87 results about "Composite blade" patented technology

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 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 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.

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 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.

The utility model discloses a powder exhaust fan composite blade angle adjusting structure which comprises an outer cylinder, a driving motor, three blades and an adjusting mechanism, the driving motor is fixedly clamped in the outer cylinder, the blades are fixedly clamped at the output end of the driving motor, and the adjusting mechanism is arranged between the blades and the output end of the driving motor. The roots of the blades are fixedly connected with connecting rods, the adjusting mechanism comprises an outer ring, bearing seats and an adjusting ring, an inner ring is arranged in the middle of the outer ring, the inner ring is fixedly connected with the output end of the driving motor in a clamped mode, the three sets of bearing seats are fixedly connected to the outer cylindrical surface of the outer ring, and the left end and the right end of each connecting rod are rotationally connected with the bearing seats in a clamped mode. The limiting frame slides in the sliding groove and then drives the connecting rod to move, the connecting rod is limited by the bearing seat, the bottom end of the connecting rod inclines, the blades incline along with the connecting rod, the angles of the blades can be changed, and therefore the air exhaust range of the device can be widened.

The application discloses a cemented carbide composite blade and a preparation process, relates to the field of alloy blades, and comprises a base body, a center hole arranged in the middle part, and inwardly recessed inclined surfaces arranged on both sides, wherein the included angle between the inwardly recessed inclined surfaces and the vertical center line is 45-80 degrees; an outer ring part is arranged on the outer side of the base body, and the vertical section included angle between the outer ring part and the base body is 65-75 degrees; a curved groove surface is formed on the outer ring part; cemented carbide blades are fixedly installed on both sides of the outer ring part; the component materials of the cemented carbide blades are as follows: W: 64.2-78.6 wt%, C: 5.1-6.8 wt%, Fe: 0.5-1.5 wt%, Si: 0.1-0.3 wt%, Al: 0.3-0.8 wt%, Cr: 1.3-2.7 wt%, Ti: 2.4-4.0 wt%, Nb: 0.8-1.6 wt%, Co: 8-12 wt%, Mo: 0.5-1.0 wt%, Ta: 0.4-1.3 wt%, and the balance is Ni and trace residual impurities; REC=(Ta+Ti+Nb) / W+(Nb+Ti) / 2(Ni+Cr) is arranged, and 0.375<=REC<=0.705, so as to solve the technical problems that the alloy cannot be axially and radially reinforced on the cutter head, and the structural strength of the cemented carbide material is enhanced.

The application belongs to the technical field of engine structure design, and particularly discloses a hybrid asymmetric layered structure of a composite blade tail edge for resisting bird strikes, which is used for forming a fan blade of a large-bypass-ratio turbofan engine, and comprises a bullet-facing surface, a central region and a bullet-facing back surface; a hybrid region is arranged in the central region, and high-toughness fibers different from those in other regions are arranged in the hybrid region to form a hybrid fiber layered structure; the hybrid region is not symmetric about the geometric median plane of the layered structure in the thickness direction, thereby forming an asymmetric layered structure. The application solves the contradiction between the stiffness and toughness of the single material system of the existing composite fan blade layered structure and the problem that the symmetric layered design limits the design freedom.

The invention discloses a composite mixed-flow turbine, which belongs to the technical field of turbines, and mainly comprises a volute, a flow guide plate and a flow guide plate, the air inlet cone is mounted in the volute casing; the rotating piece is mounted on the air inlet cone; the impeller is installed on the rotating piece, multiple layers of blades are arranged on the impeller, the blades in part of layers are composite blades, the blades in part of layers are axial flow blades, and the blade layers with the axial flow blades are arranged adjacently; the length of the projection of a blade root chord D of each axial flow blade on the axis of the impeller is the projection length H, and the distance between adjacent layers with the axial flow blades is 1 / 5H-1 / 3H; and the tail cone is mounted in the volute casing, and the tail cone corresponds to the impeller. The turbine solves the problems that when fluid passes through an existing turbine, large air volume and high air pressure cannot be provided at the same time in a small space size, and turbulent flow and too large noise are generated at the same time.

The utility model provides a multifunctional cell scraper, which relates to the technical field of cell scrapers and comprises a handle, the inner side of the handle is connected with a blade support in a sliding manner, a knife handle is fixedly mounted in the blade support, the side surface of the knife handle is fixedly connected with a composite blade, an upper button is connected to an inner groove of the blade support in a sliding manner, and a lower button is connected to the inner groove of the blade support in a sliding manner. According to the utility model, through the handle, the blade bracket, the knife handle, the composite blade, the blade, the lower button, the upper button, the upper pressing plate, the upper clamping column, the upper spring, the lower clamping column, the lower pressing plate, the lower spring and the curved surface collecting plate, when large-area cells need to be scraped, the front surface of the composite blade is used for scraping the cells; when small-area scraping is carried out, the upper button can be pressed, the lower button can be rotated and fixed, and side scraping of the composite blade is switched, so that rapid switching of the blade is realized, and various cell scraping requirements are met.

The invention discloses wide-width AEM anion exchange membrane production equipment which comprises a double-deviation-correction unwinding system, a composite blade coating system is arranged on one side of the double-deviation-correction unwinding system, and a drying oven drying system is arranged on one side of the composite blade coating system.The wide-width AEM anion exchange membrane production equipment adopts a blade coating mode, so that the production efficiency is improved; the slurry is good in applicability, and the requirement on the viscosity of the slurry is not high; according to the equipment, before coating, a net-shaped reinforcing film enters a soaking tank to be soaked, so that holes are filled with slurry, then redundant slurry is extruded out and compounded with a base film, and finally coating is conducted, so that the surface of a coating is free of holes, and the uniformity is good; according to the equipment, the double-deviation-rectifying unwinding mechanism is adopted, two different materials are integrated on one unwinding mechanism, the structure is compact, feeding and discharging are convenient, and meanwhile the deviation rectifying precision of the two materials is guaranteed; the infiltration tank adopts a quick-release mechanism, so that the cleaning is convenient, and the repeated precision is good.

The utility model relates to the technical field of deep hole milling cutters, and discloses a composite-edge deep hole milling cutter which comprises a cutter handle, a cutter body is movably connected to the top of the cutter handle, a cutter head is movably connected to the top of the cutter body, a connecting assembly is arranged between the cutter head and the cutter handle, a threaded groove is formed in the connecting assembly, and the threaded groove is communicated with the cutter body. A threaded groove is formed in the bottom of the cutter handle, an expansion bolt movably penetrates through the interior of the cutter handle, the expansion bolt extends into the threaded groove, and a containing groove is formed in the bottom of the cutter handle. The composite-edge deep hole milling cutter has the advantages that compact friction bond stress is formed between the composite-edge deep hole milling cutter and a hole wall, so that the cutter head and the cutter body can be fixed conveniently, mounting and dismounting are more convenient, the situation that a common bolt cannot be dismounted due to rusting and thread slipping is prevented, mounting is firmer, and replacement convenience of the composite-edge deep hole milling cutter is improved.

This utility model relates to the field of sedimentation tank anti-clogging technology, and in particular to a magnetically driven self-cleaning sedimentation tank sludge discharge anti-clogging device. Its technical solution includes a pretreatment chamber, on the front of which is equipped with a PLC for control and a sludge discharge valve. The pretreatment chamber contains an anti-clogging structure to prevent equipment blockage. The anti-clogging structure includes a planetary gearbox for adjusting speed and torque, and a motor for driving the device is located on one side of the planetary gearbox. This utility model, through the arrangement of the planetary gearbox, the grid body, and the composite blade, achieves three-level coordinated anti-clogging: fiber stripping, sludge breaking, and sludge pushing, improving the compactness of the structure. The magnetic drive unit enables zero-leakage transmission, fundamentally eliminating media leakage, reducing maintenance costs, and extending equipment life. Furthermore, through the coordinated use of the flushing structure, PLC, and sludge discharge valve, time-limited automatic cleaning can be achieved, reducing energy consumption and lowering operating costs.

The embodiment of the specification provides a regenerative treatment method and system of a composite material blade, the method comprising: controlling a cutting device to cut the composite material blade into blade cutting pieces conforming to a preset size range; monitoring changes in physical property parameters of the blade cutting pieces during a spray cooling process on the blade cutting pieces, and determining a brittle critical point of the blade cutting pieces; determining a target brittle temperature zone of the blade cutting pieces based on the brittle critical point and the preset size range; adjusting spray parameters of a refrigerant, so that the spray cooling process is in the target brittle temperature zone, and brittle blade cutting pieces are obtained; and crushing and screening the brittle blade cutting pieces to obtain regenerated material.

The invention discloses an iterative design method for dynamic characteristics of a carbon nano tube composite material rotor blade, and the method comprises the steps: carrying out the iterative design of the section structure size, material attribute parameters and the change of the material attribute parameters in the radius direction of the blade of the carbon nano tube composite material, and carrying out the calculation to obtain the dynamic characteristics of the blade meeting a design criterion. By changing the mass fraction of the added carbon nanotubes, the inherent frequency of the blade is changed, a new design method is provided for dynamic frequency modulation of the carbon nanotube composite material rotor blade with excellent performance, and the method is suitable for dynamic design of the helicopter rotor blade.

This invention discloses a clamping system for composite blades of aero-engines and its dot matrix support force control method. The clamping system includes a support module, a positioning module, and a clamping module. The positioning and clamping units adopt a dot matrix design. Combined with the support force control method designed for this system, the support force is coordinated and controlled. It can adaptively position and clamp aero-engine blades with different curvatures, and adaptively adjust the attitude of blades of the same type to adapt to existing CNC machining toolpaths. This avoids the complex operation of re-scanning, calculating, modeling, and planning CNC machining toolpaths due to attitude changes. At the same time, it can meet multiple processes in the manufacturing of aero-engine blades, such as blade edge and tenon root machining, simplifying the machining process of aero-engine blades and improving the machining efficiency and quality of blades.

The composite material blade balance structure is arranged on a composite material blade body, the composite material blade body comprises a front edge metal reinforcing edge, the balance structure comprises a tail edge metal reinforcing edge, the tail edge metal reinforcing edge is arranged on the tail edge of the blade body, and the tail edge metal reinforcing edge and the blade body form a complete blade profile. The trailing edge metal reinforcement edge includes a coping region as a balanced de-material region. According to the structure, the balance material removing area can be provided under the condition that the function of the composite material fan blade is not affected, and the balance material removing requirement is met. The utility model further provides a fan blade and an aero-engine.

A method of manufacturing a composite blade with an additional metallic leading edge for a gas turbine aero-engine, comprising: producing a composite blade body (10) comprising, in the longitudinal direction (D L ), a root portion (11), a shank portion (12) and an airfoil portion (13); manufacturing, by additive manufacturing, a leading edge portion (200) extending longitudinally between a lower end (206) present at the shank portion (12) of the composite blade body (10) and an upper end (208) present at a tip end (15) of the airfoil portion (13); bonding the manufactured leading edge (200) to the most forward edge portion (13a) of the airfoil of the composite blade body (10). The leading edge (200) comprises a first portion (210) of a first metallic material extending from the lower end (206) of the leading edge to an intermediate position (207) located between the lower end (206) and the upper end (208) of the leading edge, and a second portion (220) of a second metallic material extending from the intermediate position (207) to the upper end (208) of the leading edge, the second metallic material having a density greater than the density of the first metallic material.

The invention discloses an ultra-deep well efficient rock breaking method based on a special-shaped compact cutting tooth drill bit, and relates to the technical field of deep well rock breaking. The ultra-deep well efficient rock breaking method comprises the following steps that a first state event generated by a geosteering module is obtained; acquiring a second state event generated by a rock breaking parameter optimization module; the cooperative control center calls a preset cooperative strategy matrix for state matching based on the first state event and the second state event, a target cooperative strategy is determined, and the dimension of the cooperative strategy matrix is composed of geological demand strength and rock breaking efficiency strength; according to the target collaboration strategy, a collaboration instruction packet is generated, and the collaboration instruction packet at least comprises a track instruction sent to a track control module and a parameter adjustment constraint instruction sent to a rock breaking parameter optimization module; the cooperative instruction packet is issued to a track control module and a rock breaking parameter optimization module; the stability of the rock breaking efficiency is greatly improved.

The utility model discloses a diamond composite material blade forming die which comprises a pressing ring, a first fixing half block, a second fixing half block, a bottom plate and a mandrel, the first fixing half block and the second fixing half block are spliced to form a hollow cylinder-like structure, and the mandrel is arranged on the inner side of the hollow cylinder-like structure. A circular ring is formed between the hollow cylinder-like structure and the mandrel, a matched bottom plate is arranged at the bottom of the circular ring, a plurality of gaskets with matched sizes are arranged on the circular ring in a sleeving mode through the mandrel, and the outer side of the hollow cylinder-like structure is connected with a pressing ring. According to the blade forming die designed by the utility model, a structure that a plurality of blades are formed by one die is adopted, so that the production efficiency is greatly improved, the production cost of a single piece is reduced, a splicing structure is additionally arranged in the die, the demolding is simple and convenient, and the labor intensity of workers is low. The problems that the blade production efficiency is low and demolding is difficult are solved.

This invention relates to the field of drilling tool technology, specifically to a rotatable composite blade for PDC drill bits, comprising a fixed base and a cutting section. The fixed base has a rotating hole at its front end, and a rotating shaft is coaxially mounted at the rear end of the cutting section. The rotating shaft is rotatably positioned within the rotating hole, with a rotational clearance between the rotating hole and the rotating shaft. A rotating assembly is disposed within the rotational clearance to limit axial displacement between the rotating shaft and the rotating hole. This invention addresses the problem in existing technologies where PDC composite blades are mostly fixed structures, making it impossible to rotate the cutting surface. This results in extremely low overall utilization of the composite blade, requiring frequent tripping and bit replacement, which not only prolongs the drilling cycle but also significantly increases drilling operation costs.