CN117226439B - Method for forming TA12A grinding ring of aero-engine material - Google Patents
Method for forming TA12A grinding ring of aero-engine material Download PDFInfo
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- CN117226439B CN117226439B CN202311490185.4A CN202311490185A CN117226439B CN 117226439 B CN117226439 B CN 117226439B CN 202311490185 A CN202311490185 A CN 202311490185A CN 117226439 B CN117226439 B CN 117226439B
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- 238000000034 method Methods 0.000 title claims abstract description 36
- 239000000463 material Substances 0.000 title claims abstract description 31
- 238000000227 grinding Methods 0.000 title claims description 10
- 238000005096 rolling process Methods 0.000 claims abstract description 109
- 238000004080 punching Methods 0.000 claims abstract description 49
- 238000004321 preservation Methods 0.000 claims abstract description 16
- 238000002360 preparation method Methods 0.000 claims abstract description 9
- 238000005242 forging Methods 0.000 claims description 56
- 239000000203 mixture Substances 0.000 claims description 52
- 238000001816 cooling Methods 0.000 claims description 36
- 239000011248 coating agent Substances 0.000 claims description 33
- 238000000576 coating method Methods 0.000 claims description 33
- 239000000843 powder Substances 0.000 claims description 25
- 238000010438 heat treatment Methods 0.000 claims description 24
- 238000005507 spraying Methods 0.000 claims description 21
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 11
- 239000003822 epoxy resin Substances 0.000 claims description 11
- 239000007788 liquid Substances 0.000 claims description 11
- PAZHGORSDKKUPI-UHFFFAOYSA-N lithium metasilicate Chemical compound [Li+].[Li+].[O-][Si]([O-])=O PAZHGORSDKKUPI-UHFFFAOYSA-N 0.000 claims description 11
- 229910052912 lithium silicate Inorganic materials 0.000 claims description 11
- 229920000647 polyepoxide Polymers 0.000 claims description 11
- 229920005989 resin Polymers 0.000 claims description 11
- 239000011347 resin Substances 0.000 claims description 11
- 229910052710 silicon Inorganic materials 0.000 claims description 11
- 239000010703 silicon Substances 0.000 claims description 11
- XJKVPKYVPCWHFO-UHFFFAOYSA-N silicon;hydrate Chemical compound O.[Si] XJKVPKYVPCWHFO-UHFFFAOYSA-N 0.000 claims description 11
- 229910052902 vermiculite Inorganic materials 0.000 claims description 11
- 235000019354 vermiculite Nutrition 0.000 claims description 11
- 239000010455 vermiculite Substances 0.000 claims description 11
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 11
- 239000003973 paint Substances 0.000 claims description 9
- 238000002156 mixing Methods 0.000 claims description 8
- 239000002994 raw material Substances 0.000 claims description 8
- 238000003756 stirring Methods 0.000 claims description 8
- 238000007599 discharging Methods 0.000 claims description 6
- 238000009413 insulation Methods 0.000 claims description 6
- 150000004767 nitrides Chemical class 0.000 claims description 5
- 238000001132 ultrasonic dispersion Methods 0.000 claims description 5
- 238000000465 moulding Methods 0.000 claims description 4
- 239000003921 oil Substances 0.000 claims description 4
- 229920000742 Cotton Polymers 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000012805 post-processing Methods 0.000 claims 1
- 229910001069 Ti alloy Inorganic materials 0.000 abstract description 20
- 230000008569 process Effects 0.000 abstract description 16
- 230000008859 change Effects 0.000 abstract description 6
- 238000001953 recrystallisation Methods 0.000 abstract description 3
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- 238000012545 processing Methods 0.000 description 6
- 229910045601 alloy Inorganic materials 0.000 description 5
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- 238000005336 cracking Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
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- GDTSJMKGXGJFGQ-UHFFFAOYSA-N 3,7-dioxido-2,4,6,8,9-pentaoxa-1,3,5,7-tetraborabicyclo[3.3.1]nonane Chemical compound O1B([O-])OB2OB([O-])OB1O2 GDTSJMKGXGJFGQ-UHFFFAOYSA-N 0.000 description 1
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Abstract
The invention discloses an aeroengine material TA12A ring rolling forming method, which comprises the following steps: s1, preheating preparation; s2, upsetting and punching; s3, ring rolling for 1 fire; s4, ring rolling for 2 fires; s5, ring rolling for 3 fires; according to the invention, the phase change recrystallization principle is utilized, rolling rings at different temperatures and different heat preservation times are carried out three times below a two-phase region, so that the structure of the TA12A blank is uniform, the stability and reproducibility of the titanium alloy are improved, meanwhile, the punching is easier through setting upsetting punching process parameters, and the blank ring forming is easier through combining the front surface with the back surface.
Description
Technical Field
The invention relates to the technical field of aviation aircraft manufacturing, in particular to a molding method of an aero-engine material TA12A grinding ring.
Background
The TA12A alloy is near alpha-type heat strong titanium alloy with good comprehensive performance, and the long-time working temperature of the alloy can reach 550 ℃. The TA12A alloy has the main characteristics of high strength, low density, good corrosion resistance, good welding performance and excellent high temperature resistance, can effectively improve the load capacity and reduce the weight due to the lower density and the good mechanical property, and can be used for manufacturing aircraft structural members and spacecraft components in the aerospace field.
At present, the TA12A alloy has more alloy element types, higher content and poor process plasticity, particularly when the material temperature is lower than the transformation point temperature, the forging process is easy to crack, and the temperature interval for forging is narrower. The product produced by adopting the conventional forging process with the temperature from high to low has uneven high-low multiple tissues, and the performance and flaw detection level can not stably meet the related technical requirements, thereby seriously affecting the quality and the yield of the product. Therefore, the titanium alloy ring rolling forming technology faces the development directions of further improving the forming precision and the surface quality, reducing the production cost, increasing the material utilization rate and the like.
Disclosure of Invention
In order to solve the problems, the invention provides a molding method for a TA12A grinding ring of an aero-engine material.
The technical scheme of the invention is as follows: an aeroengine material TA12A ring rolling forming method comprises the following steps:
s1, preheating preparation:
firstly, taking a cylindrical blank with a material TA12A, spraying heat-insulating paint on the surface of the blank, and heating at a temperature T β -30 ℃ to T β Heating the blank in a furnace at 50 ℃ below zero for 200min, taking out, wrapping heat preservation cotton on the outer circle of the blank, returning to the furnace, continuously heating for 25min, and discharging; wherein the diameter of the cylindrical blank is marked as phi, and the height is marked as H and T β The phase transition point temperature of the blank;
s2, upsetting and punching:
upsetting the blank after discharging to a height of 0.45H-0.47H at a temperature of 850-950 ℃, punching the blank by using a punch, wherein the thickness of a punched bottom plate is 0.05H-0.15H, and the punching adopts a mode of alternately front punching and back punching, so that the blank is rounded with the punch; then air cooling to room temperature to obtain a forging;
the height of the punch head for front punching is the same as the height of the blank after upsetting, and the height of the punch head for back punching is 1/3 of the height of the blank after upsetting;
s3, ring rolling 1 fire:
at a temperature of T β -25 ℃ to T β Heating and preserving heat of the forging for 100-120 min at-45 ℃, performing primary ring rolling, then returning to the furnace and preserving heat for 55-65 min, performing secondary ring rolling, and performing air cooling to room temperature after forging;
s4, ring rolling 2 fires:
at a temperature of T β -20 ℃ to T β Heating and preserving heat of the forging at the temperature of minus 30 ℃ for 75-100 min, performing primary ring rolling, then returning to the furnace and preserving heat for 40-55 min, performing secondary ring rolling, and performing air cooling to room temperature after forging;
s5, ring rolling for 3 fires:
at a temperature of T β -25 ℃ to T β And heating and preserving heat of the forging at the temperature of-45 ℃ for 50-75 min, carrying out primary ring rolling, then returning to the furnace and preserving heat for 30-45 min, carrying out secondary ring rolling, carrying out ring rolling to the required size, carrying out air cooling to room temperature after forging, and finally carrying out post treatment to obtain the formed part.
Description: according to the method, the phase change recrystallization principle is utilized, rolling rings at different temperatures and different heat preservation times are carried out three times below a two-phase region, so that the structure of the TA12A blank is uniform, the stability and reproducibility of the titanium alloy are improved, meanwhile, punching is easier through setting upsetting and punching process parameters, and blank looping is easier through a mode of combining the front surface with the back surface.
Further, in the step S3 ring rolling 1 fire and the step S4 ring rolling 2 fire, the ring rolling adopts a horizontal ring rolling machine to grind rings, and a 2000t oil pressure machine is adopted to roll flat end surfaces; and S5, ring rolling in 3-fire ring rolling adopts a vertical ring rolling machine to roll rings.
Description: the ring rolling machine is arranged in different steps, so that the processing characteristics of the titanium alloy material can be utilized, and the ring rolling process is smoother; in the process of multiple ring rolling, the internal tissue structure of the titanium alloy material is more uniform, the forging is pre-rolled rapidly and efficiently by utilizing the larger processing capacity of the horizontal ring rolling machine in the step S3 ring rolling 1 fire and the step S4 ring rolling 2 fire, and the obtained titanium alloy has better mechanical property by utilizing the characteristics of the vertical ring rolling machine, such as better stability and grinding processability in the step S5 ring rolling 3 fire and matching with the 3 ring rolling processes.
Further, in the step S5, the forging is placed into a warm charging furnace for heating, the temperature in Wen Zhuanglu is 830-870 ℃, and the temperature is kept for 10-15 min; a molded article was obtained.
Description: through the post-treatment step, the surface property of the titanium alloy material can be enhanced, so that the titanium alloy material meets the application requirements of aviation materials.
Further, in the step S2, upsetting and punching the forging to the required height, wherein the required height is 0.42H-0.43H, and controlling the inner diameter of the forging obtained by punching to be k multiplied by phi through selecting a punch, wherein k is a proportionality coefficient, the value range is 0.10-0.80, and in the step S1, if the height-diameter ratio of the blank is less than 1.4, the value of k is 0.43-0.80; if the height-diameter ratio of the blank is 1.4-2, the value of k is 0.41-0.42; otherwise, the value of k is 0.10-0.40.
Description: through setting for the internal diameter size of punching a hole, can combine the internal diameter that obtains of punching a hole with the ratio of height to diameter of blank, make the inside structure of forging annular that obtains of punching a hole better, avoid the drift to select to use inappropriately, cause the ring difficulty to and the inside nature of ring is influenced by punching a hole and is caused inhomogeneous, not inseparable problem, can let the punching a hole become easier simultaneously, save punching a hole time.
Further, in the upsetting and punching step S2, the deformation is controlled to be 31-33% by controlling the pressure; in the step S3, in the ring rolling process of 1 fire, the deformation of the ring rolling process is controlled to be 27-29%; in the step S4, ring rolling is carried out in 2 fires, and the deformation is controlled to be 33-35%; and in the step S5, ring rolling is carried out in 3 fires, and the deformation is controlled to be 35-37%.
Description: by controlling the deformation in the 3-time rolling ring, the mechanical property and the internal structure property of the titanium alloy annular forging can be further optimized, the generation of subsequent cracks and the like is avoided, and the yield is further improved.
In the upsetting and punching step S2, cooling to room temperature by adopting air flow rate of 15-17 m/S after forging; s3, in ring rolling 1 fire, cooling to room temperature by adopting air flow rate of 18-20 m/S after forging; s4, in the ring rolling 2 fire, cooling to room temperature by adopting air flow rate of 14-16 m/S after forging; step S5 is to cool to room temperature under natural air.
Description: through the corresponding arrangement of the hollow cooling method in each step, the internal structure of the forging can be protected to a large extent while the cooling time is saved, and the phenomenon of uneven structure is avoided.
In the step S1, the thickness of the thermal insulation coating sprayed on the surface of the blank is 40-50 mu m.
Description: experiments prove that the thermal insulation coating with the thickness has better performance of finished products.
Further, the heat-insulating coating comprises the following raw materials in parts by weight: 10-20 parts of tetraboro powder, 10-15 parts of vermiculite powder, 10-15 parts of silicon micropowder, 10-20 parts of liquid lithium silicate, 15-20 parts of organic silicon water-based resin and 10-15 parts of water-based epoxy resin.
Description: the heat-insulating coating has heat insulation and oxidation resistance, can form a heat-insulating layer, reduces heat conduction, improves heat-insulating performance of materials, can effectively prevent oxidation reaction and prolongs service life of forged parts; the fine particle size and the larger specific surface area of the silicon micro powder and the excellent heat resistance of the fine heat-resistant vermiculite powder are utilized, wherein the fine properties of the tetraborate mono powder such as high melting point, high hardness, high heat conductivity, low thermal expansion coefficient and the like are utilized; the liquid lithium silicate has heat resistance, the organic silicon water-based resin has excellent weather resistance, pollution resistance and chemical corrosion resistance, and the water-based epoxy resin has the characteristics of low volatility and good environmental protection, and the raw materials can effectively protect the titanium alloy material in a high-temperature environment.
Further, the preparation method of the heat-insulating paint and the spraying method are as follows:
s1-1, mixing and stirring tetraborium nitride powder and liquid lithium silicate for 20-25 min at the temperature of 15-25 ℃ to obtain a first mixture; performing ultrasonic dispersion on the vermiculite powder and the organic silicon water-based resin for 5-7 min at 33-35 kHz at the temperature of 55-60 ℃ to obtain a second mixture; at the temperature of 75-80 ℃, the silicon micropowder and the water-based epoxy resin are homogenized and dispersed into a third mixture by adopting high-pressure homogenizing equipment under the pressure of 10-15 MPa;
s1-2, respectively taking one half of the mass of the first mixture, the second mixture and the third mixture at room temperature, and then stirring and mixing to obtain the coating;
s1-3, according to the spraying sequence of the third mixture, the second mixture and the first mixture, sequentially spraying the rest half of the third mixture, the second mixture and the first mixture on the surface of the blank until the thickness of the coating is 20-30 mu m, and then spraying the coating until the thickness of the coating is 40-60 mu m.
Description: the coating obtained by the method has more excellent performance and better protection effect on the titanium alloy, and by the spraying mode, the characteristics of each layer of material can be utilized, the heat preservation and antioxidation effects of the coating can be fully exerted, and the surface texture performance of the obtained titanium alloy forging is better.
Further, taking blanks with the specification of 1.04 phi-1.05 phi and 1.13H-1.14H as heightening parts, and carrying out the processing of the steps S1-S5 on the heightening parts.
Description: the heightening piece can effectively adjust the diameter of the ring and control the shape of the ring, so that the deformation of the ring in the forming process is more accurate and controlled, and the required forming effect and product quality are further obtained.
The beneficial effects of the invention are as follows:
(1) According to the invention, by utilizing the phase change recrystallization principle, rolling rings at different temperatures and different heat preservation times are performed three times below a two-phase region, so that the structure of a TA12A blank is uniform, the stability and reproducibility of titanium alloy are improved, meanwhile, punching is easier through setting upsetting punching process parameters, and blank looping is easier through a mode of combining the front surface with the back surface;
(2) The invention is arranged in different steps by the ring rolling machine, and can make the ring rolling process smoother by utilizing the processing characteristics of the titanium alloy material; in the process of grinding rings for multiple times, the internal tissue structure of the titanium alloy material is more uniform, so that the mechanical property of the obtained titanium alloy is better; through setting the inner diameter of the punched hole, the inner diameter obtained by punching and the height-diameter ratio of the blank can be combined, so that the punched hole is easier, the punching time is saved, meanwhile, the internal structure of the forging piece obtained by punching is better, and the problems of difficult looping and nonuniform and non-compact looping property caused by improper selection of the punch are avoided;
(3) The method controls the deformation in the 3-time rolling ring, can further optimize the mechanical property and internal structure property of the titanium alloy annular forging, avoid the generation of subsequent cracks and the like, and further improve the yield; through the corresponding arrangement of the hollow cooling method in each step, the internal structure of the forging can be protected to a large extent while the cooling time is saved, and the phenomenon of uneven structure is avoided;
(4) The novel heat-insulating coating has heat insulation and oxidation resistance, can form a heat-insulating layer, reduces heat conduction, improves heat-insulating performance of materials, can effectively prevent oxidation reaction and prolongs service life of forged parts; through the spraying arrangement, the characteristics of each layer of material can be utilized, the heat preservation and antioxidation effects of the titanium alloy forging can be fully exerted, and the tissue performance of the obtained titanium alloy forging is better.
Detailed Description
The invention will be described in further detail with reference to the following embodiments to better embody the advantages of the invention.
Example 1: an aeroengine material TA12A ring rolling forming method comprises the following steps:
s1, preheating preparation:
firstly, taking a cylindrical blank with a material TA12A, spraying heat-insulating paint with a thickness of 50 mu m on the surface of the blank, adopting the heat-insulating paint sold in the market, heating the blank in a furnace for 200min at the temperature of 965 ℃, taking out, wrapping heat-insulating cotton on the outer circle of the blank, returning to the furnace, continuously heating for 25min, and discharging; wherein, the diameter of the cylindrical blank is marked as phi=230 mm, and the height is marked as H=380 mm; t (T) β The phase transition point temperature of the blank; detected T β =1005℃；
S2, upsetting and punching:
upsetting the blank after discharging to a height of 0.46H at 900 ℃, punching the blank by using a punch, wherein the thickness of a punching bottom plate is 0.1H, and the punching adopts a mode of alternately front punching and back punching and is round with the punch; then air cooling to room temperature to obtain a forging;
the height of the punch head for front punching is the same as the height of the blank after upsetting, and the height of the punch head for back punching is 1/3 of the height of the blank after upsetting;
upsetting and punching the forging to the required height, wherein the required height is 0.42H, selecting a punch with the diameter of 130, and controlling the inner diameter of the forging obtained by punching to be k multiplied by phi, wherein the height-diameter ratio of the blank is 1.65, so that k is 0.416; the deformation amount was set to 32% by controlling the pressure; cooling to room temperature by adopting air flow rate of 16m/s after forging;
s3, ring rolling 1 fire:
at a temperature of T β Heating and preserving heat of the forging at the temperature of minus 30 ℃ for 110min, performing primary ring rolling, then returning to the furnace and preserving heat for 60min, performing secondary ring rolling, and performing air cooling to room temperature after forging; rolling rings by a horizontal ring rolling machine, and rolling flat end surfaces by a 2000t oil pressure machine; the ring rolling deformation is controlled at 28%; cooling to room temperature by adopting air flow rate of 19m/s after forging;
s4, ring rolling 2 fires:
at a temperature of T β Heating and preserving heat for 90min at the temperature of 25 ℃ below zero, performing primary ring rolling, then returning to the furnace and preserving heat for 45min, performing secondary ring rolling, and performing air cooling to room temperature after forging; rolling rings by a horizontal ring rolling machine, and rolling flat end surfaces by a 2000t oil pressure machine; ring rolling until the deformation is controlled at 34%; air cooling after forging is carried out to room temperature by adopting an air flow rate of 15 m/s;
s5, ring rolling for 3 fires:
at a temperature of T β Heating and preserving heat for 60min at the temperature of minus 35 ℃, carrying out primary ring rolling, then returning to a furnace and preserving heat for 35min, and carrying out secondary ring rolling until the ring rolling reaches the required size, wherein the ring rolling adopts a vertical ring rolling machine for ring rolling; ring rolling until the deformation is controlled at 36%; cooling to room temperature in natural air after forging; and finally, post-treatment: putting the forge piece into a warm charging furnace for heating, keeping the temperature in Wen Zhuanglu at 850 ℃ and preserving the temperature for 13min; a molded article was obtained.
Example 2: the present embodiment is different from embodiment 1 in that k is 0.41 in step S2.
Example 3: the present embodiment is different from embodiment 1 in that k is 0.42 in step S2.
Example 4: the present embodiment is different from embodiment 1 in that the temperature parameter is different, and the temperature in step S1 is T β -30 ℃; the temperature in the step S2 is 850 ℃, and the temperature in the step S3 is T β -25 ℃, temperature T in step S4 β -30 ℃, temperature T in step S5 β -45℃。
Example 5: the present embodiment is different from embodiment 1 in that the temperature parameter is different, and the temperature in step S1 is T β -50 ℃; the temperature in the step S2 is 950 ℃, and the temperature in the step S3 is T β -45 ℃, the temperature in step S4 is T β -20 ℃, temperature T in step S5 β -25℃ 。
Example 6: the present embodiment is different from embodiment 1 in that the deformation amount is different, and the deformation amount is controlled to 31% in step S2; in the step S3, the deformation is controlled at 27%; in the step S4, the deformation is controlled at 35%; the deformation amount in step S5 was controlled to 37%.
Example 7: the present embodiment is different from embodiment 1 in that the deformation amount is different, and the deformation amount is controlled to 33% in step S2; in the step S3, the deformation is controlled at 29%; in the step S4, the deformation is controlled at 33%; the deformation amount in step S5 is controlled to 35%.
Example 8: the embodiment is different from embodiment 1 in that the heat preservation time is different, in step S3, the forging is heated and preserved for 100min, the primary ring rolling is performed, then the furnace is returned for heat preservation for 65min, and the secondary ring rolling is performed; step S4, heating and preserving heat of the forging for 75min, performing primary ring rolling, then returning to the furnace and preserving heat for 55min, and performing secondary ring rolling; and step S5, heating and preserving heat of the forge piece for 75min, performing primary ring rolling, then returning to the furnace and preserving heat for 30min, and performing secondary ring rolling.
Example 9: the embodiment is different from embodiment 1 in that the heat preservation time is different, in step S3, the forging is heated and preserved for 120min, the primary ring rolling is performed, then the furnace is returned for heat preservation for 55min, and the secondary ring rolling is performed; step S4, heating and preserving heat of the forging for 100min, performing primary ring rolling, then returning to the furnace and preserving heat for 40min, and performing secondary ring rolling; and S5, heating and preserving heat of the forge piece for 50min, performing primary ring rolling, then returning to the furnace and preserving heat for 45min, and performing secondary ring rolling.
Example 10: the difference between this embodiment and embodiment 1 is that the upsetting and punching process parameters are different, in step S2, the blank after being discharged from the furnace is first upset to a height of 0.45H, and then punched by a punch, and the thickness of the punched bottom sheet is 0.05H.
Example 11: the difference between this embodiment and embodiment 1 is that the upsetting and punching process parameters are different, in step S2, the blank after being discharged from the furnace is first upset to a height of 0.47H, and then punched by a punch, and the thickness of the punched bottom sheet is 0.15H.
Example 12: the difference between this embodiment and embodiment 1 is that the air cooling air flow rate is different, and the air cooling after forging in step S2 is performed to cool to room temperature with an air flow rate of 15 m/S; in the step S3, cooling to room temperature by adopting an air flow rate of 18 m/S; in the step S4, the air cooling after forging is carried out by adopting the air flow rate of 16m/S to cool to the room temperature, in the step S5, the temperature in Wen Zhuanglu is 870 ℃, and the heat is preserved for 10min; a molded article was obtained.
Example 13: the difference between this embodiment and embodiment 1 is that the air cooling air flow rate is different, and the air cooling after forging in step S2 is performed to cool to room temperature by adopting an air flow rate of 17 m/S; in the step S3, cooling to room temperature by adopting an air flow rate of 20 m/S; in the step S4, the air cooling after forging is carried out by adopting the air flow rate of 14m/S to cool to the room temperature, in the step S5, the temperature in Wen Zhuanglu is 830 ℃, and the temperature is kept for 15min; a molded article was obtained.
Example 14: the embodiment is different from embodiment 1 in that the heat-insulating paint comprises the following raw materials in parts by mass: 15 parts of tetraborium nitride powder, 13 parts of vermiculite powder, 13 parts of silicon micro powder, 15 parts of liquid lithium silicate, 18 parts of organic silicon water-based resin and 13 parts of water-based epoxy resin.
The preparation of the heat preservation coating and the spraying process are as follows:
s1-1, mixing and stirring tetraborium nitride powder and liquid lithium silicate for 22min at the temperature of 20 ℃ to obtain a first mixture; performing ultrasonic dispersion on the vermiculite powder and the organic silicon water-based resin for 6min at the temperature of 58 ℃ under 34kHz to obtain a second mixture; homogenizing and dispersing the silicon micropowder and the water-based epoxy resin into a third mixture at the temperature of 78 ℃ by adopting high-pressure homogenizing equipment under the pressure of 14 MPa;
s1-2, respectively taking one half of the mass of the first mixture, the second mixture and the third mixture at room temperature, and then stirring and mixing to obtain the coating;
s1-3, sequentially spraying the rest half of the third mixture, the second mixture and the first mixture on the surface of the blank according to the spraying sequence of the third mixture, the second mixture and the first mixture until the thickness of the coating is 25 mu m, and then spraying the coating until the thickness of the coating is 50 mu m.
Example 15: the embodiment is different from embodiment 14 in that the raw material components are different, and according to the parts by weight, the weight of the raw material components is 10 parts of tetraborium nitride powder, 15 parts of vermiculite powder, 15 parts of silicon micro powder, 10 parts of liquid lithium silicate, 20 parts of organic silicon water-based resin and 15 parts of water-based epoxy resin; and in the step S1-3, the rest half of the third mixture, the second mixture and the first mixture are sequentially sprayed on the surface of the blank until the thickness of the coating is 30 mu m, and then the coating is sprayed until the thickness of the coating is 60 mu m.
Example 16: the embodiment is different from embodiment 14 in that the raw material components are different, and according to the parts by weight, 20 parts of tetraboro-nitride powder, 10 parts of vermiculite powder, 10 parts of silicon micropowder, 20 parts of liquid lithium silicate, 15 parts of organic silicon water-based resin and 10 parts of water-based epoxy resin are mixed; and in the step S1-3, according to the spraying sequence of the third mixture, the second mixture and the first mixture, sequentially spraying the rest half of the third mixture, the second mixture and the first mixture on the surface of the blank until the thickness of the coating is 20 mu m, and then spraying the coating until the thickness of the coating is 40 mu m.
Example 17: the difference between this example and example 14 is that the preparation parameters of the heat-insulating paint are different, S1-1, mixing and stirring the tetraboro-nitride powder and the liquid lithium silicate for 20min at 15 ℃ to obtain a first mixture; performing ultrasonic dispersion on the vermiculite powder and the organic silicon water-based resin for 5min at the temperature of 55 ℃ to obtain a second mixture; at 80 ℃, the silicon micropowder and the water-based epoxy resin are homogenized and dispersed into a third mixture by adopting high-pressure homogenizing equipment under 15 MPa.
Example 18: the difference between this example and example 14 is that the preparation parameters of the heat-insulating paint are different, S1-1, mixing and stirring the tetraboro-nitride powder and the liquid lithium silicate for 25min at the temperature of 25 ℃ to obtain a first mixture; at 60 ℃, performing ultrasonic dispersion on the vermiculite powder and the organic silicon water-based resin for 7min at 33kHz to obtain a second mixture; at 75 ℃, the silicon micropowder and the water-based epoxy resin are homogenized and dispersed into a third mixture by adopting high-pressure homogenizing equipment under 10 MPa.
Example 19: the difference between this embodiment and embodiment 1 is that a blank with a specification of 1.04 Φ and 1.13H is taken as a heightening member, and the heightening member is subjected to the processing of steps S1 to S5.
Example 20: the difference between this embodiment and embodiment 1 is that a blank with a specification of 1.05Φ and 1.14h is taken as a heightening member, and the heightening member is subjected to the processing of steps S1 to S5.
Example 21: this example differs from example 1 in that the diameter of the cylindrical billet is noted Φ=230 mm, the height is noted h=300 mm, and the aspect ratio of the billet is 1.30, so k is 0.60.
Example 22: this example differs from example 1 in that the diameter of the cylindrical billet is noted Φ=200 mm, the height is noted h=410 mm, and the aspect ratio of the billet is 2.05, so k is 0.30.
Experimental example: 1. the molded parts obtained in examples 1 to 20 were subjected to surface microstructure comparison, room temperature and high temperature tensile strength and elongation test, respectively, and the test results were as follows:
1. surface properties were explored:
comparative example 1: the ring rolling method of the step S3 is adopted for ring rolling for 1 time, the ring rolling steps in the step S4 and the step S5 are not carried out, and the rest of the treatment is the same as that of the embodiment 1;
comparative example 2: the ring rolling method of the step S3 is adopted for ring rolling for 3 times, the ring rolling steps in the step S4 and the step S5 are not carried out, and the rest of the treatment is the same as that of the embodiment 1;
comparing example 1 with comparative examples 1 and 2, it was found that example 1 had better surface properties, no cracking occurred, good uniformity of surface texture, comparative example 1 had worse surface texture, cracking occurred, slight cracking occurred in comparative example 2, and uniformity was inferior to that of example 1.
2. The influence of k value change on the mechanical property of a formed part is explored:
comparative example 3: in step S2, k is 0.6, and the rest of the process is the same as in example 1;
example 1, example 21 and example 22 were taken for comparison with comparative example 3, as shown in table 1;
TABLE 1 influence of k value changes on mechanical properties of molded parts
By means of table 1, the mechanical properties of the molded part of example 1 are better, and the mechanical properties of the molded part of comparative example 3 are poorer than those of example 1, probably because the process of forming the punching inner diameter by the punch is related to the height-diameter ratio of the blank, and by adopting the mode of example 1, the damage to the interior of the blank material in the punching process can be avoided, so that the mechanical properties of the material are better;
it can be seen from comparison of examples 1, 21 and 22 that the set height-to-diameter ratio of the blanks is different, but the mechanical properties of the materials can be ensured by limiting the k value, so that the mechanical properties of the finished products are less influenced by the sizes of the blanks.
3. The influence of different parameters on the mechanical properties of the formed part is explored;
comparing the embodiment 1 with the embodiment 4-13, as shown in Table 2;
TABLE 2 influence of different parameters on the mechanical properties of molded parts
By table 2, comparing example 1, example 4 and example 5, it can be found that the temperature parameter affects the mechanical properties of the molded part, wherein example 1 is better, the temperature setting and the change of each step in example 1 promote the secondary alpha phase change process in TA12A, so that the effect of uniform alpha phase distribution can be realized without increasing the temperature, and the mechanical properties of the material are further improved;
comparing the embodiment 1, the embodiment 6 and the embodiment 7, it can be found that the deformation setting has an influence on the mechanical properties of the molded part, wherein the embodiment 1 is better, and the internal tissue properties of the material can be better by setting different deformation in different steps;
comparing the embodiment 1, the embodiment 8 and the embodiment 9, it can be found that the setting of the heat preservation time has an influence on the mechanical property of the formed part, wherein the embodiment 1 is better, and the heat preservation time can lead the forming property of the material to be better;
as can be seen from comparison of examples 1, 12 and 13, the difference in air cooling parameters has a slight effect on the mechanical properties of the molded article, with example 1 being preferred.
4. The influence of the heat-insulating coating on the mechanical properties of the formed part is explored;
comparative example 4: the step S1-3 is as follows: directly spraying the coating obtained in the step S1-2 on the surface of a blank;
comparing examples 14-16 with comparative example 4 of example 1, as shown in Table 3;
TABLE 3 influence of thermal-insulation coating on mechanical properties of molded parts
From table 3, comparative examples 1 and 14, it can be found that the mechanical properties of the molded articles obtained from the heat-insulating coating used in example 14 are superior; and by microscopic observation of the surfaces of the two, it can be found that the surface structure of example 14 is uniform and more compact than that of example 1; thus, example 14 is preferred;
microscopic examination of the surfaces of comparative example 14 and comparative example 4 revealed that the tissue of example 14 was more excellent;
comparing examples 14, 15 and 16, it was found that the raw material composition and the spray thickness of the heat-insulating paint of example 14 were preferable.
Claims (8)
1. The molding method of the grinding ring of the aero-engine material TA12A is characterized by comprising the following steps of:
s1, preheating preparation:
firstly, taking a cylindrical blank with a material TA12A, spraying heat-insulating paint on the surface of the blank, and heating at a temperature T β -30 ℃ to T β Heating the blank in a furnace at 50 ℃ below zero for 200min, taking out, wrapping heat preservation cotton on the outer circle of the blank, returning to the furnace, continuously heating for 25min, and discharging; wherein the diameter of the cylindrical blank is marked as phi, and the height is marked as H and T β The phase transition point temperature of the blank;
s2, upsetting and punching:
upsetting the blank after discharging to a height of 0.45H-0.47H at a temperature of 850-950 ℃, punching the blank by using a punch, wherein the thickness of a punched bottom plate is 0.05H-0.15H, and the punching adopts a mode of alternately front punching and back punching, so that the blank is rounded with the punch; controlling the deformation to 31-33%; then air cooling is carried out to room temperature, and the air cooling is carried out to room temperature by adopting the air flow rate of 15-17 m/s; obtaining a forging;
the height of the punch head for front punching is the same as the height of the blank after upsetting, and the height of the punch head for back punching is 1/3 of the height of the blank after upsetting;
s3, ring rolling 1 fire:
at a temperature of T β -25 ℃ to T β Heating and preserving heat of the forging for 100-120 min at-45 ℃, performing primary ring rolling, then returning to a furnace and preserving heat for 55-65 min, performing secondary ring rolling, and controlling the deformation of the primary ring rolling to be 27-29%; air cooling to room temperature after forging; cooling to room temperature by adopting air flow rate of 18-20 m/s after forging;
s4, ring rolling 2 fires:
at a temperature of T β -20 ℃ to T β Heating and preserving heat of the forging at the temperature of minus 30 ℃ for 75-100 min, performing primary ring rolling, then returning to the furnace and preserving heat for 40-55 min, performing secondary ring rolling, and controlling the deformation of the ring rolling to 33-35%; air cooling to room temperature after forging; air cooling after forging is carried out by adopting the air flow rate of 14-16 m/s to cool to room temperature;
s5, ring rolling for 3 fires:
at a temperature of T β -25 ℃ to T β Heating and preserving heat of the forging at the temperature of-45 ℃ for 50-75 min, carrying out primary ring rolling, then returning to a furnace and preserving heat for 30-45 min, carrying out secondary ring rolling, carrying out ring rolling to the required size, and controlling the deformation of the ring rolling to 35-37%; and (3) cooling the forging product to room temperature by air cooling, cooling the forging product to room temperature by natural air, and finally performing post-treatment to obtain the formed part.
2. The method for forming the ring of the aeroengine material TA12A according to claim 1, wherein in the step S3 ring rolling 1 fire and the step S4 ring rolling 2 fire, the ring rolling adopts a horizontal ring rolling machine to roll the ring, and a 2000t oil pressure machine is adopted to roll the flat end face; and S5, ring rolling in 3-fire ring rolling adopts a vertical ring rolling machine to roll rings.
3. The method for forming a ring rolling of an aircraft engine material TA12A according to claim 1, wherein in step S5, the post-processing is as follows: placing the forge piece into a warm charging furnace for heating, wherein the temperature in Wen Zhuanglu is 830-870 ℃, and preserving heat for 10-15 min; a molded article was obtained.
4. The method for forming a ring by grinding an aeroengine material TA12A according to claim 1, wherein in the step S2, the forging is upset and punched to 0.42H-0.43H, and the inner diameter of the forging obtained by punching is controlled to be k multiplied by phi, wherein k is a proportionality coefficient, and the value range is 0.10-0.80.
5. The method for forming the ring rolling of the aircraft engine material TA12A according to claim 1, wherein in the step S1, the thickness of the thermal insulation coating sprayed on the surface of the blank is 40-50 μm.
6. The molding method of the aeroengine material TA12A rolling ring of claim 5, wherein the heat preservation coating comprises the following raw materials in parts by mass: 10-20 parts of tetraboro powder, 10-15 parts of vermiculite powder, 10-15 parts of silicon micropowder, 10-20 parts of liquid lithium silicate, 15-20 parts of organic silicon water-based resin and 10-15 parts of water-based epoxy resin.
7. The method for forming the grinding ring of the aeroengine material TA12A as claimed in claim 6, wherein the preparation and spraying methods of the heat preservation coating are as follows:
s1-1, mixing and stirring tetraborium nitride powder and liquid lithium silicate for 20-25 min at the temperature of 15-25 ℃ to obtain a first mixture; performing ultrasonic dispersion on the vermiculite powder and the organic silicon water-based resin for 5-7 min at 33-35 kHz at the temperature of 55-60 ℃ to obtain a second mixture; at the temperature of 75-80 ℃, the silicon micropowder and the water-based epoxy resin are homogenized and dispersed into a third mixture by adopting high-pressure homogenizing equipment under the pressure of 10-15 MPa;
s1-2, respectively taking one half of the first mixture, the second mixture and the third mixture at room temperature, and then stirring and mixing to obtain the coating;
s1-3, according to the spraying sequence of the third mixture, the second mixture and the first mixture, sequentially spraying the rest half of the third mixture, the second mixture and the first mixture on the surface of the blank until the thickness of the coating is 20-30 mu m, and then spraying the coating until the thickness of the coating is 40-60 mu m.
8. The method for forming the grinding ring of the aero-engine material TA12A according to claim 1, wherein blanks with the specification of 1.04 phi-1.05 phi and 1.13H-1.14H are taken as heightening pieces, and the heightening pieces are subjected to the treatment of steps S1-S5.
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