CN104004982A - Stable heat processing method of titanium alloy part - Google Patents
Stable heat processing method of titanium alloy part Download PDFInfo
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- CN104004982A CN104004982A CN201410258243.5A CN201410258243A CN104004982A CN 104004982 A CN104004982 A CN 104004982A CN 201410258243 A CN201410258243 A CN 201410258243A CN 104004982 A CN104004982 A CN 104004982A
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Abstract
The invention provides a stable heat processing method of a titanium alloy part. A stable heat processing clamp is used for processing the titanium alloy part, the problems that residual stress and a structure are not even in the processing process of the titanium alloy part are effectively resolved, and therefore the structural size and the product performance of the titanium alloy part are guaranteed.
Description
Technical field
The present invention relates to a kind of titanium alloy component steady heat processing method, be mainly used in the titanium alloy component after processing to revise, reduce or eliminate the unrelieved stress of Titanium Alloy Aircraft part, improve titanium alloy structure stability.
Background technology
At present, Titanium Alloy Aircraft part is through mechanical workout, and chemistry milling, after can manufacturing or welding processing, can obtain the corresponding and corresponding part of size of structure, is directly used in and produces in product.But in the course of processing, inevitably can produce unrelieved stress, can there is the inhomogeneous situation of weave construction in parts locally, even affects the precision of titanium alloy component.And if in titanium alloy component, unrelieved stress and the inhomogeneous situation of weave construction can not be processed in time, will As time goes on discharge gradually, thereby affect the scantlings of the structure of titanium alloy component and the performance of product.
Summary of the invention
The problem existing in order to solve prior art, the invention provides a kind of titanium alloy component steady heat processing method, adopt and stablize fixture of heat treatment machining titanium alloy part, efficiently solve in the rear titanium alloy component of processing and have unrelieved stress and the inhomogeneous problem of weave construction, thereby ensure the scantlings of the structure of titanium alloy component and the performance of product.
The technical solution used in the present invention is:
A kind of titanium alloy component steady heat processing method, comprises the steps:
1) clean titanium alloy component with acetone,
2) titanium alloy component after cleaning is placed on the base of fixture and is positioned, the briquetting assembly of fixture and the location successively that holds down assembly are placed on titanium alloy component, use the voussoir of fixture to holding down assembly, briquetting assembly, titanium alloy component and base assemble compression
3) fixture that is equipped with titanium alloy component is put into vacuum heat treatment furnace, vacuumizes,
4) vacuum heat treatment furnace is warming up to 300 degree after vacuumizing, after furnace temperature is stable, keeps 30 minutes,
5) and then be warming up to 640-660 degree, after furnace temperature is stable, keep 90 minutes,
6) carry out again stove and be chilled to after 280-200 degree, open vacuum heat treatment furnace, make the fixture air cooling that assembles titanium alloy component to room temperature,
7) titanium alloy component is taken out from fixture, obtain qualified titanium alloy component.
In described titanium alloy component steady heat processing method, the base of described fixture has shape face, and described shape face and qualified titanium alloy component match, and described titanium alloy component is placed on described shape face, and the periphery of described base is provided with lifting assembly.
In described titanium alloy component steady heat processing method, the periphery that holds down assembly of described fixture is provided with ringbolt, holding down assembly is the reticulated structure by crossbeam and vertical beam staggered, and the shape face that described reticulated structure forms and qualified titanium alloy component match.
Described titanium alloy component steady heat processing method, the material of described fixture is TA15 titanium alloy or stainless steel.
A kind of titanium alloy component steady heat of the present invention processing method has following beneficial effect:
The inventive method efficiently solves machined, chemistry milling, after can manufacturing or welding processing, in titanium alloy component, there is unrelieved stress and the inhomogeneous problem of weave construction, ensured the scantlings of the structure of titanium alloy component and the performance of product, meet titanium alloy component in specific environment as the requirement of working under high temperature.Adopt in the methods of the invention unit clamp clamping titanium alloy component, geometrical shape and the dimensional precision of titanium alloy component are not only ensured, shape and the geometric parameter of the titanium alloy component that has not also met accuracy requirement to being shaped are in advance revised, the precision that improves titanium alloy component, makes titanium alloy component meet drawing requirement.
Brief description of the drawings
Fig. 1 is the structural representation with Fixture assembly titanium alloy component in a kind of titanium alloy component steady heat of the present invention processing method.
Fig. 2 is the vertical view of Fig. 1.
Wherein, 1-holds down assembly, 2-base, and 3-briquetting assembly, 4-voussoir, 5-ringbolt, 6-titanium alloy component, 7-lifts by crane assembly, 8-crossbeam, 9-vertical beam.
Embodiment
A kind of titanium alloy component steady heat processing method, comprises the steps:
1) clean titanium alloy component 6 with acetone,
2) titanium alloy component 6 after cleaning is placed on the base 2 of fixture and is positioned, by the briquetting assembly of fixture 3 and hold down assembly 1 successively location be placed on titanium alloy component 6, the voussoir 4 that uses fixture to holding down assembly 1, briquetting assembly 3, titanium alloy component 6 and base 2 assemble compression
3) fixture that is equipped with titanium alloy component 6 is put into vacuum heat treatment furnace, vacuumizes,
4) vacuum heat treatment furnace is warming up to 290-310 degree after vacuumizing, after furnace temperature is stable, keeps 30 minutes,
5) and then be warming up to 650 degree, after furnace temperature is stable, keep 90 minutes,
6) carry out again stove and be chilled to after 280-200 degree, open vacuum heat treatment furnace, make the fixture air cooling that assembles titanium alloy component 6 to room temperature,
7) titanium alloy component 6 is taken out from fixture, obtain qualified titanium alloy component 6.
As shown in Figure 1-2, the fixture in aforesaid method comprises and holds down assembly 1, base 2, briquetting assembly 3, voussoir 4, ringbolt 5, titanium alloy component 6, lifting assembly 7.Base 2 has the shape face of titanium alloy component 6 of placement, and this shape face matches with qualified titanium alloy component, and described titanium alloy component 6 is placed on shape face, and the periphery of base 2 is installed with four lifting assemblies 7, has assembled the fixture of titanium alloy component 6 for movement.1 the periphery of holding down assembly is provided with four ringbolts 5, and holding down assembly 1 is reticulated structure by crossbeam 8 and vertical beam 9 staggereds, and the shape face that this reticulated structure forms and qualified titanium alloy component match.When titanium alloy component 6 is fitted into fixture, first titanium alloy component 6 is placed on the shape face of base 2, carry out conventional location, briquetting assembly 3 is being placed on titanium alloy component by drawing, 1 move on briquetting assembly 3 will hold down assembly by ringbolt 5,1 crossbeam 8 and the staggered compacting briquetting of vertical beam 9 assembly make to hold down assembly, carry out routine location to holding down assembly, will hold down assembly by voussoir 41 and titanium alloy component 6 be fixed on base 2, complete the assembling of fixture to titanium alloy component.Preferably, the material of fixture is TA15 titanium alloy or stainless steel.
Claims (4)
1. a titanium alloy component steady heat processing method, is characterized in that, comprises the steps:
1) clean titanium alloy component with acetone,
2) titanium alloy component after cleaning is placed on the base of fixture and is positioned, the briquetting assembly of fixture and the location successively that holds down assembly are placed on titanium alloy component, use the voussoir of fixture to holding down assembly, briquetting assembly, titanium alloy component and base assemble compression
3) fixture that is equipped with titanium alloy component is put into vacuum heat treatment furnace, vacuumizes,
4) vacuum heat treatment furnace is warming up to 290-310 degree after vacuumizing, after furnace temperature is stable, keeps 30 minutes,
5) and then be warming up to 640-660 degree, after furnace temperature is stable, keep 90 minutes,
6) carry out again stove and be chilled to after 280-200 degree, open vacuum heat treatment furnace, make the fixture air cooling that assembles titanium alloy component to room temperature,
7) titanium alloy component is taken out from fixture.
2. titanium alloy component steady heat processing method according to claim 1, it is characterized in that, the base of described fixture has shape face, and described shape face and titanium alloy component match, described titanium alloy component is placed on described shape face, and the periphery of described base is provided with lifting assembly.
3. titanium alloy component steady heat processing method according to claim 2, it is characterized in that, the periphery that holds down assembly of described fixture is provided with ringbolt, and holding down assembly is the reticulated structure by crossbeam and vertical beam staggered, and shape face and titanium alloy component that described reticulated structure forms match.
4. according to the titanium alloy component steady heat processing method one of claim 1-3 Suo Shu, it is characterized in that, the material of described fixture is TA15 titanium alloy or stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410258243.5A CN104004982B (en) | 2014-06-11 | 2014-06-11 | A kind of titanium alloy component stablizes heat treatment process method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410258243.5A CN104004982B (en) | 2014-06-11 | 2014-06-11 | A kind of titanium alloy component stablizes heat treatment process method |
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| CN104004982A true CN104004982A (en) | 2014-08-27 |
| CN104004982B CN104004982B (en) | 2016-09-21 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104388863A (en) * | 2014-11-28 | 2015-03-04 | 沈阳飞机工业（集团）有限公司 | Method for heat treatment of large-sized titanium alloy frame parts by virtue of special-shaped blocks |
| CN106381373A (en) * | 2016-11-25 | 2017-02-08 | 沈阳黎明航空发动机(集团)有限责任公司 | Correction method and device for plate type multilayered structure titanium alloy parts |
| CN107974653A (en) * | 2017-12-01 | 2018-05-01 | 中国航空工业标准件制造有限责任公司 | A kind of underproof optimization method of titanium-niobium alloy part annealing heat-treats |
| CN108115003A (en) * | 2017-12-18 | 2018-06-05 | 中国航发贵州黎阳航空动力有限公司 | A kind of multilayer metal plate weldment refractory ceramics type face school shape frock and method |
| CN110453165A (en) * | 2019-09-20 | 2019-11-15 | 宁波江丰电子材料股份有限公司 | Cobalt target blankss flatening method and fixture |
| CN114908240A (en) * | 2022-06-01 | 2022-08-16 | 沈阳飞机工业（集团）有限公司 | Heat treatment method of TC4 titanium alloy special-shaped structural part with closed angle area |
| CN115216611A (en) * | 2022-06-22 | 2022-10-21 | 沈阳飞机工业（集团）有限公司 | Aircraft tail cover stabilization heat treatment device |
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| CN201245407Y (en) * | 2008-08-05 | 2009-05-27 | 沈阳飞机工业（集团）有限公司 | Rapid hoisting clamp for thin plate |
| CN202072732U (en) * | 2011-03-14 | 2011-12-14 | 沈阳飞机工业（集团）有限公司 | Detachable heat-treatment fixture |
| CN202072731U (en) * | 2011-03-14 | 2011-12-14 | 沈阳飞机工业（集团）有限公司 | Fixture for heat treatment of large-sized wallboards |
| CN103753099A (en) * | 2014-01-03 | 2014-04-30 | 西安航天动力机械厂 | Device for heat shaping of thin-walled titanium alloy parts |
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| CN201245407Y (en) * | 2008-08-05 | 2009-05-27 | 沈阳飞机工业（集团）有限公司 | Rapid hoisting clamp for thin plate |
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| CN202072731U (en) * | 2011-03-14 | 2011-12-14 | 沈阳飞机工业（集团）有限公司 | Fixture for heat treatment of large-sized wallboards |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104388863A (en) * | 2014-11-28 | 2015-03-04 | 沈阳飞机工业（集团）有限公司 | Method for heat treatment of large-sized titanium alloy frame parts by virtue of special-shaped blocks |
| CN106381373A (en) * | 2016-11-25 | 2017-02-08 | 沈阳黎明航空发动机(集团)有限责任公司 | Correction method and device for plate type multilayered structure titanium alloy parts |
| CN107974653A (en) * | 2017-12-01 | 2018-05-01 | 中国航空工业标准件制造有限责任公司 | A kind of underproof optimization method of titanium-niobium alloy part annealing heat-treats |
| CN108115003A (en) * | 2017-12-18 | 2018-06-05 | 中国航发贵州黎阳航空动力有限公司 | A kind of multilayer metal plate weldment refractory ceramics type face school shape frock and method |
| CN110453165A (en) * | 2019-09-20 | 2019-11-15 | 宁波江丰电子材料股份有限公司 | Cobalt target blankss flatening method and fixture |
| CN114908240A (en) * | 2022-06-01 | 2022-08-16 | 沈阳飞机工业（集团）有限公司 | Heat treatment method of TC4 titanium alloy special-shaped structural part with closed angle area |
| CN115216611A (en) * | 2022-06-22 | 2022-10-21 | 沈阳飞机工业（集团）有限公司 | Aircraft tail cover stabilization heat treatment device |
| CN115216611B (en) * | 2022-06-22 | 2023-10-31 | 沈阳飞机工业（集团）有限公司 | Stable heat treatment device for aircraft tail cover |
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| Publication number | Publication date |
|---|---|
| CN104004982B (en) | 2016-09-21 |
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Effective date of registration: 20201210 Address after: No.20, Shuangji street, Jilin economic and Technological Development Zone, Jilin City, Jilin Province, 132000 Patentee after: JILIN AVIATION MAINTENANCE LLC Address before: 110034 No. 1 Ling Bei street, Huanggu District, Liaoning, Shenyang Patentee before: SHENYANG AIRCRAFT Corp. |
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