CN110586695A - Laser shock peening and shape correction method and device for engine bifurcated tail nozzle welding seam - Google Patents
Laser shock peening and shape correction method and device for engine bifurcated tail nozzle welding seam Download PDFInfo
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- CN110586695A CN110586695A CN201910703922.1A CN201910703922A CN110586695A CN 110586695 A CN110586695 A CN 110586695A CN 201910703922 A CN201910703922 A CN 201910703922A CN 110586695 A CN110586695 A CN 110586695A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D3/00—Straightening or restoring form of metal rods, metal tubes, metal profiles, or specific articles made therefrom, whether or not in combination with sheet metal parts
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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 discloses a method and a device for laser shock strengthening and shape correction of a welding line of a forked tail nozzle of an engine, the method comprises the steps of firstly carrying out failure analysis on the tail nozzle to determine a welding line area needing laser shock strengthening, then carrying out shock strengthening on the welding line area needing strengthening by a laser shock strengthening unit according to shock strengthening processing parameters of a thin-wall plate, then measuring a dynamic strain field of a material in the laser shock strengthening area on line by an optical measuring instrument, calculating strain field data to obtain a dynamic constitutive equation and dynamic strain rate data of the material, aligning a tail nozzle measuring model with a CAD model by a three-dimensional profile scanner, respectively calculating a bending error and a torsion error of the strengthening area of the tail nozzle, then transmitting all measured data to a complete machine control system, adjusting laser parameters of the shock strengthening and determining laser parameters and shape correction paths needing shape correction, and then the laser impact strengthening unit realizes the shape correction of torsion and bending in the strengthening process of the tail nozzle.
Description
Technical Field
The invention relates to the technical field of processing of an aircraft engine tail nozzle, in particular to a laser shock strengthening and shape correcting method and device for a bifurcated tail nozzle welding seam of an engine.
Background
The tail nozzle is one of key parts of an engine and is formed by welding thin-wall plates, and nozzle cracks are the most common failure modes of the tail nozzle and greatly influence the reliability of the nozzle. Because the structure of the forked tail nozzle has certain vibration natural frequency, when the forked tail nozzle works under the action of interference force or torque, the forked tail nozzle can perform forced vibration according to the excitation frequency, and when the excitation frequency is the same as the natural frequency, a resonance phenomenon can be generated, so that the crack fault of the tail nozzle is caused. The crack failure of the bifurcated tail pipe mainly occurs in the welding seam area of the front adapter section of the tail pipe. The existence of crack failure can lead the tail gas discharged into the atmosphere by the engine to be possibly diffused to the periphery of the engine, and a gas leakage accident can occur. Because the temperature of the tail gas is still very high, the air pressure in the tail spray pipe is larger than the air pressure around the tail spray pipe, the tail gas is diffused, a fuel oil pipeline and a speed reducer of the engine can be subjected to very strong heat radiation, the engine can be burnt, and finally disastrous accidents can happen. Therefore, it is an important subject to be solved urgently that the strength and fatigue resistance of the welded zone of the jet nozzle are improved and the structural destruction of the jet nozzle due to the sustained resonance is prevented.
The bifurcated tail pipe can generate welding stress in the welding process and the welding strength of a welding seam is low. The welding stress is a stress generated by welding a member to be welded. The inhomogeneous temperature field of the welding process and the local plastic deformation and the structure of different specific volumes caused by it are the root causes of the resulting welding stress. When the non-uniform temperature field caused by welding has not disappeared, this stress in the weldment is called transient welding stress; the stress after the disappearance of the welding temperature field is called residual welding stress. In the thin-walled weldment, the weld residual stress is substantially planar stress, and the stress in the thickness direction is small. The weld residual stress affects the strength, stiffness, compression stability, machining accuracy, dimensional stability, corrosion resistance, etc. of the weldment. In order to further eliminate the influence caused by welding stress generated in the welding process, improve the strength of the welding seam of the tail nozzle, prolong the service life and the like, the laser shock peening technology becomes an effective and efficient first-choice processing technology. The laser shock strengthening technology is a high-tech surface processing technology which utilizes plasma shock waves generated by strong short pulse laser beams to act on the surface of a part to be processed and modifies materials by the force effect of laser, thereby improving the fatigue resistance, wear resistance and corrosion resistance of metal materials. However, the jet nozzle is a thin-walled part with a wall thickness of only about 0.25mm, and deformation of the jet nozzle is inevitably caused during laser shock peening of a weld zone of the jet nozzle, so that further improvement and perfection are needed in the prior art.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a method for optimizing the laser shock peening of a forked tail nozzle of an engine.
Another object of the present invention is to overcome the drawbacks of the prior art and to provide a device based on the above method.
The purpose of the invention is realized by the following technical scheme:
a laser shock peening and shape correcting method for a welding seam of an engine forked tail nozzle specifically comprises the following steps:
step S1: and carrying out failure analysis on the tail nozzle to determine a welding seam area needing laser shock peening.
Step S2: and clamping the tail nozzle on a special tool clamp for the tail nozzle.
Step S3: the auxiliary lighting LED lamp set is turned on to provide a high-quality observation light source in the machining process, and the water painting robot control system is turned on and controls the water painting robot to provide a stable water painting layer for a machining area.
Step S4: the laser shock strengthening unit generates shock waves and acts on the welding seam area of the tail nozzle to carry out shock strengthening.
Step S5: in the process of laser shock peening of the tail nozzle, an optical measuring instrument is adopted to measure a dynamic strain field of a material in a laser shock peening area on line in real time, an optical equipment control system calculates strain field data to obtain a material dynamic constitutive equation and dynamic strain rate data, and the material dynamic constitutive equation and the dynamic strain rate data are acquired through a data acquisition system and fed back to a complete machine control system.
Step S6: after the jet pipe is subjected to laser shock strengthening, a three-dimensional profile scanner is adopted to measure the jet pipe, a model obtained by measurement is aligned with a CAD model, the curvature error and the torsion error of a strengthened area of the jet pipe are respectively calculated, and the curvature error and the torsion error are collected by a data collection system and fed back to a complete machine control system.
Step S7: the whole machine control system determines the correction amount according to the deformation data of the tail nozzle, presets correction laser parameters and plans a correction path, the laser generator and the clamping robot receive commands of the whole machine control system, the laser control system sets laser impact correction parameters, and the clamping robot control system sets the correction path.
Step S8: and the laser shock strengthening unit generates shock waves according to the parameters set by the system and acts on the back of the strengthening area of the tail nozzle to realize shape correction.
Step S9: and after the laser shock shape correction is finished, the whole machine control system judges whether the size of the tail nozzle subjected to the laser shock shape correction is qualified.
Step S10: and if the size of the tail spray pipe is qualified, ending the laser shock peening and the shape correction.
Step S11: and if the size of the tail nozzle is not qualified, the whole machine control system obtains optimal shape correction parameters and paths through numerical simulation, online measurement data and comprehensive reasoning by combining with an impact strengthening process database, sends the optimal shape correction parameters and paths to the laser generator and the clamping robot in real time, conducts laser impact shape correction of the tail nozzle again, repeats the steps from S7 to S11, achieves real-time feedback control of movement of the optimal laser impact shape correction parameters and shape correction tracks through the laser control system and the clamping robot control system, controls reverse deformation of a strengthening area of the tail nozzle region by region, and gradually achieves overall precise shape correction through accumulated local deformation until the size requirement is met.
Preferably, the failure analysis of step S1 is to perform stress analysis, vibration analysis, aerodynamic characteristic analysis, and fatigue crack propagation analysis on the jet nozzle by using finite element software, determine a weak region of the jet nozzle according to an analysis result, and finally determine a region requiring impact reinforcement by combining a failure mode of the jet nozzle in a historical use process.
Preferably, the special fixture for the jet nozzle in step S2 is a clamp plate type profile control fixture special for a bifurcated jet nozzle of an aircraft engine.
Preferably, the laser energy of the laser shock peening units of the steps S4 and S8 is 1-10J, a circular light spot is adopted, the diameter of the light spot is 1-3mm, the pulse width of the laser is 8ns-16ns, and the pulse repetition frequency is 20 Hz.
Preferably, the whole machine control system in steps S5, S6, S7, S9, and S11 is a computer control system having a theoretical model database and a test model database, and performs intelligent monitoring and control on the whole laser shock peening and shape correction process, and can record the following laser pulse data in real time: the pulse energy, the pulse width, the time distribution and the space distribution of each pulse are recorded, compared and optimized simultaneously, process database feedback is formed, the next laser shock peening action is guided, the theoretical model database is obtained through numerical simulation, and the experimental model database is obtained through a basic test and an empirical formula.
Preferably, the optical measuring instrument of step S5 has a measurement displacement accuracy of 0.001-0.1/pixel, a resolution of 3000 ten thousand pixels, a minimum display unit of 0.1 μm, and an exposure time of 0.059-3000 ms.
Preferably, the bending error in step S6 is a difference between corresponding bending values of the measured data model and the design model, where the bending value refers to a distance from a centroid of the cross section to be analyzed to a line connecting centroids of upper and lower cross sections of the weld, and the twisting error is an angle required for overlapping from a cross section line of the CAD to a cross section line of the measured model after the measured model and the CAD are aligned.
The other purpose of the invention is realized by the following technical scheme:
a device for laser shock strengthening and shape correction of a welding line of a bifurcated tail nozzle of an engine mainly comprises a complete machine control system, a laser control system, a laser shock strengthening unit, an auxiliary lighting LED lamp group, a special tool clamp for the tail nozzle, a clamping robot control system, a water coating robot control system, an optical measuring instrument, an optical equipment control system, a three-dimensional profile scanner and a data acquisition system;
specifically, the whole machine control system is respectively connected with the laser control system, the clamping robot control system, the water coating robot control system and the data acquisition system, and drives the systems to work in order and cooperatively; the optical equipment control system is respectively connected with the data acquisition system, the auxiliary lighting LED lamp bank, the optical measuring instrument and the three-dimensional profile scanner; the data acquisition system is connected with the optical equipment control system and the three-dimensional profile scanner; the laser control system is connected with the laser shock strengthening unit through a laser; the special tool clamp for the tail nozzle is arranged on the clamping robot; the clamping robot control system is connected with the clamping robot; the water painting robot control system is connected with the water painting robot.
The working process and principle of the invention are as follows: in the process of laser shock peening and shape correction of the tail nozzle, firstly, failure analysis is carried out on the tail nozzle to determine a welding seam area needing laser shock peening for shock peening, then, an optical measuring instrument is used for measuring a dynamic strain field of a material in the laser shock peening area on line, strain field data is calculated to obtain a material dynamic constitutive equation and dynamic strain rate data, meanwhile, a three-dimensional profile scanner is used for aligning a strengthened tail nozzle measuring model with a CAD model, the bending error and the torsion error of the strengthened area of the tail nozzle are respectively calculated, all data are transmitted to a complete machine control system, shock-strengthened laser parameters are adjusted by adopting the modes of data iteration, excavation and the like, the laser parameters and the shape correction path needing shape correction are determined, finally, the shape correction of torsion and bending is carried out on the tail nozzle in the strengthening process, so that the reliability and the service life of the tail nozzle are improved in the precision manufacturing of an aeroengine, the repeated disassembly and assembly of workpieces caused by the separation of the strengthening and shape correcting processes are avoided, and the precision and the working efficiency of laser shock strengthening and shape correcting are improved, so that the flexibility, the digitization and the intellectualization of the precision manufacturing of the aircraft engine tail nozzle are realized.
Compared with the prior art, the invention also has the following advantages:
(1) the laser shock peening and shape correcting method for the engine forked tail nozzle welding line can realize control of the forked tail nozzle welding line peening and shape correcting, carry out laser shock peening and precise shape correcting on the welding line area of the tail nozzle, eliminate local stress concentration of the welding line area, generate larger residual compressive stress, refine crystal grains, enable the welding line structure to be compact, and improve the strength, the rigidity, the stability and the like of the welding line area.
(2) The laser shock strengthening and shape correcting method for the engine forked tail nozzle welding line provided by the invention avoids local deformation caused by strengthening, ensures the shape precision of the tail nozzle, prolongs the service life of the tail nozzle, is suitable for strengthening and shape correcting of the aircraft engine forked tail nozzle, and has higher social and economic benefits.
(3) The laser shock strengthening and shape correcting method and device for the engine forked tail nozzle welding line provided by the invention avoid repeated workpiece dismounting caused by separation of strengthening and shape correcting procedures, ensure the processing stability and improve the processing precision and working efficiency.
Drawings
FIG. 1 is a flow chart of a method for laser shock peening and profiling a weld joint of an engine bifurcated jet nozzle provided by the present invention.
FIG. 2 is a schematic structural diagram of a laser shock peening and shape correction device for a split jet nozzle weld joint of an engine provided by the invention.
FIG. 3 is a schematic structural view of a bifurcated jet nozzle provided in the present invention.
FIG. 4 is a schematic structural view of the special laser shock peening clamp for the bifurcated tail nozzle of the helicopter engine provided by the invention after the bifurcated tail nozzle is installed.
Fig. 5 is a schematic structural diagram of a standard positioning block provided by the present invention.
FIG. 6 is a schematic structural view of a square connecting object bearing plate according to the present invention.
Fig. 7 is a schematic structural view of the sector-shaped fixing block provided by the present invention.
Fig. 8 is a schematic structural view of an axial fixing bolt provided by the present invention.
The reference numerals in the above figures illustrate:
1-a complete machine control system, 2-a laser control system, 3-a clamping robot control system, 4-a water coating robot control system, 5-an optical equipment control system, 6-a data acquisition system, 7-a laser, 8-a laser shock strengthening unit, 9-an auxiliary lighting LED lamp bank, 10-an optical measuring instrument, 11-a three-dimensional profile scanner, 12-a clamping robot, 13-a tail nozzle special tool clamp, 14-a water coating robot and 15-a tail nozzle;
21-the tail end of a six-axis robot manipulator, 22-a standard positioning cushion block, 23-a square connecting object bearing plate, 24-upper and lower fan-shaped fixing blocks, 25-left and right fan-shaped fixing blocks, 26-a flat head connecting bolt and 27-an axial fixing bolt.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer and clearer, the present invention is further described below with reference to the accompanying drawings and examples.
Example 1:
as shown in fig. 2, the embodiment discloses a device for laser shock peening and shape correction of a welding seam of a bifurcated tail nozzle of an engine, which mainly comprises a complete machine control system 1, a laser 7, a laser control system 2, a laser shock peening unit 8, an auxiliary lighting LED lamp set 9, a special tool clamp 13 for the tail nozzle, a clamping robot 12, a clamping robot control system 3, a water coating robot 14, a water coating robot control system 4, an optical measuring instrument 10, an optical equipment control system 5, a three-dimensional profile scanner 11 and a data acquisition system 6;
specifically, the whole machine control system 1 is respectively connected with the laser control system 2, the clamping robot control system 3, the water coating robot control system 4 and the data acquisition system 6, and drives the systems to work in order and cooperatively; the optical equipment control system 5 is respectively connected with the data acquisition system 6, the auxiliary lighting LED lamp group 9, the optical measuring instrument 10 and the three-dimensional profile scanner 11; the data acquisition system 6 is connected with the optical equipment control system 5 and the three-dimensional profile scanner 11; the laser control system 2 is connected with a laser shock strengthening unit 8 through a laser 7; the special tool clamp 13 for the tail nozzle is arranged on the clamping robot 12; the clamping robot control system 3 is connected with the clamping robot 12; the water painting robot control system 4 is connected with the water painting robot 14.
With reference to fig. 1 to 8, the present embodiment further provides a laser shock peening and shape correction method for a bifurcated exhaust nozzle weld joint of an engine, including the following steps:
1) failure analysis is carried out on the tail nozzle 15 to determine the welding seam area needing laser shock peening
2) The tail nozzle 15 is clamped on a special tool clamp 13 for the tail nozzle
3) The auxiliary lighting LED lamp set 9 is turned on to provide a high-quality observation light source in the processing process, and the water painting robot control system 4 is turned on and controls the water painting robot 14 to provide a stable water painting layer for the processing area
4) The laser shock strengthening unit 8 generates shock waves and acts on the welding seam area of the tail nozzle 15 for shock strengthening
5) In the laser shock peening process of the tail nozzle 15, an optical measuring instrument 10 is adopted to measure a dynamic strain field of the material in a laser shock peening area in real time on line, an optical equipment control system 5 calculates strain field data to obtain a material dynamic constitutive equation and dynamic strain rate data, and the material dynamic constitutive equation and the dynamic strain rate data are acquired by a data acquisition system 6 and fed back to a complete machine control system 1
6) After the tail nozzle 15 is subjected to laser shock peening, the three-dimensional profile scanner 11 is used for measuring, the measured model is aligned with the CAD model, the bending error and the torsion error of the peening area of the tail nozzle 15 are respectively calculated, and the bending error and the torsion error are acquired by the data acquisition system 6 and fed back to the whole machine control system 1
7) The whole machine control system 1 determines the correction amount according to the deformation data of the tail nozzle 15, presets the correction laser parameters and plans the correction path, the laser 7 and the clamping robot 12 receive the command of the whole machine control system 1, the laser control system 2 sets the laser impact correction parameters, and the clamping robot control system 3 sets the correction path
8) The laser shock strengthening unit 8 generates shock waves according to the parameters set by the system and acts on the back of the strengthening area of the tail nozzle 15 to realize shape correction
9) After the laser impact shape correction is finished, the whole machine control system 1 judges whether the size of the tail spray pipe 15 after the shape correction is qualified or not
10) If the size of the tail nozzle 15 is qualified, the laser shock peening and the shape correction are finished
11) If the size of the tail nozzle 15 is not qualified, the whole machine control system 1 obtains an optimal shape correction parameter and a path through numerical simulation, online measurement data and comprehensive reasoning combined with an impact strengthening process database, sends the optimal shape correction parameter and the path to the laser 7 and the clamping robot 12 in real time, conducts laser impact shape correction of the tail nozzle 15 again, repeats the steps 7) to 11), achieves real-time feedback control of the optimal laser impact shape correction parameter and movement of a shape correction track through the laser control system 2 and the clamping robot control system 3, controls reverse deformation of a strengthening area of the tail nozzle 15 region by region, and gradually achieves overall precise shape correction through accumulated local deformation until the size requirement is met.
The method comprises the steps of carrying out stress analysis, vibration analysis, aerodynamic characteristic analysis and fatigue crack propagation analysis on the tail nozzle 15 through finite element software, judging a weak area of the tail nozzle 15 according to an analysis result, and finally determining an area needing impact strengthening by combining a failure mode of the tail nozzle 15 in a historical use process.
Referring to fig. 1 and 2, in practical application, the present invention clamps and fixes the exhaust nozzle 15 on the exhaust nozzle dedicated tooling fixture 13 of the clamping robot 12, wherein the exhaust nozzle dedicated tooling fixture 13 is a clamp plate type profile control tooling dedicated for the bifurcated exhaust nozzle 15 of the aircraft engine, and the required workpiece profile is formed by adopting a profile curve of a fan-shaped support structure perpendicular to a base, and the material is aluminum alloy, so that the clamping stress and the tooling weight are minimized, thereby saving the manufacturing cost and improving the production efficiency.
In the invention, after the laser control system 2 receives an instruction sent by the complete machine control system 1, the laser 7 is controlled to set corresponding parameters such as laser pulse width, energy, spot diameter, pulse repetition frequency and the like, and finally the laser shock peening unit 8 is controlled to carry out laser shock peening and shape correction. The laser energy is set between 1J and 10J, a circular light spot is adopted, the diameter of the light spot is 1 mm to 3mm, the pulse width of the laser is 8ns to 16ns, and the pulse repetition frequency is 20 Hz.
The auxiliary lighting LED lamp bank 9 is started to provide a high-quality observation light source for the optical measuring instrument 10 and the three-dimensional profile scanner 11, the auxiliary lighting LED lamp bank 9 is provided with a laser capture sensor, the corresponding position and the distance of a workpiece can be indicated and monitored, and the water coating robot is started to provide a stable water coating layer for strengthening and shape correcting processing of the tail nozzle 15.
In the invention, the whole machine control system 1 is a computer control system with a theoretical model database and a test model database, intelligently monitors and controls the whole laser shock strengthening and shape correcting process, records the pulse energy, the pulse width, the time distribution and the space distribution of each pulse in real time, records, compares and optimizes the laser shock strengthening parameters of each time, forms the feedback of a process database and guides the next laser shock strengthening parameter setting, wherein the theoretical model database is obtained by numerical simulation, and the test model database is obtained by a basic test and an empirical formula.
The tail nozzle 15 is scanned by the optical measuring instrument 10, and is finally transmitted to the whole machine control system 1 by the data acquisition system 6 after being calculated and processed by the optical equipment control system 5, the optical measuring instrument 10 can carry out full-field scanning, and can also carry out accurate scanning and reconstruction of a local area if necessary, and simultaneously can measure a dynamic strain field of a material in a laser shock strengthening area on line in real time. The optical measuring instrument 10 has a high-speed camera shooting function, the highest sampling frequency can reach 1334Hz, the strain test precision is 20-50U, the measurement displacement precision is 0.001-0.1/pixel, the resolution ratio is 3000 ten thousand pixels, the minimum display unit is 0.1 mu m, and the exposure time is 0.059-3000 ms.
Scanning by a three-dimensional profile scanner 11 to obtain a model of a tail nozzle 15, subtracting the curvature of a measurement data model obtained by scanning from the curvature of a design model to obtain an absolute value, and thus obtaining a curvature error, wherein the curvature refers to the distance from the centroid of a section to be analyzed to a connecting line of the centroids of the upper and lower sections of a welding seam; and aligning the measurement model obtained by scanning with the CAD model to obtain an angle required by the superposition of the CAD section line and the measurement model section line, thereby obtaining the torsion error.
After receiving the data detected by the optical measuring instrument 10, the optical equipment control system 5 calculates strain field data to obtain dynamic material constitutive data, and the data acquisition system 6 acquires the dynamic material constitutive data and the curvature error and the torsion error measured by the three-dimensional profile scanner 11 and feeds the dynamic material constitutive data and the curvature error and the torsion error back to the whole machine control system 1. The whole machine control system 1 performs iterative operation, data mining and other work according to all the obtained data to form a process database, and provides data support for next laser shock peening and correction parameter optimization.
After the laser impact shape correction is finished, the whole machine control system 1 judges whether the size of the tail nozzle 15 meets the requirement, and if so, the shape correction process is finished.
If the size of the tail nozzle 15 does not meet the requirement, the whole machine control system 1 is handed over to make a decision and process. The whole machine control system 1 obtains real-time optimal laser shock shape correction parameters through numerical simulation, dynamic measurement data and process database comprehensive reasoning, so that precise shape correction is repeatedly carried out region by region and finally the size requirement is met.
As shown in fig. 4 to 8, the embodiment further discloses a special laser shock strengthening clamp for a bifurcated tail nozzle of a helicopter engine (a clamp plate type profile control tool special for a bifurcated tail nozzle 15 of an aircraft engine), which mainly comprises a standard positioning cushion block 22, a square connecting object bearing plate 23, upper and lower fan-shaped fixing blocks 24, left and right fan-shaped fixing blocks 25, a flat head connecting bolt 26 and an axial fixing bolt 27, wherein the standard positioning cushion block 22 is installed at the end of a six-axis robot manipulator 21, one end of the standard positioning cushion block 22 is connected with the square connecting object bearing plate 23, the other end of the square connecting object bearing plate 23 is connected with the upper and lower fan-shaped fixing blocks 24 and the left and right fan-shaped fixing blocks 25 through the flat head connecting bolt 26, first threaded holes are respectively formed in the upper and lower fan-shaped fixing blocks 24 and the left and right fan-shaped fixing blocks 25, the axial fixing bolt 27 passes through a circumferential hole at a front, thus ensuring the axial positioning of the bifurcated nozzle 15.
A plurality of second threaded holes are formed in the square connecting object bearing plate 23, the upper fan-shaped fixing block 24, the lower fan-shaped fixing block 24, the left fan-shaped fixing block 25 and the right fan-shaped fixing block 25 are connected with the second threaded holes in the square connecting object bearing plate 23 through flat-head connecting bolts 26 to achieve compression, and positions of the square connecting object bearing plate 23 can be adjusted according to actual requirements.
The upper fan-shaped fixing block 24, the lower fan-shaped fixing block 24, the left fan-shaped fixing block 25, the right fan-shaped fixing block 25 and the left fan-shaped fixing block are uniformly distributed on the periphery of the square connecting object bearing plate 23 to form an arc shape which is concentric with the front connecting section port of the forked tail nozzle 15, wherein three U-shaped long holes and two first threaded holes are formed in each of the upper fan-shaped fixing block 24, the lower fan-shaped fixing block 24 and the left fan-shaped fixing block 25 and the right fan-shaped fixing block 25, the U-shaped long holes are used for connecting the upper fan-shaped fixing block 24, the.
The standard positioning cushion block 22, the square connecting object bearing plate 23, the upper and lower fan-shaped fixing blocks 24 and the left and right fan-shaped fixing blocks 25 are made of aluminum alloy materials, the rigidity of the whole fixture is kept, flat pads are arranged between the standard positioning cushion block 22, the upper and lower fan-shaped fixing blocks 24, the left and right fan-shaped fixing blocks 25 and the square connecting object bearing plate 23, looseness and end surface abrasion are prevented, and connection fitness and surface integrity of a connection end surface are guaranteed.
The length of the axial fixing bolt 27 is more than or equal to 8cm, and the whole screw is provided with full threads, so that the stroke and the precision of axial positioning can be conveniently adjusted.
The working process of the invention is as follows: when in use, the forked tail nozzle 15 is firstly placed at the central position of the plane of the square connecting object bearing plate 23, then the upper and lower fan-shaped fixed blocks 24 and the left and right fan-shaped fixed blocks 25 are connected with the square connecting object bearing plate 23 through flat head connecting bolts 26, the four fan-shaped fixed blocks clamp the forked tail nozzle 15 and then the flat head connecting bolts 26 are screwed down, then, eight axial fixing bolts 27 penetrate through eight circumferential holes of a front joint section port of the forked tail nozzle 15 to be connected with first threaded holes in an upper fan-shaped fixing block 24, a lower fan-shaped fixing block 24, a left fan-shaped fixing block 25 and a right fan-shaped fixing block 25, the axial fixing bolts 27 are screwed, then the square connecting object bearing plate 23 with the forked tail nozzle 15 fixed thereon is connected with four standard positioning cushion blocks 22 through bolts, the other ends of the four standard positioning cushion blocks 22 are connected with the tail end 21 of a six-axis robot manipulator, and therefore the whole clamping and fixing of the forked tail nozzle 15 is achieved.
When the bifurcated exhaust nozzle 15 is disassembled after the machining is completed, the bifurcated exhaust nozzle 15 can be removed by loosening the eight axial fixing bolts 27 and then loosening all the flat-head connecting bolts 26 on the upper and lower fan-shaped fixing blocks 24 and the left and right fan-shaped fixing blocks 25.
The above embodiments are preferred embodiments of the present invention, but the present invention is not limited to the above embodiments, and any other changes, modifications, substitutions, combinations, and simplifications which do not depart from the spirit and principle of the present invention should be construed as equivalents thereof, and all such changes, modifications, substitutions, combinations, and simplifications are intended to be included in the scope of the present invention.
Claims (8)
1. A laser shock peening and shape correction method for a welding seam of an engine forked tail nozzle is characterized by comprising the following steps:
step S1: failure analysis is carried out on the tail nozzle, and a welding seam area needing laser shock peening is determined;
step S2: clamping the tail spray pipe on a special tool clamp for the tail spray pipe;
step S3: the auxiliary lighting LED lamp set is turned on to provide a high-quality observation light source in the processing process, and the water coating robot control system is turned on and controls the water coating robot to provide a stable water coating layer for a processing area;
step S4: the laser shock strengthening unit generates shock waves and acts on the welding seam area of the tail nozzle to carry out shock strengthening;
step S5: in the process of laser shock peening of the tail nozzle, an optical measuring instrument is adopted to measure a dynamic strain field of a material in a laser shock peening area on line in real time, an optical equipment control system calculates strain field data to obtain a material dynamic constitutive equation and dynamic strain rate data, and the material dynamic constitutive equation and the dynamic strain rate data are acquired by a data acquisition system and fed back to a complete machine control system;
step S6: after the jet pipe is subjected to laser shock strengthening, a three-dimensional profile scanner is adopted to measure the jet pipe, a measured model is aligned with a CAD model, the bending error and the torsion error of a strengthened area of the jet pipe are respectively calculated, and the bending error and the torsion error are collected by a data collection system and fed back to a complete machine control system;
step S7: the whole machine control system determines the correction amount according to the deformation data of the tail nozzle, presets correction laser parameters and plans a correction path, the laser generator and the clamping robot receive the command of the whole machine control system, the laser control system sets laser impact correction parameters, and the clamping robot control system sets the correction path;
step S8: the laser shock strengthening unit generates shock waves according to parameters set by the system and acts on the back of the strengthening area of the tail nozzle to realize shape correction;
step S9: after the laser shock shape correction is finished, the whole machine control system judges whether the size of the tail nozzle subjected to the laser shock shape correction is qualified or not;
step S10: if the size of the tail nozzle is qualified, ending the laser shock peening and shape correction;
step S11: and if the size of the tail nozzle is not qualified, the whole machine control system obtains optimal shape correction parameters and paths through numerical simulation, online measurement data and comprehensive reasoning by combining with an impact strengthening process database, sends the optimal shape correction parameters and paths to the laser generator and the clamping robot in real time, conducts laser impact shape correction of the tail nozzle again, repeats the steps from S7 to S11, achieves real-time feedback control of movement of the optimal laser impact shape correction parameters and shape correction tracks through the laser control system and the clamping robot control system, controls reverse deformation of a strengthening area of the tail nozzle region by region, and gradually achieves overall precise shape correction through accumulated local deformation until the size requirement is met.
2. The method for laser shock peening and sizing of engine bifurcated nozzle welds as claimed in claim 1, wherein said failure analysis of step S1 is a stress analysis, a vibration analysis, a aerodynamic characteristic analysis, and a fatigue crack propagation analysis of the nozzle using finite element software, determining weak areas of the nozzle based on the analysis results, and finally determining areas requiring shock peening in combination with failure modes during the historical use of the nozzle.
3. The method for laser shock peening and sizing of the engine bifurcated nozzle tip weld according to claim 1, wherein the dedicated nozzle tip tooling fixture of step S2 is a dedicated clamp plate type profile control tooling fixture for an aircraft engine bifurcated nozzle tip.
4. The method for the laser shock peening and sizing of the engine bifurcated nozzle weld joint according to claim 1, wherein the laser energy of the laser shock peening unit is 1-10J, a circular light spot is adopted, the diameter of the light spot is 1-3mm, the pulse width of the laser is 8ns-16ns, and the pulse repetition frequency is 20 Hz.
5. The laser shock peening and shape correcting method for the engine forked tail nozzle welding seam according to claim 1, characterized in that the whole machine control system is a computer control system provided with a theoretical model database and a test model database, and the whole laser shock peening and shape correcting process is intelligently monitored and controlled, and the following laser pulse data can be recorded in real time: the pulse energy, the pulse width, the time distribution and the space distribution of each pulse are recorded, compared and optimized simultaneously, the feedback of a process database is formed, the next laser shock peening action is guided, the theoretical model database is obtained through numerical simulation, and the experimental model database is obtained through a basic experiment and an empirical formula.
6. The laser shock peening and profiling method for engine bifurcated nozzle weld joint according to claim 1, wherein the measurement displacement precision of the optical measuring instrument is 0.001-0.1/pixel, the resolution of the optical measuring instrument is 3000 ten thousand pixels, the minimum display unit is 0.1 μm, and the exposure time is 0.059-3000 ms.
7. The method for laser shock peening and sizing of the engine bifurcated nozzle weld according to claim 1, wherein the curvature error in step S6 is the difference between the measured data model and the design model for the corresponding curvature, the curvature is the distance from the centroid of the cross section to be analyzed to the connecting line of the centroids of the upper and lower cross sections of the weld, and the twist error is the angle required for the measured model to coincide with the CAD model from the CAD cross section line to the measured model cross section line after aligning.
8. A device for laser shock strengthening and shape correction of a welding line of a bifurcated tail nozzle of an engine is characterized by comprising a complete machine control system, a laser control system, a laser shock strengthening unit, an auxiliary lighting LED lamp group, a special tool clamp for the tail nozzle, a clamping robot control system, a water painting robot control system, an optical measuring instrument, an optical equipment control system, a three-dimensional profile scanner and a data acquisition system;
the whole machine control system is respectively connected with the laser control system, the clamping robot control system, the water coating robot control system and the data acquisition system, and drives the systems to work in order and in coordination; the optical equipment control system is respectively connected with the data acquisition system, the auxiliary lighting LED lamp bank, the optical measuring instrument and the three-dimensional profile scanner; the data acquisition system is connected with the optical equipment control system and the three-dimensional profile scanner; the laser control system is connected with the laser shock strengthening unit through a laser; the special tool clamp for the tail nozzle is arranged on the clamping robot; the clamping robot control system is connected with the clamping robot; the water painting robot control system is connected with the water painting robot.
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