CN117327896A - Laser shock strengthening shape control method and device for blade - Google Patents
Laser shock strengthening shape control method and device for blade Download PDFInfo
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- CN117327896A CN117327896A CN202311207110.0A CN202311207110A CN117327896A CN 117327896 A CN117327896 A CN 117327896A CN 202311207110 A CN202311207110 A CN 202311207110A CN 117327896 A CN117327896 A CN 117327896A
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- 238000005728 strengthening Methods 0.000 title claims abstract description 69
- 238000000034 method Methods 0.000 title claims abstract description 58
- 230000035939 shock Effects 0.000 title claims abstract description 36
- 238000012937 correction Methods 0.000 claims abstract description 14
- 239000000843 powder Substances 0.000 claims abstract description 11
- 238000005507 spraying Methods 0.000 claims abstract description 11
- 238000013075 data extraction Methods 0.000 claims abstract description 4
- 230000000399 orthopedic effect Effects 0.000 claims description 12
- 230000002787 reinforcement Effects 0.000 claims description 12
- 230000002745 absorbent Effects 0.000 claims description 3
- 239000002250 absorbent Substances 0.000 claims description 3
- 238000004140 cleaning Methods 0.000 claims description 3
- 238000000605 extraction Methods 0.000 claims description 3
- 238000002310 reflectometry Methods 0.000 claims description 3
- 238000004088 simulation Methods 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims description 2
- 230000003287 optical effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 7
- 238000001514 detection method Methods 0.000 abstract description 4
- 239000000463 material Substances 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 4
- 230000003116 impacting effect Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 238000002679 ablation Methods 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 210000002381 plasma Anatomy 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 208000016063 arterial thoracic outlet syndrome Diseases 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008033 biological extinction Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 239000008367 deionised water Substances 0.000 description 1
- 229910021641 deionized water Inorganic materials 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 239000005304 optical glass Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 239000010409 thin film Substances 0.000 description 1
- 239000004408 titanium dioxide Substances 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
Classifications
-
- 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
-
- 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
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Optics & Photonics (AREA)
- Laser Beam Processing (AREA)
Abstract
The application discloses a laser shock strengthening shape control method for a blade, wherein the laser shock strengthening shape control method comprises the steps of acquiring She Panlun three-dimensional coordinate data, establishing a model I1, planning process parameters, blade shock strengthening, deformation detection and blade correction strengthening; the laser shock strengthening device comprises a complete machine control system, a laser control system, a point cloud data extraction system, a powder spraying control system and a mechanical arm control system. The method has the advantages that the free-form surface blade is guaranteed to be strengthened, the deformation effect of the blade is controlled, and the blade precision is improved.
Description
Technical Field
The invention relates to the technical field of laser processing, in particular to a laser shock strengthening shape control method for a blade.
Background
The laser shock strengthening technology is a material surface strengthening treatment technology. By utilizing short pulse and high peak power density laser to radiate the material surface, an absorption layer (black tape, aluminum foil and the like) on the material surface absorbs laser energy to generate explosive vaporization and evaporation, high-temperature and high-pressure plasmas are generated, and the plasmas generate high-strength pressure shock waves on a constrained layer (deionized water, K9 optical glass, silica gel and the like), and the shock waves act on the material surface and propagate into the material. When the peak pressure of the shock wave exceeds the dynamic yield limit of the processed material, the material is strained and hardened, and great compressive stress is generated. By the laser shock reinforcement technology, the material acquires residual compressive stress, so that the fatigue resistance, corrosion resistance, abrasion resistance and other performances of the material are improved. Therefore, the method is widely applied to the fields of high-end equipment such as aerospace, energy, traffic and the like.
Under the high-speed rotation driving of the rotor and the flushing of strong air flow, the aero-engine blade bears various loads such as stretching, bending, vibration and the like, and has bad working conditions. The edges of the titanium alloy blades at the front stages of the engine are very sensitive to foreign matter damage, once gaps are formed, the fatigue strength of the blades is rapidly reduced, the service life of the blades is reduced when the gaps are light, and the engine is lost when the gaps are heavy. Therefore, the comprehensive performance of the engine blade can be improved by a laser shock peening technology. However, in the strengthening process, the blade is macroscopically deformed due to the stress balance effect, and when the deformation exceeds a certain range, the use of the engine is seriously affected.
Disclosure of Invention
The invention provides a laser shock strengthening shape control method and device for a blade, which aim to ensure that the blade with a free-form surface can obtain strengthening effect, control the deformation generated by the blade and improve the precision of the blade.
According to one aspect of the present invention, there is provided a laser shock peening control method for a blade, comprising the steps of:
s1, acquiring She Panlun three-dimensional coordinate data and establishing a model I1;
s2, planning process parameters, wherein the process parameters comprise dividing an impact area, dividing the blade into a strengthening area and an orthopedic area according to the distance between the blade and the blade root, wherein the strengthening area is close to the blade root, and the orthopedic area is far away from the blade root; dividing the strengthening area into an area a and an area b according to the radian of the blade, wherein the area a is close to the blade root, and the area b is far away from the blade root;
s3, blade impact strengthening, namely carrying out laser impact strengthening on the region a and the region b of the blade by adopting planned technological parameters;
s4, detecting the deformation, obtaining the reinforced She Panlun profile model information I2, comparing the original data I1 and I2, calculating the deformation Q1 generated by the reinforced blade, and judging whether the numerical value of the deformation Q1 is within the required tolerance range. If the deformation Q1 is within the tolerance range, the strengthening is finished; if the deformation Q1 exceeds the tolerance range Q0, performing a blade reshaping strengthening step;
s5, blade correction and strengthening, namely performing correction and strengthening impact on a region c of the blade by adopting a single laser beam; after the single orthopedic reinforcement impact is completed, steps S1 and S5 are repeated until the deformation Q1 is within the tolerance range.
Optionally, in the step S3, the predetermined process parameters include a laser incident angle α, based on the original She Panlun profile model I1, and the simulation software is used to perform optical path simulation, so as to solve the incident angle that does not interfere with other blades during impact reinforcement of the blades, so as to obtain the laser incident angle α.
Alternatively, the angle α has a value of 20 ° to 70 °.
Optionally, in the step S3, the impact strengthening of the blade adopts dual laser to synchronously perform impact strengthening on two sides of the blade.
Optionally, in step S3, the predetermined process parameter includes an impact path, and a continuous overlap-free impact path is adopted, and the impact path direction is from the blade root to the blade tip.
Optionally, in the step S3, before performing blade impact strengthening, strengthening pretreatment is performed on the blade, where the strengthening pretreatment includes the following steps: cleaning the impact area, and ensuring that the impact area is clean and free of foreign matters; an absorbent layer is attached to the impact region.
Optionally, in the step S3, the predetermined process parameter includes laser energy Q, and according to the model M1 and the impact path, the thickness of the blade on the impact path is calculated, where the magnitude of the laser energy Q is in a proportional relationship with the magnitude of the thickness of the blade.
Optionally, in step S1, a blue light three-dimensional scanner is used to send a blue light beam to the impeller disc, a reflection signal of the impeller disc is received through multiple lenses, three-dimensional coordinates of the surface points are calculated, reflectivity and texture information are recorded, she Pandian cloud information is obtained, and the surface profile information of the impeller disc is extracted through She Pandian cloud information to serve as original data I1 of a reference for deformation of the impeller disc.
Optionally, in step S5, a single laser beam is used to perform blade correction in the region c, and a laser beam in a corresponding direction is used to perform correction according to the deformation direction of the blade.
According to another aspect of the present invention, there is also provided a laser shock peening apparatus for a blade, which is characterized in that the laser shock peening control method for a blade includes: the system comprises a complete machine control system, a laser control system, a point cloud data extraction system, a powder spraying control system and a mechanical arm control system, wherein the complete machine control system is connected with the laser control system, the point cloud extraction system, the powder spraying control system and the mechanical arm control system, and all the subsystems are controlled by the complete machine system to cooperatively work.
In summary, the present application includes at least one of the following beneficial technical effects:
the laser shock strengthening parameters are optimized through extracting the blade point cloud information; the deformation amount of the blade in the strengthening process is regulated and controlled by obtaining the specific direction and the numerical value of the deformation of the blade after strengthening and carrying out the blade shape correcting process. Compared with the prior art, the method realizes the accurate control of the strengthening effect by calculating various input parameters. In addition, the method integrates laser strengthening and detection, and automatically feeds back the detection result to the laser processing process, so that the time for clamping and manually detecting the blade is saved, and the laser shock strengthening efficiency of the free-form surface is greatly improved.
In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a flow chart of a laser shock peening control method according to a preferred embodiment of the present invention;
FIG. 2 is a schematic view of the impact area of a preferred embodiment of the present invention;
FIG. 3 is a schematic diagram of a strengthening path according to a preferred embodiment of the present invention;
FIG. 4 is a schematic illustration of a lap-free impingement path according to a preferred embodiment of the present invention;
FIG. 5 is a schematic view of a blade impact reinforcement path according to a preferred embodiment of the present invention;
FIG. 6 is a schematic view of a blade orthopedic reinforcement path according to a preferred embodiment of the present invention;
fig. 7 is a schematic view of a laser shock peening apparatus according to a preferred embodiment of the present invention.
Legend description:
1. a computer complete machine control system; 2. a laser control system; 3. a three-dimensional scanning system; 4. a powder spraying control system; 5. a robotic arm control system; 6. a powder spraying machine; 7. a blade; 8. a clamp; 9. a work table; 10. a three-dimensional scanner; 11. a mechanical arm; 12. a lighting lamp; 13. a water coating device; 14. a water coating device; 15. a laser; 16. a laser.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawing figures, but the invention can be practiced in a number of different ways, as defined and covered below.
The present application is described in further detail below in conjunction with figures 1-7.
The embodiment of the application discloses a laser shock enhancement shape control method for a blade.
Referring to fig. 1, a laser shock peening control method for a blade is characterized by comprising the steps of:
s1, acquiring She Panlun three-dimensional coordinate data and establishing a model I1;
s2, dividing an impact area, dividing the blade into a strengthening area and an orthopedic area according to the distance between the blade and the blade root, wherein the strengthening area is close to the blade root, and the orthopedic area is far away from the blade root; dividing the strengthening area into an area a and an area b according to the radian of the blade, wherein the area a is close to the blade root, and the area b is far away from the blade root;
s3, blade impact strengthening, namely carrying out laser impact strengthening on the areas a and b of the blade by adopting preset technological parameters;
s4, detecting the deformation, obtaining the reinforced She Panlun profile model information I2, comparing the original data I1 and I2, calculating the deformation Q1 generated by the reinforced blade, and judging whether the numerical value of the deformation Q1 is within the required tolerance range. If the deformation Q1 is within the tolerance range, the strengthening is finished; if the deformation Q1 exceeds the tolerance range Q0, performing a blade reshaping strengthening step;
s5, blade correction and strengthening, namely performing correction and strengthening impact on a region c of the blade by adopting a single laser beam; after the single orthopedic reinforcement impact is completed, steps S1 and S5 are repeated until the deformation Q1 is within the tolerance range.
Referring to fig. 2 and 3, in the present embodiment, the real coordinate data of the impeller is obtained by scanning and a model is built, and the parameters of laser shock peening are planned according to the actual shape of She Panlun instead of the theoretical shape, so that the machining precision can be improved. Because the blade is a cantilever beam, the whole deformation generated in the a and b strengthening areas (near the blade root) is overlapped, and finally the maximum deformation is shown in the c area (near the blade tip), so that the correction strengthening is carried out in the c area according to the actual deformation condition, and the accumulated deformation in the a and b area impact strengthening process can be compensated while the strengthening is carried out, and the deformation of the blade after the strengthening process is further reduced.
Step S1, acquiring She Panlun three-dimensional coordinate data and establishing a model I1, wherein a blue light three-dimensional scanner is used for sending out blue light beams to an impeller disc, reflection signals of the impeller disc are received through multiple lenses, three-dimensional coordinates of surface points are calculated, reflectivity and texture information are recorded, she Pandian cloud information is obtained, and leaf disc surface profile information is extracted through She Pandian cloud information to serve as original data I1 of a reference for leaf disc deformation. In a specific embodiment, a GOM ATOS Q blue light three-dimensional scanner is used, an LED blue light source is adopted, the number of single scanning points is 800 ten thousand, the scanning range size is 120 multiplied by 80mm, the point spacing is 0.033mm, the detection error is 0.003mm, and an optical fiber transmission mode is adopted for communication with a computer host.
Optionally, in order to enable the impeller in the step S1 to better reflect signals and obtain more accurate coordinate data, before scanning the blades, powder spraying extinction treatment is required, titanium dioxide powder and 99% absolute ethyl alcohol are used, blending is carried out according to the proportion of 1 to 20 by weight, and then spraying is carried out, so that even coverage of white titanium powder is ensured, and the white titanium powder is in a thin film mist shape.
In step S2, the process parameters to be planned include the impact mode, the impact area, the impact path, the laser energy Q, and the laser incident angle α.
Impact mode and impact area: in the areas a and b, the impact strengthening of the blade adopts double lasers to synchronously carry out the impact strengthening on the two sides of the blade; in region c, unilateral laser is used for orthopedic purposes. The areas a and b are vulnerable areas of the blade under working conditions. The reason why the reinforced region is divided into the regions a and b is that the blades interfere with each other, and it is difficult to cover the reinforced region entirely by oblique incidence at the same angle. The double laser beams are selected to strengthen the front and back sides simultaneously, so that the forces in the normal direction of the blade serving as the cantilever beam cancel one another, and the deformation of the blade is reduced. By adopting a double-sided strengthening mode without lap joint tracks, the surface ablation of the blade can be prevented, the strengthening effect of the blade is improved, and the integral deformation of the blade is reduced. The region c is an orthopedic region. Because the blade is cantilevered, the overall deformation produced in the a, b strengthening areas (near the root) will overlap, eventually exhibiting the greatest amount of deformation in the c area (near the tip). Depending on the direction of deformation of the region c, the laser beam is used to correct the deformation direction. The track of the region c is shown in figure 2, so that the ablation of the surface of the blade can be prevented, the strengthening effect of the blade is improved, and the integral deformation of the blade is reduced.
Impact path: a continuous lap-free impact path is adopted, and the impact path direction is from the blade root to the blade tip. In a specific embodiment, the impingement path of each blade includes four impingement procedures, one for each: program 1, program 2, program 3 and program 4, wherein the paths of each impacting program are composed of impacting light spots distributed in a matrix, and the impacting light spots of program 1, program 2, program 3 and program 4 are uniformly distributed on the blade and jointly cover the surface of the blade. In order to ensure that no gap exists in the impact path, all positions on the blade can be impact reinforced, and the impact light spot edges of the procedure 1, the procedure 2, the procedure 3 and the procedure 4 are mutually overlapped. Procedure 1, procedure 2, procedure 3 and procedure 4 refer to four consecutive reinforcements in time sequence, four reinforcements being different parts of the same region (region a or region b).
The sequence of the light spots in each procedure of the non-overlap impact path is shown as a sequence number in fig. 4, for example, the light spots with two sequence numbers 1 in fig. 4 represent that the front and back surfaces of the blade are impacted for the first time by two laser beams.
a. The impact path of the b area is shown in fig. 5, the front and back sides are impacted simultaneously, and the light spot sequence is shown in the sequence number in the figure:
procedure 1:1-2-3-4-5-6-7-8;
procedure 2:9-10-11-12-13-14;
procedure 3:15-16-17-18-19-20-21-22;
procedure 4:23-24-25-26-27-28.
Referring to fig. 6, the impact path in the c region is the same as that in the b region, and the impact mode is a single-sided impact.
Laser incidence angle α: based on an original She Panlun profile model I1, carrying out light path simulation by using simulation software, and solving the incident angle which does not interfere with other blades when the blades are subjected to impact reinforcement so as to obtain a laser incident angle alpha, wherein the value of the angle alpha is 20-70 degrees. In a specific embodiment, the angle α has a value of 70 °.
Laser energy Q: according to the model M1 and the impact path, calculating the thickness of the blade on the impact path, wherein the laser energy Q is in a proportional relation with the thickness of the blade.
In step S3, before blade impact strengthening, the blade is first subjected to strengthening pretreatment, where the strengthening pretreatment includes the following steps: cleaning the impact area, and ensuring that the impact area is clean and free of foreign matters; an absorbent layer is attached to the impact region. Impact mode: adopts a dual-laser synchronous impact strengthening mode. The laser incidence angle α=70°. Impact area S: and selecting the regions a and b as double laser strengthening regions and the region c as a single laser correction region. Impact path R: a continuous lap-free impact path is adopted, and the direction is from the blade root to the blade tip. Laser energy Q: and the laser control system is used for automatically controlling according to the thickness of the blade. Overlap ratio: 30%. Spot diameter: 1mm.
In step S5, the stage is moved to the calibration area by the robot arm control system. And (3) correcting the shape: and (5) single-sided impact shaping. Incidence angle α: normal incidence. Impact path: continuous overlap, toward the tip. Overlap ratio: 30%. Spot diameter: 1mm. Energy: and (3) automatically planning shape correction energy according to the I2 information, wherein the laser energy Q is in a proportional relation with the thickness of the blade.
Referring to fig. 7, this embodiment further discloses a laser shock peening apparatus for a blade, which is used in the above laser shock peening control method for a blade, including: the system comprises a complete machine control system, a laser control system, a point cloud data extraction system, a powder spraying control system and a mechanical arm control system, wherein the complete machine control system is connected with the laser control system, the point cloud extraction system, the powder spraying control system and the mechanical arm control system, and all the subsystems are controlled by the complete machine system to cooperatively work.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The laser shock strengthening shape control method for the blade is characterized by comprising the following steps of:
s1, acquiring She Panlun three-dimensional coordinate data and establishing a model I1;
s2, planning process parameters, wherein the process parameters comprise dividing an impact area, dividing the blade into a strengthening area and an orthopedic area according to the distance between the blade and the blade root, wherein the strengthening area is close to the blade root, and the orthopedic area is far away from the blade root; dividing the strengthening area into an area a and an area b according to the radian of the blade, wherein the area a is close to the blade root, and the area b is far away from the blade root;
s3, blade impact strengthening, namely carrying out laser impact strengthening on the region a and the region b of the blade by adopting planned technological parameters;
s4, detecting the deformation, obtaining the reinforced She Panlun profile model information I2, comparing the original data I1 and I2, calculating the deformation Q1 generated by the reinforced blade, and judging whether the numerical value of the deformation Q1 is within the required tolerance range. If the deformation Q1 is within the tolerance range, the strengthening is finished; if the deformation Q1 exceeds the tolerance range Q0, performing a blade reshaping strengthening step;
s5, blade correction and strengthening, namely performing correction and strengthening impact on a region c of the blade by adopting a single laser beam; after the single orthopedic reinforcement impact is completed, steps S1 and S5 are repeated until the deformation Q1 is within the tolerance range.
2. The method for controlling the shape of a blade by laser shock peening according to claim 1,
in the step S2, the predetermined process parameters include a laser incident angle α, based on the original She Panlun profile model I1, and the simulation software is used to perform optical path simulation, so as to solve the incident angle that does not interfere with other blades when the blades are impact strengthened, so as to obtain the laser incident angle α.
3. The method for controlling the shape of a blade by laser shock peening according to claim 2,
the alpha angle is 20-70 deg.
4. The method according to claim 1, wherein in the step S3, the blade is impact reinforced by using dual lasers to synchronously impact-reinforce both sides of the blade.
5. The method for controlling the shape of a blade by laser shock peening according to claim 1,
in the step S2, the predetermined process parameters include an impact path, and a continuous overlap-free impact path is adopted, and the impact path direction is from the blade root to the blade tip.
6. The method for controlling the shape of a blade by laser shock peening according to claim 1,
in the step S3, before the blade is impact reinforced, the blade is first subjected to a reinforcement pretreatment, where the reinforcement pretreatment includes the following steps: cleaning the impact area, and ensuring that the impact area is clean and free of foreign matters; an absorbent layer is attached to the impact region.
7. The method for controlling the shape of a blade by laser shock peening according to claim 5,
in the step S2, the predetermined process parameters include laser energy Q, and according to the model M1 and the impact path, the thickness of the blade on the impact path is calculated, where the laser energy Q is proportional to the thickness of the blade.
8. The method for controlling the shape of a blade by laser shock peening according to claim 1,
in the step S1, a blue light three-dimensional scanner is used to send a blue light beam to the impeller disc, a reflection signal of the impeller disc is received through multiple lenses, three-dimensional coordinates of surface points are calculated, reflectivity and texture information are recorded, she Pandian cloud information is obtained, and leaf disc surface profile information is extracted through She Pandian cloud information to serve as original data I1 of a reference for the leaf disc deformation.
9. The method for controlling the shape of a blade by laser shock peening according to claim 1,
in the step S5, a single laser beam is used to perform blade correction work in the region c, and a laser beam in a corresponding direction is used to perform correction according to the deformation direction of the blade.
10. A laser shock peening apparatus for a blade, characterized by being used for the laser shock peening shape control method for a blade according to any one of claims 1 to 9, comprising:
the system comprises a complete machine control system, a laser control system, a point cloud data extraction system, a powder spraying control system and a mechanical arm control system, wherein the complete machine control system is connected with the laser control system, the point cloud extraction system, the powder spraying control system and the mechanical arm control system, and all the subsystems are controlled by the complete machine system to cooperatively work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311207110.0A CN117327896A (en) | 2023-09-19 | 2023-09-19 | Laser shock strengthening shape control method and device for blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311207110.0A CN117327896A (en) | 2023-09-19 | 2023-09-19 | Laser shock strengthening shape control method and device for blade |
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| Publication Number | Publication Date |
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| CN117327896A true CN117327896A (en) | 2024-01-02 |
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|---|---|---|---|
| CN202311207110.0A Pending CN117327896A (en) | 2023-09-19 | 2023-09-19 | Laser shock strengthening shape control method and device for blade |
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| Country | Link |
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2023
- 2023-09-19 CN CN202311207110.0A patent/CN117327896A/en active Pending
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