CN112935056B - Spinning solution treatment composite forming method for nickel-based high-temperature alloy cylinder with bottom - Google Patents
Spinning solution treatment composite forming method for nickel-based high-temperature alloy cylinder with bottom Download PDFInfo
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- CN112935056B CN112935056B CN202110213521.5A CN202110213521A CN112935056B CN 112935056 B CN112935056 B CN 112935056B CN 202110213521 A CN202110213521 A CN 202110213521A CN 112935056 B CN112935056 B CN 112935056B
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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
- B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
- B21D22/14—Spinning
- B21D22/16—Spinning over shaping mandrels or formers
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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
- B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
- B21D22/20—Deep-drawing
- B21D22/30—Deep-drawing to finish articles formed by deep-drawing
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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
Abstract
The invention discloses a spinning solution treatment composite forming method of a nickel-based superalloy tubular piece with a bottom, which comprises the following steps: prefabricating a circular plate blank with a corresponding size according to the wall thickness, the diameter and the machining allowance of the component and the law of constant volume; reversely deducing the diameter and the thickness of the round blank according to the volume invariance principle and the thinning rate during flow spinning; determining the times of solid solution treatment in the drawing spinning process; performing multi-pass deep drawing spinning by adopting a single spinning wheel and a forward and backward spinning track; when the middle prefabricated round plate blank is drawn and spun, the material is removed from work hardening and the plasticity is recovered by adopting vacuum solid solution heat treatment. The invention can realize the room temperature forming of the nickel-based high-temperature alloy component difficult to deform, does not need heating in the forming process, only needs one core die in the forming process, and can greatly improve the production efficiency, improve the surface quality of parts and reduce the manufacturing cost.
Description
Technical Field
The invention relates to the field of plastic forming of metal materials, in particular to a spinning solution treatment composite forming method of a nickel-based high-temperature alloy cylinder with a bottom.
Background
The nickel-based high-temperature alloy is a metal material which takes nickel as a matrix and can work for a long time at a high temperature of more than 600 ℃ under the action of certain stress. The high-strength high-corrosion-resistance high-strength steel has the advantages of high strength, good oxidation resistance and corrosion resistance, and is widely applied to the high-end technical fields of aviation, aerospace, chemical engineering, ships and the like. The combustion chamber of an aircraft engine and a gas turbine contains a large number of nickel-based high-temperature alloy (Haynes 230) shell components, so parts need to be used in severe environments such as high temperature, high pressure and the like, and the combustion chamber has the characteristics of thin wall thickness, high precision, high performance requirements and the like. However, the nickel-based superalloy has serious forming work hardening (work hardening index is 0.78) at room temperature and serious rebound, so that the parts have high forming difficulty and are restricted in production.
Such parts need to be assembled with other parts, the surface precision and the dimensional precision of the parts need to be high, the work hardening can be eliminated by hot forming, but the surface oxidation is inevitably generated during hot forming, so the surface quality of the parts is seriously reduced. At present, the composite material is generally prepared by adopting a process of multi-pass stamping and drawing forming and solution treatment. Due to the particularity of the nickel-based high-temperature alloy material and the limitation of the drawing forming process, the formed product has the phenomena of wall thickness reduction and uneven wall thickness in different degrees, the limit dimensional tolerance (the diameter of the cylinder part, the angle of the conical surface, the wall thickness and the like) obtained by drawing forming is difficult to guarantee, multiple times of drawing needs multiple molds, and the production cost is high.
In the actual production process, on one hand, the requirements of the surface quality and the forming precision of the material need to be met; on the other hand, the production process needs to be simplified as much as possible, the production efficiency needs to be improved, and the production cost needs to be reduced, so that the industrial production is facilitated; for the hot forming of the nickel-based alloy, the control difficulty of the heating mode and the forming quality is higher; however, the wall thickness uniformity cannot be ensured by drawing.
Disclosure of Invention
In order to overcome the limitation of low forming precision of the nickel-based superalloy component prepared by the prior art, the invention provides a composite forming method of spinning solution treatment of a cylinder-shaped piece with a bottom made of a nickel-based superalloy; the method can prepare the nickel-based high-temperature alloy component with higher precision and excellent mechanical property, and can save special heating equipment during hot forming, thereby achieving the purposes of improving the production efficiency and reducing the manufacturing cost.
The invention is realized by the following technical scheme:
a spinning solution treatment composite forming method for a nickel-based superalloy tubular piece with a bottom comprises the following steps:
the method comprises the following steps: prefabricating a circular plate blank with a corresponding size according to the wall thickness, the diameter and the machining allowance of the component and the law of unchanged volume; the round sheet blank is (hard to deform) nickel-based high-temperature alloy, and the diameter and the thickness of the round blank are reversely deduced according to the trimming allowance of 10-15mm and the size of a part according to the volume invariance principle and the thinning rate during flow spinning.
Step two: determining the times of solid solution treatment in the drawing and spinning process according to the limit drawing coefficient of the nickel-based superalloy during drawing and spinning;
step three: adopting a corresponding core mould and a spinning wheel for deep-drawing spinning, and adopting a single spinning wheel and a reciprocating spinning track to carry out multi-pass deep-drawing spinning;
step four: in the process of drawing and spinning the middle prefabricated round plate blank, the material work hardening is eliminated by adopting vacuum solid solution heat treatment, and the plasticity is recovered; in the vacuum solid solution heat treatment, in order to improve the temperature uniformity of the component during the solid solution treatment and prevent the growth of crystal grains, the temperature is firstly equalized at 600 ℃ and 800 ℃, and then the temperature is increased to 1190-1210 ℃ for solid solution; the time of temperature equalization and solution treatment is calculated according to the wall thickness of the round plate blank by the following formulas (1) to (3), and finally gas quenching cooling treatment is carried out (the cooling speed is 30-50 ℃/s);
τ1＝(25～30)+2t (1)
τ2＝(25～30)+1.5t (2)
τ3＝(18～20)+0.5t (3)
in the formula, tau 1, tau 2 and tau 3 are respectively time of primary temperature equalization, secondary temperature equalization and solution treatment, and t is blank wall thickness;
step five: drawing and spinning the prefabricated blank after the solution heat treatment again;
step six: repeating the third step and the fourth step; until the drawing and spinning are finished to form the cylindrical part.
Step seven: adopting a double-conical-surface spinning wheel to perform flow spinning shaping on the cylindrical part formed in the fourth step; the aim is that the cylindrical part obtained by drawing and spinning has the phenomenon of uneven wall thickness distribution, reduced middle wall thickness and thickened mouth part; the uniformity of the wall thickness is improved by flow spinning. Because the nickel-based superalloy is seriously processed and hardened and has serious resilience, the core die needs to adopt a certain inverted cone angle to compensate the resilience.
Step eight: cutting off the straight cylindrical opening part of the cylindrical part by 10-15mm to obtain a cylindrical component with a bottom; aiming at the phenomenon that the height of the mouth part is different after flowing spinning, the edge of the mouth part is trimmed by 10-15mm by using an edge trimming wheel.
In the vacuum solution heat treatment process in the step four, the heating speed is 20 ℃/min, the temperature is kept at 600 ℃ and 800 ℃ for 30min, and then the temperature is kept at 1200 ℃ for 20min.
In the first step, the round plate blank is made of (hard to deform) nickel-based high-temperature alloy, and the diameter and the thickness of the round plate blank are reversely deduced according to the volume invariance law and the thinning rate during flow spinning according to the trimming allowance of 10-15mm and the size of the part.
And in the second step, the limit spinning coefficient of the nickel-based superalloy during drawing spinning is about 0.75-0.78, and the number of times of intermediate solution treatment is calculated according to the limit spinning coefficient.
The multi-pass deep-drawing spinning in the third step is specifically as follows: a core mold with a diameter of 176mm, and a small diameter r ρ =10mm, large diameter r ρ ' =25mm composite profile spinning wheel, and spinning core mould with 3 degree back taper angle; and (3) performing multi-pass deep-drawing spinning by adopting a first pass of circular arc track with the elevation angle of 60 degrees and the feeding ratio of 2mm/r until the outer edge of the blank reaches the required diameter.
And sixthly, when the step 3 is repeated, the cylindrical part is formed by multi-pass deep drawing and spinning again, and the first-pass elevation angle is selected to be 30-40 degrees.
Compared with the prior art, the invention has the following advantages and effects:
1. the invention can realize the room temperature forming of the nickel-based high-temperature alloy component which is difficult to deform, does not need heating in the forming process, only needs a core mold in the forming process, and can greatly improve the production efficiency, improve the surface quality of parts and reduce the manufacturing cost;
2. the invention can effectively avoid the mouth flaring phenomenon caused by serious rebound caused by uneven wall thickness during drawing and serious work hardening of the nickel-based alloy during spinning and the surface oxidation caused by hot forming; the high-precision low-cost forming of the parts can be effectively realized.
3. The method for processing the cylindrical part with the bottom can greatly save materials and reduce the material cost.
Drawings
FIG. 1 is a schematic view of a nickel-based superalloy bottomed cylindrical component prepared by the method.
FIG. 2 is a schematic diagram of the present invention using multiple passes of conventional spin forming to form the part shown in FIG. 1.
FIG. 3 is a specification of the solution treatment of the present invention.
FIG. 4 is a microstructure view of a nickel-base superalloy spin piece after solution treatment.
FIG. 5 is a schematic representation of the present invention when flow-spinning is used to form the part shown in FIG. 1.
FIG. 6 is a schematic view of a trim wheel trimming the part of FIG. 1 in accordance with the present invention.
FIG. 7 shows a stepped cylindrical member made of a nickel-base superalloy difficult to deform according to the invention.
FIG. 8 is a schematic view of a small-end cylindrical section formed by multi-pass drawing and spinning in the process of manufacturing the part shown in FIG. 7 according to the present invention.
FIG. 9 is a schematic view of a large-end cylindrical section formed by multi-pass deep-drawing and spinning in the process of manufacturing the part shown in FIG. 7 according to the present invention.
FIG. 10 is a schematic view of flow-spinning profiling of the present invention in making the part shown in FIG. 7.
FIG. 11 is a schematic side view of the invention in the preparation of the part shown in FIG. 7.
FIG. 12 is a flow chart of the present invention for preparing a (hard to deform) nickel-base alloy tube with a bottom.
Reference numbers in the above figures: a composite profile spinning wheel 1; 2, tail fixation; drawing and spinning tracks 3; a main shaft 4; a double conical surface spinning wheel 11; a trimming wheel 12; a circular arc rotary wheel 13; the profile contour of the composite profile rotary wheel 1 is formed by connecting two arcs with different radiuses, namely a large arc and a small arc.
Detailed Description
The present invention will be described in further detail with reference to specific examples.
Example 1
The composite forming method for the spinning solution treatment of the nickel-based superalloy tubular piece with the bottom can be realized by the following steps:
1. FIG. 1 is a schematic diagram of a certain nickel-based superalloy with a bottom cylindrical part which is difficult to deform and made of Haynes230 alloy, wherein the wall thickness t =2.0mm and the outer diameter D of the part are required 0 =180mm, length 62mm. Adopting multi-pass deep drawing and spinning forming, selecting trimming allowance of 10mm according to the principle of volume invariance and theoretical analysis, and calculating a circular plate blankThe diameter of the material is D t ＝281mm。
2. Ultimate drawing coefficient (about m) according to Haynes230 alloy t = 0.76), the number of intermediate solution treatments, D, was calculated 1 ＝D t× m t ＝214mm；D 2 ＝D 1× m t =163mm < 180mm; therefore, two solid solution treatments are required.
3. Figure 2 is a schematic illustration of the construction shown in figure 1 for multiple pass conventional spin forming. Design core mold with diameter of 176mm, and small diameter r ρ =10mm, large diameter r ρ ' =25mm composite profile spinning wheel, and spinning mandrel with 3 ° back taper angle (as shown in fig. 3); and performing multi-pass deep-drawing spinning to the outer edge diameter of the blank to 214mm by adopting a first pass elevation angle of 60 degrees and a circular arc track with a feeding ratio of 2 mm/r.
4. As shown in FIG. 3, vacuum solution heat treatment is performed at a heating rate of 20 ℃/min, heat preservation is performed at 600 ℃ and 800 ℃ for 30min, then heating is performed to 1200 ℃ and heat preservation is performed for 20min for solution treatment, and then rapid cooling is performed by gas quenching. As shown in fig. 4, the microstructure after the solution treatment was refined into uniform and fine grains.
5. After the solution treatment, repeating the third step, performing multi-pass drawing and spinning again to form a cylindrical part, wherein the first-pass elevation angle is selected to be 40 degrees, and other process parameters and spinning wheel structure parameters are the same as those in the third step; and then repeating step four.
6. As shown in fig. 5, a spinning core mold with a 3 degree inverted cone angle is adopted, the reduction rate is 10%, the feed ratio is 0.6mm/r, a double-conical spinning wheel is adopted for flow spinning, and the spinning wheel feeds along the core mold bus; on one hand, the uniformity of the wall thickness is improved through flow spinning, and on the other hand, the flaring phenomenon of a deep-drawing spinning prefabricated blank is compensated by adopting an inverted cone-shaped core die.
7. As shown in fig. 6, the obtained mouth of the cylindrical spinning member is trimmed by using a trimming rotary wheel, and the height of the part is ensured to be 62mm. The spinning step is formed at room temperature, and the heat treatment adopts vacuum solution treatment without surface oxidation, so that good surface quality can be obtained. Thus, the Haynes230 alloy cylindrical part with the bottom meeting the precision requirement can be obtained.
Example 2:
s1, FIG. 7 shows a stepped cylindrical component made of a nickel-base superalloy difficult to deform, and the stepped cylindrical component is required to have a wall thickness t =2.5mm, a small-end cylindrical part with a diameter of 50mm and a length of 20mm; the large-end cylindrical part has a diameter of 100mm and a length of 50mm. According to the shape and size of the part, after multi-pass deep-drawing spinning forming is adopted, the large-end cylindrical part is subjected to flow spinning shaping. According to the principle of unchanged volume, 10mm trimming margin is reserved, a 3mm plate blank is adopted, and the diameter of the circular plate is calculated to be 170mm.
S2, according to Haynes230 alloy ultimate drawing coefficient (about m) t = 0.75), the number of intermediate solution treatments, D) was calculated 1 ＝D t× m t ＝130mm；D 2 ＝D 1× m t =98.8mm < 100mm; therefore, two solid solution treatments are required.
S3, as shown in FIG. 8, the small-end cylindrical portion is formed by multi-pass drawing and spinning using a circular arc spinning roller, and since the flange is large when forming the portion, the wall thickness is reduced relatively largely, and finally the spinning roller is fed along the surface of the core mold with a clearance of 2.5mm (clearance between the spinning roller and the core mold) to perform shaping.
S4, as shown in the figure 9, a composite profile spinning wheel is adopted to carry out multi-pass drawing spinning forming, the elevation angle of the first pass is 60 degrees, and the feeding ratio is 2mm/r; spinning until the diameter of the outer edge of the blank reaches about 130 mm.
S5, as shown in figure 3, carrying out vacuum solution heat treatment on the blank after drawing and spinning at a heating speed of 20 ℃/min, carrying out heat preservation at 600 ℃ and 800 ℃ for 30min, then heating to 1200 ℃ and carrying out heat preservation for 20min for carrying out solution treatment, and then carrying out rapid cooling by adopting gas quenching.
S6, repeating the step S4, and performing drawing and spinning forming by adopting a first-pass elevation angle of 40 degrees to form a cylindrical part by spinning; subsequently, step S5 is repeated to perform solution treatment.
S7, as shown in figure 10, adopting a core mould for flow spinning with a 3-degree inverted cone angle, adopting a double-conical spinning wheel to symmetrically arrange, wherein the thinning rate is 17 percent, the feeding ratio is 0.6mm/r, performing flow spinning, and feeding the spinning wheel along a core mould generating line.
And S8, as shown in the figure 11, trimming the mouth part of the obtained cylindrical spinning piece by using a trimming rotating wheel to ensure that the height of the part is 62mm. The spinning step is formed at room temperature, and the heat treatment adopts vacuum solution treatment without surface oxidation, so that good surface quality can be obtained. Thus, the Haynes230 alloy cylindrical part with the bottom meeting the precision requirement can be obtained.
The general flow of the spin-solution treatment of the nickel-base alloy component is shown in fig. 12.
As described above, the present invention can be preferably realized.
The embodiments of the present invention are not limited to the above-described embodiments, and any other changes, modifications, substitutions, combinations, and simplifications which do not depart from the spirit and principle of the present invention should be construed as equivalents thereof, and they are included in the scope of the present invention.
Claims (9)
1. A spinning solution treatment composite forming method for a nickel-based superalloy tubular piece with a bottom is characterized by comprising the following steps:
the method comprises the following steps: prefabricating a circular sheet blank with a corresponding size according to the wall thickness, the diameter and the machining allowance of the cylindrical part and the law of constant volume;
step two: determining the times of vacuum solid solution heat treatment in the drawing and spinning process according to the limit drawing coefficient of the nickel-based superalloy during drawing and spinning;
step three: adopting a corresponding core mould and a spinning wheel for deep-drawing spinning, and adopting a single spinning wheel and a reciprocating spinning track to carry out multi-pass deep-drawing spinning;
step four: in the process of drawing and spinning a round plate blank, the work hardening of the material is eliminated by adopting vacuum solid solution heat treatment, and the plasticity is recovered; in the vacuum solution heat treatment, in order to improve the temperature uniformity and prevent the crystal grains from growing when the round plate blank is subjected to vacuum solution heat treatment, the round plate blank is firstly subjected to temperature equalization treatment at 600 ℃ and 800 ℃, and then is subjected to vacuum solution heat treatment at 1190-1210 ℃; the time of uniform temperature and vacuum solid solution heat treatment is calculated according to the wall thickness of a round plate blank by adopting the following formulas (1) to (3), and finally gas quenching and cooling treatment are carried out;
τ1＝(25～30)+2t (1)
τ2＝(25～30)+1.5t (2)
τ3＝(18～20)+0.5t (3)
in the formula, tau 1, tau 2 and tau 3 are respectively time of first temperature equalization, second temperature equalization and solution treatment;
τ 1, τ 2, and τ 3 in min; t is the thickness of the blank wall, and the unit is mm;
step five: drawing and spinning the round plate blank subjected to the vacuum solution heat treatment again to form;
step six: repeating the third step and the fourth step; until the drawing and spinning are finished to form the cylindrical part.
2. The spinning solution treatment composite forming method of the nickel-base superalloy belt bottom cylindrical part according to claim 1 is characterized in that: the cooling speed of gas quenching is 30-50 ℃/s.
3. The spinning solution treatment composite forming method of the nickel-based superalloy belt bottom cylindrical part according to claim 2, characterized in that: in the vacuum solution heat treatment process in the step four, the heating speed is 20 ℃/min, the temperature is kept at 600 ℃ and 800 ℃ for 30min, and then the temperature is kept at 1200 ℃ for 20min.
4. The spinning solution treatment composite forming method of the nickel-base superalloy belt bottom cylindrical part as claimed in claim 3, wherein the spinning solution treatment composite forming method comprises the following steps: in the first step, the round sheet blank is made of nickel-based high-temperature alloy which is difficult to deform, and the diameter and the thickness of the round sheet blank are reversely deduced according to the volume invariance law and the thinning rate during flow spinning according to the trimming allowance of 10-15mm and the size of a part.
5. The spinning solution treatment composite forming method of the nickel-based superalloy belt bottom cylinder part according to claim 4, wherein the spinning solution treatment composite forming method comprises the following steps: and step two, the limit spinning coefficient of the nickel-based superalloy during drawing spinning is about 0.75-0.78, and the number of times of intermediate solution treatment is calculated according to the limit spinning coefficient.
6. The spinning solution treatment composite forming method of the nickel-based superalloy belt bottom cylinder part according to claim 5, wherein the spinning solution treatment composite forming method comprises the following steps: step three, the multi-pass deep drawing spinning specifically comprises the following steps:
a core mold with a diameter of 176mm, and a small diameter r ρ =10mm, large diameter r ρ ' =25mm composite profile spinning roller and spinning core die with 3 degree back taper angle; and (3) performing multi-pass deep-drawing spinning by adopting a first pass elevation angle of 60 degrees and feeding circular arc tracks with a ratio of 2mm/r until the outer edge of the circular plate blank reaches the required diameter.
7. The spinning solution treatment composite forming method of the nickel-based superalloy belt bottom cylindrical part according to claim 6, characterized in that: and sixthly, when the step three is repeated, the round plate blank is subjected to multi-pass deep drawing and spinning again to form a cylindrical part, and the first-pass elevation angle is selected to be 30-40 degrees.
8. The spinning solution treatment composite forming method of the nickel-based superalloy belt bottom cylinder part according to claim 7, characterized in that: and step four, performing flow spinning shaping on the cylindrical part formed in the step four, wherein a spinning roller used in the flow spinning shaping process is a double-conical-surface spinning roller.
9. The spinning solution treatment composite forming method of the nickel-based superalloy belt bottom cylinder part according to claim 8, characterized in that: the spinning solution treatment composite forming method of the nickel-based superalloy belt bottom cylindrical part further comprises the following eight steps: and cutting off the straight cylindrical opening part of the cylindrical part by 10-15mm to obtain the cylindrical part with the bottom.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1189711A1 (en) * | 1999-05-05 | 2002-03-27 | Standex International Corporation | Manufacturing a dome from an undersized blank |
| CN103170798A (en) * | 2011-12-21 | 2013-06-26 | 北京有色金属研究总院 | Machining method of high-quality large-diameter thin-wall metal barrel body |
| CN104404418A (en) * | 2014-12-09 | 2015-03-11 | 中南大学 | Thermal treatment method for nickel-base high temperature alloy |
| CN104975248A (en) * | 2015-06-30 | 2015-10-14 | 西北工业大学 | Solution treatment method of third generation nickel-base single crystal high temperature alloy |
| CN107309317A (en) * | 2016-12-19 | 2017-11-03 | 长春理工大学 | Spinning processing method of the nickel-base alloy with bottomless drum shape part |
| CN111054819A (en) * | 2019-11-22 | 2020-04-24 | 华南理工大学 | Precise plastic forming method for deep cup-shaped thin-walled part |
-
2021
- 2021-02-26 CN CN202110213521.5A patent/CN112935056B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1189711A1 (en) * | 1999-05-05 | 2002-03-27 | Standex International Corporation | Manufacturing a dome from an undersized blank |
| CN103170798A (en) * | 2011-12-21 | 2013-06-26 | 北京有色金属研究总院 | Machining method of high-quality large-diameter thin-wall metal barrel body |
| CN104404418A (en) * | 2014-12-09 | 2015-03-11 | 中南大学 | Thermal treatment method for nickel-base high temperature alloy |
| CN104975248A (en) * | 2015-06-30 | 2015-10-14 | 西北工业大学 | Solution treatment method of third generation nickel-base single crystal high temperature alloy |
| CN107309317A (en) * | 2016-12-19 | 2017-11-03 | 长春理工大学 | Spinning processing method of the nickel-base alloy with bottomless drum shape part |
| CN111054819A (en) * | 2019-11-22 | 2020-04-24 | 华南理工大学 | Precise plastic forming method for deep cup-shaped thin-walled part |
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