44results about How to "Guaranteed contour" patented technology

The invention provides a cartridge receiver welding method. The cartridge receiver welding method includes the following steps that during installation, it is guaranteed that an upper installation side and a lower installation side are higher than the wall of a cartridge receiver by 0-0.2 mm; manual argon arc welding positioning welding is conducted, and weld joint rolling and profile correction are conducted by a bench worker; through automatic argon arc welding and weld joint rolling and profile correction which are conducted by the bench worker, punching is conducted at the positions, to be welded and corresponding to twelve bosses, of the wall of the cartridge receiver through laser cutting; manual argon arc welding positioning welding is conducted on the twelve bosses, weld joints are leveled by the bench worker, and it is guaranteed that the bosses at the butt joint positions are higher than the wall of the cartridge receiver by 0-0.2 mm; manual argon arc welding is conducted on the twelve bosses; weld joints are leveled by the bench worker, the profile tolerance of a part is corrected, and it is guaranteed that gaps between the part and a model is not larger than 0.5 mm; welding of the cartridge receiver is completed. According to the cartridge receiver welding method, welding deformation can be well controlled, and therefore it is guaranteed that the size and the profile tolerance of the finished cartridge receiver meet requirements. The invention further provides a special clamp applied to the welding method.

The invention belongs to machining technologies of blades of aircraft engine gas compressors, and provides a method for machining an arc-tooth tenon blade of an aircraft engine gas compressor. The method includes the steps that a blade blank with a root process boss and a blade tip process boss is clamped to a numerical control milling machine, and rough milling is conducted on the intake side and the exhaust side of the blade; the blade subjected to the rough milling is clamped in a positioning casting fixture and cast through low-melting-point alloy, and the outline of the cast blade is a cuboid; rough milling is conducted on the cuboid blade obtained after being clamped and cast on the numerical control milling machine so that a tenon and a margin plate can be formed at the root of the blade, and the blade root process boss is removed; the tenon is subjected to finish grinding on a six-axis creep-feed grinding center to be in an arc-tooth shape; the cuboid blade is placed into a melting furnace and heated to be 180 DEG C, and is taken out after the low-melting-point alloy melts; finish grinding is conducted on the intake side and the exhaust side on a numerical control abrasive belt grinding machine by using the tenon for positioning and clamping; and the blade tip is machined on a numerical control linear cutting machine by using the tenon for positioning and clamping, and the blade tip process boss is removed.

A combined grinder with multiple grinding heads for grinding the straight rolling track and slide block on the track is composed of a machine body, two vertical columns, a transverse beam installed to said vertical columns, a tool carriage on said transverse beam, 2-4 grinding heads (including vertical and horizontal grinding heads), and an abrasive disc repairing device.

The invention discloses a method for machining a molded line of a scroll plate, and relates to the technical field of mechanical machining. The scroll plate is provided with an end plate and a scroll wall thereon, wherein an annular groove is formed in the periphery of the end plate; and a positioning hole is formed in the lower end face of the end plate. According to the method, a clamp for machining the molded line of the scroll plate is fixedly arranged on a workbench of a vertical machining center; the scroll plate is fixed on the clamp for machining the molded line of the scroll plate by a spring check ring; according to rough machining and semifinishing, a cutter feeding instruction of a cutter is set into fifth-degree step lengths; and according to finish machining, a cutter feeding instruction of the cutter is set into first-degree step lengths. Compared with the prior art, the method has the advantages that the cutter feeding instruction of the cutter is set from large to small, the machining accuracy is improved gradually, and machining equipment and the cutter are used reasonably while the machining accuracy of the molded line is ensured, so that the efficiency of machining the molded line is improved.

The invention discloses a machining method of a thin-wall abnormally-shaped metal casting. By the adoption of the machining method of the thin-wall abnormally-shaped metal casting, the whole thin-wallabnormally-shaped metal casting is cast and formed, and then machining operation of the appearance outline, the end and inner cavity installation parts of a casting blank is conducted according to the follow-up steps. The corresponding machining allowances are reserved in the rough machining process, the semi-finishing process and the finish machining process of the machining process, the machining standard is timely adjusted according to the wall thickness uniformity degree each time machining operation is accomplished, and the material object correction of the machining standard is accomplished on a machine tool through re-machining operation of a technological pin hole, and therefore the accumulative error, caused by the micro deviation, of the follow-up machining operation can be eliminated as much as possible in the machining process of the large-size thin-wall abnormally-shaped metal casting, the outline degree of the appearance outline can be guaranteed under the condition thatthe situation that the end and the inner cavity installation parts are machined in place is guaranteed, and the uniformity of the wall thickness can also be guaranteed.

The invention discloses a flexible curved surface display screen and a preparation method thereof. The flexible curved surface display screen is provided with a plane area and a curved surface area connected to the plane area; the flexible curved surface display screen comprises a flexible display panel, a supporting gasket and a flexible filling piece, wherein the flexible display panel extends from the plane area and is bent to the curved surface area; the supporting gasket is attached to and supported on the back of the flexible display panel and extends from the plane area to the curved surface area; and the flexible filling piece is arranged in the curved surface area and is filled between the supporting gasket and the flexible display panel, so that the flexible display panel is supported by the supporting gasket. A groove is formed in the surface of the side, facing the flexible display panel, of the supporting gasket, the groove is filled with foam rubber to form a flexible filling piece, an arc-shaped surface is formed on the flexible filling piece, and the arc-shaped surface is perfectly attached to the back of the flexible display panel. The foam rubber can be compressed, so that the profile tolerance zone of the supporting gasket can be ensured, and when the flexible display panel is bent, the flexible display panel can be perfectly attached to the supporting gasketduring bending, and the accuracy and precision during bending of the flexible display panel are guaranteed.

The invention belongs to the processing technology of aero-engine compressor blades. The invention provides a method for processing an aero-engine compressor arc-tooth tenon blade, which includes: clamping the blade wool material with a root process boss and a blade tip process boss in a numerical control On the milling machine, carry out rough milling on the air inlet and exhaust sides of the blade; clamp the blade after rough milling in the positioning casting fixture, and pour the blade with low melting point alloy, and the shape of the blade after casting is a cuboid; CNC milling machine Clamp the poured cuboid blade, rough mill the tenon and edge plate at the root of the blade, and remove the technological boss at the root of the blade; finely grind the tenon into an arc tooth shape on the six-axis slow-feed grinding center; place the cuboid blade on the Put it into the melting furnace, heat it to 180°C, and take out the blade after the low-melting point alloy is melted; use the tenon to position and clamp, and finely grind the intake side and exhaust side on the CNC abrasive belt grinder; The blade tip is processed on the machine tool, and the process boss is removed.

The invention relates to the technical field of thermal protection materials, in particular to a tool and method for sleeving a rigid thermal protection layer on a non-closed equal-diameter revolvingbody cabin section. The tool comprises a bottom plate, a front extension part, a rear extension part, a plurality of stand columns and at least one sliding die; one end of each stand column is perpendicularly connected to the bottom plate; the front extension part and the rear extension part are installed at the front end and the rear end of the cabin section correspondingly; the sliding dies areinstalled on the stand columns, can move in the axial direction of the stand columns and can be adjusted to a certain degree in the radial direction; the overall profile tolerance of the thermal protection layer can be guaranteed within a certain range, an interference area can be avoided, and therefore the cabin body or the thermal protection layer is prevented from being damaged; and in addition, in the process of sleeving the thermal protection layer, the thermal protection layer can be efficiently and accurately connected to the non-closed equal-diameter revolving body cabin section in a sleeving mode without an additional positioning tool, the structure is simple, and operation is convenient. The method uses the tool for auxiliary installation, is easy and convenient to implement andhigh in operability, and suitable for batch production.

The invention discloses a modeling method for a blade tip process extension section of a rotor blade forging. The modeling method comprises the following steps: 1, analyzing blade body molded line data; 2, calculating a middle arc line; 3, making a trend control line in the blade spreading direction; 4, calculating a mean camber line of the extension section; 5, calculating blade basins and bladeback molded lines of the three control lines of the extension section; And 6, smoothing each section molded line. According to the modeling method for the extension section of the blade body of the precision forging blade without allowance design, the profile tolerance, the torsion angle and the bending of the tip part of the blade and the blade spreading waviness of the whole blade body can be better guaranteed.

The invention relates to a chemical milling method for titanium alloy precisely-forged blades. The chemical milling method comprises the steps that firstly, through measurement and grouping, the placewith the minimum blade thickness difference is protected through an acid-alkali-resistant protective adhesive; and then, each group of the blades are subjected to chemical milling correspondingly, the purpose of uniform margin removal of the blades is effectively achieved, and the profile tolerance and the degree of finish of the blades can meet the technological requirements. Consistency in margin removal is realized, the complex uniform margin removal work after finish forging is ended is avoided, the whole chemical milling protection process and method are simple and easy to control, and the profile tolerance and the degree of finish of the titanium alloy blades are guaranteed.

The invention discloses a Z-axis air cylinder support structure of a three-gantry five-axis linkage numerically-controlled milling machine. The Z-axis air cylinder support structure of the three-gantry five-axis linkage numerically-controlled milling machine comprises a base, gantries mounted on the base, and numerical control systems for driving and controlling the gantries, wherein the base is composed of two machine bodies arranged in parallel to form the X-axis of five-axis linkage; above the machine bodies, the three gantries in a combined moving beam structure are arranged, and a worktable is arranged under the gantries; every gantry is provided with an independent numerical control system, and the altitudes of the same positions of the gantries are identical; every gantry is composed of stand columns in transmission connection with the machine bodies, a beam mounted on the stand columns, a ram in transmission connection with the beam, and a spindle in transmission connection with the ram, a milling head is mounted under the spindle, the beam serves as the Y-axis of five-axis transmission, the ram serves as the Z-axis of five-axis linkage, and a double-support nitrogen balance cylinder is mounted on the ram.

The invention discloses a high-precision three-portal five-axis linkage numerically-controlled milling machine. The high-precision three-portal five-axis linkage numerically-controlled milling machinecomprises a pedestal, portals mounted thereon, and numerical control systems for driving and controlling the portals, wherein the pedestal comprises two sets of machine bodies arranged in parallel, which form an X axis for five-axis linkage; three portals adopting combined moving beam structures are mounted above the machine bodies; a workbench is arranged below the portals; each portal is equipped with an independent numerical control system; the same positions of all the portals have consistent contour points; each portal comprises vertical columns in transmission connection with the machine bodies, a cross beam mounted on the vertical column, a ram in transmission connection with the cross beam, and a main shaft in transmission connection with the ram; the cross beam forms a Y axis forthe five-axis linkage; the ram forms a Z axis for the five-axis linkage; a double-swing milling head is mounted below the main shaft; two rotating shafts are arranged inside the double-swing millinghead, and form a B axis and a C axis for the five-axis linkage respectively.

The invention discloses a method for milling and processing a carbon fiber sacrifice layer of a connecting plane, which is applied to milling and processing the carbon fiber sacrifice layer of a butting plane for connecting a composite material afterbody and a vertical tail of an aircraft. The method comprises the following steps: (1) positioning an assembly part of the front section of the afterbody, i.e., maintaining a product of the front section of the afterbody after assembly, and positioning the front section of the afterbody and an assembly tooling together in a processing area of plane milling equipment; (2) selecting a processing tool for the plane milling, wherein the tool is a disc type milling tool, and is made of hard alloy; (3) determining a processing technology, aligning the tool by the milling equipment, determining the allowance of milling, and determining the feeding direction of the tool processing; (4) determining parameters of the processing technology; (5) milling the butting plane by the milling equipment. The method has the advantages that the contour of the butting plane is checked by a laser tracking instrument; the contour requirement of the connecting plane of the front section of the afterbody and the vertical tail is guaranteed, and the front section of the afterbody and the vertical tail can be smoothly butted.

The invention provides a multifunctional end wall assembly welding tool and welding technology. The multifunctional end wall assembly welding tool comprises embedded iron; supporting beam assemblies are arranged on the embedded iron and used for supporting an end wall; and the tops of the supporting beam assemblies are provided with an outer contour measuring mechanism matched with the end wall, and a welding anti-deformation mechanism which corresponds to the end wall and is used for preventing deformation of the end wall are arranged on the supporting beam assemblies. The multifunctional tool provided by the invention is high in flexibility and adjustability, two procedures are integrally conducted through the tool, manpower and the space are greatly saved, and meanwhile, through the tool, prefabrication deformation prevention can be precisely conducted on the welding deformation position, and the overall outer contour radian can be ensured.

The invention discloses a rotor blade precision forging structure and a preparation method. A reinforcing rib is arranged on the back surface of a homeopathic extending section, the reinforcing rib is used as a support of the homeopathic extending section, and the strength of the homeopathic extending section close to an air inlet and exhaust edge area is improved by utilizing the reinforcing rib, so that the strength of a blade tip homeopathic extending section in the polishing process is ensured; the end surface of one end of the reinforcing rib and the plane where the blade tip section is located are arranged at intervals, so that the influence of the reinforcing rib on the blade tip structure is prevented; meanwhile, the size of the reinforcing rib in the length direction of a rotor blade precision forging body is smaller than the length of the homeopathic extending section, so that the reinforcing rib is prevented from interfering with the air inlet and exhaust edge of the blade tip section, the influence degree of factors such as elastic-plastic deformation of a metal material and residual stress release in the heat treatment process on a blade tip portion is reduced, and the profile tolerance, the torsion angle and the bending of the blade tip section are guaranteed; and the reinforcing rib is designed, so that the air inlet and exhaust edge of the blade tip section is protected in the polishing process, deformation is eliminated, the machining precision is improved, and the machining efficiency is also improved.

The invention discloses a hump stamping device of a hump pipe and a stamping method of the hump stamping device of the hump pipe. The stamping device comprises a hump forming assembly and a hump shaping assembly, wherein the hump forming assembly is used for achieving a hump forming technology, and the hump shaping assembly is used for conducting a hump shaping technology on a formed hump. The stamping method comprises the steps of blanking, circle rolling, welding, grinding and polishing, hump forming, and hump shaping. According to the stamping method, processing and manufacturing are conducted by means of a hardware stamping mould, so that the stamping speed and efficiency are greatly improved, and a product can be produced in 30 seconds; according to the technology (hump stamping device of the hump pipe and the stamping method of the hump stamping device of the hump pipe), due to inner and outer anti-deformation shaping and whole surface contact, the product profile tolerance and the product roundness can be guaranteed; and according to the technology (hump stamping device of the hump pipe and the stamping method of the hump stamping device of the hump pipe), one-time forming can be achieved, so that a product thinning rate is greatly lowered.

The invention discloses a Y-axis mounting structure of a three-gantry five-axis linkage numerically-controlled milling machine. The Y-axis mounting structure of the three-gantry five-axis linkage numerically-controlled milling machine comprises a base, gantries mounted on the base, and numerical control systems for driving and controlling the gantries, wherein the base is composed of two machine bodies arranged in parallel to form the X-axis of five-axis linkage; above the machine bodies, the three gantries are arranged; a worktable is arranged under the gantries, every gantry is provided withan independent numerical control system, and the altitudes of the same positions of the gantries are identical; every gantry is composed of stand columns in transmission connection with the machine bodies, a beam mounted on the stand columns, a ram in transmission connection with the beam, and a spindle in transmission connection with the ram, a milling head is mounted under the spindle, the beamserves as the Y-axis of five-axis linkage, and the ram serves as the Z-axis of five-axis linkage; the front end of every beam is provided with an upper linear rail and a lower linear rail which are arranged in a staggered mode from front to back to disperse bearing force.

The invention provides a clamp for machining a plastic impeller of a water pump for an automobile engine. The clamp comprises a backboard, a tensioner column and a screw, wherein the tensioner column is formed by two or more than two tensioner pieces, and one end of the tensioner column is fixedly connected with the center of one side of the backboard; the other end of the tensioner column is provided with internal threads, and the screw is provided with external threads; and when the screw is turned into the internal threads of the tensioner column through the external threads, the diameter of the tensioner column increases. The clamp provided by the invention can ensure the profile control and the concentricity of the plastic impeller of the water pump for the automobile engine, improves the precision of the outer circle and the tapered surface of the plastic impeller of the water pump for the automobile engine, reduces the runout of the impeller in rotation, and improves the rotation precision of the impeller.

The invention discloses a vertical disc milling cutter device. The vertical disc milling cutter device comprises a cutter handle and a cutter disc, wherein one end of the cutter disc is detachably andfixedly connected with one end of the cutter handle, at least five blade grooves are circumferentially formed in the periphery of the other end of the cutter disc at intervals, a finishing blade is fixedly connected with the interior of at least one blade groove through an adjusting bolt, and rough blades are fixedly connected with the interiors of at least four blade grooves through fixing bolts. According to the vertical disc milling cutter device, the machining effect of a combined surface of a cylinder body and a top cover is improved.

The invention discloses a reinforcing fiber soft mold forming method and application for composite material component forming. The method is characterized in that a metal false piece which is completely consistent with the outline dimension of a composite material reinforcing rib structure component is machined through a mechanical manufacturing method, and a reinforced fiber soft mold tool with acertain rigidity used for forming the composite material component is manufactured through the metal false piece; and through the soft mold tool, the pressure applied by a hot pressing tank can be uniformly and accurately transferred to the composite material reinforcing rib structure component, so that the thermal hysteresis effect of the reinforcing rib part is avoided, the appearance size andthe contour degree of the reinforcing rib strip are guaranteed, and meanwhile, the manufacturing efficiency of the workpiece is improved.

The invention aims at providing a brake disc DTV repairing machine which is simple in structure, convenient to operate, low in cost and good in universality. The brake disc DTV repairing machine comprises an inner plate and an outer plate which are fixedly connected. Two opposite grinding wheels are arranged between the inner plate and the outer plate. The first grinding wheel is movably connected with the inner plate, the outer plate is provided with a feeding propelling nut through thread matching, and the second grinding wheel is movably connected with the feeding propelling nut; the inner plate is movably connected with a connection support through guide pins, and the inner plate can move relative to the connection support in the axis direction of grinding wheel rotation shafts; and the connection support is provided with a connection mechanism which is used for being movably connected with a brake disc to be repaired. The brake disc DTV repairing machine is further provided with a drive assembly. A drive shaft of the drive assembly is connected with the rotation shafts of the first grinding wheel and the second grinding wheel through belts. The drive shaft of the drive assembly is provided with a drive segment with a preset length so that driving to the first grinding wheel and the second grinding wheel can be guaranteed when the first grinding wheel and the second grinding wheel move relative to the drive assembly.

The invention provides a manufacturing process and equipment for a hyperconventional-size conformal curved surface reflecting plate. The manufacturing process comprises the following steps of: performing segmented numerical control processing on the conformal reflecting plate, and integrally riveting the conformal reflecting plate by using a conformal tool; designing segmented reflecting plates of the conformal reflecting plate according to the specification data of the pre-stretched material, and processing the conformal reflecting plate in a segmented manner by using five-axis numerical control processing, rough and fine processing and natural aging processes to obtain segmented reflecting plates; using a conformal assembly tool conformal with the conformal reflecting plate to rivet the segmented part of the segmented reflecting plate so as to assemble the conformal reflecting plate; carrying out low-temperature destressing by utilizing a preset temperature condition and an aging condition so as to eliminate the assembly stress of the conformal reflecting plate; and the surface profile tolerance and the dimensional accuracy of the conformal reflecting plate are monitored by using a three-coordinate detection and photogrammetry method. The technical problem that processing of a large-curvature-feature conformal reflecting plate, the profile tolerance of the reflecting plate, the size precision control of installation positions such as a connector and the like are large in difficulty is solved.

The invention discloses a machining method for a nozzle ring blade. The machining method comprises the following steps that the outer circle allowance of the blade end is removed; the shaft end outercircle and end face allowances are removed, and subsequent machining locating faces are obtained; the nozzle ring blade is located and clamped by a milling tool, the shaft end outer circle and the large end face serve as locating faces, the large end face is flattened, the blade is milled roughly first, then finish milling is conducted for the blade profile, and the profile tolerance of the bladeprofile is ensured; finish turning is conducted on the shaft end face, the outer circle and a shaft end face chamfer; the shaft end face is flattened, and finish turning is conducted on the blade endouter circle and an annular groove; the nozzle ring blade is clamped by a turning tool, the blade profile serves as a locating face, the top end of the blade is flattened, and a shaft end flat squareis formed by cutting; and a bench worker removes burrs. The special milling tool and the turning tool are designed, thus the nozzle ring blade is milled, the shaft end flat square is machined, and meanwhile, an auxiliary measuring tool is designed to solve the problem of partial dimension measurement.

The invention discloses a riveting process suitable for a die-cast piece. The riveting process is characterized by comprising the following steps: 1) a first layer of workpiece and a second layer of workpiece are provided, and are placed up and down in sequence to form a piece to be riveted; 2) a bearing mold is provided; and the piece to be riveted is put in the bearing mold; 3) the piece to be riveted is riveted on the bearing mold; and 4) the riveted workpiece in the step 3) is machined to form a final product. The riveting process has the following beneficial effects: the process firstly rivets the two layers of workpieces, and then, performs such processes as punching, typing, trimming and burr pressing to obtain the final product; and the process arrangement guarantees the product appearance profile and the coaxiality of upper and lower holes, so that the subsequent assembly is guaranteed, and the cost is largely saved.

An adaptive test bench for a lifeboat diesel engine, including a base, a load device, and a horizontal parallel iron; there are two horizontal parallel irons, which are fixedly connected to four bracket seats, and correspond to the mounting feet of the diesel engine one by one; the four bracket seats are at least Two adjacent bracket seats are provided with adjustment devices; the adjustment devices are arranged in sequence from top to bottom: screw sleeves, fixed nuts, nut seats, and positioning pins; the upper half of the inner wall of the screw sleeves is threaded, and the lower The half section is a light hole, the upper section of the outer wall of the tube is a hexagonal column, the middle section is a left-handed external stud, and the lower section is a cylinder; the upper hole of the fixing nut is provided with a left-handed internal thread, and the lower hole is a cylindrical hole, and the left-handed internal thread of the upper hole is connected to the middle section of the screw sleeve. A thread pair is formed, and the cylindrical hole of the lower hole and the lower column of the screw sleeve form a cylindrical pair; the fixed nut is fixedly connected to the nut seat; the nut seat is fixedly connected to the support frame by a positioning pin. The invention utilizes the adjustment and support function of the adjustment support to meet the installation requirements of the diesel engine test and can effectively prevent the installation screws from loosening.

The invention discloses a method for forming a thick-wall large-diameter pipeline with a large bending angle and a small bending radius. The method for forming the thick-wall large-diameter pipeline with the large bending angle and the small bending radius comprises two aspects, namely design of a pipe blank and design of a mould, wherein the pipe blank is a straight pipe, a step is formed in the outer diametric plane and used for mounting and clamping; the mould is divided into a cross beam part, a connecting rod part, a bending die part and a core rod part; the connecting rod part comprises a left connecting rod and a right connecting rod, the bending die part comprises a left bending die and a right bending die, the core rod part comprises a left core rod and a right core rod, the left connecting rod is connected between the cross beam and the left bending die, the right connecting rod is connected between the cross beam and the right bending die, and the lower ends of the left bending die and the right bending die are jointly pivoted and rotate together by virtue of one supporting pin shaft; and the pipe blank is placed in pipe penetrating cavities of the left bending die and the right bending die, and the left core rod and the right core rod respectively penetrate through the pipe blank from the left end and the right end. The method for forming the thick-wall large-diameter pipeline with the large bending angle and the small bending radius has the advantages that a simple mould is adopted for converting a provided pressure into a bending forming force of an elbow and the related technology is applicable to a large-angle bent pipeline with a thick wall, a large diameter and a small bending diameter ratio.

The invention discloses a method for milling and processing a carbon fiber sacrifice layer of a connecting plane, which is applied to milling and processing the carbon fiber sacrifice layer of a butting plane for connecting a composite material afterbody and a vertical tail of an aircraft. The method comprises the following steps: (1) positioning an assembly part of the front section of the afterbody, i.e., maintaining a product of the front section of the afterbody after assembly, and positioning the front section of the afterbody and an assembly tooling together in a processing area of plane milling equipment; (2) selecting a processing tool for the plane milling, wherein the tool is a disc type milling tool, and is made of hard alloy; (3) determining a processing technology, aligning the tool by the milling equipment, determining the allowance of milling, and determining the feeding direction of the tool processing; (4) determining parameters of the processing technology; (5) milling the butting plane by the milling equipment. The method has the advantages that the contour of the butting plane is checked by a laser tracking instrument; the contour requirement of the connecting plane of the front section of the afterbody and the vertical tail is guaranteed, and the front section of the afterbody and the vertical tail can be smoothly butted.

The invention provides a machining technology of a cam-mould special-shaped concave-mould. The machining technology sequentially comprises the following processes of material sawing, rough turning, special shape rough milling of a machining center, heat treatment, numerical-control finish turning, plane abrasion, pressure distribution, special shape finish milling of the machining center, grinding, pressure withdrawing, S-N co-diffusion, polishing and secondary pressure distribution. According to the machining technology of the cam-mould special-shaped concave-mould, the profile tolerance of the concave-mould after the follow-up special shape finish milling of the machining center is guaranteed through the pressure distribution process in the concave-mould machining technology, so that the profile tolerance of the concave-mould is ensured to be within 0.02 mm, therefore the profile tolerance of a cam forge piece is guaranteed, further the product profile tolerance after the follow-up heat treatment is conducted is ensured, and the production quality is improved.

A machining method for the plasma-sprayed surface of the internal annular surface of an annular housing is used for finishing the plasma-sprayed surface of the internal annular surface of the annular housing sprayed with plasma spraying material. The method includes the following steps: along the axial direction of the annular housing, the annular housing is divided into a plurality of continuous annular blocks, and the actual measured diameter of the plasma-sprayed surface of the internal annular surface of each annular block is measured; a spline curve is constructed for the actual measured diameters meeting design requirements, machining allowances are determined by using machining diameters measured on the spline curve, finally, the machining allowance corresponding to each annular block is set into a numerically controlled machine tool, the numerically controlled machine tool is utilized to remove the machining allowance of each annular block, so that the machined annular housing is obtained, and thereby the profile tolerance of the plasma-sprayed surface of the internal annular surface of the annular housing can meet the design requirements.