CN107858500B - A kind of blade laser peening intensifying method becoming the controllable residual stress of pulse width - Google Patents
A kind of blade laser peening intensifying method becoming the controllable residual stress of pulse width Download PDFInfo
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- CN107858500B CN107858500B CN201710916369.0A CN201710916369A CN107858500B CN 107858500 B CN107858500 B CN 107858500B CN 201710916369 A CN201710916369 A CN 201710916369A CN 107858500 B CN107858500 B CN 107858500B
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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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- 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
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Abstract
The present invention discloses a kind of blade laser peening intensifying method for becoming the controllable residual stress of pulse width, technical solution of the present invention is by taking leaf structure as the pulse width according to setting ps pulsed laser and ns pulsed laser, penetration depth of the control induction shock wave in blade, and then control the distributed depth for generating residual stress, the final residual stress distribution for realizing blade different zones is matched with the consistency of structure feature, is reached and is strengthened and conformal dual purpose.The distribution of leaf margin (intake and exhaust side) through thickness residual compressive stress can be achieved in the present invention, eliminates blade root stress and concentrates and the laser peening intensive treatment without macroscopic deformation, suitable for aviation turbofan engine fan, compressor titanium alloy blade at different levels.
Description
Technical field
The present invention relates to laser peening surface strengthening technology fields, the in particular to a kind of controllable residual stress of change pulse width
Blade laser peening intensifying method.
Background technique
Laser peening strengthen (Laser Shock Peening, LSP) be a kind of efficient surface strengthening technology, using swash
The mechanics effect of light shock wave forms amplitude residual compressive stress and microstructure variation on metal material surface layer, passes through introducing
Residual pressure inhibits fatigue strength and the service life of crack initiation and propagation and then lifting component, wherein the leaf of US Airways engine
The technology has been widely used in piece manufacturing process.
The fan or gas compressor blade chip size span of aero-engine be larger and wall thin (length is 20~800mm, wall thickness
For 0.5~2mm), and there is the cross section of complicated curved profile and variation, is typical weak rigid thin wall's class component.?
Following general character underlying issue: residual pressure caused by shot-peening is faced as introducing amplitude residual stress when carrying out laser peening reinforcing
The stress field strengthening effect consistency problem different with blade dimensions stability problem and variable section structure thickness.
To solve the above problems, " a kind of multi-layer intercrossed laser-impact of darkening spot is uniformly strong by Chinese patent CN105002349A
Change the method for blade " using adjacent spots closely overlapped mode, the interlayer for carrying out multiple darkening spot staggeredly impacts, wherein the
One layer of large spot is mainly used for laser-impact and generates deeper residual stress layer, and the second layer and third layer are staggeredly impacted for eliminating
Hot spot boundary effect reduces the roughness of finished surface.But this method only changes spot size and overlapping rate, there is no adjust
Control influences the laser energy and pulse width of residual stress distribution characteristic, therefore this method is only capable of within the scope of specific layer depth
The stress distribution of laser peening is homogenized, it cannot be guaranteed that form accuracy.
Chinese patent CN103205545 A " a kind of combined method and device of laser-impact processing engine blade " passes through
Distance between focus lamp and blade is adjusted to realize that power density is adjusted to adjust spot size, make blade edge surface layer residual pressure
Stress and untreated areas realize gentle transition.This method changes the power density of laser peening in itself, therefore can only adjust
Control generates residual stress amplitude, is unable to proof stress distributed depth, can not control form accuracy, and power density and hot spot
There are the constraint relationships for size, will lead to hot spot overlap joint boundary effect using large spot to thin wall vane, influence dimensional accuracy and table
Face quality.
Chinese patent CN104862468 A " method for improving turbine blade life based on laser double-surface impact technology " is used
Gradual change overlapping rate impact root of blade makes the changes in distribution of residual stress field tend towards stability, and impacts mode using laser double-surface, keeps away
Exempt from deformation and destruction that single side laser-impact causes blade, while impact keeps blade tow sides stress identical.But this method is only
Carried out the optimization of overlapping rate parameter, in itself for influence residual stress characteristics laser energy and pulse width parameter all
It is not set, therefore accuracy controlling is difficult to stress distribution range value and depth, do not have blade and strengthens and conformal process requirement.
Therefore keep the blade laser peening residual stress field during laser peening surface peening consistent with architectural characteristic
Property matching, and solve the technical issues of dimension control and residual stress characteristics control and be extremely important.
Summary of the invention
The main object of the present invention is to propose a kind of blade laser peening reinforcing side for becoming the controllable residual stress of pulse width
Method, it is intended to the consistency matching for improving blade laser peening residual stress field and architectural characteristic, solve dimension control and
The technical issues of residual stress characteristics control.
To achieve the above object, the present invention proposes that a kind of blade laser peening for becoming the controllable residual stress of pulse width is strengthened
Method, this method are according to setting ps pulsed laser and ns pulsed laser pulse width with leaf structure, and control induction shock wave is in blade
Interior penetration depth, so control generate residual stress distributed depth, realize blade different zones residual stress distribution with
Structure feature matches.
Preferably, the present invention becomes the blade laser peening intensifying method of the controllable residual stress of pulse width, including following step
It is rapid:
S1: according to the weak setting short pulse width of the thin rigidity of leaf margin wall thickness, with shallow depth residual compressive stress layer and multilayer shot-peening
Through thickness distribution of the compressive stress is realized in superposition；
S2: leaf margin is gradually increased to blade transition region thickness, and it is directly proportional to section thickness that setting becomes pulse width, and subtracts
Few shot-peening number, realizes stress gentle transition of the processing region to untreated areas；
S3: being arranged short-pulse laser shot-peening parameter at blade root, eliminate stress with shallow-layer residual compressive stress multilayer shot-peening and concentrate,
Avoid blade macroscopic view torsional deflection.
Preferably, the laser pulse width, penetration depth of the induction shock wave in blade, point for generating residual stress
It is positively correlated between cloth depth three.
Preferably, the shallower residual compressive stress of layer depth is generated using short-pulse laser shot-peening to be distributed, while keeping outside structure
Shape does not change.
Preferably, residual compressive stress is superimposed by multilayer shot-peening, realizes deeper stress distribution.
Technical solution of the present invention is by taking leaf structure as the pulse width according to setting ps pulsed laser and ns pulsed laser, control
Penetration depth of the shock wave in blade is induced, and then controls the distributed depth for generating residual stress, it is final to realize that blade is different
The residual stress distribution in region is matched with the consistency of structure feature, is reached and is strengthened and conformal dual purpose.
The present invention can be achieved leaf margin (intake and exhaust side) through thickness residual compressive stress distribution, eliminate blade root stress concentrate and without macro
See deformation, the laser peening intensive treatment suitable for aviation turbofan engine fan, compressor titanium alloy blade at different levels.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
The structure shown according to these attached drawings obtains other attached drawings.
Fig. 1 is the shock wave characteristics figure of 16ns of embodiment of the present invention pulse width induction；
Fig. 2 is the shock wave characteristics figure of 8ns of embodiment of the present invention pulse width induction；
Fig. 3 is blade of embodiment of the present invention laser peening processing region figure；
Fig. 4 is short-pulse laser shot-peening schematic diagram at leaf margin of the embodiment of the present invention；
Fig. 5 is leaf margin of the embodiment of the present invention to blade transition region shot-peening schematic diagram；
Fig. 6 is blade root of embodiment of the present invention laser peening schematic diagram.
Drawing reference numeral explanation:
| Label | Title | Label | Title |
| 1 | The shock wave of 16ns pulse width induction | 7 | It is vented side |
| 2 | The shock wave of 8ns pulse width induction | 8 | Blade root |
| 3 | Test specimen | 9 | Leaf cross-section |
| 4 | Induce shock wave | 10 | Thickness is to residual stress distribution |
| 5 | Blade | 11 | Blade transition region |
| 6 | Leading edge | 12 | Fillet |
The embodiments will be further described with reference to the accompanying drawings for the realization, the function and the advantages of the object of the present invention.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.Base
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
It is to be appreciated that if relating to directionality instruction (such as up, down, left, right, before and after ...) in the embodiment of the present invention,
Then directionality instruction be only used for explain under a certain particular pose (as shown in the picture) between each component relative positional relationship,
Motion conditions etc., if the particular pose changes, directionality instruction is also correspondingly changed correspondingly.
In addition, being somebody's turn to do " first ", " second " etc. if relating to the description of " first ", " second " etc. in the embodiment of the present invention
Description be used for description purposes only, be not understood to indicate or imply its relative importance or implicitly indicate indicated skill
The quantity of art feature." first " is defined as a result, the feature of " second " can explicitly or implicitly include at least one spy
Sign.It in addition, the technical solution between each embodiment can be combined with each other, but must be with those of ordinary skill in the art's energy
It is enough realize based on, will be understood that the knot of this technical solution when conflicting or cannot achieve when occurs in the combination of technical solution
Conjunction is not present, also not the present invention claims protection scope within.
The present invention proposes a kind of blade laser peening intensifying method for becoming the controllable residual stress of pulse width, and this method is with leaf
Chip architecture feature is according to setting ps pulsed laser and ns pulsed laser pulse width, and control induces penetration depth of the shock wave in blade, into
And the distributed depth for generating residual stress is controlled, realize that the residual stress distribution of blade different zones matches with structure feature.
Specifically, the present invention becomes the blade laser peening intensifying method of the controllable residual stress of pulse width, including following step
It is rapid:
S1: according to the weak setting short pulse width of the thin rigidity of leaf margin wall thickness, with shallow depth residual compressive stress layer and multilayer shot-peening
Through thickness distribution of the compressive stress is realized in superposition；
S2: leaf margin is gradually increased to blade transition region thickness, and it is directly proportional to section thickness that setting becomes pulse width, and subtracts
Few shot-peening number, realizes stress gentle transition of the processing region to untreated areas；
S3: being arranged short-pulse laser shot-peening parameter at blade root, eliminate stress with shallow-layer residual compressive stress multilayer shot-peening and concentrate,
Avoid blade macroscopic view torsional deflection.
Preferably, the laser pulse width, penetration depth of the induction shock wave in blade, point for generating residual stress
It is positively correlated between cloth depth three.
Preferably, the shallower residual compressive stress of layer depth is generated using short-pulse laser shot-peening to be distributed, while keeping outside structure
Shape does not change.
Preferably, residual compressive stress is superimposed by multilayer shot-peening, realizes deeper stress distribution.
Embodiment
Since the selection of ps pulsed laser and ns pulsed laser shot-peening power density is related to material to be processed, processing region operating condition.This hair
The blade of bright embodiment is the titanium alloy blade of material TC4 or TC17, and selection laser peening power density is 5~7GW/cm2,
According to laser power density formula I=E/ (S × t), wherein E is laser single-pulse energy, and S is facula area, and t is laser pulse
Width.Wherein laser single-pulse energy E influences to generate the amplitude of residual stress, and laser pulse width t influences point of residual stress
Cloth depth.
The work for becoming the blade laser peening intensifying method of the controllable residual stress of pulse width in technical solution of the present invention is former
Reason is that laser pulse width, induction shock wave are between the distributed depth three of penetration depth, residual stress in blade in just
Correlation generates the shallower residual compressive stress of layer depth using short-pulse laser shot-peening and is distributed, while keeping construction profile constant, passes through
Multilayer shot-peening is superimposed residual compressive stress, realizes deeper stress distribution.
In Fig. 1, when inputting laser pulse width is 16ns, on 3 thickness direction of test specimen, the induction of 16ns pulse width
1 penetration depth of shock wave it is as shown in Figure 1.In Fig. 2, when inputting laser pulse width is 8ns, in 3 thickness direction of test specimen
On, 2 penetration depth of shock wave of 8ns pulse width induction is as shown in Figure 2.Obviously, on 3 thickness direction of test specimen, when input swashs
The short pulse that it is 8ns when input laser pulse width that the penetration depth for the long pulse width that light impulse length is 16ns, which is deeper than, is wide
Degree.
Technical solution of the present invention is with the pulse width that leaf structure is according to setting ps pulsed laser and ns pulsed laser, control production
The distributed depth of residual stress, the final residual stress distribution for realizing 5 different zones of blade are matched with the consistency of structure feature,
Reach and strengthens and conformal dual purpose.As shown in figure 3, the region that blade 5 is handled includes leading edge 6, exhaust side
7, the blade root 8 on blade face and tongue-and-groove transition position, by different-thickness region need be arranged become pulse width realize residual stress with
Structure feature matches.
Specifically, the step of blade laser peening intensifying method of the present invention change controllable residual stress of pulse width includes:
Fig. 4 is referred to, according to the weak corresponding short pulse width of setting of the thin rigidity of leaf margin wall thickness, with shallow depth residual stress layer
It is superimposed with multilayer shot-peening and realizes through thickness distribution of the compressive stress.Leaf cross-section 9 is the distribution of not uniform thickness, and leading edge 6 uses the short arteries and veins of 8ns
Impulse light bead, the depth for generating induction shock wave 4 is shallower, while being handled by multiple-layer stacked and guaranteeing form accuracy, most
It is generated eventually in leading edge through thickness section thick to residual stress distribution 10.
Fig. 5 is referred to, is then gradually increased from leaf margin to blade transition region thickness, setting becomes pulse width and section thickness
Matching reduces shot-peening number, realizes stress gentle transition of the processing region to untreated areas.Leaf margin is thick to blade transition region 11
Degree is gradually increased, and the effect that this region carries out laser peening processing is the stress ladder slowed down between processing region and untreated areas
Degree keeps residual stress strengthening effect.Therefore the pulse width of gradual change is set according to blade face thickness, section is [8ns, 16ns],
Pulse width and section thickness are proportional.It generates gradual change and induces shock wave 4, gradually transition more balances by total pressure stress distribution
Distribution curve of stress.As shown in Figure 5 is thick to residual stress distribution 10.
Fig. 6 is referred to, short-pulse laser shot-peening parameter is set at blade root, with the elimination of shallow-layer residual compressive stress multilayer shot-peening
Stress is concentrated, and blade macroscopic view torsional deflection is avoided.Fillet 12 at the transition region blade root of blade face, the stress as caused by size mutation
The service performance for seriously affecting blade is concentrated, shallower residual compressive stress layer is formed using 8ns short-pulse laser shot-peening parameter and is protected
Blade is held without macroscopic deformation, 3-5 shot-peening is then carried out and is superimposed to form strong constraint residual compressive stress, so as to improve answering for blade root 8
Power is concentrated.
The blade laser peening intensifying method that the present invention becomes the controllable residual stress of pulse width can realize leaf margin (intake and exhaust
Side) distribution of through thickness residual compressive stress, it eliminates blade root stress and concentrates without macroscopic deformation, be suitable for aviation turbofan engine wind
The laser peening intensive treatment of fan, compressor titanium alloy blade at different levels.
The above description is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all at this
Under the design of invention, using equivalent structure transformation made by description of the invention and accompanying drawing content, or directly/it is used in it indirectly
He is included in scope of patent protection of the invention relevant technical field.
Claims (4)
1. a kind of blade laser peening intensifying method for becoming the controllable residual stress of pulse width, which is characterized in that including following step
It is rapid:
S1: it according to the weak setting short pulse width of the thin rigidity of leaf margin wall thickness, is superimposed with shallow depth residual compressive stress layer and multilayer shot-peening
Realize through thickness distribution of the compressive stress；
S2: leaf margin is gradually increased to blade transition region thickness, and it is directly proportional to section thickness that setting becomes pulse width, and reduces spray
Ball number realizes stress gentle transition of the processing region to untreated areas；
S3: being arranged short-pulse laser shot-peening parameter at blade root, eliminate stress with shallow-layer residual compressive stress multilayer shot-peening and concentrate, avoid
Blade macroscopic view torsional deflection；
It is according to setting ps pulsed laser and ns pulsed laser pulse width, control induction shock wave penetrating in blade with leaf structure
Depth, and then the distributed depth for generating residual stress is controlled, realize the residual stress distribution and structure feature of blade different zones
Match.
2. becoming the blade laser peening intensifying method of the controllable residual stress of pulse width as described in claim 1, feature exists
In the distributed depth three of the laser pulse width, the penetration depth for inducing shock wave in blade, the residual stress
It is positively correlated between person.
3. becoming the blade laser peening intensifying method of the controllable residual stress of pulse width as described in claim 1, feature exists
In generating the shallower residual compressive stress of layer depth using short-pulse laser shot-peening and be distributed, while construction profile being kept not change.
4. becoming the blade laser peening intensifying method of the controllable residual stress of pulse width as described in claim 1, feature exists
In, by multilayer shot-peening be superimposed residual compressive stress, realize deeper stress distribution.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710916369.0A CN107858500B (en) | 2017-09-30 | 2017-09-30 | A kind of blade laser peening intensifying method becoming the controllable residual stress of pulse width |
| PCT/CN2018/102597 WO2019062427A1 (en) | 2017-09-30 | 2018-08-28 | Method with variable pulse width and controllable residual stress for laser shock peening of blades |
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| CN201710916369.0A CN107858500B (en) | 2017-09-30 | 2017-09-30 | A kind of blade laser peening intensifying method becoming the controllable residual stress of pulse width |
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| CN107858500B true CN107858500B (en) | 2019-06-14 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107858500B (en) * | 2017-09-30 | 2019-06-14 | 广东工业大学 | A kind of blade laser peening intensifying method becoming the controllable residual stress of pulse width |
| CN108728782B (en) * | 2018-05-31 | 2021-08-17 | 中国人民解放军空军工程大学 | Method for absorbing shock wave of nanosecond pulse laser shock-strengthened titanium alloy thin blade |
| CN108531713B (en) * | 2018-06-25 | 2020-03-27 | 广东工业大学 | Multilayer laser shock peening method and device |
| CN110438426A (en) * | 2019-09-19 | 2019-11-12 | 中国人民解放军空军工程大学 | A kind of laser impact intensified process of titanium alloy slim vane variable pulse width |
| CN110938740B (en) * | 2019-10-31 | 2021-07-27 | 中国航发沈阳黎明航空发动机有限责任公司 | Intermetallic compound laser shock peening life prolonging and deformation control method |
| CN115821027A (en) * | 2022-10-25 | 2023-03-21 | 北京翔博科技股份有限公司 | Method, device and equipment for eliminating residual stress based on laser ultrasound |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101275177A (en) * | 2007-11-30 | 2008-10-01 | 江苏大学 | Anti-fatigue controlled laser shot peening method and device therefor |
| CN101288888A (en) * | 2008-06-25 | 2008-10-22 | 中国科学院力学研究所 | Laser and blast compound forming method based prestress force |
| CN103014278A (en) * | 2012-12-25 | 2013-04-03 | 中国人民解放军空军工程大学 | Method for improving blade fatigue strength through comprehensive means |
| CN103898297A (en) * | 2012-12-24 | 2014-07-02 | 中国科学院沈阳自动化研究所 | Laser shock peening method of blisk |
| CN105385839A (en) * | 2014-09-09 | 2016-03-09 | 中国科学院沈阳自动化研究所 | System and method for automatic control over laser shock peening |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6558485B2 (en) * | 2001-08-13 | 2003-05-06 | General Electric Company | Laser shock peening with an explosive coating |
| CN107858500B (en) * | 2017-09-30 | 2019-06-14 | 广东工业大学 | A kind of blade laser peening intensifying method becoming the controllable residual stress of pulse width |
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2017
- 2017-09-30 CN CN201710916369.0A patent/CN107858500B/en active Active
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2018
- 2018-08-28 WO PCT/CN2018/102597 patent/WO2019062427A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101275177A (en) * | 2007-11-30 | 2008-10-01 | 江苏大学 | Anti-fatigue controlled laser shot peening method and device therefor |
| CN101288888A (en) * | 2008-06-25 | 2008-10-22 | 中国科学院力学研究所 | Laser and blast compound forming method based prestress force |
| CN103898297A (en) * | 2012-12-24 | 2014-07-02 | 中国科学院沈阳自动化研究所 | Laser shock peening method of blisk |
| CN103014278A (en) * | 2012-12-25 | 2013-04-03 | 中国人民解放军空军工程大学 | Method for improving blade fatigue strength through comprehensive means |
| CN105385839A (en) * | 2014-09-09 | 2016-03-09 | 中国科学院沈阳自动化研究所 | System and method for automatic control over laser shock peening |
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| CN107858500A (en) | 2018-03-30 |
| WO2019062427A1 (en) | 2019-04-04 |
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