1168 results about "Suction surface" patented technology

An airfoil is provided that includes a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side. The leading edge and the trailing edge are joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil. The exterior airfoil surface are formed in conformance with a plurality of cross-section profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location.

The invention relates to the technical field of grabbing manipulators, and discloses a self-adaptive grabbing device for a special-shaped curved surface workpiece, which comprises a central bearing base made of a light metal material and provided with a multifunctional quick connector at the top; the central adsorption module is fixed at the central position of the bottom of the central bearing base and comprises an air pressure balance pipeline communicated with an external air source; by means of radial adjustment of the cross shaft and cooperation of the elastic buffering structure and the vertical guiding assembly, high-precision centering and stable adsorption are achieved, vertical contact of the suction cup is ensured through vertical guiding, the suction cup is suitable for different curved surface radians, and the stable adsorption force under the small area is kept; and electric control connection supports installation, namely electrification, and is suitable for automatic precise grabbing.

The invention discloses a honeycomb cross rib cooling structure for the trailing edge of a turbine blade, the structure comprises a suction surface, a pressure surface, a crack cavity and honeycomb cross ribs, the suction surface and the pressure surface are opposite in position, the crack cavity is formed between the suction surface and the pressure surface, the honeycomb cross ribs are arranged in the crack cavity, and the honeycomb cross ribs ensure that cooling gas fully exchanges heat; and the honeycomb cross ribs are high in structural strength, so that the structural strength is improved at the thin layer of the trailing edge.

Disclosed is a negative pressure suction-based fixing device comprising a housing, a suction and holding member, a negative pressure creating assembly and a sealing member. The housing has an accommodating cavity thereinside. The suction and holding member has an abutting and holding surface recessed to form a suction cavity communicated with the accommodating cavity. The abutting and holding surface has a mounting structure connected to the sealing member, so that the sealing member is arranged on the abutting and holding surface for abutting against the suction surface. The sealing member can be elastically deformed to fit with the suction surface so as form an enclosed space together with the cooperation of the suction cavity and the suction surface. In this way, it is difficult for the negative pressure suction-based fixing device to fall off from a rough surface.

The utility model relates to the technical field of axially split pumps, in particular to an axially split pump impeller with offset blades and an axially split pump. The axially split pump impeller with the offset blades comprises a front cover plate, a hub, a plurality of long blades and a plurality of short blades, the hub is arranged in the front cover plate, and the long blades and the short blades are arranged between the hub and the front cover plate; the multiple long blades are evenly arranged around the axis of the impeller, and the short blades are arranged between every two adjacent long blades. Projections of one end, far away from the axis of the impeller, of each long blade and one end, far away from the axis of the impeller, of each short blade in the axial direction of the impeller are distributed on the circumference of the same circle; each short blade is provided with a pressure face and a suction face which are opposite. According to the axially split pump impeller with the offset blades, the flow field in the blade channels can be improved, the pressure gradient of an outlet of the impeller can be greatly reduced, the wake flow area of the outlet of the impeller is reduced, and smooth transition of the speed and pressure from the wake flow area to a jet flow area is achieved.

The invention discloses a method for rapidly predicting and dynamically regulating and controlling the quality of a flow field of a gas compressor under a low Reynolds number. According to the method, firstly, pressure gradient parameters Ks of a blade suction surface laminar flow separation point under different Reynolds numbers are obtained through high-precision performance testing / numerical calculation, and then experience prediction models of the Ks, an incoming flow Reynolds number Re, a separation point momentum thickness Reynolds number Re theta s, a blade surface separation scale and boundary layer development characteristics are sequentially established; and the influence of the low Reynolds number effect on the separation bubble structure and the boundary layer growth rate is quantified, so that the performance degradation degree of the gas compressor under the low Reynolds number can be quickly predicted. Based on the model, parameters such as excitation frequency of the front edge deformation surface of the blade are optimally configured, periodic pressure disturbance waves are induced to be generated, and dynamic regulation and control of large-scale separation flow under the low Reynolds number are achieved. The prediction speed of the performance variation of the gas compressor under the low Reynolds number is increased, and support is provided for aerodynamic design and performance regulation and control of the high-altitude gas compressor.

A substrate is reliably suctioned regardless of a flatness of a surface to be suctioned of the substrate. A substrate suction member 330 includes a porous member 334 including a substrate suction surface 334a for suctioning a substrate WF and a pressure reducer 334b communicating with pressure reducing means, a shielding member 332 including a first shielding member 332-1 configured to shield a surface 334c in an opposite side of the substrate suction surface 334a of the porous member 334 and a frame-shaped second shielding member 332-2 configured to shield at least a part of a side surface 334d of the porous member 334, and a frame-shaped elastic seal member 336 attached to the second shielding member 332-2 so as to surround the porous member 334 and provided with a contact surface 336a in contact with the substrate WF.

The invention provides a blade winglet control method and system for three-dimensional flow field analysis of a wind turbine blade, and relates to the technical field of intelligent control, and the method comprises the steps: solving a hydrodynamic equation through a numerical solution to generate three-dimensional speed, pressure and temperature distribution data of a blade surface; according to the speed, pressure and temperature data, the aerodynamic performance and the flow failure mode of the blade tip are recognized, so that the flow state of the blade area is obtained; the flow state of the blade area is analyzed to obtain geometric parameters of the winglet, and the geometric parameters comprise the length, the width, the installation angle and the shape; according to the geometric parameters of the winglets, the installation positions of the winglets are obtained, and the winglets comprise the pressure surface winglet and the suction surface winglet. According to the invention, the instability of airflow can be reduced, vortex and noise are reduced, noise emission during operation of the wind turbine is effectively reduced, and the environmental adaptability of the wind turbine is improved.

The utility model provides a blade for a centrifugal fan, a double-suction centrifugal impeller applying the blade and the fan. The blade comprises a suction surface wall, a pressure surface wall, a front edge, a rear edge, a convex air inlet part and a concave air outlet part, the suction surface wall and the pressure surface wall are arranged back to back and extend in the length direction of the blade firstly and then extend between the front edge and the rear edge; the protruding air inlet part is formed in the mode that the front edge part of the blade protrudes towards one side of the suction surface wall, the concave air outlet part is formed in the mode that the rear edge part of the blade protrudes towards one side of the pressure surface wall, and the protruding air inlet part and the concave air outlet part are connected in the direction from the front edge to the rear edge. In the length direction of the blade, the convex air inlet part is of a structure with high middle and two low sides, and the concave air outlet part is of a structure with low middle and two high sides; in the direction from the front edge to the rear edge, the middle height of the convex air inlet part is in a decreasing trend; and in the direction from the rear edge to the front edge, the middle height of the sunken air outlet part is in a decreasing trend.

The invention discloses a method for quickly generating a compressor blade profile containing local geometric deviation. The method comprises the following steps: determining a mean camber line point and thickness distribution according to geometric data of a suction surface and a pressure surface; determining parameterized expression of the mean camber line geometry according to the camber line points, and obtaining parameter expression of a thickness distribution curve according to the thickness distribution; generating pressure surface geometric points and suction surface geometric points containing local geometric deviation based on parameterized expression of mean camber line geometry and parameterized expression of the thickness distribution curve; a blade profile leading edge curve and a blade profile trailing edge curve are generated; and integrating the curve data to generate the blade profile containing the local geometric deviation. The blade obtained on the basis of the method contains the local geometric deviation, control over the machining deviation of the blade is facilitated, and the method has great significance in determining the influence of the typical geometric deviation of the blade on the aerodynamic characteristics of the gas compressor through simulation calculation.

The utility model relates to the technical field of air conditioners, and discloses an axial flow fan and an air conditioner. The axial fan includes a blade including: a blade body; and the flow guide structure is positioned on the suction surface of the blade main body and is arranged at the root of the blade main body. The distance between the flow guide structure and the blade outer edge is larger than that between the flow guide structure and the blade inner edge, that is, compared with the blade tip, the flow guide structure is closer to the blade root. In the rotating process of the fan, the flow guide structure can guide air flow to flow and scatter the air flow, so that an area with higher pressure at the root of the blade can be divided into a plurality of small areas, the pressure of each small area is reduced, channel vortexes can be inhibited, and the operation noise of the axial flow fan is reduced to a greater extent.

The invention provides a pump blade structure, a pump body and an air conditioner, the pump blade structure comprises a plurality of blades and a rotating shaft, the blades are arranged on the rotating shaft, the multiple blades are arranged at intervals in the circumferential direction of the rotating shaft, each blade comprises a tail edge, a suction surface and a pressure surface, and the suction surfaces, the tail edges and the pressure surfaces are sequentially connected; the suction surface is provided with a line type S1, the pressure surface is provided with a line type P1, the line type S1 and the line type P1 are arc lines in smooth transition, the tail edge is provided with a chord line, the chord line is perpendicular to the line type S1, and the chord line is perpendicular to the line type P1. According to the invention, the technical problem of low lift of the water pump in the prior art can be solved.

The present invention provides a noise reduction blade and a fan thereof, which relates to the technical field of fan devices, including a wind wheel blade, the wind wheel blade including a blade pressure surface, a blade suction surface, a blade leading edge and a blade trailing edge; the blade leading edge adopts a corrugated noise reduction design, and the blade is designed with corrugated noise reduction in both the circumferential and axial directions from the blade tip to the blade root. The present invention designs corrugations in the circumferential and axial directions on the blade leading edge, so that the blade leading edge has airflow inlet angles of different angles from the blade tip to the blade root, so that when the airflow enters the wind wheel blade, it interacts with the blade leading edge to generate pressure pulsations in different directions, which can effectively reduce the fan inlet noise; the blade is designed with corrugations in the circumferential and axial directions from the blade tip to the blade root, so that an airflow guide flow channel from deep to shallow from the blade leading edge to the blade trailing edge can be formed on the blade pressure surface and the blade suction surface, which can increase the blade strength, and can also play a role in guiding the airflow so that the airflow flows more evenly on the blade surface, thereby achieving the effect of improving the fan efficiency and reducing noise.

The invention relates to the technical field of axial flow fans, in particular to an impeller with S-shaped blades and an axial flow fan applying the impeller. On the axial projection of the impeller, the peripheral contour of each blade is defined by a blade root edge, a blade front edge, a blade outer edge and a blade rear edge, and the blade root edge is connected with the hub; the blade front edge and the blade rear edge are both wavy curves, and the blade root edge and the blade outer edge are both arc-shaped lines with the axis O of the hub as the circle center. Each blade is provided with a pressure face and a suction face, the pressure faces and the suction faces are oppositely arranged, and on the radial projection of the impeller, the pressure faces are arranged in a wave shape in a protruding mode from one end of the blade root edge to one end of the blade rear edge towards the suction faces and then concavely arranged, so that the blades are of an S-shaped structure. The problem that a traditional blade structure cannot meet the use requirements of high efficiency and low noise can be solved.

To provide an axial flow turbine which can be improved in the overall efficiency.SOLUTION: An axial flow turbine includes: a turbine shaft; a turbine rotor blade row; and a turbine housing having an exhaust chamber on a downstream side of the turbine rotor blade row. The turbine housing includes a flow guide portion having an inner peripheral-side wall surface forming a diffuser flow path for guiding the working fluid that has passed through the turbine rotor blade row to the gap from an inner wall of the exhaust chamber in a radially outward side. When a minimum distance between a rear edge end and a negative pressure surface of the other adjacent turbine rotor blade is denoted as throat s, a pitch of the plurality of turbine rotor blade is denoted as t, a blade height position at a blade root is 0%, and the blade height position at the blade tip end is 100%, a distribution of throat / pitch ratio in a blade height direction having a throat / pitch ratio at the 25% blade height position is smaller than a line segment between the blade root portion and a center portion in the blade height direction, and a throat / pitch ratio at the 75% blade height position is smaller than a line segment between the center portion and the blade distal end portion.SELECTED DRAWING: Figure 3

The utility model discloses a ducted fan, which belongs to the technical field of aviation ducted fan engines, and comprises an annular duct, a plurality of blades and a plurality of blades, the fan blades are arranged in the annular duct, blade tip arc surfaces are arranged at the blade tips of the fan blades, and blowing gaps are formed in the sides, close to the suction surfaces, of the fan blades; the fan blades are fixedly connected to the outer side of the fan shaft; the driving part is used for driving the fan shaft to rotate, and the driving part is arranged on the rear side of the annular duct; the ratio of the height of the air blowing seam to the diameter of the arc surface of the blade tip is set to be 0.01-0.05; an air flow channel is formed in the fan blade and communicates with the air blowing seam. The number of the fan blades is two or more. The interior of the fan shaft is of a hollow structure. According to the utility model, the blade top clearance leakage flow is reduced by blowing at the top ends of the blades, so that the propulsion efficiency of the ducted fan is improved.

The invention discloses a non-overload centrifugal impeller with the characteristic of reducing pressure pulsation, which belongs to the technical field of non-overload centrifugal pumps and comprises a wheel disc, and a plurality of blades are fixedly connected to the circumference of the wheel disc; the part from the tail edge of the blade to the front edge of the blade is hollowed out to form a pulse pressure buffer area, the pulse pressure buffer area is located between the pressure face and the suction face of the blade, and the pulse pressure buffer area penetrates through the tail edge of the blade but does not penetrate through the front edge of the blade. The pulse pressure buffer area is arranged, so that instantaneous pressure change caused by local flow channel contraction can be absorbed and dispersed, and the peak value of pressure waves is effectively stabilized through compressibility, viscosity and inertia of fluid; therefore, the phenomenon of periodic pressure change caused by contraction of a local flow channel between the blade and the baffle tongue is relieved.

The invention discloses a variable geometry turbine guider blade adjusting structure and method and application, through cooperative adjustment of a slidable clamshell-shaped suction surface and a rotatable tail flap, the front thickness, the aerodynamic configuration and the throat area of a turbine blade are accurately controlled, and therefore wide-range flow adjustment is achieved. The pressure surface side fixing part provides a stable supporting and flowing path through a pressure surface section, a front end groove and a tail semicircular arc surface which are integrally formed. The slidable clamshell-shaped suction surface is connected with an external driving source and can slide along the front-end groove to adjust the shape of the blade; the rotatable tail flap further optimizes the flow regulation by rotating to regulate the shape of the throat area at the tail of the blade. According to different working condition requirements, the clamshell-shaped suction surface and the tail flap can be adjusted independently or in a linkage mode, high efficiency and stability of the turbine guider blade under different flight working conditions are guaranteed, and meanwhile the turbine guider blade has good thermal protection performance and high-temperature tolerance.

The utility model provides an impeller structure with baffles at outlet parts of folded blades and a vortex pump. The impeller structure comprises a rear cover plate, a plurality of folded blades on the front end face of the rear cover plate, a plurality of back blades on the rear end face of the rear cover plate, the baffles on the folded blades and a hub in the center of the rear cover plate. The folded blade comprises a long blade section and a short blade section which are connected with each other, the baffle plate is vertically arranged on a pressure surface and / or a suction surface of the short blade section, the width of the baffle plate is b0 = (1-2) t, the thickness of the baffle plate is t0 = (0.5-0.8) t, b0 is the width of the baffle plate, t0 is the thickness of the baffle plate, and t is the thickness of the folded blade. The baffle is arranged at the outlet part of the folded blade, so that fluid can be better guided to flow to the outlet, abrasion and blockage caused by the fact that a medium in a vaneless cavity flows into a blade channel are reduced, flow state disturbance and hydraulic loss of the blade channel are reduced, and the conveying efficiency of the vortex pump is improved.

A device has a rotor module comprising a motor generator, rotor blades, and a rotary-wing kinematic system for the rotor blades connected to the motor generator. The rotor blades are each divided into a plurality of longitudinal sections, each for receiving at least one actuator integrated in a longitudinal member or transverse member of the rotor blade, and have a variable, asymmetrical airfoil which, in one revolution of the rotor blade on a diameter of the circular path, the diameter being freely orientable within an adjustment range and having turning points, can be adjusted in at least one longitudinal section of the rotor blade with a length in such a way that the suction surface and the pressure surface of the asymmetrical airfoil change at the turning points from the outside to the inside of the circular path, or vice versa.

To provide a magnetic attraction device capable of detecting the presence or absence of a workpiece even when the workpiece has a hole or is smaller than the bottom surface of a cylinder tube. [Solution] The magnetic adhesion device 1 has a cylinder tube 7 whose bottom surface is an adhesion surface 3 for adsorbing the workpiece, and which has a pressure chamber 5 inside, a piston 11 which is equipped with a permanent magnet 9 and moves up and down within the pressure chamber 5, a control unit 13 which, when adsorbing the workpiece W, moves the piston 11 to the lower end of the pressure chamber 5 to adsorb the workpiece W to the adhesion surface 3 using the magnetic force of the permanent magnet 9, and a magnetic sensor 15 which detects the position of the piston 11. After moving the piston 11 to the lower end of the pressure chamber 5, if the workpiece W is not adsorbed to the adhesion surface 3, the control unit 13 moves the piston 11 upward, and determines whether or not the workpiece W is adsorbed to the adhesion surface 3 depending on whether or not the magnetic sensor 15 detects that the piston 11 has moved upward.

A cutting system for a labelling apparatus comprises: a transfer carousel (14) including a plurality of suction surface arrangements, angularly distributed along a periphery of the transfer carousel (14) and comprising corresponding recesses (140R), the transfer carousel (14) being configured to keep a web (2) adherent to one or more of the suction surface arrangements; a cutting roller (13) provided with a knife (130) configured to cut the web (2) so as to divide the web (2) into pieces constituting labels (20), the transfer carousel (14) being configured to interact with the cutting roller (13) in a cutting zone (T), wherein the rotations of the cutting roller (13) and of the transfer carousel (14) are synchronized so that the knife (130) of the cutting roller (13) is inserted cyclically into the recesses (140R) of the transfer carousel (14) to cut the web (2). The cutting system is characterized in that the cutting roller (13) comprises a shoe, positioned alongside the knife (130) so that, with the knife in the cutting zone (T), it presses against the web (2) positioned on one of the suction surfaces of the corresponding suction surface arrangement.

The utility model relates to the technical field of automatic production, in particular to a matrix type suction cup assembly which comprises a suction cup cylinder body and adsorption assemblies, one end of the suction cup cylinder body is communicated with an external vacuum generating device so as to supply negative pressure airflow, the other end of the suction cup cylinder body is communicated with the adsorption assemblies, and at least one adsorption assembly is fixedly connected to the suction cup cylinder body. The air channel is communicated with the suction cup cylinder body; the adsorption assembly is provided with at least two vacuum suction nozzles, one end of each vacuum suction nozzle communicates with the adsorption assembly, and the other end of each vacuum suction nozzle forms a free end and is used for sucking external materials. A pneumatic part is arranged in an airflow channel in the adsorption assembly. In conclusion, the pneumatic part in the air flow channel is used for flow dividing, negative pressure is evenly dispersed in the unclosed vacuum suction nozzles, the suction force of the whole suction face is even, the suction face is not affected by vacancy avoiding positions of local structures of products, the suction face is suitable for the products of different structures, the debugging time for replacing the suction cup assembly is shortened, and the production efficiency is greatly improved; and the cost is greatly reduced.

The utility model belongs to the technical field of centrifugal fans, and discloses a multi-wing centrifugal impeller and a multi-wing centrifugal fan, the multi-wing centrifugal impeller comprises an impeller disc, a plurality of blades and an impeller circular ring, the impeller disc and the impeller circular ring are connected to the two ends of the plurality of blades, each blade extends towards the circle center of the impeller disc, and the impeller circular ring is connected with the impeller disc. Each blade is provided with a front end and a rear end which are arranged at intervals in the radial direction of the impeller disc and a pressure face and a suction face which are arranged at intervals in the circumferential direction of the impeller disc, the front ends are arranged close to the circle center of the impeller disc, and sand dune type protrusions protruding towards the suction face are formed on the portions, close to the front ends, of the blades. The flow field uniformity and stability of the multi-wing centrifugal impeller are high, the flow channel shrinkage coefficient of the impeller is increased, and therefore the problem that the aerodynamic performance is poor when inlet impact loss and blade tail edge separation loss of airflow of an existing multi-wing centrifugal fan are large is solved.

The utility model relates to the technical field of air conditioners, and discloses an axial flow fan and an air conditioner. The axial fan comprises a blade, a plurality of tooth-shaped structures are arranged on the suction surface of the blade, each tooth-shaped structure extends in the direction from the inner edge to the outer edge of the blade, the plurality of tooth-shaped structures are sequentially arranged in the circumferential direction of the axial fan to form a feather structure similar to a bird wing, and the wing characteristics of better pneumatic and acoustic characteristics of birds in the flying process are imitated. When the multi-layer multi-dimensional wing noise reduction structure is applied to the blade, the blade vortex and the separation noise can be effectively improved, so that the noise in the rotation of the axial flow fan is reduced.

The invention is suitable for the technical field of tunnel construction equipment, and provides tunnel construction self-moving type dust collection ventilation equipment which comprises an AGV trolley and a dust collection mechanism above the AGV trolley. The dust collecting mechanism comprises a group of mounting plates; the dust collection cylinder is rotationally matched between the two mounting plates through a bearing, one end of the dust collection cylinder is an open dust collection surface, a stainless steel filter screen is arranged on the open dust collection surface, the other end of the dust collection cylinder is communicated with the adsorption end of the fan through a dust guide pipe, and the discharge end of the fan is communicated with the dust collection bin through the dust guide pipe; efficient collection and treatment of dust in tunnel construction are achieved; the deep purification of the air on the construction site is jointly ensured, the dust pollution is obviously reduced, and the quality of the whole working environment is improved; and meanwhile, an intelligent monitoring system formed by the integrated dust sensor group and the PLC can monitor the dust concentration in real time and adaptively adjust the working state of the dust collection mechanism, so that the optimal dust removal effect is always kept, and the autonomy and reliability of the equipment are remarkably enhanced.

The invention discloses a turbine blade surface skin parameterized mapping grid creation and automatic interpolation method, which realizes efficient post-processing of blade surface simulation data through molded line partition splitting, arc length parameterized grid generation and physical quantity data interpolation, and comprises the following steps of: firstly, performing partition preprocessing on a blade molded line according to a pressure surface, a suction surface and front and rear tail edges; constructing a body-attached parameterized grid; then simulation data are imported and automatically partitioned, an optimization interpolation algorithm is adopted for different regions, and the interpolation precision is improved in combination with an invalid value correction technology; and finally, mapping the three-dimensional data to a two-dimensional parameter plane to realize feature visualization and analysis. According to the method, manual intervention is remarkably reduced through an automatic process, the post-processing efficiency is improved while the data precision is guaranteed, and reliable support is provided for pneumatic optimization and cooling design of the turbine blade.

A holding mechanism includes a suction section, an elastic seal member, and a clamp mechanism. The suction section has a suction surface on which a workpiece is to be vacuum-suctioned. The elastic seal member is disposed around the suction surface such that at least part of the elastic seal member is hidden by the workpiece in plan view when the suction surface is viewed from above. The clamp mechanism includes a clamp that presses the workpiece such that the workpiece comes into contact with the elastic seal member, and drives the clamp to press the workpiece when the workpiece is suctioned by the suction section.

The invention relates to the technical field of wind power generation, in particular to a blade deicing device and method and a wind generating set, and the blade deicing device comprises heating modules which are arranged on the front edge, the rear edge, the pressure surface and the suction surface of a blade and used for heating an ice layer on the surface of the blade; the monitoring module is mounted on the surface of the blade and is configured to monitor the ice layer thickness, the environment temperature and the humidity of the surface of the blade; the control module is electrically connected with the heating module and the monitoring module, and the control module is configured to start the heating module to deice if the thickness of the ice layer is larger than or equal to a first threshold value and the environment temperature and humidity meet the icing condition. The icing state of the blade can be intelligently monitored, efficient deicing is achieved, and energy conservation and environmental protection are achieved.