Electromagnetic impact treatment method for efficiently regulating and controlling performance of aero-engine gear steel

Abstract

According to the electromagnetic impact treatment method for efficiently regulating and controlling the performance of the aero-engine gear steel, the aero-engine gear steel is connected into electromagnetic impact treatment equipment to be subjected to electromagnetic impact treatment; the method can quickly and effectively regulate and control the phase change of the aero-engine gear steel, refine grains, adjust dislocation distribution and homogenize carbide precipitation to a certain extent, can repair micro-nano defects generated by a turning or carburizing process, alleviates the problem of uneven carbide distribution, remarkably improves the wear resistance and fatigue life of a gear steel substrate, and improves the service life of the gear steel substrate. And redistribution and repair of microstructures can be achieved by means of local strengthening of short-time high-density pulse current after macroscale manufacturing, the comprehensive performance of the treated gear steel component is finally improved, the gear steel component can adapt to severe conditions such as high-temperature friction and fatigue, and the service performance and the service life limit of an existing aviation gear are broken through.

Description

Technical Field

[0001] This invention relates to the field of aerospace gear steel materials technology, and in particular to an electromagnetic shock treatment method for efficiently controlling the performance of aero-engine gear steel. Background Technology

[0002] As a crucial component for power transmission, aero-engine gears face extremely high working intensity and harsh environmental conditions, typically requiring long-term operation under high loads, high speeds, and high temperatures. Therefore, the wear resistance, fatigue resistance, and high-temperature resistance of aero-engine gear steel are key to ensuring engine stability and durability.

[0003] However, while traditional surface strengthening techniques such as laser cladding and ion penetration can improve material properties to some extent, they are prone to surface defects during the process. Furthermore, these techniques cannot precisely control the microstructure of the material, leading to insufficient stability under extreme conditions. Especially under complex conditions such as high-temperature friction and fatigue, the overall performance of the material has not yet been fully improved.

[0004] Therefore, there is an urgent need for an efficient electromagnetic shock treatment method to regulate the properties of aero-engine gear steel in order to solve the above-mentioned technical problems. Summary of the Invention

[0005] The purpose of this invention is to provide an efficient electromagnetic shock treatment method for regulating the performance of aero-engine gear steel, thereby solving the technical problem of poor overall performance of existing aero-engine gear steel.

[0006] To solve the above-mentioned technical problems, the present invention provides an efficient electromagnetic shock treatment method for controlling the properties of aero-engine gear steel, the method comprising: S10 provides an electromagnetic shock treatment device, which includes a primary circuit and a secondary circuit electromagnetically coupled to the primary circuit. The primary circuit is used to input electrical energy and generate a changing magnetic field, and the secondary circuit is used to sense the changing magnetic field and generate a pulse current. S20 fixes the aero-engine gear steel to the secondary circuit and enables the aero-engine gear steel to conduct to the secondary circuit; S30: Turn on the AC power supply of the primary circuit to perform electromagnetic shock treatment on the gear steel of the aircraft engine to obtain the treated gear steel component; the peak current of the electromagnetic shock treatment is 10~5000A, and the electromagnetic shock treatment time is 0.01~1s.

[0007] Preferably, in step S10: the primary circuit includes an AC power supply, an excitation circuit, and a converter connected in sequence; the secondary circuit includes a converter and an oscilloscope connected in sequence; the secondary circuit achieves electromagnetic coupling with the primary circuit through the converter.

[0008] Preferably, the converter includes a conversion body, a primary induction coil, and a secondary induction coil, and the conversion body includes a first winding portion and a second winding portion disposed opposite to each other; The primary induction coil is wound on the first winding section, and the secondary induction coil is wound on the second winding section.

[0009] Preferably, step S20 specifically includes: S201, clamp the aero-engine gear steel between the first electrode and the second electrode, and ensure that the contact surfaces of the aero-engine gear steel with the first electrode and the second electrode are flat respectively. S202, the first electrode is electrically connected to the oscilloscope, and the second electrode is electrically connected to the second winding section.

[0010] Preferably, the electromagnetic shock treatment in step S30 further includes: real-time monitoring of the temperature at the contact point between the aero-engine gear steel and the first and second electrodes, and real-time monitoring of the current density flowing through the aero-engine gear steel.

[0011] Preferably, the gear steel for aero-engines is CSS-42L type gear steel; both the first electrode and the second electrode are made of copper.

[0012] Preferably, in step S30, the pulse width of the electromagnetic shock treatment is 0.01s, and the pulse period is 1 to 10s.

[0013] Preferably, the friction coefficient of the treated gear steel component at 500°C is lower than that of the aero-engine gear steel at 500°C.

[0014] Preferably, the dislocation density of the treated gear steel component is lower than that of the gear steel for aero-engines.

[0015] Preferably, during the electromagnetic shock treatment in step S30, M is deposited in the region near the first and second electrodes of the treated gear steel component. 23 C6 type carbides.

[0016] The beneficial effects of this invention are as follows: Unlike existing technologies, this invention provides an efficient electromagnetic shock treatment method for regulating the performance of aero-engine gear steel. This method involves connecting the aero-engine gear steel to an electromagnetic shock treatment device for electromagnetic shock treatment, which can quickly and effectively regulate the phase transformation of the aero-engine gear steel, refine the grains, adjust the dislocation distribution, and uniformly precipitate carbides to a certain extent. It can not only repair micro-nano defects caused by turning or carburizing processes and alleviate the problem of uneven carbide distribution, but also significantly improve the wear resistance and fatigue life of the gear steel matrix. Furthermore, after macro-scale manufacturing, it can achieve the redistribution and repair of the microstructure through local strengthening by short-duration high-density pulse current, ultimately improving the comprehensive performance of the treated gear steel components. This allows them to adapt to harsh conditions such as high-temperature friction and fatigue, breaking through the service performance and life limits of existing aero-engine gears. Attached Figure Description

[0017] Figure 1 This is a flowchart of the electromagnetic shock treatment method for efficiently regulating the performance of aero-engine gear steel provided in the embodiments of the present invention; Figure 2 This is a circuit diagram showing the connection between the electromagnetic shock treatment equipment and the aero-engine gear steel in the electromagnetic shock treatment method for efficiently regulating the performance of aero-engine gear steel provided in this embodiment of the invention. Figure 3a This is a schematic diagram of the wear morphology of CSS-42L type gear steel base material after 60 minutes of friction; Figure 3b This is a schematic diagram of the wear morphology of the treated gear steel component provided in Example 1 after 60 minutes of friction; Figure 3c A comparative schematic diagram of the real-time friction coefficient curves of the CSS-42L type gear steel base material and the treated gear steel component provided in Example 1 during the friction and wear test: Figure 4 A comparative schematic diagram of XRD characterization results for CSS-42L type gear steel base material and the treated gear steel component provided in Example 1; Figure 5 XPS photoelectron spectroscopy of the processed gear steel component provided in Example 1. Detailed Implementation

[0018] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0019] To address the shortcomings of existing technologies, this invention proposes a novel method based on electromagnetic shock treatment (EST): by applying a high-density pulsed current, the microstructure of the material is altered in a short time. This method can effectively promote transient phase transformation in gear steel, and can also refine grains, adjust dislocation distribution, and optimize carbide precipitation to a certain extent. Compared with traditional strengthening methods, EST is more applicable to large components, has higher processing efficiency, and can control materials from the micro to the macro scale. Furthermore, current electromagnetic shock treatment processes mostly use self-made equipment, have short processing times, are environmentally friendly, and possess multifunctionality. The mechanisms by which pulsed current enhances material properties have been extensively studied, encompassing electromigration, Joule heating, electron wind, and electromagnetic effects. It can not only effectively reduce residual stress and deformation stress in specimens but also improve the anisotropy of metallic materials and repair microscopic defects. Applying this EST method to aero-engine gear steel allows for targeted control of the matrix micro-regions, thereby significantly improving its service performance and service life.

[0020] Please see Figures 1 to 2 , Figure 1 This is a flowchart of the electromagnetic shock treatment method for efficiently regulating the performance of aero-engine gear steel provided in the embodiments of the present invention; Figure 2 This is a circuit diagram illustrating the connection between the electromagnetic shock treatment equipment and the aero-engine gear steel in the electromagnetic shock treatment method for efficiently regulating the properties of aero-engine gear steel provided in this embodiment of the invention; wherein, the above-mentioned preparation method includes: S10 provides an electromagnetic shock processing device, which includes a primary circuit and a secondary circuit electromagnetically coupled to the primary circuit. The primary circuit is used to input electrical energy and generate a changing magnetic field, and the secondary circuit is used to sense the changing magnetic field and generate a pulse current.

[0021] Specifically, the primary circuit includes an AC power supply (preferably a 380V AC power supply), a trigger circuit, and a converter connected in sequence, and the secondary circuit includes a converter and an oscilloscope connected in sequence; the secondary circuit is electromagnetically coupled to the primary circuit through the converter.

[0022] Specifically, the converter includes a conversion body, a primary induction coil (with N1 turns) and a secondary induction coil (with N2 turns). The conversion body includes a first winding section and a second winding section arranged opposite to each other, and the conversion body is an iron core. The primary induction coil is wound on the first winding section, and the secondary induction coil is wound on the second winding section.

[0023] Specifically, the electromagnetic shock treatment equipment provided in step S10, through optimized design of the primary and secondary circuits, can not only stably input electrical energy and efficiently generate a changing magnetic field through the primary circuit, but also accurately sense the changing magnetic field to generate a controllable pulse current through the secondary circuit. At the same time, the oscilloscope can monitor the circuit parameters in real time to ensure the stability and controllability of the pulse current. This lays a reliable equipment foundation for subsequent electromagnetic shock treatment to achieve microstructure control of aero-engine gear steel (such as grain refinement and optimization of carbide precipitation) and improve its key properties such as wear resistance and fatigue resistance.

[0024] S20 fixes the aero-engine gear steel to the secondary circuit and enables the aero-engine gear steel to conduct to the secondary circuit.

[0025] Specifically, step S20 also includes: S201, the aero-engine gear steel is clamped between the first electrode and the second electrode, and it is ensured that the contact surfaces of the aero-engine gear steel with the first electrode and the second electrode are flat and maintain good contact. S202, the first electrode is electrically connected to the oscilloscope, and the second electrode is electrically connected to the second winding section.

[0026] Specifically, in step S20, the aero-engine gear steel is clamped between the first and second electrodes, ensuring a smooth and flat contact surface. This avoids abnormal current density caused by insufficient actual contact area, reduces the risk of localized oxidation, and provides a uniform current conduction basis for subsequent electromagnetic shock treatment. Simultaneously, the first electrode is electrically connected to an oscilloscope, and the second electrode is electrically connected to the second winding section. This allows for real-time monitoring of circuit parameters via the oscilloscope to ensure controllable processing and ensures stable connection of the gear steel to the secondary circuit. This enables the pulse current generated by the secondary induction coil to reliably act on the aero-engine gear steel, laying a stable conductive foundation for subsequent electromagnetic shock-based control of the gear steel's microstructure (such as grain refinement and optimized carbide precipitation) and improvement of its wear resistance and fatigue resistance.

[0027] S30: Turn on the AC power supply of the primary circuit to perform electromagnetic shock treatment on the gear steel of the aircraft engine to obtain the treated gear steel component; the peak current of the electromagnetic shock treatment is 10~5000A, and the electromagnetic shock treatment time is 0.01~1s.

[0028] Specifically, the electromagnetic shock treatment process for aero-engine gear steel using electromagnetic shock treatment equipment is as follows: An excitation circuit and converter generate a primary current in the primary induction coil, and its changes excite a secondary induction coil to form a secondary current. Through the synergistic effect of these induction coils, a pulsed current can be generated flowing through the aero-engine gear steel.

[0029] Specifically, the electromagnetic shock treatment in step S30 also includes: real-time monitoring of the temperature at the contact point between the aero-engine gear steel and the first and second electrodes, and real-time monitoring of the current density flowing through the aero-engine gear steel.

[0030] Furthermore, in actual electromagnetic shock treatment processes, the surface of aero-engine gear steel is prone to oxidation after electro-pulse treatment. This phenomenon occurs because, under high-density current, the actual contact area between the contact point and the aero-engine gear steel is smaller than the coverage area, leading to an abnormally high current density at the end-face contact point. The current-induced thermal effect causes a rapid temperature rise in a short time, resulting in localized oxidation. Therefore, during electro-pulse treatment, it is crucial to monitor the temperature at the contact point and ensure that the current density of the workpiece being treated is within the specified range to avoid severe surface oxidation.

[0031] In step S30, the aero-engine gear steel is CSS-42L type gear steel (CSS-42L Sample); both the first and second electrodes are made of copper; the pulse width of the electromagnetic shock treatment is 0.01s, and the pulse period is 1-10s; the friction coefficient of the treated gear steel component at 500℃ is lower than that of the aero-engine gear steel at 500℃; the dislocation density of the treated gear steel component is lower than that of the aero-engine gear steel; and M-type deposits precipitate in the region of the treated gear steel component near the first and second electrodes. 23 C6 type carbides.

[0032] Specifically, the copper electrode, with its excellent conductivity and smooth contact characteristics, ensures the stable application of pulsed current to gear steel, preventing localized oxidation caused by abnormal current density. Specific pulse parameters, adapted to the CSS-42L material, can efficiently control its microstructure, significantly reducing the coefficient of friction of the treated component at 500℃ (reducing high-temperature friction loss), and enhancing the structural stability of the component under high-temperature friction and fatigue conditions by reducing dislocation density (promoting recrystallization and refining grains). Simultaneously, the M-precipitated material near the electrode in the treated component... 23 C6 type carbides can further improve surface hardness and wear resistance, prevent surface cracks from appearing during long-term service, and ultimately comprehensively improve the high-temperature service performance and service life of CSS-42L type gear steel, making it suitable for the harsh working environment of high load and high temperature of aero engines.

[0033] The following specific examples illustrate the effectiveness of the aforementioned electromagnetic shock treatment method for efficiently regulating the properties of aero-engine gear steel.

[0034] Example 1: The specific preparation process of the electromagnetic shock treatment method for efficiently controlling the properties of aero-engine gear steel provided in Example 1 is as follows: Step (1), the CSS-42L type gear steel is subjected to the following process: Figure 2 As shown in the installation diagram, the CSS-42L gear steel is fixed by the upper and lower copper electrodes to ensure that the contact surfaces between the CSS-42L gear steel and the copper electrodes are flat and maintain good contact.

[0035] Step (2): Turn on the AC power supply (380V) of the primary circuit to perform electromagnetic shock treatment on the CSS-42L type gear steel to obtain the treated gear steel component; the peak current of the electromagnetic shock treatment is 4200A, the electromagnetic shock treatment time is 0.5s, the pulse width is 0.01s, and the pulse period is 1s.

[0036] Please see Figures 3a to 3b Under an optical microscope (OM), the wear mark width of the treated gear steel component (EST sample) provided in Example 1 was reduced compared to that of the CSS-42L type gear steel base material.

[0037] Please see Figure 3c , Figure 3c A comparative schematic diagram of the real-time friction coefficient curves during friction and wear testing for the CSS-42L type gear steel base material (Control sample) and the treated gear steel component provided in Example 1 (EST sample): Figure 3c It can be seen that under a test environment of 500℃, the coefficient of friction of the CSS-42L gear steel base material is basically stable at around 0.65, while the coefficient of friction of the EST sample drops to about 0.57. This is because the EST treatment produces an oxide film or a similar molten film on the metal surface. These films can fill the tiny pits and uneven areas on the metal surface, thereby reducing friction and wear. Electro-impact treatment generates high temperatures on the metal surface, causing thermal expansion of the metal surface layer, shearing off protrusions, increasing the hardness and strength of the metal surface, reducing the friction between metals, and thus reducing the coefficient of friction.

[0038] Specifically, during the electromagnetic shock treatment of CSS-42L gear steel base material, the localized Joule heating of high-density current can promote the slip rate of dislocations and lead to dislocation annihilation. DC electric stress can generate high-density dislocations in the metal, and the resulting Joule heating induces in-situ recrystallization. The grain refinement effect of high-density current on the microstructure of metallic materials has been observed. This grain refinement can be attributed to the coupling effect of the thermal and non-thermal effects of the current during the recrystallization process. Throughout the recrystallization process of the metallic material, high-density pulsed current can increase the nucleation rate and recrystallization rate while inhibiting grain growth, thereby achieving grain refinement.

[0039] Please see Figure 4 , Figure 4 A comparative schematic diagram of XRD characterization results for the CSS-42L type gear steel base material (Control sample) and the treated gear steel component (EST sample) provided in Example 1; wherein, Figure 4 XRD results show that the effects of high-density current on dislocations include dislocation recovery and annihilation, which leads to a refinement of the recrystallized structure.

[0040] Specifically, the dislocation density of α-Fe can be accurately calculated using the following process: First, the diffraction angle of each diffraction peak ( θ The full width at half maximum (FWHM) and the full width at half maximum (FWHM) can be obtained from the XRD pattern fitted by the Lorentz function. The FWHM value obtained from each peak of α-Fe can be substituted into the following MWH equation (Modified Williamson-Hall equation): (1); in, ΔK=2cosθ(Δθ) / λ; K=2sinθ / λ ; Δθ and λ These represent the FWHM value and wavelength, respectively. D , b and ρ These represent the average grain size, Burgers vector, and dislocation density, respectively.

[0041] Specifically, in formula (1): b =2.55×10 -10 m, λ=0.15405nm; M is a constant that depends on the effective outer cutoff radius of the dislocation and the dislocation density; dislocation correlation factor ( The calculation method for ) is shown in formula (2): (2); in, q It is a parameter that depends on the characteristics of the edge dislocation or screw dislocation. H 2 It is a key parameter used to calculate the dislocation contrast factor. H 2 The calculation method is shown in formula (3): (3); Specifically, It is a constant corresponding to the elastic constant of the material, and its calculation method is shown in formula (4): =a[1-exp(- A i / b)+c A i+d](4;wherein, A i It is an independent variable reflecting the degree of deformation or energy accumulation. For body-centered cubic (BCC) crystals, A i The value is 2C44 / (C11-C12); C44, C11 and C12 are the elastic constants of body-centered cubic crystals.

[0042] Furthermore, let α=0.9 / D and ,Will α , Substituting the combined equations (1) and (2) into... back, q The reciprocal of is given by the following formula (5): the intercept of the extrapolation line with the horizontal axis. (5); In formula (4): a=0.1740, b=1.9522, c=0.0293, d=0.0662, C44=280Gpa, C11=120Gpa, C12=80Gpa.

[0043] Furthermore, this can be achieved by considering the left-hand side terms in formula (5) and... H 2 Apply a linear relationship between them to determine α The experimental values, q The measured value is derived from the linear function. H 2 The coefficients are given. Therefore, it is possible to... q The value is inserted into formula (2) to obtain the value for each reflection. Through equation (1) and ΔK The linear fit between the two is used to calculate the change in dislocation density before and after electromagnetic pulse treatment.

[0044] according to Figure 4 middle Δθ and λ Based on the calculations using formulas (1) to (5) above, the dislocation density of the CSS-42L gear steel base material before electromagnetic pulse treatment can be determined. ρ 3.547223*10 8 / mm 2 Dislocation density after electromagnetic pulse treatment ρ 1.781433*10 8 / mm 2 Therefore, electromagnetic shock treatment can significantly reduce dislocation density, promote recrystallization, refine the grains of the material, and enhance its stability under high-temperature friction and fatigue conditions.

[0045] To further demonstrate the effects of electromagnetic shock treatment on the formation of the oxide film, the distribution of alloy element oxidation states, and the tribological behavior of CSS-42L gear steel, this invention tested the XPS photoelectron spectroscopy of the treated gear steel component provided in Example 1, as follows: Figure 5 As shown, the electromagnetically impacted samples exhibited strong oxide characteristic peaks in the O 1s, Fe 2p, Co 2p, and Cr 2p energy regions. Furthermore, the content of high-valence metal elements increased significantly with pulsed current treatment (the surface oxidation state of the CSS-42L gear steel base material was fully characterized by XRD phase analysis and frictional performance comparison; the surface layer mainly consisted of α-Fe phase and a small amount of carbides, with no obvious multivalent metal peaks). The formation of the oxide layer and the change in the distribution of multivalent oxides can provide a well-adhesive anti-friction protective film under high-temperature frictional conditions at 500℃. Simultaneously, the coupling effect of the pulsed current on the surface microstructure and carbide precipitation can significantly improve the hardness and wear resistance of the steel matrix and reduce the coefficient of friction.

[0046] Please see Figure 5 In (a), the 1s spectrum of O can be decomposed into three main peaks: a metal oxide peak near 529.85 eV (O-Metal), a C=O peak near 531.39 eV, and an adsorbed oxygen peak near 532.84 eV (Oabs). In the electromagnetic shock treated sample, the area ratio of the O-Metal peak is relatively increased, indicating a significant increase in the content of metal oxides on its surface; the C=O peak and the adsorbed oxygen peak indicate the presence of a slight oxide film and adsorption of organic groups on the surface. The presence of these oxidized components helps to form a stable surface protective film under high-temperature wear conditions, thereby reducing the friction coefficient and improving wear resistance.

[0047] Please see Figure 5 In (b), the split peaks of Fe 2p_3 / 2 and Fe 2p_1 / 2 shown are present, except for metallic iron (Fe). 0 In addition, Fe can also be observed. 2+ with Fe 3+ The characteristic peaks of Fe were observed, with satellite peaks (Sat.) appearing in the high binding energy region. Compared to the parent material sample, Fe after electromagnetic shock treatment showed... 2+ Fe 3+ The significant increase in peak area ratio indicates that the surface oxidation process is jointly promoted by the instantaneous heating of high-density pulsed current and the "electronic wind" effect; some Fe elements are converted into high-valence oxides (such as FeO, Fe3O4 or Fe2O3), which in turn play the role of anti-wear protective layer during the friction process.

[0048] Please see Figure 5 In the middle (c), the 2p spectrum of Co can distinguish Co. 0 Co 2+ and Co3+ Co exhibits multiple valence states and a distinct satellite peak (Sat.). On the surface of the electromagnetically impact-treated sample, Co... 2+ With Co 3+ The relative enhancement of the peaks indicates that the pulsed current also promotes the transformation of the cobalt oxidation state. The oxide formed by Co has a synergistic effect on improving the wear resistance and high-temperature stability of the alloy surface.

[0049] Please see Figure 5 In the middle (d), the two main peaks of Cr are 2p3 / 2 and 2p1 / 2, with Cr as the dominant element. 3+ The main binding energies are approximately 576.62 eV and 586.48 eV, respectively. After electromagnetic shock treatment, Cr... 3+ The relatively increased peak intensity indicates that chromium is more likely to form stable Cr2O3 or complex oxides under pulsed current driving. Since Cr2O3 has excellent anti-oxidation and anti-wear properties at high temperatures, its increased concentration further explains the reduced wear tracks and lower friction coefficient observed in the electromagnetic shock treated samples under high-temperature friction conditions.

[0050] This invention addresses the need to improve the comprehensive performance of gear steel under harsh conditions such as high-temperature friction and fatigue. It proposes an electromagnetic shock treatment technology that can rapidly and effectively control phase transformation, grain refinement, and dislocation distribution in gear steel, and to a certain extent, uniformly precipitate carbides. This method can repair micro- and nano-defects generated during processes such as turning or carburizing, alleviate uneven carbide distribution, and improve the wear resistance and fatigue life of the matrix. Its innovation lies in the fact that after macro-scale manufacturing, the local strengthening effect of short-duration, high-density pulsed current achieves the redistribution and repair of the microstructure, thereby breaking through the service performance and life limits of existing aerospace gears.

[0051] In summary, electromagnetic shock treatment can effectively induce microstructure refinement and carbide precipitation in CSS-42L gear steel: when the microstructure is subjected to an electric field, its crystal structure undergoes microscopic changes, and adjacent microstructure fragments randomly orient to suppress grain boundary diffusion. Simultaneously, the high-frequency vibration and bombardment of the electron beam further refines the microstructure. Under the influence of the electric field, carbide precipitation within the microstructure is more uniform, and the high-intensity electric field generated by electromagnetic shock can locally activate ions, electrons, and magnetic microparticles in the steel, accelerating carbide precipitation. Figure 4 XRD characterization results show that carbon atoms in CSS-42L gear steel migrate along the direction of the electric field and precipitate M on the electrode surface. 23 C6 type carbides are used to strengthen the steel.

[0052] Specifically, during the application of an electric field, a potential gradient is generated on the surface of the steel. Because carbon and iron elements in the steel have different charge states, carbon atoms move towards the electrode surface under the influence of the electric field, while iron atoms move towards the interior of the material. This process makes it easier for carbon atoms to accumulate near the electrode, further promoting carbide precipitation. One reason for the increased hardness of the EST sample is the combined effect of microstructure refinement and carbide precipitation: since the hardness of carbide precipitation on the surface is much higher than that of the matrix, the surface carbide precipitation density affects wear resistance to a certain extent. Within a certain range, the higher the precipitation density, the lower the wear rate and the better the wear resistance. Simultaneously, the microstructure refinement of CSS-42L gear steel can improve its hardness, making it more able to withstand high-speed friction and loads. Carbide precipitation can also further enhance hardness and wear resistance, preventing surface cracks caused by prolonged wear. In addition, current has a gain effect in reducing residual stress and can play a certain lubricating role. High-density current can improve micro-inhomogeneity on the basis of ultrasonic impact surface strengthening, making deformation, phase transformation and internal energy distribution more uniform. By repairing damage defects in situ and specifically enhancing the structure of weak areas, it can solve the problem of controlling matrix micro-nano-scale damage in macro-scale manufacturing, and ultimately further improve the fatigue life of existing aero-engine gears.

[0053] It should be noted that all the above embodiments belong to the same inventive concept, and the descriptions of each embodiment have different focuses. Where the description in a particular embodiment is not detailed, please refer to the description in other embodiments.

[0054] The above embodiments merely illustrate implementation methods of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this invention patent should be determined by the appended claims.

Claims

1. A method for efficiently regulating the performance of aero-engine gear steel by electromagnetic impact treatment, characterized in that, The method comprises: S10, providing an electromagnetic impact treatment device, the electromagnetic impact treatment device comprising a primary circuit and a secondary circuit electromagnetically coupled with the primary circuit, the primary circuit being used for inputting electric energy and generating a changing magnetic field, and the secondary circuit being used for inducing the changing magnetic field and generating a pulse current; S20, fixing an aero-engine gear steel into the secondary circuit and realizing conduction of the aero-engine gear steel and the secondary circuit; S30, turning on an alternating current power supply of the primary circuit to perform electromagnetic impact treatment on the aero-engine gear steel to obtain a treated gear steel component; the peak current of the electromagnetic impact treatment is 10-5000 A, and the electromagnetic impact treatment time is 0.01-1 s.

2. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 1, characterized in that, In the S10 step: the primary circuit comprises the alternating current power supply, an excitation circuit and a converter which are electrically connected in sequence, and the secondary circuit comprises the converter and an oscilloscope which are electrically connected in sequence; the secondary circuit is electromagnetically coupled with the primary circuit through the converter.

3. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 2, characterized in that, The converter comprises a conversion body, a primary induction coil and a secondary induction coil, and the conversion body comprises oppositely arranged first and second winding parts; wherein the primary induction coil is wound on the first winding part, and the secondary induction coil is wound on the second winding part.

4. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 3, characterized in that, The S20 step specifically comprises: S201, clamping the aero-engine gear steel between a first electrode and a second electrode, and ensuring that the aero-engine gear steel is flat with the contact surfaces of the first electrode and the second electrode, respectively; S202, electrically connecting the first electrode with the oscilloscope, and electrically connecting the second electrode with the second winding part.

5. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 4, characterized in that, The S30 step further comprises: monitoring the temperature of the contact position of the aero-engine gear steel with the first electrode and the second electrode in real time, and monitoring the current density flowing through the aero-engine gear steel in real time when the electromagnetic impact treatment is performed.

6. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 4, characterized in that, The aero-engine gear steel is CSS-42L gear steel; and the materials of the first electrode and the second electrode are both copper.

7. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 6, characterized in that, In the S30 step, the pulse width of the electromagnetic impact treatment is 0.01 s, and the pulse period is 1-10 s.

8. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 7, characterized in that, The friction coefficient of the treated gear steel component in a 500℃ environment is lower than that of the aero-engine gear steel in a 500℃ environment.

9. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 7, characterized in that, The dislocation density of the treated gear steel component is lower than that of the aero-engine gear steel.

10. The electromagnetic impact treatment method for efficiently regulating the properties of aeroengine gear steel according to claim 7, characterized in that, The S30 step is performed by the electromagnetic impact treatment, and the treated gear steel member precipitates M 23 C6-type carbide.

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