565 results about "Shot peening" patented technology

The invention belongs to the application of a computer technology in the field of shot blasting processing, and discloses a shot blasting strength calculation method and system based on control parameters of intelligent shot blasting equipment. According to the method, an intelligent calculation method system is constructed by establishing a prediction model of the control parameters and the shot blasting strength. According to the method, nozzle pressure, moving speed, spraying angle, shot flow and target distance parameters of shot blasting equipment are collected in real time, workpiece material attribute data are combined, a multi-dimensional data fitting algorithm is adopted for processing, and an accurate shot blasting strength value is output. Meanwhile, a self-adaptive parameter adjusting module is developed, and dynamic calculation optimization can be carried out according to residual stress field distribution and coverage rate requirements. Compared with a traditional Almen test piece method, the method achieves real-time calculation of shot blasting strength and closed-loop control of technological parameters, the calculation error rate is reduced to be within 5%, test piece consumption is reduced by 80% or above, machining efficiency and quality stability are remarkably improved, and an innovative solution is provided for intelligent manufacturing in the field of surface strengthening.

The invention discloses a method for improving the high-cycle fatigue performance of a Ti6Al4V titanium alloy, and belongs to the technical field of metal material processing, and the method comprises the following steps: S1, determining shot peening strengthening parameters based on material performance parameters and related standards; according to the method, high-amplitude residual compressive stress is introduced through shot peening strengthening, the stress state of the surface and the depth direction of the material is changed, accordingly, crack extension can be restrained, the fatigue life is prolonged, in addition, a plastic deformation layer is induced to be generated under the surface depth in the shot peening process, the microstructure of the material is improved, and the anti-fatigue performance of the material is improved; through femtosecond laser shock, surface defects can be effectively removed, the surface compactness can be improved, microcracks can be reduced, and a refined grain structure can be generated, so that the strength and toughness of the material are further enhanced, the high-cycle fatigue performance of the material is further improved, the two are combined, the residual stress state is optimized, and the surface integrity is improved. The fatigue performance of the Ti6Al4V titanium alloy is remarkably improved.

The invention belongs to the technical field of metal part surface modification, and relates to a composite strengthening method for a carburized surface of a high-bearing gear of an aero-engine. According to the method, high-hardness and high-density ceramic shots are adopted as media for high-energy mechanical shot peening strengthening, the advantage that the subsurface strain hardening effect of the contact strengthening technology is good and the barb-shaped distribution characteristic of mechanical shot peening residual compressive stress are utilized, extremely high residual compressive stress is introduced to the subsurface position, and the contact fatigue performance of the tooth surface of the gear is improved. High-frequency laser shot peening strengthening is used for secondary treatment, so that the surface layer of the material is subjected to plastic deformation, high-amplitude residual compressive stress is introduced into the surface layer of the material within the depth range of more than 500 microns by utilizing the advantage of large influence depth of laser-induced shock waves, and the residual compressive stress can inhibit fatigue crack initiation, has a certain depth and inhibits fatigue crack propagation; and the bending fatigue resistance of the root of the gear can be effectively improved. And an abrasive flow process is adopted, so that the roughness is reduced to be more than 0.4 mu m.

The present invention relates to a heat treatment method for a high-strength, tough, lightweight, wear-resistant high-manganese steel casting, and the steps are as follows: pretreatment: coating an anti-oxidation protective coating on the surface of the high-manganese steel casting; water toughening treatment: heating the high-manganese steel casting to the water toughening temperature at a preset speed, keeping the temperature and then water quenching; cryogenic treatment: cooling the high-manganese steel casting after water toughening to the cryogenic treatment temperature and keeping the temperature; aging treatment: heating the high-manganese steel casting after cryogenic treatment to the aging temperature and keeping the temperature, keeping the temperature, and then air cooling to room temperature, and the interval between cryogenic treatment and aging treatment is not more than 1h; shot peening treatment: shot peening treatment is performed on the surface of the high-manganese steel casting after aging treatment. The present invention utilizes a combination of water toughening, cryogenic treatment and aging treatment to obtain a single austenite structure, obtain an effective dispersed nano-scale carbide structure, and effectively improve the grain refinement and solid solution strengthening effect of the high-strength, tough, lightweight high-manganese steel.

The invention discloses a TiAl alloy electron beam selective melting and shot peening strengthening in-situ compounding manufacturing method and device, and relates to the technical field of additive manufacturing. The method comprises the following steps: establishing a three-dimensional digital model of a to-be-printed part, and performing slicing and layering to obtain layered scanning data; under the vacuum condition, TiAl alloy powder is spread on the preheated base plate according to the set thickness, and a powder bed is formed; according to the layered scanning data, scanning and melting the powder bed through a focused electron beam, completing single-layer scanning and melting, completing scanning and melting layer by layer until the part is printed and cooled, and recovering unmelted TiAl alloy powder; and under the vacuum condition, the surface of the printed part is scanned and heated through a defocusing electron beam, TiAl alloy powder is adopted as shot blasting powder, the surface of the heated part is subjected to microparticle shot blasting strengthening treatment, after the treatment is finished, cooling is conducted, scattered shot blasting powder is recycled, and the finished TiAl alloy part is obtained. By means of the collaborative process design of electron beam selective melting and in-situ high-temperature microparticle shot blasting and device integration, the problems that in TiAl alloy additive manufacturing, cracking is prone to occurring, and the strengthening effect is poor are solved.

The invention provides a typical component shot peening strengthening process design method. The typical component shot peening strengthening process design method mainly comprises the steps that 1, typical component shot peening strengthening parameter design technical requirements are determined; 2, a reasonable shot blasting material is selected based on typical component technical requirements; 3, establishing a shot blasting process parameter optimization model based on the neural network; and 4, optimizing and solving shot blasting process parameters on the basis of the surface strengthening requirements of the part. The method is suitable for shot peening strengthening process design with the purpose of improving fatigue strength and stress corrosion breaking strength of typical components, and other parts can be used for reference.

The invention relates to the technical field of residual stress regulation and control of castings, in particular to a device and a method for regulating and controlling residual stress of a casting after heat treatment. In order to solve the problem that a common method for regulating and controlling the residual stress of the casting after heat treatment is poor in regulating and controlling effect on a stress concentration area or internal residual stress of the casting, the invention provides a device and a method for regulating and controlling the residual stress of the casting after heat treatment. The vibration aging mechanism comprises a vibration reduction platform, an elastic cushion and a vibration exciter, and the elastic cushion is fixed to the upper surface of the vibration reduction platform; the shot peening strengthening mechanism comprises two linear modules, two six-axis mechanical arms and two shot peening assemblies, the two six-axis mechanical arms are fixed to the two linear modules correspondingly, each shot peening assembly comprises a shot peening pipe, and the shot peening pipes are fixed to the tail ends of the six-axis mechanical arms. During use, the vibration aging mechanism and the shot peening strengthening mechanism are used for carrying out synchronous coupling regulation and control on the casting. The regulation and control device is simple in structure and convenient to operate.

The invention provides a method for automatically detecting the coverage rate of a blade part after shot blasting, which realizes objective evaluation and screening of the surface coverage rate of the part based on an intelligent platform, and comprises the following steps: S1, establishing a database for comparison through sample coverage rate calibration; s2, performing shot blasting treatment on the part to form a to-be-detected surface; s3, the part subjected to shot blasting treatment is fixedly arranged in a designated area and transferred to a detection platform; s4, carrying out image acquisition on the shot blasting area of the part by adopting intelligent visual equipment; s5, comparing the acquired image with a calibration picture in a database through image analysis software, and judging a coverage rate value of the part; and S6, re-checking and post-processing the judgment result, and screening out qualified parts. According to the method, the roughness of parts such as blades after shot blasting can be quantitatively detected, and the coverage condition of the parts after surface treatment can be more objectively judged; the detection efficiency can be improved, and the problem of missing detection can be effectively avoided.

The invention relates to an aviation titanium alloy laser shock peening and mechanical shot peening composite process strengthening method. The method comprises the following steps: cutting an aviation titanium alloy material into a plurality of square blocks and tensile fatigue parts by using a wire cutting machine; grinding with abrasive paper, and then polishing with a polishing agent, so that the surface of the aviation titanium alloy test material is smooth; carrying out laser shock peening treatment on one part of the aviation titanium alloy test material subjected to surface treatment; performing various detections on the aviation titanium alloy test material subjected to the same parameter and different impact strengthening times; the method comprises the following steps: carrying out mechanical shot blasting on an aviation titanium alloy sample with the best detection effect, carrying out mechanical shot blasting on part of original samples, then carrying out laser shock peening, and comparing the mechanical properties of the materials subjected to shock peening in different modes to obtain an optimal result. According to the method, two processes of mechanical shot peening and laser shock peening are combined, so that the fatigue resistance, the damage resistance and the stress corrosion resistance of the material are improved.

The invention provides a shot peening process parameter optimization and generation method and device, equipment and a storage medium. The shot peening process parameter optimization method of a thin-wall component comprises the steps that initial state data of the thin-wall component is obtained; generating a multilayer constitutive model; initial shot blasting process parameters are obtained; a geometric model after shot blasting and residual stress distribution data after shot blasting are predicted through shot blasting simulation; shot blasting forming efficiency is obtained according to the initial shot blasting process parameters; the residual stress gradient uniformity is obtained according to the residual stress distribution data after shot blasting; and optimal shot blasting process parameters are obtained through multi-objective optimization. According to the shot peening process parameter optimization and generation method and device, the equipment and the storage medium, the shot peening forming efficiency and the stress distribution uniformity can be both considered.

The invention relates to the technical field of shot blasting protection, in particular to an aperture-adjustable shot blasting modular protection device and method, which comprises a double-end threaded pull rod, a variable-diameter supporting mechanism positioned on the double-end threaded pull rod, blocking pieces positioned at two ends of the variable-diameter supporting mechanism, and an adjusting piece in threaded connection with the double-end threaded pull rod, the variable-diameter supporting mechanism is used for supporting the inner wall of a hole, and rotation of the adjusting piece is used for adjusting the supporting range of the variable-diameter supporting mechanism. The blocking pieces are detachably connected to the two ends of the variable-diameter supporting mechanism and used for blocking the opening portion of the hole. The variable-diameter supporting mechanism is driven by the adjusting piece to adapt to different hole diameters, various hole types are compatible and adapted, the universality of the protection equipment is greatly improved, and the cost is reduced; disassembly and assembly are convenient and efficient, shot blasting operation auxiliary time is shortened, and machining efficiency is improved; the modular design facilitates independent replacement of damaged parts, the maintenance cost is reduced, and the service life of the device is prolonged.

The invention provides a shot peening inherent strain reverse calculation method and system based on unequal-thickness thin plates. The method comprises the steps that unequal-thickness calibration samples are prepared; technological parameters to be calibrated are selected, and shot blasting is conducted on the calibration sample; measuring the profile of the center line of the shot-blasted surface of the calibration sample after shot blasting; calculating the surface ductility and the bending curvature according to the contour of the center line of the sample; based on the surface ductility and the bending curvature, the inherent strain corresponding to the to-be-calibrated process parameters is reversely solved. According to the method, the inherent strain is reversely solved based on the multi-deformation geometric parameters, compared with an inherent strain reverse solving method based on residual stress, the reverse solving efficiency is higher, the robustness and the accuracy are better, and meanwhile the problem that the inherent strain is reversely solved based on a single deformation parameter is uncertain is solved; and a method support is provided for construction of a shot blasting inherent strain process database.

The invention belongs to the technical field of metal material mechanical property research, and discloses a gear shot peening tooth surface residual stress calculation method and system.The method comprises the steps that a shot speed calculation model in the gear shot peening process is built, shot peening process analog simulation is carried out, and dynamic information of collision between shots and a tooth surface is output; the projectile speed is converted from a machine tool coordinate system to a local coordinate system; establishing a sprayed target plate model and a projectile model, dividing grids, and assembling the grid-divided projectile model and the sprayed target plate model to construct a random multi-shot finite element geometric model; and performing finite element simulation calculation on the random multi-shot finite element geometric model, and outputting residual stress distribution of the gear. According to the method, computational fluid mechanics and a discrete element method are coupled, a high-precision calculation model of the shot speed in the gear shot blasting process is constructed, the forming mechanism and distribution characteristics of the tooth surface residual stress in the actual shot blasting process are effectively reflected, and the method is good in economical efficiency, high in simulation precision, high in process executability and closer to engineering practice.

The invention provides a method for composite manufacturing of a ribbed wallboard structure through friction stir solid phase additive and needleless friction stir, which comprises the following steps: firstly, manufacturing a reinforcing rib structure on a substrate layer by layer through a friction stir additive manufacturing process, and meanwhile, carrying out friction stir treatment on a deposition layer by using a needleless stirring head; therefore, the reinforcing rib generates plastic deformation at the recrystallization temperature, the reinforcing rib and the matrix structure are combined more tightly, meanwhile, the surface roughness of the reinforcing rib is further reduced through needle-free stirring, grains are refined, and the overall strength of the reinforcing rib is improved. And finally integrally forming the part through a shot blasting forming process. According to the method, the problems that a reinforcing rib structure made of dissimilar materials cannot be manufactured through a traditional method, and a ribbed integral wallboard is difficult to integrally form are solved, redundant machining is avoided, the forming cost of the ribbed wallboard structure is reduced, meanwhile, the bonding strength between the reinforcing rib and a base body is further improved through needle-free stirring, and the production efficiency is improved. And the performance of the wallboard structure can be better improved.

The invention belongs to the technical field of machining and manufacturing, and relates to a repairing method suitable for a pit defect of a hammer anvil and application of the repairing method. The method specifically comprises the following steps that S1, shot blasting is conducted on the surface with the pit defect needing to be repaired; s2, measuring the size of the surface which needs to be repaired and has the pit defect; s3, a steel plate suitable for the pit defect surface is prepared; s4, a steel plate is welded to the surface of the pit to be repaired; s5, filling powder into a closed space formed by the steel plate and the surface of the pit defect; S6, sealing and welding by using a sealing cover after the powder filling is completed; s7, carrying out hot isostatic pressing; and S8, the repaired surface is milled and flattened. And the hammer anvil with large defects can also be repaired, machining treatment is not needed, the repairing rate is high, the repairing cost is low, time and labor are saved, and economic waste is avoided.

The present invention relates to a method for siliconizing on the surface of a copper alloy, comprising the following steps: shot peening is performed on the copper alloy to be treated; wherein the shot peening used for the shot peening is composed of a first tungsten ball with a diameter of 5mm, a second tungsten ball with a diameter of 4mm, a third tungsten ball with a diameter of 3mm, and a fourth tungsten ball with a diameter of 2mm; the time of the shot peening is 1-3h; the treated copper alloy is placed in a loading boat, and a siliconizing agent is filled in the loading boat so that the copper alloy is completely covered by the siliconizing agent; the loading boat is then placed in an atmosphere furnace, a mixed gas of silane and hydrogen is continuously passed into the atmosphere furnace, after the temperature is raised to 380-420°C, the temperature is kept for 5-8h, and the furnace is cooled and discharged. The method of the present invention can effectively improve the wear resistance of the copper alloy, improve the service life of the copper alloy, and the siliconizing process of the present invention can be carried out under low temperature conditions, without worrying about causing the copper alloy to anneal and soften while siliconizing.

The invention discloses a metal dust processing cyclone type wet dust collector and an intelligent control system thereof. The cyclone type wet dust collector for metal dust processing comprises a box body, a multi-stage filtering device, a dust recovery device and an intelligent control device, the box body is provided with an exhaust inlet and an air outlet; a multi-stage filtering device is arranged in the box body and comprises a water curtain filtering area, a spraying pressing area and a water mist separation area which are arranged in sequence; the dust recovery device comprises a sewage treatment tank and an air locking and dust discharging device which are arranged at the bottom of the box body; the intelligent control device is used for monitoring water level, water flow, water pressure, temperature and air pressure difference parameters and automatically controlling the operation state of the system according to monitoring results. The intelligent control system is applied to the dust remover. The dust removal device has the following beneficial effects that through multi-stage filtration and intelligent control, the problems of low efficiency, poor safety, difficulty in maintenance and low automation degree when existing dust removal equipment is used for treating sand blasting and shot blasting dust are solved.

The invention discloses a welding repair method for cracks of a main frame of a 20Mn5 cast steel cone crusher, which comprises the following steps of: cleaning rust, dirt and oil dirt, punching a 65-80-degree double-groove and removing an oxide layer, using a high-strength and high-plasticity welding material and a direct-current welding machine, performing direct-current reverse connection, controlling the welding current to be 82.5-87.5 A and the electric arc length to be 1.2-1.8 mm, adopting a multi-layer welding mode, performing linear reciprocating operation on a first layer of welding bead, and performing welding on a second layer of welding bead and a third layer of welding bead, so as to repair the cracks of the main frame of the 20Mn5 cast steel cone crusher. And after the five layers of welding beads are welded, welding sine curves to strengthen the welding beads by taking a connecting line between the starting point and the ending point of the welding seam as a central line, preheating at 275-295 DEG C before welding, preserving heat at 210-230 DEG C for about 1.5 hours after welding, and carrying out shot peening hardening on ceramic shots of an ultrasonic flaw detector and the welding seam. According to the method, a high-strength and high-plasticity welding material and proper temperature control conditions are selected and used, welding cracks and welding deformation are effectively prevented, the tensile strength of a welding seam reaches 890 MPa and is higher than the tensile ultimate strength 785 MPa of 20Mn5, and welding repair of cracks of the main rack of the 20Mn5 cast steel cone crusher is met.

The invention relates to the technical field of metal material strengthening treatment, in particular to a micropitting-resistant wind driven generator gear carburizing and quenching composite strengthening process which comprises the following steps: S1, gear blank pretreatment and surface activation; s2, gradient carburizing strengthening treatment; s3, grain refinement annealing treatment; s4, step quenching strengthening treatment; s5, performing deep cooling and thermal cycle treatment; s6, directional tempering regulation and control treatment; s7, composite shot peening strengthening treatment is conducted; and S8, an antifriction composite film layer is deposited on the surface of the gear subjected to shot peening strengthening in the S7. According to the method, through a synergistic strengthening mechanism of gradient carburization, step quenching, structure regulation and control and surface functionalization, the residual stress distribution and tribological performance are optimized while the high surface hardness of the gear is kept, and the technical problems that in a traditional technology, the carburized layer is concentrated in stress, uneven in structure, single in surface performance and the like are solved.

The invention discloses a method, a device, equipment, a medium and a product for determining a shot peening forming process scheme, and the method comprises the following steps: constructing a geometric part digital model for a target part, applying a corresponding equivalent heat source model to the geometric part digital model at a shot peening path of a current scheme, and carrying out reverse simulation deformation calculation based on a material shrinkage parameter, obtaining a plate part mathematical model; calculating the weight of each node of the digital model based on the part thickness information and the flatness index value of the flat plate part digital model, and returning to the operation of obtaining the current scheme until all the schemes are processed; and according to the flatness index values, a target shot peening forming process scheme is obtained. Starting from the shape of the target part, reverse calculation is carried out through the equivalent heat source model and the shrinkage parameters, and the digital model of the flat plate part can be generated more accurately. Through the flatness judgment method of the weight of the part thickness information, all the process schemes are sequentially processed, the simulation result can be quantitatively evaluated, and the accuracy and reliability of shot peening forming process scheme selection are improved.

The invention relates to the technical field of aero-engine titanium alloy rotor blade repair, in particular to a stress regulation and control method for improving fatigue strength of a titanium alloy rotor blade after welding repair, which comprises the following steps: vacuum heat treatment, self-adaptive machining, first vibration finishing, laser shock peening, shot peening and second vibration finishing. Performing vacuum heat treatment on the blade subjected to electron beam welding repair; a machining program is compiled, machining is conducted on the patch repairing area, and the blade with the profile size meeting the use requirement is obtained; and after the first time of vibration finishing, laser strengthening equipment is used for carrying out laser strengthening on the blade area needing to be strengthened, shot blasting is carried out, then second time of vibration finishing is carried out, and the stress regulation and control method is completed. The vibration fatigue strength of the repaired blade is improved by 30% compared with that of a welding heating treatment process, the service life of the blade is effectively prolonged, the use performance requirement of parts is met, the maintenance and part replacement cost of an aero-engine is reduced, and the method has large economic benefits.

The invention relates to a shot peening method for strengthening the mechanical property of a laser additive manufacturing titanium-based composite material, which comprises the following steps of: performing single-pass shot peening on the surface of the titanium-based composite material under the conditions that the air pressure is 0.1-0.25 MPa and the shot peening time is 3-10 minutes, and removing residual shots on the surface of the titanium-based composite material after the shot peening is finished, the tensile strength of the reinforced titanium-based composite material at the room temperature is improved by 50-100 MPa from 1152.76 MPa in an initial printing state. According to the shot blasting treatment provided by the invention, residual compressive stress is introduced by bombarding the metal surface through small particles, the surface structure is subjected to plastic deformation, grains on the outermost surface are remarkably refined, and the mechanical property of the titanium-based composite material manufactured by laser additive manufacturing is effectively improved at low cost.

The invention discloses an electromagnetic-coupling-assisted aero-engine single-crystal blade additive manufacturing repairing method, and belongs to the technical field of aero-engine turbine blade repairing. The method comprises the steps that pretreatment and first electromagnetic coupling treatment are conducted on a to-be-repaired area of a blade; repairing a to-be-repaired area of the blade by adopting laser additive manufacturing and carrying out secondary electromagnetic coupling treatment; strengthening a blade repair area by adopting a shot blasting technology; and machining treatment and third electromagnetic coupling treatment are conducted on the blade repairing area. According to the method, the nickel-based single-crystal high-temperature alloy blade is repaired by combining electromagnetic coupling treatment and the additive manufacturing technology, on the premise that the size precision of the blade is not changed, residual stress generated in all links in the additive manufacturing repairing process of the nickel-based single-crystal turbine blade is effectively reduced, microstructure defects generated in the additive manufacturing process are repaired, and the quality of the blade is improved. And meanwhile, the service life of the repaired blade is prolonged through shot peening strengthening, and the whole treatment process is green and low in consumption.

The invention provides a shot blasting method for strengthening the surface of a gear. The shot blasting method mainly comprises the following steps: step 1, determining basic parameters of a gear material and dividing a blasted material area; 2, calculating the shot blasting surface coverage rate based on shot blasting parameters such as the shot size, the crater diameter and the shot number; step 3, randomly generating and calculating the spatial position of the multi-shot peening shot; and 4, shot peening strengthening parameter design with the gear surface roughness and the residual compressive stress as targets is carried out. According to the method, the gear roughness and residual stress calculation method is combined, the influence of various shot blasting parameters on the surface strengthening integrity of the gear is analyzed, the tooth surface performance of the gear is improved, and the fatigue life of the gear is prolonged.

The invention belongs to a part surface treatment technology, and relates to an actuator cylinder inner surface ultrasonic impact strengthening device and a use method thereof. Comprising an actuator cylinder upper cover plate (1), an actuator cylinder supporting table (2), an ultrasonic vibration head fastening screw (3), an ultrasonic impact device, an ultrasonic vibration head supporting platform (6), an ultrasonic working rotary table (8), a vertical lifting working table (9) and an ultrasonic strengthening working table base (10). According to the method, only a small amount of shots are consumed and are far less than traditional shot peening strengthening, the machining cost is lower, the dust amount is smaller, and noise is lower. In the strengthening process, a tool and actuator cylinder parts do not need to be moved, all the inner surfaces of the actuator cylinders are strengthened only through rotation of the ultrasonic working rotary table and lifting of the vertical lifting working table, high positioning precision is achieved, and the machining efficiency is remarkably improved.

The invention belongs to the technical field of shot peening forming of aircraft wing wallboards, and particularly relates to a non-ribbed wing wallboard torsion appearance shot peening forming method which comprises the following steps: step 1, carrying out spanwise pre-bending clamping on a torsion appearance area; secondly, chordwise shot peening forming is conducted on the outer surface of the torsion shape area; thirdly, spanwise shot peening forming is conducted on the inner surface of the torsion shape area; fourthly, torsion shape pre-bending clamping is conducted on the torsion shape area; and 5, equal-pressure opposite spraying is conducted on the inner surface and the outer surface of the torsion shape area.

The invention discloses a quality prediction method and system in the shot blasting treatment process of a brake drum, and relates to the technical field of data processing, and the method comprises the steps: obtaining a to-be-treated area and a qualified coverage rate threshold value, obtaining a shot launching number, obtaining a shot blasting time period, and obtaining shot blasting starting time and shot blasting ending time; acquiring a real-time surface image of the surface to be subjected to shot blasting treatment of the brake drum in the shot blasting treatment process, and acquiring a real-time coverage rate according to the real-time surface image; judging whether the real-time coverage rate is smaller than a qualified coverage rate threshold, if so, obtaining a first quality prediction result according to the real-time coverage rate, and if not, obtaining a coverage rate difference value between the qualified coverage rate threshold and the real-time coverage rate; and obtaining a change weight based on the coverage rate degree change model and the coverage rate difference value, and obtaining a second quality prediction result according to the change weight, the shot peening treatment time, the real-time coverage rate and the shot peening end time. The method has the advantages of high prediction efficiency, dynamic prediction, accuracy and reliability.

The invention provides a spiral bevel gear composite shot blasting process parameter optimization method and optimization system based on discrete element-finite element analysis, and relates to the technical field of gear parameter optimizing.The method comprises the specific steps that process parameters are generated through random combination and input into a model for simulation; acquiring residual stress distribution, stress gradient and crack characteristic data of the spiral bevel gear; constructing a parameter prediction model, and training the model by using a simulation result; inputting an initial parameter to obtain a performance index; calculating a stress uniformity coefficient and a crack risk coefficient, and generating a comprehensive evaluation coefficient through correlation analysis to evaluate the surface quality of the gear; and with maximization of the comprehensive evaluation coefficient as a target, iterative optimization is carried out on the parameters by using a genetic algorithm, and optimal process parameters are extracted. According to the method, the interaction effect between the composite shot blasting process parameters can be comprehensively considered, then the composite shot blasting process parameters can be optimized, it is ensured that the performance of the spiral bevel gear is optimal in use, and the failure risk is reduced.

The invention discloses a surface strengthening process capable of improving the high-cycle fatigue performance of a TiAl alloy casting, which is characterized by comprising the following steps of: 1, carrying out sand blasting treatment on the casting with the mesh number of 40-120; secondly, dirt on the surface of the casting obtained in the first step is removed; and thirdly, shot blasting treatment is conducted on the casting obtained in the second step, and the shot blasting strength ranges from 0.1 mmN to 0.3 mmN. In the first step, the fatigue strength of the casting after sand blasting can reach the level of a standard smooth sample by reasonably selecting the mesh number of sand blasting sand, and then in the second step, the fatigue strength of the casting after sand blasting and shot blasting can be remarkably improved compared with that of the standard smooth sample by reasonably selecting the shot blasting strength. The surface strengthening process disclosed by the invention is simple, short in flow, low in requirements on production equipment and simple and convenient to operate, can be applied to high-temperature rotating parts such as aero-engine low-pressure turbine blades and automobile engine impellers, and has great application and popularization values.

A machining method for improving residual compressive stress of a raceway surface of a bearing ring relates to the technical field of bearing machining and comprises the following steps: turning a bearing ring blank, and then quenching and tempering a machined part; the surface of the ferrule raceway subjected to heat treatment is subjected to shot blasting machining strengthening; carrying out primary grinding processing on the surface of the reinforced ring raceway, and then carrying out additional tempering treatment; the surface of the ring raceway is subjected to fine grinding, and then the surface of the ring raceway is subjected to final grinding; and carrying out superfinishing on the surface of the ring raceway. According to the method, a machining procedure mutual matching strategy is adopted, the machining technological process is optimized, machining parameters of all procedures are strictly controlled in the machining process, through progressive machining of all the procedures, the surface residual compressive stress of the bearing ring raceway is gradually increased, good control over the residual compressive stress scattering difference is achieved, and the fatigue life of the bearing can be effectively prolonged. The residual compressive stress on the surface of the bearing ring raceway machined through the method is not smaller than 515 MPa, and the residual compressive stress range is not larger than 68 MPa.