CN114589406A - Laser shock strengthening system and method for preventing deformation of blisk of aircraft engine - Google Patents
Laser shock strengthening system and method for preventing deformation of blisk of aircraft engine Download PDFInfo
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- CN114589406A CN114589406A CN202210209082.5A CN202210209082A CN114589406A CN 114589406 A CN114589406 A CN 114589406A CN 202210209082 A CN202210209082 A CN 202210209082A CN 114589406 A CN114589406 A CN 114589406A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/352—Working by laser beam, e.g. welding, cutting or boring for surface treatment
- B23K26/356—Working by laser beam, e.g. welding, cutting or boring for surface treatment by shock processing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/70—Auxiliary operations or equipment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/70—Auxiliary operations or equipment
- B23K26/702—Auxiliary equipment
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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
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/06—Surface hardening
- C21D1/09—Surface hardening by direct application of electrical or wave energy; by particle radiation
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention discloses an anti-deformation laser shock strengthening system and method for an aero-engine blisk, wherein the system comprises: a laser emitter mechanism; a manipulator; blisk anchor clamps, blisk anchor clamps include: the blade disc comprises a disc body clamp and a blade clamping clamp, wherein a disc body of the blade disc is fixed at the tail end of a mechanical arm through the disc body clamp; the blade clamping fixture is fixed on the blade of the blade disc, and the blade clamping fixture is clamped and fixed with the disc body; offer the laser shock that is used for supplying laser transmitter mechanism to send and pass on the blade centre gripping anchor clamps and strengthen regional position of laser shock on corresponding the blade and strengthen the opening, laser shock strengthens regional including: a blade back root, a blade basin root, a blade back leading edge, a blade basin leading edge, a blade back trailing edge, and a blade basin trailing edge. In the laser shock peening process, the blade is clamped through the blade clamping fixture, so that a certain support is provided for the blade, the force arm of the blade is reduced, the purpose of controlling deformation is achieved, and the quality of the blade is guaranteed.
Description
Technical Field
The invention relates to the technical field of strengthening treatment of blades of an aero-engine blisk, in particular to an anti-deformation laser shock strengthening system and method for the aero-engine blisk.
Background
Laser Shock Peening (LSP) technology is also called Laser Peening technology. When high-power-density (GW/cm magnitude) short-pulse (10-30 ns magnitude) laser acts on an energy absorption coating coated on the metal surface through a transparent constraint layer, the coating absorbs laser energy and is rapidly gasified, and a large amount of dense high-temperature (>10K) and high-pressure (>1GPa) plasmas are almost formed at the same time. The plasma continues to absorb laser energy and rapidly rises in temperature to expand, and then the plasma explodes to form high-strength shock waves to act on the surface of the metal. When the peak pressure of the shock wave exceeds the dynamic yield strength of the material, the material plastically deforms and creates a compressive stress perpendicular to the surface of the material at the surface layer. After the laser action is finished, the mechanical effect of the laser is shown as that the surface of the material obtains higher residual compressive stress due to the reaction of the material around the impact area. The residual compressive stress reduces the tensile stress level in the alternating load, reducing the average stress level, and thereby increasing the fatigue crack initiation life. Meanwhile, the existence of the residual compressive stress can cause the closing effect of the crack, thereby effectively reducing the driving force of the fatigue crack expansion and prolonging the fatigue crack expansion life.
The blisk is a novel structural member designed for meeting the requirement of a high-performance aeroengine, and integrates engine rotor blades and a wheel disc (a disc body), so that tenons, mortises, locking devices and the like in the traditional connection are omitted, the structural weight and the number of parts are reduced, the tenon airflow loss is avoided, the starting efficiency is improved, and the engine structure is greatly simplified.
At present, when the laser shock peening technology is used for strengthening the blisk, certain support is not provided for the blades, so that the blades are easy to deform in the strengthening process, and the quality of the blisk is reduced.
Therefore, the problem to be solved by the technical personnel in the field is how to provide a laser shock peening system and a laser shock peening method for preventing deformation of an aircraft engine blisk, wherein the deformation of the disk is ensured after shock peening.
Disclosure of Invention
In view of the above, the invention provides a laser shock peening system and method for preventing deformation of an aircraft engine blisk, which can prevent deformation during smile laser shock peening and ensure quality of the blisk after shock peening.
In order to achieve the purpose, the invention adopts the following technical scheme:
laser shock peening system of shape is preapred for an unfavorable turn of events to aeroengine blisk includes:
a laser emitter mechanism;
a manipulator;
a blisk clamp, the blisk clamp comprising: the blade disc comprises a disc body clamp and a blade clamping clamp, wherein a disc body of the blade disc is fixed at the tail end of the manipulator through the disc body clamp; the blade clamping fixture is fixed on the blade of the blade disc, and the blade clamping fixture is clamped and fixed with the disc body; the blade centre gripping anchor clamps are gone up and are corresponded laser shock peening regional position on the blade is seted up and be used for supplying the laser that laser emitter mechanism sent passes laser shock peening opening, laser shock peening region includes: a blade back root, a blade basin root, a blade back leading edge, a blade basin leading edge, a blade back trailing edge, and a blade basin trailing edge.
According to the technical scheme, compared with the prior art, the laser shock strengthening system for preventing the deformation of the integral blade disc of the aircraft engine is disclosed, in the laser shock strengthening process, the blade is clamped through the blade clamping fixture, so that certain support is provided for the blade, the force arm of the blade is reduced, the purpose of controlling the deformation is achieved, and the quality of the blade is guaranteed.
Further, machining allowances are arranged on the blade back front edge, the blade basin front edge, the blade back rear edge and the blade basin rear edge.
The beneficial effect that adopts above-mentioned technical scheme to produce is for leaf back leading edge, leaf basin leading edge, leaf back trailing edge and leaf basin trailing edge have certain thickness, when laser shock peening, can make these positions warp for a short time.
Further, the laser shock peening opening includes: first laser shock peening opening and second laser shock peening opening, blade centre gripping anchor clamps include:
the blade back clamping plate is positioned on the blade back side of the blade, two first disk body clamping grippers are fixed on one side of the blade back clamping plate at intervals from top to bottom, the two first disk body clamping grippers are respectively clamped on the upper surface and the lower surface of the disk body, and first laser shock strengthening openings are respectively formed in the positions, corresponding to the root of the blade back, the front edge of the blade back and the rear edge of the blade back, of the blade back clamping plate;
leaf basin grip block, leaf basin grip block is located the leaf basin side of blade, just leaf basin grip block one side is fixed with two second disk body centre gripping tongs at the interval from top to bottom, two second disk body centre gripping tongs centre gripping is in respectively on the upper and lower surface of disk body, correspond on the leaf basin grip block leaf basin root leaf basin leading edge with the position at leaf basin trailing edge has been seted up respectively the opening is reinforceed to second laser shock, the leaf back grip block with the inboard of leaf basin grip block all is stained with flexible gasket, the blade centre gripping is fixed the leaf back grip block with on the leaf basin grip block inboard between the flexible gasket, just the leaf back grip block with leaf basin grip block fixed connection.
The beneficial effect who adopts above-mentioned technical scheme to produce is, adopts leaf back grip block and leaf basin grip block with the blade centre gripping between the two to the parcel is inside flexible gasket, not only provides effective support for the blade, and flexible gasket can prevent the centre gripping of blade from damaging moreover, and flexible gasket can be according to the blade shape structure, parcel blade that can be better, has reduced the arm of force of blade greatly.
Furthermore, the blade back clamping plate and the blade basin clamping plate are fixedly connected through a plurality of locking screws.
The beneficial effect who adopts above-mentioned technical scheme to produce is, the dismouting of easy leaf back grip block and leaf basin grip block.
Furthermore, the positions, located on two sides of the first laser shock peening opening, on the blade back clamping plate are respectively covered with a first baffle plate, a first elongated hole is formed in the first baffle plate, a plurality of first fixing screw holes are formed in the blade back clamping plate at intervals corresponding to the positions of the first elongated hole, and a first locking screw penetrates through the first elongated hole and is fixed with the corresponding first fixing screw hole in a threaded connection manner; the leaf basin grip block is last to be located the position of second laser shock strengthening opening both sides has been covered the second baffle respectively, the second rectangular shape hole has been seted up on the second baffle, correspond on the leaf basin grip block the position interval in second rectangular shape hole has seted up a plurality of second fixed screw holes, and second locking screw passes second rectangular shape hole and corresponding the second fixed screw hole spiro union is fixed.
The beneficial effects that adopt above-mentioned technical scheme to produce are that, through first locking screw and second locking screw spiro union on corresponding first fixed screw hole and second fixed screw hole, can adjust the position of first baffle and second baffle to adjust first laser shock strengthening opening and second laser shock strengthening open-ended size respectively, thereby realize the laser shock strengthening and different blade shock strengthening of different light paths, improved the suitability of this system to different blades greatly.
Further, first disk body centre gripping tongs with second disk body centre gripping tongs structure is the same, wherein, every first disk body centre gripping tongs all includes:
one end of the transverse telescopic column is fixedly connected with one side of the blade back clamping plate;
the tray body tongs, tray body tongs with horizontal flexible post other end fixed connection, two tray body tongs centre gripping is in respectively on the upper and lower surface of tray body.
The beneficial effect who adopts above-mentioned technical scheme to produce is, the length of the horizontal flexible post of width regulation according to the disk body to utilize the disk body tongs to fix leaf back grip block and leaf basin grip block on the disk body of blisk. Therefore, the clamp can adapt to clamping of disks with different widths.
Further, the device also comprises a nozzle which is arranged towards the blade in the spraying direction and is used for covering the surface of the blade with the deionized water constraint layer.
The beneficial effect that adopts above-mentioned technical scheme to produce is that, thereby the deionized water confined layer can not only restrain the inflation of plasma and improve the peak pressure of shock wave, can also prolong its operating time through the reflection to shock wave, improves laser shock peening effect.
The invention also provides a laser shock peening method adopting the laser shock peening system, which comprises the following steps:
step 1: fixing the blisk on the tail end of a manipulator through the disk body clamp, wiping the surface of the blade with alcohol to remove surface dirt, and attaching an absorption layer on the surface of the laser shock strengthening area;
step 2: determining laser process parameters of the laser emitter mechanism according to the material and the thickness of the blades of the blisk of the aircraft engine;
and step 3: fixing the blade on the blade clamping fixture, and then fixing the blade clamping fixture on the disk body through the disk body fixture;
and 4, step 4: carrying out laser shock strengthening on the blade back root, the blade basin root, the blade back front edge, the blade basin front edge, the blade back rear edge and the blade basin rear edge in sequence by using the laser emitter mechanism and the manipulator, and continuing strengthening 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 clean by absolute ethyl alcohol.
According to the technical scheme, compared with the prior art, the laser shock strengthening method adopting the laser shock strengthening system is disclosed and provided, in the laser shock strengthening process, the blade is clamped through the blade clamping fixture, so that certain support is provided for the blade, the force arm of the blade is reduced, the purpose of controlling deformation is achieved, and the quality of the blade is guaranteed.
Further, in the above-mentioned case,
before step 1, the method further comprises the following steps: reserving the machining allowance at the front edge of the blade back, the front edge of the blade basin, the rear edge of the blade back and the rear edge of the blade basin according to the material characteristic parameters of the blisk blade, wherein the numerical value of the machining allowance is larger than the expected depth of a micro-pit generated after laser shock strengthening 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.
The beneficial effect that adopts above-mentioned technical scheme to produce is for leaf back leading edge, leaf basin leading edge, leaf back trailing edge and leaf basin trailing edge have certain thickness, when laser shock peening, can make these positions warp for a short time.
Further, in the above-mentioned case,
the laser process parameters of the step 2 are as follows: the strengthening of the leaf back root and the leaf basin root 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, the blade basin front edge, the blade back rear edge and the blade basin rear edge are reinforced by round light spots with the wavelength of 1064nm, the pulse width of 10-25ns, the laser energy of 18-22J and the diameter of 1-2mm, and the lap joint rate is 0-10%;
the specific steps of step 3 are as follows: clamping and fixing the blade between flexible gaskets on the inner sides of the blade back clamping plate and the blade basin clamping plate, fixedly connecting the blade back clamping plate and the blade basin clamping plate through a plurality of locking screws, adjusting the length of the transverse telescopic column according to the width of the disk body, fixing the blade back clamping plate and the blade basin clamping plate on the disk body of the integral blade disk by using a disk body gripper, and then respectively screwing the blade back clamping plate and the blade basin clamping plate on the corresponding first fixing screw hole and the second fixing screw hole through the first locking screw and the second locking screw so as to adjust the positions of the first baffle and the second baffle and respectively adjust the sizes of the first laser shock strengthening opening and the second laser shock strengthening opening;
and 4, spraying deionized water to the blade through the nozzle in the laser shock peening process in the step 4, so that a deionized water restraint layer with uniform thickness is covered on the surface of the blade, the resistivity of the deionized water is 18 MOmega-cm, and the thickness of the restraint layer is 1-2 mm.
The technical scheme has the beneficial effects that the root part is closer to the disc body, so that the moment arm is small relative to the moment arms of the front edge and the rear edge during laser shock strengthening, and the energy is higher; the energy decreases with increasing distance from the disk and therefore the setting of the laser process parameters of step 2 can control the deformation of the blade. In the step 4, the deionized water restraint layer can restrain the expansion of the plasma so as to improve the peak pressure of the shock wave, and can prolong the action time of the shock wave through the reflection of the shock wave so as to improve the laser shock strengthening effect.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a laser shock strengthening system for preventing deformation of an aircraft engine blisk.
FIG. 2 is a schematic diagram of a laser shock peening path of a blade back.
FIG. 3 is a schematic diagram of a laser shock peening path of a leaf pot.
FIG. 4 is a schematic structural view of a blade back clamping plate.
FIG. 5 is a schematic structural view of a leaf basin holding plate.
FIG. 6 is a schematic view of blade clamping.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6, the embodiment of the invention discloses a laser shock strengthening system for preventing deformation of an aircraft engine blisk, comprising:
a laser transmitter mechanism 1 mainly including a laser transmitter (not shown), a 45 ° mirror (not shown), and a focusing mirror (not shown);
a manipulator 2;
The blade back leading edge 513, the blade basin leading edge 514, the blade back trailing edge 515 and the blade basin trailing edge 516 are provided with machining allowances.
The laser shock peening opening includes: first laser shock peening opening 3401 and second laser shock peening opening 3402, blade clamp jig 32 includes:
the blade back clamping plate 321 is positioned on the blade back side of the blade 5, two first disk body clamping hand grips 322 are fixed on one side of the blade back clamping plate 321 at intervals up and down, the two first disk body clamping hand grips 322 are respectively clamped on the upper surface and the lower surface of the disk body 4, and first laser shock strengthening openings 3401 are respectively formed in 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;
the leaf basin clamping plate 323 is located on the leaf basin side of the blade 5, two second disk body clamping grippers 324 are fixed on one side of the leaf basin clamping plate 323 at intervals from top to bottom, the two second disk body clamping grippers 324 are respectively clamped on the upper surface and the lower surface of the disk body 4, second laser shock strengthening openings 3402 are respectively formed in positions, corresponding to the leaf basin root 512, the leaf basin front edge 514 and the leaf basin rear edge 516, of the leaf basin clamping plate 323, flexible gaskets 325 are respectively adhered to the inner sides of the leaf back clamping plate 321 and the leaf basin clamping plate 323, the blade 5 is clamped and fixed between the flexible gaskets 325 on the inner sides of the leaf back clamping plate 321 and the leaf basin clamping plate 323, and the leaf back clamping plate 321 and the leaf basin clamping plate 323 are fixedly connected.
The blade back holding plate 321 and the blade basin holding plate 323 are fixedly connected by a plurality of locking screws 326.
The positions, located on two sides of the first laser shock peening opening 3401, of the blade back clamping plate 321 are respectively covered with a first baffle 327, a first elongated hole 3271 is formed in the first baffle 327, a plurality of first fixing screw holes are formed in the position, corresponding to the first elongated hole 3271, of the blade back clamping plate 321 at intervals, and a first locking screw 328 penetrates through the first elongated hole 3271 to be fixed with the corresponding first fixing screw hole in a threaded manner; the positions, located on the two sides of the second laser shock peening opening 3402, of the leaf basin clamping plate 323 are respectively covered with a second baffle 329, a second elongated hole 3291 is formed in the second baffle 329, a plurality of second fixing screw holes are formed in the position, corresponding to the second elongated hole 3291, of the leaf basin clamping plate 323 at intervals, and a second locking screw 330 penetrates through the second elongated hole 3291 and is fixed with the corresponding second fixing screw hole in a threaded manner.
First dish body centre gripping tongs 322 and second dish body centre gripping tongs 324 structure is the same, and wherein, every first dish body centre gripping tongs 322 all includes:
one end of the transverse telescopic column 3221 is fixedly connected with one side of the blade back clamping plate 321;
the disc body grippers 3222 are fixedly connected with the other end of the transverse telescopic column 3221, and the two disc body grippers 3222 are respectively clamped on the upper surface and the lower surface of the disc body 4.
Specifically, the transverse telescopic column can adopt the structural form of the existing telescopic rod, and the disc body gripper can also adopt the structural form of the existing telescopic rod.
The laser shock strengthening system for preventing the deformation of the blisk of the aircraft engine further comprises a nozzle 6 which is arranged towards the blade 5 in the spraying direction and is used for covering the surface of the blade 5 with a deionized water restraint layer.
The laser shock peening method adopting the laser shock peening system comprises the following steps:
step 1: fixing the blisk on the tail end of a manipulator through a 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, wherein the absorption layer can be made of common absorption layer materials such as aluminum foil, black adhesive tape or black paint;
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 a blade holding jig 32, and then fixing the blade holding jig 32 on the disc 4 through the disc jig 31;
and 4, step 4: the laser emitter mechanism 1 and the manipulator 2 are utilized to sequentially carry 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, and strengthening of other blades is continued 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 clean by absolute ethyl alcohol.
Before step 1, the method further comprises the following steps: according to the material characteristic parameters of the blisk blade, machining allowance of 0.15-0.2mm is reserved on the front edge 513 of the blade back, the front edge 514 of the blade basin, the rear edge 515 of the blade back and the rear edge 516 of the blade basin, the numerical value of the machining allowance is larger than the predicted depth of a micro-pit generated after laser shock strengthening of the blade and the depth corresponding to the preset residual compressive stress, and the depth corresponding to the preset residual stress is determined through an empirical formula: calculating Lp as epsilon + d + c, wherein Lp presets the depth of the residual stress, epsilon and c are constants, and d is the depth of the micro-pits;
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.
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 strengthening of the blade back leading edge 513, the blade basin leading edge 514, the blade back trailing edge 515 and the blade basin trailing edge 516 adopts a round light spot with the wavelength of 1064nm, the pulse width of 10-25ns, the laser energy of 18-22J and the diameter of 1-2mm, and the lap joint rate is 0-10%;
the specific steps of step 3 are as follows: the method comprises the following steps of clamping and fixing a blade 5 between flexible gaskets 325 on the inner sides of a blade back clamping plate 321 and a blade basin clamping plate 323, fixedly connecting the blade back clamping plate 321 and the blade basin clamping plate 323 through a plurality of locking screws 326, adjusting the length of a transverse telescopic column 3221 according to the width of a disk body 4, fixing the blade back clamping plate 321 and the blade basin clamping plate 323 on the disk body 4 of the integral blade disk by using a disk body gripper 3222, and then screwing the blade back clamping plate 321 and the blade basin clamping plate 323 on a corresponding first fixing screw hole and a corresponding second fixing screw hole through a first locking screw 328 and a second locking screw 330 respectively to adjust the positions of a first baffle 327 and a second baffle 329 so as to adjust the sizes of a first laser shock strengthening opening 3401 and a second laser shock strengthening opening 3402 respectively;
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 enable the surface of the blade 5 to be covered with a deionized water restraint layer with uniform thickness, wherein the resistivity of the deionized water is 18 MOmega-cm, and the thickness of the restraint layer is 1-2 mm.
According to the invention, the blade is clamped and fixed by the blade back clamping plate and the blade basin clamping plate, and then the blade back clamping plate and the blade basin clamping plate are respectively fixed on the disk body by the first disk body clamping gripper and the second disk body clamping gripper, so that the force arm of the blade during laser shock strengthening can be reduced, and the deformation is reduced; and for the front edge region and the rear edge region of the blade, a certain machining allowance is reserved, and the preset machining allowance is removed through finish machining after laser shock strengthening, so that the blisk with a certain thickness on the surface, uniform residual compressive stress and small deformation is obtained.
Therefore, the method can effectively control the macroscopic deformation of the blade of the blisk of the aircraft engine in the laser shock strengthening process, and can enable the surface of the blade after laser shock strengthening to be relatively flat, thereby ensuring the quality of the strengthened blade.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
The previous description of the disclosed embodiments is provided to enable 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 applied to 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.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5742028A (en) * | 1996-07-24 | 1998-04-21 | General Electric Company | Preloaded laser shock peening |
| CN103882188A (en) * | 2012-12-24 | 2014-06-25 | 中国科学院沈阳自动化研究所 | Laser shock strengthening device of blisk |
| CN103898297A (en) * | 2012-12-24 | 2014-07-02 | 中国科学院沈阳自动化研究所 | Laser shock peening method of blisk |
| CN112048614A (en) * | 2020-09-10 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Hollow blade life-prolonging shape-controlling method based on laser shock peening |
| CN113088678A (en) * | 2021-04-08 | 2021-07-09 | 中国航发北京航空材料研究院 | Laser shock peening method for blades of small-size blisk |
-
2022
- 2022-03-04 CN CN202210209082.5A patent/CN114589406B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5742028A (en) * | 1996-07-24 | 1998-04-21 | General Electric Company | Preloaded laser shock peening |
| CN103882188A (en) * | 2012-12-24 | 2014-06-25 | 中国科学院沈阳自动化研究所 | Laser shock strengthening device of blisk |
| CN103898297A (en) * | 2012-12-24 | 2014-07-02 | 中国科学院沈阳自动化研究所 | Laser shock peening method of blisk |
| CN112048614A (en) * | 2020-09-10 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Hollow blade life-prolonging shape-controlling method based on laser shock peening |
| CN113088678A (en) * | 2021-04-08 | 2021-07-09 | 中国航发北京航空材料研究院 | Laser shock peening method for blades of small-size blisk |
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| CN114589406B (en) | 2022-11-25 |
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