CN101797629A - High temperature titanium alloy precision casting method based on rapid prototyping - Google Patents
High temperature titanium alloy precision casting method based on rapid prototyping Download PDFInfo
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- CN101797629A CN101797629A CN 201010160205 CN201010160205A CN101797629A CN 101797629 A CN101797629 A CN 101797629A CN 201010160205 CN201010160205 CN 201010160205 CN 201010160205 A CN201010160205 A CN 201010160205A CN 101797629 A CN101797629 A CN 101797629A
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Abstract
The invention relates to a high temperature titanium alloy precision casting method based on a rapid prototyping and relates to a casting method. The high temperature titanium alloy precision casting method solves the problems that the preparation technology is complex, the cost is high and a high temperature titanium alloy part with a complex shape is difficult to obtain in the existing method. The method comprising the following steps: 1, rapidly make mould to obtain a cere; 2, make a shell mold; 3, roast; 4, pour a high temperature titanium alloy casting; 5, post treat, the high temperature titanium alloy casting is obtained after cleaning shell, spraying sand, annealing, finishing and pressure maintaining. The preparation technology of the invention is simple, the cost is low, the design is flexible, thereby being capable of volume production, and the high temperature titanium alloy part with the complex shape can be obtained.
Description
Technical field
The present invention relates to a kind of casting method.
Background technology
Because high-temperature titanium alloy has higher serviceability temperature, elevated temperature strength, good oxidization resistance energy, creep-resistant property, anti-fatigue performance etc., in the used high-temperature structural material of new generation of aircraft engine and rocket propulsion system, enjoy the material supplier authors' of aerospace community attention, become one of the research direction of high-temperature structural material of new generation and development trend with remarkable advantages.Along with further developing of aircraft industry, titanium alloy use aboard will get more and more.Be used for making the important spare part and the aircraft body structure spare of aero-engine desired strength height and good heat resistance more.
The large complicated middle casing formula of the engine fan frame of the U.S. has adopted Ti-6242 high-temperature titanium alloy precision castings, adopt the casting method preparation, but the operating temperature of this Ti-6242 high-temperature titanium alloy precision castings only is that operating temperature is low about 450 ℃.U.S. Howmet company and Boeing have carried out the evaluation of system to the casting character of the high-temperature titanium alloy of use more than 550 ℃ this year, think and adopt suitable ceramic shell, and the mechanical property of the precision castings that obtains through Overheating Treatment and hip treatment is expected to approach the Ti-6Al-4V alloy, now begun to carry out the application study of engine foundry goods, for example the composition of this method preparation is the high-temperature titanium alloy foundry goods of Ti-6-2-4-2, though performance is than higher, the maximum operation (service) temperature of this high-temperature titanium alloy only is 450 ℃; The high-temperature titanium alloy of Ti-Al-Sn-Zr-Mo-Si system can use under 550 ℃ ~ 600 ℃ conditions, but many at present the forms application of this alloy system with ingot casting, sheet material, forging, particularly based on forging.For complex-shaped part, exist the design cycle long, cost height, the problem that is difficult to be shaped.
Summary of the invention
The objective of the invention is in order to solve existing method complicated process of preparation, cost height, to be difficult to obtain the problem of complex-shaped high-temperature titanium alloy part, and a kind of high temperature titanium alloy precision casting method based on rapid prototyping is provided.
The high temperature titanium alloy precision casting method that the present invention is based on rapid prototyping carries out according to following steps: one, rapid die-manufacturing obtains cere; Two, the cere surface is coated with the surface layer of hanging 1 ~ 2 layer and 5 ~ 7 layers backing layer promptly obtains shell, wherein, investment precoat by acetic acid zirconium and yittrium oxide powder according to 2 ~ 2.6: 1 mass ratio is formed, backing layer by Ludox and coal-gangue-powder according to 1.1 ~ 1.8: 1 mass ratio is formed; Three, the shell of step 1 roasting 0.5 ~ 2h under 850 ~ 1100 ℃ of conditions; Four, the shell after the roasting is put into centrifugal titanium casting machine in the step 3, carries out centrifugal casting in the shell with being poured into behind the titanium alloy smelting then, is cooled to room temperature and promptly obtains titanium alloy casting; Four, titanium alloy casting through clear shell, sandblast, annealing and finishing after, be that 850 ~ 1150 ℃, high temperature insostatic pressing (HIP) power are under the condition of 100 ~ 150MPa at hip temperature, pressurize 0.5 ~ 4 hour has promptly realized the hot investment casting of high-temperature titanium alloy.
In the method for the present invention with acetic acid zirconium and yittrium oxide powder as surface layer, and with Ludox and coal-gangue-powder as backing layer, carry out roasting under proper condition, then again through casting, successfully realized the hot investment casting of high-temperature titanium alloy, the present invention is lower to the requirement of preparation condition, preparation technology is simple, and the utilization rate height of material, it is low to have reduced production cost, and method of the present invention has the advantage of near-net-shape, can realize producing in batches, and can prepare complex-shaped high-temperature titanium alloy part, the operating temperature of the high-temperature titanium alloy that the inventive method prepares is 550 ℃ ~ 600 ℃, and resistance to elevated temperatures is good.
Method of the present invention provides a kind of preparation method of high-temperature titanium alloy foundry goods of fast and flexible design preparation complicated shape.
The specific embodiment
Technical solution of the present invention is not limited to the following cited specific embodiment, also comprises any combination between each specific embodiment.
The specific embodiment one: present embodiment is carried out according to following steps based on the high temperature titanium alloy precision casting method of rapid prototyping: one, rapid die-manufacturing obtains cere; Two, the cere surface is coated with the surface layer of hanging 1 ~ 2 layer and 5 ~ 7 layers backing layer promptly obtains shell, wherein, investment precoat by acetic acid zirconium and yittrium oxide powder according to 2 ~ 2.6: 1 mass ratio is formed, backing layer by Ludox and coal-gangue-powder according to 1.1 ~ 1.8: 1 mass ratio is formed; Three, the shell of step 1 roasting 0.5 ~ 2h under 850 ~ 1100 ℃ of conditions; Four, the shell after the roasting is put into centrifugal titanium casting machine in the step 3, carries out centrifugal casting in the shell with being poured into behind the titanium alloy smelting then, is cooled to room temperature and promptly obtains titanium alloy casting; Four, titanium alloy casting through clear shell, sandblast, annealing and finishing after, be that 850 ~ 1150 ℃, high temperature insostatic pressing (HIP) power are under the condition of 100 ~ 150MPa at hip temperature, pressurize 0.5 ~ 4 hour has promptly realized the hot investment casting of high-temperature titanium alloy.
The method of rapid die-manufacturing is to utilize computer that high-temperature titanium alloy foundry goods three-dimensional is designed earlier in the present embodiment step 1, design document is imported rapidform machine finished parts wax-pattern, the rapid die-manufacturing material adopts polystyrene powder, polish with 2000 order sand paper after the molding, to increase the fineness of wax-pattern; And then warm wax is made running gate system in adopting, and with running gate system with made wax-pattern and bond together, the mould tree that makes is come and gone in the wax-pattern cleaning fluid vibrate, about 10-18 second.Wherein, the wax-pattern cleaning fluid is ethanol, acetone, n-octyl alcohol or detergent liquid.
When surface layer slurry prepares in the step 1 in the present embodiment raw material is mixed stirring 24 ~ 36h., promptly obtain surface layer slurry.
Raw material mixed during the pulp preparation of backing layer in the step 1 in the present embodiment and stir 12 ~ 24h, promptly obtain the backing layer slurry.
Acetic acid zirconium in the present embodiment in the step 1, yittrium oxide powder, Ludox and coal-gangue-powder all can be bought from the market and obtain, yittrium oxide powder degree 80 ~ 320 orders wherein, bastard coal fineness of sand 30 ~ 60 orders.
Cutting removal running gate system after the sandblast in the present embodiment step 4, and then annealing.
In the present embodiment with acetic acid zirconium and yittrium oxide powder as surface layer, and with Ludox and coal-gangue-powder as backing layer, carry out roasting under proper condition, then again through casting, successfully realized the hot investment casting of high-temperature titanium alloy, present embodiment is lower to the requirement of preparation condition, preparation technology is simple, and the utilization rate height of material, it is low to have reduced production cost, method of the present invention has the advantage of near-net-shape, can realize producing in batches, and can prepare complex-shaped high-temperature titanium alloy part.
The present embodiment method is according to the difference of use raw material, can realize the prepared in batches of following high-temperature titanium alloy: Ti-1100 (composition is Ti-6Al-2.75Sn-4Zr-0.4Mo-0.45Si), IMI834 (composition is Ti-5.8Al-4Sn-3.5Zr-0.7Nb-0.5M-0.135Si), T36 (composition is Ti-6.2A1-2Sn-3.6Zr-0.7Mo-0.1Y-5.0W-0.15Si), Ti60 (composition is Ti-5.8Al-4.8Sn-2.0Zr-1.0Mo-0.135Si-0.85Nd), and can prepare complex-shaped high-temperature titanium alloy part, serviceability temperature all reaches 550 ℃ ~ 600 ℃, and resistance to elevated temperatures is good.
The specific embodiment two: what present embodiment and the specific embodiment one were different is: the cere surface is coated with the surface layer of hanging 1 layer and 7 layers backing layer in the step 1.Other steps and parameter are identical with the specific embodiment one.
The specific embodiment three: what present embodiment and the specific embodiment one were different is: the cere surface is coated with the surface layer of hanging 2 layers and 5 layers backing layer in the step 1.Other steps and parameter are identical with the specific embodiment one.
The specific embodiment four: what present embodiment was different with one of specific embodiment one to three is: in the step 1 investment precoat by acetic acid zirconium and yittrium oxide powder according to 2.2 ~ 2.4: 1 mass ratio is formed.Other steps and parameter are identical with one of specific embodiment one to three.
The specific embodiment five: what present embodiment was different with one of specific embodiment one to three is: investment precoat is made up of according to 2.3: 1 mass ratio acetic acid zirconium and yittrium oxide powder in the step 1.Other steps and parameter are identical with one of specific embodiment one to three.
The specific embodiment six: what present embodiment was different with one of specific embodiment one to three is: investment precoat is made up of according to 2.2: 1 mass ratio acetic acid zirconium and yittrium oxide powder in the step 1.Other steps and parameter are identical with one of specific embodiment one to three.
The specific embodiment seven: what present embodiment was different with one of specific embodiment one to three is: investment precoat is made up of according to 2.4: 1 mass ratio acetic acid zirconium and yittrium oxide powder in the step 1.Other steps and parameter are identical with one of specific embodiment one to three.
The specific embodiment eight: what present embodiment was different with one of specific embodiment one to seven is: in the step 1 backing layer by Ludox and coal-gangue-powder according to 1.3 ~ 1.6: 1 mass ratio is formed.Other steps and parameter are identical with one of specific embodiment one to seven.
The specific embodiment nine: what present embodiment was different with one of specific embodiment one to seven is: backing layer is made up of according to 1.4: 1 mass ratio Ludox and coal-gangue-powder in the step 1.Other steps and parameter are identical with one of specific embodiment one to seven.
The specific embodiment ten: what present embodiment was different with one of specific embodiment one to seven is: in the step 1
Backing layer is made up of according to 1.35: 1 mass ratio Ludox and coal-gangue-powder.Other steps and parameter are identical with one of specific embodiment one to seven.
The specific embodiment 11: what present embodiment was different with one of specific embodiment one to seven is: backing layer is made up of according to 1.6: 1 mass ratio Ludox and coal-gangue-powder in the step 1.Other steps and parameter are identical with one of specific embodiment one to seven.
The specific embodiment 12: what present embodiment was different with one of specific embodiment one to 11 is: shell roasting 0.9 ~ 1.5h under 890 ~ 1050 ℃ of parts in the step 2.Other steps and parameter are identical with one of specific embodiment one to seven.
The specific embodiment 13: what present embodiment was different with one of specific embodiment one to 11 is: shell roasting 1.2h under 1000 ℃ of parts in the step 2.Other steps and parameter are identical with one of specific embodiment one to seven.
The specific embodiment 14: what present embodiment was different with one of specific embodiment one to 11 is: shell roasting 1.5h under 890 ℃ of parts in the step 2.Other steps and parameter are identical with one of specific embodiment one to seven.
The specific embodiment 15: what present embodiment was different with one of specific embodiment one to 11 is: shell roasting 0.9h under 1050 ℃ of parts in the step 2.Other steps and parameter are identical with one of specific embodiment one to seven.
The specific embodiment 16: what present embodiment was different with one of specific embodiment one to 15 is: 200 ~ 400rpm during centrifugal casting in the step 3.Other steps and parameter are identical with one of specific embodiment one to 15.
The specific embodiment 17: what present embodiment was different with one of specific embodiment one to 16 is: annealing temperature is 700 ~ 800 ℃ in the step 4, insulation 1 ~ 3h.Other steps and parameter are identical with one of specific embodiment one to 16.
The specific embodiment 18: what present embodiment was different with one of specific embodiment one to 16 is: annealing temperature is 730 ~ 780 ℃ in the step 4, insulation 1.5 ~ 2.5h.Other steps and parameter are identical with one of specific embodiment one to 16.
The specific embodiment 19: what present embodiment was different with one of specific embodiment one to 16 is: annealing temperature is 750 ℃ in the step 4, insulation 2h.Other steps and parameter are identical with one of specific embodiment one to 16.
The specific embodiment 20: what present embodiment was different with one of specific embodiment one to 16 is: annealing temperature is 780 ℃ in the step 4, insulation 2.5h.Other steps and parameter are identical with one of specific embodiment one to 16.
The specific embodiment 21: what present embodiment was different with one of specific embodiment one to 16 is: annealing temperature is 730 ℃ in the step 4, insulation 1.5h.Other steps and parameter are identical with one of specific embodiment one to 16.
The specific embodiment 22: what present embodiment was different with one of specific embodiment one to 21 is: hip temperature is that 900 ~ 1000 ℃, high temperature insostatic pressing (HIP) power are under the condition of 110 ~ 140MPa in the step 4,2 ~ 3 hours dwell times.Other steps and parameter are identical with one of specific embodiment one to 21.
The specific embodiment 23: what present embodiment was different with one of specific embodiment one to 21 is: hip temperature is that 950 ℃, high temperature insostatic pressing (HIP) power are under the condition of 135MPa in the step 4, pressurize 2.5 hours.Other steps and parameter are identical with one of specific embodiment one to 21.
The specific embodiment 24: what present embodiment was different with one of specific embodiment one to 21 is: hip temperature is that 900 ℃, high temperature insostatic pressing (HIP) power are under the condition of 140MPa in the step 4, pressurize 3 hours.Other steps and parameter are identical with one of specific embodiment one to 21.
The specific embodiment 25: what present embodiment was different with one of specific embodiment one to 21 is: hip temperature is that 1000 ℃, high temperature insostatic pressing (HIP) power are under the condition of 110MPa in the step 4, pressurize 2 hours.Other steps and parameter are identical with one of specific embodiment one to 21.
The specific embodiment 26: what one of present embodiment specific embodiment one to 25 was different is: the cere surface is coated with and hangs 2 layers surface layer in the step 1, ground floor to second layer investment precoat is made up of according to 2.3: 1 mass ratio mixing acetic acid zirconium and yttrium oxide sand powder, the baking temperature of ground floor investment precoat is 22 ~ 26 ℃, humidity is 50% ~ 70%, be 8 ~ 10h drying time, second layer investment precoat is made up of according to 2.3: 1 mass ratio mixing acetic acid zirconium and yittrium oxide powder, the baking temperature of ground floor investment precoat is 22 ~ 26 ℃, humidity is 50% ~ 70%, and be 12 ~ 14h drying time; The cere surface is coated with the backing layer that hangs up 5 layers, ground floor to layer 5 backing layer coating is made up of according to the mass ratio mixing of 1.6:1 Ludox and coal-gangue-powder, the baking temperature of ground floor backing layer coating is 22 ~ 26 ℃, humidity is 40% ~ 60%, and be 15 ~ 16h drying time, and wind speed is 3 ~ 5m/s, ground floor is 22 ~ 26 ℃ to the baking temperature of layer 5 backing layer coating, humidity is 30% ~ 50%, and be 16 ~ 20h drying time, and wind speed is 6 ~ 8m/s.Other steps and parameter are identical with one of specific embodiment one to 25.
The specific embodiment 27: present embodiment is carried out according to following steps based on the high temperature titanium alloy precision casting method of rapid prototyping: one, rapid die-manufacturing obtains cere; Two, the cere surface is coated with the surface layer of hanging 2 layers and 5 layers backing layer promptly obtains shell, and wherein, investment precoat is made up of according to 2.3: 1 mass ratio acetic acid zirconium and yittrium oxide powder, and backing layer is made up of according to 1.6: 1 mass ratio Ludox and coal-gangue-powder; Three, the shell of step 1 roasting 1.5h under 900 ℃ of conditions; Four, the shell after the roasting is put into centrifugal titanium casting machine in the step 3, carries out centrifugal casting in the shell with being poured into behind the titanium alloy smelting then, is cooled to room temperature and promptly obtains titanium alloy casting; Four, titanium alloy casting through clear shell, sandblast, annealing and finishing after, be that 1000 ℃, high temperature insostatic pressing (HIP) power are under the condition of 120MPa at hip temperature, pressurize 2 hours has promptly realized the hot investment casting of high-temperature titanium alloy.
[0043]The method of rapid die-manufacturing is to utilize computer that high-temperature titanium alloy foundry goods three-dimensional is designed earlier in the present embodiment step 1, design document is imported rapidform machine finished parts wax-pattern, the rapid die-manufacturing material adopts polystyrene powder, polish with 2000 order sand paper after the molding, to increase the fineness of wax-pattern; And then warm wax is made running gate system in adopting, and with running gate system with made wax-pattern and bond together, the mould tree that makes is come and gone in the wax-pattern cleaning fluid shake, about 10-18 second.Wherein, the wax-pattern cleaning fluid is ethanol, acetone, n-octyl alcohol or detergent liquid.
The cere surface is coated with and hangs 2 layers surface layer in the present embodiment step 1, ground floor to second layer investment precoat is made up of according to 2.3: 1 mass ratio mixing acetic acid zirconium and yittrium oxide powder, the baking temperature of ground floor investment precoat is 24 ℃, humidity is 60%, be 9h drying time, and second layer investment precoat is made up of according to 2.3: 1 mass ratio mixing acetic acid zirconium and yittrium oxide powder, and the baking temperature of ground floor investment precoat is 24 ℃, humidity is 60%, and be 13h drying time; The cere surface is coated with the backing layer that hangs up 5 layers, ground floor to layer 5 backing layer coating is made up of according to the mass ratio mixing of 1.6:1 Ludox and coal-gangue-powder, the baking temperature of ground floor backing layer coating is 22 ~ 26 ℃, humidity is 50%, and be 15h drying time, and wind speed is 4m/s, ground floor is 24 ℃ to the baking temperature of layer 5 backing layer coating, humidity is 40%, and be 18h drying time, and wind speed is 7m/s.
The operating temperature of the high-temperature titanium alloy that present embodiment prepares is 550 ℃ ~ 600 ℃, and resistance to elevated temperatures is good.
Claims (8)
1. high temperature titanium alloy precision casting method based on rapid prototyping, it is characterized in that carrying out according to following steps based on the high temperature titanium alloy precision casting method of rapid prototyping: one, rapid die-manufacturing obtains cere; Two, the cere surface is coated with the surface layer of hanging 1 ~ 2 layer and 5 ~ 7 layers backing layer promptly obtains shell, wherein, investment precoat by acetic acid zirconium and yittrium oxide powder according to 2 ~ 2.6: 1 mass ratio is formed, backing layer by Ludox and coal-gangue-powder according to 1.1 ~ 1.8: 1 mass ratio is formed; Three, the shell of step 1 roasting 0.5 ~ 2h under 850 ~ 1100 ℃ of conditions; Four, the shell after the roasting is put into centrifugal titanium casting machine in the step 3, carries out centrifugal casting in the shell with being poured into behind the titanium alloy smelting then, is cooled to room temperature and promptly obtains titanium alloy casting; Four, titanium alloy casting through clear shell, sandblast, annealing and finishing after, be that 850 ~ 1150 ℃, high temperature insostatic pressing (HIP) power are under the condition of 100 ~ 150MPa at hip temperature, pressurize 0.5 ~ 4 hour has promptly realized the hot investment casting of high-temperature titanium alloy.
2. a kind of high temperature titanium alloy precision casting method based on rapid prototyping according to claim 1 is characterized in that the cere surface is coated with the surface layer of 2 layers of extensions and 5 layers backing layer in the step 1.
3. a kind of high temperature titanium alloy precision casting method according to claim 1 and 2 based on rapid prototyping, it is characterized in that in the step 1 investment precoat by acetic acid zirconium and yittrium oxide powder according to 2.2 ~ 2.4: 1 mass ratio is formed.
4. a kind of high temperature titanium alloy precision casting method according to claim 3 based on rapid prototyping, it is characterized in that in the step 1 backing layer by Ludox and coal-gangue-powder according to 1.3 ~ 1.6: 1 mass ratio is formed.
5. according to claim 1,2 or 4 described a kind of high temperature titanium alloy precision casting methods, it is characterized in that shell roasting 0.9 ~ 1.5h under 890 ~ 1050 ℃ of parts in the step 2 based on rapid prototyping.
6. a kind of high temperature titanium alloy precision casting method based on rapid prototyping according to claim 5, centrifugal rotational speed is 200 ~ 400rpm when it is characterized in that in the step 3 centrifugal casting.
7. according to claim 1,2,4 or 6 described a kind of high temperature titanium alloy precision casting methods, it is characterized in that annealing temperature is 700 ~ 800 ℃ in the step 4, insulation 1 ~ 3h based on rapid prototyping.
8. a kind of high temperature titanium alloy precision casting method based on rapid prototyping according to claim 7 is characterized in that in the step 4 that hip temperature is that 900 ~ 1000 ℃, high temperature insostatic pressing (HIP) power are under the condition of 110 ~ 140MPa, pressurize 2 ~ 3 hours.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101927321A (en) * | 2010-09-03 | 2010-12-29 | 北京钢研高纳科技股份有限公司 | Method for preparing high-air permeability and high-strength ceramic shell mold for anti-gravity casting |
| CN102151787A (en) * | 2011-05-30 | 2011-08-17 | 哈尔滨工业大学 | 600-DEG C high-temperature titanium alloy fired mold casting type shell surface painting and preparation method thereof |
| CN102366819A (en) * | 2011-10-10 | 2012-03-07 | 刘群联 | Method for precision casting of titanium alloy |
| CN104001856A (en) * | 2014-05-30 | 2014-08-27 | 张勇弢 | Preparation method of oxide ceramic composite shell for precision casting of titanium alloy |
| CN105195981A (en) * | 2014-05-27 | 2015-12-30 | 遵义林棣科技发展有限公司 | Preparation method for conical-body and square-head bolt |
| CN105545566A (en) * | 2015-12-27 | 2016-05-04 | 张磊 | Waste water generation device |
| CN105886732A (en) * | 2016-06-20 | 2016-08-24 | 安徽宜安精密机械零部件有限公司 | Thermal treatment process for precision castings |
| CN115821184A (en) * | 2022-11-08 | 2023-03-21 | 河北钢研德凯科技有限公司 | Densification treatment method for ZTi60 titanium alloy and application thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58132344A (en) * | 1982-01-29 | 1983-08-06 | Iwatani & Co | Casting method of titanium casting consisting of pure titanium or alloy consisting essentially of titanium |
| CN101143381A (en) * | 2007-10-25 | 2008-03-19 | 大连金煤阀门有限公司 | Titanium alloy fine casting melting method |
-
2010
- 2010-04-30 CN CN 201010160205 patent/CN101797629A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58132344A (en) * | 1982-01-29 | 1983-08-06 | Iwatani & Co | Casting method of titanium casting consisting of pure titanium or alloy consisting essentially of titanium |
| CN101143381A (en) * | 2007-10-25 | 2008-03-19 | 大连金煤阀门有限公司 | Titanium alloy fine casting melting method |
Non-Patent Citations (2)
| Title |
|---|
| 《中国铸造装备与技术》 20060131 张敏华等 《基于SL原型钛合金精铸工艺规程的确定》 , 第1期 2 * |
| 《铸造技术》 20040531 李冰等 《基于SL原型快速精铸钛型壳制备的工艺研究》 第25卷, 第5期 2 * |
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| CN101927321A (en) * | 2010-09-03 | 2010-12-29 | 北京钢研高纳科技股份有限公司 | Method for preparing high-air permeability and high-strength ceramic shell mold for anti-gravity casting |
| CN101927321B (en) * | 2010-09-03 | 2011-12-21 | 北京钢研高纳科技股份有限公司 | Method for preparing high-air permeability and high-strength ceramic shell mold for anti-gravity casting |
| CN102151787A (en) * | 2011-05-30 | 2011-08-17 | 哈尔滨工业大学 | 600-DEG C high-temperature titanium alloy fired mold casting type shell surface painting and preparation method thereof |
| CN102366819A (en) * | 2011-10-10 | 2012-03-07 | 刘群联 | Method for precision casting of titanium alloy |
| CN105195981A (en) * | 2014-05-27 | 2015-12-30 | 遵义林棣科技发展有限公司 | Preparation method for conical-body and square-head bolt |
| CN104001856A (en) * | 2014-05-30 | 2014-08-27 | 张勇弢 | Preparation method of oxide ceramic composite shell for precision casting of titanium alloy |
| CN104001856B (en) * | 2014-05-30 | 2016-07-13 | 张勇弢 | The titanium alloy precision casting preparation method of oxide ceramics composite shell |
| CN105545566A (en) * | 2015-12-27 | 2016-05-04 | 张磊 | Waste water generation device |
| CN105545566B (en) * | 2015-12-27 | 2017-11-14 | 金华市秸和环保技术咨询有限公司 | A kind of wastewater electric generator |
| CN105886732A (en) * | 2016-06-20 | 2016-08-24 | 安徽宜安精密机械零部件有限公司 | Thermal treatment process for precision castings |
| CN115821184A (en) * | 2022-11-08 | 2023-03-21 | 河北钢研德凯科技有限公司 | Densification treatment method for ZTi60 titanium alloy and application thereof |
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