GH5188 high-temperature alloy ring part for aero-engine and forging spinning composite hot forming method thereof

Abstract

The invention discloses a GH5188 high-temperature alloy annular piece for an aero-engine and a forging spinning composite hot forming method of the GH5188 high-temperature alloy annular piece. The forming method comprises the steps that under the condition of 1135-1165 DEG C, raw materials are subjected to forging forming to obtain a forged annular blank; the forged annular blank is heated and subjected to heat preservation to 900-950 DEG C; the forged annular blank is transferred to spinning equipment and clamped, and the total time for transferring and clamping operation does not exceed 1 min; after clamping, temperature compensation and temperature measurement monitoring are carried out, so that the temperature of the forged annular blank is not lower than 900 DEG C; and under the temperature compensation condition, at least one pass of hot spinning is conducted on the forged annular blank according to the spinning track, it is guaranteed that the spinning temperature fluctuation range is smaller than or equal to + / -20 DEG C, the spinning annular piece is obtained, and the rough machining allowance of 2-2.5 mm is reserved on the single side of the spinning annular piece. According to the method, small-allowance and low-heat-loss high-temperature forming of the GH5188 high-temperature alloy thin-wall part is achieved, the high-temperature plasticity of the material is guaranteed, the utilization rate and forming precision of the raw material are improved, and finally the high-temperature alloy ring part material and machining cost are reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of high-temperature alloy hot forming, and in particular to a GH5188 high-temperature alloy ring part for an aero-engine and a forging and spinning composite hot forming method thereof. Background Art

[0002] GH5188 high-temperature alloy is a typical solid-solution-strengthened cobalt-based high-temperature alloy. It has excellent wear resistance, high-temperature elasticity, ductility, and good oxidation resistance at high service temperatures. It has been widely used in high-temperature components such as aircraft engine combustion chamber flame tubes. Parts made from GH5188 high-temperature alloy are generally thin-walled special-shaped ring parts. Currently, such parts are mainly manufactured by ring rolling and machining. In order to envelop the processing dimensions of the special-shaped parts, the general single-side allowance is 5-7mm, and even more than 10mm. The blank allowance is large. At the same time, since forging is an integral forming process, it is difficult to accurately form complex cross-sections. This leads to high raw material costs. The large amount of machining removal leads to high processing costs and large residual stresses, which ultimately causes large deformation of the parts during finishing. Therefore, it is very necessary to develop a near-net-shape forming technology suitable for difficult-to-deform metal ring parts to reduce part processing costs.

[0003] The spinning process utilizes the plastic deformation of metal to form various rotationally symmetrical hollow workpieces from metal blanks through rotation and localized pressure. This process features high machining accuracy and efficiency, as well as minimal part machining allowances. It is a precision forming process widely used in aerospace, military equipment, automotive parts, and other fields. Currently, the vast majority of spun parts are spun from slabs, and some are spun from preforms, but these are mostly light metal parts such as cones or heads. These preforms are also mostly made from sheet metal, and are processed using stamping or drum forming. This processing method still results in the waste of raw material in the core of the slab.

[0004] Therefore, the spinning process can be used to form GH5188 high-temperature alloy ring parts. This method of using cylindrical forging raw materials combined with spinning will show great advantages in cost control. However, GH5188 high-temperature alloy is a difficult-to-deform alloy material with a high forming temperature. The current spinning process also has the problem of temperature control under high-temperature spinning conditions. Summary of the Invention

[0005] The purpose of the present invention is to solve the problems of large blank allowance, high raw material and machining costs, large residual stress, and difficult temperature control in the spinning process when the existing GH5188 high-temperature alloy ring parts are processed by the ring rolling forming process, and to provide a GH5188 high-temperature alloy ring part for aircraft engines and a forging and spinning composite hot forming method thereof.

[0006] In order to achieve the above-mentioned object of the invention, the present invention provides the following technical solutions: A forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring part for an aircraft engine comprises the following steps: Step S1: forming a forged ring blank by ring rolling and forging a GH5188 high-temperature alloy rod-shaped raw material at 1135-1165° C.; the forged ring blank is a cylindrical part with a constant wall thickness or a special-shaped part with a constant wall thickness; Step S2: hot spinning the forged ring blank. The specific method is as follows: Step S21, heating the forged ring blank and keeping the temperature at 900-950° C.; Step S22: transferring the forged ring blank that has reached the process temperature to the spinning equipment and clamping it, wherein the total time for the transfer and clamping operations does not exceed 1 minute; Step S23: After the clamping is completed, the forged ring blank is heated up and the temperature of the forged ring blank is monitored to ensure that the temperature of the forged ring blank is not lower than 900° C. Step S24: After the temperature replenishment is completed, the heat preservation is continued to ensure that the forged ring blank is hot spun at least once according to the spinning trajectory under high temperature conditions to obtain a spun ring part, and the spun ring part has a rough processing allowance of 2 to 2.5 mm.

[0007] In the above technical scheme, ring rolling forging is first used to form a forged ring blank at 1135~1165℃. The forged ring blank is a cylindrical part with equal wall thickness or a special-shaped part with equal wall thickness. The shape requirements of the forged ring blank are low and the forging process is simple. Then, the shape of the ring part is formed by a spinning process. During the hot spinning process, the forged ring blank is first preheated, and the heated forged ring blank is transferred and clamped within a specified time to reduce the temperature loss in the process. Then, the temperature of the forged ring blank is supplemented to not less than 900℃. The temperature is continuously supplemented during the spinning process, and the forged ring blank is hot spun at least once according to the spinning trajectory to obtain a spun ring part. The hot forming method of the present invention adopts a composite forming process combining forging and spinning, combining the advantages of efficient blank making by forging and high precision by spinning, and leaving a rough processing allowance of 2 to 2.5 mm for the spun ring part, that is, the inner and outer contours of the cross section of the spun ring part differ from the inner and outer contours of the cross section of the rough-processed ring part by 2 to 2.5 mm, respectively, to achieve small-allowance forming of GH5188 high-temperature alloy thin-walled parts, and at the same time, the forged ring blank is constantly heated during the spinning process, and is under high temperature conditions, resulting in less temperature loss, thereby improving the utilization rate of raw materials and forming accuracy, and ultimately achieving a reduction in the material and machining costs of the high-temperature alloy ring part, a reduction in the thickness of the processed part, and a reduction in the residual stress of the formed part, and at the same time, the present invention adopts temperature-controllable hot spinning forming during the spinning process to achieve near-isothermal forming of special-shaped thin-walled ring parts, thereby greatly reducing the production cost of the parts.

[0008] As a preferred embodiment of the present invention, the detailed method of step S1 is as follows: under the condition of 1135~1165℃, the GH5188 high-temperature alloy rod-shaped raw material is subjected to the process of blanking → upsetting → punching → horse rack reaming → ring rolling to obtain the required forging blank, and the forged ring blank is obtained by machining.

[0009] As a preferred embodiment of the present invention, the spun annular part is machined to obtain a ring part with a final outer contour. During the spinning process, the size of the spun annular part after spinning is designed based on the outer contour of the machined ring part.

[0010] As a more preferred embodiment of the present invention, the design method of the size of the spun ring is as follows: S011. Based on the inner and outer contour dimensions of the ring part after fine machining, a machining allowance of δ1 is added to one side to obtain a ring part in a rough machining state; S012. Based on the size of the rough-machined ring part, a spun ring part is obtained by adding a δ2 machining allowance to one side; S013 , performing smooth transition on the steps and / or right-angle transition positions of the spun ring component obtained in step S012 to obtain the size of the spun ring component.

[0011] As a preferred embodiment of the present invention, the sum of δ1 and δ2 does not exceed 5 mm, wherein δ1 is 2-2.5 mm, and δ2 is 2-2.5 mm.

[0012] As a preferred embodiment of the present invention, the theoretical dimensions of the forged ring blank are designed based on the dimensions of the spun ring part. The specific method is as follows: based on the dimensions of the spun ring part, the inner diameter D0, wall thickness t0, and height L0 of the forged ring blank are calculated according to the basic principle that the volume of the metal material remains unchanged before and after spinning. The inner diameter of the forged ring blank is the minimum inner diameter of the spun ring part, and the wall thickness t0 of the forged ring blank is not less than the maximum thickness of the spun ring part, which is determined based on the capacity of the spinning equipment and the forming properties of the high-temperature alloy itself. The height L0 of the forged ring blank is determined by the height of the spun ring part and the clamping length. When physical and chemical testing of the spun ring part is required, the height L0 of the forged ring blank is determined by the height of the spun ring part, the clamping length, and the length of the sample ring required for subsequent physical and chemical testing.

[0013] As a preferred embodiment of the present invention, when a spinning mold is used in the hot spinning process, in step S1, the spinning mold is preheated to a temperature not lower than 400° C. The spinning mold matches the spinning ring part and is used to fix and form the spinning ring part.

[0014] As a preferred embodiment of the present invention, the total time for the transfer and clamping operations does not exceed 1 minute. There is heat loss in the transfer and clamping process of the forged ring blank, which causes the temperature of the blank to drop. Before spinning, the temperature of the blank may not reach the starting spinning temperature condition allowed by the process, and hot spinning cannot be performed immediately. Spinning needs to be started when the spinning conditions are met after heating. This makes the process flow complicated. Therefore, the requirement for the transfer and clamping time is as short as possible, which can reduce the heat loss of the blank during the transfer and fixation process, reduce the temperature drop, reduce the waiting time for warming, and reduce energy loss. Taking into account factors such as the equipment status, the total time for the transfer and clamping operations does not exceed 1 minute.

[0015] As a preferred embodiment of the present invention, during the spinning process in step S24, the forged ring blank is continuously heated, insulated, and temperature-monitored using a semi-enclosed resistance heating device. This ensures that the temperature of the forged ring blank is no less than 900°C and that the spinning temperature fluctuates within ±20°C from the start to the end of the spinning process. During the spinning process, the forged ring blank is placed in a semi-enclosed resistance heating environment, minimizing temperature loss and improving raw material utilization and forming accuracy. The spinning temperature refers to the temperature of the spinning deformation zone of the forged ring blank during the spinning process. The spinning temperature fluctuates within a single spinning pass (i.e., from the start to the end of a single spinning pass) within a range of no more than ±20°C. In other words, the difference between the maximum and minimum values ​​of the spinning temperature within a single spinning pass is no more than 40°C. This maintains the deformation temperature of the high-temperature alloy material within a narrow fluctuation range during the forming process, thereby achieving near-isothermal spinning. This configuration can reduce the deformation resistance of difficult-to-deform metal materials, maintain a high deformation capacity during the spinning process, improve forming quality and efficiency, and meet workpiece manufacturing requirements.

[0016] As a preferred embodiment of the present invention, the method for determining the number of spinning passes is: calculating the thickness t of the forged ring blank o The spinning process is used to reduce the thickness of the spinning ring to t f The deformation rate φ, with φ max As the spinning limit deformation rate of high temperature alloy materials, if φ≤φ max The forged ring blank is made into a thickness t by hot spinning in one pass. o Spinning to t f ; If φ>φ max The maximum thinning rate of the first hot spinning pass is φ max Determine, then the thickness t1 of the ring after the first spinning pass is f By comparison, if the deformation rate of the second pass is less than or equal to φ max , you can spin it directly to t f ; If the deformation rate of the second pass is still greater than φ max , then continue according to φ max The thickness t2 after the second spinning pass is determined, and the deformation rate of the third pass is calculated according to the above principle. Similarly, the deformation pass n of the spun annular component is determined.

[0017] As a preferred embodiment of the present invention, the spindle speed is controlled at 50-60 r / min, the feed speed is 240-340 mm / min, and the spinning wheel radius R is 15-25 during the spinning process.

[0018] As a preferred embodiment of the present invention, during the spinning process, the gap c between the forged ring blank and the spinning die should be controlled according to a negative deviation, and the specific deviation value is determined according to the rebound characteristics of the GH5188 high-temperature alloy.

[0019] As a preferred embodiment of the present invention, the hot forming method further comprises step S3, wherein the spun annular part is subjected to solution heat treatment at 1163-1191° C. for 40-50 minutes, followed by oil cooling.

[0020] As a preferred embodiment of the present invention, after spinning, the GH5188 high-temperature alloy spinning ring has a tensile strength of ≥862 MPa, a yield strength of ≥379 MPa, an elongation of ≥45%, and a grain size of grade 5 or above at room temperature.

[0021] Another aspect of the present invention provides a GH5188 high-temperature alloy ring part for an aircraft engine, wherein the ring part is produced by the above-mentioned hot forming method.

[0022] Compared with the prior art, the present invention has the following beneficial effects: 1. The hot forming method provided by the present invention adopts a composite forming process combining forging and spinning, combining the advantages of efficient blank making by forging and high precision by spinning. The inner and outer contours of the cross section of the spun ring part differ from the inner and outer contours of the cross section of the rough-machined ring part by 2~2.5mm, that is, the rough machining allowance is 2~2.5mm, realizing small-residue forming of GH5188 high-temperature alloy thin-walled parts, improving the utilization rate of raw materials, and ultimately reducing the material and machining costs of high-temperature alloy ring parts, reducing the thickness of machined parts, and reducing the residual stress of formed parts. At the same time, the present invention adopts temperature-controllable hot spinning forming in the spinning process to realize near-isothermal forming of special-shaped thin-walled ring parts, greatly reducing the production cost of parts.

[0023] 2. The method of the present invention can achieve near-net hot forming of GH5188 high-temperature alloy special-shaped ring parts. The ring parts processed by this method save more than 20% of raw materials compared with the traditional forging process, and all performances can meet the use requirements. The tensile strength at room temperature is 960MPa, the yield strength reaches 425MPa, and the elongation reaches more than 36%. In the 729℃ endurance test, the endurance strength is 83MPa, the endurance time is greater than 34.8h, and the elongation reaches more than 111%. The obtained product body sampling performance is much higher than the room temperature and high temperature endurance and other performance requirements of the material in the AMS5772 standard.

[0024] 3. The forged ring blank used in the hot forming method of the present invention is a cylindrical part with uniform wall thickness or a simple special-shaped part with uniform wall thickness. There is no need to manufacture a particularly complex preform. At the same time, spinning can realize the forming of complex surfaces. The combination of the two processes gives full play to the advantages of the two processes, which can realize the precise forming of special-section ring parts and significantly reduce the cost of the product.

[0025] 4. The thermoforming method of the present invention forms a spun ring part, which is obtained by machining. Since the machining allowance is greatly reduced, while reducing machining and improving production efficiency, it is also beneficial to the size control of the part during fine machining. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 A flow chart of a forging-spinning composite hot forming method for a high-temperature alloy ring part; Figure 2 is a cross-sectional view of the annular member in Example 1; Figure 3 This is a schematic diagram of the design of the spinning part forming blank in Example 1; Figure 4 FIG1 is a diagram of the spinning process of the forged ring blank in Example 1; Figure 5 This is a cross-sectional view of the annular member in Example 2. DETAILED DESCRIPTION

[0027] In order to more clearly describe the invention purpose, technical solutions and technical effect advantages in the specific implementation cases of the present invention, the solutions in the specific embodiments will be described in detail in conjunction with the drawings of the specification of the present invention. The specific technical solutions involved in the following specific embodiments are only for the purpose of clearly and completely describing the innovative technical solutions of the present invention. They themselves are only part of the specific implementation plans that can be adopted by the present invention, not all embodiments, and should not be understood as limiting the innovative solutions of the present invention. Any solution that adopts the same inventive concept of the present invention should be included in the scope of protection of the present invention.

[0028] Secondly, the descriptions of the drawings in the specific embodiments of the present invention are only for the purpose of facilitating technical personnel's understanding of the present invention. The details in the drawings are for the purpose of clearly presenting the technical solution. It should not be assumed that all technical features in the drawings must be included in the specific implementation cases, nor should the details in the drawings be considered as additional limitations on the innovative technical solution of the present invention. The components in the various embodiments described and shown in the drawings can be combined and arranged in different configurations. These changes in combination and arrangement should be considered as part of the entire embodiment of the innovative solution of the present invention and included in the scope of protection of the present invention.

[0029] In summary, the solutions or descriptions presented in the specific embodiments and drawings of the present invention are not intended to limit the scope of protection claimed, but merely represent selected embodiments / cases to help technicians understand the relevant innovative solutions. Based on these embodiments, all other equivalent or parallel embodiments obtained by those skilled in the art without inventive effort are also within the scope of protection claimed by the present invention.

[0030] Example 1 GH5188 high temperature alloy ring shape and size Figure 2 As shown, the height is 100mm and the minimum wall thickness is 10.5mm. Before manufacturing, the spinning ring and forging ring blank are designed. The design method of the spinning ring size is: S011. Based on the inner and outer contour dimensions of the ring part after fine machining, a machining allowance of δ1 is added to one side to obtain a ring part in a rough machining state; S012. Based on the size of the rough-machined ring part, a spun ring part is obtained by adding a machining allowance of δ2 on one side. In this embodiment, δ1 is 2.5 mm, δ2 is 2.5 mm, and the sum of δ1 and δ2 is 5 mm. The theoretical diagram of the spun ring part is obtained, as shown in FIG. Figure 3 As shown; S013 , performing smooth transition on the steps and / or right-angle transition positions of the spun ring component obtained in step S012 to obtain the size of the spun ring component.

[0031] The size of the forged ring blank is designed, and the specific method is: based on the size of the spun ring part, the inner diameter D0, wall thickness t0, and height L0 of the forged ring blank are calculated according to the basic principle that the volume of the metal material remains unchanged before and after spinning. The inner diameter of the forged ring blank is the minimum inner diameter of the spun ring part, and the wall thickness t0 of the forged ring blank is not less than the maximum thickness of the spun ring part. It is determined according to the capacity of the spinning equipment and the forming properties of the high-temperature alloy itself; when the spun ring part needs to be subjected to physical and chemical tests in this embodiment, the height L0 of the forged ring blank is determined by the height of the spun ring part, the clamping length h1, and the sample ring length h2 required for subsequent physical and chemical testing. The clamping length h1 is determined according to the assembly relationship between the forged ring blank and the spinning die. In principle, from an economic point of view, this length should not be too large while meeting the clamping requirements; the sample ring length h2 is generally 10 mm. For Figure 2 The designed forged ring blank is a cylindrical part with equal wall thickness and a wall thickness of 25 mm.

[0032] Figure 1 The figure shows a flow chart of forging-spinning composite hot forming of GH5188 high-temperature alloy ring parts for aircraft engines, which includes the following steps: S1. Under the condition of 1135~1165℃, the required forging blank is obtained by blanking + upsetting + punching + horse frame expansion + ring rolling, and the forged ring blank with the above requirements is obtained by machining.

[0033] S2. Hot spinning is performed on the forged ring blank. This step mainly includes the following processes: (1) Preheating of the blank: Heat the forged ring blank in a heating furnace to a holding temperature of 900-950°C. The holding time t is determined according to the thickness of the blank; (2) Preheat the spinning mold. Start the spinning equipment to rotate the spinning mold at a low speed, and use external heating equipment to preheat the spinning mold. The preheating temperature should not be lower than 400℃.

[0034] (3) After the blank holding time reaches the process requirements, the blank is quickly transferred to the spinning equipment and the clamping is completed quickly. The total time of the transfer and clamping operation does not exceed 1 minute; (4) After the blank is loaded, the blank is immediately heated externally. While heating, the temperature of the blank is monitored to ensure that the temperature of the blank is not lower than 900°C; (5) After the blank is heated to room temperature, the spinning equipment is started and the forging blank is subjected to single or multiple passes of hot spinning according to the predetermined spinning trajectory. The blank is continuously heated during each spinning pass until the spinning is completed to obtain a spun ring. During the spinning process, the spindle speed should be controlled at 50-60 r / min, the feed speed at 240-340 mm / min, and the roller radius R15-25; the gap c between the spun blank and the spinning die should be controlled according to the negative deviation, and the specific deviation value is determined according to the rebound characteristics of the metal material.

[0035] During the spinning process, the forged ring blank is heated, insulated, and monitored using a semi-enclosed resistance heating device. The device comprises a furnace body and a temperature control system. The temperature control system comprises a furnace body temperature measurement module, a control module, and a heating module. The heating module comprises several heating rods. The furnace body is a semi-enclosed, movable, split structure, forming a furnace cavity within the body. Heating rods are arranged on the inner wall of the furnace cavity to heat the forged ring blank within the cavity. The furnace body comprises furnace body 1 and furnace body 2, a semi-cylindrical cavity structure. Furnace body 1 and furnace body 2 are arranged opposite each other and can move closer or further away from each other. The spinning equipment utilizes existing equipment, which can be integrated with the semi-enclosed resistance heating device to achieve simultaneous heating and insulation during the spinning of the forged ring blank.

[0036] S3, subjecting the spun ring to a solution heat treatment at 1163-1191° C. for 40-50 minutes, followed by oil cooling, and then machining to obtain a GH5188 high-temperature alloy ring.

[0037] Example 2 The shape and size of the GH5188 high-temperature alloy ring in this embodiment are as follows: Figure 5 As shown, the height is 210 mm and the minimum wall thickness is 15 mm. The method of Example 1 is used to design the spun ring parts and forged ring blanks. In the process of designing the size of the spun ring parts, the processing allowance δ1 is 1.2 mm, δ2 is 1.3 mm, and the sum of δ1 and δ2 is 2.5 mm. The forged ring blank obtained by design is a special-shaped part with equal wall thickness and a wall thickness of 25 mm.

[0038] The forging-spinning composite hot forming method of GH5188 high-temperature alloy ring parts includes the following steps: S1. Under the condition of 1135~1165℃, the required forging blank is obtained by blanking + upsetting + punching + horse frame expansion + ring rolling, and the forged ring blank with the above requirements is obtained by machining.

[0039] S2. Hot spinning is performed on the forged ring blank. The spinning equipment of this embodiment integrates a heat supplement system and a rotating wheel system. A workbench is installed on the main shaft of the spinning equipment body, and the main shaft can drive the workbench to rotate. The heat supplement system includes a furnace body and a temperature control system. The temperature control system includes a furnace body temperature measurement module, a control module and a heating module. The heating module includes several heating rods; the furnace body structure is a semi-enclosed movable split structure, a furnace cavity is formed in the furnace body, and heating rods are arranged on the inner wall of the furnace cavity to form an effective temperature supplement zone in the furnace cavity. The rotating wheel system includes an inner rotating wheel and an outer rotating wheel. When the rotating wheel assembly is working, the entire structure of the inner rotating wheel and part of the structure of the outer rotating wheel are in the effective temperature supplement zone of the heat supplement system, and the inner rotating wheel and the outer rotating wheel can move freely along the radial and axial directions of the blank. This step mainly includes the following processes: (1) Preheating of the blank: Heat the forged ring blank in a heating furnace to a holding temperature of 800-900°C. The holding time t is determined according to the thickness of the blank; (2) The furnace body of the heating system is heated, and the heating target temperature after the furnace body is closed is consistent with the spinning temperature required by the process; (3) After the blank is kept warm for a long time and reaches the process requirements, the blank is quickly transferred to the workbench of the spinning equipment and the clamping is completed quickly. The total time for the transfer and clamping operations does not exceed 1 minute. (4) After the blank is loaded, the blank is externally heated by the heating system. The temperature of the blank is monitored while heating to ensure that the temperature of the blank is not lower than 800°C; (5) After the billet is heated to temperature, the spinning equipment is started and the forging billet is subjected to single or multiple passes of hot spinning according to the established spinning trajectory. During each spinning pass, the billet is continuously heated by the heating system to ensure that the temperature of the forged ring billet is not lower than 800°C, and the fluctuation range of the spinning temperature of the forged ring billet from the beginning to the end of the spinning deformation does not exceed ±20°C until the spinning is completed and the spun ring part is obtained. Among them, the spindle speed during the spinning process should be controlled at 50-60r / min, the feed speed at 240-340mm / min, and the roller radius should not be greater than R15~25.

[0040] S3. The spun ring part is subjected to solution heat treatment at 1163-1191° C. for 40-50 min, followed by oil cooling, and then machined to obtain a GH5188 high-temperature alloy ring part.

[0041] Comparative Example 1 This embodiment provides a GH5188 high temperature alloy ring, the shape and size of which are as follows: Figure 2 As shown in the figure, the ring blank is formed by ring rolling + machining. Specifically, the GH5188 high-temperature alloy rod raw material is blanked, upsetting, punching, horse rack expansion, and rolling. The manufacturing temperature is controlled at 1135-1165℃, pre-rolling and final rolling are carried out. After multiple fire rolling, solid solution heat treatment is carried out at 1163-1191℃ for 40-50min and then oil cooling treatment is carried out to obtain a forged ring part. The inner and outer contours of the cross-section of the forged ring part are respectively increased by 5-6mm on the basis of the inner and outer contours of the cross-section of the rough-machined part of the ring part, and then the GH5188 high-temperature alloy ring part is obtained by machining.

[0042] Comparative Example 2 This embodiment provides a GH5188 high temperature alloy ring, the shape and size of which are as follows: Figure 5 As shown in the figure, the ring blank is formed by ring rolling + machining. Specifically, the GH5188 high-temperature alloy rod raw material is processed through blanking, upsetting, punching, horse rack expansion, and rolling. The manufacturing temperature is controlled at 1135-1165℃. Pre-rolling and final rolling are carried out. After multiple rounds of rolling, solid solution heat treatment is carried out at 1163-1191℃ for 40-50min and then oil cooling treatment is carried out to obtain a forged ring part. The outer contour of the forged ring part increases the outer contour of the ring part by 5-7mm, and then the GH5188 high-temperature alloy ring part is obtained by machining.

[0043] Test Example 1 The raw material saving calculation of the ring parts of Example 1 and Comparative Example 1, as well as Example 2 and Comparative Example 2, is shown in Table 1 below.

[0044] Table 1 Comparison of raw material savings

[0045] It can be seen from the data in the above table that the ring parts processed by the method of the present invention can save more than 20% of raw materials compared with the traditional forging process, which are 28.3% and 48.5% respectively.

[0046] Test Example 2 The spun ring parts of Example 1, Example 2, Comparative Example 1, Comparative Example 3, and Comparative Example 4 were sampled and then subjected to performance testing using ASTM E8 / E8M-24 (room temperature tensile) and ASTM E8 / 139-11 (R2018) (729°C endurance performance). The test results are the average values ​​of the three samples, as shown in Table 2 below.

[0047] Table 2 Performance test results of spun parts body sampling

[0048] From the data in the above table, it can be seen that the various properties of the ring parts processed by the method of the present invention can meet the use requirements. The tensile strength at room temperature is 960 MPa, the yield strength reaches 425 MPa, and the elongation reaches more than 36%. In the 729℃ endurance test, the endurance strength is 83 MPa, the endurance time is greater than 34.8 h, and the elongation reaches more than 111%. The obtained product body sampling performance is much higher than the room temperature and high temperature endurance and other performance requirements of the material in the AMS5772 standard, and the test results show that the grain size is level 5 or above.

[0049] For those skilled in the art, when understanding the solutions described in the specific embodiments of the present invention, they can refer to conventional technical manuals in the field. At the same time, for the places where the above-mentioned terms appear, they can make appropriate understanding or adjustments for reference, and deduce the implementation of the same or similar technical solutions without paying any creative work.

[0050] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A forging and spinning composite hot forming method for GH5188 high-temperature alloy ring parts for aircraft engines, characterized in that: The following steps are involved: Step S1: Forging a GH5188 high-temperature alloy rod-shaped raw material at 1135-1165° C. to obtain a forged ring blank; the forged ring blank is a cylindrical part with a constant wall thickness or a special-shaped part with a constant wall thickness; Step S2: hot spinning the forged ring blank. The specific method is as follows: Step S21, heating the forged ring blank and keeping the temperature at 900-950° C.; Step S22: transferring the forged ring blank that has reached the process temperature to the spinning equipment and clamping it, wherein the total time for the transfer and clamping operations does not exceed 1 minute; Step S23: After the clamping is completed, the forged ring blank is heated up and the temperature of the forged ring blank is monitored to ensure that the temperature of the forged ring blank is not lower than 900° C. Step S24: After the temperature replenishment is completed, continue to perform hot spinning on the forged ring blank according to the spinning trajectory under the heat preservation condition, to obtain a spun ring part, and leave a rough machining allowance of 2-2.5 mm for the spun ring part.

2. The forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring for an aircraft engine according to claim 1, characterized in that: The detailed method of step S1 is as follows: under the condition of 1135-1165° C., the GH5188 high-temperature alloy rod-shaped raw material is subjected to the processes of blanking → upsetting → punching → horse rack reaming → ring rolling to obtain the required forging blank, and the forged ring blank is obtained by machining.

3. The forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring for an aircraft engine according to claim 1, characterized in that: The spun annular part is machined to obtain a ring part with a final outer contour. During the spinning process, the size of the spun annular part after spinning is designed based on the outer contour of the machined ring part.

4. The forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring for an aircraft engine according to claim 3, characterized in that: The design method of the size of the spun ring is: S011. Based on the inner and outer contour dimensions of the ring part after fine machining, a machining allowance of δ1 is added to one side to obtain a ring part in a rough machining state; S012. Based on the size of the rough-machined ring part, a spun ring part is obtained by adding a δ2 machining allowance to one side; S013 , performing smooth transition on the steps and / or right-angle transition positions of the spun ring component obtained in step S012 to obtain the size of the spun ring component.

5. The forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring for an aircraft engine according to claim 4, characterized in that: The sum of δ1 and δ2 does not exceed 5 mm, where δ1 is 2~2.5 mm and δ2 is 2~2.5 mm.

6. The forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring for an aircraft engine according to claim 1, characterized in that: Based on the size of the spun ring part, the theoretical size of the forged ring blank is designed. The specific method is: based on the size of the spun ring part, the inner diameter D0, wall thickness t0, and height L0 of the forged ring blank are calculated according to the basic principle that the volume of the metal material remains unchanged before and after spinning, wherein the inner diameter of the forged ring blank is the minimum inner diameter of the spun ring part, and the wall thickness t0 of the forged ring blank is not less than the maximum thickness of the spun ring part, which is determined according to the capacity of the spinning equipment and the forming performance of the high-temperature alloy itself; the height L0 of the forged ring blank is determined by the height of the spun ring part and the clamping length.

7. The forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring for an aircraft engine according to claim 1, characterized in that: During the spinning process of step S24, the forged ring blank is continuously subjected to temperature compensation, heat preservation and temperature monitoring using a semi-enclosed resistance heating device, so that the temperature of the forged ring blank is not lower than 900°C, and the spinning temperature of the forged ring blank is ensured to fluctuate within a range of no more than ±20°C during the process from the start to the end of the spinning deformation.

8. The forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring for an aircraft engine according to any one of claims 1 to 7, characterized in that: The hot forming method further includes step S3, wherein the spun annular component is subjected to a solution heat treatment at 1163-1191° C. for 40-50 minutes, followed by an oil cooling treatment.

9. The forging-spinning composite hot forming method for a GH5188 high-temperature alloy ring for an aircraft engine according to any one of claims 1 to 7, characterized in that: The tensile strength of GH5188 high-temperature alloy spun ring parts at room temperature is ≥862MPa, the yield strength is ≥379MPa, the elongation is ≥45%, and the grain size is grade 5 or above.

10. A GH5188 high-temperature alloy ring for an aircraft engine, characterized in that: The ring part is produced by the forging-spinning composite hot forming method of the GH5188 high-temperature alloy ring part for aircraft engines according to any one of claims 1 to 9.

Images