forging, square drawing, rounding, upsetting, punching, rough turning, hole expansion process steps of forging physical and chemical testing high-magnification organization diagram see Figure 8 and Fig. 9 , the forging has uniform grain structure.

[0140] Embodiment 3

[0141] 1. The bar size is Φ180mm*186mm, the height-to-diameter ratio is 1.03, the weight is m=39kg, and the size of the forging after upsetting is Φ211mm*135mm. Substituting these data into formula ①, we get: A=1865σ S , and thus the work required for forging upsetting can be obtained. S Substituting into formula ④, we can get: G = 152σ S , thereby determining the corresponding forging equipment tonnage.

[0142] 2. Place the blank in a heating furnace for heating.

[0143] The bar material is heated in the furnace at ≤800℃. Preheating: heating temperature 800±10℃, holding time 182~230min, then heating to: (980~1030)±20℃, holding time 110~255min.

[0144] 3. The heated blank is upset, squared, rounded, upset and punched on a free forging hammer, and punched with a special punch.

[0145] Upsetting: Upset the blank to 135±3mm. During the upsetting process, the blank should be rotated around the blank axis continuously. When upsetting to 160±5, it should be turned upside down once;

[0146] Punching: Use a Φ90 punch with a taper of 3° (special punch), first punch forward (L=100) and then back punch (L=130).

[0147] 4. Rough turn the inner hole of the blank to the specified size

[0148] The inner hole size is Φ120±1mm.

[0149] 5. Solution heat treatment of forgings.

[0150] Forgings enter the furnace at ≤780℃, (770℃~790℃)±10℃, keep warm for 3h~4h, then raise the temperature to (960℃~980℃)±10℃ with the furnace, keep warm for 2h~2.5h, and then oil cool the forgings.

[0151] 6. Take samples of forgings after solution treatment for physical and chemical tests

[0152] 7. Rough turning shall be carried out on forgings that have passed the physical and chemical tests.

[0153] 8. Perform ultrasonic inspection on forgings after rough turning.

[0154] At this point, the preparation of the GH4169 load-bearing cylinder is completed.

[0155] Forging, square drawing, rounding, upsetting, punching, rough turning, hole expansion process steps of forging physical and chemical testing high-magnification organization diagram see Fig.10 and Fig.11 , the forging has uniform grain structure.

[0156] According to another aspect of the present application, a deep-barrel thin-walled part forming tool for an aircraft engine is also provided, which is applied to the above-mentioned deep-barrel thin-walled part forming process for an aircraft engine. The deep-barrel thin-walled part forming tool for an aircraft engine comprises a forward punch 1 and a recoil punch 2. The forward punch 1 is used to connect to a punching device to punch holes in the deep-barrel thin-walled part blank through the forward punch 1, and the recoil punch 2 is used to connect to a punching device to punch out the negative film of the punched deep-barrel thin-walled part blank through the recoil punch 2.

[0157] The aircraft engine deep barrel thin-walled parts forming tooling of the present application also has the above beneficial effects. At the same time, the forming tooling of the present application can also achieve the effect of easier punching of the punching plate. The tooling structure is simple and efficient, and it is very convenient to use, which is conducive to further improving the processing efficiency.

[0158] Preferably, please refer to Figure 3 and Figure 4 As shown, both the forward punch 1 and the recoil punch 2 are truncated cone structures that are wide at the top and narrow at the bottom, and the bottom and top surfaces of the forward punch 1 and the recoil punch 2 are chamfered at the same angle, the minimum diameter of the recoil punch 2 is smaller than the diameter of the forward punch 1, and the height of the recoil punch 2 is higher than the forward punch 1.

[0159] It can be understood that the positive punch 1 and the recoil punch 2 both adopt a simple and efficient structure as a whole. By designing punches of different sizes and using them in different ways, the punching film can be punched out efficiently, which is beneficial to improving the punching processing efficiency.

[0160] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0161] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the protection of this application.

Claims

1. A forming process for deep-barrel thin-walled parts of aircraft engines, characterized in that: The following steps are involved: S100, according to the size requirements of the deep tube thin-walled parts to be processed and formed, select the diameter and length of the GH4169 bar blank; S200, placing the blank in a heating furnace for preheating at a temperature of 800±10°C, and keeping the temperature for 168 to 212 minutes; S300, heating the preheated and heat-insulated blank to (980-1030)±20°C, and then heat-insulating for 101-228 minutes; S400, the heated blank is subjected to upsetting, square drawing, rounding, upsetting and punching in sequence on a free forging hammer device; S500, rough turning the inner hole of the blank to a preset forming size; S600, the rough-turned blank is heated in the furnace, first preheated at 800±10℃, and kept warm for 64-104min, then heated at 960-1050℃, and kept warm for 39-95min; S700, the blank that has been heated after being remelted is expanded on a free forging hammer to obtain a GH4169 bearing tube forging; S800, the forging that has been expanded is subjected to solution heat treatment; S900. Take samples of forgings that have completed solution heat treatment for physical and chemical tests. Forgings that pass the physical and chemical tests are then rough turned to specified dimensions. After rough turning, the forgings are ultrasonically inspected to see if they are qualified.

2. The process for forming a deep-barrel thin-walled component of an aircraft engine according to claim 1, characterized in that: In step S400, the striking energy or tonnage of the free forging equipment is selected according to the deformation work required for forging forming, and the calculation formula of the upsetting deformation work A required for billet upsetting is as follows: Where: S is the true flow stress at the corresponding deformation temperature and speed, in MPa; D1, H1 are the diameter and height of the billet, in mm; D2, H2 are the diameter and height of the billet after upsetting, in mm; V is the volume of the forging, in mm 3 .

3. The process for forming a deep-barrel thin-walled component of an aircraft engine according to claim 2, characterized in that: In step S400, during upsetting, the calculation formula of the striking energy E of the free forging equipment is as follows: Where: E is the striking energy required by the free forging equipment, unit is J; η is the striking efficiency, usually η = 0.7 ~ 0.

9.

4. The process for forming a deep-barrel thin-walled component of an aircraft engine according to claim 2, characterized in that: In step S400, during upsetting, the calculation formula of the forging hammer tonnage G of the free forging equipment is as follows: Where: g is the acceleration due to gravity, g = 9.8 / s 2 ; v is the striking speed of the forging hammer, usually v=5~6m / s.

5. The process for forming a deep-barrel thin-walled component of an aircraft engine according to claim 1, characterized in that: In step S400, the blank is transferred from the heating furnace to the free forging equipment for forging, and the transfer time shall not exceed 15S.

6. The forming process of aero-engine deep barrel thin-walled parts according to claim 1, characterized in that: In step S400, during the forging process on the free forging hammer equipment, attention should be paid to the temperature of the forging. The temperature of the forging should be detected by an optical pyrometer or an infrared thermometer. The final forging temperature of the forging should not be lower than 900°C.

7. The process for forming a deep-barrel thin-walled component of an aircraft engine according to claim 1, characterized in that: In step S400, the blank should be continuously rotated around the blank axis during the upsetting process, and the blank should be turned upside down when the upsetting process is halfway completed.

8. The process for forming a deep-barrel thin-walled component of an aircraft engine according to claim 1, characterized in that: In step S800, when the forging is ≤780°C, it enters the heating furnace, is heated to (770°C~790°C)±10°C, and is kept warm for 2h~4h. The temperature is raised with the furnace to (960°C~980°C)±10°C, and is kept warm for 2h~2.5h. The forging is then oil-cooled.

9. A forming tool for deep-barrel thin-walled parts of aircraft engines, characterized in that: The aircraft engine deep barrel thin-walled parts forming tool is applied to the aircraft engine deep barrel thin-walled parts forming process as described in any one of claims 1 to 8. The aircraft engine deep barrel thin-walled parts forming tool comprises a forward punch (1) and a recoil punch (2). The forward punch (1) is used to connect to a punching device to punch holes in the deep barrel thin-walled parts blank through the forward punch (1), and the recoil punch (2) is used to connect to a punching device to punch out the bottom plate of the deep barrel thin-walled parts blank through the recoil punch (2).

10. The aircraft engine deep barrel thin-walled parts forming tool according to claim 9, characterized in that: The forward punch (1) and the recoil punch (2) are both truncated cone structures that are wide at the top and narrow at the bottom, and the bottom and top surfaces of the forward punch (1) and the recoil punch (2) are chamfered at the same angle, the minimum diameter of the recoil punch (2) is smaller than the diameter of the forward punch (1), and the height of the recoil punch (2) is higher than that of the forward punch (1).

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