CN109079143A - The method for removing precinct laser fusion formation of parts surface of internal cavity crackle - Google Patents
The method for removing precinct laser fusion formation of parts surface of internal cavity crackle Download PDFInfo
- Publication number
- CN109079143A CN109079143A CN201710445500.XA CN201710445500A CN109079143A CN 109079143 A CN109079143 A CN 109079143A CN 201710445500 A CN201710445500 A CN 201710445500A CN 109079143 A CN109079143 A CN 109079143A
- Authority
- CN
- China
- Prior art keywords
- laser fusion
- precinct laser
- parts
- fusion formation
- internal cavity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 67
- 230000004927 fusion Effects 0.000 title claims abstract description 59
- 230000015572 biosynthetic process Effects 0.000 title claims abstract description 52
- 208000037656 Respiratory Sounds Diseases 0.000 title claims abstract description 44
- 230000008569 process Effects 0.000 claims abstract description 22
- 238000005111 flow chemistry technique Methods 0.000 claims abstract description 12
- 239000006061 abrasive grain Substances 0.000 claims abstract description 6
- 238000005520 cutting process Methods 0.000 claims description 34
- 238000004458 analytical method Methods 0.000 claims description 31
- 238000001514 detection method Methods 0.000 claims description 14
- 238000012545 processing Methods 0.000 claims description 12
- 238000009826 distribution Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 8
- 239000003082 abrasive agent Substances 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 6
- 238000007781 pre-processing Methods 0.000 claims description 5
- 230000003068 static effect Effects 0.000 claims description 5
- 206010011376 Crepitations Diseases 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 3
- 238000005070 sampling Methods 0.000 claims description 3
- 238000001513 hot isostatic pressing Methods 0.000 abstract description 11
- 238000004804 winding Methods 0.000 abstract description 4
- 238000009740 moulding (composite fabrication) Methods 0.000 description 14
- 230000000694 effects Effects 0.000 description 9
- 238000013461 design Methods 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 8
- 238000004140 cleaning Methods 0.000 description 4
- 239000000843 powder Substances 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 3
- 239000000956 alloy Substances 0.000 description 3
- 230000000740 bleeding effect Effects 0.000 description 3
- 239000003795 chemical substances by application Substances 0.000 description 3
- 238000000227 grinding Methods 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 239000003350 kerosene Substances 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000002844 melting Methods 0.000 description 3
- 230000008018 melting Effects 0.000 description 3
- 239000003921 oil Substances 0.000 description 3
- 239000000758 substrate Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 238000005498 polishing Methods 0.000 description 2
- 238000007712 rapid solidification Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000003746 surface roughness Effects 0.000 description 2
- 238000003723 Smelting Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000001680 brushing effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 238000010892 electric spark Methods 0.000 description 1
- 239000003995 emulsifying agent Substances 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 150000008282 halocarbons Chemical class 0.000 description 1
- 239000012216 imaging agent Substances 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 238000010309 melting process Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000010742 number 1 fuel oil Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- -1 pressure Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000004439 roughness measurement Methods 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 238000007514 turning Methods 0.000 description 1
- 238000001291 vacuum drying Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
- 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
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
-
- 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
- B22F10/60—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
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/66—Treatment of workpieces or articles after build-up by mechanical 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
- 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
- B22F3/10—Sintering only
- B22F3/105—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding
-
- 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
- B22F2003/247—Removing material: carving, cleaning, grinding, hobbing, honing, lapping, polishing, milling, shaving, skiving, turning the surface
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- Optics & Photonics (AREA)
- Powder Metallurgy (AREA)
- Sampling And Sample Adjustment (AREA)
Abstract
The present invention relates to a kind of methods for removing precinct laser fusion formation of parts surface of internal cavity crackle comprising: hip treatment hip treatment step: is carried out to precinct laser fusion formation of parts；Abrasive Flow processing step: abrasive grain stream process is carried out to the precinct laser fusion formation of parts after hip treatment.The present invention removes the method for precinct laser fusion formation of parts surface of internal cavity crackle by the way that abrasive grain flow step is arranged after hot isostatic pressing step, precinct laser fusion formation of parts initial surface quality is preferable, inner cavity of component open-delta winding is eliminated using abrasive Flow technique, effectively promotes the comprehensive performance of part.
Description
Technical field
The present invention relates in material working process technical field more particularly to a kind of removal precinct laser fusion formation of parts
The method of chamber face crack.
Background technique
Precinct laser fusion (Selective Laser Melting, abbreviation SLM) technology is a kind of typical increasing material manufacturing
(Additive Manufacturing) technology is predicted to be one of the key technology that may cause " the third time industrial revolution ",
Its main technical principle are as follows: part three-dimensional digital model to be processed is successively divided, be input to precinct laser fusion at
In shape equipment.Substrate is fixed in forming platform first, and is leveled, carries out single berth using scraper plate or powder roller later
Powder carries out selective melting using a branch of or multiple laser single layer powder good to laying, realize by put to line, by line to face at
Shape process, later forming platform decline certain altitude, carry out next layer of powdering and selective melting forming, finally realize by face to
The forming process of body, thus to obtain final part.Compared to traditional handicraft, selective laser melting process has stock utilization
It is high, increase the degree of design freedom, shape the multiple advantages such as high-precision, surface quality be good, add particularly suitable for aerospace is contour
It is worth industry.
However, rapid solidification is along with pole since precinct laser fusion forming process is along with rapid solidification
High-temperature gradient, resulting in part, there are biggish residual stress, and when local residual stress is more than tensile strength, part occurs
Crackle obtains stress by cracking and discharges to a certain extent.In general, crack distribution range not only includes inside parts, also include
Piece surface.
Since there are crackles for precinct laser fusion formation of parts, it is difficult to meet wanting for structure durability and damage tolerance design
It asks, this point is especially pronounced in aerospace field.For this problem, the elimination of following two method is generallyd use at present and is split
Line: first is that making inside parts crack closure using heat and other static pressuring processes；Second is that using machining process (such as turning, milling)
Processable face is machined.However the feature intrinsic due to heat and other static pressuring processes, it is only capable of making inside parts crack closure,
Play the role of eliminating underbead crack, and there is no effect for cracks with surface openings.And machining process is used to there is processing
The problems such as position limitation is high, to parts with complex structures complex process, especially precinct laser fusion formation of parts usually has
Complicated inner-cavity structure, mechanical processing technique are often difficult to play a role.
It can be seen that by heat and other static pressuring processes and tradition machinery processing technology, can eliminate inside parts micro-crack and
Open surface crackle, and the face crack of inner cavity is difficult to remove.It is molten that the presence of surface of internal cavity crackle can seriously destroy precinct laser
The surface integrity for changing part, has a significant impact to the military service performance of components, life and reliability.Such as it is with titanium alloy member
Example, statistics shows that the failure of 90% aero titanium alloy part is related to fatigue behaviour, and face crack often plays fatigue
The effect of formation of crack improves the surface integrity of titanium alloy by certain techniques, has key effect for promoting fatigue behaviour.
Summary of the invention
To overcome the above technological deficiency, the technical problem to be solved by the present invention is to provide a kind of formings of removal precinct laser fusion
The method of inner cavity of component face crack can effectively remove the face crack of precinct laser fusion formation of parts inner cavity.
In order to solve the above technical problems, the present invention provides a kind of removal precinct laser fusion formation of parts surface of internal cavity to split
The method of line comprising:
Hip treatment step: hip treatment is carried out to precinct laser fusion formation of parts；
Abrasive Flow processing step: abrasive grain stream process is carried out to the precinct laser fusion formation of parts after hip treatment.
Further, further include cutting analytical procedure between hip treatment step and abrasive Flow processing step: right
Part after completing hot isostatic pressing carries out cutting analysis, to obtain the maximum of the crack depth on inner cavity of component surface, according to splitting
The maximum of line depth determines the material removal amount that abrasive Flow need to reach.
Further, if the maximum of crack depth is greater than the pattern allowance of precinct laser fusion formation of parts, increase mould
Type surplus, and the minimum value of total pattern allowance is greater than the maximum of crack depth.
Further, the roughness that the maximum of crack depth passes through the surface of internal cavity different location after the completion of detection cutting
It is obtained with crack distribution and by analysis on cracks.
Further, analysis on cracks includes: to carry out multiposition cutting to precinct laser fusion formation of parts, to precinct laser
Formation of parts is melted to analyze using progress Metallographic Analysis after the cutting of vertical crack direction and multiple batches of repetition cutting.
Further, abrasive Flow processing step includes: to carry out abrasive Flow, carry out abrasive material removal and whether detect stock removal
Reach desired value, if the stock removal measured and desired value are not met, resets the model of precinct laser fusion formation of parts
Surplus.
Further, further include part sampling observation step: to extract carry out abrasive Flow treated the part of preset quantity into
Row cutting analysis detection, judges whether there is crackle.
It further, further include the model preprocessing step, blank procedure of processing and heat treatment step successively carried out, heat
Processing step is located at before hip treatment step.
As a result, based on the above-mentioned technical proposal, the present invention removes the side of precinct laser fusion formation of parts surface of internal cavity crackle
Method after hot isostatic pressing step by being arranged abrasive grain flow step.Abrasive Flow is used for finishing, polishing, the deburring of part, has
Favorable repeatability, the high feature of surface quality.Precinct laser fusion formation of parts initial surface quality is preferable, using abrasive Flow work
Skill eliminates inner cavity of component open-delta winding, further increases surface roughness.The present invention is directed to can not lead to after hot isostatic pressing
The inner cavity crackle that over mechanical processing or manual grinding are eliminated.
Detailed description of the invention
The drawings described herein are used to provide a further understanding of the present invention, constitutes part of this application, this hair
Bright illustrative embodiments and their description for explaining only the invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the flow chart of the method for present invention removal precinct laser fusion formation of parts surface of internal cavity crackle；
Fig. 2 is cutting analytical procedure in the method for present invention removal precinct laser fusion formation of parts surface of internal cavity crackle
Flow chart；
Fig. 3 is abrasive Flow processing step in the method for present invention removal precinct laser fusion formation of parts surface of internal cavity crackle
Flow chart；
Fig. 4 (a) and Fig. 4 (b) is respectively that precinct laser fusion forming GH4169 alloy utilizes present invention removal precinct laser
Underbead crack distribution map of the method for fusing forming inner cavity of component face crack under deposited and hot isostatic pressing state；
Fig. 5 (a) and Fig. 5 (b) is that precinct laser fusion shapes GH4169 alloy part using present invention removal precinct laser
Surface cracks distribution map of the method for fusing forming inner cavity of component face crack after hot isostatic pressing.
Specific embodiment
Below by drawings and examples, technical scheme of the present invention will be described in further detail.
A specific embodiment of the invention be for the ease of to design of the invention, it is solved the technical issues of, constitute skill
The technical characteristic and bring technical effect of art scheme have further description.It should be noted that for these embodiment party
The explanation of formula does not constitute a limitation of the invention simultaneously.In addition, technology involved in the embodiment of present invention described below is special
Sign can be combined with each other as long as they do not conflict with each other.
In one schematical embodiment of method of present invention removal precinct laser fusion formation of parts surface of internal cavity crackle
In, as shown in Figure 1, this method comprises:
Hip treatment step 4: hip treatment is carried out to precinct laser fusion formation of parts；
Abrasive Flow processing step 6: abrasive Flow is carried out to the precinct laser fusion formation of parts after hip treatment
Processing.
The processing step of usual precinct laser fusion formation of parts includes: that model treatment-blank forming-destressing is moved back
Fire-remove support-hot isostatic pressing.In the schematical embodiment, the present invention unlike conventional processing routes, by
Abrasive Flow processing step 6 is set after hip treatment step 4, and abrasive Flow is used for finishing, polishing, the deburring of part, has
Favorable repeatability, the high feature of surface quality.Precinct laser fusion formation of parts initial surface quality is preferable, using abrasive Flow
Technique eliminates inner cavity of component open-delta winding, further increases precinct laser fusion formation of parts surface of internal cavity roughness.This hair
It is bright to be disappeared by the inner cavity crackle of machining or manual grinding elimination using abrasive Flow method for after hot isostatic pressing
Except inner cavity of component face crack.
Specifically or preferably, as shown in Figure 1, the present invention removes precinct laser fusion formation of parts surface of internal cavity crackle
Method further includes the cutting analytical procedure 5 between hip treatment step 4 and abrasive Flow processing step 6: to completing, heat etc. is quiet
Part after pressure carries out cutting analysis, to obtain the maximum of the crack depth on inner cavity of component surface, according to the pole of crack depth
Big value determines the material removal amount that abrasive Flow need to reach.The present invention is according to the maximum of the crack depth on inner cavity of component surface come really
Determine the material removal amount that abrasive Flow need to reach, effectively eliminates inner cavity of component open-delta winding and realization uses as needed, avoid not
Cost is saved in necessary waste.
Specifically or preferably illustrate present invention removal precinct laser fusion below with reference to process shown in FIG. 1 to FIG. 3
The method of formation of parts surface of internal cavity crackle is as follows:
(1) model preprocessing step 1, addition and supported design comprising pattern allowance, and threedimensional model is sliced,
Obtain process modeling；
(2) blank procedure of processing 2, including by process modeling file import equipment, using optimization precinct laser fusion at
Shape technological parameter carries out precinct laser fusion forming, part is collected and inner cavity powder is cleared up etc.；
(3) heat treatment step 3, at the same contain part complete stress relief annealing after, substrate is separated into required line with part
Cutting action, and support removing step.
(4) hip treatment step 4 plays a part of to eliminate inside parts crackle.
(5) processing step 5 is analyzed in cutting, cutting analysis is carried out to the part after completion hot isostatic pressing, as shown in Fig. 2, tool
Body includes the cutting scheme 5.1 of design elements, and cutting scheme should be can show complete inner-cavity structure as optimum state；Implement
Cutting 5.2 carries out cutting using electric spark wire cutting machine or other technologies；Roughness measurement 5.3, after the completion of detection cutting
Surface of internal cavity different location roughness, provide foundation for analysis on cracks and detection；Crack detection 5.4, utilizes fluorescent penetrant
Detection, Metallographic Analysis or two kinds of techniques combine, and determine the distribution situation of face crack；Analysis on cracks 5.5, emphasis is for thick
Rugosity is worth lesser region and intracavity section product sudden change region, using appropriate method (as further to precinct laser fusion
Formation of parts carries out multiposition cutting, utilizes progress metallographic point after the cutting of vertical crack direction to precinct laser fusion formation of parts
Analysis and multiple batches of repetition cutting analysis) crack depth is analyzed, the maximum of crack depth is obtained after comprehensive comparison.It should be noted that
It is that when due to carrying out abrasive Flow, the former biggish surface stock removal of roughness can be greater than roughness smaller area, therefore in crackle depth
When degree analysis, it should perform an analysis emphasis for the preferable region of apparent surface's mass.
According to determining crack depth maximum, if the maximum of crack depth is less than precinct laser fusion formation of parts
Pattern allowance then carries out abrasive Flow；If maximum is greater than the pattern allowance of precinct laser fusion formation of parts, repeat step
1 model treatment increases corresponding surplus in crackle surface of internal cavity.It should be noted that the occurrence of inner cavity different location surplus,
It is closely related with the design feature of inner cavity of component, but the pattern allowance minimum value after increase should be greater than analyzing resulting crack depth
Maximum levels off to 100% to ensure that crackle removal reaches effect, promotes the comprehensive performance of part.
(6) abrasive Flow processing step 6, as shown in figure 3, specifically including process parameters design 6.1, not according to material category
Same, abrasive type, abrasive grain, pressure, binder type that the different selections of intracavity section product are different etc.；Engineered abrasives cleaning side
Case 6.2, it is significant to note that, after removing surface of internal cavity crackle using abrasive Flow, it is using appropriate technique cleaning abrasive material
Key link；Abrasive Flow implements 6.3；Abrasive material removal 6.4；Whether analysis detection 6.5 reaches pre- using industry CT detection stock removal
Time value need to repeat the setting of step 1 pattern allowance when the stock removal and desired value that analysis detection measures are not met.
(7) part inspects step 7 by random samples, refers mainly to realizing the volume production stage, extracts certain amount part, repeat according to step 5
It is detected, checks whether and achieved the purpose that remove surface of internal cavity crackle.
(8) final inspection and step 8 is checked and accepted, adoptable means include but is not limited to Metallographic Analysis, X-ray detection, glimmering
Light detection etc..
The present invention is proposed and is eliminated using abrasive Flow technique on the basis of hip treatment eliminates inside parts crackle
The method of part surface crack is finally reached the purpose for completely eliminating the crackle in part, with current prior art method phase
Than having the advantage that
(1) improve part mechanical property；
Eliminate crackle process can to avoid inside parts and face crack to mechanical property (including stretch, persistently, fatigue
Deng) destruction, to promoted part comprehensive performance play an important role.
(2) lot stability of part is improved；
The dispersibility that the presence of precinct laser fusion formation of parts crackle will lead to the batch performance data of part substantially mentions
Height results in part service life and fluctuates in a big way, it is difficult to the service life of Accurate Prediction part.Eliminate crackle work
Sequence can be such that part performance inconsistency reduces, and promote lot stability.
(3) roughness, dimensional accuracy are optimized；
Dimensional accuracy, the surface roughness of precinct laser fusion formation of parts are generally difficult to meet high-precision labyrinth zero
The requirement of part.While eliminating crackle, by appropriate technology controlling and process, the coarse of surfaces externally and internally can be greatly improved
Degree improves dimensional accuracy, meets product demand.
To sum up, by eliminate inner cavity of component face crack can effective Improving The Quality of Products, for promote constituency swash
Engineering application of the light smelting technology in fields such as aerospaces has important practical significance.
Illustrated for removing precinct laser fusion forming GH4169 pipe component containing cross-section surface cracks below
The method of the present invention is as follows:
(1) model preprocessing is carried out with cross-section internal duct part to some using UG NX7.5, part material is
GH4169 alloy, tubing internal diameter φ 3.2mm, outer diameter φ 10.0mm have the rounding off and one that bending radius is R6.0mm at one
Place R10.0mm causes pipeline direction to occur to change twice, pipeline total length about 100mm.First to the machinery determined outside part
Machined surface adds 1mm or so surplus, and exports stl file, be supported design using Magics19.0 and export slice file.
Slice file is imported into precinct laser fusion former, blank forming process is carried out.Setting forming parameters are layer
It is 40 μm, laser power 200W, scanning speed 900mm/s thick, 100 μm of laser spot diameter, 110 μm of sweep span, complete blank
Destressing heat treatment is carried out after forming, heat treating regime is 1170 ± 50 DEG C/1h, AC.It will using wire cutting after the completion of heat treatment
Part is separated from substrate, and support is removed, shown in observation inside parts crack distribution situation such as Fig. 4 (a).
(2) hot isostatic pressing is carried out to the part for completing support removal using vacuum heat treatment furnace, eliminates internal split to reach
The purpose of line, selection heat and other static pressuring processes are 1170 DEG C/2h, pressure 150MPa, cooling velocity 3K/min.By analysis, interior
Crack effect is eliminated close to 100%, as shown in Fig. 4 (b) in portion.Such as eliminate crack effect it is undesirable when, hot isostatic pressing work need to be adjusted
Skill repeats above step.
(3) cutting is carried out to part using Wire EDM or other method for slitting.
(4) determining crack depth maximum is combined with Metallographic Analysis using fluorescent penetrant detection.
Liquid penetrant testing cleans the part after cutting using halogenated hydrocarbon solvent, sufficiently removes grease existing for piece surface
And other may influence the substance of Liquid penetrant testing effect, guarantee that part cleans drying.It is being carried out using black light lamp to effect is applied
Under the premise of monitoring, bleeding agent is applied using the method for manual brushing, keeps bleeding agent time of contact 15min~30min.Using
Emulsifier is coated, and carry out most after washing the removal a large amount of bleeding agent of piece surface in advance with the consistent water temperature of environment temperature
Cleaning eventually applies imaging agent.It is finally checked under black light lamp, obtains the distribution situation of part surface crack.It is equal that there are crackles
Position should carry out further Metallographic Analysis.
Metallographic Analysis, crack position of the selection by fluorescent penetrant inspection discovery, and selection certain amount are representative
Surface region or viewing area crackle distribution situation.As shown in figure 5,2~5 μ of the viewing area surface cracks width
m.In this example, it can determine about 30 μm of crack depth maximum by whole cross section observation observation, certain surplus considered, by crackle
The positioning of depth maximum.
Test cutting plane hardness number is HRB94.
(5) repeat step 1 model preprocessing, after tubing internal diameter is adjusted to φ 3.1mm, repeat step 2~step
4.
(6) abrasive Flow process flow is carried out.150 mesh silicon carbide abrasives are selected, pressure 10MPa is set.Abrasive Flow continuously into
After the row 30min time, using the variation of industry CT signal piping diameter, it is determined whether need to continue abrasive Flow.Work as pipeline
After diameter reaches preset value φ 3.2mm, process stops.
Under 12MPa pressure, after carrying out cleaning 20min using aviation kerosine, original clean aviation kerosine is replaced
Rinse 5min, collect whole oil outlets, kerosene clean level at visual comparison's oil outlet and oil inlet, until both close to one
It causes.Later, vacuum drying is carried out, and 3min is blown from inlet using compressed air, while manually being tapped, such as finds pipeline
Exit has particle to be blown out, then continues to repeat Filter Tuber For Clean Coal oil flushing-drying-blowing compressed air, until there is no particles
Object generates.
(7) fluorescent penetration test, Metallographic Analysis are detected whether there are still face crack after progress X-ray procedure, cutting,
As produced in batches there is no after curing process if crackle.But batch sampling observation should be executed.
(8) part final inspection and storage are completed.
The embodiment combined above is described in detail embodiments of the present invention, but the present invention is not limited to be retouched
The embodiment stated.For a person skilled in the art, in the case where not departing from the principle and substance of the present invention spirit
A variety of variations, modification, equivalence replacement and modification is carried out to these embodiments to still fall within protection scope of the present invention.
Claims (8)
1. a kind of method for removing precinct laser fusion formation of parts surface of internal cavity crackle characterized by comprising
Hip treatment step: hip treatment is carried out to precinct laser fusion formation of parts；
Abrasive Flow processing step: abrasive grain stream process is carried out to the precinct laser fusion formation of parts after hip treatment.
2. the method for removal precinct laser fusion formation of parts surface of internal cavity crackle according to claim 1, feature exist
In further including the cutting analytical procedure between the hip treatment step and the abrasive Flow processing step: to completing heat
Part after equal static pressure carries out cutting analysis, to obtain the maximum of the crack depth on inner cavity of component surface, according to the crackle
The maximum of depth determines the material removal amount that abrasive Flow need to reach.
3. the method for removal precinct laser fusion formation of parts surface of internal cavity crackle according to claim 2, feature exist
In if the maximum of the crack depth increases the model greater than the pattern allowance of the precinct laser fusion formation of parts
Surplus, and the minimum value of total pattern allowance is greater than the maximum of the crack depth.
4. the method for removal precinct laser fusion formation of parts surface of internal cavity crackle according to claim 2, feature exist
In the roughness and crack distribution that the maximum of the crack depth passes through the surface of internal cavity different location after the completion of detection cutting
And it is obtained by analysis on cracks.
5. the method for removal precinct laser fusion formation of parts surface of internal cavity crackle according to claim 4, feature exist
In the analysis on cracks includes: to carry out multiposition cutting to the precinct laser fusion formation of parts, molten to the precinct laser
Change formation of parts to analyze using progress Metallographic Analysis after the cutting of vertical crack direction and multiple batches of repetition cutting.
6. the method for removal precinct laser fusion formation of parts surface of internal cavity crackle according to claim 1, feature exist
In the abrasive Flow processing step includes: to carry out abrasive Flow, carry out abrasive material removal and detect whether stock removal reaches expected
Value resets the pattern allowance of the precinct laser fusion formation of parts if the stock removal measured and desired value are not met.
7. the method for described in any item removal precinct laser fusion formation of parts surface of internal cavity crackles according to claim 1~6,
It is characterized in that, further including part sampling observation step: carrying out cutting to carry out abrasive Flow treated the part for extracting preset quantity
Analysis detection judges whether there is crackle.
8. the method for described in any item removal precinct laser fusion formation of parts surface of internal cavity crackles according to claim 1~6,
It is characterized in that, further including the model preprocessing step, blank procedure of processing and heat treatment step successively carried out, at the heat
Reason step is located at before the hip treatment step.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710445500.XA CN109079143B (en) | 2017-06-13 | 2017-06-13 | Method for removing cracks on inner cavity surface of selective laser melting formed part |
| PCT/CN2018/090088 WO2018228251A1 (en) | 2017-06-13 | 2018-06-06 | Method for removing cracks on inner cavity surface of part formed by selective laser melting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710445500.XA CN109079143B (en) | 2017-06-13 | 2017-06-13 | Method for removing cracks on inner cavity surface of selective laser melting formed part |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109079143A true CN109079143A (en) | 2018-12-25 |
| CN109079143B CN109079143B (en) | 2020-12-29 |
Family
ID=64660099
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710445500.XA Active CN109079143B (en) | 2017-06-13 | 2017-06-13 | Method for removing cracks on inner cavity surface of selective laser melting formed part |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN109079143B (en) |
| WO (1) | WO2018228251A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110940215A (en) * | 2019-11-14 | 2020-03-31 | 上海卫星装备研究所 | Structure and manufacturing method of variable cross-section heat pipe |
| CN112589118A (en) * | 2020-10-30 | 2021-04-02 | 北京航天控制仪器研究所 | Method for cleaning inner cavity of titanium alloy valve body part formed by selective laser melting based on shot impact |
| CN115121811A (en) * | 2022-06-29 | 2022-09-30 | 中国航发动力股份有限公司 | Welding method of powder-spreading 3D printer case and engine case |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115740501A (en) * | 2022-12-14 | 2023-03-07 | 南京中科神光科技有限公司 | Laser additive manufacturing method for eliminating formation cracks of large-width structural part |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1861296A (en) * | 2006-06-14 | 2006-11-15 | 华中科技大学 | Method for near-purification formation of parts |
| CN102922244A (en) * | 2012-11-21 | 2013-02-13 | 哈尔滨东安发动机（集团）有限公司 | Processing method for realizing integrity of surface of titanium alloy impeller |
| CN103056782A (en) * | 2012-11-07 | 2013-04-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for controlling removal quantities of re-melting layers of blade film holes by abrasive flow processing |
| JP2013194263A (en) * | 2012-03-16 | 2013-09-30 | Panasonic Corp | Method of manufacturing three-dimensionally shaped object |
| CN106271902A (en) * | 2016-09-27 | 2017-01-04 | 飞而康快速制造科技有限责任公司 | A kind of material that increases manufactures aluminium alloy pipeline accessory inner surface finishing method |
| GB2543157A (en) * | 2015-09-22 | 2017-04-12 | Delavan Inc | Additive manufacture of interior passages |
| CN106583881A (en) * | 2016-12-13 | 2017-04-26 | 西安铂力特激光成形技术有限公司 | Cast iron arc welding repair method |
| CN106623934A (en) * | 2017-03-03 | 2017-05-10 | 大族激光科技产业集团股份有限公司 | After-treatment method for SLM (selective laser melting) shaped steel mold blank and method for preparing SLM shaped steel mold |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH705662A1 (en) * | 2011-11-04 | 2013-05-15 | Alstom Technology Ltd | Process for producing articles of a solidified by gamma-prime nickel-base superalloy excretion by selective laser melting (SLM). |
| GB201213940D0 (en) * | 2012-08-06 | 2012-09-19 | Materials Solutions | Additive manufacturing |
| CN103008657A (en) * | 2013-01-13 | 2013-04-03 | 北京科技大学 | Method for preparing oxide dispersion strengthened alloy by rapid forming |
| DE102014212246B3 (en) * | 2014-06-26 | 2015-08-06 | MTU Aero Engines AG | Method and device for quality assurance |
| CN104308153B (en) * | 2014-10-27 | 2016-08-03 | 西安交通大学 | A kind of manufacture method of high-entropy alloy turbogenerator hot-end component based on precinct laser fusion |
| CN105537587B (en) * | 2015-12-18 | 2018-02-27 | 绍兴文理学院 | A kind of method for eliminating nickel-base alloy selective laser and melting crackle |
-
2017
- 2017-06-13 CN CN201710445500.XA patent/CN109079143B/en active Active
-
2018
- 2018-06-06 WO PCT/CN2018/090088 patent/WO2018228251A1/en active Application Filing
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1861296A (en) * | 2006-06-14 | 2006-11-15 | 华中科技大学 | Method for near-purification formation of parts |
| JP2013194263A (en) * | 2012-03-16 | 2013-09-30 | Panasonic Corp | Method of manufacturing three-dimensionally shaped object |
| CN103056782A (en) * | 2012-11-07 | 2013-04-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for controlling removal quantities of re-melting layers of blade film holes by abrasive flow processing |
| CN102922244A (en) * | 2012-11-21 | 2013-02-13 | 哈尔滨东安发动机（集团）有限公司 | Processing method for realizing integrity of surface of titanium alloy impeller |
| GB2543157A (en) * | 2015-09-22 | 2017-04-12 | Delavan Inc | Additive manufacture of interior passages |
| CN106271902A (en) * | 2016-09-27 | 2017-01-04 | 飞而康快速制造科技有限责任公司 | A kind of material that increases manufactures aluminium alloy pipeline accessory inner surface finishing method |
| CN106583881A (en) * | 2016-12-13 | 2017-04-26 | 西安铂力特激光成形技术有限公司 | Cast iron arc welding repair method |
| CN106623934A (en) * | 2017-03-03 | 2017-05-10 | 大族激光科技产业集团股份有限公司 | After-treatment method for SLM (selective laser melting) shaped steel mold blank and method for preparing SLM shaped steel mold |
Non-Patent Citations (1)
| Title |
|---|
| N.P.马哈里: "《微制造与纳米技术》", 31 August 2015 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110940215A (en) * | 2019-11-14 | 2020-03-31 | 上海卫星装备研究所 | Structure and manufacturing method of variable cross-section heat pipe |
| CN110940215B (en) * | 2019-11-14 | 2021-05-11 | 上海卫星装备研究所 | Structure and manufacturing method of variable cross-section heat pipe |
| CN112589118A (en) * | 2020-10-30 | 2021-04-02 | 北京航天控制仪器研究所 | Method for cleaning inner cavity of titanium alloy valve body part formed by selective laser melting based on shot impact |
| CN115121811A (en) * | 2022-06-29 | 2022-09-30 | 中国航发动力股份有限公司 | Welding method of powder-spreading 3D printer case and engine case |
| CN115121811B (en) * | 2022-06-29 | 2024-03-12 | 中国航发动力股份有限公司 | Welding method of powder-spreading 3D printer casing and engine casing |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2018228251A1 (en) | 2018-12-20 |
| CN109079143B (en) | 2020-12-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109079143A (en) | The method for removing precinct laser fusion formation of parts surface of internal cavity crackle | |
| Denkena et al. | Engine blade regeneration: a literature review on common technologies in terms of machining | |
| Kuang et al. | Fretting wear behaviour of machined layer of nickel-based superalloy produced by creep-feed profile grinding | |
| CN104439884A (en) | Mould three-dimensional rapid forming and repairing method based on reverse engineering | |
| US7934975B2 (en) | Water jet stripping and recontouring of gas turbine buckets and blades | |
| KR102176957B1 (en) | Method for repairing a turbomachine component | |
| Gong et al. | Analysis of tool wear performance and surface quality in post milling of additive manufactured 316L stainless steel | |
| CN106346198B (en) | A kind of processing method for improving rotating member and obturaging comb tooth surface integrality | |
| KR102347222B1 (en) | Austenite Stainless Steel Life Evaluation Method | |
| Mouralova et al. | Influence of the cut direction through the semi-finished product on the occurrence of cracks for X210Cr12 steel using WEDM | |
| CN108453568A (en) | A kind of planar optical elements grinding processing method | |
| CN102059500A (en) | Laser repairing method for tooth corona reconstructing of transmission tooth roller of single-roller crusher | |
| Transchel et al. | Influence of the clearance angle on the cutting efficiency of blunt, octahedral-shaped diamonds in an active filler alloy | |
| CN106226307A (en) | A kind of method measuring 617 nickel-base alloy heat affected area length | |
| Dolimont et al. | Impact of chemical polishing on surface roughness and dimensional quality of electron beam melting process (EBM) parts | |
| CN104874973A (en) | Steam turbine cylinder joint surface deformation processing method | |
| CN106757005B (en) | A kind of laser repair method of heavy combustion engine wheel hub tenon tooth | |
| CN115740950A (en) | DZ125 alloy based on reverse modeling turbine blade laser deposition repair method | |
| Kenda et al. | Investigation of the surface integrity induced by abrasive flow machining on AISI D2 hardened steel | |
| Minetola et al. | Experimental validation of laser powder bed fusion simulation | |
| Luo et al. | Investigating the effect of WEDM process parameters on 3D micron-scale surface topography related to fractal dimension | |
| Mouralova et al. | Micro-milling machinability of pure molybdenum | |
| Wu et al. | Modeling of grinding chip thickness distribution based on material removel mode in grinding of SiC ceramics | |
| CN113909600A (en) | Quality evaluation method for turbine blade electrosparking gas film hole | |
| CN108044509B (en) | A kind of grinding wheel dressing method guaranteeing crank spindle radius quality |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |