CN104404409A - Heat treatment process of Y7 aerofoil girder profile - Google Patents
Heat treatment process of Y7 aerofoil girder profile Download PDFInfo
- Publication number
- CN104404409A CN104404409A CN201410766261.4A CN201410766261A CN104404409A CN 104404409 A CN104404409 A CN 104404409A CN 201410766261 A CN201410766261 A CN 201410766261A CN 104404409 A CN104404409 A CN 104404409A
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- China
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- section bar
- treatment process
- wing crossbeam
- crossbeam section
- wing
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Heat Treatment Of Articles (AREA)
Abstract
The application provides a heat treatment process of a Y7 aerofoil girder profile. The heat treatment process comprises the following step: quenching the Y7 aerofoil girder profile, wherein the quenching temperature is 490-510 DEG C, and the quenching holding time is 195-225 min. Since the Y7 aerofoil girder profile adopts a special profile, and the maximum wall thickness is relatively small, the triaxial mechanical property of the Y7 aerofoil girder profile is stable and relatively high through the optimization of the quenching temperature and the quenching time of the heat treatment process.
Description
Technical field
The present invention relates to technical field of aluminum alloy technology, particularly relate to a kind of thermal treatment process of Y7 wing crossbeam section bar.
Background technology
Y7 aviation series section bar is the important military project section bar of forge works, and along with the change of international situation, this series aerospace materials demand amount is larger.Due to the change of the factors such as technique, equipment and quality control system, between constant product quality and demand, there is outstanding contradiction, main manifestations be exist aborning structure property fluctuation, technological specification meet in the ability of technological standard still inadequate.
Y7 wing crossbeam section bar comprises XC6470 type, XC6471 type, XC6472 type and XC6473 type.Y7 wing crossbeam section bar is the special-shaped aviation section bar of T-shaped, and its thickest is 51 ~ 73mm, and sectional area is minimum is 96cm
2, be section bar minimum in similar shape section bar, it is higher to three-dimensional mechanical property requirements.By technical requirements, mechanical property only samples from head end, and due to Y7 wing crossbeam series section bar mechanical property requirements high, surplus capacity is relatively little, like this may just exist: when head end performance is qualified, and the actual performance of tail end is not necessarily qualified, particularly three-dimensional performance has the section bar of requirement, its head end is horizontal, high very little to surplus capacity, it is completely qualified that its tail end performance is difficult to, therefore, it is very necessary for designing a kind of thermal treatment process to meet the performance requriements of Y7 wing crossbeam series section bar.
Summary of the invention
The technical problem that the present invention solves is the thermal treatment process providing a kind of Y7 wing crossbeam section bar, and thermal treatment process provided by the invention can realize Y7 wing crossbeam section bar three-dimensional stable mechanical property and higher.
This application provides a kind of thermal treatment process of Y7 wing crossbeam section bar, comprising:
Y7 wing crossbeam section bar is carried out quench treatment, and the temperature of described quench treatment is 490 DEG C ~ 510 DEG C, and the soaking time of quench treatment is 195min ~ 225min.
Preferably, the thickest of described Y7 wing crossbeam section bar is 51mm.
Preferably, the temperature of described Y7 wing crossbeam section bar quench treatment is 495 DEG C, and the soaking time of quench treatment is 195min.
Preferably, the thickest of described Y7 wing crossbeam section bar is 53mm.
Preferably, the temperature of described Y7 wing crossbeam section bar quench treatment is 495 DEG C, and the soaking time of quench treatment is 195min.
Preferably, the thickest of described Y7 wing crossbeam section bar is 62mm.
Preferably, the temperature of described Y7 wing crossbeam section bar quench treatment is 495 DEG C, and the soaking time of quench treatment is 195min.
Preferably, the thickest of described Y7 wing crossbeam section bar is 73mm.
Preferably, the temperature of described Y7 wing crossbeam section bar quench treatment is 495 DEG C, and the soaking time of quench treatment is 225min.
This application provides a kind of thermal treatment process of Y7 wing crossbeam section bar, comprising: Y7 wing crossbeam section bar is carried out quench treatment, the temperature of described quench treatment is 490 DEG C ~ 510 DEG C, and the soaking time of quench treatment is 195min ~ 225min.Because Y7 wing crossbeam section bar is the special-shaped aviation section bar of a kind of T-shaped, the application, by optimizing quenching temperature and the cool time of thermal treatment process, make the three-dimensional stable mechanical property of Y7 wing crossbeam section bar, and strength and toughness is all better.
Accompanying drawing explanation
Fig. 1 is XC6470 wing crossbeam section bar sectional view of the present invention.
Embodiment
In order to understand the present invention further, below in conjunction with embodiment, the preferred embodiment of the invention is described, but should be appreciated that these describe just for further illustrating the features and advantages of the present invention, instead of limiting to the claimed invention.
The embodiment of the invention discloses a kind of thermal treatment process of Y7 wing crossbeam section bar, comprising:
Y7 wing crossbeam section bar is carried out quench treatment, and the temperature of described quench treatment is 490 DEG C ~ 510 DEG C, and the soaking time of quench treatment is 195min ~ 225min.
This application provides the thermal treatment process of Y7 wing crossbeam section bar, this thermal treatment process, by optimizing quenching temperature in heat treatment process and soaking time, makes the three-dimensional stable mechanical property of Y7 wing crossbeam section bar and higher.
The special-shaped aviation section bar of goods T-shaped due to Y7 wing crossbeam section bar, thickest is 51mm ~ 73mm, and sectional area is minimum is 96cm
2.Along with the increase of Y7 wing crossbeam section bar thickest, the heat-up rate of metal obviously wants slow, if therefore metal obtains abundant solid solution, should regulate thermal treatment temp and the heat treatment time of Y7 wing crossbeam section bar.
The sectional view of Y7 wing crossbeam section bar XC6470 type described in the application as shown in Figure 1.Y7 wing crossbeam section bar XC6470 type, XC6471 type, XC6472 type and XC6473 type are wing crossbeam section bar well known to those skilled in the art, the application does not do special restriction, not too large difference in the wing crossbeam profile structure of above-mentioned model, just thickest is different.According to the difference of the thickest of above-mentioned wing crossbeam section bar, and have employed different thermal treatment process.In the application, the material of Y7 wing crossbeam section bar is well known to those skilled in the art, and the application is preferably 2A12T4 aluminium alloy.Concrete, for XC6470 section bar, the temperature of described quench treatment is preferably 495 DEG C, and soaking time is preferably 195min, and the type of cooling of described quench treatment is water-cooled, and the water temperature of described water-cooled is preferably 20 ~ 40 DEG C.For XC6471 section bar, the temperature of described quench treatment is preferably 495 DEG C, and the soaking time of described quench treatment is preferably 195min.For XC6472 section bar, the temperature of described quench treatment is preferably 495 DEG C, and the soaking time of described quench treatment is preferably 195min.For XC6473 section bar, the temperature of described quench treatment is preferably 495 DEG C, and the soaking time of described quench treatment is preferably 225min.
Described in the application, the treatment process of Y7 wing crossbeam section bar is that heat treating regime there occurs change, and other technique changes.
This application provides a kind of thermal treatment process of Y7 wing crossbeam section bar, comprising: Y7 wing crossbeam section bar is carried out quench treatment, the temperature of described quench treatment is 490 DEG C ~ 510 DEG C, and the soaking time of quench treatment is 195min ~ 225min.Because Y7 wing crossbeam section bar thickest is thicker and be special-shaped section, the application, by optimizing quenching temperature and the cool time of thermal treatment process, make the three-dimensional stable mechanical property of Y7 wing crossbeam section bar, and strength and toughness is all better.
In order to understand the present invention further, be described in detail below in conjunction with the thermal treatment process of embodiment to Y7 wing crossbeam section bar provided by the invention, protection scope of the present invention is not limited by the following examples.
Embodiment 1
Quenched in air furnace by the wing crossbeam section bar of XC6470,2A12T4, quenching temperature is 495 DEG C, and soaking time is 195min, then cools in the water of 20 DEG C, natural aging.To carry out mechanics properties testing through heat treated wing crossbeam section bar, detected result is as shown in table 1.
Embodiment 2
Quenched in air furnace by the wing crossbeam section bar of XC6471,2A12T4, quenching temperature is 495 DEG C, and soaking time is 195min, then cools in the water of 20 DEG C, natural aging.To carry out mechanics properties testing through heat treated wing crossbeam section bar, detected result is as shown in table 1.
Embodiment 3
Quenched in air furnace by the wing crossbeam section bar of XC6472,2A12T4, quenching temperature is 495 DEG C, and soaking time is 195min, then cools in the water of 30 DEG C, natural aging.To carry out mechanics properties testing through heat treated wing crossbeam section bar, detected result is as shown in table 1.
Embodiment 4
Quenched in air furnace by the wing crossbeam section bar of XC6473,2A12T4, quenching temperature is 495 DEG C, and soaking time is 225min, then cools in the water of 40 DEG C, natural aging.To carry out mechanics properties testing through heat treated wing crossbeam section bar, detected result is as shown in table 1.
The mechanical performance data table of the section bar of table 1 embodiment 1 ~ embodiment 6 preparation
The explanation of above embodiment just understands method of the present invention and core concept thereof for helping.It should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention, can also carry out some improvement and modification to the present invention, these improve and modify and also fall in the protection domain of the claims in the present invention.
To the above-mentioned explanation of the disclosed embodiments, professional and technical personnel in the field are realized or uses the present invention.To be apparent for those skilled in the art to the multiple amendment of these embodiments, General Principle as defined herein can without departing from the spirit or scope of the present invention, realize in other embodiments.Therefore, the present invention can not be restricted to these embodiments shown in this article, but will meet the widest scope consistent with principle disclosed herein and features of novelty.
Claims (9)
1. a thermal treatment process for Y7 wing crossbeam section bar, comprising:
Y7 wing crossbeam section bar is carried out quench treatment, and the temperature of described quench treatment is 490 DEG C ~ 510 DEG C, and the soaking time of quench treatment is 195min ~ 225min.
2. thermal treatment process according to claim 1, is characterized in that, the thickest of described Y7 wing crossbeam section bar is 51mm.
3. thermal treatment process according to claim 2, is characterized in that, the temperature of described Y7 wing crossbeam section bar quench treatment is 495 DEG C, and the soaking time of quench treatment is 195min.
4. thermal treatment process according to claim 1, is characterized in that, the thickest of described Y7 wing crossbeam section bar is 53mm.
5. thermal treatment process according to claim 4, is characterized in that, the temperature of described Y7 wing crossbeam section bar quench treatment is 495 DEG C, and the soaking time of quench treatment is 195min.
6. thermal treatment process according to claim 1, is characterized in that, the thickest of described Y7 wing crossbeam section bar is 62mm.
7. thermal treatment process according to claim 6, is characterized in that, the temperature of described Y7 wing crossbeam section bar quench treatment is 495 DEG C, and the soaking time of quench treatment is 195min.
8. thermal treatment process according to claim 1, is characterized in that, the thickest of described Y7 wing crossbeam section bar is 73mm.
9. thermal treatment process according to claim 8, is characterized in that, the temperature of described Y7 wing crossbeam section bar quench treatment is 495 DEG C, and the soaking time of quench treatment is 225min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410766261.4A CN104404409A (en) | 2014-12-12 | 2014-12-12 | Heat treatment process of Y7 aerofoil girder profile |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410766261.4A CN104404409A (en) | 2014-12-12 | 2014-12-12 | Heat treatment process of Y7 aerofoil girder profile |
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| CN104404409A true CN104404409A (en) | 2015-03-11 |
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| CN201410766261.4A Pending CN104404409A (en) | 2014-12-12 | 2014-12-12 | Heat treatment process of Y7 aerofoil girder profile |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108118271A (en) * | 2017-12-08 | 2018-06-05 | 北京星航机电装备有限公司 | A kind of allotype aluminum alloy bay section method for controlling heat treatment deformation |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101484604A (en) * | 2006-07-07 | 2009-07-15 | 阿勒里斯铝业科布伦茨有限公司 | Aa7000-series aluminium alloy products and a method of manufacturing thereof |
| CN103045972A (en) * | 2012-12-11 | 2013-04-17 | 上海市电力公司 | Quenching process of aluminum alloy tubular bus |
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2014
- 2014-12-12 CN CN201410766261.4A patent/CN104404409A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101484604A (en) * | 2006-07-07 | 2009-07-15 | 阿勒里斯铝业科布伦茨有限公司 | Aa7000-series aluminium alloy products and a method of manufacturing thereof |
| CN103045972A (en) * | 2012-12-11 | 2013-04-17 | 上海市电力公司 | Quenching process of aluminum alloy tubular bus |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108118271A (en) * | 2017-12-08 | 2018-06-05 | 北京星航机电装备有限公司 | A kind of allotype aluminum alloy bay section method for controlling heat treatment deformation |
| CN108118271B (en) * | 2017-12-08 | 2019-08-06 | 北京星航机电装备有限公司 | A kind of allotype aluminum alloy bay section method for controlling heat treatment deformation |
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Application publication date: 20150311 |
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