CN109513925A - The big temperature gradient structural member of thin-walled and its laser direct deposition preparation method - Google Patents
The big temperature gradient structural member of thin-walled and its laser direct deposition preparation method Download PDFInfo
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- CN109513925A CN109513925A CN201811465224.4A CN201811465224A CN109513925A CN 109513925 A CN109513925 A CN 109513925A CN 201811465224 A CN201811465224 A CN 201811465224A CN 109513925 A CN109513925 A CN 109513925A
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- 230000008021 deposition Effects 0.000 title claims abstract description 112
- 238000002360 preparation method Methods 0.000 title claims abstract description 37
- 239000000463 material Substances 0.000 claims abstract description 86
- 230000007704 transition Effects 0.000 claims abstract description 81
- 239000000203 mixture Substances 0.000 claims abstract description 4
- 239000010410 layer Substances 0.000 claims description 198
- 239000002356 single layer Substances 0.000 claims description 28
- 239000000843 powder Substances 0.000 claims description 27
- 238000000034 method Methods 0.000 claims description 18
- 238000012545 processing Methods 0.000 claims description 14
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 8
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 4
- 238000007689 inspection Methods 0.000 claims description 4
- 229910052760 oxygen Inorganic materials 0.000 claims description 4
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- 229910000765 intermetallic Inorganic materials 0.000 claims description 3
- 238000000465 moulding Methods 0.000 claims description 3
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- 229910004349 Ti-Al Inorganic materials 0.000 claims 1
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- 230000008646 thermal stress Effects 0.000 abstract description 5
- 238000000151 deposition Methods 0.000 description 95
- 230000015572 biosynthetic process Effects 0.000 description 11
- 229910045601 alloy Inorganic materials 0.000 description 10
- 239000000956 alloy Substances 0.000 description 10
- 230000008569 process Effects 0.000 description 10
- 238000012797 qualification Methods 0.000 description 7
- 238000010438 heat treatment Methods 0.000 description 6
- 238000000137 annealing Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 238000011017 operating method Methods 0.000 description 4
- 238000001556 precipitation Methods 0.000 description 4
- 239000010936 titanium Substances 0.000 description 4
- 208000037656 Respiratory Sounds Diseases 0.000 description 3
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- 238000005137 deposition process Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
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- 238000005516 engineering process Methods 0.000 description 3
- 239000004615 ingredient Substances 0.000 description 3
- 239000000758 substrate Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000003475 lamination Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
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- 230000036244 malformation Effects 0.000 description 1
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- 230000004044 response Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
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- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
- B22F10/25—Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
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- B22F12/00—Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
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- C—CHEMISTRY; METALLURGY
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- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
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Abstract
The invention discloses a kind of big temperature gradient structural members of thin-walled.A kind of big temperature gradient structural member of thin-walled, the temperature gradient direction along the structural member successively include: medium temperature layer, temperature gradient transition zone, high temperature basal layer and heat zone；Wherein, the group of temperature gradient transition zone is divided into the mixture of medium temperature layer and heat zone material, and the material of high temperature basal layer is identical as heat zone material, and temperature gradient transition zone and high temperature basal layer are for reducing the structural stress and thermal stress of big temperature gradient structural member.The invention also discloses a kind of laser direct deposition preparation methods of the big temperature gradient structural member of thin-walled.The present invention increases temperature gradient transition zone, high temperature basal layer in dissimilar material gradient-structure, temperature gradient transition zone realizes the uniform and stable transition of buffer layer material, temperature gradient transition zone and high temperature basal layer deposition velocity are slower, gradient-structure structural stress and thermal stress are reduced, the structure-integrated forming of the big temperature gradient of dissimilar material is realized.
Description
Technical field
The invention belongs to metal special type forming technique field, it is related to a kind of big temperature gradient structural member of thin-walled and its swashs
Light Direct precipitation preparation method.
Background technique
For aircraft during high-speed flight, the temperature gradient at each position is very big, such as air intake duct temperatures at localized regions
Up to 700 DEG C~800 DEG C, the material manufacture using high temperature resistant, high intensity, high rigidity is needed, and other spot temperatures are lower, it is general
Logical titanium alloy is just able to satisfy requirement.By be integrated the big temperature gradient structural member of titanium alloy with different performance with
Make its monolithic molding, at lower cost realize part different parts use temperature requirement, not only eliminate components connection and
Sealing problem, it is often more important that improve the integral strength and rigidity of part.
Prepare big temperature gradient structural member using laser direct deposition has its peculiar tired compared with preparing single material material
Difficulty prepares big temperature gradient structural member and selects dissimilar material powder, since the physicochemical property of material is different, will cause fusing and coagulates
Gu process is different, it is easy to produce objectionable impurities or micro-crack；In addition, for thin-wall construction, it is easier to because of material composition and
Stress caused by performance is mutated is concentrated and leads to malformation, and structure precision is influenced.In response to this, people need to existing
Method improves the defect to overcome existing laser direct deposition.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, providing a kind of performance, to stablize transition, integral strength higher, no
It is also easy to produce the big temperature gradient structural member of thin-walled and its laser direct deposition preparation method of crackle.This method carries out before deposition
Reasonable transition zone design and processes design, makes the structure property of transitional region form the shape of steady and continuous with deposition fraction
State, retention property is consistent, increases the integral strength of structural member, avoids the generation of crackle；In addition, preparing gradient-structure
When, the variation for component changes deposition process parameters, keeps the transition zone structure property of deposition good, to keep higher whole
Body intensity.
Technical solution of the invention:
A kind of big temperature gradient structural member of thin-walled, the temperature gradient direction along the structural member successively includes: medium temperature layer, temperature
Spend gradient transitional lay, high temperature basal layer and heat zone；Wherein, the group of temperature gradient transition zone is divided into medium temperature layer and heat zone material
Mixture, the material of high temperature basal layer is identical as heat zone material, and temperature gradient transition zone and high temperature basal layer are for reducing
The structural stress and thermal stress of big temperature gradient structural member.
In the present invention, high temperature basal layer can make temperature as the structure sheaf between temperature gradient transition zone and heat zone
Gradient transitional lay and heat zone performance continuous-stable are spent, to guarantee structural member integral strength.
In the big temperature gradient structural member of above-mentioned thin-walled, temperature gradient transition zone is total as a preferred implementation manner,
Thickness (i.e. the short transverse of whole knot component) is 0.8~2mm.
In the big temperature gradient structural member of above-mentioned thin-walled, the overall thickness of high temperature basal layer as a preferred implementation manner,
(i.e. the short transverse of whole knot component) is 1~2mm.
In the big temperature gradient structural member of above-mentioned thin-walled, the temperature gradient transition zone as a preferred implementation manner,
Including at least two sublayers, medium temperature layer material mass percentage is greater than 50% in the sublayer of the medium temperature layer, close to institute
The mass percentage for stating the sublayer high temperature layer material of high temperature basal layer is greater than 50%；Preferably, the temperature gradient transition
Layer includes three sublayers, and medium temperature layer material mass percentage is 60-70%, intermediate part-layer in the sublayer of the medium temperature layer
Medium temperature layer material mass percentage is identical as heat zone material mass percentage, close to the sublayer of the high temperature basal layer
The mass percentage of high temperature layer material is greater than 60-70%.
In the big temperature gradient structural member of above-mentioned thin-walled, the medium temperature layer material is to make as a preferred implementation manner,
With 400 DEG C of titanium alloys below of temperature, the material of the heat zone is high-temperature titanium alloy or Ti- using 500 DEG C of temperature or more
Al intermetallic compound.
A kind of laser direct deposition preparation method of the big temperature gradient structural member of thin-walled, the big temperature gradient structural member
It is an integral molding structure part, the temperature gradient direction along the structural member at least successively includes: medium temperature layer, temperature gradient transition
Layer, high temperature basal layer and heat zone, the preparation method include:
The first step, initialization laser forming equipment；
Then the threedimensional model of second step, the building structural member carries out subdivision to threedimensional model to generate laser scanning
Path；
The selection of each layer material of third step, the structural member, wherein the component of temperature gradient transition zone include medium temperature layer and
The material of the material of heat zone, high temperature basal layer is identical as heat zone material；
4th step carries out laser direct deposition processing according to the material of the medium temperature layer to form medium temperature layer；
5th step is directly sunk according to the component proportion of the temperature gradient transition zone in medium temperature layer surface progress laser
Product processing is to form the temperature gradient transition zone；
6th step carries out at laser direct deposition according to the material of high temperature basal layer in the temperature gradient transition layer surface
Reason is to form high temperature basal layer；
7th step carries out laser direct deposition processing in the layer surface of the high temperature basis according to the material of heat zone with shape
At heat zone.
In above-mentioned laser direct deposition preparation method, the method also includes at heat as a preferred implementation manner,
Step is managed, the blank for structural product that the 7th step obtains is heat-treated；Preferably, the temperature of the heat treatment is 500-
650 DEG C, soaking time 1.5-2.5h, specific heat treatment temperature and time change with material and are changed.
In above-mentioned laser direct deposition preparation method, the medium temperature layer material is to make as a preferred implementation manner,
With 400 DEG C of titanium alloys below of temperature, the material of the heat zone is high-temperature titanium alloy or Ti- using 500 DEG C of temperature or more
Al intermetallic compound.
In above-mentioned laser direct deposition preparation method, the temperature gradient transition zone as a preferred implementation manner,
Including at least two sublayers, medium temperature layer material mass percentage is greater than 50% in the sublayer of the medium temperature layer, close to institute
The mass percentage for stating the sublayer high temperature layer material of high temperature basal layer is greater than 50%.It is highly preferred that the temperature gradient mistake
Crossing layer includes three sublayers, and medium temperature layer material mass percentage is 60-70% in the sublayer of the medium temperature layer, intermediate son
Medium temperature layer material mass percentage is identical as heat zone material mass percentage in layer, close to the son of the high temperature basal layer
The mass percentage of layer high temperature layer material is greater than 60-70%.
In above-mentioned laser direct deposition preparation method, temperature gradient transition zone is total as a preferred implementation manner,
Thickness (i.e. short transverse or temperature gradient direction) is 0.8~2mm, and the thickness of transition zone and high temperature basal layer will be blocked up will affect
Preparation efficiency, and the integral strength of structural member will not be obviously increased；It is too thin, it is whole that enhancing structure part well cannot be played
The effect of intensity.
In above-mentioned laser direct deposition method, the overall thickness of high temperature basal layer is (i.e. high as a preferred implementation manner,
Spend direction or temperature gradient direction) it is 1~2mm.
In above-mentioned laser direct deposition preparation method, the initialization laser forming as a preferred implementation manner,
Equipment includes: to carry out each systems inspection and preparation in laser direct deposition equipment, this step preparation is that this field is public
Know technology, open atmosphere protection system, makes oxygen content lower than 50ppm；
In above-mentioned laser direct deposition preparation method, as a preferred implementation manner, in the second step, utilize
3 d modeling software Siemens NX establishes the threedimensional model of the structural member, using laser direct deposition equipment (i.e. laser at
Shape equipment) included subdivision software carries out subdivision, medium temperature layer and heat zone subdivision 0.4~0.6mm of thickness in monolayer to the threedimensional model,
Gradient transitional lay and high temperature basal layer subdivision 0.1~0.2mm of thickness in monolayer, by the CNC program (laser scanning of subdivision Software Create
Path) input laser direct deposition equipment；
In above-mentioned laser direct deposition preparation method, as a preferred implementation manner, in the third step, it will tie
The powder feeder as numerical control variate-value input laser direct deposition equipment such as component proportion and thickness in monolayer of each layer raw material of component
Digital control system, the powder feeding ratio and powder feeding rate of different location when controlling laser direct deposition；Powder feeding rate and scanning speed, list
The parameters such as layer deposition thickness are related, and the powder feeding rate of usual medium temperature layer and heat zone is preferably 1.5~3g/min；Temperature gradient mistake
Cross layer, the powder feeding rate of high temperature basal layer is preferably 0.8~1g/min.
In above-mentioned laser direct deposition method, as a preferred implementation manner, in the 4th step, medium temperature is formed
The technological parameter of the laser direct deposition processing of layer includes: 4~6mm/s of scanning speed, 1200~1800W of laser power, single layer
0.4~0.6mm of deposition thickness；The technological parameter is too high or too low, influences structural member intensity and qualification rate, total layer of deposition
Number is determined by the medium temperature layer height of prepared structural member.
In above-mentioned laser direct deposition preparation method, as a preferred implementation manner, in the 5th step, formed
The technological parameter of the laser direct deposition processing of the temperature gradient transition zone includes: 1.5~2.5mm/s of scanning speed, laser
800~1200W of power, 0.1~0.2mm of monolayer deposition thickness (transition zone overall thickness is 0.8~2mm)；It is highly preferred that described swash
800~1000W of optical power.
Transition zone is divided into several laser scanning layers on the thickness direction (i.e. the short transverse of structural member) of layer, often
A laser scanning layer guarantees that two kinds of material powder sending quantity variations are consistent, realizes the uniform and stable transition of buffer layer material；
In above-mentioned laser direct deposition preparation method, as a preferred implementation manner, in the 6th step, formed
The technological parameter of the laser direct deposition processing of the high temperature basal layer includes: 1.5~2.5mm/s of scanning speed, laser power
800~1200W, 0.1~0.2mm of monolayer deposition thickness；It is highly preferred that 800~the 1000W of laser power.
In transition zone and high temperature basal layer preparation step, scanning speed, laser power are swept less than the 4th step medium temperature layer
Speed, laser power are retouched, to reduce the structural stress and thermal stress of structure, continues deposition 5~10 on temperature gradient transition zone
After layer (high temperature basal layer overall thickness is 1~2mm), high temperature basal layer is formed；High temperature basal layer is blocked up will to largely effect on structural member
Producing efficiency.
In above-mentioned laser direct deposition preparation method, as a preferred implementation manner, in the 7th step, formed
The technological parameter of the laser direct deposition processing of the heat zone includes: that (scanning speed is 4~6mm/s of scanning speed herein
Scan linear velocity), 1200~1800W of laser power, 0.4~0.6mm of monolayer deposition thickness；By the mistake of transition zone and basal layer
It crosses, heat zone has been converted to the preparation of single material, and relevant parameter is turned up in form stable at this time, and forming efficiency can be improved.Deposition
Total number of plies determined by the high temperature layer height of prepared structural member.
On the basis of high temperature basal layer, synchronous height adjusting scanning speed, laser power improve forming efficiency, carry out uniformly steady
Figuration, until end of embarking on journey.
After blank removes working chamber, powder is glued on surface and is removed completely, then blank is put into heat-treatment furnace, is carried out
Stress relief annealing process (specific heat treatment process is depending on gradient-structure material therefor).
The present invention is not specially limited the wall thickness of the big temperature gradient structural member of the thin-walled, but the method for this law is especially suitable
Being used to prepare wall thickness is 2mm structural member below.
The present invention compared with prior art the utility model has the advantages that
(1) present invention increases temperature gradient transition zone, high temperature basal layer, temperature gradient mistake in dissimilar material gradient-structure
Crossing layer realizes the uniform and stable transition of buffer layer material, and temperature gradient transition zone and high temperature basal layer deposition velocity are slower, subtract
Small gradient-structure structural stress and thermal stress, realize the structure-integrated forming of the big temperature gradient of dissimilar material, improve whole
The intensity of body structural member；
(2) present invention reduces material because ingredient and performance are mutated using the gradually transition of big temperature gradient structural material
Caused stress is concentrated, and thin-wall construction deformation is effectively inhibited；
(3) present invention is by the stress relief annealing process after integral forming, while carrying out dissimilar material tissue modulation, protects
It is consistent to hold performance, it is uniform and stable to realize big temperature gradient structure organization, eliminates cracking risk.
Detailed description of the invention
Fig. 1 is medium temperature layer of the present invention, gradient transitional lay and high temperature basal layer laser direct deposition schematic diagram；
Fig. 2 is cone cylinder structured high temperature layer laser direct deposition schematic diagram of the present invention；
Fig. 3 is cylindrical structure heat zone laser direct deposition schematic diagram of the present invention；
Fig. 4 is flow chart of the present invention.
Detailed description of the invention: 1,2 be powder feeder；3 be turntable；4 be cylinder；5 be the conical surface.
Specific embodiment
Below in conjunction with drawings and concrete examples, the present invention is described in detail.
Embodiment 1
The big temperature gradient cone cylinder structural member of TA15/Ti2AlNb thin-walled is prepared using laser direct deposition, as shown in Fig. 2,
The hollow revolving body (i.e. cone cylinder structural member) formed, wall thickness are connected by cylinder 4 and the conical surface 5 using the preparation of laser direct deposition equipment
2mm, cylinder material (canister portion material) are TA15 alloy, and conical surface material (tapering material) is Ti2AlNb alloy, cylinder end (canister portion)
Diameter phi 160mm, height 100mm, conical surface big end (tapering big end) diameter phi 200mm, revolving body total height 200mm, 3 be production
The turntable of rotary structure part.
The first step, initialization laser forming equipment.
Laser direct deposition equipment LSF- III (laser CP4000) each systems inspection and preparation are carried out, atmosphere is opened
Protection system makes oxygen content lower than 50ppm, TA15 and Ti2AlNb alloy powder is respectively charged into powder feeder 1 and 2；
Second step generates laser beam scan path.
Gradient-structure threedimensional model is established using 3 d modeling software Siemens NX, certainly using laser direct deposition equipment
Band subdivision software carries out subdivision to the threedimensional model, by CNC program (laser beam scan path) input equipment of subdivision Software Create；
Third step, the design of gradient-structure ingredient.
The component proportion of big temperature gradient structural member different location is designed, medium temperature layer, that is, cylinder partial material is TA15,
Heat zone, that is, tapered portion material is Ti2AlNb, gradient transitional lay is designed as three layers, first layer (close to medium temperature layer)
60wt%TA15/40wt%Ti2AlNb, second layer 50wt%TA15/50wt%Ti2AlNb, third layer is (close to high temperature basis
Layer) 40wt%TA15/60wt%Ti2AlNb, by the powder feeder numerical control system of this numerical control variate-value input laser direct deposition equipment
System, the powder feeding ratio of different location when controlling laser direct deposition；
4th step, medium temperature layer laser direct deposition.
The deposition of TA15 alloy component is carried out first on substrate, as shown in Figure 1, technological parameter is arranged are as follows: scan angle speed
It spends 2.87 °/s (linear velocity 4mm/s), laser power 1500W, monolayer deposition thickness 0.4mm, is co-deposited 250 layers of (thickness
100mm), it completes TA15 alloy component and stablizes fast deposition；
5th step, temperature gradient transition zone laser direct deposition.
Above-mentioned three layers of transition zone is divided into several laser scanning layers on layer thickness direction, each laser scanning layer is protected
It is consistent to demonstrate,prove two kinds of material powder sending quantity variations, realizes the uniform and stable transition of buffer layer material TA15/Ti2AlNb.Technological parameter is set
Be set to: scanning speed 2mm/s, laser power 1000W, monolayer deposition thickness 0.1mm deposit 10 layers of (thickness on medium temperature layer
1mm, wherein the overall thickness of First Transition layer is 0.3mm, and the overall thickness of the second transition zone is 0.3mm, the total thickness of third transition zone
Degree is 0.4mm), formation temperature gradient layer；
6th step, high temperature basal layer laser direct deposition, basis of formation sedimentary.
After thermal gradient layer deposits, depositing Ti 2AlNb basal layer, technological parameter setting are as follows: scanning speed 2mm/s,
Laser power 1000W, monolayer deposition thickness 0.2mm continue to deposit 10 layers (thickness 2mm), basis of formation deposition on transition zone
Layer；
7th step, heat zone stabilized lasers Direct precipitation.
By 15 ° of the rotation of turntable 3 (or being inclination), (because the embodiment is that big temperature gradient air intake duct part is in kind, 5 be to expand
Section is opened, the part is higher using temperature, therefore, is set as the conical surface in Fig. 2 5), 5 stably depositing of heat zone is carried out, such as Fig. 2 institute
Show.Technological parameter are as follows: scanning speed 4mm/s, laser power 1600W, monolayer deposition thickness 0.5mm, in deposition process, scan angle
Speed is variable angular velocity, to guarantee that identical scanning line rate, angular speed should accordingly reduce, is co-deposited 207 layers of (thickness
103.5mm) terminate forming process (when the deposition parameter of heat zone is all higher than medium temperature layer, effect can be more preferable)；
8th step is heat-treated after gradient-structure laser direct deposition.
After blank removes working chamber, powder is glued on surface and is removed completely, then blank is put into heat-treatment furnace, to hair
Blank carries out the stress relief annealing process of " 550 DEG C × 2h, air-cooled ".
Unspecified part of the present invention is known to the skilled person technology.
The structural member that the embodiment obtains is undeformed and precision is good, according to GB/T 228.1-2010 " metal room temperature tensile
Test method " measure structural member integral strength be 1091Mpa, transition zone and high temperature basal layer position flawless, product qualification rate
Reach 95% or more.
Embodiment 2
Using laser direct deposition prepare the big temperature gradient cylindrical structure part of TA15/Ti2AlNb thin-walled, diameter phi 150mm,
Wall thickness 2mm, lower end material are TA15, and height 100mm, upper end material is Ti2AlNb, height 50mm.
The first step, initialization laser forming equipment.
Laser direct deposition equipment LSF- III (laser CP4000) each systems inspection and preparation are carried out, atmosphere is opened
Protection system makes oxygen content lower than 50ppm, TA15 and Ti2AlNb alloy powder is respectively charged into powder feeder 1 and 2；
Second step generates laser beam scan path.
Gradient-structure threedimensional model is established using 3 d modeling software Siemens NX, certainly using laser direct deposition equipment
Band subdivision software carries out subdivision to the threedimensional model, by CNC program (laser beam scan path) input equipment of subdivision Software Create；
Third step, the design of gradient-structure ingredient.
The component proportion of big temperature gradient structure different location is designed, medium temperature layer material is TA15, and the material of heat zone is
Transition zone is designed as two layers by Ti2AlNb, first layer (close to medium temperature layer) 60wt%TA15/40wt%Ti2AlNb, the second layer
This numerical control variate-value is inputted powder feeder digital control system, control by (close to high temperature basal layer) 40wt%TA15/60wt%Ti2AlNb
The powder feeding ratio of different location when laser direct deposition processed；
4th step, medium temperature layer laser direct deposition.
The deposition of TA15 alloy component is carried out first on substrate, as shown in figure 3, technological parameter is arranged are as follows: scanning speed
5mm/s, laser power 1600W, monolayer deposition thickness 0.5mm are co-deposited 200 layers (thickness 100mm), complete TA15 alloy component
Stablize fast deposition；
5th step, thermal gradient layer laser direct deposition.
Above-mentioned two layers of transition zone is divided into several laser scanning layers in a thickness direction, each laser scanning layer guarantees
Two kinds of material powder sending quantity variations are consistent, realize the uniform and stable transition of buffer layer material TA15/Ti2AlNb.Technological parameter setting
Are as follows: scanning speed 2mm/s, laser power 1200W, monolayer deposition thickness 0.1mm, on medium temperature layer deposit 8 layers (thickness 0.8mm,
Wherein, the overall thickness of First Transition layer is 0.2mm, and the overall thickness of the second transition zone is 0.3mm, and the overall thickness of third transition zone is
0.3mm), formation temperature gradient layer；
6th step, high temperature basal layer laser direct deposition, basis of formation sedimentary.
After thermal gradient layer deposits, depositing Ti 2AlNb basal layer, technological parameter setting are as follows: scanning speed 2mm/s,
Laser power 1200W, monolayer deposition thickness 0.15mm continue to deposit 10 layers (thickness 1.5mm) on transition zone, and basis of formation is heavy
Lamination；
7th step, heat zone stabilized lasers Direct precipitation.
6 stably depositing of heat zone is carried out, as shown in Figure 3.Technological parameter are as follows: scanning speed 6mm/s, laser power 1800W,
Monolayer deposition thickness 0.5mm, being co-deposited 100 layers (thickness 50mm) terminates forming process；
8th step is heat-treated after gradient-structure laser direct deposition.
After blank removes working chamber, powder is glued on surface and is removed completely, then blank is put into heat-treatment furnace, to hair
Blank carries out the stress relief annealing process of " 550 DEG C × 2h, air-cooled ".
Unspecified part of the present invention is known to the skilled person technology.
The structural member that the embodiment obtains is undeformed and precision is good, integral strength 1051Mpa, transition zone and high temperature base
Plinth layer position flawless, product qualification rate reach 95% or more.
Embodiment 3
The present embodiment is 0.6mm (thickness of three layers of transition zone is 0.2mm), high temperature basal layer except the overall thickness of transition zone
Overall thickness be 0.5mm other than, other steps are same as Example 1.
Gradient transitional lay and high temperature basal layer are also easy to produce crackle or cause in the structural member preparation process that the embodiment obtains
Structural member deformation, influences product qualification rate.
Embodiment 4
The present embodiment except transition zone overall thickness be 3mm (thickness of three layers of transition zone is 1mm), high temperature basal layer it is total
Other than 3mm, other steps are same as Example 1.
The structural member gradient transitional lay and high temperature basal layer preparation time that the embodiment obtains are longer, influence structural member forming
Efficiency.
Embodiment 5
In addition to the technological parameter of the 5th step and the 6th step is different from embodiment 1, other operating procedures and method and implementation
Example 1 is identical.5th step of the present embodiment and the 6th step are as follows:
Step 5: above-mentioned three layers of transition zone is divided into several laser scanning layers, each laser on layer thickness direction
Scanning slice guarantees that two kinds of material powder sending quantity variations are consistent, realizes the uniform and stable transition of buffer layer material TA15/Ti2AlNb.Work
Skill parameter setting are as follows: scanning speed 3mm/s, laser power 1300W, monolayer deposition thickness 0.3mm deposit 3 layers on medium temperature layer
(thickness 0.9mm, wherein the overall thickness of First Transition layer is 0.3mm, and the overall thickness of the second transition zone is 0.3mm, third transition
The overall thickness of layer is 0.3mm), formation temperature gradient layer；
6th step, after thermal gradient layer deposits, depositing Ti 2AlNb basal layer, technological parameter setting are as follows: scanning speed
3mm/s, laser power 1300W, monolayer deposition thickness 0.4mm continue to deposit 5 layers (thickness 2mm), basis of formation on transition zone
Sedimentary.
The integral strength for the structural member that the embodiment obtains is 1002Mpa, and product qualification rate reaches 70%.
Embodiment 6
In addition to the technological parameter of the four to seven step is different from embodiment 1, other operating procedures and method and 1 phase of embodiment
Together.Four to seven step of the present embodiment is as follows:
4th step, medium temperature layer laser direct deposition.
The deposition of TA15 alloy component is carried out first on substrate, as shown in Figure 1, technological parameter is arranged are as follows: scanning speed
6mm/s, laser power 1800W, monolayer deposition thickness 0.6mm are co-deposited 167 layers (thickness 100mm), complete TA15 alloy component
Stablize fast deposition；
5th step, temperature gradient transition zone laser direct deposition.
Above-mentioned three layers of transition zone is divided into several laser scanning layers on layer thickness direction, each laser scanning layer is protected
It is consistent to demonstrate,prove two kinds of material powder sending quantity variations, realizes the uniform and stable transition of buffer layer material TA15/Ti2AlNb.Technological parameter is set
Be set to: scanning speed 2.5mm/s, laser power 1200W, monolayer deposition thickness 0.15mm deposit 7 layers of (thickness on medium temperature layer
1mm, wherein the overall thickness of First Transition layer is 0.3mm, and the overall thickness of the second transition zone is 0.3mm, the total thickness of third transition zone
Degree is 0.4mm), formation temperature gradient layer；
6th step, high temperature basal layer laser direct deposition, basis of formation sedimentary.
After thermal gradient layer deposits, depositing Ti 2AlNb basal layer, technological parameter setting are as follows: scanning speed 2.5mm/
S, laser power 1200W, monolayer deposition thickness 0.15mm continue to deposit 14 layers (thickness 2mm) on transition zone, and basis of formation is heavy
Lamination；
7th step, heat zone stabilized lasers Direct precipitation.
By 15 ° of the rotation of turntable 3 (or being inclination), 5 stably depositing of heat zone is carried out, as shown in Figure 2.Technological parameter are as follows:
Scanning speed 6mm/s, laser power 1800W, monolayer deposition thickness 0.5mm, in deposition process, angular scanning speed is angle speed
Degree, to guarantee that identical scanning line rate, angular speed should accordingly reduce, being co-deposited 207 layers (thickness 103.5mm) terminates forming
Process.
The integral strength for the structural member that the embodiment obtains is 1025Mpa, and product qualification rate reaches 90%.
Embodiment 7
For the present embodiment other than gradient transitional lay only has one layer, other steps are same as Example 1, the component of transition zone
For 50wt% medium temperature layer material and 50wt% heat zone material.
The integral strength for the structural member that the embodiment obtains is 1020Mpa, and product qualification rate reaches 80%.
Comparative example 1
This comparative example, which is removed, is omitted the 6th step of embodiment 1, other than high temperature basal layer laser direct deposition, other steps with
Embodiment 1 is identical.
It cracks, can not be continued to complete between gradient transitional lay and heat zone in the structural member preparation process that the comparative example obtains
Heat zone preparation.
Claims (10)
1. a kind of big temperature gradient structural member of thin-walled, which is characterized in that the temperature gradient direction along the structural member successively includes:
Medium temperature layer, temperature gradient transition zone, high temperature basal layer and heat zone；
Wherein, the group of temperature gradient transition zone is divided into the mixture of medium temperature layer and heat zone material, the material of high temperature basal layer with
Heat zone material is identical, and the structural stress and heat that temperature gradient transition zone and high temperature basal layer are used to reduce the structural member are answered
Power.
2. the big temperature gradient structural member of thin-walled according to claim 1, which is characterized in that the temperature gradient transition zone
Overall thickness is 0.8~2mm；Preferably, the overall thickness of high temperature basal layer is 1~2mm.
3. the big temperature gradient structural member of thin-walled according to claim 1, which is characterized in that the temperature gradient transition zone packet
At least two sublayers are included, medium temperature layer material mass percentage is greater than 50% in the sublayer of the medium temperature layer, close to described
The mass percentage of the sublayer high temperature layer material of high temperature basal layer is greater than 50%；Preferably, the temperature gradient transition zone
Including three sublayers, medium temperature layer material mass percentage is 60-70% in the sublayer of the medium temperature layer, in intermediate part-layer
Medium temperature layer material mass percentage is identical as heat zone material mass percentage, in the sublayer of the high temperature basal layer
The mass percentage of heat zone material is greater than 60-70%.
4. the big temperature gradient structural member of thin-walled according to claim 1, which is characterized in that the medium temperature layer material is to use
400 DEG C of titanium alloys below of temperature, the material of the heat zone are high-temperature titanium alloy or Ti-Al using 500 DEG C of temperature or more
Intermetallic compound.
5. a kind of laser direct deposition preparation side of the big temperature gradient structural member of thin-walled of any of claims 1-4
Method, which is characterized in that the structural member is an integral molding structure part, at least successively wraps along the temperature gradient direction of the structural member
Include: medium temperature layer, temperature gradient transition zone, high temperature basal layer and heat zone, the preparation method include:
The first step, initialization laser forming equipment；
Then the threedimensional model of second step, the building structural member carries out subdivision to threedimensional model to generate laser beam scan path；
The selection of each layer raw material material of third step, the structural member, wherein the component of temperature gradient transition zone include medium temperature layer and
The material of the material of heat zone, high temperature basal layer is identical as heat zone material；
4th step carries out laser direct deposition processing according to the material of the medium temperature layer to form medium temperature layer；
5th step carries out at laser direct deposition according to the component proportion of the temperature gradient transition zone in the medium temperature layer surface
Reason is to form the temperature gradient transition zone；
6th step, according to the material of high temperature basal layer the temperature gradient transition layer surface carry out laser direct deposition processing with
Form high temperature basal layer；
7th step carries out laser direct deposition processing in the layer surface of the high temperature basis according to the material of heat zone to form height
Warm layer.
6. the laser direct deposition preparation method of the big temperature gradient structural member of thin-walled according to claim 5, feature exist
In in the first step, the initialization laser forming equipment includes: to carry out each systems inspection in laser direct deposition equipment
And preparation, atmosphere protection system is opened, makes oxygen content lower than 50ppm；
Preferably, in the second step, the threedimensional model of the structural member is established using 3 d modeling software Siemens NX,
Using laser direct deposition equipment (i.e. laser forming equipment) carry subdivision software to the threedimensional model carry out subdivision, it is described in
Warm layer and heat zone 0.4~0.6mm of subdivision thickness in monolayer, the gradient transitional lay and the high temperature basal layer subdivision thickness in monolayer
The CNC program of subdivision Software Create is inputted laser direct deposition equipment by 0.1~0.2mm；
Preferably, in the third step, using the component proportion of each layer raw material of structural member and thickness in monolayer as numerical control variate-value
The powder feeder digital control system for inputting laser direct deposition equipment the powder feeding ratio of different location and is sent when controlling laser direct deposition
Powder rate.
7. the laser direct deposition preparation method of the big temperature gradient structural member of thin-walled according to claim 5, feature exist
In in the 4th step, the technological parameter for forming the laser direct deposition processing of medium temperature layer includes: 4~6mm/ of scanning speed
S, 1200~1800W of laser power, 0.4~0.6mm of monolayer deposition thickness.
8. the laser direct deposition preparation method of the big temperature gradient structural member of thin-walled according to claim 5, feature exist
In in the 5th step, the technological parameter for forming the laser direct deposition processing of the temperature gradient transition zone includes: scanning
1.5~2.5mm/s of speed, 800~1200W of laser power, 0.1~0.2mm of monolayer deposition thickness；It is highly preferred that the laser
800~1000W of power.
9. the laser direct deposition preparation method of the big temperature gradient structural member of thin-walled according to claim 5, feature exist
In in the 6th step, the technological parameter for forming the laser direct deposition processing of the high temperature basal layer includes: scanning speed
1.5~2.5mm/s, 800~1200W of laser power, 0.1~0.2mm of monolayer deposition thickness；It is highly preferred that the laser power
800~1000W.
10. the laser direct deposition preparation method of the big temperature gradient structural member of thin-walled according to claim 5, feature exist
In, in the 7th step, formed the heat zone laser direct deposition processing technological parameter include: scanning speed 4~
6mm/s, 1200~1800W of laser power, 0.4~0.6mm of monolayer deposition thickness.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114769615A (en) * | 2022-01-21 | 2022-07-22 | 上海镭镆科技有限公司 | Method for metal 3D printing of unsupported structure |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1803348A (en) * | 2006-01-24 | 2006-07-19 | 华中科技大学 | Preparation method for quick preparing functional gradient material |
| CN101598139A (en) * | 2008-06-04 | 2009-12-09 | 北京有色金属研究总院 | A kind of titanium alloy integral blade disc and manufacture method thereof with composite performance |
| WO2013112217A2 (en) * | 2011-10-31 | 2013-08-01 | California Institute Of Technology | Methods for fabricating gradient alloy articles with multi-functional properties |
| CN103498142A (en) * | 2013-09-03 | 2014-01-08 | 航天特种材料及工艺技术研究所 | Laser-clad high-temperature alloy special-shaped connection structure forming method |
| CN103495729A (en) * | 2013-09-03 | 2014-01-08 | 航天特种材料及工艺技术研究所 | Laser three-dimensional forming method of large-size titanium-aluminum-based alloy |
| CN104651663A (en) * | 2015-01-19 | 2015-05-27 | 中南大学 | Double-layer titanium aluminum/aluminum silicon composite material as well as preparation method and application thereof |
| CN104999080A (en) * | 2015-08-03 | 2015-10-28 | 北京理工大学 | Composite material increase manufacturing method for precise fine complex structural component |
| CN105154872A (en) * | 2015-09-06 | 2015-12-16 | 中国航空工业集团公司北京航空材料研究院 | Laser manufacturing method for preparing Ni base alloy gradient materials on titanium alloy |
| CN106001967A (en) * | 2016-07-18 | 2016-10-12 | 西安交通大学 | Butt welding method for double-layer metal composite boards |
| CN106312061A (en) * | 2015-07-01 | 2017-01-11 | 安萨尔多能源英国知识产权有限公司 | Method for manufacturing a metal part with bi-metallic characteristic and manufacturing arrangement for conducting said method |
| US20170361600A1 (en) * | 2016-06-21 | 2017-12-21 | Washington State University | Additive manufacturing of composite materials with composition gradient |
| CN107737932A (en) * | 2017-10-26 | 2018-02-27 | 西北工业大学 | A kind of integrated laser increasing material manufacturing method that titanium or titanium alloy constituency is strengthened |
| CN107774997A (en) * | 2017-10-23 | 2018-03-09 | 江西瑞曼增材科技有限公司 | A kind of Ni-based orientation high temperature alloy laser orientation increases material method |
| CN108145160A (en) * | 2016-12-05 | 2018-06-12 | 航天特种材料及工艺技术研究所 | A kind of laser forming method of gradient composite structure |
-
2018
- 2018-12-03 CN CN201811465224.4A patent/CN109513925B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1803348A (en) * | 2006-01-24 | 2006-07-19 | 华中科技大学 | Preparation method for quick preparing functional gradient material |
| CN101598139A (en) * | 2008-06-04 | 2009-12-09 | 北京有色金属研究总院 | A kind of titanium alloy integral blade disc and manufacture method thereof with composite performance |
| WO2013112217A2 (en) * | 2011-10-31 | 2013-08-01 | California Institute Of Technology | Methods for fabricating gradient alloy articles with multi-functional properties |
| US20150044084A1 (en) * | 2011-10-31 | 2015-02-12 | California Institute Of Technology | Methods for fabricating gradient alloy articles with multi-functional properties |
| CN103498142A (en) * | 2013-09-03 | 2014-01-08 | 航天特种材料及工艺技术研究所 | Laser-clad high-temperature alloy special-shaped connection structure forming method |
| CN103495729A (en) * | 2013-09-03 | 2014-01-08 | 航天特种材料及工艺技术研究所 | Laser three-dimensional forming method of large-size titanium-aluminum-based alloy |
| CN104651663A (en) * | 2015-01-19 | 2015-05-27 | 中南大学 | Double-layer titanium aluminum/aluminum silicon composite material as well as preparation method and application thereof |
| CN106312061A (en) * | 2015-07-01 | 2017-01-11 | 安萨尔多能源英国知识产权有限公司 | Method for manufacturing a metal part with bi-metallic characteristic and manufacturing arrangement for conducting said method |
| CN104999080A (en) * | 2015-08-03 | 2015-10-28 | 北京理工大学 | Composite material increase manufacturing method for precise fine complex structural component |
| CN105154872A (en) * | 2015-09-06 | 2015-12-16 | 中国航空工业集团公司北京航空材料研究院 | Laser manufacturing method for preparing Ni base alloy gradient materials on titanium alloy |
| US20170361600A1 (en) * | 2016-06-21 | 2017-12-21 | Washington State University | Additive manufacturing of composite materials with composition gradient |
| CN106001967A (en) * | 2016-07-18 | 2016-10-12 | 西安交通大学 | Butt welding method for double-layer metal composite boards |
| CN108145160A (en) * | 2016-12-05 | 2018-06-12 | 航天特种材料及工艺技术研究所 | A kind of laser forming method of gradient composite structure |
| CN107774997A (en) * | 2017-10-23 | 2018-03-09 | 江西瑞曼增材科技有限公司 | A kind of Ni-based orientation high temperature alloy laser orientation increases material method |
| CN107737932A (en) * | 2017-10-26 | 2018-02-27 | 西北工业大学 | A kind of integrated laser increasing material manufacturing method that titanium or titanium alloy constituency is strengthened |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114769615A (en) * | 2022-01-21 | 2022-07-22 | 上海镭镆科技有限公司 | Method for metal 3D printing of unsupported structure |
| CN114769615B (en) * | 2022-01-21 | 2024-01-30 | 上海镭镆科技有限公司 | Metal 3D printing method without supporting structure |
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