CN108914029A - A method of preventing different metal materials zigzag Interface Cracking - Google Patents
A method of preventing different metal materials zigzag Interface Cracking Download PDFInfo
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- CN108914029A CN108914029A CN201710440357.5A CN201710440357A CN108914029A CN 108914029 A CN108914029 A CN 108914029A CN 201710440357 A CN201710440357 A CN 201710440357A CN 108914029 A CN108914029 A CN 108914029A
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- metal materials
- different metal
- zigzag
- interface
- sawtooth
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D6/00—Heat treatment of ferrous alloys
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Manufacturing & Machinery (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Heat Treatment Of Articles (AREA)
Abstract
The invention discloses a kind of methods for preventing different metal materials zigzag Interface Cracking, belong to material increasing field.The present invention solves the problems, such as that zigzag different metal materials composite members combination interface is easy cracking, different metal materials joint product to temperature is entered furnace held for some time, then with the speed cooling down of 0.8 ~ 1.6 DEG C/min to room temperature；The section of the different metal materials combination interface is zigzag, and is metallurgical bonding interface.Present method solves the biggish different metal materials of difference of linear expansion when carrying out laser gain material manufacture, is easy the problem of interface cracks.
Description
Technical field
The invention belongs to material increasing fields, are related to a kind of heat treatment method of composite material.
Background technique
Homogenous material is unable to satisfy use demand in many cases in life production, often uses two kinds or even multiple material
The corresponding product of composite manufacturing.The increasing material manufacturings skills such as Laser Clad Deposition manufacturing technology, electron beam fuse and plasma fuse
Art there is significant technical advantage, especially graded metal material structure to manufacture the composite manufacturing of different metal materials.
But there are many restrictions for different metal materials composite manufacturing, such as the different melting points of different metal materials, the phase of material
The height of dissolubility, whether there is or not the formation of intermetallic compound, difference of linear expansion, solderability height is low.Wherein, linear expansion coefficient
The material to differ greatly, the composite manufacturing carried out by hot-working easily form crackle in interface in cooling procedure and lack
It falls into, leads to scrap of the product.
The present invention is mentioned for the product of the biggish different metal materials hot-working composite manufacturing one kind of difference of linear expansion
A kind of method that rapid cooling generation Interface Crack is eliminated by heat treatment is supplied.This method is easy to use low in cost.
Summary of the invention
The present invention, when carrying out laser gain material manufacture, is easy for the biggish different metal materials of difference of linear expansion
The problem of interface cracks proposes a kind of new solution.
A kind of method preventing different metal materials zigzag Interface Cracking proposed by the present invention, component to temperature enter furnace and protect
Warm certain time, then with the speed cooling down of 0.8 ~ 1.6 DEG C/min to room temperature, the line of the different metal materials expands system
The difference of number is greater than 3 × 10-6。
The optimal technical scheme of the method for the invention is that the different metal materials are that stainless steel material and cobalt-based close
Golden material, stainless steel and high temperature alloy.
The optimal technical scheme of the method for the invention is that the temperature charging temperature that arrives is 200 ~ 600 DEG C, and soaking time is
30~60min。
The optimal technical scheme of the method for the invention is that the longitudinal section of the different metal materials combination interface is sawtooth
Shape, and be metallurgical melting.
The optimal technical scheme of the method for the invention is that the longitudinal section zigzag is periodically contour isometric sawtooth,
Its parameter is that sawtooth height is：The mm of 0.5 mm ~ 2, screw pitch：0.3~1.5 mm.
The optimal technical scheme of the method for the invention is that the longitudinal section zigzag is periodically not contour sawtooth,
Basic unit is 1 ~ 3 short 1 ~ 3 high sawtooth of jigsaw fit, and the difference in height of short sawtooth and high sawtooth is high for 1 ~ 3 short tooth tooth.
The optimal technical scheme of the method for the invention is, is periodical Length discrepancy saw according to the longitudinal section zigzag
Tooth, a kind of screw pitch of material are 2 ~ 4 times of another material tooth pitch.
The optimal technical scheme of the method for the invention is that the cross section of the different metal materials combination interface is straight
Line, broken line, camber line, circle, semicircle, ellipse, polygon.
Scheme of the present invention can effectively eliminate between dissimilar material, due to big linear expansion coefficient, easily go out when in use
The problem of existing crackle；This programme is more suitable for the biggish dissimilar metal of difference of linear expansion of laser gain material manufacturing method preparation
Material can effectively prevent the generation of crackle, effectively improve the stability in use of material.
Detailed description of the invention
Fig. 1 composite structure.
Specific embodiment
Embodiment 1
The present embodiment is using Laser Clad Deposition manufacturing technology manufacture control nitrogen austenitic stainless steel and 6 cobalt-base alloys of Stellite
Component, and its zigzag Interface Cracking is prevented using heat treatment process of the present invention.
Product members sectional view is as shown in Figure 1.Dash area is control nitrogen austenitic stainless steel in figure, and two side areas is
6 cobalt-base alloys of Stellite.
The product zigzag includes uniform contour sawtooth, and periodically not contour sawtooth, sawtooth area trend is for straight line and tiltedly
Line, interface cross section linearly, broken line and curve shape.
The manufacturing method of the composite component is as follows：
S1：Establish component three-dimensional digital-to-analogue.As shown in Figure 1.
S2：The combination interface of this product includes uniform isometric broached-tooth design, the facewidth（Screw pitch）0.9mm, the high 1.5mm of tooth；Week
Phase property Length discrepancy broached-tooth design, the short high 1.5mm of sawtooth tooth, short sawtooth facewidth 0.9mm, high high 3 mm of sawtooth tooth, the high sawtooth facewidth
1.8mm；There are two types of period sawtooth, and each 1 one is short sawtooth and high sawtooth, another kind is short sawtooth and each 3, high sawtooth, week
Phase arrangement, as shown in Figure 1.
S3：Three-dimensional digital-to-analogue is sliced using Slice Software, slice thickness 0.9mm；Subregion, material are carried out to slice
Boundary respectively translates 0.75mm towards two sides, forms sawtooth combined area, control nitrogen austenitic stainless steel and 6 cobalt-base alloys of Stellite.
S4：Path planning is scanned to slice, exports nc program；
S5：It uses control nitrogen austenitic stainless steel alloy powder and 6 Co-based alloy powder of Stellite for raw material, utilizes laser
Cladding deposit manufacture technology carries out product manufacturing.
Composite element shown in Fig. 1 is obtained by above step, then component is heat-treated.Heat treatment process
For：600 DEG C of holding temperature, soaking time 30min, until room temperature, cooling velocity is 0.8 DEG C/min for furnace cooling.
Metallographic, product members interface flawless is dissected and observed.
Embodiment 2
It is heat-treated after the completion of Laser Clad Deposition manufacture for the product members in embodiment 1.
Heat treatment process is：200 DEG C of holding temperature, soaking time 60min, furnace cooling, cooling velocity be 1.6 DEG C/
min.
Metallographic, product members interface flawless is dissected and observed.
Claims (8)
1. a kind of method for preventing different metal materials zigzag Interface Cracking, which is characterized in that the different metal materials produce
Product enter furnace held for some time to temperature, then with the speed cooling down of 0.8 ~ 1.6 DEG C/min to room temperature；The dissimilar metal material
The longitudinal section for expecting combination interface is zigzag, and is metallurgical melting interface.
2. a kind of method for preventing different metal materials zigzag Interface Cracking described in claim 1, which is characterized in that described different
The difference of the linear expansion coefficient of kind metal material is greater than 3 × 10-6。
3. a kind of method for preventing different metal materials zigzag Interface Cracking described in claim 1, which is characterized in that described different
Kind metal material is stainless steel material and Co-base alloy material, stainless steel and high temperature alloy.
4. a kind of method for preventing different metal materials zigzag Interface Cracking described in claim 1, which is characterized in that described to arrive
Warm charging temperature is 200 ~ 600 DEG C, and soaking time is 30 ~ 60min.
5. a kind of method for preventing different metal materials zigzag Interface Cracking according to claim 1, which is characterized in that institute
Different metal materials combination interface longitudinal section zigzag is stated as periodically contour isometric sawtooth, parameter is that sawtooth height is：0.5
The mm of mm ~ 2, screw pitch：0.3~1.5 mm.
6. a kind of method for preventing different metal materials zigzag Interface Cracking according to claim 1, which is characterized in that institute
Different metal materials combination interface longitudinal section zigzag is stated as periodically not contour sawtooth, basic unit is 1 ~ 3 short sawtooth
Cooperate 1 ~ 3 high sawtooth, the difference in height of short sawtooth and high sawtooth is high for 1 ~ 3 short tooth tooth.
7. a kind of method for preventing different metal materials zigzag Interface Cracking according to claim 1, which is characterized in that institute
Longitudinal section zigzag is stated as periodical Length discrepancy sawtooth, a kind of screw pitch of material is 2 ~ 4 times of another material tooth pitch.
8. a kind of method for preventing different metal materials zigzag Interface Cracking according to claim 1, which is characterized in that institute
The cross section for stating different metal materials combination interface is straight line, broken line, camber line, circle, semicircle, ellipse, polygon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710440357.5A CN108914029A (en) | 2017-06-13 | 2017-06-13 | A method of preventing different metal materials zigzag Interface Cracking |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710440357.5A CN108914029A (en) | 2017-06-13 | 2017-06-13 | A method of preventing different metal materials zigzag Interface Cracking |
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| Publication Number | Publication Date |
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| CN108914029A true CN108914029A (en) | 2018-11-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710440357.5A Withdrawn CN108914029A (en) | 2017-06-13 | 2017-06-13 | A method of preventing different metal materials zigzag Interface Cracking |
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| CN (1) | CN108914029A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115747784A (en) * | 2022-10-11 | 2023-03-07 | 湖北超卓航空科技股份有限公司 | Cold spraying additive interface strength improving method and shaft part lengthening method |
Citations (6)
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|---|---|---|---|---|
| CN102651264A (en) * | 2011-02-25 | 2012-08-29 | 北京有色金属研究总院 | Sintered composite soft magnetic material and method for preparing same |
| CN103160825A (en) * | 2013-03-18 | 2013-06-19 | 张翀昊 | Method for improving metal 3D (three-dimensional) printing compactness by utilizing synchronous double-beam laser |
| CN104684667A (en) * | 2012-10-08 | 2015-06-03 | 西门子公司 | Additive manufacture of turbine component with multiple materials |
| US20150322557A1 (en) * | 2014-05-12 | 2015-11-12 | Alstom Technology Ltd | Method for post-built heat treatment of additively manufactured components made of gamma-prime strengthened superalloys |
| CN105499569A (en) * | 2015-12-24 | 2016-04-20 | 华中科技大学 | Active temperature field regulating and controlling system for manufacturing high-energy beam reinforced material and control method for active temperature field regulating and controlling system |
| US20160108483A1 (en) * | 2014-10-17 | 2016-04-21 | Airbus Group Limited | Method of Additive Manufacturing and Heat Treatment |
-
2017
- 2017-06-13 CN CN201710440357.5A patent/CN108914029A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102651264A (en) * | 2011-02-25 | 2012-08-29 | 北京有色金属研究总院 | Sintered composite soft magnetic material and method for preparing same |
| CN104684667A (en) * | 2012-10-08 | 2015-06-03 | 西门子公司 | Additive manufacture of turbine component with multiple materials |
| CN103160825A (en) * | 2013-03-18 | 2013-06-19 | 张翀昊 | Method for improving metal 3D (three-dimensional) printing compactness by utilizing synchronous double-beam laser |
| US20150322557A1 (en) * | 2014-05-12 | 2015-11-12 | Alstom Technology Ltd | Method for post-built heat treatment of additively manufactured components made of gamma-prime strengthened superalloys |
| US20160108483A1 (en) * | 2014-10-17 | 2016-04-21 | Airbus Group Limited | Method of Additive Manufacturing and Heat Treatment |
| CN105499569A (en) * | 2015-12-24 | 2016-04-20 | 华中科技大学 | Active temperature field regulating and controlling system for manufacturing high-energy beam reinforced material and control method for active temperature field regulating and controlling system |
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| 赵海鸥等: "激光熔覆工艺特性及裂纹敏感性研究", 《金属热处理》 * |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115747784A (en) * | 2022-10-11 | 2023-03-07 | 湖北超卓航空科技股份有限公司 | Cold spraying additive interface strength improving method and shaft part lengthening method |
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Application publication date: 20181130 |