CN115287414B - Electromagnetic composite field in-situ regulation and control technical device and method for aeronautical titanium alloy blade material - Google Patents
Electromagnetic composite field in-situ regulation and control technical device and method for aeronautical titanium alloy blade material Download PDFInfo
- Publication number
- CN115287414B CN115287414B CN202210858744.1A CN202210858744A CN115287414B CN 115287414 B CN115287414 B CN 115287414B CN 202210858744 A CN202210858744 A CN 202210858744A CN 115287414 B CN115287414 B CN 115287414B
- Authority
- CN
- China
- Prior art keywords
- titanium alloy
- blade material
- alloy blade
- conductive electrode
- avionics
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000463 material Substances 0.000 title claims abstract description 123
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 121
- 239000002131 composite material Substances 0.000 title claims abstract description 48
- 238000011065 in-situ storage Methods 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 title claims abstract description 21
- 230000008859 change Effects 0.000 claims abstract description 26
- 230000005684 electric field Effects 0.000 claims abstract description 17
- 238000012806 monitoring device Methods 0.000 claims abstract description 11
- 230000005540 biological transmission Effects 0.000 claims description 17
- 238000009434 installation Methods 0.000 claims description 16
- 238000005516 engineering process Methods 0.000 claims description 13
- 239000004020 conductor Substances 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 4
- 238000012544 monitoring process Methods 0.000 claims description 2
- 230000002787 reinforcement Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 31
- 230000007547 defect Effects 0.000 abstract description 16
- 238000009826 distribution Methods 0.000 abstract description 13
- 239000000956 alloy Substances 0.000 abstract description 9
- 239000011159 matrix material Substances 0.000 abstract description 8
- 229910045601 alloy Inorganic materials 0.000 abstract description 7
- 230000008878 coupling Effects 0.000 abstract description 4
- 238000010168 coupling process Methods 0.000 abstract description 4
- 238000005859 coupling reaction Methods 0.000 abstract description 4
- 230000001939 inductive effect Effects 0.000 abstract 1
- 238000009792 diffusion process Methods 0.000 description 16
- 230000004907 flux Effects 0.000 description 11
- 230000008569 process Effects 0.000 description 9
- 230000008439 repair process Effects 0.000 description 9
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 6
- 238000005187 foaming Methods 0.000 description 6
- 238000010438 heat treatment Methods 0.000 description 6
- 230000005284 excitation Effects 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000008685 targeting Effects 0.000 description 5
- 239000000306 component Substances 0.000 description 4
- 230000006872 improvement Effects 0.000 description 4
- 230000005012 migration Effects 0.000 description 4
- 238000013508 migration Methods 0.000 description 4
- 230000006911 nucleation Effects 0.000 description 4
- 238000010899 nucleation Methods 0.000 description 4
- 230000005501 phase interface Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000007731 hot pressing Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910021645 metal ion Inorganic materials 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 230000035699 permeability Effects 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000975 Carbon steel Inorganic materials 0.000 description 1
- 229910002065 alloy metal Inorganic materials 0.000 description 1
- 239000010962 carbon steel Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 230000002500 effect on skin Effects 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/04—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering with simultaneous application of supersonic waves, magnetic or electric fields
-
- 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
- C21D1/34—Methods of heating
- C21D1/40—Direct resistance heating
-
- 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
- C21D11/00—Process control or regulation for heat treatments
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the field of electromagnetic composite field coupling, and particularly relates to an in-situ regulation and control technical device and method for an electromagnetic composite field of an aeronautical titanium alloy blade material. Comprises an electric field generating device, a magnetic field generating device, an executing device and a monitoring device; the electric-magnetic composite energy is used for inducing the non-uniform micro-area of the blade material to rapidly target the phase change, so that the residual stress distribution of the material is homogenized, the free energy of nuclei is increased, the effect of phase change thermal driving force is reduced, the problems of structural damage defect of a matrix of the aerofoil alloy blade material, uneven residual stress distribution and the like are solved, and the service performance and the fatigue life of the conventional aerofoil are improved.
Description
Technical Field
The invention belongs to the field of electromagnetic composite field coupling, and particularly relates to an in-situ regulation and control technical device and method for an electromagnetic composite field of an aeronautical titanium alloy blade material.
Background
The blade is a core component of an aeroengine, and the blade material is generally manufactured by processing high-specific-strength materials such as titanium alloy, nickel-based superalloy and the like. The current blade faces the technical problems in the manufacturing fields of poor structural toughness, complex manufacturing process, low fatigue life and the like. Studies have shown that the primary failure modes of aero-engine blades are fatigue, overstress, creep, corrosion and wear. The existing manufacturing and forming process and heat treatment method are difficult to realize in-situ regulation and control on the aerial hair blade, the aim of repairing the existing micro-nano defects is fulfilled by optimizing the residual stress distribution of the blade, the reliability and fatigue life of the aerial hair blade are greatly restricted, and the problem of neck clamping which restricts the manufacturing of high-performance aerial hair blades in China is solved.
The invention provides a novel method for in-situ regulation and control technology of an electromagnetic composite field based on an aeronautical titanium alloy blade material. The method comprises the steps of utilizing the Joule heat effect, skin effect and electron wind effect of the avionic titanium alloy blade matrix material under the electromagnetic composite field energy coupling effect to carry out in-situ regulation and control on a defect micro-region, optimizing residual stress distribution, repairing micro-nano damage in situ and directionally strengthening a tissue performance weak region. The invention discloses a novel technology for 'in-situ regulation and control' of an aeronautical titanium alloy blade, which realizes breakthrough of the service performance and fatigue life of the existing aeronautical titanium alloy blade.
Disclosure of Invention
Aiming at the problems that the residual stress distribution of the prior processed and manufactured aeronautical titanium alloy blade material is uneven, micro-nano damage defects are difficult to repair in situ and the like, the invention provides an electromagnetic composite field in-situ regulation and control technical device and method for the aeronautical titanium alloy blade material, which induce the non-uniform micro-area of the blade material to rapidly target phase change through electric-magnetic composite energy, thereby homogenizing the residual stress distribution of the material, increasing nuclear free energy, reducing the effect of phase change thermal driving force, solving the problems of the damaged defects of the matrix tissue of the aeronautical titanium alloy blade material, the uneven residual stress distribution and the like, and realizing the improvement of the service performance and the service life of the prior aeronautical blade. In order to achieve the above purpose, the invention adopts the following technical scheme:
an electromagnetic composite field in-situ regulation and control technical device for an aeronautical titanium alloy blade material comprises an electric field generating device, a magnetic field generating device, an executing device and a monitoring device;
the electric field generating device mainly comprises an electric pulse generator and a Hall current sensor, wherein an output terminal contact of the electric pulse generator is connected with an input terminal contact of the upper conductive shaft and is used for providing current signals with different pulse waveforms; the Hall current sensor input terminal contact is connected with the lower conductive shaft output terminal contact and is used for collecting electric pulse signal data sent by the electric pulse generator in real time;
the magnetic field generating device comprises a magnetic pulse waveform generator, a high-voltage output power supply, an excitation coil and a coil supporting platform. The coil support platform is fixed and used for fixing and installing the coil, and the output end contact of the pulse waveform generator is connected with the input end contact of the high-voltage output power supply and used for providing different pulse waveforms so as to excite gradient magnetic fields with different intensities; the input end contact and the output end contact of the high-voltage output power supply are respectively connected with two ends of the exciting coil and are used for amplifying the voltage of the pulse waveform, so that a high-voltage pulse waveform is provided for the exciting coil; the appearance of the exciting coil is spiral, the exciting coil is connected with a high-voltage pulse waveform to excite a magnetic field in the accessory space, and the exciting coil and the aeroluminescent titanium alloy blade material are arranged and installed in a manner that central axes are coincident in the vertical direction.
The actuating device comprises a hydraulic cylinder, a coupler, a transmission shaft, a transmission bracket, an upper conductive shaft, an upper conductive electrode, a lower conductive electrode and a lower conductive shaft. The fixed support, the lower conductive shaft and the lower conductive electrode are fixed in position and used for initial positioning and installation of the aeronautical titanium alloy blade material; the hydraulic cylinder, the coupler, the transmission shaft, the transmission support, the upper conductive shaft and the upper conductive electrode are movable components, and the distance between the upper conductive electrode and the lower conductive electrode is adjusted by controlling the hydraulic cylinder so as to be used for positioning and fixing the aeroluminescent titanium alloy blade material;
the monitoring device comprises an oscilloscope, a thermal infrared imager and a personal computer. The oscilloscope is used for monitoring the electric pulse signal in real time and determining whether the current pulse signal is distorted or not; the thermal infrared imager is arranged on the aerial titanium alloy blade material in the horizontal direction and is used for collecting surface temperature data of the blade material component in real time; the personal computer is connected with the electric pulse generator and is used for editing proper electric pulse waveforms and sending the waveforms to the electric pulse generator; the personal computer can be connected with the thermal infrared imager at the same time and is used for transmitting the data of the thermal infrared imager to the personal computer in real time so as to display the surface temperature change process of the aeroluminescent titanium alloy blade material in real time.
In the scheme, the instantaneous high-energy pulse intensity of the electric pulse generator ranges from 1 to 10 6 A/cm 2 The number of instantaneous high-energy pulse currents is 1-9999.
In the scheme, the magnetic field strength of the magnetic field generating device ranges from 0.001 to 100 tesla.
In the above scheme, the output voltage range of the high-voltage output power supply is 0-380V.
In the scheme, the conductive electrode comprises an upper conductive electrode and a lower conductive electrode, and the upper conductive electrode, the lower conductive electrode, the avionics titanium alloy blade material and the exciting coil are arranged in a superposition manner in the central axis of the vertical direction and are fixedly arranged.
In the scheme, the two end surfaces of the avionics titanium alloy blade material are designed to be plane shapes matched with the end surfaces of the conductive electrodes, so that the conductive electrodes are tightly matched with the avionics titanium alloy blade material, and the avionics titanium alloy blade material is prevented from tilting and collapsing under the action of current pulses.
In the scheme, the lower conductive electrode of the conductive electrode is arranged above the lower conductive shaft, and the upper conductive electrode of the conductive electrode can adjust the distance between the lower conductive electrode and the avionics titanium alloy blade material by controlling the hydraulic cylinder, so that the upper conductive electrode, the lower conductive electrode and the avionics titanium alloy blade material are arranged.
Correspondingly, the invention also provides an in-situ control technical method for the electromagnetic composite field of the aeronautical titanium alloy blade material, which is carried out by adopting the device and specifically comprises the following steps:
s1, preparing an execution device and a magnetic field generation device which are matched with the selected avionics titanium alloy blade material according to the selected avionics titanium alloy blade material, and preparing an electric field generation device and a monitoring device.
S2, equipment installation and adjustment: firstly, a coil supporting platform carrying an exciting coil is arranged above the supporting platform for installation and fixation, and then a avionic titanium alloy blade material is arranged above a lower conductive electrode, so that a avionic titanium alloy blade material workpiece coincides with a central axis of the exciting coil in the vertical direction to finish initial positioning of the workpiece; starting a hydraulic cylinder to adjust the interval between the upper conductive electrode and the lower conductive electrode, and finishing fixation and positioning of the aeronautical titanium alloy blade material;
the input end contact and the output end contact of the electric pulse generator are respectively contacted with the upper conductive shaft and the lower conductive shaft, and a loop is formed by taking the avionics titanium alloy blade material as a conductor.
The positive and negative poles of the output end of the high-voltage output power supply are respectively connected with the input end contact and the output end contact of the magnetic pulse generator, and a magnetic field loop is formed by taking an exciting coil as a conductor.
And (3) installing and fixing the lens of the thermal infrared imager in a horizontal direction aiming at the aeroluminescent titanium alloy blade material, and connecting a signal data line with a personal computer.
S3, starting the thermal infrared imager, and collecting temperature data of the aeroluminescent titanium alloy blade material in real time; starting a high-voltage output power supply and a magnetic pulse waveform generator, and selecting a required pulse waveform to excite a magnetic field; the electric pulse generator is started to generate pulse current so as to excite an electric field, so that the surface of the component generates severe plastic deformation, nano reinforcement of the surface of the aeronautical blade is realized, and simultaneously, a pulse current signal and the surface temperature of the aeronautical titanium alloy blade material component are displayed in real time through the personal computer.
Compared with the prior art, the invention has the beneficial effects that:
1. aiming at the problems that microscopic defects, uneven residual stress and the like are easy to generate after the aerofoil blade material is manufactured and processed, the temperature of the blade material is rapidly increased by utilizing the Joule heating effect of high-energy pulse current, and the material is subjected to rapid targeting and uneven micro-area phase change due to current bypass, so that micro-area phase change in-situ regulation and control are realized, the toughness and structural stability of the matrix structure of the aerofoil blade material are greatly improved, and the service performance and the fatigue life of the aerofoil blade are obviously improved.
2. The invention realizes the close contact between the avionics titanium alloy blade material and the conductive electrode by controlling the hydraulic cylinder, and is more convenient for installing avionics blades with various shapes and sizes.
3. The subsystems of each part of the device comprise an electric field generating device, a magnetic field generating device, an executing device and a monitoring device which are all independently arranged and are not mutually interfered, so that later maintenance and installation are facilitated; meanwhile, the optimization of the technological parameters of the performance of the aeronautical titanium alloy blade material can be realized by adjusting the technological conditions related to the electric field generating device and the magnetic field generating device.
4. The invention applies pulse current and pulse magnetic field to the aeroluminescent titanium alloy blade material to form an electric-magnetic composite field; the current bypass effect in the coupling treatment process based on the electromagnetic composite field can induce the rapid targeted phase change of the titanium alloy non-uniform micro-region; the electromigration effect is beneficial to the migration of the titanium alloy blade tissue elements, increases nucleation free energy and reduces the phase change thermal driving force effect; the electromagnetic composite field can improve microscopic non-uniformity of the material, homogenize deformation phase change and internal energy distribution, repair damage defects in situ, solve the problems of damaged matrix structure of the aerofoil alloy blade material, uneven residual stress distribution and the like, and realize improvement of service performance and fatigue life of the existing aerofoil.
5. The in-situ regulation and control technology of the electro-magnetic composite field provided by the invention is not only suitable for aeronautical titanium alloy blade materials, but also suitable for other aeronautical blade metal materials such as nickel-based alloys, and the in-situ regulation and control technology of the electro-magnetic composite field can be popularized to other mechanical parts such as an aircraft body, an aircraft wing and a turbine pressure increasing disc on the basis of being suitable for aeronautical blades. The new technology of in-situ regulation of the electric-magnetic composite field can obviously strengthen the matrix structure property and prolong the service life.
Drawings
The invention will be further described with reference to the accompanying drawings and examples, in which:
FIG. 1 is a schematic diagram of a first overall structure of an electromagnetic composite field micro-nano targeting in-situ control technical device for an aeronautical titanium alloy blade material.
Fig. 2 is a front view of an actuator of the device of fig. 1.
FIG. 3 is a schematic diagram of a second overall structure of the device for the micro-nano targeting in-situ control technology of the electromagnetic composite field of the aeronautical titanium alloy blade material.
In the figure: the hydraulic cylinder 1, the coupler 2, the transmission shaft 3, the transmission bracket 4, the upper conductive shaft 5, the personal computer 6, the electric pulse generator 7, the magnetic pulse waveform generator 8, the high-voltage output power supply 9, the fixed bracket 10, the upper conductive electrode 11, the avionics titanium alloy blade material 12, the exciting coil 13, the coil supporting table 14, the infrared thermal imager 15, the oscilloscope 16, the Hall current sensor 17, the interconnection wire 18 and the lower conductive shaft 19.
Detailed Description
For a clearer understanding of technical features, objects and effects of the present invention, a detailed description of embodiments of the invention will be made with reference to the accompanying drawings.
As shown in fig. 1 and fig. 2, the device for in-situ control of an electromagnetic composite field of an aerofoil blade provided by the embodiment of the invention comprises an electric field generating device, a magnetic field generating device, an executing device 23 and a monitoring device.
The actuating device 23 comprises a hydraulic cylinder 1, a coupler 2, a transmission shaft 3, a transmission bracket 4, an upper conductive shaft 5, an upper conductive electrode 11, an avionics titanium alloy blade material 12, a lower conductive electrode 20, a lower conductive shaft 19 and a fixed bracket 10. The output shaft of the hydraulic cylinder 1 is connected with the transmission shaft 3 through the coupler 2, the transmission shaft 3 is tightly connected with the left and right side through holes of the transmission support 4 through interference fit respectively, the protruding shaft of the upper conductive electrode 11 is tightly connected with the hole of the conductive shaft 5 through clearance fit and screw thread pre-tightening, and the transmission shaft 3 is driven to drive the upper conductive electrode 11 to move up and down. The protruding shaft of the lower conductive electrode 20 is tightly connected with the concave hole of the lower conductive shaft 19 through interference fit, the lower conductive shaft 19 is in interference fit with the through hole of the fixed support 10, and the fixed support 10, the lower conductive shaft 19 and the lower conductive electrode 20 have no degree of freedom, so that a fixed support function is realized. The aeronautical titanium alloy blade material workpiece is arranged on the plane above the lower conductive electrode 20, the hydraulic cylinder 1 is started to drive the upper conductive electrode 11 to move up and down, and therefore the position installation and fixation of the aeronautical titanium alloy blade material workpiece 12 with a certain size can be realized.
Pulse current input end contact 21 and output end contact 22 of the electric pulse generator are respectively connected to two ends of the upper conductive shaft 5 and the lower conductive shaft 19;
the magnetic field generating device comprises a high-voltage output power supply 9, a magnetic pulse waveform generator 8, a coil supporting platform 14 and a spiral exciting coil 13 arranged above the coil supporting platform 14. The coil support platform 14 and the exciting coil 13 are fixedly connected through threads; the exciting coil 13 is overlapped with the central axis of the avionics titanium alloy blade material 12 in the vertical direction, the avionics titanium alloy blade material 12 is covered in the exciting coil, and the exciting coil 13 is arranged below the avionics titanium alloy blade material workpiece 12. The magnetic pulse waveform generator 8 can edit any pulse waveform, the waveform signal voltage is amplified by the high-voltage output power supply 9 and then output to the exciting coil 13, and the pulse waveforms with different voltages can generate space domain magnetic fields with different intensities after being introduced into the exciting coil.
The invention realizes the in-situ regulation and control of the electromagnetic composite field and the homogenization of residual stress through the combined action of the electric pulse generator 7 and the magnetic field generating device. The pulse current generated by the electric pulse generator 7 has the effect of repairing the local micro-nano defect of the aeronautical titanium alloy blade, and realizing the targeting treatment of the local strain area and the micro-nano defect; the pulsed magnetic field excited by the exciting coil 13 plays a role in helping atoms in the aeroluminescent titanium alloy blade to diffuse, reducing and homogenizing residual stress, reducing the thermal stability of the titanium alloy and improving the fatigue life of the titanium alloy. The invention applies pulse current and pulse magnetic field to the aeroluminescent titanium alloy blade material to form an electric-magnetic composite field; the current bypass effect in the coupling treatment process based on the electromagnetic composite field can induce the rapid targeted phase change of the titanium alloy non-uniform micro-region; the electromigration effect is beneficial to the migration of the titanium alloy blade tissue elements, increases nucleation free energy and reduces the phase change thermal driving force effect; the electromagnetic composite field can improve microscopic non-uniformity of the material, homogenize deformation phase change and internal energy distribution, repair damage defects in situ, solve the problems of damaged matrix structure defects of the aerofoil alloy blade material, uneven residual stress distribution and the like, and realize improvement of service performance and fatigue life of the existing aerofoil;
further preferably, the coil supporting platform 14 is integrally arranged on the lifting frame, the relative positions of the exciting coil 13 and the avionics titanium alloy blade material 12 are adjusted through the lifting frame, the magnetic field line path excited by the exciting coil 13 can be adjusted, the effective magnetic field intensity directly acting on the avionics titanium alloy blade material 12 can be adjusted, and the magnetic field utilization rate is improved.
Further optimized, in order to ensure the initial installation and positioning of the avionics titanium alloy blade material 12, the fixed support 10 and the lower conductive shaft 19 are fixed and immovable, the lower conductive electrode 20 is arranged above the lower conductive shaft 19, the protruding shaft of the lower conductive electrode 20 and the hole of the lower conductive shaft 19 are in clearance fit, the upper surface of the lower conductive electrode 20 is neat and smooth, and the avionics titanium alloy blade material 12 is firstly arranged above the lower conductive electrode 20 to finish the initial positioning of workpiece installation.
Further optimizing, aiming at the aero-titanium alloy blade materials 12 with different sizes, the hydraulic cylinder drives the upper conductive electrode 11 to move up and down, and fixing of the aero-titanium alloy blade materials 12 with different sizes is completed by adjusting the distance between the upper conductive electrode 11 and the lower conductive electrode 20.
Further optimizing, many times of high-intensity pulse current can burn and corrode the lower surface of the upper conductive electrode 11 and the upper surface of the lower conductive electrode 20, so that in order to ensure the effective action of electromagnetic composite field energy on the aeroluminescent titanium alloy blade material 12, the upper conductive electrode 11 and the lower conductive electrode 20 are designed to be detachable for subsequent installation and replacement.
Further optimizing, the number of the instantaneous high-energy pulse intensities is 1-9999.
In this embodiment, taking a TC11 titanium alloy aeroluminescent titanium alloy blade material as an example, the workpiece is cylindrical with a length of 10mm and a diameter of 5mm, and the workpiece is mounted and fixed between the upper conductive electrode 11 and the lower conductive electrode 20 by adjusting the up-down movement distance of the upper conductive electrode 11. The vertical exciting coil is overlapped with the central axis of the cylindrical TC11 titanium alloy blade material in the vertical direction; and starting an electric field generating device and a magnetic field generating device to implement in-situ regulation and defect repair of the TC11 titanium alloy aerofoil material 12 by an electromagnetic composite field.
The electromagnetic composite field in-situ regulation and control technical device for the aero-titanium alloy blade material has two technical schemes, one is an in-situ regulation and control technical device in which an exciting coil is arranged below the aero-titanium alloy blade material 12, and the other is an in-situ regulation and control technical device in which the exciting coil is arranged above the aero-titanium alloy blade material 12.
An in-situ control technical device for arranging an exciting coil below an aeroluminescent titanium alloy blade material 12 is shown in fig. 1, and the method specifically comprises the following steps:
s1, preparing relevant equipment such as an electric field generating device, a magnetic field generating device, an executing device 23, a monitoring device and the like according to the selected avionics alloy blade material 12.
S2, equipment installation and adjustment: firstly, a coil support platform 14 carrying an excitation coil is arranged above a support platform 10 for installation and fixation, and then a avionics titanium alloy blade material 12 is arranged above a lower conductive electrode 20, so that the avionics titanium alloy blade material 12 coincides with the central axis of the excitation coil 13 in the vertical direction to finish the initial positioning of the avionics titanium alloy blade material 12; starting the hydraulic cylinder 1 to adjust the interval between the upper conductive electrode 11 and the lower conductive electrode 20, and finishing fixation and positioning of the aeroluminescent titanium alloy blade material 12;
the input end contact 21 and the output end contact 22 of the electric pulse generator are respectively contacted with the upper conductive shaft 5 and the lower conductive shaft 19, and a loop is formed by taking the aeroluminescent titanium alloy blade material workpiece 12 as a conductor.
The positive and negative poles of the output end of the high-voltage output power supply 9 are respectively connected with the input end contact 23 and the output end contact 24 of the magnetic pulse generator, and a magnetic field loop is formed by taking the exciting coil 13 as a conductor.
The infrared thermal imager 15 is arranged and fixed in the horizontal direction aiming at the aeroluminescent titanium alloy blade material 12, and a signal data line is connected with the personal computer 6.
S3, starting the thermal infrared imager 7, and collecting temperature data of the aeroluminescent titanium alloy blade material 12 in real time; starting a high-voltage output voltage 9 and a magnetic pulse waveform generator 8, and selecting a proper pulse waveform to excite a magnetic field; the electric pulse generator 7 is turned on to generate a pulse current to excite an electric field.
The diffusion flux J of the total atoms of the ith element at the phase interface can be obtained by using the "Joule heating effect", "electron wind air stream effect", "electromigration effect" based on the traditional metal theory i Is represented by the formula (1-1):
the kTf (c) term in the formula (1-1) is the atomic diffusion flux caused by Joule heat, the second term K ew Omega j is atomic diffusion flux generated by air current flow caused by 'electron wind force', third termIs an atomic diffusion flux caused by electromigration. Diffusion of the ith element by electromagnetic composite fieldsFlux J ie
D in i An intra-crystalline atomic diffusion coefficient that is an element in i; f (C) is a vacancy concentration gradient function; k is boltzmann constant; t is the temperature; kew is the electronic wind coefficient; omega is atomic volume; j is the current density; n (N) i The intra-crystalline atomic concentration of the i-th element; ρ is the resistivity; eZi is the effective charge of the metal ion of the i-th element.
The electromagnetic composite field in-situ regulation and control process can improve the diffusion flux J of elements by remarkably increasing the current density J ie The migration and diffusion of element atoms near the phase interface are promoted, the content and distribution of elements in a structure are changed, and the fatigue life and service performance of the titanium alloy blade material are improved;
the electromagnetic composite field in-situ regulation and control process can realize local tissue structure and phase content change; phase change driving force delta G required by transformation of beta phase of aeroluminescent titanium alloy blade material into secondary alpha phase EST As shown in the formula (1-3):
ΔG EST ＝ΔG therm -ΔG f -ΔG V +ΔG αtherm (1-3)
wherein ΔG therm Is a phase change thermal driving force; ΔG f Surface free energy for new phase formation ΔG V The volume strain energy caused by the volume difference and lattice phase difference between the new phase and the old phase; ΔG αtherm Phase change driving force provided by non-thermal effect (electromagnetic energy) for electromagnetic composite field, and ΔG αtherm Can be represented by the formula (1-4);
wherein u is 0 Is vacuum magnetic permeability; g is a coarse-grain geometric factor; v is the nucleation volume; j is the current density; sigma (sigma) β Is beta phase conductivity; sigma (sigma) α Is the secondary alpha phase conductivity;
the conductivity of the secondary alpha phase in the aerofoil titanium alloy material is higher than that of the beta phase, so that the delta G αtherm >0, ΔG provided by electromagnetic composite field non-thermal effect αtherm Can be driven at a lower thermal driving force ΔG therm Next, ΔG is set EST The phase change from beta phase to secondary alpha phase is achieved, and the local tissue structure and the phase content change are achieved; meanwhile, the Joule heating effect of electromagnetic impact treatment, the selective effect of high-density pulse current and the compression effect of hot pressing stress compress the pores of the aero-foaming blade inwards to completely repair the defects of the aero-foaming titanium alloy blade, and the service performance and the fatigue life of the aero-foaming titanium alloy blade are improved.
The magnetic coil is arranged on the in-situ control technical device above the aeroluminescent titanium alloy blade material 12, the effect of targeting repair after forming and manufacturing is shown in fig. 3, and the method specifically comprises the following steps:
s1, preparing relevant equipment such as an electric field generating device, a magnetic field generating device, an executing device 23, a monitoring device and the like according to the selected avionics alloy blade material 12.
S2, equipment installation and adjustment: firstly, arranging a coil support platform 14 carrying an excitation coil under a transmission bracket 4 for installation and fixation, and then arranging a aerial titanium alloy blade material workpiece 12 above a lower conductive electrode 20, so that the aerial titanium alloy blade material workpiece 12 coincides with a central axis of the excitation coil 13 in the vertical direction to finish initial positioning of the workpiece; starting the hydraulic cylinder 1 to adjust the interval between the upper conductive electrode 11 and the lower conductive electrode 20, and finishing the fixation and positioning of the aeronautical titanium alloy blade material workpiece 12; the input end contact 21 and the output end contact 22 of the electric pulse generator are respectively contacted with the upper conductive shaft 5 and the lower conductive shaft 19, and a loop is formed by taking the aeroluminescent titanium alloy blade material workpiece 12 as a conductor.
The positive and negative poles of the output end of the high-voltage output power supply 9 are respectively connected with the input end contact 23 and the output end contact 24 of the magnetic pulse generator, and a magnetic field loop is formed by taking the exciting coil 13 as a conductor.
The infrared thermal imager 15 is arranged and fixed in the horizontal direction aiming at the aeroluminescent titanium alloy blade material 12, and a signal data line is connected with the personal computer 6.
S3, starting the thermal infrared imager 7, and collecting temperature data of the aeroluminescent titanium alloy blade material 12 in real time; starting a high-voltage output voltage 9 and a magnetic pulse waveform generator 8, and selecting a proper pulse waveform to excite a magnetic field; the electric pulse generator 7 is turned on to generate a pulse current to excite an electric field.
The diffusion flux J of the total atoms of the ith element at the phase interface can be obtained by using the "Joule heating effect", "electron wind air stream effect", "electromigration effect" based on the traditional metal theory i Is represented by the formula (1-1):
the kTf (c) term in the formula (1-1) is the atomic diffusion flux caused by Joule heat, the second term K ew Omega j is atomic diffusion flux generated by air current flow caused by 'electron wind force', third termIs an atomic diffusion flux caused by electromigration. Diffusion flux J of ith element caused by electromagnetic composite field ie
D in i An intra-crystalline atomic diffusion coefficient that is an element in i; f (C) is a vacancy concentration gradient function; k is boltzmann constant; t is the temperature; kew is the electronic wind coefficient; omega is atomic volume; j is the current density; n (N) i The intra-crystalline atomic concentration of the i-th element; ρ is the resistivity; eZi is the effective charge of the metal ion of the i-th element.
The electromagnetic composite field in-situ regulation and control process can improve the diffusion flux J of elements by remarkably increasing the current density J ie The migration and diffusion of element atoms near the phase interface are promoted, the content and distribution of elements in a structure are changed, and the fatigue life and service performance of the titanium alloy blade material are improved;
in-situ regulation and control process of electromagnetic composite fieldLocal tissue structure and phase content change can be realized; phase change driving force delta G required by transformation of beta phase of aeroluminescent titanium alloy blade material into secondary alpha phase EST As shown in the formula (1-3):
ΔG EST ＝ΔG therm -ΔG f -ΔG V +ΔG αtherm (1-3)
wherein ΔG therm Is a phase change thermal driving force; ΔG f Surface free energy for new phase formation ΔG V The volume strain energy caused by the volume difference and lattice phase difference between the new phase and the old phase; ΔG αtherm Phase change driving force provided by non-thermal effect (electromagnetic energy) for electromagnetic composite field, and ΔG αtherm Can be represented by the formula (1-4);
wherein u is 0 Is vacuum magnetic permeability; g is a coarse-grain geometric factor; v is the nucleation volume; j is the current density; sigma (sigma) β Is beta phase conductivity; sigma (sigma) α Is the secondary alpha phase conductivity;
the conductivity of the secondary alpha phase in the aerofoil titanium alloy material is higher than that of the beta phase, so that the delta G αtherm >0, ΔG provided by electromagnetic composite field non-thermal effect αtherm Can be driven at a lower thermal driving force ΔG therm Next, ΔG is set EST The phase change from beta phase to secondary alpha phase is achieved, and the local tissue structure and the phase content change are achieved; meanwhile, the Joule heating effect of electromagnetic impact treatment, the selective effect of high-density pulse current and the compression effect of hot pressing stress compress the pores of the aero-foaming blade inwards to completely repair the defects of the aero-foaming titanium alloy blade, and the service performance and the fatigue life of the aero-foaming titanium alloy blade are improved.
The repair effects of the two process schemes are not greatly different, and one of the two repair schemes can be timely selected through the existing defect characteristics (such as positions, quantity and the like) of the aeroluminescent titanium alloy blade material 12.
The new electromagnetic composite field in-situ regulation technology provided by the invention is suitable for various alloy metal materials, such as high-temperature nickel-based alloy, aluminum alloy, carbon steel and the like.
The novel electromagnetic composite field in-situ regulation technology is suitable for repairing defects of various aeroengine materials such as aerovane materials, aerovane rotating part reinforcing rings and the like and reinforcing matrixes.
The novel electromagnetic composite field in-situ regulation technology can be popularized to the enhancement of the surface and matrix tissue performance and the improvement of service life of other mechanical parts such as an airplane body, an airplane wing, a turbine pressurizing disc and the like.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other.
The embodiments of the present invention have been described above with reference to the accompanying drawings, but the present invention is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those having ordinary skill in the art without departing from the spirit of the present invention and the scope of the claims, which are to be protected by the present invention.
Claims (8)
1. The device is characterized by comprising an electric field generating device, a magnetic field generating device, an executing device and a monitoring device;
the electric field generating device comprises an electric pulse generator and a Hall current sensor, wherein an output terminal contact of the electric pulse generator is connected with an input terminal contact of the upper conductive shaft and is used for providing current signals with different pulse waveforms; the Hall current sensor input terminal contact is connected with the lower conductive shaft output terminal contact and is used for collecting electric pulse signal data sent by the electric pulse generator in real time;
the magnetic field generating device comprises a magnetic pulse waveform generator, a high-voltage output power supply, an exciting coil and a coil supporting platform, wherein the coil supporting platform is fixed and used for fixing and installing a coil, and an output end contact of the pulse waveform generator is connected with an input end contact of the high-voltage output power supply and used for providing different pulse waveforms so as to excite gradient magnetic fields with different intensities; the input end contact and the output end contact of the high-voltage output power supply are respectively connected with two ends of the exciting coil and are used for amplifying the voltage of the pulse waveform, so that a high-voltage pulse waveform is provided for the exciting coil; the appearance of the exciting coil is spiral, the exciting coil is connected with a high-voltage pulse waveform to excite a magnetic field in the space of an accessory, and the exciting coil and the aeroluminescent titanium alloy blade material are arranged and installed in a manner that central axes are overlapped in the vertical direction;
the actuating device comprises a hydraulic cylinder, a coupler, a transmission shaft, a transmission bracket, an upper conductive shaft, an upper conductive electrode, a lower conductive shaft and a fixed bracket, wherein the fixed bracket, the lower conductive shaft and the lower conductive electrode are fixed in position and are used for initial positioning and installation of the aeronautical titanium alloy blade material; the hydraulic cylinder, the coupler, the transmission shaft, the transmission support, the upper conductive shaft and the upper conductive electrode are movable components, and the distance between the upper conductive electrode and the lower conductive electrode is adjusted by controlling the hydraulic cylinder so as to be used for positioning and fixing the aeroluminescent titanium alloy blade material;
the monitoring device comprises an oscilloscope, a thermal infrared imager and a personal computer, wherein the oscilloscope is used for monitoring the electric pulse signal in real time and determining whether the current pulse signal is distorted or not; the thermal infrared imager is arranged on the aerial titanium alloy blade material in the horizontal direction and is used for collecting surface temperature data of the blade material component in real time; the personal computer is connected with the electric pulse generator and is used for editing proper electric pulse waveforms and sending the waveforms to the electric pulse generator; the personal computer can be connected with the thermal infrared imager at the same time and is used for transmitting the data of the thermal infrared imager to the personal computer in real time and displaying the surface temperature change of the aeroluminescent titanium alloy blade material in real time.
2. The avionics titanium alloy blade material electromagnetic composite field in-situ control technology device according to claim 1, wherein the electric pulse generator has an electric pulse intensity ranging from 1 to 10 6 A/cm 2 。
3. The avionics titanium alloy blade material electromagnetic composite field in-situ control technology device according to claim 1, wherein the pulse number of the pulse generator ranges from 1 to 9999.
4. The avionics titanium alloy blade material electromagnetic composite field in-situ control technology device according to claim 1, wherein the output voltage of the high-voltage output circuit ranges from 0V to 380V.
5. The avionics titanium alloy blade material electromagnetic composite field in-situ control technology device according to claim 1, wherein the magnetic pulse intensity of the exciting coil ranges from 0.001 to 100 tesla.
6. The device for in-situ regulation and control of the electromagnetic composite field of the avionics titanium alloy blade material according to claim 1, wherein the conductive electrode comprises an upper conductive electrode and a lower conductive electrode, and the upper conductive electrode, the lower conductive electrode, the avionics titanium alloy blade material and the exciting coil are arranged and fixed in a manner of overlapping central axes in the vertical direction.
7. The avionics titanium alloy blade material according to claim 1, wherein two end surfaces of the avionics titanium alloy blade material are designed into a planar shape matched with the end surfaces of the conductive electrode, so that the conductive electrode is tightly matched with the avionics titanium alloy blade material, and the avionics titanium alloy blade material is prevented from tilting and collapsing under the action of electric pulses.
8. An in-situ control method for an electromagnetic composite field of an aeronautical titanium alloy blade material, which is characterized by being applicable to the device of any one of claims 1 to 7, and comprising the following steps:
s1, preparing an execution device and a magnetic field generation device which are matched with the selected avionics titanium alloy blade material according to the selected avionics titanium alloy blade material, and preparing a set of electric field generation device and a set of monitoring device;
s2, equipment installation and adjustment: firstly, a coil supporting platform carrying an exciting coil is arranged above the supporting platform for installation and fixation, and then a avionic titanium alloy blade material is arranged above a lower conductive electrode, so that a avionic titanium alloy blade material workpiece coincides with a central axis of the exciting coil in the vertical direction to finish initial positioning of the workpiece; starting a hydraulic cylinder to adjust the interval between the upper conductive electrode and the lower conductive electrode, and finishing fixation and positioning of the aeronautical titanium alloy blade material;
the input end contact and the output end contact of the electric pulse generator are respectively contacted with the upper conductive shaft and the lower conductive shaft, and a loop is formed by taking the avionics titanium alloy blade material as a conductor;
the positive and negative electrodes of the output end of the high-voltage output power supply are respectively connected with the input end contact and the output end contact of the magnetic pulse generator, and a magnetic field loop is formed by taking an exciting coil as a conductor;
the lens of the thermal infrared imager is aligned with the aerial titanium alloy blade material in the horizontal direction for installation and fixation, and a signal data line is connected with a personal computer;
s3, starting the thermal infrared imager, and collecting temperature data of the aeroluminescent titanium alloy blade material in real time; starting a high-voltage output power supply and a magnetic pulse waveform generator, and selecting a required pulse waveform to excite a magnetic field; the electric pulse generator is started to generate pulse current so as to excite an electric field, so that the surface of the component generates severe plastic deformation, nano reinforcement of the surface of the aeronautical blade is realized, and simultaneously, a pulse current signal and the surface temperature of the aeronautical titanium alloy blade material component are displayed in real time through the personal computer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210858744.1A CN115287414B (en) | 2022-07-20 | 2022-07-20 | Electromagnetic composite field in-situ regulation and control technical device and method for aeronautical titanium alloy blade material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210858744.1A CN115287414B (en) | 2022-07-20 | 2022-07-20 | Electromagnetic composite field in-situ regulation and control technical device and method for aeronautical titanium alloy blade material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115287414A CN115287414A (en) | 2022-11-04 |
| CN115287414B true CN115287414B (en) | 2024-01-30 |
Family
ID=83824523
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210858744.1A Active CN115287414B (en) | 2022-07-20 | 2022-07-20 | Electromagnetic composite field in-situ regulation and control technical device and method for aeronautical titanium alloy blade material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115287414B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116694871A (en) * | 2023-05-31 | 2023-09-05 | 武汉理工大学 | Electromagnetic impact improving method for rolling contact fatigue performance of bearing steel |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005076061A (en) * | 2003-08-29 | 2005-03-24 | Sodick Co Ltd | Method and device for reforming surface of metal member |
| CN201125261Y (en) * | 2007-11-20 | 2008-10-01 | 浙江大学 | System for eliminating material internal residual stress by electric shock ageing process |
| CN104947046A (en) * | 2015-07-28 | 2015-09-30 | 魏永强 | Multistage magnetic field arc ion plating and high power pulse magnetron sputtering compound deposition method |
| CN107190222A (en) * | 2017-05-27 | 2017-09-22 | 武汉理工大学 | A kind of titanium alloy blade residual stress shot-peening electromagnetic field is combined regulation and control method |
| CN113305743A (en) * | 2021-05-06 | 2021-08-27 | 武汉理工大学 | Micro-nano targeted repairing device and method for electromagnetic composite field of inner ring of aeroengine bearing |
| CN114709068A (en) * | 2022-06-07 | 2022-07-05 | 四川大学 | Device and method for improving magnetic performance of manganese-zinc ferrite through coupling of microwave field, electric field and magnetic field |
-
2022
- 2022-07-20 CN CN202210858744.1A patent/CN115287414B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005076061A (en) * | 2003-08-29 | 2005-03-24 | Sodick Co Ltd | Method and device for reforming surface of metal member |
| CN201125261Y (en) * | 2007-11-20 | 2008-10-01 | 浙江大学 | System for eliminating material internal residual stress by electric shock ageing process |
| CN104947046A (en) * | 2015-07-28 | 2015-09-30 | 魏永强 | Multistage magnetic field arc ion plating and high power pulse magnetron sputtering compound deposition method |
| CN107190222A (en) * | 2017-05-27 | 2017-09-22 | 武汉理工大学 | A kind of titanium alloy blade residual stress shot-peening electromagnetic field is combined regulation and control method |
| CN113305743A (en) * | 2021-05-06 | 2021-08-27 | 武汉理工大学 | Micro-nano targeted repairing device and method for electromagnetic composite field of inner ring of aeroengine bearing |
| CN114709068A (en) * | 2022-06-07 | 2022-07-05 | 四川大学 | Device and method for improving magnetic performance of manganese-zinc ferrite through coupling of microwave field, electric field and magnetic field |
Non-Patent Citations (1)
| Title |
|---|
| 电磁场在材料科学中的应用;代威, 傅正义, 卢北平, 张丰收;国外建材科技(第03期) * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115287414A (en) | 2022-11-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115287414B (en) | Electromagnetic composite field in-situ regulation and control technical device and method for aeronautical titanium alloy blade material | |
| CN111299578B (en) | Method for electromagnetic-assisted direct laser deposition of nickel-based superalloy-titanium alloy functionally-graded material | |
| CN107675172A (en) | One kind is based on the laser cladding apparatus and method of ultrasound-Lorentz force complex vibration | |
| CN106757001B (en) | The method and apparatus that electromagnetic agitation auxiliary carries out laser melting coating under a kind of pressure cooler environment | |
| CN113249668B (en) | Method for improving anisotropy of additive manufacturing titanium alloy by using pulse current | |
| CN111590076A (en) | Electric pulse post-processing method and device for improving performance of metal component | |
| WO2021129338A1 (en) | Device for decoupling electric effects in electromagnetic forming process | |
| CN108406224A (en) | A kind of high-frequency direct-current heating auxiliary roll processing device and its processing method | |
| CN113305743B (en) | Micro-nano targeted repairing device and method for electromagnetic composite field of inner ring of aeroengine bearing | |
| CN113502379B (en) | Device and method for eliminating residual stress of workpiece by using pulse electromagnetic force | |
| CN111855432A (en) | Device and method for testing stress-strain curve of titanium alloy material under high-temperature high-strain rate | |
| CN110773868A (en) | Steady-state magnetic field coupling laser wire-filling narrow groove repairing method | |
| WO2014088423A1 (en) | Apparatus and method for induction heating of magnetic materials | |
| CN115404313B (en) | Microstructure homogenizing method and device in metal material deformation process | |
| CN211638677U (en) | Steady-state magnetic field coupling laser wire-filling narrow groove repairing equipment | |
| CN110773869A (en) | Steady state magnetic field coupling laser filler wire narrow groove prosthetic devices | |
| CN207435546U (en) | One kind is based on the laser cladding apparatus of ultrasound-Lorentz force complex vibration | |
| CN214218862U (en) | Laser cladding equipment with synchronous induction heating device | |
| CN112588974B (en) | Aluminum alloy heating equipment and operation method | |
| CN207498471U (en) | Laser cladding apparatus based on clamping electrified regulation and rotating electric field stirring | |
| CN211305210U (en) | Steady state magnetic field coupling laser filler wire narrow groove prosthetic devices | |
| WO2021109257A1 (en) | Steady-state magnetic field coupling laser filler-wire narrow slot repair method and device | |
| CN112423416A (en) | Novel high-temperature superconducting induction heating device | |
| CN113884534B (en) | Method for improving heat transfer performance of nickel-based alloy heat transfer pipe through electromagnetic coupling treatment | |
| CN112185645B (en) | Magnetic conductive iron core with adjustable size |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |