520 results about "Suction surface" patented technology

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 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.

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 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.

The invention provides an axial flow fan blade and a fan comprising the same. The axial flow fan blade comprises a hub and blades. Each blade sequentially comprises a plurality of base circle sections in the direction from the blade inner edge to the blade outer edge. The contour line SP of each base circle section is generated by a first multinomial function; the starting points of the contour lines SP are connected together to form a blade front edge, the blade front edge is a large-radian curved surface, and the blade front edge is generated by a second multinomial function; the chord length L of each contour line SP is generated by a third multinomial function; the suction surface and the pressure surface of the blade in the direction from the inner edge of the blade to the outer edge of the blade are both of a curved surface structure, and the curved surface is generated by boundary mixing of a fourth multi-term function; the end points of the contour lines SP are connected together to form a blade tail edge, and the blade tail edge is of a wavy curved surface structure and is generated by a fifth multi-term function. The blades and the trailing edge of the axial flow fan blade are both based on multi-frequency harmonic superposition collaborative optimization design, the operation power consumption of the fan blade is remarkably reduced while the requirement for the air volume is met, and noise is greatly restrained.

The application discloses a low-stress clamp and a clamping method, the low-stress clamp comprising a suction cup, a sliding ring mechanism mounted on the suction cup and a swing arm structure capable of driving the sliding ring mechanism to translate, the sliding ring mechanism comprising a sliding ring body and a sliding ring sleeve coaxially connected, the suction surface of the suction cup is provided with a plurality of suction parts, the cavity in the suction cup and the suction parts are communicated, the communication channel in the sliding ring body is communicated with the cavity, the annular channel between the sliding ring body and the sliding ring sleeve and the vacuum pipe communicated with the annular channel on the sliding ring sleeve, and the air in the cavity is sucked to enable the plurality of suction parts to uniformly adsorb the parts to be polished; the clamping method is as follows: the sliding ring mechanism and the suction cup are assembled, the suction parts contact the parts to be polished on the polishing disc, the external air suction part is opened to adsorb the parts to be polished, and then the swing arm structure is made to abut against the sliding ring body; the surface of the parts to be polished after clamping can be guaranteed to be flat through vacuum adsorption, the polishing quality is improved, the clamping is fast and convenient, and the machining efficiency is improved.

A pressure side rib wall is arranged on the side, close to the tip end face, of the pressure face of the high-pressure turbine blade, a suction side tail-cut winglet is arranged on the side, close to the tip end face, of the suction face, and the pressure side rib wall and the suction side tail-cut winglet form a groove located in a blade tip. The inclined rib wall on the pressure side is used for preventing fluid from entering the gap, meanwhile, the suction side tail cut winglet of an improved structure is adopted, formation and development of leakage vortexes can be controlled, a high-heat load area at the tail edge of the suction surface can be improved, cooling holes are formed in the bottom of the groove to effectively cool the blade top, and therefore the purposes of reducing leakage loss and improving the service life of the blade are achieved. And the heat exchange performance of the blade tip is improved.

The invention relates to the technical field of cross-flow wind wheels, in particular to a cross-flow fan blade tail edge sawtooth structure and a cross-flow wind wheel applying the cross-flow fan blade tail edge sawtooth structure. The sawtooth structure comprises a fan blade body, and the peripheral contour of the fan blade body is defined by a fan blade root edge, a fan blade tail edge, a fan blade top edge and a fan blade front edge; the fan blade main body is provided with a pressure surface and a suction surface, the pressure surface and the suction surface are oppositely arranged, the pressure surface is concavely arranged towards the suction surface, so that the suction surface is convexly arranged, and the section shape of the pressure surface, the section shape of the suction surface, the fan blade root edge and the fan blade top edge are arranged in an arc shape; a plurality of notches are formed in the tail edge of the fan blade in an inwards-concave mode, and the adjacent notches are different. By means of the innovative structural design, noise is effectively reduced, and meanwhile it is guaranteed that the core aerodynamic performance of the fan blade is stable.

A docking device for intraocular surgery is provided having an upper edge portion having a second diameter, a lower edge portion having a first diameter and a bottom surface with at least one aperture, and a sidewall extending between the upper edge portion and the lower edge portion. An arm is also provided having a first portion coupled to the central portions of the upper and lower edge portions and a second portion configured for connection to a positioning arm. The lower edge portion also has a lower surface having a suitable profile configured to be secured to the sclera and / or conjunctiva of the surgical eye. Optionally, the lower surface of the upper edge portion is adapted and configured to releasably engage with the upper surface of the lower edge portion. Other variations include a split coupling that allows the suction surface to remain coupled to the surgical eye while removing other portions of the docking device.

The invention relates to the technical field of intelligent household appliances, and discloses a refrigerator heat dissipation method, a refrigerator comprises a heat dissipation fan arranged in an air duct, a condenser arranged on the air suction surface of the heat dissipation fan, and a compressor arranged on the air outlet surface of the heat dissipation fan; the method comprises the steps that the air speed of a set position between the compressor and the condenser is detected; and when the wind speed of the set position is out of the target wind speed range, the rotating speed of the cooling fan is adjusted, so that the wind speed of the set position is within the target wind speed range. The ventilation quantity of the fan can measure the heat dissipation effect of the heat dissipation fan, and the ventilation quantity is equal to the product of the air speed and the diameter of the air port of the heat dissipation fan, so that the air speed is the only factor influencing the ventilation quantity under the condition that the diameter of the air port of the heat dissipation fan is not changed. Therefore, by making the wind speed of the specific point within the target range, the influence of wind resistance on the wind speed of the cooling fan can be reduced, and the cooling effect of the refrigerator is guaranteed. The invention further discloses a device for cooling the refrigerator, the refrigerator and a computer readable storage medium.

The application provides a flow control method based on three-curved-surface fish scale bionic structure, comprising the following steps: S1, constructing a main structure of an impeller blade, including a suction surface e and a pressure surface f, and fish scale areas g with multiple fish scale bionic structure coupling elements arranged regularly are arranged on the suction surface e and the pressure surface f; S2, constructing and designing a single fish scale bionic structure coupling element, including a bottom surface adhering to a blade surface, a top surface in a fish scale structure, and a rear side cylindrical surface; the top surface comprises two groups of parallel fold surfaces, and each group of fold surfaces is composed of three quadrilateral surfaces; a space rectangular coordinate system is established with a front end point of the bottom surface as an origin, and the fish scale bionic structure coupling element is constructed in the space rectangular coordinate system; and S3, establishing multiple fish scale bionic structure arrangement rules. The application can improve the fluid flow characteristics of the blade surface and reduce noise generation based on the control of flow by bionic structure.

A turbine blade (30) comprising: a flow profile section (34) extending in a blade height direction and having a pressure surface (46, 46A) and a suction surface (48, 48A), each of which extends between a leading edge (42, 42A) and a trailing edge (44, 44A); a cover section (52) arranged at an outer end face of the flow profile section (34); a rounding section (40) formed by a curved surface (40a) and connected to an end section of the cover section (52) on one side of the flow profile section (34); at least one first cooling hole (60, 60a-60i) extending along the blade height direction within the flow profile section (34); and at least one cooling cavity (70) arranged at least partially within the cover section (52) and connected to with at least one first cooling hole (60, 60a-60i),and a second cooling hole (62) connected to the at least one cooling cavity (70) and open to a surface of the cover section (52), wherein the flow profile section (34) has a reference flow profile (34A) in which a maximum blade thickness at a reference position (PA) in the blade height direction is minimal, wherein the at least one cooling cavity (70) comprises a cavity (72) extending such that it overlaps the fillet section (40) in the blade height direction, wherein in a cross-section enclosing the cavity (72) perpendicular to the blade height direction, the cavity (72) extends inside and outside a first region where a contour of the reference flow profile (34A) is projected onto the cross-section in the blade height direction, and wherein the cavity (72) has: a bottom surface (76),which extends along a direction perpendicular to the blade height direction; and an inner wall surface (78) which extends along the blade height direction into an extension area (Ra1, Rb1) into which the rounding section (40) extends, and which is connected to the bottom surface (76) in an area, viewed from the blade height direction, outside the first area at the cross-section.

The invention provides an adsorption plate capable of forming a semi-cut groove with high precision. A suction plate for holding an object to be cut having a substrate and a resin layer, the suction plate including: a base member including a base portion disposed on a base provided with a suction mechanism, and a protruding portion formed so as to protrude upward from the base portion and having a suction surface capable of sucking the resin layer; and a frame-shaped member that is disposed so as to surround the periphery of the protruding portion and that includes a placement surface on which the substrate can be placed, the placement surface being formed so as to be positioned above the suction surface, a discharge passage being formed in at least one of the base member and the frame-shaped member, the discharge passage is capable of discharging foreign matter in a predetermined space defined by the protruding portion and the frame-shaped member to the outside of the predetermined space.

The application discloses a wind turbine blade vortex-induced vibration suppression unit, device and method, the suppression unit comprises a synthetic jet exciter, a connecting pipe and a vibration suppression accessory, the synthetic jet exciter is arranged in a cavity of a blade shell, the vibration suppression accessory is attached to a suction surface of the blade shell, a cavity is formed in the vibration suppression accessory, an air inlet hole is arranged on the lower surface of the vibration suppression accessory, and at least one flow regulation unit is arranged on the upper surface of the vibration suppression accessory, the flow regulation unit is composed of an air outlet hole and a vortex generator which cooperate with each other, the air inlet hole and the air outlet hole are communicated with the cavity respectively, one end of the connecting pipe is connected with the synthetic jet exciter, and the other end of the connecting pipe is connected with the air inlet hole of the vibration suppression accessory through the suction surface of the blade shell. The vibration suppression unit is attached to the surface of the blade, the flow state of the surface of the blade is improved, the vibration of the blade can be effectively suppressed, the vibration suppression unit does not need to be removed when the blade normally operates, the method is simple and efficient, and the removal time and the labor cost are effectively saved.

The invention discloses a composite material fairing, a combined die and a forming method. The fairing comprises a connecting support, a supporting core material, a suction surface shell, a pressure surface shell, a left wing type surface shell, a right wing type surface shell and an empennage. The supporting core materials are arranged on the two sides of the connecting support, the suction surface shell covers the tops of the supporting core materials and the top of the connecting support, and the pressure surface shell covers the bottoms of the supporting core materials and the bottom of the connecting support. The leftmost side of the supporting core material is covered with the left wing profile shell, the rightmost side of the supporting core material is covered with the right wing profile shell, and the rear end of the connecting support is covered with the tail wing. The suction surface shell, the pressure surface shell, the left wing type surface shell, the right wing type surface shell and the empennage are all carbon fiber reinforced resin matrix composite material structural parts. The manufacturing method is applied to the field of fairing manufacturing, high forming precision is achieved, light-weight treatment of the fairing can be achieved, and the manufacturing process is relatively simple.

A vehicle, comprising a blade, an impeller, and a centrifugal fan. The blade comprises: a blade body, the blade body comprising a suction surface, a leading edge, and a through-flow path, wherein the through-flow path is configured to communicate the leading edge with the suction surface so as to reduce the impact of an airflow on the leading edge.

The invention relates to a guide vane (1) for a turbomachine, in particular for a stationary gas turbine, comprising an inner platform (2), an outer platform (3) and a blade (4) extending between them in a longitudinal direction (L) with an outer wall (5) defining a leading edge (6), a trailing edge (7), a suction side (8) and a pressure side (9), wherein the blade (4) is provided with at least one meandering cavity (10) through which a cooling fluid is guided during operation of the turbomachine, wherein the cavity (10) has longitudinally extending (L) cavity sections (13, 14, 15) arranged adjacent to one another in a front-to-back direction (X) and transition sections (16, 17) connecting these at their ends in a meandering manner, wherein inserts extending longitudinally (L) into at least two immediately adjacent cavity sections (13, 14) (18,19) are inserted, which give these cavity sections (13, 14) an annular cross-section, and wherein the downstream insert (19) has at least one cooling fluid deflection element (25) which projects outwards from the insert (19) in the direction of the outer platform (3).

A substrate processing device according to the present invention includes a holding unit having, on a suction surface for suctioning a substrate, a circular central region and an annular outer region arranged outside the central region. A plurality of zones are set on the suction surface, the plurality of zones being in the central region and in regions obtained by dividing the outer region in the circumferential direction. The substrate processing device includes a pressure generation unit which generates pressure in each of the plurality of zones. In a state in which the substrate is mounted on the suction surface and in which negative pressure is applied to at least one of the plurality of zones, the pressure generation unit applies positive pressure to at least one of the plurality of zones to which negative pressure is not applied.

The invention discloses a large wind tunnel blade which is characterized in that a pressure surface shell and a pressure surface main beam are co-cured into a whole, a plurality of first rib plates are adhered to one side of the pressure surface main beam of the pressure surface shell, a suction surface shell and a suction surface main beam are co-cured into a whole, and a plurality of second rib plates are adhered to one side of the suction surface main beam of the suction surface shell. The pressure surface main beam and the suction surface main beam are bonded to form an integral main beam, one end of the metal blade root is tightly held at one end of the pressure surface main beam and one end of the suction surface main beam and is bonded with the pressure surface main beam and the suction surface main beam in a matched mode, and the suction surface shell and the pressure surface shell are bonded to form a blade body. The first rib plate and the second rib plate are distributed on the two sides of the integral main beam and bonded between the pressure surface shell and the suction surface shell. The invention further discloses a preparation method of the large wind tunnel blade. The large wind tunnel blade and the manufacturing method thereof have the advantages that connection is convenient, the connection strength is guaranteed, the requirement for a mold is low, and the manufacturing cost is low.

The invention relates to the technical field of vane pumps, and provides a shield motor nuclear main pump hydraulic model and a shield motor nuclear main pump. The shielding motor nuclear main pump hydraulic model comprises an impeller, wherein blades of the impeller are blades of a line element three-dimensional structure; the guide vane is matched with the impeller, and blades of the guide vane are blades of a linear element three-dimensional structure; the pump shell is matched with the guide vane; the appearance of the line element three-dimensional structure blade is determined through two sets of curve elements located on the front cover plate and the rear cover plate, and the curve elements comprise a front edge line, a tail edge line, a pressure surface line and a suction surface line. According to the line element three-dimensional structure blade, a front edge line, a tail edge line, a pressure surface line and a suction surface line of a front cover plate and a rear cover plate are generated on the basis of parameterized meridian curve, mean camber line angle distribution and thickness distribution, and a continuous curved surface is constructed through a lofting method, a sweeping method or a grid method. The linear element three-dimensional structure blade can be integrally milled, so that the material utilization rate, the machining efficiency and the machining quality are improved, and the casting defects are overcome.

The utility model relates to a reverse thrust exhaust volute of an aero-engine, belongs to the technical field of exhaust volutes, and solves the problems that in the prior art, a pneumatic profile of an exhaust volute is complex in structure and difficult to machine and assemble. The utility model provides an aero-engine reverse thrust exhaust volute which comprises two binding surfaces and a pneumatic molded surface, and the pneumatic molded surface is fixed between the front binding surface and the rear binding surface to jointly form a box type exhaust volute. The pneumatic molded surface comprises a pressure surface, a first flow deflector, a second flow deflector and a suction surface, the pressure surface and the suction surface are arc surfaces with extending surfaces at exhaust ends, and the first flow deflector and the second flow deflector are arc surfaces. The pneumatic profile of the exhaust volute is simple in structure, machining difficulty and cost are remarkably reduced, and assembly is convenient and fast; a flow field in the exhaust volute is stable and smooth, streamline / exhaust airflow leaving from an outlet of the volute can smoothly enter the injection barrel, the influence on reverse thrust exhaust back pressure is smaller than or equal to 200 Pa, and the exhaust effect is stable and excellent.

To further improve determination accuracy of presence / absence of a foreign matter in a suction surface of a suction nozzle.SOLUTION: A component mounting machine includes: a suction nozzle; an imaging part arranged on a side of the suction nozzle; and a control part for controlling the imaging part so as to image a suction surface of the suction nozzle from the side and determining presence / absence of a foreign matter in the suction surface on the basis of an image obtained by imaging. The control part can execute center specification processing for, in the image, scanning a scanning line along a width direction crossing an axial direction of the suction nozzle, to detect an edge corresponding to a boundary between a background region of the suction nozzle and an object region not corresponding to a background in each of one side and the other side in the width direction and to specify an intermediate position between two edges as a central position of the suction nozzle in the width direction, range specification processing for specifying a range of the suction surface in the width direction in the image on the basis of the central position and a width value of the suction surface, and first determination processing for determining the presence / absence of the foreign matter on the basis of a plurality of edges detected in the range of the suction surface.SELECTED DRAWING: Figure 4

The present disclosure relates to an axial flow fan blade, a fan assembly, an air conditioner outdoor unit and an air conditioner. The axial flow fan blade comprises a hub and a plurality of blades arranged on the outer side of the hub, each blade comprising a pressure surface and a suction surface arranged oppositely, each blade comprising a blade inner edge and a blade outer edge arranged oppositely, and each blade further comprising a blade leading edge and a blade trailing edge arranged oppositely. Each blade is divided into a first region, a second region and a third region in a circumferential direction. The first included angle of the first region, the second included angle of the second region and the third included angle of the third region are selected to be in a ratio of 1:1.25-1.9:1.25-1.9.

This invention discloses a method for rapid prediction and dynamic control of compressor flow field quality at low Reynolds numbers. The method first obtains the pressure gradient parameters at the laminar separation point of the blade suction surface at different Reynolds numbers through high-precision performance testing / numerical calculation. K s Then establish them in sequence. K s With the incoming Reynolds number Re, the momentum-thickness Re at the separation point θs An empirical predictive model for blade surface separation scale and boundary layer development characteristics quantifies the impact of low Reynolds number effects on the separated bubble structure and boundary layer growth rate, thereby rapidly predicting the degree of compressor performance degradation at low Reynolds numbers. Based on the above model, parameters such as the excitation frequency of the blade leading-edge deformable surface are optimized to induce periodic pressure disturbance waves, achieving dynamic control of large-scale separated flow at low Reynolds numbers. This invention improves the prediction speed of compressor performance variations at low Reynolds numbers, providing support for the aerodynamic design and performance control of high-altitude compressors.

The invention belongs to the field of aero-engine fan and air compressor pneumatic design, and discloses a fan blade grid pneumatic design method based on a Bezier suction surface superposition channel. The pneumatic design method for the fan blade grid comprises the steps of determining geometric parameters of the blade grid; calculating suction surface inlet and outlet angles; defining the axial length of the suction surface; setting a dimensionless suction surface control point; calculating the minimum included angle and the maximum included angle of the dimensional suction surface control points; calculating a dimensional suction surface control point; dimensional suction surface control points are drawn; calculating curve coordinates of the suction surface; calculating a blade grid channel pitch; calculating the inlet width of a cascade channel; calculating the outlet width of a cascade channel; calculating a cascade channel width distribution rule; generating a pressure surface front section curve; generating a pressure surface rear section curve; and completing the two-dimensional cascade design. According to the pneumatic design method for the fan blade grid, the blade profile suction surface curve change rule and the blade grid channel size change rule can be directly regulated and controlled, regulation and control are direct and effective, the design convenience is high, and the practical engineering value is achieved.

The invention provides a bent blade of an air-cooled turbine and a design method of the bent blade of the air-cooled turbine, and relates to the technical field of aero-engines and gas turbines. The bent blade comprises a plurality of blade-shaped sections which are stacked in sequence, and the gravity centers of the blade-shaped sections form a stacking line of the bent blade; wherein the stacking line is configured as a C-shaped arc line, and the center of gravity of a third blade-shaped cross section located in the center of the plurality of blade-shaped cross sections is horizontally shifted by a first distance toward the pressure surface side relative to the center of gravity of a first blade-shaped cross section located at the blade root. The gravity center of the second blade-shaped section located at the blade top horizontally shifts towards the suction surface side by a second distance relative to the gravity center of the first blade-shaped section.

This invention discloses a gantry-type stacking robot for mold steel storage, relating to the field of automated storage robot technology. It includes a fine-tuning device mounted on the bottom surface of a rotating device; a horizontal plate mounted on the bottom surface of the fine-tuning device; a bidirectional adjustment component mounted on the bottom surface of the horizontal plate; and magnetic suction components for aligning plates mounted on both sides of the bottom surface of the bidirectional adjustment component, respectively, at the center of the bottom surface of the horizontal plate. A trigger mechanism is mounted on the drive shaft of the magnetic suction component, with its end slidably connected in a groove. An air blowing mechanism is rotatably mounted on the bottom of the aligning plate. The air blowing mechanism is driven by the linkage between the trigger mechanism and the magnetic suction component's lifting and lowering mechanism, enabling aligning, suction, and cleaning actions. Combined with a rotatable air wheel and a flat air nozzle, it specifically removes iron filings, dust, and other fine impurities from the aligning and electromagnetic suction surfaces of the mold steel, preventing wear and uneven stacking caused by residual impurities.

The invention relates to the related technical field of carrying machinery, discloses a transferring and overturning device for glass production, and aims to solve the problems that a suction cup on a rotating arm is not parallel to glass, so that the suction cup leaks air, a movable frame capable of moving up and down and an overturning rod capable of enabling a supporting cantilever to drive the suction cup to rotate by 180 degrees are mounted on a supporting frame; in the glass transferring process, the overturning rod adjusts all the suction cups to be in a horizontal state through the supporting cantilever, the adsorption faces of all the suction cups are aligned with the glass, then the horizontally-aligned suction cups are right attached to the surface of the glass through the lifting effect of the movable frame, and the situation that gaps are generated due to the fact that the suction cups and the glass are not parallel is avoided; and finally, the floating leveling adsorption effect is achieved.

The invention provides a wheel flange sealing structure of a gas compressor end of a gas turbine, the gas compressor end comprises a static impeller and a movable impeller which are alternately arranged, the static impeller and the movable impeller are in sealing fit through a wheel flange sealing structure, and a second wheel flange matching part on the movable impeller is provided with a sealing blade. The sealing blade is provided with a suction surface and a pressure surface which are arranged back to back, the suction surface is an outer convex cambered surface, and the pressure surface is an inner concave cambered surface; the pressure surface is arranged towards the high-pressure area, and the sealing blade forms a pressure difference between the suction surface and the pressure surface along with the rotation of the compressor impeller, so that an acting force opposite to a high-pressure leakage flow of the high-pressure area is obtained; leakage of high-pressure leakage flow is efficiently prevented.

This application relates to the field of impeller structure optimization technology, and particularly to a high-speed centrifugal fan and its impeller structure optimization method. The high-speed centrifugal fan includes a main shaft, an impeller, a thin-film pressure sensing layer, a surface protective coating, a flexible circuit adapter belt, and a slip ring actuator. The impeller includes a disc and multiple blades. The thin-film pressure sensing layer is attached to the surface of at least one blade. The surface protective coating covers the outside of the thin-film pressure sensing layer, and the thickness of the surface protective coating is uniform while the surface profile of the blade remains unchanged. The flexible circuit adapter belt extends along the blade surface to the edge of the disc and is communicatively connected to the thin-film pressure sensing layer. The slip ring actuator is mounted on the main shaft and is electrically connected to the end of the flexible circuit adapter belt to transmit pressure signals under rotational conditions. This method can solve the problem of the mismatch between the starting position and range of flow separation on the blade suction surface and the design expectation.