CN102896267A - Isothermal forging method of TC17 titanium alloy disc-shaped forge piece - Google Patents
Isothermal forging method of TC17 titanium alloy disc-shaped forge piece Download PDFInfo
- Publication number
- CN102896267A CN102896267A CN2012103696218A CN201210369621A CN102896267A CN 102896267 A CN102896267 A CN 102896267A CN 2012103696218 A CN2012103696218 A CN 2012103696218A CN 201210369621 A CN201210369621 A CN 201210369621A CN 102896267 A CN102896267 A CN 102896267A
- Authority
- CN
- China
- Prior art keywords
- forging
- biscuit
- die
- titanium alloy
- temperature
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Forging (AREA)
Abstract
The invention relates to a forging method of a titanium alloy disc-shaped forge piece and particularly relates to an isothermal forging method of a TC17 titanium alloy disc-shaped forge piece. The method includes heating a titanium alloy rod ingot to the temperature which is smaller than a transformation temperature by 40 DEG C-50 DEGC, heating an upper flat die and a lower flat die to a temperature which is smaller than the transformation temperature by 40 DEG C-50 DEGC, and enabling the upper flat die to move downwards so that the rod ingot is subjected to first isothermal upsetting to form a primary biscuit at the strain rate of 0.001s<-1>-0.01s<-1> and then to second isothermal upsetting to form a secondary biscuit at the strain rate of 0.001s<-1>-0.01s<-1>, and the deformation amount is 30%-50%; heating the secondary biscuit to the temperature which is smaller than the transformation temperature by 20 DEG C-30 DEGC, heating an upper cavity die and a lower cavity die to the temperature which is smaller than the transformation temperature by 20 DEG C-30 DEGC, and forging the secondary biscuit by using a pressing machine so that the upper cavity die and the lower cavity die are molded to a forge piece under the conditions that the strain rate is 0.001s<-1>-0.01s<-1> and the deformation amount reaches 30%-50% in the cavity dies; and subjecting the forge piece to heat treatment after forging, wherein the heat treatment includes solid solution treatment and aging treatment. According to the method, the disc-shaped forge piece forged by the method is provided with ideal equiaxed structures and high performances, and the method is suitable for manufacturing forge pieces of compressor disks and turbine disks of aero-engines.
Description
Technical field
The present invention relates to a kind of forging method of titanium alloy disk forge piece, particularly a kind of isothermal forging method of TC17 titanium alloy disk forge piece.
Background technology
The characteristic such as it is anticorrosive that titanium alloy has that intensity is high, quality is light and good, in the Aeronautics and Astronautics field important application is arranged, especially the diskwares such as the compressor disc of aero-engine, the turbine disk are because work under bad environment, stressed complexity often adopts the type alpha+beta diphasic titanium alloy forging and molding of excellent combination property.The series of advantages such as the diskware that adopts the type alpha+beta diphasic titanium alloy to forge has high strength, fracture toughness is good, quenching degree is high and forging range is wide can satisfy the needs of loss tolerance limit design and the requirement of high structure, high reliability and low manufacturing cost.The variation of microscopic structure is comparatively remarkable on the mechanical performance impact, and above-mentioned Good All-around Property must guarantee by desirable forging microstructure.
" the Shanghai steel grinds " 02 periodical in 2006 is stepped on one piece of Isothermal Forging Technology of Titanium Alloy Blisk article by name, this article is studied the shape of the forging drawing of TC17 alloy monolithic leaf dish, rough forging and mould structure and isothermal forging process, and produces whole titanium alloy leaf dish Isothermal Forging by isothermal forging process.This article described TC17 diskware isothermal forging and this patent are described to be same class material diskware isothermal forging, but this article is not described the forming process of described forging.No forming process has different effects and economic benefit.
In the research that alpha and beta type titan alloy forges, can obtain the microscopic structure of Four types because of the thermal deformation technique difference, along with the requirement more and more higher to engine performance, the properties design objective improves constantly, many research work are put into and are obtained the basket tissue, CN1403622A discloses a kind of titanium alloy quasi-beta forging process, when adopting this technique that alpha and beta type titan alloy is carried out accurate β forging, that titanium alloy blank is heated near the beta transformation point temperature zone, be that following 10 ℃ of phase point temperature forges to 10 ℃ scope more than the phase point temperature, when heat in this zone, because the cooling of blank after coming out of the stove, the distortion of forging is actually to be carried out in the alpha+beta district, and the primary α of this basket tissue is in 15.But the method is to forge by hot forging, can not effectively control the forging deformation temperature, therefore the control of forging tissue is not had stability.
Patent CN101804441A " near isothermal forging method of TC17 two-phase titanium alloy disk forge piece ", the method adopts " low-Gao-low " technique base, namely TC17 titanium alloy bar ingot is heated to below the transformation temperature 30 ℃～75 ℃, jumping-up; Be heated to again above 20 ℃～60 ℃ of transformation temperature, pulling; Be heated to again following 30 ℃～75 ℃ of transformation temperature, obtain the circular material blank that the α isometry distributes after the jumping-up punching, again circular material blank is heated to more than the transformation temperature 20 ℃～60 ℃, forging die is heated to below the transformation temperature forging of the basket tissue of preparation the whole network after 10 ℃～20 ℃.Although the method also is the forging method of TC17 titanium alloy disk forge piece, what prepare is the forging of the basket tissue of the whole network, if will obtain the forging of bifurcation tissue, the party's rule can not realize.
Summary of the invention
It is the approximately isothermal forging method of the TC17 titanium alloy disk forge piece of 20% α phase such as axle such as grade and equally distributed bifurcation tissue of content that the technical problem to be solved in the present invention provides a kind of disk forge piece internal microstructure that makes.Technical solution of the present invention is,
The TC17 titanium alloy rod bar is become excellent ingot by the specification blanking, heat this rod ingot to below the alloy phase height 40 ℃～50 ℃, by this rod ingot effective thickness 0.6～1min/mm insulation; Heat upper and lower flat-die after below the transformation temperature 40 ℃～50 ℃ the described excellent ingot flat-die of packing into, press forges and presses excellent ingot makes it with 0.001s
-1～0.01s
-1Strain rate reach 30%～50% in flat-die internal strain amount and be configured as biscuit one time, in flat-die, take out a biscuit, melt down while hot heat tracing;
Melt down temperature retention time by after temperature, calculating, temperature retention time by the first time temperature retention time reduce by half; After insulation finishes, again biscuit flat-die of packing into is carried out the second fire time jumping-up, biscuit of press forging and pressing makes it with 0.001s
-1～0.01s
-1Strain rate reach 30%～50% in flat-die internal strain amount and be configured as the secondary biscuit, in flat-die, take out secondary biscuit air cooling;
Heat above-mentioned secondary biscuit to following 20 ℃～30 ℃ of transformation temperature, by this secondary biscuit effective thickness 0.6～1min/mm insulation; Heat upper and lower swaging die after below the transformation temperature 20 ℃～30 ℃ the secondary biscuit swaging die of packing into, press forging and pressing secondary biscuit makes it with 0.001s
-1～0.01s
-1Strain rate reach 30%～50% postforming forging in swaging die internal strain amount, take out the forging air cooling in the swaging die;
After forging forging is heat-treated, forging is heat-treated after forging, and its heat treating regime is for being 780 ℃～820 ℃ * 4 hours, water-cooled; 590 ℃～650 ℃ * 8 hours, air cooling.
Described forging heat treating regime is 800 ℃ ± 10 ℃ * 4 hours, water-cooled; 620 ℃ ± 10 ℃ * 8 hours, air cooling.
For making things convenient for delivery, described excellent ingot and biscuit are preheating to first 200 ℃～300 ℃ before adding the hot charging mould after at its surface spraying glass lubricant; Described flat-die and swaging die before described excellent ingot dress mould at the mould surface spraying glass lubricant.
Compared with prior art, beneficial effect of the present invention is as follows:
The present invention adopts excellent ingot two fire time isothermal jumping-up technique bases, namely TC17 titanium alloy bar ingot is heated to below the transformation temperature 40 ℃～50 ℃, and flat-die is heated to below the transformation temperature after 40 ℃～50 ℃, make excellent ingot in flat-die with strain rate 0.001s
-1～0.01s
-1In the scope, deflection reaches and carries out two fire time jumping-ups in 30%～50% scope, guarantees that excellent ingot carries out in two-phase section, obtains the biscuit that waits axle α to organize tiny and that be evenly distributed, for follow-up forging forming lays the foundation.
Biscuit is heated to below the transformation temperature 20 ℃～30 ℃, swaging die is heated to below the transformation temperature after 20 ℃～30 ℃, make biscuit in swaging die with strain rate 0.001s
-1～0.01s
-1Scope is interior, deflection reaches 30%～50% scope internal shaping forging, guarantees that forging stock carries out in two-phase section, obtains equiaxial alpha content and is about 20% bifurcation tissue, thereby obtain best fracture toughness and the coupling of plasticity, the needs of fully satisfied loss tolerance limit design.
Advantage of the present invention is to forge district's isothermal forging by the alpha+beta two-phase of routine, it is isothermal jumping-up+isothermal die forging process, resistance of deformation is little, easily be shaped, good stability, yield rate are high, and avoided how fire time open die forgings change expensive, the long period that the forging base brings in the current technology, when meeting design requirement, greatly increased economic benefit.
The forging that adopts the method to forge after heat treatment has comparatively ideal combination property, and realizes that the thick forging ultrasound examination of 150mm clutter level satisfies the 0.8-12DB requirement.
Description of drawings
Fig. 1 is that titanium alloy two fire time isothermal jumping-up bases and a fire time isothermal forging cause shape disk forge piece process chart.
Fig. 2 adopts the TC17 Isothermal Forging of Titanium Alloy to become shape Forging along the metallographic structure photo of the R/2 position, longitudinal section that center line is cut open.
The specific embodiment
The type alpha+beta diphasic titanium alloy, for example: the Chinese material trade mark is the titanium alloy of TC17.
The below has provided the near isothermal forging processing step of TC17 titanium alloy:
Step 1: detecting the TC17 titanium alloy material phase point temperature that adopts is 895 ℃.
Step 2: as shown in Figure 1, TC17 titanium alloy circular bar is become excellent ingot 1 by the blanking of forging specification, after excellent ingot 1 is preheating to 300 ℃ at its surface spraying lubricant agent special, again this rod ingot 1 is put into and is heated to below the titanium alloy transformation temperature 855 ℃ in the forge furnace, insulation, temperature retention time is calculated by excellent ingot effective thickness 0.6min/mm.
Step 3: upper flat-die 2 and lower flat-die 3 are heated to following 855 ℃ of this titanium alloy transformation temperature, if convenient when delivery, can be at the surface spraying glass lubricant of upper flat-die 2 and lower flat-die 3, heat by the ring mould heating furnace 8 that is installed on the forging press during heating, again the flat-die of packing into of the excellent ingot 1 after step 1 heating, excellent ingot 1 is carried out isothermal be upset as biscuit 4 one time by upper flat-die is descending.One time biscuit 4 melts down while hot.The deflection of a biscuit 4 is that the forging strain rate of 33%, biscuit 4 in the forging and pressing process is 0.001s
- 1～0.01s
-1
Step 4: an above-mentioned biscuit 4 that melts down while hot is heated to following 855 ℃ of this titanium alloy transformation temperature, insulation, temperature retention time reduces by half by the temperature retention time of step 2.
Step 5: take out a biscuit 4 in the forge furnace, be put into and carry out again the second fire time jumping-up on the forging press and obtain secondary biscuit 5, air cooling after forging.The deflection of secondary biscuit 5 is 36%, and the forging strain rate of secondary biscuit 5 in the forging and pressing process is 0.001s
-1～0.01s
-1
Step 6: at its surface spraying glass lubricant, again this biscuit is heated to these below titanium alloy transformation temperature 865 ℃ after secondary biscuit 5 is preheating to 300 ℃, insulation, temperature retention time is calculated by this biscuit effective thickness 0.6min/mm.
Step 7: upper impression mould 6 and lower impressions mould 7 are heated to these below titanium alloy transformation temperature 865 ℃, if convenient when delivery, can be at the surface spraying glass lubricant of upper impression mould 6 and lower impressions mould 7, heat by the ring mould heating furnace 8 that is installed on the forging press during heating, again the swaging die of packing into of the biscuit 5 after step 5 heating, exert pressure by forging press and to make upper impression mould 6 descending, inferior to biscuit 5 excellent suitability for press forming forging 9 with lower impressions mould 7 matched moulds and a fire, forging 9 depanning air coolings.The deflection of forging 9 is 33%, and the forging strain rate of forging 9 in the forging and pressing process is 0.001s
-1～0.01s
-1
Step 8: forging 9 is heat-treated, i.e. solid solution+Ageing Treatment, and wherein solution treatment is that forging 9 is heated to 800 ℃ ± 10 ℃, puts into water behind the insulation 4h and cools off rapidly (shrend); Ageing Treatment is that the forging 9 after solution treatment is heated to 620 ℃ ± 10 ℃, and the laggard line space of insulation 8h is cold.
Claims (4)
1. the isothermal forging method of a TC17 titanium alloy disk forge piece is characterized in that, may further comprise the steps:
The TC17 titanium alloy rod bar is become excellent ingot by the specification blanking, heat this rod ingot to below the alloy phase height 40 ℃～50 ℃, by this rod ingot effective thickness 0.6～1min/mm insulation;
Heat upper and lower flat-die and after below the transformation temperature 40 ℃～50 ℃ described excellent ingot is put into flat-die, press forges and presses excellent ingot makes it with 0.001s
-1～0.01s
-1Strain rate after flat-die internal strain amount reaches 30%～50%, obtain one time biscuit, take out and to melt down while hot;
Biscuit melts down temperature retention time while hot by calculating after temperature, temperature retention time reduces by half, and after insulation finishes, biscuit flat-die of packing into is carried out the second fire and is upset as the secondary biscuit, and press forges and presses a biscuit makes it with 0.001s
- 1～0.01s
-1Strain rate reach 30%～50% rear taking-up air cooling in flat-die internal strain amount;
Heat described secondary biscuit to following 20 ℃～30 ℃ of transformation temperature, by this secondary biscuit effective thickness 0.6～1min/mm insulation; Heat upper and lower swaging die after below the transformation temperature 20 ℃～30 ℃ the described secondary biscuit swaging die of packing into, press forging and pressing secondary biscuit makes it with 0.001s
-1～0.01s
-1Strain rate reach 30%～50% postforming forging in swaging die internal strain amount;
Forging is heat-treated after forging, and its heat treating regime is for being 780 ℃～820 ℃ * 4 hours, water-cooled; 590 ℃～650 ℃ * 8 hours, air cooling.
2. according to the isothermal forging method of TC17 titanium alloy forging claimed in claim 1, it is characterized in that: described excellent ingot is preheating to 200 ℃～300 ℃ before adding the hot charging mould after at its surface spraying glass lubricant.
3. according to the isothermal forging method of TC17 titanium alloy forging claimed in claim 1, it is characterized in that: described flat-die and swaging die before described excellent ingot dress mould at the mould surface spraying glass lubricant.
4. according to the isothermal forging method of TC17 titanium alloy forging claimed in claim 1, it is characterized in that: described forging heat treating regime is 800 ℃ ± 10 ℃ * 4 hours, water-cooled; 620 ℃ ± 10 ℃ * 8 hours, air cooling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210369621.8A CN102896267B (en) | 2012-09-28 | 2012-09-28 | Isothermal forging method of TC17 titanium alloy disc-shaped forge piece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210369621.8A CN102896267B (en) | 2012-09-28 | 2012-09-28 | Isothermal forging method of TC17 titanium alloy disc-shaped forge piece |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102896267A true CN102896267A (en) | 2013-01-30 |
| CN102896267B CN102896267B (en) | 2015-04-15 |
Family
ID=47568918
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210369621.8A Active CN102896267B (en) | 2012-09-28 | 2012-09-28 | Isothermal forging method of TC17 titanium alloy disc-shaped forge piece |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102896267B (en) |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103537594A (en) * | 2013-09-30 | 2014-01-29 | 中国航空工业集团公司北京航空材料研究院 | Isothermal forging heating device capable of expanding heating zone space effectively |
| CN103706743A (en) * | 2013-12-12 | 2014-04-09 | 无锡透平叶片有限公司 | Die-forging forming process of titanium-alloy forged drum piece |
| CN104451491A (en) * | 2014-12-15 | 2015-03-25 | 西北有色金属研究院 | Preparation method of Ti12LC titanium alloy forge piece |
| CN104646578A (en) * | 2013-12-31 | 2015-05-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Isothermal forging method for titanium alloy whole frame-shaped piece |
| CN105397001A (en) * | 2015-12-02 | 2016-03-16 | 贵州安大航空锻造有限责任公司 | Isothermal forging forming method of titanium alloy complex sheet forged piece |
| CN105728617A (en) * | 2014-12-12 | 2016-07-06 | 陕西宏远航空锻造有限责任公司 | Ti60 titanium alloy isothermal forging and heat treatment method |
| CN106607540A (en) * | 2015-10-27 | 2017-05-03 | 陕西宏远航空锻造有限责任公司 | Isothermal beta forging method for TC17 titanium alloy blade |
| CN106862452A (en) * | 2015-12-14 | 2017-06-20 | 陕西宏远航空锻造有限责任公司 | A kind of isothermal β forging methods of TC17 titanium alloys blisk |
| CN107486524A (en) * | 2017-10-16 | 2017-12-19 | 陕西海恩得工贸有限公司 | A kind of preparation method of titanium alloy cake material |
| CN109093048A (en) * | 2018-08-01 | 2018-12-28 | 西安三角防务股份有限公司 | A kind of mainframe lock forging mold and forging method |
| CN109622837A (en) * | 2018-12-11 | 2019-04-16 | 陕西宏远航空锻造有限责任公司 | A kind of preparation method and device of the TC11 titanium alloy biscuit that high flaw detection is horizontal |
| CN110976747A (en) * | 2019-12-24 | 2020-04-10 | 陕西宏远航空锻造有限责任公司 | Method for forging TC17 alloy blisk by β forging |
| CN112676505A (en) * | 2020-11-20 | 2021-04-20 | 沈阳中钛装备制造有限公司 | Forging forming method |
| CN113369428A (en) * | 2021-07-07 | 2021-09-10 | 中国航发北京航空材料研究院 | Preparation method of large-size TC17 titanium alloy beta-forged blisk forging |
| CN113958409A (en) * | 2020-07-21 | 2022-01-21 | 中国航发商用航空发动机有限责任公司 | Aviation titanium alloy part and preparation method thereof |
| CN114226616A (en) * | 2021-10-29 | 2022-03-25 | 中国航发北京航空材料研究院 | Isothermal forging method of TB17 titanium alloy |
| CN115007775A (en) * | 2022-06-29 | 2022-09-06 | 中国航发北京航空材料研究院 | Preparation method of high-strength 650 ℃ high-temperature titanium alloy large-size blisk forging |
| CN116372075A (en) * | 2023-02-07 | 2023-07-04 | 贵州锆石科技发展有限责任公司 | Vacuum isothermal forging method for 3D printing blank of titanium alloy integral disc shaft forging |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4854977A (en) * | 1987-04-16 | 1989-08-08 | Compagnie Europeenne Du Zirconium Cezus | Process for treating titanium alloy parts for use as compressor disks in aircraft propulsion systems |
| JPH0525597A (en) * | 1991-07-15 | 1993-02-02 | Daido Steel Co Ltd | Manufacture of titanium alloy parts |
| JPH07252617A (en) * | 1994-03-11 | 1995-10-03 | Sumitomo Metal Ind Ltd | Production of titanium alloy having high strength and high toughness |
| CN101480689A (en) * | 2008-12-25 | 2009-07-15 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of two-phase titanium alloy disc-shaped forging |
| CN101804441A (en) * | 2008-12-25 | 2010-08-18 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of TC17 biphase titanium alloy disc forge piece |
| CN101829749A (en) * | 2008-12-25 | 2010-09-15 | 贵州安大航空锻造有限责任公司 | Approximate isothermal forging method of BT25 two-phase titanium alloy disk forge piece |
-
2012
- 2012-09-28 CN CN201210369621.8A patent/CN102896267B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4854977A (en) * | 1987-04-16 | 1989-08-08 | Compagnie Europeenne Du Zirconium Cezus | Process for treating titanium alloy parts for use as compressor disks in aircraft propulsion systems |
| JPH0525597A (en) * | 1991-07-15 | 1993-02-02 | Daido Steel Co Ltd | Manufacture of titanium alloy parts |
| JPH07252617A (en) * | 1994-03-11 | 1995-10-03 | Sumitomo Metal Ind Ltd | Production of titanium alloy having high strength and high toughness |
| CN101480689A (en) * | 2008-12-25 | 2009-07-15 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of two-phase titanium alloy disc-shaped forging |
| CN101804441A (en) * | 2008-12-25 | 2010-08-18 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of TC17 biphase titanium alloy disc forge piece |
| CN101829749A (en) * | 2008-12-25 | 2010-09-15 | 贵州安大航空锻造有限责任公司 | Approximate isothermal forging method of BT25 two-phase titanium alloy disk forge piece |
Non-Patent Citations (2)
| Title |
|---|
| 徐斌等: "TC17钛合金在热变形过程中的组织演变规律", 《中国有色金属学报》 * |
| 赵张龙等: "激光烧结/等温锻造TC17粉末钛合金的组织与性能", 《稀有金属材料与工程》 * |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103537594A (en) * | 2013-09-30 | 2014-01-29 | 中国航空工业集团公司北京航空材料研究院 | Isothermal forging heating device capable of expanding heating zone space effectively |
| CN103706743A (en) * | 2013-12-12 | 2014-04-09 | 无锡透平叶片有限公司 | Die-forging forming process of titanium-alloy forged drum piece |
| CN104646578A (en) * | 2013-12-31 | 2015-05-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Isothermal forging method for titanium alloy whole frame-shaped piece |
| CN105728617A (en) * | 2014-12-12 | 2016-07-06 | 陕西宏远航空锻造有限责任公司 | Ti60 titanium alloy isothermal forging and heat treatment method |
| CN104451491A (en) * | 2014-12-15 | 2015-03-25 | 西北有色金属研究院 | Preparation method of Ti12LC titanium alloy forge piece |
| CN104451491B (en) * | 2014-12-15 | 2016-11-30 | 西北有色金属研究院 | A kind of preparation method of Ti12LC titanium alloy forging |
| CN106607540A (en) * | 2015-10-27 | 2017-05-03 | 陕西宏远航空锻造有限责任公司 | Isothermal beta forging method for TC17 titanium alloy blade |
| CN105397001A (en) * | 2015-12-02 | 2016-03-16 | 贵州安大航空锻造有限责任公司 | Isothermal forging forming method of titanium alloy complex sheet forged piece |
| CN106862452A (en) * | 2015-12-14 | 2017-06-20 | 陕西宏远航空锻造有限责任公司 | A kind of isothermal β forging methods of TC17 titanium alloys blisk |
| CN107486524A (en) * | 2017-10-16 | 2017-12-19 | 陕西海恩得工贸有限公司 | A kind of preparation method of titanium alloy cake material |
| CN109093048A (en) * | 2018-08-01 | 2018-12-28 | 西安三角防务股份有限公司 | A kind of mainframe lock forging mold and forging method |
| CN109622837A (en) * | 2018-12-11 | 2019-04-16 | 陕西宏远航空锻造有限责任公司 | A kind of preparation method and device of the TC11 titanium alloy biscuit that high flaw detection is horizontal |
| CN110976747A (en) * | 2019-12-24 | 2020-04-10 | 陕西宏远航空锻造有限责任公司 | Method for forging TC17 alloy blisk by β forging |
| CN110976747B (en) * | 2019-12-24 | 2021-10-15 | 陕西宏远航空锻造有限责任公司 | Method for forging TC17 alloy blisk through beta forging |
| CN113958409A (en) * | 2020-07-21 | 2022-01-21 | 中国航发商用航空发动机有限责任公司 | Aviation titanium alloy part and preparation method thereof |
| CN113958409B (en) * | 2020-07-21 | 2023-02-24 | 中国航发商用航空发动机有限责任公司 | Aviation titanium alloy part and preparation method thereof |
| CN112676505A (en) * | 2020-11-20 | 2021-04-20 | 沈阳中钛装备制造有限公司 | Forging forming method |
| CN113369428A (en) * | 2021-07-07 | 2021-09-10 | 中国航发北京航空材料研究院 | Preparation method of large-size TC17 titanium alloy beta-forged blisk forging |
| CN114226616A (en) * | 2021-10-29 | 2022-03-25 | 中国航发北京航空材料研究院 | Isothermal forging method of TB17 titanium alloy |
| CN114226616B (en) * | 2021-10-29 | 2023-03-14 | 中国航发北京航空材料研究院 | Isothermal forging method of TB17 titanium alloy |
| CN115007775A (en) * | 2022-06-29 | 2022-09-06 | 中国航发北京航空材料研究院 | Preparation method of high-strength 650 ℃ high-temperature titanium alloy large-size blisk forging |
| CN115007775B (en) * | 2022-06-29 | 2024-02-02 | 中国航发北京航空材料研究院 | Preparation method of high-strength 650 ℃ high-temperature titanium alloy large-size blisk forging |
| CN116372075A (en) * | 2023-02-07 | 2023-07-04 | 贵州锆石科技发展有限责任公司 | Vacuum isothermal forging method for 3D printing blank of titanium alloy integral disc shaft forging |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102896267B (en) | 2015-04-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102896267B (en) | Isothermal forging method of TC17 titanium alloy disc-shaped forge piece | |
| CN101804441B (en) | Near-isothermal forging method of TC17 biphase titanium alloy disc forge piece | |
| CN111235506B (en) | Thermal processing technology of TC25G titanium alloy forging | |
| CN101480689B (en) | Near-isothermal forging method of two-phase titanium alloy disk-type forgeable piece | |
| CN101829749B (en) | Approximate isothermal forging method of BT25 two-phase titanium alloy disk forge piece | |
| CN103465027B (en) | The thin brilliant dish base manufacture method of a kind of GH4169 alloy | |
| CN102312118B (en) | Hot-working method for GH864 Waspaloy with accurately controlled structure | |
| EP2659993B1 (en) | Closed-die forging method and method of manufacturing forged article | |
| CN105506525B (en) | Preparation method of Ti2AlNb-based alloy large-size uniform fine-grain bar | |
| CN101941039B (en) | High-strength aluminum alloy isothermal direction-change open die forging method and device | |
| CN109482796B (en) | Beta forging and heat treatment method of TC4 titanium alloy disc forging | |
| CN101758159A (en) | Near isothermal forging method for whole titanium alloy disc shaft forgeable piece | |
| CN103071743B (en) | Preparation method for TC11 titanium alloy small-bore thick-walled cylindrical part | |
| RU2013116806A (en) | TECHNOLOGICAL ROUTES FOR TITANIUM AND TITANIUM ALLOYS | |
| CN102764838A (en) | Gear thermal precision forging machining process adopting carburizing steel 20CrMnTi as material | |
| CN104139141A (en) | Equiaxed grain forging forming method for titanium alloy ring piece | |
| CN106363352A (en) | Manufacturing process of high-strength aluminum alloy ring forge | |
| CN105689613A (en) | Special forging method suitable for super duplex stainless steel bars | |
| CN108044007B (en) | Forging method of high-uniformity Ti632211 titanium alloy plate | |
| CN106148762B (en) | A kind of preparation method of low temperature TA7 DT titanium alloy rod bars | |
| CN102764837A (en) | Method for forging GH4169 disc-shaped piece | |
| CN108246948B (en) | Forging method for improving GH901 die forging structure | |
| CN102886643A (en) | Method for manufacturing sliding fork for automobile | |
| CN103071753B (en) | Forging method of ball valve stem | |
| CN112355208A (en) | Near-net rolling forming method of GH907 special-shaped ring forging |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |