156 results about "Composite blade" patented technology

The invention discloses a method for simulating a mold temperature field and curing deformation through finite elements and a mold optimization design method based on the method. The finite element analogue simulation method comprises the following steps: firstly, modeling and simulating a mold grid; secondly, calculating equivalent thermal and mechanical parameters of the composite material by adopting a multi-scale homogenization method; then, a heat conduction model of the mold and the composite material blade is constructed and coupled with the curing dynamic model through temperature, and mold temperature distribution is simulated; and finally, establishing a mold thermal expansion and curing stress coupling model, and predicting thermal deformation and stress change of the mold. By identifying the weak area of the mold in the simulation process, the mold is optimally designed. By improving a mold temperature field distribution simulation method, optimizing a grid modeling process and introducing an accurate calculation method of equivalent material parameters, the precision of mold design and the controllability of a curing process are effectively improved, so that the problem of inaccurate mold temperature field distribution and curing deformation prediction is solved.

A testing device and a testing method of a composite blade tilt rotor power assembly are related. The testing method includes the following steps: installing a tilt rotor flight power assembly on a flange platform of a testing device through a connector; confirming normal operation of an external power supply, the tilt rotor flight power assembly and a data acquisition computer; starting the tilt rotor flight power assembly, and controlling a tilt motor to rotate a cantilever shaft according to a tilt angle instruction; and recording the energy consumption and the tensile forces and torques in x, y and z directions of the tilt rotor flight power assembly by the data acquisition computer in real time. The testing method has the beneficial effects that the processes of starting, starting and stopping, hovering and descending can be simulated for the composite blade tilt rotor power assembly which is a core driving component of a vertical take-off and landing type electric driving hovercar, and the flight performance of the hovercar can be tested. The testing method can also be used for cold rotation test, take-off strategy verification test, hover strategy verification test, durability test and acceleration performance test of the composite blade tilt rotor power assembly.

The invention discloses an ultrafast laser partition impact strengthening method and device for a thin-wall covered edge of a composite blade. According to the method, the surface of the thin-wall covered edge is strengthened by utilizing the characteristics of instantaneous high pressure of shock waves induced by ultrafast laser and accurate and controllable propagation depth, and meanwhile, according to the thickness characteristics of different areas of the covered edge, laser with different pulse widths is selected to carry out partitioned strengthening treatment, so that accurate regulation and control of a surface residual stress field are realized on the premise of inhibiting deformation; the problem of cooperative control of surface strengthening deformation and a stress field of the thin-wall edge covering structure is solved. According to the thickness characteristics of different areas of the edge covering structure, based on the principle that the shorter the laser pulse width is, the shallower the shock wave propagation depth is, the shallow the depth of a residual stress field influence layer is and the edge covering structure is not prone to deformation, a femtosecond / picosecond pulse width laser combined shock peening method is provided, and femtosecond laser shock is adopted in a thin-wall area; femtosecond laser or picosecond laser with relatively long pulse width is adopted for impact in a wall thickness area, and precise regulation and control of a surface stress field are achieved on the premise of restraining thin-wall wrapping edge deformation.

The invention discloses a composite blade electroforming metal wrapping sheet and a production device thereof, and relates to the technical field of blade metal wrapping sheets, the composite blade electroforming metal wrapping sheet comprises a plurality of wrapping sheet sections, one side surface of each wrapping sheet section is provided with a fixing slot, a reinforcing assembly is arranged in each wrapping sheet section, and the reinforcing assembly comprises an additional side plate arranged on one side surface of each wrapping sheet section, the multiple wrapping sheet sections and the additional side plates are combined into a wrapping sheet finished product piece, a fixed side block is arranged at one end of the wrapping sheet finished product piece, the surface of one side of the fixed side block is connected with the surface of one side of the additional side plate at one tail end of the wrapping sheet finished product piece, a connecting shaft rod is arranged on the upper surface of the fixed side block, and a turnover anchoring plate is arranged on the surface of one side of the connecting shaft rod. And a plurality of anchoring screws are arranged on the upper surface of the overturning anchoring plate, and in the scheme, by arranging the reinforcing assembly and the machining mechanism, the stability of the wrapping piece in the using process and the production efficiency are improved.

The invention belongs to the technical field of blade ring structure optimization design of composite materials, and particularly relates to a structure optimization design method of a titanium-based composite material integral blade ring, which comprises the following steps of: analyzing and calculating an equivalent elastic constant of a titanium-based composite material on a micro-scale, and performing secondary development on Abaqus software by using a Python language on a macro-scale to obtain an equivalent elastic constant of the titanium-based composite material integral blade ring; and then compiling a static analysis plug-in of the integral blade ring structure, and finally realizing optimal design of the blade ring structure by utilizing an automatic plug-in. The method has the advantages of being simple, easy to operate, high in efficiency and the like, the static strength reserve coefficient-optimization parameter curve is formed by carrying out automatic finite element simulation of various integral blade ring structural forms, and the further obtained optimization conclusion provides effective guidance and basis for the structural forms of the integral blade ring.

The invention discloses a solar shutter system, which comprises a composite blade, which is composed of an outer layer transparent photovoltaic film and an inner layer phase change energy storage material and is used for realizing photoelectric conversion and heat energy storage; the driving mechanism comprises a driving motor and a gear transmission system, is connected with the composite blade and is used for adjusting the opening and closing angle of the composite blade; the illumination sensor is installed on the sun shield and used for collecting environment illumination intensity data in real time; the intelligent control module comprises a central controller and a micro MCU, the central controller is used for receiving the illumination intensity data and generating a blade angle adjusting instruction, and the micro MCU is used for controlling the driving mechanism to act according to the adjusting instruction; and the energy storage unit comprises a super capacitor brick and a lithium battery pack and is used for storing the electric energy generated by the transparent photovoltaic film. The system is suitable for energy-saving reconstruction of existing buildings and energy management of green buildings, and has the advantages of being self-powered, intelligent, efficient, energy-saving and the like.

A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

The present invention belongs to the technical field of foreign object impact on composite material blades of aircraft engines, and specifically discloses a composite material engine blade trailing edge delamination damage test device and test method, the device includes a foreign object impact launch subsystem, a blade typical part test bench and a high-speed camera monitoring subsystem; the foreign object impact launch subsystem is used to launch birdshot; the blade typical part test bench is used to fix the blade typical part so that it is impacted by the birdshot; the high-speed camera monitoring subsystem is used to monitor the birdshot impact process and record the birdshot impact test data. The present invention realizes the control and adjustment of the bird cutting angle, bird impact height and bird cutting amount by designing an adjustable tooling and a detachable typical part fixture of the blade typical part test bench, which solves the problem that the existing technology cannot simultaneously realize the adjustment of the impact height, impact angle and bird cutting amount, and the test research plan is limited by the equipment, and it is difficult to accurately control the impact working condition.

The present application relates to a kind of composite material blade tenon sampling piece tensile test fixture and test method.The tensile test fixture is used to clamp the two ends of tenon sampling piece and carry out tensile test, specifically includes ear piece adapter, mortise simulation piece, pin, a pair of clamping plate and several clamping plate bolts.The upper end of ear piece adapter is connected with the upper clamp of testing machine, and the lower end of mortise simulation piece is connected with the lower clamp of testing machine.The lower end of ear piece adapter is connected with the upper end of two clamping plates by pin penetration, and pin shaft connection pair is formed.Two clamping plates are oppositely arranged and clamp tenon sampling piece by clamping plate bolt in array compression mode.The inner side of clamping plate and tenon sampling piece contact is provided with tooth groove structure, and the inner cavity profile of mortise simulation piece is adapted to the shape of the outer surface of tenus sampling piece.Compared with prior art, the present application is suitable for static strength test under 0~250 kN large load range, and significantly improves the stability and success rate of composite material special-shaped sampling piece test.

The invention discloses a single-crystal high-temperature alloy and ceramic matrix composite material-based functional partition type composite blade design method, which comprises the following steps of defining a temperature bearing area and a force bearing area of a blade through heat and force simulation; the brazing residual stress is predicted, and the optimal assembly gap between the two partition interfaces of the temperature bearing area and the force bearing area of the composite blade is optimized and determined; predicting peak stress, and optimizing and determining the optimal position and size of a mechanical locking structure between two partition interfaces of a temperature bearing area and a force bearing area of the composite blade; and through heat-force-flow coupling simulation, the maximum equivalent stress of the composite blade and the bonding strength between partition interfaces are evaluated, and then the design of the composite blade is completed. According to the method, through heat-force-flow coupling simulation and iterative optimization, precise definition of function partitions and cooperative compatibility of mechanical locking and the process are achieved, and the low-stress and high-strength performance of the composite blade in the high-temperature and high-pressure environment is ensured.

This invention belongs to the field of oil and gas drilling technology, specifically relating to a PDC drill bit with automatically updating composite cutting discs. It aims to solve the problem of existing drill bits requiring tripping and bit replacement when drilling speed decreases due to tooth wear, thus affecting drilling efficiency. The PDC drill bit with automatically updating composite cutting discs includes a drill bit body, a mounting groove on the drill bit body, and multiple cutting discs arranged side-by-side in the mounting groove. Below the mounting groove is a longitudinally extending output channel communicating with the mounting groove, and adjacent cutting discs are connected in the output channel by a tenon and mortise structure. It also includes a drive device located at the bottom of the drill bit body. During normal drill bit operation, the drive device is pressurized and stores power; when the drill bit is lifted, the drive device applies a downward pulling force to the cutting discs to move them downwards. This PDC drill bit can automatically update the cutting discs during drilling, to a certain extent avoiding tripping due to drill bit wear and improving production efficiency.

The utility model relates to the field of photocatalysts, in particular to a photocatalyst material mixing device which comprises a base, a tank and a motor, a stirring mechanism is arranged in the tank and comprises a straight rod, a fixing sleeve and a composite blade set, the composite blade set comprises a first rotating cylinder, a bearing, a fixing ring and a butt joint column, and a ratchet wheel is fixed to the butt joint column. Materials for preparing the photocatalyst are put into the tank body, then the motor is started to provide power needed during operation for the stirring mechanism, the motor drives the straight rod to rotate, the assembly cylinder installed on the straight rod starts to drive the composite blade set to rotate, and in the rotating process of the composite blade set, the composite blade set is driven to rotate. The arc-shaped blades on the surface of the first rotary drum drive the first rotary drum to rotate after being subjected to resistance of a liquid material, and the arc-shaped blades can provide a spiral force in the horizontal direction during rotation, so that gel particles floating in the material on the liquid surface can be better fed to the bottom surface of the material, and the gel particles are uniformly distributed in the tank body.

The invention relates to a method for manufacturing a turbomachine blade having a composite blade and a metal root, comprising the steps of: - a) providing a blade preform and a spar comprising a first part inserted into a cavity of said preform and a second part external to the preform and forming the root, - b) gluing the first part, - c) introducing the first part into the cavity (80) - d) depositing this assembly in a mold, - e) heating the mold to a first temperature, - f) injecting a resin into the mold, - g) consolidating the resin at a second curing temperature, characterized in that it comprises a step i) of cooling the spar to a third temperature lower than said first temperature, which begins before step e) and ends after step f). Figure for abstract: Figure 9

The application discloses a method for integrally injection-molding a metal small shaft and a composite small blade, extending an easy-to-break tail section of the same material from a non-injection-molding end of the metal small shaft, processing a notch and a plane on the surface of the injection-molding end of the metal small shaft, placing a tooling on the outside of a mold cavity of an injection-molding mold and corresponding to the position of the metal small shaft, adjusting the clamping position of the metal small shaft on the tooling, starting injection molding, keeping the tooling clamping the tail section of the metal small shaft during the injection molding, and removing the tail section after the injection molding. The method accurately integrally injection-molds one end of the metal small shaft and an end of the composite small blade, ensures that the length direction of the metal small shaft exposed from the end of the composite small blade meets the specified length, and ensures that the metal small shaft does not rotate in the composite small blade or is not separated from the composite small blade due to loosening of the joint position during use, so that the metal small shaft and the composite small blade form an integrated louver blade.

Tool (40) for manufacturing a bucket (10) made of composite material for a turbomachine, in particular a turbomachine of an aircraft, comprising:-a mould (30) and a counter-mould (34) defining between them a cavity (32) configured to receive a woven preform, the cavity (32) having a first portion (Z1) and a second portion (Z2), the first portion is configured to receive the shield (22) and at least one edge of the preform and the second portion is configured to receive at least a portion of the remaining portion of the preform,-an element (42, 44, 46) for managing the temperature of the cavity (32), these elements are configured to heat the first and second portions (Z1, Z2) of the cavity (32) at different temperatures during at least one step of the method for manufacturing the vane (10).

The present invention belongs to the technical field of automatic laying of composite blade skins, and specifically relates to a composite device for molding and wrinkle elimination. It includes a central vacuum suction cup, a side vacuum suction cup, a side suction cup driving cylinder, a guide shaft, an electric cylinder, a cam assembly, a molding die, a side wrinkle elimination plate, a fixing seat, a plate extension cylinder, a plate rotation cylinder, etc. The central vacuum suction cup and the side vacuum suction cup are distributed on the same plane, and are used to vacuum absorb fabric prepreg sheets. The electric cylinder drives the symmetrically distributed cam assemblies to drive the molding die to symmetrically expand and contract, thereby realizing the laying and compaction of the fabric prepreg sheets. The side wrinkle elimination assemblies distributed on both sides of the mold are driven by the plate extension cylinder and the plate rotation cylinder to realize the expansion and rotation of the side wrinkle elimination plate. Adjusting the pressure of the side wrinkle elimination plate combined with the lifting and lowering of the molding die can realize the molding and preforming of the fabric prepreg sheets and eliminate the wrinkles generated during the laying process.

The utility model discloses a PCD compound tool with a self-lubricating mechanism, and relates to the field of PCD compound tools, the PCD compound tool comprises a PCD compound tool body, the PCD compound tool body comprises a compound tool apron, a compound tool bar and a compound blade, the bottom of the compound blade is fixedly provided with a compound tool bit, and a plurality of first through holes are formed in the compound blade; a plurality of balls are fixedly mounted on the outer wall of the composite tool apron, the outer walls of the balls are sleeved with mounting sleeves, and a plurality of clamping grooves are formed in the inner walls of the mounting sleeves; a cavity is formed in the composite tool apron, and a plurality of second through holes are formed in the bottom of the composite tool apron. By arranging the movable plug and the movable annular plate, lubricating oil can be evenly distributed on the surface, connected with the composite tool bit, of the composite blade through the multiple first through holes, the PCD composite tool is evenly self-lubricated, and by arranging the compression spring, the self-lubricating amount can be effectively controlled.

The utility model discloses a high-efficiency ball-end ultra-dense tooth milling cutter with a composite blade, which belongs to the technical field of milling cutters and comprises a milling cutter body, the milling cutter body comprises a cutter body and a blade component, the blades are distributed on the outer surface of the cutter body along the circumferential direction, and the blades are unequally distributed on the cutter body; each blade comprises a margin, the width value of the margin is 1% of the blade diameter, and the margin is distributed at the + / -75-degree position of the ball head; the edge strip is smooth in surface, has certain hardness and wear resistance, can effectively restrain the retreating of the edge point caused by the wear of the cutter, and ensures the contour precision of the ball head, so that the cutting precision is ensured. The tool nose is arranged at the foremost end of the blade, the tool nose is provided with the two contact points, and the two contact points of the tool nose are both located at the foremost end of the blade, so that the abrasion problem caused by stress concentration possibly occurring to a single contact point and zero linear speed is effectively avoided.

The invention discloses an active control device for aerial stable steering of a hoisted object of a crane. An outer frame is fixedly provided with three layers of platforms from top to bottom; an upper-layer lifting ring is mounted in the center of the upper-layer platform and is upwards hooked with a crane hook; the middle-layer platform is provided with a motor, a motor controller of the motor and a dual-output planetary gear assembly; a centrifugal blade composite flywheel is mounted in the center of the upper surface of the lower-layer platform; the motor controls the centrifugal blade composite flywheel to rotate through the double-output planetary gear assembly, and two lower hanging rings and a network camera are installed on the lower surface of the lower layer platform. The invention belongs to the technical field of crane auxiliary machinery, utilizes fluid reaction type indirect transmission and a centrifugal composite blade structure to realize driving, braking and stable control of rotation of a hoisted object, avoids inertia impact of large-load start and stop, inhibits instantaneous attitude fluctuation of a rotating shaft, reduces vibration and improves the stability of the hoisted object. The problem that in the prior art, a crane is not enough in stability and safety in the aerial angle control process of a hoisted object is solved.

The invention relates to a composite blade RTM compression molding mold and a molding method, and belongs to the technical field of aerospace, the composite blade RTM compression molding mold comprises an upper mold plate, a lower mold plate, a first sliding block, a second sliding block, an upper pressing part and a lower pressing part, the bottom surface of the upper mold plate is provided with an upper pressing groove, and the two inner groove walls of the upper pressing groove are inclined; a lower pressing groove is formed in the top surface of the lower template, and two inner groove walls are inclined; the first sliding block and the second sliding block are oppositely arranged in the upper pressing groove and the lower pressing groove; the upper pressing part and the lower pressing part are oppositely arranged in the two forming grooves and make contact with the groove bottoms of the two forming grooves. The method comprises the following steps: firstly, inserting a propeller root paved with a lightning-protection braid into a forming cavity; and then the upper mold plate and the lower mold plate are pushed to be closed, the first sliding block and the second sliding block are driven to be close to each other, the upper pressing part and the lower pressing part are linked to be close to each other to extrude the paddle root on which the lightning-protection braid is laid, wrinkles of the lightning-protection braid due to horizontal stirring are avoided, and the qualified rate of RTM compression molding of the composite paddle is increased.

A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

The invention belongs to the technical field of engine structure design, and particularly discloses a bird-impact-resistant layered hybrid asymmetric layering structure for the tail edge of a composite material blade, and the bird-impact-resistant layered hybrid asymmetric layering structure is used for forming a fan blade of a large-bypass-ratio turbofan engine. The bird-impact-resistant layered hybrid asymmetric layering structure for the tail edge of the composite material blade comprises a bullet-facing surface, a central area and a bullet-backing surface, a hybrid region is arranged in the central region, and fibers which are different from other regions and have high toughness are arranged in the hybrid region, so that a hybrid fiber laying layer structure is formed; the mixed area is not symmetrical about the geometric middle plane of the layering structure in the thickness direction, so that an asymmetric layering structure is formed. The problems that the rigidity and toughness of a single material system of an existing composite material fan blade laying layer are contradictory, and the design freedom degree is limited by symmetrical laying layer design are solved.

A propeller assembly to facilitate the cleaning of aquaculture nets. The propeller assembly has a centrally disposed hub with a plurality of plastic composite blades extending outwardly to a perimeter ring. A plurality of triangular shaped rigid knuckles are coupled to the perimeter ring. A blade spacer is attached to a leading edge of each blade, the knuckle and blade spacer are constructed of a wear resistant non-ferrous material, ferrous material, or combination thereof. In operation, rotation of the blades provides thrust for positioning the knuckles against an aquaculture net, whereby the knuckles remove fouling from the aquaculture net by violently shaking the aquaculture net. The blade spacer positions the propeller assembly a predetermined distance from the aquaculture net to protect the leading edge by distance and / or use of the wear resistant material.

The application discloses a self-sharpening kitchen knife, a regenerated material crushing knife, a cutter and a preparation method, an outer side section of a first side of a blade base is provided with a thin-layer alloy reinforcing part through laser additive, the thin-layer alloy reinforcing part is embedded into the blade base; the thin-layer alloy reinforcing part and the blade base form a composite blade; the hardness of the thin-layer alloy reinforcing part is greater than the hardness of the blade base; the thin-layer alloy reinforcing part extends to a blade edge; the thin-layer alloy reinforcing part has better layer combination, is not easy to crack and separate, has higher strength, the hardness of the thin-layer alloy reinforcing part is greater than the hardness of the blade base, so that the wear resistance of a blade A surface is better than that of a blade B surface; during cutting operation, the blade B surface is first worn due to the lower hardness, so that a front edge of the thin-layer alloy reinforcing part protrudes, and then the cutter can keep relatively sharp cutting performance for a long time.

The invention discloses a blade tip grinding method for a long and short composite blade, which is used for grinding a blade tip of a blade disc with a long blade and a short blade, an overlapping part exists on the blade tip of the short blade adjacent to the long blade, and the method comprises the following steps of: mounting the blade disc on a rotary table of a five-axis machine tool; an angular reference is determined through the preset line position of the index plate, and the angles of the long blades and the short blades are located; the position of the first grinding wheel is adjusted, so that the rotating center line of the first grinding wheel is parallel to the blade tip contour lines of the long blade and the short blade, and the blade tip of the long blade and the blade tip of the non-overlapped part of the short blade are sequentially ground; and finally, the second grinding wheel is used for grinding the overlapped part on the short blade. By means of the method, grinding machining of the blade tips of the blade discs of the long and short composite blades can be achieved, the machining precision is high, the strict requirement of aero-engine blades for the dimensional tolerance of the blade tips is met, a blade tip collision-grinding test is conveniently carried out, and control over the gaps between the blade tips and a cartridge receiver is facilitated.

A composite vane with a locking feature including a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the composite vane; a dovetail section formed within the composite vane proximate the radially outer attachment region; a shoe member in operative communication with the dovetail section; a boot in operative communication with an inner portion opposite spanwise from the dovetail portion; and a failsafe fastener in operative communication with the boot and the inner portion of the composite vane.

A composite blade (10) is provided with: an airfoil part (11); a blade root part (12); and main laminates (32) and sub-laminates (33) each of which include a composite material layer of a fiber-reinforced resin and which are alternately laminated in the blade root part (12). A lateral surface (12a) of the blade root part (12) includes a contact-enabled surface (13) capable of making contact with an attachment groove (50). The main laminates (32) extend from the blade root part (12) to the airfoil part (11) so as to merge together before reaching the airfoil part (11). The sub-laminates (33) extend from the blade root part (12) to respective merging points of the main laminates (32). The contact surface (13) has a first edge part (14) and a second edge part (15). Inside the blade root part (12), a first section (41) positioned around the first edge part (14) and a second section (42) positioned between the first section (41) and a center surface (5) of the blade root part (12) are set. In the first section (41), the end parts of the sub-laminates (33) are not positioned. In at least a part of the second section (42), respective parts of the main laminates (32) and the sub-laminates (33) are alternately positioned along the blade thickness direction.

The present invention discloses a design method for a composite impeller of a centrifugal pump. The composite impeller consists of two parts: a twisted blade and a cylindrical blade. The twisted blade is adopted at the inlet part of the impeller to reduce the turbulence and impact loss at the inlet of the centrifugal pump and improve the efficiency of the pump. The cylindrical blade is adopted at the outlet part of the blade, so that other parameters of the impeller change less except the impeller diameter during the cutting process, thereby ensuring the similarity between the external characteristic curve of the pump after cutting and the external characteristic curve of the original pump, and realizing precise cutting of the impeller outer diameter. Compared with the traditional centrifugal pump impeller cutting method, the time cost and trial-and-error cost of cutting are greatly shortened, which is beneficial to reducing the production cost of enterprises.

The invention discloses an aero-engine composite material blade positioning and processing method based on reverse design. The method comprises the following steps: step (A), blade scanning and profile fitting; step (B), reversely designing a blade machining tool; (C), a tool positioning molded surface of the blade machining tool is machined; (D), the blade to be machined is positioned; and (E) processing the blade. According to the method, fitting is conducted on the basis of the actually-formed composite material blade, the scanning mathematical model and the blank mathematical model, precise positioning is conducted on the blade on the basis of the reversely-designed tool profile, the positioning precision is guaranteed, the positioning efficiency is improved, clamping deformation cannot be caused in the blade positioning and clamping process, and good application prospects are achieved.