CN117187603A - Preparation method of high-temperature titanium alloy forging for aerospace structural part - Google Patents
Preparation method of high-temperature titanium alloy forging for aerospace structural part Download PDFInfo
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- CN117187603A CN117187603A CN202311131843.0A CN202311131843A CN117187603A CN 117187603 A CN117187603 A CN 117187603A CN 202311131843 A CN202311131843 A CN 202311131843A CN 117187603 A CN117187603 A CN 117187603A
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- 238000005242 forging Methods 0.000 title claims abstract description 92
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 33
- 238000002360 preparation method Methods 0.000 title claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims abstract description 48
- 239000000956 alloy Substances 0.000 claims abstract description 19
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 17
- 238000000034 method Methods 0.000 claims abstract description 12
- 238000003723 Smelting Methods 0.000 claims abstract description 11
- 230000007704 transition Effects 0.000 claims description 17
- 238000005070 sampling Methods 0.000 claims description 15
- 230000007547 defect Effects 0.000 claims description 13
- 238000001816 cooling Methods 0.000 claims description 12
- 238000001514 detection method Methods 0.000 claims description 11
- 238000007689 inspection Methods 0.000 claims description 11
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 claims description 10
- 230000032683 aging Effects 0.000 claims description 8
- 238000005520 cutting process Methods 0.000 claims description 8
- 238000010304 firing Methods 0.000 claims description 8
- 239000000243 solution Substances 0.000 claims description 8
- 239000000126 substance Substances 0.000 claims description 7
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 5
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 5
- 238000005266 casting Methods 0.000 claims description 5
- 239000004615 ingredient Substances 0.000 claims description 5
- 238000002844 melting Methods 0.000 claims description 5
- 230000008018 melting Effects 0.000 claims description 5
- 239000004408 titanium dioxide Substances 0.000 claims description 5
- 229910052726 zirconium Inorganic materials 0.000 claims description 5
- 238000005057 refrigeration Methods 0.000 claims description 4
- 239000006104 solid solution Substances 0.000 claims description 3
- 230000035882 stress Effects 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 claims 5
- 238000007599 discharging Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 239000002994 raw material Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910052761 rare earth metal Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 238000005563 spheronization Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Abstract
The invention belongs to the technical field of titanium alloy material processing, and relates to a preparation method of a high-temperature titanium alloy forging for a space structure. According to the invention, by adding the conventional Al, si, mo, zr element (adopting common alloy elements with low cost), the gap element in the alloy is improved; the titanium alloy forging which can be applied to 650 ℃ at the highest is obtained through the combined process of vacuum consumable arc furnace smelting, free forging, die forging and heat treatment, the tensile strength of the forging can reach 530MPa at 650 ℃, and the residual deformation is less than or equal to 2% under the stress of 300MPa at the temperature.
Description
Technical Field
The invention belongs to the technical field of titanium alloy material processing, and relates to a preparation method of a high-temperature titanium alloy forging for a space structure.
Background
As the working speed of the spacecraft is faster and faster, the requirement on the service temperature of the whole structural member is correspondingly higher and higher, and meanwhile, the weight reduction requirement is met, and the weight of the spacecraft cannot meet the requirement although the traditional high-temperature alloy can meet the temperature requirement. Therefore, titanium alloys are most desirable, but conventional titanium alloys are typically used at temperatures up to about 500 ℃.
At present, some titanium alloys suitable for being used at about 600 ℃ are developed at home, but a small amount of rare earth elements W, nb and the like are generally adopted, and are easy to form inclusion, segregation and the like in the smelting process due to higher melting point, so that higher requirements are put on the preparation process of the alloy in order to obtain materials with uniform components. Meanwhile, as more rare earth elements are added, the cost of the material is increased.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a preparation method of a high-temperature titanium alloy forging for a space structural member.
In order to achieve the above purpose, the present invention provides the following technical solutions:
according to the preparation method of the high-temperature titanium alloy forging for the aerospace structural member, the titanium alloy forging which can be suitable for the temperature below 650 ℃ is obtained through the combined process of vacuum consumable arc furnace smelting, free forging, die forging and heat treatment.
Further, the tensile strength of the titanium alloy forging can reach 530MPa at the temperature of 650 ℃.
Further, the residual deformation of the titanium alloy forging piece at the temperature of 650 ℃ and the stress of 300MPa is less than or equal to 2 percent.
Further, the method specifically comprises the following steps:
s1, firstly, selecting ingot casting ingredients; then adopting three times of vacuum consumable arc melting to obtain cast ingots with uniform components and no metallurgical defects; finally, processing and sampling the cast ingot to finish the detection of the chemical components of the cast ingot;
s2, cogging an ingot: heating the cast ingot to a temperature of 100-200 ℃ above the beta phase transition temperature, and cogging, wherein the total deformation of the blank after cogging forging is more than or equal to 80%;
s3, forging with intermediate firing time I: heating the blank to 10-40 ℃ below the beta phase transition temperature to forge for 2-4 times, wherein the single-time deformation is more than or equal to 50%;
s4, forging the beta forging: heating the blank to 20 ℃ above the beta phase transition temperature to perform 1-time forging, wherein the deformation of the heat is more than or equal to 80%;
s5, forging II in middle fire: heating the blank to 20-40 ℃ below the beta phase transition temperature to forge for 2-4 times, wherein the single-time deformation is more than or equal to 50%;
s6, heating the blank to 20-40 ℃ below the beta phase transition temperature, and forming to the required specification;
s7, blanking to a required size according to the requirements of the forging, and polishing the blank;
s8, performing ultrasonic inspection on the blank;
s9, heating the blank to 20-40 ℃ below the beta phase transition temperature, and forging the blank in a corresponding die to the size of a forging piece;
s10, carrying out solid solution and aging treatment on the forging, and completing preparation of the high-temperature titanium alloy forging.
Further, the S1 specifically includes:
s1.1, selecting titanium sponge, alMo intermediate alloy, tiSi intermediate alloy, zirconium sponge and titanium dioxide, and proportioning according to the following component ranges;
| element(s) | Al | Si | Mo | Zr | O |
| Content range | 6.2～8 | 0.4～0.6 | 3.2～5.0 | 1.5～3.5 | 0.18～0.25 |
S1.2, adopting three times of vacuum consumable arc melting to obtain an ingot with uniform components and no metallurgical defects;
s1.3, cutting off a riser of the ingot after processing and removing the surface defects of the ingot;
s1.4, sampling respectively at the head part, the middle part and the tail part of the ingot, and detecting the chemical components of the ingot.
Further, in the step S10,
the technological parameters of the solution treatment are as follows: preserving heat for 60-150 min at the temperature of 50-80 ℃ below the beta phase transition temperature, and adopting oil cooling or water cooling in a refrigeration mode;
the technological parameters of the aging treatment are as follows: preserving heat for 240-480 min at 500-600 deg.C, and adopting air cooling in refrigeration mode.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:
according to the invention, by adding conventional Al, si, mo, zr element (adopting common alloy element with lower cost), the gap element in the alloy is improved, and the titanium alloy forging which can be suitable for 650 ℃ at the highest is obtained through the combined process of vacuum consumable arc furnace smelting, free forging, die forging and heat treatment, the tensile strength of the forging at 650 ℃ can reach 530MPa, and meanwhile, the residual deformation is less than or equal to 2% under the stress of 300MPa at the temperature.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate principles of the invention and together with the description, serve to explain the principles of the invention.
In order to more clearly illustrate the embodiments of the invention or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, and it will be obvious to a person skilled in the art that other drawings can be obtained from these drawings without inventive effort.
Fig. 1 is a schematic structural diagram of a high-temperature titanium alloy forging for aerospace structural members provided in embodiment 1 of the invention.
Detailed Description
Reference will now be made in detail to exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, the same numbers in different drawings refer to the same or similar elements, unless otherwise indicated. The implementations described in the following exemplary examples do not represent all implementations consistent with the invention. Rather, they are merely examples of methods consistent with aspects of the invention that are set forth in the following claims.
For better understanding of the technical solution of the present invention by those skilled in the art, the present invention will be described in further detail with reference to the accompanying drawings and examples, wherein "ζ" represents a square billet;
example 1
Referring to fig. 1, the embodiment provides a method for preparing a high-temperature titanium alloy forging for a space structural member, which specifically comprises the following steps:
1) Ingot casting ingredients
Selecting raw materials such as titanium sponge, alMo intermediate alloy, tiSi intermediate alloy, zirconium sponge, titanium dioxide and the like, and proportioning according to the following component ranges;
2) Ingot smelting
The ingot is smelted in three times of vacuum consumable smelting to obtain phi 450mm ingot with uniform components and no metallurgical defects;
3) Ingot processing and sampling
After the surface defects of the ingot are processed and removed, cutting off a riser of the ingot, and sampling at the head part, the middle part and the tail part of the ingot respectively;
4) Ingot chemical composition inspection
| Sampling position | Al | Si | Mo | Zr | O |
| Head part | 6.05 | 0.35 | 3.11 | 1.45 | 0.185 |
| Middle part | 6.08 | 0.37 | 3.05 | 1.56 | 0.180 |
| Tail part | 5.97 | 0.32 | 3.14 | 1.40 | 0.185 |
5) Cogging an ingot, wherein the phase transition point of the ingot is 1020 DEG C
First heat: heating the cast ingot to 1150 ℃ for cogging, and cogging, forging and deforming to be:
the total deformation is 110%;
6) Forging I with intermediate firing time
Second heat time: heating the blank to 1010 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
third heat time: heating the blank to 980 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
7) Beta forging-to-forging
Fourth heat time: heating the blank to 1040 ℃, ≡400 heading →≡500 heading →≡400 deformation 144% by single fire;
8) Forging II with intermediate firing
Fifth heat time: heating the blank to 1010 ℃, and carrying out the steps of ≡400 upsetting ≡500 drawing ≡400 and 72% of single-fire deformation;
sixth heat time: heating the blank to 980 ℃, and carrying out the steps of ≡400 upsetting ≡500 drawing ≡250 and 111% of single-fire deformation;
9) Blank forming
Seventh heat: heating the blank to 980 ℃, +.250 spheronization phi 250;
10 Blank processing
Feeding and discharging blanks with the length of 350mm on phi 250 blanks, and processing the blanks to phi 240 multiplied by 340;
11 Inspection of blanks
Ultrasonic inspection is carried out on the blank according to the A-level requirement in GB/T5193-2007;
12 Forging of forgings
Heating the blank to 980 ℃, and placing the blank into a die to forge the size of the branch forging piece;
13 Heat treatment of forgings
Solution treatment: preserving heat at 940 ℃ for 60min, and cooling with oil;
aging treatment: preserving heat at 500 ℃ for 240min, and air cooling;
14 Forging processing
Machining the forging to the required size;
15 Mechanical property detection, namely cutting a sample at a specified sampling position of the forging to perform mechanical property detection, wherein the detection result is shown in the following table 1:
example 2
The embodiment provides a preparation method of a high-temperature titanium alloy forging for a space structural member, which specifically comprises the following steps:
1) Ingot casting ingredients
Selecting raw materials such as titanium sponge, alMo intermediate alloy, tiSi intermediate alloy, zirconium sponge, titanium dioxide and the like, and proportioning according to the following component ranges;
| element(s) | Al | Si | Mo | Zr | O |
| Content range | 8.0 | 0.6 | 5.0 | 3.5 | 0.205 |
2) Ingot smelting
The ingot is smelted in three times of vacuum consumable smelting to obtain phi 450mm ingot with uniform components and no metallurgical defects;
3) Ingot processing and sampling
After the surface defects of the ingot are processed and removed, cutting off a riser of the ingot, and sampling at the head part, the middle part and the tail part of the ingot respectively;
4) Ingot chemical composition inspection
5) Cogging an ingot, wherein the phase transition point of the ingot is 1045 ℃;
first heat: heating the cast ingot to 1200 ℃ for cogging, and cogging, forging and deforming to obtain the following components: phi 450 heading-phi 500 drawing- ≡400 heading- ≡500 drawing- ≡400, and the total deformation is 110%;
6) Forging I with intermediate firing time
Second heat time: heating the blank to 1035 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
third heat time: heating the blank to 1005 ℃, and carrying out ≡400 upsetting ≡500 drawing ≡400, wherein the single-fire deformation amount is 72%;
7) Beta forging-to-forging
Fourth heat time: heating the blank to 1065 ℃, wherein the deformation amount of single fire is 144%;
8) Forging II with intermediate firing
Fifth heat time: heating the blank to 1035 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
sixth heat time: heating the blank to 1005 ℃, and carrying out ≡400 upsetting ≡500 drawing ≡250, wherein the single-fire deformation amount is 111%;
9) Blank forming
Seventh heat: heating the blank to 1005 ℃, ∈250 round-off phi 250;
10 Blank processing
Blank with feeding and discharging length of 350mm is processed to phi 240 multiplied by 340;
11 Inspection of blanks
Ultrasonic inspection is carried out on the blank according to the A-level requirement in GB/T5193-2007;
12 Forging of forgings
Heating the blank to 1005 ℃, and placing the blank into a die to forge the size of the branch forging piece;
13 Heat treatment of forgings
Solution treatment: preserving heat at 995 ℃ for 60min, and water-cooling;
aging treatment: preserving heat at 500 ℃ for 240min, and air cooling;
14 Forging processing
Machining the forging to the required size;
15 Mechanical property detection, namely cutting a sample at a specified sampling position of the forging to perform mechanical property detection, wherein the detection result is shown in the following table 2:
example 3
The embodiment provides a preparation method of a high-temperature titanium alloy forging for a space structural member, which specifically comprises the following steps:
1) Ingot casting ingredients
Selecting raw materials such as titanium sponge, alMo intermediate alloy, tiSi intermediate alloy, zirconium sponge, titanium dioxide and the like, and proportioning according to the following component ranges;
| element(s) | Al | Si | Mo | Zr | O |
| Content range | 7.5 | 0.5 | 4.0 | 2.5 | 0.18 |
2) Ingot smelting
The ingot is smelted in three times of vacuum consumable smelting to obtain phi 450mm ingot with uniform components and no metallurgical defects;
3) Ingot processing and sampling
After the surface defects of the ingot are processed and removed, cutting off a riser of the ingot, and sampling at the head part, the middle part and the tail part of the ingot respectively;
4) Ingot chemical composition inspection
| Sampling position | Al | Si | Mo | Zr | O |
| Head part | 7.44 | 0.44 | 3.92 | 2.51 | 0.210 |
| Middle part | 7.30 | 0.40 | 3.88 | 2.44 | 0.200 |
| Tail part | 7.49 | 0.49 | 3.94 | 2.46 | 0.205 |
5) Cogging an ingot, wherein the phase transition point of the ingot is 1045 ℃;
first heat: heating the cast ingot to 1150 ℃ for cogging, and cogging, forging and deforming to be: phi 450 heading-phi 500 drawing- ≡400 heading- ≡500 drawing- ≡400, and the total deformation is 110%;
6) Forging I with intermediate firing time
Second heat time: heating the blank to 1035 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
third heat time: heating the blank to 1025 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
fourth heat time: heating the blank to 1015 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
fifth heat time: heating the blank to 1005 ℃, and carrying out ≡400 upsetting ≡500 drawing ≡400, wherein the single-fire deformation amount is 72%;
7) Beta forging-to-forging
Sixth heat time: heating the blank to 1065 ℃, wherein the deformation amount of single fire is 144%;
8) Forging II with intermediate firing
Seventh heat: heating the blank to 1035 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
eighth heat time: heating the blank to 1005 ℃, and carrying out ≡400 upsetting ≡500 drawing ≡250, wherein the single-fire deformation amount is 111%;
ninth fire: heating the blank to 1035 ℃, wherein the deformation amount of the blank is 72% in single fire, and the blank is in the range of ≡400 to ≡500 to ≡400;
tenth fire: heating the blank to 1005 ℃, and carrying out ≡400 upsetting ≡500 drawing ≡250, wherein the single-fire deformation amount is 111%;
9) Blank forming
Eleventh heat: heating the blank to 1005 ℃, ∈250 round-off phi 250;
10 Blank processing
Feeding and discharging a blank with the diameter of 250 mm to a blank with the diameter of 350mm, and processing the blank to the diameter of 240 multiplied by 340;
11 Inspection of blanks
Ultrasonic inspection is carried out on the blank according to the A-level requirement in GB/T5193-2007;
12 Forging of forgings
Heating the blank to 1005 ℃, and placing the blank into a die to forge the size of the branch forging piece.
13 Heat treatment of forgings
Solution treatment: preserving heat at 990 ℃ for 60min, and cooling with water;
aging treatment: preserving heat at 600 ℃ for 240min, and air cooling;
14 Forging processing
Machining the forging to the required size;
15 Mechanical property detection, namely cutting a sample at a specified sampling position of the forging to perform mechanical property detection, wherein the detection result is shown in the following table 3:
in summary, the preparation method of the high-temperature titanium alloy forging for the aerospace structural part provided by the invention adopts common alloy elements with low cost, and the high-temperature titanium alloy forging which can be used at 650 ℃ at most is prepared by different ratios of the elements, a high-low-high-low forging mode and a solid solution aging heat treatment mode.
The foregoing is only a specific embodiment of the invention to enable those skilled in the art to understand or practice the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention.
It will be understood that the invention is not limited to what has been described above and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.
Claims (6)
1. A preparation method of a high-temperature titanium alloy forging for a space structural member is characterized in that the titanium alloy forging which can be suitable for below 650 ℃ is obtained through a combined process of vacuum consumable arc furnace smelting, free forging, die forging and heat treatment.
2. The method for producing a high temperature titanium alloy forging for aerospace structural members of claim 1, wherein the titanium alloy forging has a tensile strength of up to 530MPa at a temperature of 650 ℃.
3. The method for manufacturing a high temperature titanium alloy forging for a aerospace structural member according to claim 1, wherein the titanium alloy forging has a residual deformation of 2% or less at a temperature of 650 ℃ and a stress of 300 MPa.
4. The method for manufacturing a high-temperature titanium alloy forging for a aerospace structural member according to claim 1, which is characterized by comprising the following steps:
s1, firstly, selecting ingot casting ingredients; then adopting three times of vacuum consumable arc melting to obtain cast ingots with uniform components and no metallurgical defects; finally, processing and sampling the cast ingot to finish the detection of the chemical components of the cast ingot;
s2, cogging an ingot: heating the cast ingot to a temperature of 100-200 ℃ above the beta phase transition temperature, and cogging, wherein the total deformation of the blank after cogging forging is more than or equal to 80%;
s3, forging with intermediate firing time I: heating the blank to 10-40 ℃ below the beta phase transition temperature to forge for 2-4 times, wherein the single-time deformation is more than or equal to 50%;
s4, forging the beta forging: heating the blank to 20 ℃ above the beta phase transition temperature to perform 1-time forging, wherein the deformation of the heat is more than or equal to 80%;
s5, forging II in middle fire: heating the blank to 20-40 ℃ below the beta phase transition temperature to forge for 2-4 times, wherein the single-time deformation is more than or equal to 50%;
s6, heating the blank to 20-40 ℃ below the beta phase transition temperature, and forming to the required specification;
s7, blanking to a required size according to the requirements of the forging, and polishing the blank;
s8, performing ultrasonic inspection on the blank;
s9, heating the blank to 20-40 ℃ below the beta phase transition temperature, and forging the blank in a corresponding die to the size of a forging piece;
s10, carrying out solid solution and aging treatment on the forging, and completing preparation of the high-temperature titanium alloy forging.
5. The method for manufacturing a high-temperature titanium alloy forging for aerospace structural members according to claim 4, wherein the step S1 specifically comprises:
s1.1, selecting titanium sponge, alMo intermediate alloy, tiSi intermediate alloy, zirconium sponge and titanium dioxide, and proportioning according to the following component ranges;
S1.2, adopting three times of vacuum consumable arc melting to obtain an ingot with uniform components and no metallurgical defects;
s1.3, cutting off a riser of the ingot after processing and removing the surface defects of the ingot;
s1.4, sampling respectively at the head part, the middle part and the tail part of the ingot, and detecting the chemical components of the ingot.
6. The method for manufacturing a high-temperature titanium alloy forging for a aerospace structural member according to claim 4, wherein in S10,
the technological parameters of the solution treatment are as follows: preserving heat for 60-150 min at the temperature of 50-80 ℃ below the beta phase transition temperature, and adopting oil cooling or water cooling in a refrigeration mode;
the technological parameters of the aging treatment are as follows: preserving heat for 240-480 min at 500-600 deg.C, and adopting air cooling in refrigeration mode.
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