CN104226722B - A kind of space flight electric blasting valve TB3 bar processing method - Google Patents

A kind of space flight electric blasting valve TB3 bar processing method Download PDF

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CN104226722B
CN104226722B CN201410450665.2A CN201410450665A CN104226722B CN 104226722 B CN104226722 B CN 104226722B CN 201410450665 A CN201410450665 A CN 201410450665A CN 104226722 B CN104226722 B CN 104226722B
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forging
fire
resistance
time
transformation point
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CN201410450665.2A
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CN104226722A (en
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刘安武
余日成
黄艳华
杨胜
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湖南金天钛业科技有限公司
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Abstract

The present invention relates to a kind of space flight electric blasting valve TB3 bar processing method, the bar of processing dimension Φ 16mm.This technique particular content: the TB3 titan alloy casting ingot adopting φ 480mm specification, ingot casting is 1150 ~ 1200 DEG C of high-temperature heating insulation 48h in electric furnace, after quick forging machine carries out cogging forging, more than beta transformation point, carry out time forging of three fire, below beta transformation point, carry out time upsetting pull forging of two fire and time diagonal angle pulling of two fire subsequently.By water-cooled after optimized alloy forging deformation technique, forging, quench aging process before finish forge, obtains Deng Zhou mirco structure uniform formation, obtains the bar of required size finally by finish forge and rolling, bar metaplasia is abundant, uniformity, and ensures the requirement of properties of product.

Description

A kind of space flight electric blasting valve TB3 bar processing method

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-heated 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.

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-heated 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.

(1), in resistance-heated furnace carry out hammer cogging, ingot casting is coated with ORC shove charge when resistance-heated 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 resistance-heated 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 resistance-heated 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 resistance-heated 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 resistance-heated 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.

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-heated 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.

(1), in resistance-heated furnace carry out hammer cogging, ingot casting is coated with ORC shove charge when resistance-heated 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 resistance-heated 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 resistance-heated 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 resistance-heated 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 resistance-heated 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.

(1), in resistance-heated furnace carry out hammer cogging, ingot casting is coated with ORC shove charge when resistance-heated 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 resistance-heated 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 resistance-heated 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 resistance-heated 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 resistance-heated 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-heated 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.
CN201410450665.2A 2014-09-05 2014-09-05 A kind of space flight electric blasting valve TB3 bar processing method CN104226722B (en)

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CN105039886B (en) * 2015-08-05 2017-02-01 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
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
CN109234656B (en) * 2018-11-08 2020-02-14 江苏理工学院 Pre-deformation heat treatment process for improving strength of metastable β titanium alloy

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JPS58145323A (en) * 1982-02-22 1983-08-30 Toshiba Corp Forging method of titanium alloy
JP2004091893A (en) * 2002-09-02 2004-03-25 Kobe Steel Ltd High strength titanium alloy
CN101294264A (en) * 2007-04-24 2008-10-29 宝山钢铁股份有限公司 Process for manufacturing type alpha+beta titanium alloy rod bar for rotor impeller vane
CN102230097A (en) * 2011-03-31 2011-11-02 西北有色金属研究院 Preparation method of titanium alloy bars
CN102581188A (en) * 2012-02-29 2012-07-18 湖南金天钛业科技有限公司 Method for machining TC4-DT titanium alloy large-specification slab forged piece
CN102641978A (en) * 2012-05-17 2012-08-22 湖南金天钛业科技有限公司 Method for processing TC18 titanium alloy large-sized section bar
CN103526144A (en) * 2013-11-05 2014-01-22 湖南金天钛业科技有限公司 TC17 titanium alloy large-scale bar free forging method
CN103586380A (en) * 2013-11-08 2014-02-19 中国航空工业集团公司北京航空材料研究院 Cast ingot cogging forging technology for improving structure uniformity of forging stocks of titanium alloy

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS58145323A (en) * 1982-02-22 1983-08-30 Toshiba Corp Forging method of titanium alloy
JP2004091893A (en) * 2002-09-02 2004-03-25 Kobe Steel Ltd High strength titanium alloy
CN101294264A (en) * 2007-04-24 2008-10-29 宝山钢铁股份有限公司 Process for manufacturing type alpha+beta titanium alloy rod bar for rotor impeller vane
CN102230097A (en) * 2011-03-31 2011-11-02 西北有色金属研究院 Preparation method of titanium alloy bars
CN102581188A (en) * 2012-02-29 2012-07-18 湖南金天钛业科技有限公司 Method for machining TC4-DT titanium alloy large-specification slab forged piece
CN102641978A (en) * 2012-05-17 2012-08-22 湖南金天钛业科技有限公司 Method for processing TC18 titanium alloy large-sized section bar
CN103526144A (en) * 2013-11-05 2014-01-22 湖南金天钛业科技有限公司 TC17 titanium alloy large-scale bar free forging method
CN103586380A (en) * 2013-11-08 2014-02-19 中国航空工业集团公司北京航空材料研究院 Cast ingot cogging forging technology for improving structure uniformity of forging stocks of titanium alloy

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