742 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.

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 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 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.

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 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.

The invention discloses a split type adjustable blade structure of a variable geometry turbine and application of the split type adjustable blade structure, and relates to the technical field of variable geometry turbines of aero-engines. An adjustable blade is designed into a fixed petal body and a rotating petal body in a split mode, the fixed petal body is fixed in a turbine blade channel, a blade front edge and a pressure face front blade body are formed, and no radial gap exists between the blade front edge and a casing; the structure stability is ensured; the end region leakage is reduced; the rotating valve body is located on the rear portion of the fixed valve body and connected with an external adjusting mechanism through the rotating boss to achieve angle adjustment, and a blade suction face, a tail edge and a blade body on the rear portion of a pressure face are formed. A molded line transition fit structure is arranged between the fixed petal body and the rotating petal body, and the gap between the fixed petal body and the rotating petal body is kept minimum and mechanical interference does not occur in the initial and adjusting processes. A dynamic and static clearance sealing structure is further designed, and clearance leakage flow is effectively restrained by arranging a sealing groove and sealing teeth. The structure can reduce flow loss and clearance leakage loss and improve turbine efficiency and engine performance.

The invention provides a blade structure, an axial flow blade, an axial flow fan and an air conditioner, the blade structure comprises a blade body, the blade body comprises a front edge, a suction surface, a tail edge and a pressure surface which are sequentially connected end to end, the pressure surface and the suction surface respectively extend between the front edge and the tail edge, in the airflow flowing direction, the front edge or the pressure surface is provided with a leading-in hole, and the leading-in hole is communicated with the suction surface. A leading-out hole is formed in the tail edge or the suction surface; a silencing cavity is formed in the blade body, the guide-in hole and the guide-out hole communicate with the silencing cavity, the guide-in hole guides airflow into the silencing cavity, and the guide-out hole guides the airflow in the silencing cavity out of the blade body. The leading-in holes reduce impact noise of airflow to the front edge, and the leading-out holes reduce noise of the trailing edge by changing the flowing state of the airflow at the trailing edge.

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 invention provides a high-load supersonic cascade and a gas compressor, and belongs to the technical field of gas turbine gas compressors. The blade grid comprises blades and vortex generators, the vortex generators are installed in the front edge areas of the blades, and the vortex generators and the suction surfaces of the blades are located on the surfaces of the same sides of the blades. In the airflow direction corresponding to the blades, the height of the vortex generator is gradually reduced, the width of the vortex generator is gradually increased, and the width of the vortex generator is the size of the vortex generator in the spreading direction of the blades. The vortex generators in specific shapes are arranged on the surfaces of the blades, so that after airflow passes through the vortex generators, two reverse vortex pairs spaced by a certain distance can be generated, and the two reverse vortex pairs can entrain the airflow from a mainstream area with more gas and supplement the airflow to a shock wave / boundary layer interference separation area lacking gas; therefore, flow separation of the rear half section of the suction surface is inhibited, flow loss is reduced, and aerodynamic performance of the cascade is improved.

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.

The utility model discloses a blade of an axial flow pump, which belongs to the technical field of axial flow pumps and comprises a blade body, and a first wing blade and a second wing blade are fixedly connected to a pressure surface and a suction surface of the blade body respectively. The first wing cutter strip and the second wing cutter strip are respectively fixed at the same blade height of the blade main body; and the chord lengths of the first wing blade and the second wing blade are equal to those of the blade height corresponding to the blade main body. By means of the first wing cutter strips and the second wing cutter strips, secondary backflow formed on the hub side at the outlet of the impeller can be weakened in a physical interception mode when flow is reduced.

The invention discloses a wind power system and a wind power blade detection method, and relates to the technical field of wind power generation, the wind power system comprises a wind power blade, an elastic air bag, an air supply device, an image acquisition device and an image analysis module, the wind power blade is provided with a suction surface and a pressure surface which are oppositely arranged along the thickness direction, and a front edge and a rear edge which are oppositely arranged along the width direction; the elastic air bag is arranged on the pressure face and comprises a first bag body and a second bag body, and the first bag body and the second bag body define an inflation cavity. The air supply device supplies air to the inflation cavity so that the elastic air bag can be inflated and expanded. The image acquisition device is used for acquiring an actual measurement image of the elastic airbag; and the image analysis module is used for superposing the actual measurement image and the standard image on the same display surface, and outputting a damage prompt signal when the coverage area of the actual measurement image is larger than that of the standard image. According to the scheme, the technical problem that the damaged elastic material for realizing load reduction on the wind power blade cannot be found in time, so that the load reduction effect is influenced, and the blade is damaged due to overload can be solved.

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.

To determine easily and in a short time whether or not a combination of a carrier pad and a spinner table in proper sizes with respect to a diameter of a wafer is set, as well as, whether or not the spinner table is mounted.SOLUTION: A carrier unit 60 of a processing device 1 comprises: a suction path 63; a pressure gauge 65 which measures a pressure of the suction path 63; a horizontal movement mechanism 66 which moves a carrier pad 62 in a horizontal direction; and an elevation mechanism 67 which moves the carrier pad 62 in a vertical direction. In a state where a center of a holding surface 41a of a spinner table 41 and a center of a suction surface 62a of the carrier pad 62 are offset just by a predetermined distance ε in the horizontal direction, a control section 70 brings the suction surface 62a of the carrier pad 62 into contact with the holding surface 41a of the spinner table 41 and determines a combination pattern in accordance with sizes of the spinner table 41 and the carrier pad 62 based on a pressure value which is measured by the pressure gauge 65 when the suction surface 62a of the suction pad 62 is suctioned by a suction source 64.SELECTED DRAWING: Figure 2

The utility model discloses a cornea negative pressure suction trephine device for an eye library, which is a device for obtaining a cornea graft from an eyeball of a donor, and comprises an adsorption ring which is positioned on the eyeball above the cornea and a trephine which is sleeved on the periphery of the adsorption ring and can rotate relative to the adsorption ring, an annular adsorption face capable of being adsorbed to the eyeball in a negative pressure suction mode is formed on the end face of the adsorption ring, the trephine comprises a circular ring component and a circular cutting part formed at the far end of the circular ring component and used for annularly cutting the sclera, and the circular ring component is arranged on the periphery of the end, close to the annular adsorption face, of the adsorption ring in a sleeving mode. Thus, the cornea acquisition negative pressure suction trephine device for the eye library can be provided, the cornea acquisition negative pressure suction trephine device for the eye library is suitable for acquiring a cornea graft with uniform sclera tissue from a donor in a rotary cutting mode, and extrusion damage to cornea endothelial cells can be effectively reduced.

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.

A storage device (10) that stores an unmanned aerial vehicle (30) includes a gripping portion (11) for gripping the unmanned aerial vehicle (30), and a main body portion (10) having a suction surface (21) to which an upper surface (313) of the unmanned aerial vehicle (30) is suctioned.

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.

The present invention discloses a closed-component electrochemical machining device and method, belonging to the field of electrochemical machining. The fixture is divided into a blade pressure surface cathode fixture and a blade suction surface cathode fixture. Each fixture is provided with a main liquid supply flow channel inlet, two auxiliary liquid supply flow channels, and two liquid sealing supply / air flow channels. The blade suction surface cathode fixture, the blade pressure surface cathode fixture, the closed component, and the electrolyte / gas ejected from the liquid sealing supply / air flow channel form a closed flow field mode in which the electrolyte in each flow channel is independently controlled. The present invention improves the uniformity and stability of the flow field in the machining area, and realizes the simultaneous machining of the internal and external flow channels and the blade profile of closed components such as rectifiers and stator vane rings; the integrated fixture is convenient for clamping and improves the electrochemical machining efficiency.

The fan blade comprises a blade body and a drainage structure, the blade body is provided with a blade front edge and a blade rear edge, the drainage structure is arranged on the suction surface of the blade body and close to the blade front edge, and the drainage structure comprises a first drainage plate and a second drainage plate. The first drainage plate and the second drainage plate are of a splayed structure in the direction from the blade front edge to the blade rear edge, the drainage structure is provided with a symmetry axis in the direction from the blade front edge to the blade rear edge, and the first drainage plate and the second drainage plate are symmetrically arranged relative to the symmetry axis. The flow guide structure composed of the first flow guide plate and the second flow guide plate is arranged at the blade front edge of the suction surface of the blade, vortex is reduced, fluid entering the impeller is rectified, axial air inlet fluid is changed into uniform radial fluid after flowing through the part, and therefore unstable flowing of the fluid between the adjacent blades is reduced, and the flow guide effect of the impeller is improved. And the fan flow and efficiency are improved.

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.