CN106947856A - The manufacture method and intensifying method of a kind of member for prolonging service life - Google Patents
The manufacture method and intensifying method of a kind of member for prolonging service life Download PDFInfo
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- CN106947856A CN106947856A CN201710220202.0A CN201710220202A CN106947856A CN 106947856 A CN106947856 A CN 106947856A CN 201710220202 A CN201710220202 A CN 201710220202A CN 106947856 A CN106947856 A CN 106947856A
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- service life
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- 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
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
- C21D10/005—Modifying the physical properties by methods other than heat treatment or deformation by laser shock processing
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- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/64—Treatment of workpieces or articles after build-up by thermal means
-
- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
-
- 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
- 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]
-
- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/36—Process control of energy beam parameters
-
- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/38—Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
-
- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/50—Treatment of workpieces or articles during build-up, e.g. treatments applied to fused layers during build-up
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Materials Engineering (AREA)
- Automation & Control Theory (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- Optics & Photonics (AREA)
- Crystallography & Structural Chemistry (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Laser Beam Processing (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
For the defect of prior art, the present invention proposes manufacture and the intensifying method of a kind of member for prolonging service life.Methods described handles special component by way of laser gain material is manufactured, pass through the loading analysis to component actual condition, by adjusting powder feed rate and Material growth direction, in the optimal anti-load crystallite dimension of component different zones generation and crystal grain arrangement, so as to reach the purpose of increase component service life.
Description
Technical field
The present invention relates to laser gain material manufacture and laser peening field, refers in particular to a kind of by laser gain material manufacture manufacture whirlpool
Turbine blade, impeller etc. have complex-curved component, and by laser impact intensified its surface stress situation of improvement simultaneously
Extend the manufacture method and intensifying method of its practical life-time dilatation component service life.
Technical background
Laser gain material manufacturing technology and Laser Peening Technology are presently the most advanced manufacture and surface strengthening technology.With
Modern mechanical equipment performance is stepped up, the requirement more and more higher to the performance of component, life-span and volume, traditional group
Dress formula component can not meet the high performance design requirement of small size.The critical component of high-performance mechanical equipment such as turbogenerator
The overall manufacture of the critical components such as blisk, equation motorcycle race cylinder turns into trend.Traditional manufacture method can be only formed
The product of the unified arrangement of crystal grain, forming different crystal grain arrangements in product different zones needs by some additional process, this nothing
Doubt and add production cost, and the new crystal grain layer of generation is often relatively thin, it is difficult to meet the high performance requirements of modern mechanical.
Laser gain material manufacturing technology is difficult to meet antifatigue system due to the essence of its heat manufacture, its product surface residual stress
The requirement made.Laser Peening Technology can perfectly solve this problem, and Laser Peening Technology being capable of accurate controlled material table
The residual stress in face, and the significantly service life of member for prolonging.But in actual applications, often there is thin-walled element in component,
And with complex-curved, plastic deformation is also easy to produce at component thin-walled if laser energy is not adjusted according to the dimensional parameters of part
Even ftracture, cause part failure.In view of the shortcomings of the prior art, the present invention proposes a kind of sharp according to scantling parameter regulation
The method of light energy, this method is combined with increases material manufacturing technology, optimizes the properties of product of increasing material manufacturing part, for component not
Laser energy optimization is made in same region, solves the problem of laser peening thin-wall part is deformed.
The content of the invention
For the defect of prior art, the present invention proposes manufacture method and the reinforcing side of a kind of member for prolonging service life
Method.
A kind of method for manufacturing component, it is characterised in that special component is manufactured by way of laser gain material is manufactured, by right
The loading analysis of component actual condition, by adjusting powder feed rate and Material growth direction, is generated optimal in component different zones
Anti- load crystallite dimension and crystal grain arrangement so that reach increase component service life purpose.
A kind of laser impact intensified method of component, it is characterised in that：Obtain first and treat the size of impact structure and microcosmic
Tissue distribution, according to the corresponding part thickness of the different shock point of component surface and crystal grain arrangement choose different laser energy E (T,
γ, VF), wherein T be shock point at component thickness, γ be crystal grain arrangement factor (0.5-0.9), VF be volume energy parameter its
Span is：1200J/cm3-1800J/cm3, (E is T, γ and VF function), so as to be swashed to different zones using different
Optical power density is impacted.
Its implementation process is as follows：
Manufacture part：
Blade surface, can be greatly classified into 4 regions, blade inlet edge, trailing edge, leaf by certain type blade as shown in Figure 1
At the top of piece and blade, wherein blade inlet edge and trailing edge fringe region at work not only by during blade movement from
The tensile load that mental and physical efforts are produced, also suffers from the compressive load that air-flow is produced to it, therefore in this two-part manufacturing process
Ensure that its crystal grain arragement direction is inclined to air flow direction, as shown in Figure 2.And the centrifugal force that blade and bucket tip region are mainly subject to
The tensile load of generation, so the arrangement of its crystal grain is arranged using the column crystal parallel to blade longitudinal direction.In laser gain material system
During making, powder feed rate is set first as V1, longitudinal direction successively manufactures blade portion, form the column crystal arrangement of longitudinal direction, treat leaf
Body some growth adjusts blade attitude after finishing, regulation powder feed rate is V2, and the increasing of blade inlet edge and trailing edge is carried out respectively
Material is manufactured, and forms leading edge equiax crystal and trailing edge equiax crystal.During the increasing material manufacturing of blade, first, pass through coaxial powder-feeding
Mode it is laser sintered form the substrate that thickness is T1, the thickness and size of substrate are selected according to different parts, substrate solidification
Afterwards, using laser peening in substrate surface formation residual compressive stress.Laser burns by way of coaxial powder-feeding again after bead
Its surface stress is regulated and controled using laser peening again after the completion of the layer material of knot second, the second layer material sintering.Its process such as Fig. 1 institutes
Show.S1 increasing material manufacturings form substrate, and S2 manufactures the second layer material in substrate, and the material of S3 laser impact formings judges that part is
No manufacture is finished, and is then progress S4 heat treatments, is cooled down more than heat parts to recrystallization initial temperature point rear, to obtain more
The crystal grain of refinement, otherwise repeats S2-S3 until part manufacture is finished.
Reinforced portion:
Fig. 3 is blade profile figure, it can be seen that the thickness of blade inlet edge and trailing edge is smaller, and blade
The thickness at middle part is larger, to prevent from producing blastic deformation in blade thinner region, it is necessary to according to blade surface different-thickness region
Laser energy density E=(T, γ, the VF) table 1 used at laser energy optimization, shock point is that long-pending energy parameter is
1800J/cm3When blade surface shock point thickness and its laser energy size of use.
The advantage of the invention is that：
1. by optimizing powder feed rate and crystal grain is arranged to manufacture special component, make the component under special operation condition have compared with
High antifatigue damage capability；
2. laser impact intensified to the progress of every layer material in the fabrication process, the knot enhanced between every layer material interface is strong
Degree, while introducing residual compressive stress in material internal, improves the fatigue resistance of integrated member；
3. Technology for Heating Processing ensure that component has the grainiess more refined；
4. according to different volumes parameter and crystal grain parameter optimization laser-impact parameter, it is therefore prevented that laser-impact thin-walled portion is produced
Raw deformation of products timeliness, it is ensured that the surface compress residual stresses of certain layer depth
Brief description of the drawings
Fig. 1 is certain h type engine h blade construction schematic diagram；
Fig. 2 is blade surface crystal grain layout viewing；
Fig. 3 is laser-impact energy profile；
Fig. 4 is laser-impact schematic diagram；
Fig. 5 is laser gain material manufacturing flow chart.
Specific embodiment
Following examples are used for illustrating the present invention, but are not the limitation present invention.The invention will now be described in detail with reference to the accompanying drawings
The details and performance of the method for proposition.
The surface of blade 1, can be greatly classified into 4 regions, blade inlet edge 3, trailing edge by certain type blade 1 as shown in Figure 1
5, vane tip 4 and blade 2, wherein blade inlet edge 3 and trailing edge edge 5 not only being produced by centrifugal force at work
Tensile load, also suffers from the compressive load that air-flow is produced to it, therefore arranges its crystal grain in this two-part manufacturing process
Cloth direction is inclined to air flow direction and forms the closeer equiax crystal of quality, (leading edge equiax crystal 8, trailing edge equiax crystal 6) as shown in Figure 2.
And the tensile load that the centrifugal force that blade 2 is mainly subject to is produced, so the arrangement of its crystal grain is using parallel to the longitudinal direction of blade 2
Column crystal arrangement 9.Vane tip 4 is easily loss region, therefore using the thinner top column crystal 7 of crystal grain.In laser gain material system
During making, first longitudinal direction is grown into blade 2, adjusts blade attitude after the growth of blade 2 is finished, then carry out blade inlet edge respectively
3 and the increasing material manufacturing of trailing edge 5.In laser gain material manufacturing process, powder feed rate is set first as V1, and longitudinal direction is successively manufactured
Blade 2, forms the column crystal arrangement 9 of longitudinal direction, and regulation powder feed rate is V2, carries out the manufacture on leaf top, forms the thinner top of crystal grain
Portion's column crystal 7.The attitude of blade 2 is adjusted after blade 2 and the growth of vane tip 4 are finished, regulation powder feed rate is V3, is carried out respectively
The increasing material manufacturing of blade inlet edge 3 and trailing edge 5, forms leading edge equiax crystal 8 and trailing edge equiax crystal 6.In the increasing material manufacturing of blade
During, it is first, laser sintered by way of coaxial powder-feeding to form the substrate that thickness is T1, the thickness and size root of substrate
It is selected according to different parts, after substrate solidification, using laser peening in substrate surface formation residual compressive stress.After bead again
It is regulated and controled using laser peening again after the completion of laser sintered second layer material by way of coaxial powder-feeding, the second layer material sintering
Surface stress.Its process is as shown in Figure 1.S1 increasing material manufacturings form substrate, and S2 manufactures the second layer material, the punching of S3 laser in substrate
The material for hitting shaping judges whether part manufactures and finished, and is then progress S4 heat treatments, by heat parts to recrystallizing initial temperature
Cooled down after more than point, to obtain the crystal grain more refined, otherwise repeat S2-S3 until part manufacture is finished.
Reinforced portion:
Fig. 3 is blade profile figure, it can be seen that the thickness of blade inlet edge 3 and trailing edge 5 is smaller, and blade
The thickness at middle part is larger, to prevent from producing blastic deformation in blade thinner region, it is necessary to according to blade surface different-thickness region
Laser energy optimization is carried out, according to the material parameter at shock point, using different laser energy E (T, γ, VF), the thickness of blade
Degree is down gradually incremented by therefore laser strikes power density from vane tip 4 and is also gradually incremented by (leading edge power density 11, trailing edge work(
Rate density 12), leaf top power density 10 is changed according to the thickness value of the different zones of vane tip 4.Table 1 rushes for blade surface
Hit path R1, R2, R3 thickness and its laser energy of use.
Make after laser energy parameter, by the clamping of blade 1 on manipulator 13 manipulator 13 according to the curvature of the table of blade 1
The change constantly adjustment attitude of blade 1, it is ensured that the vertical incidence blade 1 of laser 16 treats shock zone, and pitch-dark work is pasted on the surface of blade 1
For absorbed layer, Tu Shui robots 14 form uniform moisture film in blade surface, and laser 16 is projected by laser head 15 and acts on workpiece
Surface, carries out shot-peening.
Table 1
Claims (3)
1. a kind of manufacture method of member for prolonging service life, it is characterised in that institute is manufactured by way of laser gain material is manufactured
Component is stated, it is different in component by adjusting powder feed rate and Material growth direction by the loading analysis to component actual condition
The optimal anti-load crystallite dimension of Area generation and crystal grain arrangement, so as to reach the purpose of increase component service life.
2. a kind of intensifying method of member for prolonging service life, it is characterised in that：The size of the component is obtained first and microcosmic
Tissue distribution, different laser energies, institute are chosen according to the corresponding part thickness of the different shock points of component surface and crystal grain arrangement
The laser energy function of determination is E (T, γ, VF), and wherein T is the component thickness at shock point, and γ is crystal grain arrangement factor, VF
For volume energy parameter, so as to be impacted to different zones using different laser power densities.
3. a kind of intensifying method of member for prolonging service life as claimed in claim 2, it is characterised in that：Crystal grain row therein
Cloth factor span is 0.5-0.9, and its span of volume energy parameter therein is：1200J/cm3-1800J/cm3。
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| CN201710220202.0A CN106947856A (en) | 2017-04-06 | 2017-04-06 | The manufacture method and intensifying method of a kind of member for prolonging service life |
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| CN201710220202.0A CN106947856A (en) | 2017-04-06 | 2017-04-06 | The manufacture method and intensifying method of a kind of member for prolonging service life |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109261964A (en) * | 2018-10-30 | 2019-01-25 | 首都航天机械有限公司 | A kind of titanium alloy structure part and its Laser Melting Deposition manufacturing process |
| CN109703029A (en) * | 2018-04-05 | 2019-05-03 | 苏州先机动力科技有限公司 | A kind of positive increasing material manufacturing control method based on Material Physics model-driven |
| CN110629014A (en) * | 2019-09-27 | 2019-12-31 | 江苏大学 | Laser shock strengthening method for dual-phase titanium alloy additive component |
| CN113088678A (en) * | 2021-04-08 | 2021-07-09 | 中国航发北京航空材料研究院 | Laser shock peening method for blades of small-size blisk |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110629014A (en) * | 2019-09-27 | 2019-12-31 | 江苏大学 | Laser shock strengthening method for dual-phase titanium alloy additive component |
| CN113088678A (en) * | 2021-04-08 | 2021-07-09 | 中国航发北京航空材料研究院 | Laser shock peening method for blades of small-size blisk |
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Application publication date: 20170714 |
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