48 results about "Radial distribution" patented technology

The invention relates to the technical field of cable manufacturing, in particular to cable insulation sheath extrusion molding equipment which comprises an extrusion device, and the extrusion device comprises an extrusion head and a rotating assembly. The plurality of convex surfaces are uniformly arranged on the outer wall of the extrusion head along the circumferential direction, so that the radial distribution of the molten material in the flow channel is adjusted, and the molten material is guided to supplement gaps among strands of the multi-strand stranded cable. Meanwhile, the extrusion head is driven by the rotating assembly to rotate, so that the convex surface can adapt to the outline of the outer surface of the cable in real time. Therefore, it is ensured that the thickness of the insulating layer is uniform, the surface of the insulating layer is smooth, the phenomenon that materials are excessively gathered towards gaps or are not evenly distributed is avoided, the electrical hidden danger of an over-thin area is eliminated, material waste of an over-thick area is reduced, and the insulating performance and the material utilization rate of the cable are improved.

A filling device (1) for filling a container with a particulate material (28) comprises a supply container (2) that can be filled with the particulate material (28), wherein the supply container (2) has a lower opening (2.2). Moreover, the filling device (1) comprises a radial distribution unit (3), which can be supplied with the particulate material via the lower opening (2.2) of the supply container (2) and which is connected to the supply container (2) in such a way that it can rotate about a rotational axis (A), in order to distribute in the container the particulate material (28) supplied from the supply container (2) to the distribution unit (3). The filling device is characterized in that the distribution unit (3) can be driven by a drive unit (4) that is arranged outside the supply container (2).

The invention relates to a self-powered detector on-pile test device and method.The device comprises an outer support fixed in a test dry hole channel and an inner support coaxially nested in an inner cavity of the outer support, the outer diameter of the outer support and the inner diameter of the test dry hole channel form micro-tight fit, and the inner support can rotate around the axis relative to the outer support; a first mounting position for mounting at least one standard self-powered detector is arranged on the outer support, a second mounting position for mounting at least one self-powered detector to be detected is arranged on the inner support, and a cross arm is arranged at the bottom of the outer support and used for being in contact with the lower end of the inner support so as to limit the axial insertion position of the inner support. According to the on-pile test device and method for the self-powered detector, single-point calibration errors caused by uneven radial distribution of neutron fluence rates can be effectively eliminated or greatly reduced, and the calibration precision and the representativeness of results are remarkably improved.

The utility model belongs to steam turbine equipment technical field, concretely relates to a steam turbine shaft seal rack assembly tool, and this tool includes: base, is equipped with the arc locating surface that matches with the curvature of shaft seal strip in its inner ring, a pair of support is arranged in both ends of base, the rotating drum is coaxially suspended in the above of arc locating surface with locating surface, the rotating shaft is through rotating drum and is rotatablely arranged on the support in both ends, drive assembly is connected with one end of rotating shaft, wherein, the rotating drum extends along the axial direction of rotating shaft, and there are multiple containing grooves in radial distribution, the containing groove extends along the circumference of rotating drum, covers the rack groove that shaft seal strip sets, and the depth of containing groove is adapted to the height of rack, when drive assembly drives rotating drum to rotate to the direction of arc locating surface, the lug of rack circumference is embedded in the rack groove.

The invention discloses a gas distribution device and semiconductor film equipment, the gas distribution device is arranged above a spraying plate, the gas distribution device comprises a gas distribution piece and a gas distribution valve island, the gas distribution piece is internally provided with a plurality of annular flow channels which are distributed at intervals in the radial direction and are concentrically arranged, and the annular flow channels are communicated with the spraying plate. A plurality of air outlet holes axially penetrating through the air distribution piece are uniformly formed in each annular flow channel in the circumferential direction; the air distribution valve island comprises a plurality of air distribution valve sets connected with the annular flow channels in a one-to-one correspondence mode, and each air distribution valve set independently controls connection and disconnection of the corresponding annular flow channel. According to the invention, the gas distribution piece with a plurality of independent controllable annular flow channels is arranged above the spraying plate above the wafer, so that the on-off and gas flow of the corresponding annular flow channels can be accurately controlled through the gas distribution valve island according to the radial distribution requirement of the wafer film thickness in the technological process; independent adjustment of reaction or diluent gas flow in different radial intervals is realized, so that the film thickness uniformity of each area of the wafer is adjusted in a targeted manner, and the increase or decrease of the film thickness in the specified radial interval is realized.

The utility model discloses a karting boat relates to karting boat technical field. The karting boat includes the hull and the propeller, and the propeller includes the casing, the motor, the connecting rod, the impeller, the first flow guide and the second flow guide, and the motor drives the rotation of the impeller, and the water flow is inhaled from the casing side wall water inlet, and the water flow is formed after the acceleration of the impeller and is rotated jet. Rotating water flow first hits the first flow guide piece, and the first flow guide piece of radial distribution divides the water flow into multiple sub flow channels, and forces the water flow to discharge along the axial direction. Subsequently, the water flow enters the second flow guide area, and the taper structure makes the flow passage cross section area gradually reduce, and the water flow speed improves, and finally the water flow is sprayed from the water outlet in the approximate straight line form. Through the first flow guide, the preliminary rectification is realized, and the second flow guide carries out secondary despinning to the central vortex, and the synergistic effect is formed, and the second flow guide piece produces the reverse moment, converts the rotation energy into the additional thrust, and can improve the power of the propeller.

The present disclosure relates to the technical field of flow tube calibration, and particularly relates to a flow tube calibration data processing method. The flow tube calibration data processing method comprises: determining a piecewise linear function of radial distribution of boundary total pressure P s and total pressure P t within a boundary layer based on measured static pressure P tbl_cri and total pressure P tbl at a measurement section of a flow tube; and determining a thickness δ of the boundary layer based on the determined piecewise linear function of radial distribution of boundary total pressure P tbl_cri and total pressure P tbl within the boundary layer. Thus, the deviation caused by the distance between adjacent measurement points can be reduced, the thickness of the boundary layer can be more accurate, and the accuracy of the flow tube calibration result can be effectively improved.

The application discloses a distortion generator arranged in an engine case, which comprises a plurality of threaded rods arranged between an inner case and an outer case of the engine case along the radial direction of the engine case, nuts arranged on and engaged with the threaded rods, distortion members respectively connected to the nuts of different threaded rods at two ends along the length direction, the distortion members being elastic along the length direction, and a driving mechanism connected to the threaded rods and used for driving the threaded rods to rotate. When the driving mechanism drives the threaded rods to rotate, the position of the nut arranged on the threaded rod in the engine case can be changed, the distortion member connected to the nut is stretched or shrunk, and the position of the distortion member in the engine case is changed, so that the adjustment of the position of the distortion structure in the case is realized, different total pressure radial distribution rules are simulated, and the experimental period of an air intake experiment is shortened.

The utility model discloses a caliber-adjustable silage bagging device, which belongs to the technical field of silage filling, and realizes dynamic adjustability of connecting caliber by arranging caliber adjusting devices with the same structure at two ends of an elastic connecting pipe and combining a plurality of radially distributed telescopic rods and driving mechanisms matched with the telescopic rods. The telescopic rod drives the elastic connecting pipe with flexible deformation capacity, the caliber of the elastic connecting pipe expands or contracts along with the telescopic rod in the telescopic process, the telescopic rod can be effectively attached to the outlines of the filling machine and the ensiling bags, and the device is simple in structure, convenient to adjust, capable of adapting to the ensiling bags with different calibers and high in practicability. And the connecting sealing performance and the filling stability are improved, and the silage filling device is suitable for various silage filling working conditions.

The application provides a heavy gas turbine air-cooled turbine aerodynamic layout design method and system, electronic equipment and a storage medium. The method comprises the following steps: step 1: obtaining the design requirements of the heavy gas turbine air-cooled turbine, and determining the turbine stage number; step 2: determining the enthalpy drop and load distribution scheme of each turbine stage; step 3: performing preliminary evaluation on the stress of the blade and the disc, if the requirement is not met, adjusting the load coefficient and the flow coefficient, if the requirement is met, entering step 4; step 4: initial meridian flow passage design, evaluating the strength of the blade and the disc after the meridian flow passage design is completed, if the requirement is not met, repeating steps 2 to 4 to perform parameter optimization, if the requirement is met, entering step 5; step 5: determining the radial distribution law of the turbine stage reaction degree; step 6: determining the radial distribution law of the aerodynamic parameter according to the one-dimensional average parameter design result; step 7: S2 inverse problem calculation; and step 8: aerodynamic performance analysis and optimization. The scheme provided by the application shortens the turbine engineering design cycle.

The application discloses a novel connecting structure for large-span steel-bamboo buildings, and belongs to the technical field of large-span buildings. The connecting structure comprises a supporting body which is formed by mutually splicing a plurality of connecting units, long steel-bamboo poles are connected to the periphery of the supporting body, a central lifting point is arranged directly above the supporting body, and a plurality of lifting pieces are connected between the supporting body and the central lifting point. The connecting unit comprises a plurality of short steel-bamboo poles which are in equal-angle radial distribution and are connected at the ends, and the ends of the short steel-bamboo poles are fixed through connecting nodes. Two adjacent connecting units are connected through the connecting nodes or through a shared short steel-bamboo pole. The novel connecting structure for large-span steel-bamboo buildings fully utilizes the initial vertical form of natural steel bamboo, and combines the novel connecting node to form a novel building structure system, which is characterized by low cost, structural safety and building aesthetics, and can be used for large-span steel-bamboo buildings.

The present invention relates to a flow distributor for a parallelized microfluidic chip system, adapted for the individual feeding of a large number of microfluidic channels. In particular, the invention proposes a distributor comprising at least one radial flow distribution channel, said channel having a central opening leading into peripheral openings distributed circularly around an axial center of said distributor, characterized in that: - the distributor comprises a support in the form of a regular cylinder, preferably circular, in which said at least one radial distribution channel is integrated, and such that - the peripheral openings are distributed on vertical walls of said support to convey a flow into or out of said distributor along a horizontal flow plane.

A chemical mechanical polishing system includes a chuck assembly that has a chuck to hold a substrate, a motor to rotate the chuck about a first axis, and a pad carrier assembly. The pad carrier assembly includes a support that is movably along a radial direction relative to the first axis, a lateral actuator coupled the support to cause the support to move along the radial direction, a support arm extending from the support over the chuck, a pad carrier suspended from the support arm, the pad carrier configured to receive and hold a polishing pad, and a flexible membrane secured to the support arm to form a plurality of individually pressurizable chambers between the pad carrier and the support arm such that variation of a pressure difference between the chambers adjusts a radial distribution of pressure on the pad carrier.

The invention provides an aerodynamic layout design method and system for an air-cooled turbine of a heavy-duty gas turbine, electronic equipment and a storage medium, and the method comprises the following steps: 1, obtaining the design requirement of the air-cooled turbine of the heavy-duty gas turbine, and determining the stage number of the turbine; 2, determining an enthalpy drop and load distribution scheme of each turbine stage; 3, preliminarily evaluating the stress of the blade and the wheel disc, if the requirement is not met, adjusting the load coefficient and the flow coefficient, and if the requirement is met, entering the step 4; 4, primary meridian flow channel design is conducted, the strength of the blades and the strength of the wheel disc are evaluated after the meridian flow channel design is completed, if the requirements are not met, the second step to the fourth step are repeated for parameter optimization, and if the requirements are met, the fifth step is conducted; 5, determining the radial distribution rule of the reaction power of the turbine stage; step 6, determining a radial distribution rule of the aerodynamic parameters according to a one-dimensional average parameter design result; step 7, S2, inverse problem calculation; and step 8, analyzing and optimizing aerodynamic performance. According to the scheme, the design period of turbine engineering is shortened.

The utility model discloses a fan framework which comprises a main body, and the main body is provided with a center installation position used for being connected with a motor driving shaft. The mounting parts and the main body are integrally and uniformly arranged in the circumferential direction of the central mounting position at intervals, and the mounting parts approximately extend in the radial direction and are used for being connected with blades; wherein the main body and the plurality of mounting parts jointly form a first extension surface and a second extension surface which are approximately distributed along the radial direction, and the first extension surface sinks relative to the second extension surface. According to the technical scheme, the common surface of the main body of the fan framework and the mounting part integrated with the main body is divided into two extension surfaces, and one extension surface sinks relative to the other extension surface, so that the strength of the framework with the same material and the same thickness can be obviously improved at the joint of the two surfaces, damage to the framework can be reduced, and the service life of the framework is prolonged. Therefore, the purposes of reducing the fan blade cost and improving the fan efficiency are achieved while the thickness of the framework is reduced.

The application relates to a thread tool grinding method, device and numerical control equipment. The method comprises the following steps: determining the intersection between the chip flute edge line on the outer cylindrical surface of a blank and a thread guide line; determining the circumferential machining range of a machining track section from the intersection based on a machining range parameter; determining the axial distribution of the thread guide line along the tool axis within the circumferential machining range as the axial distribution of the machining track section along the tool axis from the intersection; decreasing the bottom surface circle radius of the blank along the circumferential deflection angle relative to the intersection based on a radial clearance angle parameter to obtain the radial distribution of the machining track section along the tool radial direction from the intersection; and determining the grinding track of a grinding wheel on the blank when grinding thread teeth based on the geometric parameters of the grinding wheel and the radial distribution and axial distribution of the machining track section. The method can ensure the grinding efficiency of the thread tool.

The utility model relates to the technical field of semiconductor manufacturing equipment, specifically disclose a tray structure for silicon carbide epitaxial equipment, including tray base, the concentric circle arrangement of multiple wafer bearing positions is provided with in the upper end surface of circular tray base, each wafer bearing position is the recessed structure of ladder, including embedding setting bottom support ring in the upper end of circular tray base, the inclined transition surface is connected with the upper surface of tray base the outer edge of bottom support ring's upper end surface, through recessed bearing position structure of ladder, the risk of wafer thermal deformation breakage is reduced significantly, radial flow guide groove optimizes reaction gas radial distribution uniformity, and the composite structure of graphite matrix and silicon carbide coating and the processing of round corner edge are matched, effectively improve the anti -peeling ability of coating and equipment service life under high temperature working condition, finally realize the synchronous improvement of epitaxial layer thickness consistency and production yield.

The utility model relates to a cooling structure, turbulence unit and turbine blade relates to aircraft technical field to solve the problem of turbine blade trailing edge cooling performance is poor, radial distribution uneven in the prior art. The cooling structure of the utility model, including turbulence rib and turbulence column, the periphery of turbulence rib sets at least 2 turbulence columns. The utility model can increase the contact area between turbine blade pressure side wall surface and suction side wall surface, thereby enhancing the pressure -bearing capacity of turbine blade, and promoting structural strength.

The invention discloses a variable geometry turbine guider blade combined winglet structure and a design method and application thereof, the variable geometry turbine guider blade combined winglet structure comprises a blade body and a combined winglet arranged on the blade body, and the blade body is divided into a front edge section, a gap section and a tail edge section by taking the axial start-stop position of a rotating shaft local gap as a reference. The combined winglet is composed of a front side leakage control module and a rear side leakage control module which are arranged on the blade surface main control areas of the front edge section and the tail edge section correspondingly, and cooperative control is carried out on leakage sources on the front side and the rear side of the rotating shaft. Each leakage control module comprises a main section offset curve and a bridging transition curve in a two-dimensional plane, and the bridging transition curve is used for smoothly connecting the offset curve with the prototype molded line. The design method comprises the steps of blade modeling, section division, leakage analysis, configuration selection, molded line design, radial distribution and the like. The problem of leakage suppression of a local gap formed by the rotating shaft and the end wall is solved, leakage jet flow and induced vortex interference can be effectively weakened, and the method is suitable for leakage control of a wide-working-condition high-load variable geometry turbine.

The application discloses a kind of linear defect depth's ray detection calculation method, comprising the following steps: special positioning mark is made;Special positioning mark includes several with the same point as center outward radial distribution branch;Part is once penetrated, and once penetrated negative is obtained, and the object distance f and focal length F are determined;Linear defect fitting line is obtained by linear fitting to linear defect on once penetrated negative, according to the direction of linear defect fitting line, the branch of special positioning mark is selected and is parallel to linear defect fitting line, and the vertical distance L1 of the branch of special positioning mark and linear defect fitting line is measured;According to the normal direction of linear defect overall trend, part is parallelly displaced, and the parallel displacement distance W is displaced;Part after parallel displacement is twice penetrated, and twice penetrated negative is obtained, and linear defect fitting line is obtained by linear fitting to linear defect on twice penetrated negative, the branch of special positioning mark is selected and is parallel to linear defect fitting line, and the vertical distance L2 between the branch of special positioning mark and linear defect fitting line is measured;Linear defect depth is calculated according to the following public demonstration:。

The present application belongs to the field of measuring the plume divergence angle of the gasification product of a thruster, and particularly relates to a method for measuring the plume divergence angle of the gasification product of a solid propellant after ignition, comprising the following steps: obtaining a background image before ignition of the solid propellant and a gasification product inflation movement image during the ignition process; comparing the background image and the gasification product inflation movement image to obtain a gasification product image; solving the radial distribution of radiation intensity on N cross sections of the gasification product image; determining the maximum intensity value on each cross section and calculating the position of 98% maximum intensity value on each cross section; using the least square method to perform linear regression on the positions of all 98% maximum intensity values, calculating the slope of the regression straight line, and calculating the plume divergence angle of the gasification product according to the slope of the regression straight line. The plume divergence angle measurement method provided by the present application ensures measurement efficiency and high measurement accuracy.

The application relates to a design method for deriving and developing a downward flow path of an aero-engine axial flow compressor, which comprises the following steps: step one, downward pressing of compressor inlet and outlet hubs, namely, downward pressing of inner flow paths of the compressor inlet and outlet; step two, re-determination of the compressor hub flow path according to the downward pressing amount of the compressor inlet and outlet hubs; step three, re-determination of the compressor casing flow path while keeping the compressor flow path area unchanged; step four, re-determination of the design rotating speed of the compressor while keeping the compressor rotating speed inlet blade tip tangential velocity unchanged; step five, adjustment of the blade profile of each stage of rotor and stator blades while keeping the compressor stage pressure ratio, efficiency and radial distribution unchanged; step six, adjustment of the inlet pre-whirl angle of each stage while keeping the compressor rotor counterforce unchanged; and step seven, checking of the radial distribution of the diffusion factors of each stage of the compressor rotor and stator, and if the radial distribution exceeds the engineering applicable value, returning to step one, adjusting the downward pressing amount of the compressor inlet and outlet hubs and performing iterative optimization.

A chemical mechanical polishing system includes a chuck assembly that has a chuck to hold a substrate, a motor to rotate the chuck about a first axis, and a pad carrier assembly. The pad carrier assembly includes a support that is movably along a radial direction relative to the first axis, a lateral actuator coupled the support to cause the support to move along the radial direction, a support arm extending from the support over the chuck, a pad carrier suspended from the support arm, the pad carrier configured to receive and hold a polishing pad, and a flexible membrane secured to the support arm to form a plurality of individually pressurizable chambers between the pad carrier and the support arm such that variation of a pressure difference between the chambers adjusts a radial distribution of pressure on the pad carrier.

The invention discloses a tooth surface machining process for shaft workpieces, and belongs to the technical field of machining. The method comprises the following steps: machining radially-distributed first tooth surfaces of a plane tooth shape on a first flat plate through a grinding machine to form a first gear rolling plate half body; and a second tooth surface which is obliquely arranged in an inclined surface tooth form is machined on the side edge of the second flat plate to form a second gear rolling plate half body. And the two half bodies are aligned, spliced and fixed to form the complete gear rolling plate. The rolling device is installed on rolling equipment, arranged on the two sides of a workpiece respectively and moves oppositely, the surface of the workpiece is extruded, and a rack which extends along the axis and is provided with a taper angle at the tooth end is rolled. The gear rolling plate is divided into the first gear rolling plate half body in the plane tooth shape and the second gear rolling plate half body in the conical tooth shape to be machined respectively, and then the first gear rolling plate half body and the second gear rolling plate half body are aligned and spliced, so that the technical problem that a tooth end taper angle structure is difficult to manufacture through a traditional integral gear rolling plate is solved, and a taper angle tooth end with a leading-in function can be stably and reliably rolled on a workpiece; the assembly performance is improved.

The utility model discloses a spiral-based device for measuring the inner diameter of a steel pipe, which comprises a measuring disc and a driving disc which are coaxially arranged, and the measuring disc is rotatably connected with the driving disc; a plurality of sliding rulers which are radially distributed by taking the circle center of the measuring disc as the center are arranged on the measuring disc along the circumferential direction, and the sliding rulers are in sliding connection with the measuring disc; and the sliding ruler can move along the radial direction to extend out of the edge of the measuring disc under the rotation action of the driving disc. According to the device for measuring the inner diameter of the steel pipe, the plurality of sliding rulers can extend out by driving the driving disc to rotate, so that when the end parts of all the sliding rulers are in contact with the inner wall of the steel pipe at the same time, the inner diameter of the steel pipe at each time can be visually observed; meanwhile, if the inner wall of the steel pipe is uneven, the position of the measuring disc can be rotated to enable the sliding ruler not to be in contact with the sunken part, so that a worker can accurately observe and record data.

The utility model relates to the technical field of cycloid motors, in particular to a shaft flow distribution cycloid hydraulic motor which comprises a body shell, a front cover, a rear cover, a rotor and stator pair and an output shaft, a flow distribution channel is formed in the arc-shaped face of the outer side of the output shaft, a radial flow distribution hole matched with the flow distribution channel is formed in the body shell, and the radial flow distribution hole is of an oval structure. According to the axial flow distribution cycloid hydraulic motor, the radial flow distribution holes are designed to be oval, so that the flow distribution channels can be gradually opened and closed, the situation that due to position errors of the flow distribution grooves, the opening of the flow distribution channels is advanced or lagged in the working process of the motor is avoided, and pressure pulsation is reduced; and the arc-shaped guide inclined surfaces are arranged at the inner side ends of the flow distribution channels, so that hydraulic noise can be reduced.

The invention belongs to the technical field of aero-engine multi-duct compression component design, and particularly relates to an aero-engine multi-duct compression component S2 flow field design pressure ratio optimization method which comprises the steps that firstly, radial distribution of all stages of pressure ratios of a multi-duct compression component under all working conditions is obtained; secondly, radial distribution of the pressure ratios of all levels of the multi-duct compression component under all the working conditions is adjusted, and the average value of the radial distribution of the pressure ratios of all levels of the multi-duct compression component under all the working conditions is made to be equal to the S2 flow field design pressure ratio of the corresponding level; and 3, for each stage of multi-duct compression component, calculating the arithmetic average of the pressure ratios of different blade heights under each working condition, and correcting the radial distribution of the designed pressure ratio of the S2 flow field.

The utility model discloses a double-channel expander which comprises a pipe part, a first partition plate and a head part. A guide wire cavity is formed in the tube part, the first partition plate is arranged in the guide wire cavity and divides the guide wire cavity into a first containing cavity and a second containing cavity which are distributed in the radial direction of the guide wire cavity, the head part is arranged at one end of the tube part, and a first penetrating hole communicated with the first containing cavity and a second penetrating hole communicated with the second containing cavity are formed in the head part. According to the double-channel dilator, the hollow pipe part is used for forming the main body part of the double-channel dilator, so that the weight of the double-channel dilator is greatly reduced, the production cost of the double-channel dilator is reduced, the operation difficulty of an operator is reduced, and the working intensity of the operator is reduced.

The utility model provides an integrally cast end cover of a motor, and belongs to the technical field of machinery. The problem that an existing end cover is poor in structural stability is solved. The motor integrally-cast end cover comprises an end cover body, the middle of the end cover body is a bearing seat with an approximately U-shaped axial section, the bearing seat comprises an inner ring and an outer ring which are distributed in the radial direction, an inner hole of the inner ring is a bearing hole, a circle of rib plate is formed between the inner ring and the outer ring, and the two sides of the rib plate extend to the inner side wall of the inner ring and the outer side wall of the outer ring respectively; a plurality of strip-shaped grooves are formed in the side wall of the inner ring in the radial direction in a penetrating mode, extend in the axial direction of the inner ring in the length direction and are evenly distributed in the circumferential direction of the inner ring. The integrally-cast end cover of the motor is stable in structure.

The invention belongs to the technical field of pressure reducing valves, and particularly relates to a non-uniformly distributed and asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve. According to the technical scheme, the nozzle comprises a nozzle body, a bearing handle, an ejector pin, a high-pressure spring, a positioning rivet and a sealing gasket. The angle difference delta is 8 degrees, namely, the angle a of the first central angle is 128 degrees, the angle b of the second angle is 120 degrees, and the angle c of the third angle is 112 degrees. The non-uniformly distributed and asymmetric nozzles are created for the first time, through non-uniform and asymmetric radial distribution of 112 degrees, 120 degrees and 128 degrees, moderately non-uniform enhanced vortex flow is formed in the low-pressure cavity through the nozzles, and the rotation stability effect is improved. Compared with turbulent flow caused by other designs (single nozzle, uniformly distributed nozzle and symmetrically distributed nozzle), the enhanced vortex flow generated by the design can eliminate uncertainty caused by the turbulent flow, and the output airflow can be more regular and more stable.