CN114589406A - Laser shock strengthening system and method for preventing deformation of blisk of aircraft engine - Google Patents

Abstract

The invention discloses a laser shock strengthening system and method for preventing deformation of an aero-engine integral blisk. The system includes: a laser transmitter mechanism; a manipulator; The disc body is fixed on the end of the manipulator by the disc body clamp; the blade clamping clamp is fixed on the blade of the blisk, and the blade clamping clamp is clamped and fixed with the disc body; the blade clamping clamp corresponds to the laser shock strengthening area on the blade There is a laser shock strengthening opening for the laser emitted by the laser transmitter mechanism to pass through, and the laser shock strengthening area includes: the root of the leaf back, the root of the leaf basin, the leading edge of the leaf back, the leading edge of the leaf basin, the back edge of the leaf and the Back edge of leaf pot. In the laser shock strengthening process, the blade is clamped by the blade clamping fixture, so as to provide a certain support for the blade, reduce the force arm of the blade, and achieve the purpose of controlling the deformation, thereby ensuring the quality of the blade.

Description

Laser shock strengthening system and method for anti-deformation of aero-engine integral blisks

technical field

The invention relates to the technical field of aero-engine integral blisk blade strengthening treatment, and more particularly to a laser shock strengthening system and method for preventing deformation of an aero-engine integral blisk.

Background technique

Laser Shocking Peening (LSP for short) technology, also known as laser shot peening technology. When a laser with high power density (GW/cm order) and short pulse (10-30ns order) acts on the energy absorbing coating coated on the metal surface through the transparent confinement layer, the coating absorbs the laser energy and rapidly vaporizes And almost simultaneously formed a large number of dense high temperature (>10K), high pressure (>1GPa) plasma. The plasma continues to absorb laser energy and rapidly heat up and expand, and then explode to form a high-intensity shock wave that acts on the metal surface. When the peak pressure of the shock wave exceeds the dynamic yield strength of the material, the material undergoes plastic deformation and a compressive stress perpendicular to the material surface is generated in the surface layer. After the laser action ends, due to the reaction of the material around the impact area, the mechanical effect is manifested as a higher residual compressive stress on the surface of the material. The residual compressive stress will reduce the tensile stress level in the alternating load, so that the average stress level will decrease, thereby increasing the fatigue crack initiation life. At the same time, the existence of residual compressive stress can cause the closing effect of cracks, thereby effectively reducing the driving force of fatigue crack growth and prolonging the fatigue crack growth life.

The blisk is a new type of structure designed to meet high-performance aero-engines. It integrates the engine rotor blades and the wheel disk (disk body), eliminating the need for tenons, tenon grooves and locking devices in traditional connections. The weight of the structure and the number of parts can avoid the loss of air flow of the tenon, improve the starting efficiency, and greatly simplify the engine structure.

At present, when using the laser shock strengthening technology to strengthen the blisk, there is no certain support for the blade, so during the strengthening process, the blade is prone to deformation, thereby reducing the quality of the blisk.

Therefore, how to provide a laser shock-strengthening system and method for preventing deformation of an aero-engine integral blisk that has a funny deformation during laser shock-strengthening and ensures the quality of the blade-disk after shock-strengthening is an urgent problem for those skilled in the art to solve .

SUMMARY OF THE INVENTION

In view of this, the present invention provides a laser shock-strengthening system and method for preventing deformation of an aero-engine integral blisk, which has a funny deformation during laser shock-strengthening and ensures the quality of the blade-disk after shock-strengthening.

In order to achieve the above object, the present invention adopts the following technical solutions:

Laser shock strengthening system for anti-deformation of aero-engine integral blisks, including:

Laser transmitter mechanism;

manipulator;

The leaf disc clamp includes: a disc body clamp and a blade clamping clamp, the disc body of the leaf disc is fixed on the end of the manipulator through the disc body clamp; the blade clamping clamp is fixed on the blade on the blade of the disk, and the blade clamping fixture is clamped and fixed with the disk body; on the blade clamping fixture, a position corresponding to the laser shock strengthening area on the blade is provided for the laser transmitter The laser shock strengthening opening through which the laser emitted by the mechanism passes, and the laser shock strengthening area includes: the root of the leaf back, the root of the leaf basin, the leading edge of the leaf back, the leading edge of the leaf basin, the back edge of the leaf and the trailing edge of the leaf basin.

It can be seen from the above technical solutions that, compared with the prior art, the present invention provides a laser shock strengthening system for preventing deformation of an aero-engine integral blisk. During the laser shock strengthening process, the blade is clamped by a blade clamping fixture, In order to provide a certain support for the blade, reduce the force arm of the blade, achieve the purpose of controlling the deformation, and ensure the quality of the blade.

Further, machining allowances are provided on the leading edge of the blade back, the leading edge of the blade basin, the trailing edge of the blade and the trailing edge of the blade basin.

The beneficial effect of the above technical solution is that the leading edge of the blade back, the leading edge of the blade basin, the trailing edge of the blade and the trailing edge of the blade basin have a certain thickness, and the deformation of these positions can be reduced during laser shock strengthening.

Further, the laser shock reinforced opening includes: a first laser shock reinforced opening and a second laser shock reinforced opening, and the blade clamping fixture includes:

Blade back clamping plate, the blade back clamping plate is located on the blade back side of the blade, and two first disc body clamping grippers are fixed at an upper and lower interval on one side of the blade back clamping plate, and the two The first disc body clamping gripper is clamped on the upper and lower surfaces of the disc body, respectively, and the blade back clamping plate corresponds to the blade back root, the blade back front edge and the blade back edge. The positions are respectively provided with the first laser shock strengthening openings;

Leaf basin clamping plate, the leaf basin clamping plate is located on the blade basin side of the blade, and two second disc body clamping grippers are fixed at an upper and lower interval on one side of the leaf basin clamping plate. The second plate body clamping grippers are respectively clamped on the upper and lower surfaces of the plate body, and the leaf basin clamping plate corresponds to the leaf basin root, the leaf basin front edge and the leaf basin trailing edge The second laser shock reinforced openings are respectively opened at the positions of the blades, flexible gaskets are adhered to the inner sides of the blade back clamping plate and the blade basin clamping plate, and the blade is clamped and fixed on the blade back between the clamping plate and the flexible gasket on the inner side of the blade basin clamping plate, and the blade back clamping plate and the blade basin clamping plate are fixedly connected.

The beneficial effect of adopting the above technical solution is that the blade back clamping plate and the blade basin clamping plate are used to clamp the blade between the two and wrap them inside the flexible gasket, which not only provides effective support for the blade, but also provides flexible The gasket can prevent the clamping damage of the blade, and the flexible gasket can be configured according to the shape of the blade, which can better wrap the blade and greatly reduce the force arm of the blade.

Further, the blade back clamping plate and the blade basin clamping plate are fixedly connected by a plurality of locking screws.

The beneficial effect of adopting the above technical solution is that it is easy to disassemble and assemble the blade back clamping plate and the blade basin clamping plate.

Further, first baffles are respectively covered with positions on both sides of the first laser shock-strengthened opening on the blade back clamping plate, and first elongated holes are opened on the first baffles, so A plurality of first fixing screw holes are spaced apart at positions corresponding to the first elongated holes on the blade back clamping plate, and first locking screws pass through the first elongated holes and the corresponding first elongated holes. The fixing screw holes are screwed and fixed; the positions on the two sides of the second laser shock strengthening opening on the blade basin clamping plate are respectively covered with second baffles, and the second baffles are provided with second long strips A plurality of second fixing screw holes are spaced apart from the positions corresponding to the second elongated holes on the blade basin clamping plate, and the second locking screws pass through the second elongated holes and correspond to the corresponding second elongated holes. The second fixing screw hole is screwed and fixed.

The beneficial effect of adopting the above technical solution is that, by screwing the first locking screw and the second locking screw on the corresponding first fixing screw hole and the second fixing screw hole, the distance between the first baffle and the second baffle can be adjusted. position, to adjust the size of the first laser shock strengthening opening and the second laser shock strengthening opening respectively, so as to realize the laser shock strengthening of different optical paths and the impact strengthening of different blades, which greatly improves the applicability of the system to different blades.

Further, the first disk body clamping gripper and the second disk body clamping gripper have the same structure, wherein each of the first disk body clamping gripper includes:

a horizontal telescopic column, one end of the horizontal telescopic column is fixedly connected to one side of the blade back clamping plate;

The disk body gripper is fixedly connected with the other end of the horizontal telescopic column, and the two disk body grippers are respectively clamped on the upper and lower surfaces of the disk body.

The beneficial effect of the above technical solution is that the length of the horizontal telescopic column is adjusted according to the width of the disc body, and the blade back clamping plate and the leaf basin clamping plate are fixed on the disc body of the integral blisk by means of the disc body gripper. Therefore, the clamp can adapt to the clamping of discs with different widths.

Further, it also includes a nozzle arranged toward the blade with a spraying direction and used to cover the surface of the blade with a confinement layer of deionized water.

The beneficial effect of the above technical solution is that the deionized water confinement layer can not only constrain the expansion of the plasma to increase the peak pressure of the shock wave, but also prolong the action time of the shock wave and improve the laser shock strengthening effect.

The present invention also provides a laser shock strengthening method using the above-mentioned laser shock strengthening system, comprising the following steps:

Step 1: Fix the blisk on the end of the manipulator through the disk body clamp, and wipe the surface of the blade with alcohol to remove surface dirt and stick an absorption layer on the surface of the laser shock-strengthened area;

Step 2: Determine the laser process parameters of the laser transmitter mechanism according to the material and thickness of the overall blisk blade of the aero-engine;

Step 3: fixing the blade on the blade clamping fixture, and then fixing the blade clamping fixture on the disc body through the disc body clamp;

Step 4: Using the laser transmitter mechanism and the manipulator, sequentially align the root of the leaf back, the root of the leaf basin, the leading edge of the leaf back, the leading edge of the leaf basin, the back edge of the leaf, and the leaf The rear edge of the basin is strengthened by laser shock, and after the strengthening of one blade is completed, the strengthening of other blades is continued;

Step 5: Remove the absorbing layer of the strengthened laser shock-strengthened area, and wipe clean with absolute ethanol.

As can be seen from the above technical solutions, compared with the prior art, the present disclosure provides a laser shock strengthening method using the above-mentioned laser shock strengthening system. During the laser shock strengthening process, the blade is clamped by a blade clamping fixture, In order to provide a certain support for the blade, reduce the force arm of the blade, achieve the purpose of controlling the deformation, and ensure the quality of the blade.

further,

Before step 1, the method further includes: according to the material characteristic parameters of the overall blisk blade, reserving the machining surplus on the leading edge of the blade back, the leading edge of the leaf basin, the trailing edge of the blade and the trailing edge of the blade basin The value of the machining allowance is greater than the expected depth of the micro-pits generated by the blade after laser shock strengthening and greater than the depth corresponding to the preset residual compressive stress;

After step 5, the method further includes: after the laser shock strengthening of all the blades is completed, finishing the area with the machining allowance reserved to the precision required for the finished blade.

The beneficial effect of the above technical solution is that the leading edge of the blade back, the leading edge of the blade basin, the trailing edge of the blade and the trailing edge of the blade basin have a certain thickness, and the deformation of these positions can be reduced during laser shock strengthening.

further,

The laser process parameters of step 2 are as follows: the strengthening of the root of the leaf back and the root of the leaf basin adopts a circular light spot with a wavelength of 1064 nm, a pulse width of 10-25 ns, a laser energy of 22-27 J, and a φ1-φ2 mm. is 0-10%; the strengthening of the front edge of the leaf back, the front edge of the leaf basin, the back edge of the leaf and the rear edge of the leaf basin adopts a wavelength of 1064nm, a pulse width of 10-25ns, and a laser energy of 18 -22J, φ1～φ2mm circular light spot, the overlap rate is 0-10%;

The specific steps of step 3 are as follows: clamping and fixing the blade between the blade back clamping plate and the flexible gasket on the inner side of the blade basin clamping plate, and then fixing the blade by a plurality of the locking screws. The blade back clamping plate and the blade basin clamping plate are fixedly connected, and then the length of the horizontal telescopic column is adjusted according to the width of the disc body, and the blade back clamping plate is clamped by the disc body gripper. and the blade basin clamping plate is fixed on the disc body of the integral blisk, and then screwed to the corresponding first fixing screw hole and the first fixing screw hole through the first locking screw and the second locking screw respectively. two fixing screw holes to adjust the positions of the first baffle plate and the second baffle plate, so as to adjust the size of the first laser shock reinforced opening and the second laser shock reinforced opening respectively;

In the process of laser shock strengthening in step 4, deionized water is sprayed to the blade through the nozzle, so that the surface of the blade is covered with a deionized water confinement layer with a uniform thickness, and the resistivity of the deionized water is 18MΩ. cm, the thickness of the constraining layer is 1-2 mm.

The beneficial effect of adopting the above technical solution is that since the root is closer to the disk body, the force arm of the force arm is smaller than the force arm of the leading edge and the trailing edge during laser shock strengthening, so the energy is higher; the energy increases with the distance from the disk body. Therefore, the setting of the laser process parameters in step 2 can control the deformation of the blade. In step 4, the deionized water confinement layer can not only constrain the expansion of the plasma to increase the peak pressure of the shock wave, but also prolong the action time of the shock wave and improve the laser shock strengthening effect.

Description of drawings

In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only It is an embodiment of the present invention. For those of ordinary skill in the art, other drawings can also be obtained according to the provided drawings without creative work.

1 is a schematic structural diagram of a laser shock strengthening system for preventing deformation of an aero-engine integral blisk provided by the present invention.

FIG. 2 is a schematic diagram of the laser shock strengthening path of the blade back.

FIG. 3 is a schematic diagram of the laser shock strengthening path of the blade basin.

Figure 4 is a schematic diagram of the structure of the blade back clamping plate.

Figure 5 is a schematic diagram of the structure of the leaf basin clamping plate.

Figure 6 is a schematic diagram of blade clamping.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

Referring to FIGS. 1 to 6 , an embodiment of the present invention discloses a laser shock strengthening system for preventing deformation of an aero-engine integral blisk, including:

Laser transmitter mechanism 1, which mainly includes a laser transmitter (not shown), a 45° reflector (not shown), and a focusing mirror (not shown);

manipulator 2;

The leaf disc clamp 3 includes: a disc body clamp 31 and a blade clamping clamp 32, the disc body 4 of the leaf disc is fixed on the end of the manipulator 2 through the disc body clamp 31; the blade clamping clamp 32 is fixed on the blade disc On the blade 5, and the blade clamping fixture 32 is clamped and fixed with the disc body 4; the blade clamping fixture 32 is provided with a laser beam for the laser beam emitted by the laser transmitter mechanism 1 at the position corresponding to the laser shock strengthening area 51 on the blade 5. The laser shock-strengthened openings have been passed through, and the laser shock-strengthened area 51 includes: a blade dorsal root 511 , a blade basin root 512 , a blade blade leading edge 513 , a blade basin front edge 514 , a blade rear edge 515 , and a blade basin trailing edge 516 .

The blade back leading edge 513 , the blade basin leading edge 514 , the blade rear edge 515 and the blade basin trailing edge 516 are all provided with machining allowances.

The laser shock reinforced openings include: a first laser shock reinforced opening 3401 and a second laser shock reinforced opening 3402, and the blade clamping fixture 32 includes:

The blade back clamping plate 321, the blade back clamping plate 321 is located on the blade back side of the blade 5, and two first disc body clamping grippers 322 are fixed at an upper and lower interval on one side of the blade back clamping plate 321. The disc body clamping gripper 322 is respectively clamped on the upper and lower surfaces of the disc body 4, and the blade back clamping plate 321 is provided with a first laser at the positions corresponding to the blade back root 511, the blade back front edge 513 and the blade back edge 515 respectively. Impact strengthening opening 3401;

The blade basin clamping plate 323 is located on the blade basin side of the blade 5 , and two second disc body clamping grippers 324 are fixed at an upper and lower interval on one side of the blade basin clamping plate 323 . The plate body holding gripper 324 is respectively clamped on the upper and lower surfaces of the plate body 4, and the leaf basin clamping plate 323 is provided with a second position corresponding to the leaf basin root 512, the leaf basin front edge 514 and the leaf basin trailing edge 516, respectively. The laser shock reinforced opening 3402, the inner side of the blade back clamping plate 321 and the blade basin clamping plate 323 are adhered with a flexible gasket 325, and the blade 5 is clamped and fixed on the inner side of the blade back clamping plate 321 and the blade basin clamping plate 323 between the flexible gaskets 325 on the top, and the blade back clamping plate 321 and the blade basin clamping plate 323 are fixedly connected.

The blade back clamping plate 321 and the blade basin clamping plate 323 are fixedly connected by a plurality of locking screws 326 .

The positions on both sides of the first laser shock-strengthening opening 3401 on the blade back clamping plate 321 are respectively covered with first baffles 327 , and first elongated holes 3271 are formed on the first baffle 327 . The positions corresponding to the first elongated holes 3271 on the 321 are provided with a plurality of first fixing screw holes, and the first locking screws 328 pass through the first elongated holes 3271 and are screwed and fixed with the corresponding first fixing screw holes; The positions on both sides of the second laser shock-strengthening opening 3402 on the basin clamping plate 323 are respectively covered with a second baffle plate 329, and the second baffle plate 329 is provided with a second elongated hole 3291. The leaf basin clamping plate 323 A plurality of second fixing screw holes are spaced apart at positions corresponding to the second elongated holes 3291 , and the second locking screws 330 pass through the second elongated holes 3291 and are screwed and fixed to the corresponding second fixing screw holes.

The first disk body gripping gripper 322 and the second disk body gripping gripper 324 have the same structure, wherein each first disk body gripping gripper 322 includes:

A horizontal telescopic column 3221, one end of the horizontal telescopic column 3221 is fixedly connected to one side of the blade back clamping plate 321;

The disk body gripper 3222 is fixedly connected to the other end of the horizontal telescopic column 3221 , and the two disk body grippers 3222 are respectively clamped on the upper and lower surfaces of the disk body 4 .

Specifically, the horizontal telescopic column can adopt the structural form of the existing telescopic rod, and the pan body gripper can also adopt the structural form of the existing telescopic rod.

The laser shock strengthening system for preventing the deformation of the integral blisk of the aero-engine further includes a nozzle 6 arranged toward the blade 5 in the spray direction, and used to cover the surface of the blade 5 with a deionized water confinement layer.

The present invention adopts the laser shock strengthening method of the above-mentioned laser shock strengthening system, comprising the following steps:

Step 1: Fix the blisk on the end of the manipulator through the disc body fixture 31, and wipe the surface of the blade 5 with alcohol to remove the surface dirt and stick an absorption layer on the surface of the laser shock-strengthened area 51. The absorption layer can be made of aluminum foil, black Commonly used absorbing layer materials such as tape or black paint;

Step 2: Determine the laser process parameters of the laser transmitter mechanism 1 according to the material and thickness of the overall blisk blade of the aero-engine;

Step 3: Fix the blade 5 on the blade clamping fixture 32, and then fix the blade clamping fixture 32 on the disc body 4 through the disc body fixture 31;

Step 4: Use the laser transmitter mechanism 1 and the manipulator 2 to sequentially perform laser impact on the root 511 of the blade, the root of the blade basin 512, the leading edge of the blade blade 513, the blade basin front edge 514, the blade rear edge 515, and the blade basin trailing edge 516. Strengthening, after the strengthening of one blade is completed, the strengthening of other blades is continued;

Step 5: Remove the absorbing layer of the strengthened laser shock-strengthened area, and wipe clean with absolute ethanol.

Before step 1, the method further includes: according to the material characteristic parameters of the overall blisk blade, a machining allowance of 0.15-0.2 mm is reserved on the leading edge of the blade back 513 , the leading edge 514 of the blade basin, the trailing edge 515 of the blade and the trailing edge 516 of the blade basin , the value of the machining allowance is greater than the expected depth of the micro-pits generated by the blade after laser shock strengthening and greater than the depth corresponding to the preset residual compressive stress, and the depth corresponding to the preset residual stress is obtained through the empirical formula: Lp=ε*d+c Calculation, where Lp preset residual stress depth, ε and c are constants, d is the depth of micro-pits to calculate;

After step 5, it also includes: after the laser shock strengthening of all the blades is completed, finish machining the area reserved for machining allowance to the required precision of the finished blade.

The laser process parameters of step 2 are as follows: the strengthening of the leaf dorsal root 511 and the leaf basin root 512 adopts a circular light spot with a wavelength of 1064 nm, a pulse width of 10-25 ns, a laser energy of 22-27 J, φ1-φ2 mm, and the overlap ratio is 0. -10%; The strengthening of the leading edge of the leaf dorsal edge 513, the leading edge of the leaf basin 514, the posterior edge of the leaf blade 515 and the trailing edge of the leaf basin 516 adopts a wavelength of 1064nm, a pulse width of 10-25ns, a laser energy of 18-22J, φ1～φ2mm The circular light spot, the overlap rate is 0-10%;

The specific steps of step 3 are as follows: the blade 5 is clamped and fixed between the blade back clamping plate 321 and the flexible gasket 325 on the inner side of the blade basin clamping plate 323 , and then the blade back is clamped by a plurality of locking screws 326 The plate 321 and the leaf basin clamping plate 323 are fixedly connected, and then the length of the horizontal telescopic column 3221 is adjusted according to the width of the disc body 4, and the disc body gripper 3222 is used to fix the blade back clamping plate 321 and the leaf basin clamping plate 323 on the plate. On the disc body 4 of the integral blisk, the first locking screw 328 and the second locking screw 330 are respectively screwed to the corresponding first fixing screw hole and the second fixing screw hole to adjust the first baffle 327 and the second fixing screw hole. The positions of the two baffles 329 are adjusted to adjust the size of the first laser shock reinforced opening 3401 and the second laser shock reinforced opening 3402 respectively;

During the laser shock strengthening process in step 4, deionized water is sprayed to the blade 5 through the nozzle 6, so that the surface of the blade 5 is covered with a deionized water confinement layer with a uniform thickness. The thickness of the layers is 1-2 mm.

In the invention, the blade back clamping plate and the leaf basin clamping plate are used to clamp and fix the blade, and then the blade back clamping plate and the leaf basin are clamped by the first disc body clamping gripper and the second disc body clamping gripper. The clamping plates are respectively fixed on the disc body, so that during the laser shock strengthening process, the force arm of the blade can be reduced to reduce deformation; and for the front and rear edge areas of the blade, a certain machining allowance is reserved, and the After strengthening, the preset machining allowance is removed by finishing, so as to obtain an integral blisk with a certain thickness on the surface, uniform residual compressive stress and small deformation.

Therefore, the present invention can effectively control the macroscopic deformation of the aero-engine integral blisk blade during the laser shock strengthening process, and can make the surface of the blade after laser shock strengthening relatively flat, so as to ensure the quality of the strengthened blade.

The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments can be referred to each other. As for the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant part can be referred to the description of the method.

The above description of the disclosed embodiments enables any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (10)

1. Laser shock peening system of shape is preapred for an unfavorable turn of events to aeroengine blisk, its characterized in that includes:

a laser transmitter mechanism (1);

a manipulator (2);

a blisk clamp (3), the blisk clamp (3) comprising: the blade disc clamping device comprises a disc body clamp (31) and a blade clamping clamp (32), wherein a disc body (4) of the blade disc is fixed at the tail end of the manipulator (2) through the disc body clamp (31); the blade clamping fixture (32) is fixed on a blade (5) of the blade disc, and the blade clamping fixture (32) is fixedly clamped with the disc body (4); set up on blade centre gripping anchor clamps (32) corresponding on the position of laser shock peening region (51) on blade (5) and be used for supplying the laser that laser emitter mechanism (1) sent passes the laser shock peening opening, laser shock peening region (51) includes: a blade back root (511), a blade basin root (512), a blade back leading edge (513), a blade basin leading edge (514), a blade back trailing edge (515), and a blade basin trailing edge (516).

2. The laser shock peening system for preventing deformation of an aircraft engine blisk according to claim 1, wherein the leading blade back edge (513), the leading blade basin edge (514), the trailing blade back edge (515) and the trailing blade basin edge (516) are provided with machining allowances.

3. The laser shock peening system for preventing deformation of an aircraft engine blisk according to claim 2, wherein the laser shock peening openings include: a first laser shock peening opening (3401) and a second laser shock peening opening (3402), the blade clamp jig (32) comprising:

the blade back clamping plate (321) is positioned on the blade back side of the blade (5), two first disk body clamping grippers (322) are fixed on one side of the blade back clamping plate (321) at intervals from top to bottom, the two first disk body clamping grippers (322) are respectively clamped on the upper surface and the lower surface of the disk body (4), and the positions, corresponding to the blade back root (511), the blade back front edge (513) and the blade back rear edge (515), of the blade back clamping plate (321) are respectively provided with the first laser shock strengthening openings (3401);

a leaf basin holding plate (323), the leaf basin holding plate (323) being located on a leaf basin side of the blade (5), and two second tray body clamping grippers (324) are fixed on one side of the leaf tray clamping plate (323) at intervals from top to bottom, the two second tray body clamping grippers (324) are respectively clamped on the upper surface and the lower surface of the tray body (4), the positions of the blade basin clamping plate (323) corresponding to the blade basin root (512), the blade basin front edge (514) and the blade basin rear edge (516) are respectively provided with a second laser shock strengthening opening (3402), flexible gaskets (325) are adhered to the inner sides of the blade back clamping plate (321) and the blade basin clamping plate (323), the blade (5) is clamped and fixed between the blade back clamping plate (321) and the flexible gasket (325) on the inner side of the blade basin clamping plate (323), and the blade back clamping plate (321) is fixedly connected with the blade basin clamping plate (323).

4. The laser shock peening system for preventing deformation of an aircraft engine blisk according to claim 3, wherein the blade back clamping plate (321) and the blade basin clamping plate (323) are fixedly connected by a plurality of locking screws (326).

5. The laser shock peening system for preventing deformation of the blisk of an aircraft engine as claimed in claim 3, wherein the positions, located on both sides of the first laser shock peening opening (3401), of the blade back clamping plate (321) are respectively covered with a first baffle plate (327), the first baffle plate (327) is provided with a first strip-shaped hole (3271), the blade back clamping plate (321) is provided with a plurality of first fixing screw holes at intervals corresponding to the positions of the first strip-shaped hole (3271), and a first locking screw (328) penetrates through the first strip-shaped hole (3271) to be fixed with the corresponding first fixing screw hole in a threaded manner; lie in on leaf basin grip block (323) the position of second laser shock strengthening opening (3402) both sides has been covered with second baffle (329) respectively, second rectangular shape hole (3291) has been seted up on second baffle (329), correspond on leaf basin grip block (323) a plurality of second fixed screw holes have been seted up to the position interval of second rectangular shape hole (3291), and second locking screw (330) passes second rectangular shape hole (3291) and corresponding the second fixed screw hole spiro union is fixed.

6. The laser shock peening system for preventing deformation of an aircraft engine blisk according to claim 3, wherein the first and second disk clamping grips (322, 324) are identical in structure, wherein each of the first disk clamping grips (322) includes:

one end of the transverse telescopic column (3221) is fixedly connected with one side of the blade back clamping plate (321);

the tray body grabs (3222), tray body grabs (3222) with horizontal flexible post (3221) other end fixed connection, two tray body grabs (3222) centre gripping respectively on the upper and lower surface of tray body (4).

7. The laser shock peening system for preventing deformation of an aircraft engine blisk according to any one of claims 1 to 6, further comprising a nozzle (6) for covering the surface of the blade (5) with a deionized water constraining layer, the nozzle being arranged with the spraying direction toward the blade (5).

8. A laser shock peening method using the laser shock peening system of any one of claims 1 to 7, comprising the steps of:

step 1: fixing the blisk on the tail end of a mechanical arm through the disk body clamp (31), wiping the surface of the blade (5) with alcohol to remove surface dirt, and attaching an absorption layer on the surface of the laser shock strengthening area (51);

step 2: determining laser process parameters of the laser emitter mechanism (1) according to the material and the thickness of the blades of the blisk of the aircraft engine;

and step 3: fixing the blade (5) on the blade clamping fixture (32), and then fixing the blade clamping fixture (32) on the disc body (4) through a disc body fixture (31);

and 4, step 4: sequentially carrying out laser shock strengthening on the blade back root (511), the blade basin root (512), the blade back front edge (513), the blade basin front edge (514), the blade back rear edge (515) and the blade basin rear edge (516) by using the laser transmitter mechanism (1) and the manipulator (2), and continuing to strengthen other blades after the strengthening of one blade is finished;

and 5: and removing the absorption layer of the strengthened laser shock strengthening area, and wiping the absorption layer with absolute ethyl alcohol.

9. The laser shock peening method according to claim 8,

before step 1, the method further comprises the following steps: reserving machining allowance in the blade back front edge (513), the blade basin front edge (514), the blade back rear edge (515) and the blade basin rear edge (516) according to material characteristic parameters of the blisk blade, wherein the numerical value of the machining allowance is larger than the estimated depth of a micro-pit generated after laser shock peening of the blade and the depth corresponding to the preset residual compressive stress;

after the step 5, the method further comprises the following steps: and after the laser shock strengthening of all the blades is finished, performing finish machining on the area reserved with the machining allowance to the precision required by the finished blade.

10. The laser shock peening method according to any one of claims 8 or 9,

the laser process parameters of the step 2 are as follows: the strengthening of the leaf back root (511) and the leaf basin root (512) adopts round light spots with the wavelength of 1064nm, the pulse width of 10-25ns, the laser energy of 22-27J and the phi of 1-phi 2mm, and the lap joint rate is 0-10 percent; the blade back front edge (513), the blade basin front edge (514), the blade back rear edge (515) and the blade basin rear edge (516) are strengthened by circular light spots with the wavelength of 1064nm, the pulse width of 10-25ns, the laser energy of 18-22J and the diameter of phi 1-phi 2mm, and the lap joint rate is 0-10%;

the specific steps of step 3 are as follows: will blade (5) centre gripping is fixed between back of the leaf grip block (321) and flexible gasket (325) on leaf basin grip block (323) inboard, then through a plurality of locking screw (326) will back of the leaf grip block (321) with leaf basin grip block (323) fixed connection, then according to the width regulation of disk body (4) the length of horizontal flexible post (3221) to utilize disk body tongs (3222) will back of the leaf grip block (321) with leaf basin grip block (323) are fixed on disk body (4) of whole leaf dish, then pass through respectively first locking screw (328) with second locking screw (330) spiro union is in corresponding on first fixed screw hole with the second fixed screw hole, with the adjustment the position of first baffle (327) and second baffle (329), carry out the size to first laser shock strengthening opening (3401) and second laser shock strengthening opening (3402) respectively Adjusting;

and 4, in the laser shock peening process of the step 4, spraying deionized water to the blade (5) through the nozzle (6) so as to cover a deionized water restraint layer with uniform thickness on the surface of the blade (5), wherein the resistivity of the deionized water is 18M omega cm, and the thickness of the restraint layer is 1-2 mm.

Images