CN105862046A - Device and method for strengthening surface of aero engine part - Google Patents
Device and method for strengthening surface of aero engine part Download PDFInfo
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- CN105862046A CN105862046A CN201610354631.2A CN201610354631A CN105862046A CN 105862046 A CN105862046 A CN 105862046A CN 201610354631 A CN201610354631 A CN 201610354631A CN 105862046 A CN105862046 A CN 105862046A
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
- C23F17/00—Multi-step processes for surface treatment of metallic material involving at least one process provided for in class C23 and at least one process covered by subclass C21D or C22F or class C25
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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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Abstract
The invention provides a device and method for strengthening the surface of an aero engine part. The device comprises a multi-degree-of-freedom robot, a clamping module, a three-dimensional shape measuring module, a nanometer composite coating addition module, high-power short-pulse laser devices, a sprayer module, a shock wave intensity detecting module and a controller, wherein the robot is used for driving a workpiece to move; the clamping module is used for mounting of the workpiece and connected with the robot; the three-dimensional shape measuring module is used for detecting the appearance outline of the workpiece; the nanometer composite coating addition module is used for adding a nanometer composite coating on the surface of the workpiece; the high-power short-pulse laser devices are used for emitting pulse laser towards the surface of the workpiece; the sprayer module is used for spraying a liquid to a contact area between a laser beam and the surface of the workpiece in a laser shock strengthening process; and the shock wave intensity detecting module is used for detecting the intensity of a shock wave induced by the pulse laser on the surface of the workpiece. After the device provided by the invention is adopted for strengthening the workpiece, the surface of the strengthened workpiece is resistant to abrasion and high-temperature creep, and the strengthened workpiece is high in stability, higher in hardness and stable in residual stress at high temperature. Accordingly, stable operation of the strengthened workpiece, namely the strengthened aero engine part, can be guaranteed, and the fatigue life can be prolonged.
Description
Technical field
The present invention relates to complex parts surface Hardening Treatment field in aero-engine, be specifically related to device and the intensifying method of a kind of aircraft engine parts surface peening based on nLSP combination process.
Background technology
Parts in aero-engine, such as turbo blade, blisk etc., are operated under high temperature, environment under high pressure, the stability under the high temperature of part, wear-resisting, creep-resistant property etc. are had the highest requirement.Complex parts is implemented relatively difficult by traditional shot peening strengthening, easily cause the deformation of thin-wall part, affecting surface roughness and size, nLSP technology used in the present invention then avoids this shortcoming, can guarantee that the mechanical performance at high temperature of the surface of the work after strengthening simultaneously.
At present, patent CN103614541B " for laser reinforcing device and the laser impact intensified processing method of surface of the work " in terms of laser impact intensified discloses a kind of device improving laser induced shock wave utilization ratio, and patent CN103898281A " blisk covers the laser impact intensified laser head in position " discloses a kind of flexibility laser head and improves the working ability to blisk.But the limiting layer that the reiforcing laser impact technology of these patents uses mostly is aqueous solution, and shock wave is more weak, inefficiency.
Summary of the invention
It is an object of the invention to provide device and the intensifying method of a kind of aircraft engine parts surface peening based on nLSP combination process, it is intended to for solving existing traditional schedule of reinforcement relatively difficult to complex parts enforcement, easily cause the deformation of thin-wall part, affect surface roughness and size and ineffective problem.
The present invention is achieved in that
The present invention provides the device of a kind of aircraft engine parts surface peening, it is characterised in that including: multi-freedom robot, is used for driving workpiece to move；Clamping module, is used for installing workpiece, and it is connected with described robot；Measuring three-dimensional morphology module, for detecting the profile of surface of the work；Nano composite material coating adds module, for adding nano composite material coating at surface of the work；High-power short-pulse laser, for surface of the work emission pulse laser；Head module, for spraying liquid to laser beam with surface of the work contact area during laser impact intensified；Shock strength detection module, for detecting the shock strength that pulse laser induces at surface of the work；And controller, it is used for controlling to coordinate the work of whole device.
Further, the artificial six-shaft industrial robot of described machine or multiple degrees of freedom portal frame form robot.
Further, described nano composite material coating adds module employing laser direct deposition or plasma spray technology.
Further, described nano composite material coating interpolation module is provided with the multiple nozzles forming array.
Further, the liquid of described head module injection is H2O2 or isopropanol.
Further, also include the body for installing fixing modules, described body comprises the subsystem for reclaiming, filter and repair the solution that head module sprays.
Further, described measuring three-dimensional morphology module is three-dimensional laser scanner or binocular camera.
Further, described shock strength detection module is piezoelectric transducer.
Further, described high-power short-pulse laser has two, and one of them is used for laser impact intensified process, can be nanosecond YAG, psec or femto-second laser；Another is used for crystallization nano composite material coating, can be the combination of continuous-wave laser or continuous-wave laser and nanosecond laser.
The present invention provides the intensifying method of a kind of device based on the aircraft engine parts surface peening described in any of the above-described item, it is characterised in that comprise the following steps:
(1) nano composite material coating is added at surface of the work, it includes being installed in robot workpiece by clamping workpiece module, measuring three-dimensional morphology module is used to obtain the surface profile data of workpiece, the threedimensional model on controller obtains these data and reconstruction is gone to work part surface, and carry out processing of robots path planning, robot drives workpiece to move to nano composite material coating interpolation module, nano composite material coating add module and be coated with one or more layers uniform nano composite material coating to surface of the work；
(2) surface of the work carries out crystallization process, its implementation is that high-power short-pulse laser launches the pulse laser of certain power to surface of the work, making the crystal boundary in nano composite material merge, robot drives workpiece to move, and the crystallization completing whole workpiece processes；
(3) again surface of the work is carried out laser impact intensified, the process of implementing is: use measuring three-dimensional morphology module to obtain the surface profile data of workpiece, the threedimensional model on controller obtains these data and reconstruction is gone to work part surface, and carry out processing of robots path planning, robot drives workpiece to move to the initial position of laser impact intensified process, head module sprays liquid on workpiece, the most high-power short-pulse laser emission pulse laser on workpiece, robot drives workpiece to move, and completes the intensive treatment of whole workpiece.
The method have the advantages that
1, the present invention uses combination process that aircraft engine parts surface is carried out intensive treatment, first add nano composite material coating at surface of the work, carry out laser crystallization process the most again, it it is finally laser impact intensified process, nano material hard particles fully acts in laser impact intensified with the matrix material of workpiece, effect carved by the nail utilizing nano material hard particles, prevent the sliding of dislocation, this characteristic is at high temperature, remain under high pressure keep stable, so the surface of the work after Qiang Hua has wearability, high temperature creep-resisting and at high temperature have high stability, hardness improves, residual stress is stable, ensure that aviation part is at high temperature, steady operation under high pressure, fatigue life.
2, the limiting layer during laser impact intensified is strong oxidizing solution H2O2 or high energy density liquid isopropanol, can obtain higher shock wave, improves working (machining) efficiency.
3, workpiece is driven mobile by robot, flexible high, is possible not only to carry out plane machining, it is possible to be processed curved surface of high curvature.
Accompanying drawing explanation
The schematic diagram of the device of a kind of aircraft engine parts surface peening that Fig. 1 provides for the embodiment of the present invention；
The process chart that surface of the work is strengthened that Fig. 2 provides for the embodiment of the present invention；
Machining area schematic diagram when workpiece is carried out laser impact intensified that Fig. 3 provides for the embodiment of the present invention.
Description of reference numerals: 1-robot, 2-clamping module, 3-workpiece, 4-shock strength detection module, 5-body, 6-nano composite material coating adds module, the high-power short-pulse laser of 7-, 8-head module, 9-measuring three-dimensional morphology module.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, all other embodiments that those of ordinary skill in the art are obtained under not making creative work premise, broadly fall into the scope of protection of the invention.
As shown in Figure 1, the embodiment of the present invention provides the device of a kind of aircraft engine parts surface peening, including multi-freedom robot 1, for installing the clamping module 2 of workpiece 3, for detecting the shock strength detection module 4 of pulse laser induction shock strength, for installing the body 5 of fixing modules, module 6 is added for adding the nano composite material coating of nano composite material coating on workpiece 3 surface, high-power short-pulse laser 7 for emission pulse laser, for spraying the head module 8 of liquid at laser beam with workpiece 3 surface area contact during laser impact intensified, for detecting the measuring three-dimensional morphology module 9 of workpiece 3 surface profile, and controller.
Described robot 1 is six-shaft industrial robot or multiple degrees of freedom portal frame form robot.Clamping device in described clamping module 2 is the professional clamping device of scroll chuck, universal fixturing or custom-made.
Described nano composite material coating adds module 6 and uses laser direct deposition technology or plasma spray technology, and the nano composite material of spraying is the composite being made up of metal dust and 0D ~ 2D nano material.When using laser direct deposition technology, design a nozzle that can spray what nano composite material (such as Graphene, CNT, nitride hard nanoparticle) and workpiece 3 material (such as high temperature alloy etc.) premixing were formed micron powder, high-power short-pulse laser 7 scorification powder is used in nozzle, then by spraying high-pressure gas to workpiece 3 surface.When using plasma spray technology, produce high temperature in nozzle, the nano composite powder in nozzle is melted by the plasma gas of high pressure, then through spraying high-pressure gas to workpiece 3 surface.Comparing laser direct deposition technology, plasma spray technology is the spraying technology of the three-dimension curved surface type surface of the works such as a kind of maturation, low price, applicable blade.Described nano composite material coating adds module 6 and is provided with the multiple nozzles forming array, can improve spray efficiency.
The liquid of described head module 8 injection can be strong oxidizing solution (such as H2O2) or high energy density liquid (such as isopropanol), for improve laser impact intensified during the intensity of shock wave, raising working (machining) efficiency.
The subsystem for reclaiming, filter and repair the liquid that head module 8 sprays is comprised, for recycling these liquid ejected, to improve the utilization rate of liquid, to reduce cost on described body 5.
Described measuring three-dimensional morphology module 9 is three-dimensional laser scanner or binocular camera, for obtaining workpiece 3 surface profile data information in real time when workpiece 3 surface Hardening Treatment, for coating and the positional information of laser impact intensified process offer workpiece 3 of nano composite material coating.
Described shock strength detection module 4 is piezoelectric transducer, for the intensity of Laser Measurement induction shock wave, and for regulating and controlling high power laser output to adapt to the demand of the different parts shock wave intensity of different workpieces, workpiece.
Preferably, described high-power short-pulse laser 7 has two, and one of them is used for laser impact intensified process, can be nanosecond YAG, psec or femto-second laser；Another can be the combination of continuous-wave laser or continuous-wave laser and nanosecond laser for sintering or crystallization nano composite material coating.
As shown in Figure 2, the method that workpiece 3 surface is strengthened by the device of the aircraft engine parts surface peening of the present invention, including adding nano composite material coating, laser crystallization and laser pulse strengthening, detailed process is as follows:
One, nano composite material coating is added on workpiece 3 surface, comprises the following steps:
(1) workpiece 3 is installed in robot 1 by clamping workpiece module 2, uses measuring three-dimensional morphology module 9 to obtain the surface profile data of workpiece 3, the threedimensional model on controller obtains these data and reconstruction is gone to work part 3 surface, and carry out robot 1 machining path planning；
(2) robot 1 drives workpiece 3 to move in the jeting area that nano composite material coating adds module 6, uses laser direct deposition or plasma spray technology that the nano composite powder of thawing is ejected under the effect of gases at high pressure workpiece 3 surface；
(3) after completing the injection in one region, workpiece 3 surface, robot 1 drives workpiece 3 to continue to move to, and completes the injection of whole workpiece 3, it is thus achieved that one layer of uniform nano composite material coating；
(4) repeat above step, multi-layer nano composite coating can be obtained on workpiece 3 surface.
Two, carry out crystallization process, comprise the following steps:
(1) high-power short-pulse laser 7 is to the pulse laser of the workpiece 3 certain power of surface emitting, makes the crystal boundary in nano composite material merge, and robot 1 drives workpiece 3 to move, and the crystallization completing whole workpiece 3 processes；
(2) crystallization processes and adds nano composite material coating alternately, i.e. adds a layer nano composite material coating and just carries out primary crystallization process, and circulation comes and goes can add multi-layer nano composite crystallization coating on workpiece 3 surface.
Three, laser impact intensified process, comprises the following steps:
(1) measuring three-dimensional morphology module 9 is used to obtain the surface profile data of workpiece 3, the threedimensional model on controller obtains these data and reconstruction is gone to work part 3 surface, and carry out robot 1 machining path planning；
(2) robot 1 drives workpiece 3 to move to the initial position of laser impact intensified process, head module 8 sprays liquid to workpiece 3 surface, the most high-power short-pulse laser 7 is to liquid and workpiece 3 contact area emission pulse laser, high temperature, high pressure plasma is formed on workpiece 3 surface, and induce the shock wave of high intensity, workpiece 3 surface is carried out laser impact intensified process, and robot 1 drives workpiece 3 to move, and completes the intensive treatment of whole workpiece 3.
As shown in Figure 3, laser impact intensified mechanism is, pulsed laser irradiation produces high temperature, the plasma of high pressure on workpiece, then strong shock wave is induced, by this shock wave, surface of the work is carried out intensive treatment, shock wave makes matrix material fully act on nano-grain, improves the wearability of surface of the work, Properties of High Temperature Creep etc..Shower nozzle is ejected into the solution of surface of the work and forms limiting layer, and on the one hand the effect of limiting layer is to prevent from spreading in laser induced impact wave direction surrounding, improves the utilization rate of shock wave.On the other hand it is that, when the liquid of shower nozzle injection is the strong oxidizing solution such as H2O2, the heating of laser and the chemical etching effect of H2O2 can produce the plasma of more high pressure, and then produce the shock wave that intensity is higher；When liquid is the high energy density liquid such as isopropanol, laser can induce solution and produce explosivity reaction, produces more intensive shock wave, and this improves laser impact intensified working (machining) efficiency.
Carry out laser impact intensified during, measuring three-dimensional morphology module 9 obtains the outline data on workpiece 3 surface in real time, calculates the intensive treatment regional location of workpiece 3 after being transferred to controller in real time.Shock strength detection module 4 real-time Laser Measurement induction shock strength and be transferred to controller, then controller is by regulating the output of high-power short-pulse laser 7, to adapt to the demand of the zones of different shock wave intensity of different workpieces, surface of the work.
In these technical processs, for ensureing machining accuracy, use mode Compensating Robot 1 kinematic accuracy of feedback compensation, the impact of other Error on Machining Accuracies.Concrete implementation mode is, is obtained the outline data information on workpiece to be machined 3 surface before processing by measuring three-dimensional morphology module 9, and the threedimensional model on via controller acquisition workpiece 3 surface carries out the path planning of robot 1；In the course of processing, the outline data information of current workpiece 3 is obtained in real time by measuring three-dimensional morphology module 9, and via controller measuring and calculating workpiece to be machined 3 adds module 6, head module 8 or the relative position of high-power short-pulse laser 7 with nano composite material coating, by the contrast with ideal position, feed back in the motion of robot 1, it is ensured that coating and laser impact intensified machining accuracy.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all within the spirit and principles in the present invention, any modification, equivalent substitution and improvement etc. made, should be included in protection scope of the present invention.
Claims (10)
1. the device of an aircraft engine parts surface peening, it is characterised in that including:
Multi-freedom robot, is used for driving workpiece to move；
Clamping module, is used for installing workpiece, and it is connected with described robot；
Measuring three-dimensional morphology module, for detecting the profile of surface of the work；
Nano composite material coating adds module, for adding nano composite material coating at surface of the work；
High-power short-pulse laser, for surface of the work emission pulse laser；
Head module, for spraying liquid to laser beam with surface of the work contact area during laser impact intensified；
Shock strength detection module, for detecting the shock strength that pulse laser induces at surface of the work；
And controller, it is used for controlling to coordinate the work of whole device.
2. the device of aircraft engine parts surface peening as claimed in claim 1, it is characterised in that: the artificial six-shaft industrial robot of described machine or multiple degrees of freedom portal frame form robot.
3. the device of aircraft engine parts surface peening as claimed in claim 1, it is characterised in that: described nano composite material coating adds module and uses laser direct deposition or plasma spray technology.
4. the device of aircraft engine parts surface peening as claimed in claim 1, it is characterised in that: described nano composite material coating adds module and is provided with the multiple nozzles forming array.
5. the device of aircraft engine parts surface peening as claimed in claim 1, it is characterised in that: the liquid of described head module injection is H2O2 or isopropanol.
6. the device of aircraft engine parts surface peening as claimed in claim 1, it is characterised in that: farther include the body for installing fixing modules, described body comprises the subsystem for reclaiming, filter and repair the solution that head module sprays.
7. the device of aircraft engine parts surface peening as claimed in claim 1, it is characterised in that: described measuring three-dimensional morphology module is three-dimensional laser scanner or binocular camera.
8. the device of aircraft engine parts surface peening as claimed in claim 1, it is characterised in that: described shock strength detection module is piezoelectric transducer.
9. the device of aircraft engine parts surface peening as claimed in claim 1, it is characterised in that: described high-power short-pulse laser has two, and one of them is used for laser impact intensified process, can be nanosecond YAG, psec or femto-second laser；Another is used for crystallization nano composite material coating, can be the combination of continuous-wave laser or continuous-wave laser and nanosecond laser.
10. the method for an aircraft engine parts surface peening, it is characterised in that using the device of aircraft engine parts surface peening as claimed in any one of claims 1-9 wherein, the method comprises the following steps:
(1) nano composite material coating is added at surface of the work, it includes being installed in robot workpiece by clamping workpiece module, measuring three-dimensional morphology module is used to obtain the surface profile data of workpiece, the threedimensional model on controller obtains these data and reconstruction is gone to work part surface, and carry out processing of robots path planning, robot drives workpiece to move to nano composite material coating interpolation module, nano composite material coating add module and be coated with one or more layers uniform nano composite material coating to surface of the work；
(2) surface of the work carries out crystallization process, its implementation is that high-power short-pulse laser launches the pulse laser of certain power to surface of the work, making the crystal boundary in nano composite material merge, robot drives workpiece to move, and the crystallization completing whole workpiece processes；
(3) again surface of the work is carried out laser impact intensified, the process of implementing is: use measuring three-dimensional morphology module to obtain the surface profile data of workpiece, the threedimensional model on controller obtains these data and reconstruction is gone to work part surface, and carry out processing of robots path planning, robot drives workpiece to move to the initial position of laser impact intensified process, head module sprays liquid on workpiece, the most high-power short-pulse laser emission pulse laser on workpiece, robot drives workpiece to move, and completes the intensive treatment of whole workpiece.
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| CN201610354631.2A CN105862046B (en) | 2016-05-26 | 2016-05-26 | The device and method of aircraft engine parts surface peening |
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| CN201610354631.2A CN105862046B (en) | 2016-05-26 | 2016-05-26 | The device and method of aircraft engine parts surface peening |
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| CN105862046B CN105862046B (en) | 2018-08-24 |
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Cited By (11)
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| CN106312323A (en) * | 2016-11-02 | 2017-01-11 | 广东工业大学 | Laser peening straightening method and device for deformed blade |
| CN106636563A (en) * | 2016-11-04 | 2017-05-10 | 广东工业大学 | Multiple-unit control method and multiple-unit control device for reverse laser shot peening |
| CN108251831A (en) * | 2018-01-15 | 2018-07-06 | 湖南科美达电气股份有限公司 | A kind of oil film bearing block spraying reproducing method and system |
| CN108621059A (en) * | 2018-07-06 | 2018-10-09 | 温州大学激光与光电智能制造研究院 | Laser-impact experimental sample special fixture |
| CN110695856A (en) * | 2019-11-08 | 2020-01-17 | 北京航空航天大学 | Shot blasting method for thin-wall complex surface of aviation membrane disc |
| CN111051045A (en) * | 2017-09-05 | 2020-04-21 | Slm方案集团股份公司 | Apparatus and method for producing large workpieces by moving production units |
| CN111805247A (en) * | 2020-06-22 | 2020-10-23 | 无锡中车时代智能装备有限公司 | Automatic milling, grinding and polishing combined machining system and method for large workpiece |
| CN112692304A (en) * | 2020-12-14 | 2021-04-23 | 武汉大学 | Laser composite additive manufacturing method based on pulse laser control of molten pool flow |
| JP2021080512A (en) * | 2019-11-18 | 2021-05-27 | 株式会社サタケ | Thermal spraying apparatus |
| CN113733080A (en) * | 2021-08-10 | 2021-12-03 | 中国航发常州兰翔机械有限责任公司 | Helicopter tail nozzle laser shock peening track programming method and device |
| GB2610001A (en) * | 2021-08-16 | 2023-02-22 | Univ Qingdao Technology | Automated LSP process equipment system for aero-engine blade |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106312323A (en) * | 2016-11-02 | 2017-01-11 | 广东工业大学 | Laser peening straightening method and device for deformed blade |
| CN106636563A (en) * | 2016-11-04 | 2017-05-10 | 广东工业大学 | Multiple-unit control method and multiple-unit control device for reverse laser shot peening |
| CN111051045A (en) * | 2017-09-05 | 2020-04-21 | Slm方案集团股份公司 | Apparatus and method for producing large workpieces by moving production units |
| CN108251831A (en) * | 2018-01-15 | 2018-07-06 | 湖南科美达电气股份有限公司 | A kind of oil film bearing block spraying reproducing method and system |
| CN108621059A (en) * | 2018-07-06 | 2018-10-09 | 温州大学激光与光电智能制造研究院 | Laser-impact experimental sample special fixture |
| CN110695856A (en) * | 2019-11-08 | 2020-01-17 | 北京航空航天大学 | Shot blasting method for thin-wall complex surface of aviation membrane disc |
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| JP2021080512A (en) * | 2019-11-18 | 2021-05-27 | 株式会社サタケ | Thermal spraying apparatus |
| CN111805247A (en) * | 2020-06-22 | 2020-10-23 | 无锡中车时代智能装备有限公司 | Automatic milling, grinding and polishing combined machining system and method for large workpiece |
| CN111805247B (en) * | 2020-06-22 | 2021-03-09 | 无锡中车时代智能装备有限公司 | Automatic milling, grinding and polishing combined machining system and method for large workpiece |
| CN112692304A (en) * | 2020-12-14 | 2021-04-23 | 武汉大学 | Laser composite additive manufacturing method based on pulse laser control of molten pool flow |
| CN112692304B (en) * | 2020-12-14 | 2022-01-14 | 武汉大学 | Laser composite additive manufacturing method based on pulse laser control of molten pool flow |
| CN113733080B (en) * | 2021-08-10 | 2022-10-25 | 中国航发常州兰翔机械有限责任公司 | Helicopter tail nozzle laser shock peening track programming method and device |
| CN113733080A (en) * | 2021-08-10 | 2021-12-03 | 中国航发常州兰翔机械有限责任公司 | Helicopter tail nozzle laser shock peening track programming method and device |
| GB2610001A (en) * | 2021-08-16 | 2023-02-22 | Univ Qingdao Technology | Automated LSP process equipment system for aero-engine blade |
| GB2610001B (en) * | 2021-08-16 | 2023-12-13 | Univ Qingdao Technology | Automated LSP process equipment system for aero-engine blade |
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