CN115156405A - Composite forming method for titanium alloy complex curved surface part - Google Patents

Composite forming method for titanium alloy complex curved surface part Download PDF

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Publication number
CN115156405A
CN115156405A CN202210671515.9A CN202210671515A CN115156405A CN 115156405 A CN115156405 A CN 115156405A CN 202210671515 A CN202210671515 A CN 202210671515A CN 115156405 A CN115156405 A CN 115156405A
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die
titanium alloy
forming
temperature
male die
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Inventor
陈明和
包幼林
冯瑞
谢兰生
曾强
李立新
葛严
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Nanjing University of Aeronautics and Astronautics
Hunan Aviation Powerplant Research Institute AECC
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Nanjing University of Aeronautics and Astronautics
Hunan Aviation Powerplant Research Institute AECC
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Priority to CN202210671515.9A priority Critical patent/CN115156405A/en
Publication of CN115156405A publication Critical patent/CN115156405A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D37/00—Tools as parts of machines covered by this subclass
    • B21D37/10—Die sets; Pillar guides
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
    • B21D22/02—Stamping using rigid devices or tools
    • B21D22/022—Stamping using rigid devices or tools by heating the blank or stamping associated with heat treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/021—Deforming sheet bodies
    • B21D26/027—Means for controlling fluid parameters, e.g. pressure or temperature
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/021—Deforming sheet bodies
    • B21D26/029—Closing or sealing means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/021—Deforming sheet bodies
    • B21D26/031—Mould construction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/053—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure characterised by the material of the blanks
    • B21D26/055—Blanks having super-plastic properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D35/00—Combined processes according to or processes combined with methods covered by groups B21D1/00 - B21D31/00
    • B21D35/002—Processes combined with methods covered by groups B21D1/00 - B21D31/00
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D37/00—Tools as parts of machines covered by this subclass
    • B21D37/16—Heating or cooling

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Thermal Sciences (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)

Abstract

The invention discloses a composite forming method for a titanium alloy complex curved surface part, belonging to the field of processing of metal plates and sectional materials, and comprising the following steps: heating the assembled die to a pre-stamping forming temperature, putting a titanium alloy plate, starting the movement of the male die to perform small-pressure stamping, stopping the movement when the male die reaches a preset position, and then preserving heat and pressure; and (3) after the superplastic gas bulging forming temperature is adjusted, continuously preserving heat and pressure, and increasing the pressure of the male die to form a closed cavity between the male die and the plate. And then, opening the air pressure control system, and blowing air from the punch head of the male die, so that the sheet is fully attached to the female die, and the wall thickness of the curved surface of the part is more uniform. And finally, cooling and reducing the pressure, and taking out the parts. The invention obviously improves the hot forming quality of the titanium alloy part, meets the requirement of mass production of engineering application, improves the production efficiency, saves energy and reduces the manufacturing cost of the titanium alloy part.

Description

Composite forming method for titanium alloy complex curved surface part
Technical Field
The invention belongs to the field of processing and treating metal plates and sectional materials, relates to a plastic forming composite process of a titanium alloy complex curved surface part, and particularly relates to a composite forming method for the titanium alloy complex curved surface part.
Background
The titanium alloy has the excellent characteristics of light weight, high strength, high temperature resistance, corrosion resistance and the like, and is widely applied to the field of aerospace, but the traditional hot stamping titanium alloy part has large resilience, is easy to crack and cannot be used for processing parts with complex curved surfaces;
the problem of damage defects in the production process of titanium alloy parts is solved by using the superplasticity of materials, and the more complex parts can be formed by fully using the high ductility of the materials under the superplasticity condition. However, the superplastic forming time is long, the speed is slow, the production efficiency is seriously influenced, and a new process method is urgently needed to be found to meet the requirements of rapid production and high precision of titanium alloy parts with complex curved surfaces.
The invention patent CN101786128A discloses a rapid superplastic forming process for aluminum alloy automobile body parts, which is mainly characterized in that hot stamping and superplastic gas bulging forming are combined for aluminum alloy, so that the advantages of the hot stamping and the superplastic gas bulging forming are complementary, and the purpose of rapid superplastic forming is achieved; but few researches are made on titanium alloy parts with complex curved surfaces.
Disclosure of Invention
Aiming at the problems in the prior art, the invention discloses a composite forming device and a composite forming method, which aim at titanium alloy complex curved surface parts, and design a pre-stamping process and a superplastic bulging process into integrated forming.
The invention is realized in the following way:
a composite forming method for titanium alloy parts with complex curved surfaces is disclosed, wherein the composite forming device comprises an upper heating plate and a lower heating plate, and a male die is arranged at the lower end of the upper heating plate; the upper end of the lower heating plate is provided with a female die; a front mold positioning baffle and a rear mold positioning baffle are arranged on the two sides of the male mold and the female mold; a titanium alloy plate is placed between the male die and the female die, and a blank holder is placed between the titanium alloy plate and the female die; the male die comprises a male die air inlet on the side surface, an air outlet on the bottom surface and a male die temperature measuring hole; the female die comprises a female die curved surface cavity and a female die temperature measuring hole which correspond to the male die, and the female die curved surface cavity is used for forming the complex curved surface of the titanium alloy part by monitoring the real-time temperature change of the die through the male die temperature measuring hole and the female die temperature measuring hole.
Further, the upper heating plate and the male die are fixed through a positioning fastening bolt; the lower heating plate and the female die are fixed through fastening bolts.
Furthermore, the front positioning baffle and the rear positioning baffle of the mold are fixed by a front baffle fastening bolt and a rear baffle fastening bolt respectively.
Further, a baffle bolt hole is formed in the male die and used for fixing a positioning baffle; and the female die is also provided with a connecting platform of the positioning baffle plate, and the connecting platform is connected with the positioning baffle plate.
Further, the forming method of the composite forming device comprises the following steps:
firstly, performing a high-temperature tensile test on a titanium alloy plate to obtain high-temperature stress-strain curves and performance data of the material at different temperatures and different strain rates, and preliminarily determining the range of forming process parameters as follows: the forming temperature is 700 to 850 ℃, and the strain rate is 0.001 to 0.1s -1 ；
Designing the size and the cavity curved surface of a forming die according to the size and the shape of a forming part, carrying out finite element numerical simulation on the titanium alloy plate hot forming process by adopting finite element software to optimize die design and process parameters, respectively selecting different deformation temperatures, strain rates and friction coefficients of the die to establish a simulation model, and formulating a corresponding experimental scheme of forming temperature, pressing amount and bulging pressure according to the thinning rate and the fracture failure condition of the titanium alloy plate as follows: the optimum forming temperature of the stamping is 800 ℃, and the strain rate is 0.01 s -1 (ii) a The optimal temperature for the gas bulging forming is 850 ℃, the air pressure load is 2.5MPa, and the heat preservation and pressure maintaining time is 10min;
cleaning the titanium alloy plate, removing oil stains on the surface of the material, then carrying out anti-oxidation treatment on the titanium alloy plate, the blank holder, the male die and the female die, respectively assembling the male die and the female die on heating equipment, namely on a heating plate and a lower heating plate, and preparing to start a forming experiment;
heating the die to a pre-stamping forming temperature, putting the titanium alloy plate, continuously preserving heat, and monitoring the temperature change of the upper die and the lower die in real time through a male die temperature measuring hole and a female die temperature measuring hole; then the male die starts to move downwards to perform stamping, and when the preset pressure is reached, the movement is stopped;
adjusting a temperature control system to ensure that the temperature of the male die temperature measuring hole and the female die temperature measuring hole reaches the superplastic gas bulging forming temperature, then continuing heat preservation and pressure maintaining, and increasing the blank holder force of the male die to ensure that the male die, the titanium alloy plate and the blank holder are tightly attached to form a sealing system and a cavity is formed between the sealing system and the blank holder;
step six, starting an air pressure control system, blowing argon from an air inlet of a male die, uniformly adjusting the wall thickness of the titanium alloy plate at a certain air pressure loading rate and pressure, and continuously keeping the temperature and the pressure for a period of time to ensure that the plate is fully attached to the die; finally, cooling and depressurizing, and taking out the parts.
The beneficial effects of the invention and the prior art are as follows:
the method comprises the steps of firstly carrying out preliminary low-pressure pre-stamping forming, enabling a plate material to flow into a curved surface of a cavity in a plastic manner at a high temperature, then increasing the blank holder force, forming a cavity between a male die and a part, starting the air-bulging forming, and enabling redundant material to be distributed on the side wall of the curved surface more uniformly. The invention combines the two processes of pre-stamping and super-plastic bulging, and performs low-pressure pre-stamping at high temperature to ensure that the titanium alloy performs sufficient metal plastic flow. And then heating and pressurizing, adopting superplastic gas bulging forming to repair the complex curved surface, continuously keeping the temperature and the pressure to eliminate residual stress, and finally relieving the pressure, cooling and taking the workpiece. The composite forming method perfectly combines the pre-stretching and the air-bulking superplastic forming processes, not only obviously improves the hot forming quality of the titanium alloy part, meets the requirement of mass production of engineering application, improves the production efficiency, saves energy and reduces the manufacturing cost of the titanium alloy part.
The scheme of the invention solves the problems of wrinkling, cracking and the like in the traditional hot processing of the titanium alloy plate, and simultaneously shortens the superplastic forming time. The process combines stamping and superplastic bulging, optimizes the forming result and improves the finished product rate of parts; in consideration of low superplastic forming efficiency, the invention adopts a uniform die and performs pre-stamping first, thereby greatly shortening the forming time and improving the production efficiency of the titanium alloy high-temperature part.
Compare in traditional superplastic forming, utilize the physiosis to form, make the part wall thickness more even, shorten production time, the part fracture that produces when having solved punching production, kick-back scheduling problem.
By utilizing the advantages of pre-stamping and superplastic forming, the surface precision of the titanium alloy complex curved surface part can be improved, the tonnage of forming equipment is reduced, and the service life of a die is prolonged, so that the aim of reducing the cost is fulfilled, the efficient production and manufacturing of the defect-free part are realized, and the titanium alloy complex curved surface part has higher practical and economic values.
Drawings
FIG. 1 is a process flow chart of a composite forming method for titanium alloy complex curved surface parts of the invention;
FIG. 2 is a schematic view of an example forming apparatus of a titanium alloy exhaust apparatus in an embodiment of the present invention;
FIG. 3 is a schematic diagram of a punch of a forming device for the composite forming method of the titanium alloy complex curved surface part;
FIG. 4 is a schematic diagram of a female die of a forming device of the composite forming method for the titanium alloy complex curved surface part;
the method comprises the following steps of 1-upper heating plate, 2-positioning fastening bolt, 3-mold rear positioning baffle, 4-rear baffle fastening bolt, 5-mold front positioning baffle, 6-front baffle fastening bolt, 7-titanium alloy plate, 8-blank holder, 9-male mold, 10-female mold, 11-fastening bolt, 12-lower heating plate, 13-male mold air inlet, 14-air outlet, 15-baffle bolt hole, 16-male mold temperature measuring hole, 17-female mold curved surface cavity, 18-positioning baffle connecting platform and 19-female mold temperature measuring hole.
Detailed Description
In order to make the objects, technical solutions and effects of the present invention more clear, the present invention is further described in detail by referring to examples below. It should be noted that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The process comprises the following steps: (1) firstly, performing a high-temperature forming performance test on a titanium alloy material to obtain data such as flow stress strain and the like, and preliminarily determining the range of forming process parameters; (2) according to the size and the curved surface appearance of the titanium alloy forming part, the curved surfaces and the shapes of the cavities of the male die and the female die are designed, finite element numerical simulation is carried out to optimize the design and the technological parameters of the die, the damage defect is avoided, and reasonable forming temperature and bulging pressure are formulated; (3) assembling a die, heating to an experimental temperature, putting a titanium alloy plate, performing high-temperature pre-stamping forming on the titanium alloy plate after heat preservation, wherein the forming pressure of primary forming cannot be too large, enough plates need to flow into an internal cavity through plasticity, and continuously preserving heat and pressure; (4) before argon is introduced to carry out gas bulging forming on the complex curved surface part of the titanium alloy part, the blank holder force of the plate needs to be increased, and a closed space is formed between the male die and the plate. And then, starting air pressure loading, so that the materials which flow into the part cavity before are more uniformly distributed on the curved surface side wall, and finally producing the complete and qualified titanium alloy complex curved surface part.
In the process of the invention, the remarks are that: factors such as pressing amount, punch speed, punch force, forming temperature and the like need to be controlled during preforming, and attention is paid to avoiding that the plastic flow of a plate is hindered due to overhigh pressure of a male die during punching and the part is cracked due to overhigh punching speed. Because the time required by the hot stamping process is shorter than that required by the air inflation process, the pressing amount can be increased as much as possible on the premise of ensuring the forming precision of the titanium alloy part, and the time consumed by the whole forming process is reduced. The method comprises the steps of carrying out numerical simulation on a hot stamping process by establishing an elastic-plastic finite element model of a sheet material, and determining and optimizing the sheet material deformation range and technological parameters such as punch speed, punch force, forming temperature and the like during preforming.
In the process, when superplastic ballooning is performed, appropriate pressure needs to be adopted by combining the curvature radius of a ballooning part. Generally, the smaller the radius of curvature of the part portion is, the greater the bulging pressure is applied to, and therefore, it is necessary to consider the pressure-receiving capacity of the critical part portion of the part, the pressure-receiving capacity of the inflator, the strength of the air duct, and other relevant conditions. Establishing a finite element model for the inflatable forming, carrying out numerical simulation on the inflatable process, and determining and optimizing parameters such as inflation speed, pressure, temperature and the like.
The invention adopts a composite process of stamping and superplastic bulging, and a pre-stamping die and a superplastic bulging die adopt the same die. Compare in traditional press die, the inside of this mould is processed the gas pocket passageway in advance.
The experimental equipment mainly comprises a convex-concave mould, a sealing and edge pressing device, a heating device, an argon and air pressure control system, a temperature control system and a press machine.
The composite scheme of pre-stamping and superplastic ballooning forming of the experimental titanium alloy complex curved surface part comprises the following steps: (1) cleaning a titanium alloy plate blank, and assembling a die after the blank and the die are subjected to oxidation resistance; (2) heating a die to a pre-stamping forming temperature, placing a titanium alloy plate, then starting to move a male die for small-pressure stamping, stopping moving when the male die reaches a preset position, and preventing the male die from being too tightly attached to a blank holder to prevent the plate from high-temperature plastic flow, and then keeping the temperature and pressure; (3) and (3) continuing heat preservation and pressure maintaining after the superplastic gas bulging forming temperature is adjusted, and increasing the pressure of the male die to form a closed cavity between the male die and the plate. And then, opening the air pressure control system, and blowing air from the punch head of the male die, so that the sheet is fully attached to the female die, and the wall thickness of the curved surface of the part is more uniform. And finally, cooling and reducing the pressure, and taking out the parts.
In the embodiment of the invention, a TA32 commercial titanium alloy plate is selected as the titanium alloy plate 7 to produce the exhaust device of a certain type of warplane engine, and the specific description of the embodiment in combination with figures 1 to 4 is as follows:
(1) Firstly, performing a high-temperature tensile test on a plate to obtain a high-temperature stress-strain curve and other performance data of the material at different temperatures and different strain rates, and preliminarily determining the range of forming process parameters;
(2) Designing the size and the cavity curved surface of a forming die according to the size and the shape of a forming part, carrying out finite element numerical simulation on the forming process to optimize die design and process parameters, avoiding damage defects, and formulating reasonable experimental schemes such as forming temperature, pressing amount, bulging pressure and the like, so that the production efficiency is improved, and the cost is reduced;
(3) Comprehensively considering the precision, cost and service life of a forming die, selecting proper die steel to manufacture the die, and designing a male die temperature measuring hole 16, a female die temperature measuring hole 19, a male die air inlet 13 and an air outlet 14 on a male die and a female die to prepare for super-plastic bulging;
(4) Selecting proper equipment such as a press machine, a heating device, inflation equipment, an air pressure control system, a temperature detection device, an air pressure detector and the like.
The forming method of the composite forming device comprises the following steps:
firstly, cleaning with alcoholRemoving oil stains on the surface of a titanium alloy plate 7, then carrying out anti-oxidation treatment on the titanium alloy plate 7, a blank holder 8, a male die 9 and a female die 10, assembling and fixing the male die 9 and the female die 10 on an upper heating plate 1 and a lower heating plate 12 of heating equipment, and preparing to start a forming experiment; performing a high-temperature tensile test on the titanium alloy plate to obtain high-temperature stress-strain curves and performance data of the material at different temperatures and different strain rates, and preliminarily determining the range of forming process parameters as follows: the forming temperature is 700 to 850 ℃, and the strain rate is 0.001 to 0.1s -1 ；
And step two, heating the die to a pre-stamping forming temperature, putting the titanium alloy plate 7 into the die, continuously preserving heat, and monitoring the temperature changes of the upper die and the lower die in real time through the male die temperature measuring hole 16 and the female die temperature measuring hole 19. The punch 9 then starts moving downwards for punching and stops when a predetermined pressure is reached. At this time, in order to ensure high-temperature plastic flow, the pressure of the male die 9 cannot be too large; the optimum forming temperature of the stamping is 800 ℃, and the strain rate is 0.01 s -1 (ii) a The optimal temperature for the gas bulging forming is 850 ℃, the air pressure load is 2.5MPa, and the heat preservation and pressure maintaining time is 10min;
adjusting a temperature control system to ensure that the temperature of the male die temperature measuring hole 16 and the female die temperature measuring hole 19 reaches the superplastic gas bulging forming temperature, continuing to keep the temperature and the pressure, then increasing the blank holder force of the male die 9, and ensuring that the male die 9, the titanium alloy plate 7 and the blank holder 8 are tightly attached to form a sealing system and a cavity is formed between the sealing system and the blank holder;
and step four, starting an air pressure control system, blowing argon from the male die air inlet hole 13, uniformly adjusting the wall thickness of the titanium alloy plate 7 at a proper air pressure loading rate and pressure, and continuously keeping the temperature and the pressure for a period of time to ensure that the plate is fully attached to the die. Finally, cooling and depressurizing, and taking out the parts.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that modifications can be made by those skilled in the art without departing from the principle of the present invention, and these modifications should also be construed as the protection scope of the present invention.

Claims (5)

1. The composite forming method for the titanium alloy part with the complex curved surface is characterized in that the composite forming device comprises an upper heating plate (1) and a lower heating plate (12), wherein a male die (9) is arranged at the lower end of the upper heating plate (1); the upper end of the lower heating plate (12) is provided with a concave die (10); a front mold positioning baffle (5) and a rear mold positioning baffle (3) are arranged on the two sides of the male mold (9) and the female mold (10);
a titanium alloy plate (7) is placed between the male die (9) and the female die (10), and a blank holder (8) is placed between the titanium alloy plate (7) and the female die (10);
the male die (9) comprises a male die air inlet (13) on the side surface, an air outlet (14) on the bottom surface and a male die temperature measuring hole (16); the female die (10) comprises a female die curved surface cavity (17) and a female die temperature measuring hole (19) which correspond to the male die (9), and the female die curved surface cavity (17) is used for monitoring real-time temperature change of the die and is used for forming the complex curved surface of the titanium alloy part through the male die temperature measuring hole (16) and the female die temperature measuring hole (19).
2. The composite forming method for the titanium alloy complex curved surface part is characterized in that the upper heating plate (1) and the punch (9) are fixed through a positioning fastening bolt (2); the lower heating plate (12) and the female die (10) are fixed through a fastening bolt (11).
3. The composite forming method for the titanium alloy complex curved surface part according to claim 1, wherein the front positioning baffle (5) and the rear positioning baffle (3) of the mold are fixed by a front baffle fastening bolt (6) and a rear baffle fastening bolt (4) respectively.
4. The composite forming method for the titanium alloy complex curved surface part is characterized in that a baffle plate bolt hole (15) is further formed in the male die (9) and used for fixing and positioning the baffle plate (5);
and the female die (10) is also provided with a connecting platform (18) of the positioning baffle plate, and the connecting platform is used for being connected with the positioning baffle plate (5).
5. The composite forming method for the titanium alloy complex curved surface part as claimed in claim 1, wherein the forming method of the composite forming device comprises the following steps:
firstly, performing a high-temperature tensile test on a titanium alloy plate (7) to obtain high-temperature stress-strain curves and performance data of the material at different temperatures and different strain rates, and preliminarily determining the range of forming process parameters as follows: the forming temperature is 700 to 850 ℃, and the strain rate is 0.001 to 0.1s -1 ；
Designing the size and the cavity curved surface of a forming die according to the size and the shape of a forming part, carrying out finite element numerical simulation on the titanium alloy plate hot forming process by adopting finite element software to optimize die design and process parameters, respectively selecting different deformation temperatures, strain rates and friction coefficients of the die to establish a simulation model, and formulating the corresponding experimental scheme of forming temperature, pressing amount and bulging pressure according to the thinning rate and the fracture failure condition of the titanium alloy plate (7) as follows: the optimum forming temperature of the stamping is 800 ℃, and the strain rate is 0.01 s -1 (ii) a The gas bulging forming temperature is 850 ℃, the air pressure load is 2.5MPa, and the heat preservation and pressure maintaining time is 10min;
cleaning the titanium alloy plate (7), removing oil stains on the surface of the material, then carrying out anti-oxidation treatment on the titanium alloy plate (7), the blank holder (8), the male die (9) and the female die (10), respectively assembling the male die (9) and the female die (10) on heating equipment, namely on the heating plate (1) and the lower heating plate (12), and preparing to start a forming experiment;
heating the die to a pre-stamping forming temperature, putting a titanium alloy plate (7), continuously preserving heat, and monitoring the temperature changes of the upper die and the lower die in real time through a male die temperature measuring hole (16) and a female die temperature measuring hole (19); then the male die (9) starts to move downwards for punching, and stops moving when reaching a preset pressure;
fifthly, adjusting a temperature control system to keep the temperature and pressure of the male die temperature measuring hole (16) and the female die temperature measuring hole (19) at the superplastic ballooning forming temperature, and then increasing the blank holder force of the male die (9) to enable the male die (9), the titanium alloy plate (7) and the blank holder (8) to be tightly attached to form a sealing system, and a cavity is formed between the sealing system and the blank holder;
step six, starting an air pressure control system, blowing argon from an air inlet (13) of a male die, uniformly adjusting the wall thickness of the titanium alloy plate (7) at a certain air pressure loading rate and pressure, and continuing to keep the temperature and the pressure for a period of time to ensure that the plate is fully attached to the die; and finally, cooling and depressurizing, and taking out the parts.
CN202210671515.9A 2022-06-14 2022-06-14 Composite forming method for titanium alloy complex curved surface part Pending CN115156405A (en)

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Cited By (1)

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CN115647200A (en) * 2022-11-01 2023-01-31 中国航发沈阳黎明航空发动机有限责任公司 Inflatable creep repairing device and method for titanium alloy hollow blade forming defects

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115647200A (en) * 2022-11-01 2023-01-31 中国航发沈阳黎明航空发动机有限责任公司 Inflatable creep repairing device and method for titanium alloy hollow blade forming defects

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