CN104226722A - Machining method of TB3 bar for aerospace electric explosion valve - Google Patents
Machining method of TB3 bar for aerospace electric explosion valve Download PDFInfo
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- CN104226722A CN104226722A CN201410450665.2A CN201410450665A CN104226722A CN 104226722 A CN104226722 A CN 104226722A CN 201410450665 A CN201410450665 A CN 201410450665A CN 104226722 A CN104226722 A CN 104226722A
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Abstract
The invention relates to a machining method of a TB3 bar for an aerospace electric explosion valve, which is used for machining a bar of which the size phi is 16mm. The machining method comprises the following steps: performing heating and heat preservation on a TB3 titanium alloy cast ingot of which the specification phi is 480mm at high temperature of 1,150-1,200 DEG C in an electric furnace for 48 hours; after performing billet forging on the cast ingot by a fast forging machine, performing three-firing forging on the part, above a beta phase transformation point, of the cast ingot; and performing two-firing upsetting, stretching and forging, and two-firing drawing of opposite angles on the part, below the beta phase transformation point, of the cast ingot. By optimizing of an alloy forging deformation process, water cooling after forging, and quenching aging treatment before finish forging, equiaxial microstructure and uniform structure are obtained; finally, the bar with the required size is obtained by finish forging and rolling. The bar is sufficient, uniform and consistent in structure deformation, and the performance requirements of the product are met.
Description
Technical field
The present invention relates to titanium or titanium alloy material processing field, particularly relate to a kind of space flight electric blasting valve TB3 bar processing method.
Background technology
TB3 alloy is a kind of heat-treatable strengthened metastable beta-type titanium alloy, nominal composition Ti-10Mo-8V-3.5Al-1Fe.The main feature of this alloy has excellent cold forming capability, its cold-heading ratio (D in solution treatment state
1/ D
0) can 2.8 be reached, better with mating of fracture toughness in solid solution aging state strength.With alpha-beta type alloy phase ratio, the density of this alloy is higher and high temperature creep-resisting ability is lower.Under solid solution condition, energy long-term work is at 200 DEG C of temperature; Under solid solution aging state, energy long-term work is at 200 DEG C of temperature.This alloy is applicable to manufacture Aero-Space securing member, flexible member and space flight electric blasting valve etc.The every annual requirement of space flight electric blasting valve is in increasing trend rapidly, and the electric blasting valve that common material makes can not meet the reliability and environmental suitability that use in the aircraft industry developed rapidly gradually.
TB3 is as a kind of metastable beta-type titanium alloy, its conventional wrought processes is: 850 ~ 1050 DEG C of insulation 1 ~ 3h ingot formations, then below more than beta transformation point 50 ~ 100 DEG C and beta transformation point 30 ~ 50 DEG C carry out time upsetting pull distortion of many fire, then 50 ~ 100 DEG C of finish forges are shaping more than beta transformation point.Under technique like this, if control improper a little, very likely occur organizing thick and non-uniform phenomenon to occur, cause properties of product to be difficult to reach requirement.
Summary of the invention
For the deficiency of above-mentioned technology, the object of this invention is to provide a kind of space flight electric blasting valve TB3 bar processing method.
Technical scheme of the present invention is:
A kind of space flight electric blasting valve TB3 bar processing method, its concrete steps are as follows:
(1), in resistance-heated furnace carry out hammer cogging, ingot casting is coated with ORC shove charge insulation 1 ~ 2 hour when resistance furnace is heated to 750 DEG C, is warmed up to 1150 ~ 1200 DEG C, insulation 48h, hammer cogging;
(2), in resistance-heated furnace, adopt more than beta transformation point 150 DEG C ~ 200 DEG C to be incubated, quick forging machine is carried out time upsetting pull forging of three fire, and forging ratio is 1.3 ~ 2.0, water-cooled after forging;
(3), in resistance-heated furnace, adopt below beta transformation point 20 DEG C ~ 30 DEG C to be incubated, quick forging machine is carried out time upsetting pull forging of two fire and time diagonal angle pulling of two fire, and forging ratio is 1.3 ~ 2.0, carries out quench aging process after time diagonal angle pulling of last fire;
(4), in resistance-heated furnace, adopt more than beta transformation point 100 DEG C ~ 150 DEG C to be incubated, precise forging machine is carried out two fire time finish forges, air cooling after forging;
(5), in resistance-heated furnace, adopt more than beta transformation point 30 DEG C ~ 50 DEG C to be incubated, milling train carries out two fire time rollings, mill speed 1 ~ 3m/s;
(6) surperficial grinding and polishing, is carried out after blank bar material straightening finish turning to finished size.
Compared with prior art, the present invention has following beneficial effect:
The space flight electric blasting valve TB3 titanium alloy rod bar production method that the present invention proposes, adopt ingot casting solid forging, heat with the cogging temperature forged higher than routine and overlength temperature retention time the hammer cogging carried out to produce hammer cogging with existing conventional beta alloy and compare, forging permeability can better be increased, can better the as-cast grain structure of broken ingot casting, for follow-up forging and other operations reduce the risk of possible heterogeneous structure heredity.And carry out quench aging process before finish forge, can make grain structure more refinement and evenly, for follow-up finish forge insures together with the increase of rolling structure homogenising, thus make final finished product bar metaplasia fully, uniformity, and ensure the requirement of properties of product.
Accompanying drawing explanation
Fig. 1: the mirco structure figure of finished product bar in embodiment 1.
In figure: a: hot-working state b: solid solution condition
C: solid solution+mono-aged d: solid solution+double aging state.
Fig. 2: the mirco structure figure of finished product bar in embodiment 2.
In figure: a: hot-working state b: solid solution condition
C: solid solution+mono-aged d: solid solution+double aging state.
Detailed description of the invention
The following examples can illustrate in greater detail the present invention, but do not limit the present invention in any form.
Embodiment 1:
The material processed in the present embodiment is ingot casting, and diameter is Φ 480mm.By method of the present invention, produce the bar of Φ 16mm × L.
(1), in resistance-heated furnace carry out hammer cogging, ingot casting is coated with ORC shove charge when resistance furnace is heated to 750 DEG C and is incubated 2 hours, is warmed up to 1180 DEG C, insulation 48h, hammer cogging;
(2), in electric furnace, adopt more than beta transformation point 150 DEG C to be incubated, quick forging machine is carried out time upsetting pull forging of three fire, and forging ratio is 1.6, water-cooled after forging;
(3), in electric furnace, adopt below beta transformation point 30 DEG C to be incubated, quick forging machine is carried out time upsetting pull forging of two fire and time diagonal angle pulling of two fire, and forging ratio is 1.8, carries out quench aging process after time diagonal angle pulling of last fire;
(4), in electric furnace, adopt more than beta transformation point 100 DEG C to be incubated, precise forging machine is carried out two fire time finish forges, air cooling after forging;
(5), at electric furnace adopt more than beta transformation point 30 DEG C to be incubated, milling train carries out two fire time rollings, mill speed 3m/s;
(6) surperficial grinding and polishing, is carried out after blank bar material straightening finish turning to finished size.
Detect the forging performance of embodiment 1, tissue, result is as follows:
(1) mechanical property after the heat treatment of finished product bar is as shown in the table
(2) bar mirco structure
Bar mirco structure is as accompanying drawing 1, and thermal process status crystal grain has portion deforms; Solid solution condition is single-phasely wait axle β tissue, β homogeneous grain size, without coarse-grain, be mingled with, the abnormal structure such as segregation; Single Aging Microstructure is on β matrix, separate out tiny acicular α tissue, and α fine microstructures is even; Double aging is organized as β+acicular α tissue, and α fine microstructures is even, the abnormal structures such as nothing is mingled with, segregation.
Embodiment 2:
The material processed in the present embodiment is ingot casting, and diameter is Φ 480mm.By method of the present invention, produce the bar of Φ 16mm × L.
(1), in resistance-heated furnace carry out hammer cogging, ingot casting is coated with ORC shove charge when resistance furnace is heated to 750 DEG C and is incubated 2 hours, is warmed up to 1180 DEG C, insulation 48h, hammer cogging;
(2), in electric furnace, adopt more than beta transformation point 180 DEG C to be incubated, quick forging machine is carried out time upsetting pull forging of three fire, and forging ratio is 1.6, water-cooled after forging;
(3), in electric furnace, adopt below beta transformation point 20 DEG C to be incubated, quick forging machine is carried out time upsetting pull forging of two fire and time diagonal angle pulling of two fire, and forging ratio is 1.8, carries out quench aging process after time diagonal angle pulling of last fire;
(4), in electric furnace, adopt more than beta transformation point 150 DEG C to be incubated, precise forging machine is carried out two fire time finish forges, air cooling after forging;
(5), in electric furnace, adopt more than beta transformation point 50 DEG C to be incubated, milling train carries out two fire time rollings, mill speed 2m/s;
(6) surperficial grinding and polishing, is carried out after blank bar material straightening finish turning to finished size.
Detect the forging performance of embodiment 2, tissue, result is as follows:
(1) mechanical property after the heat treatment of finished product bar is as shown in the table
(2) bar mirco structure
Bar mirco structure is as accompanying drawing 2, and thermal process status crystal grain has portion deforms; Solid solution condition is single-phasely wait axle β tissue, β homogeneous grain size, without coarse-grain, be mingled with, the abnormal structure such as segregation; Single Aging Microstructure is on β matrix, separate out tiny acicular α tissue, and α fine microstructures is even; Double aging is organized as β+acicular α tissue, and α fine microstructures is even, the abnormal structures such as nothing is mingled with, segregation.
Claims (1)
1. a space flight electric blasting valve TB3 bar processing method, it is characterized in that, concrete steps are as follows:
(1), in resistance-heated furnace carry out hammer cogging, ingot casting is coated with ORC shove charge insulation 1 ~ 2 hour when resistance furnace is heated to 750 DEG C, is warmed up to 1150 ~ 1200 DEG C, insulation 48h, hammer cogging;
(2), in resistance-heated furnace, adopt more than beta transformation point 150 DEG C ~ 200 DEG C to be incubated, quick forging machine is carried out time upsetting pull forging of three fire, and forging ratio is 1.3 ~ 2.0, water-cooled after forging;
(3), in resistance-heated furnace, adopt below beta transformation point 20 DEG C ~ 30 DEG C to be incubated, quick forging machine is carried out time upsetting pull forging of two fire and time diagonal angle pulling of two fire, and forging ratio is 1.3 ~ 2.0, carries out quench aging process after time diagonal angle pulling of last fire;
(4), in resistance-heated furnace, adopt more than beta transformation point 100 DEG C ~ 150 DEG C to be incubated, precise forging machine is carried out two fire time finish forges, air cooling after forging;
(5), in resistance-heated furnace, adopt more than beta transformation point 30 DEG C ~ 50 DEG C to be incubated, milling train carries out two fire time rollings, mill speed 1 ~ 3m/s;
(6) surperficial grinding and polishing, is carried out after blank bar material straightening finish turning to finished size.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105039886A (en) * | 2015-08-05 | 2015-11-11 | 西部超导材料科技股份有限公司 | Method for preparing Zr-2.5Nb alloy rod with uniform small structure phase |
| CN106984750A (en) * | 2017-03-27 | 2017-07-28 | 宝鸡高新兴隆钛业有限公司 | A kind of processing method of large-size titanium alloy bar |
| CN109234656A (en) * | 2018-11-08 | 2019-01-18 | 江苏理工学院 | A kind of predeformation heat treatment process improving metastable β Titanium-alloy intensity |
| CN113088758A (en) * | 2021-03-12 | 2021-07-09 | 宝鸡鑫诺新金属材料有限公司 | Production method of TB3 titanium alloy disc wire for fasteners |
| CN114178339A (en) * | 2021-12-09 | 2022-03-15 | 宁夏中色金航钛业有限公司 | Fine-grain Ti for 3D printing additive powder making2AlNb alloy bar and preparation method thereof |
| CN114346137A (en) * | 2021-12-06 | 2022-04-15 | 中国科学院金属研究所 | Hot processing preparation method of large-size titanium alloy bar with uniform thin banded structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105039886A (en) * | 2015-08-05 | 2015-11-11 | 西部超导材料科技股份有限公司 | Method for preparing Zr-2.5Nb alloy rod with uniform small structure phase |
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| CN106984750A (en) * | 2017-03-27 | 2017-07-28 | 宝鸡高新兴隆钛业有限公司 | A kind of processing method of large-size titanium alloy bar |
| CN106984750B (en) * | 2017-03-27 | 2018-12-18 | 宝鸡高新兴隆钛业有限公司 | A kind of processing method of large-size titanium alloy bar |
| CN109234656A (en) * | 2018-11-08 | 2019-01-18 | 江苏理工学院 | A kind of predeformation heat treatment process improving metastable β Titanium-alloy intensity |
| CN113088758A (en) * | 2021-03-12 | 2021-07-09 | 宝鸡鑫诺新金属材料有限公司 | Production method of TB3 titanium alloy disc wire for fasteners |
| CN114346137A (en) * | 2021-12-06 | 2022-04-15 | 中国科学院金属研究所 | Hot processing preparation method of large-size titanium alloy bar with uniform thin banded structure |
| CN114346137B (en) * | 2021-12-06 | 2023-10-13 | 中国科学院金属研究所 | Hot processing preparation method of large-size titanium alloy bar with uniform thin strip structure |
| CN114178339A (en) * | 2021-12-09 | 2022-03-15 | 宁夏中色金航钛业有限公司 | Fine-grain Ti for 3D printing additive powder making2AlNb alloy bar and preparation method thereof |
| CN114178339B (en) * | 2021-12-09 | 2023-05-16 | 宁夏中色金航钛业有限公司 | 3D prints fine grain Ti for material increase powder process 2 AlNb alloy bar and preparation method thereof |
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Address after: No. 97, Qianming Road, Qingshan Community, Deshan Street, Changde Economic and Technological Development Zone, Changde City, Hunan Province, 415001 Patentee after: Hunan Xiangtou Jintian Titanium Technology Co.,Ltd. Address before: 415001 Changde Economic and Technological Development Zone, Changde City, Hunan Province Patentee before: HUNAN GOLDSKY TITANIUM INDUSTRY TECHNOLOGY Co.,Ltd. |
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