58results about How to "Reduce viscous drag" patented technology

The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.

The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.

An article includes a body having at least one viscous drag-reducing surface defining a multiplicity of macro-scale depressions separated and enframed by ridges, at least a portion of the surface being phobic to a preselected liquid so that gas bubbles may be trapped in the macro-scale depressions in order to reduce viscous drag between the article and the liquid.

The invention relates to wings of an aircraft and provides a bionic sharkskin structure capable of reducing drag to overcome the problems that conventional aircrafts cannot improve the off-line pneumatic performance of the whole flight bag in the case of different pneumatic environment conditions on the occasion of a disordered gas field and that the aircrafts encounter great flight drag and cannot meet the demand of flying at different flight speeds in the disordered gas field. The bionic sharkskin structure comprises a dielectric elastomer, a flexible electrode layer and nano-wire conductive coatings, wherein the dielectric elastomer is of a plate structure; one plate surface of the dielectric elastomer is coated with a plurality of the nano-wire conductive coatings; the plurality of the nano-wire conductive coatings are applied along a horizontal direction and along two oblique directions in oblique crossing with the horizontal direction to form a net structure; and other plate surface, opposite to the above plate surface, of the dielectric elastomer is coated with the flexible electrode layer. The bionic sharkskin structure capable of reducing drag in the invention is applied to wing roots.

The invention relates to a thermo-acoustic engine device which comprises a thermo-acoustic engine component, an acoustic power utilization component and an acoustic power outputting component, wherein the thermo-acoustic engine component works in the low-temperature environment; the acoustic power utilization component works in the room temperature environment; the two ends of the acoustic power outputting component are connected with the thermo-acoustic engine component and the acoustic power utilization component respectively. Compared with the prior art, the thermo-acoustic engine device has the advantages of small acoustic power loss, high efficiency, simple device structure, stability in running and the like.

The invention discloses an axial flow fan ternary impeller with a vein-shaped structure and a nonuniform empennage. The axial flow fan ternary impeller comprises a hub, and a connecting piece for a shaft sleeve fixed on the hub. The axial flow fan ternary impeller further comprises twisted blades and splitter blades fixedly connected to the hub; the twisted blades include suction surfaces and pressure surfaces; wing-shaped grooves are formed in the tops of the twisted blades; vein-shaped grooves are formed in the upper half parts of the pressure surfaces of the twisted blades; the wing-shaped grooves are communicated with the vein-shaped grooves through exhaust ports; winglet projections and dense winglets are arranged at the tail parts of the suction furnaces of the twisted blades; the dense winglets are arranged on two sides of the winglet projections; parabola small holes are formed in the twisted blades; the splitter blades are arranged between two adjacent twisted blades; and the heights of the splitter blades are smaller than the heights of the twisted blades by one half.

The invention relates to a thermo-acoustic system driven by a liquefied natural gas cold energy. The thermo-acoustic system comprises a heat source (7), a liquefied natural gas cold energy (8), a hot end heat exchanger (1), a heat regenerator (2), a cold end heat exchanger (3) and a resonant cavity, wherein the hot end heat exchanger, the heat regenerator, the cold end heat exchanger and the resonant cavity are connected in sequence; the hot end heat exchanger (1) is connected with the heat source (7); the cold end heat exchanger (3) and a resonant tube (4) are arranged in the liquefied natural gas cold energy (8); the temperature difference of the hot end heat exchanger (1) and the cold end heat exchanger (3) is utilized, and a temperature gradient is built inside the heat regenerator (2), so that pressure fluctuation is generated in the resonant tube (4), and cold energy is converted into acoustic power. Compared with the prior art, the thermo-acoustic system driven by the liquefied natural gas cold energy has the advantages that the structure is simple; the acoustic power loss is low; the efficiency of the thermo-acoustic system is high, and the like.

The invention discloses an axial flow fan three-dimensional impeller with leaf vein structures and seagull-shaped splitter blades. The axial flow fan three-dimensional impeller comprises a hub and further comprises curved-twisted blades and splitter blades, wherein a shaft sleeve is fixed on the hub by a connecting piece; the curved-twisted blades and splitter blades are fixedly connected onto the hub; the curved-twisted blades comprise suction surfaces and pressure surfaces; wing grooves are formed in the tops of the curved-twisted blades; leaf vein shaped grooves are formed in upper half parts of the pressure surfaces of the curved-twisted blades; the wing grooves are communicated with the leaf vein shaped grooves through air outlets; small wing protrusions are arranged at the tails of the suction surfaces of the curved-twisted blades; parabolic pinholes are formed in the curved-twisted blades; a splitter blade is arranged between every two adjacent curved-twisted blades; and the height of each splitter blade is smaller than one half of that of the curved-twisted blade. According to the axial flow fan three-dimensional impeller disclosed by the invention, the secondary flow phenomenon can be reduced, boundary layer separation is avoided, wake vortex of the blades is suppressed, turbulent dissipation and flow losses are reduced, and the axial flow fan three-dimensional impeller has the characteristics of high efficiency, excellent performance, low noise and energy conservation.

The invention relates to an aerofoil blade of ridged surface drag reduction. The aerofoil blade of ridged surface drag reduction is used for reducing flow resistance and energy loss in operation of a pump and a draught fan, particularly, V-shaped ridged structures are arranged on the surface of the aerofoil blade, relative distance sizes among the ridged structures are set to be a, h and s, when airflow flows through a blade passage, stable secondary vortexes are formed in ridged structure gullies, and viscous resistance can be obviously reduced. According to the aerofoil blade of ridged surface drag reduction, resistance between the blade and the airflow is reduced, and the aerofoil blade of ridged surface drag reduction has the advantage of reducing the energy consumption.

The invention discloses shot blaster blades and an impeller body assembly of a shot blaster and belongs to the technical field of shot blasters. The impeller body assembly comprises an impeller body, and the impeller body comprises an impeller plate. The impeller plate is provided with clamping grooves. The shot blaster blades are connected to the clamping grooves in a clamped mode. Each shot blaster blade comprises a base and a blade body, and the blade body is provided with a surface texture. According to the shot blaster blades and the impeller body assembly of the shot blaster, viscosity resistance can be reduced, abrasion to the blades is reduced, the blasting speed of the shot blaster is increased, the work efficiency is greatly improved, energy consumption is reduced, and the use cost is reduced.

The invention provides a deformable flap with enhanced blowing-suction synergistic high lift force. The deformable flap comprises a wing composed of a leading edge flap, a wing body and a trailing edge deformable flap, wherein a jet flow cabin is arranged in the leading edge flap, and jet flow holes connected with the jet flow cabin are formed in the upper surface of the leading edge flap; a flow suction cabin is arranged in the trailing edge deformation flap, and flow suction holes connected with the flow suction cabin are formed in the upper surface of the trailing edge deformation flap; and a micro compressor is embedded in the wing body, is respectively connected with the jet flow cabin and the flow suction cabin through rubber pipes, and sucks air flow from the flow suction holes, pressurizes the air flow and then ejects the air flow from the jet flow holes. According to the invention, a blowing-suction synergistic active flow control technology is combined with the deformation flap, and the flap is used for a large fixed-wing aircraft, so a high lift enhancement effect is generated, take-off and landing aerodynamic characteristics are improved, short-distance take-off and landing are realized, airport pressure is relieved, cruising efficiency can be improved, and voyage can be increased.

The invention provides a hull structure capable of sufficiently improving pushing performance. A hull (10) has a first tail fin and a second tail fin (14, 15) respectively installed at right board hull side (12) and left board hull side in outwards extending manner. The first and the second tail fin (14, 15) are extended in horizontal direction, and installed between the after-perpendicular AP and the front position away from 10% of perpendicular length Lpp of the after-perpendicular AP. The first and the second tail fin (14, 15) can shade downward current and reduce downward current. The front end (14a) of the first tail fin (14) positioned below the second tail fin (15) is positioned in front of the front end (15a) of the second tail fin (15). Therefore, the current of the downward current Df controlled by the first tail fin (14) is guided between the first and the second tail fins (14, 15) so that the downward current Df is totally current to the back in horizontal direction and is accelerated.

An electromagnetic actuator (101) is composed of a movable unit (14) and a stationary unit (13). The movable unit (14) has an output pin (60) movably supported by a guide member (70). The guide member(70) has a cylindrical portion (73) and a first support portion (74) and a second support portion (74) which are formed on an inner peripheral surface of the cylindrical portion (73). A radially inwardly recessed portion (65) is formed on an outer peripheral surface of the output pin (60). Straight portions (66, 68) are formed in the output pin at both axial sides of the radially inwardly recessed portion, wherein an outer diameter of the straight portion is larger than an outer diameter of the radially inwardly recessed portion (65). Each of the straight portions of the output pin (60) is movably in contact with the first and second support portions (74, 75).

The invention relates to a low-Reynolds-number lower wing with oblique grooves. A plurality of inclined groove groups which are alternately distributed in a left-inclined manner and a right-inclined manner are arranged near the tail edge of the upper surface; each oblique groove group consists of a plurality of inclined grooves which are arranged in parallel at intervals in the chordwise direction, so that a spanwise array is formed; and the adjacent inclined groove groups are arranged at intervals, so that the plurality of inclined groove groups are integrally zigzag. The inclined grooves are formed in the tail edge of the upper surface of the wing, on one hand, a stable secondary vortex can be formed in the inclined grooves, the effect of a rolling bearing in machinery is achieved, and the effect of reducing viscous resistance is achieved; and on the other hand, the inclined grooves play a role of a vortex generator, secondary flow is formed in the boundary layer of the upper wing surface of the wing, mixing of high-speed flow of main flow and low-speed flow of the boundary layer is enhanced, propagation of the low-speed flow to the main flow is blocked, the capability of resisting reverse pressure gradient is higher, separation of the boundary layer can be restrained, and the lift-drag ratio is effectively increased.

The invention discloses a steam-turbine large hydraulic valve performance life test device and belongs to the fatigue test device technology field. The device comprises a reversing valve driven by a driving mechanism. The driving mechanism comprises a machine body. A worm and a worm wheel which are mutually transmitted and cooperated are arranged in the machine body. The worm is driven by a motor installed on the machine body. The worm wheel is fixedly connected to a lower middle portion of a stroke adjusting sleeve. The stroke adjusting sleeve is rotatably cooperated with the machine body. An upper portion of the stroke adjusting sleeve is clamped with a stroke adjusting block which is integrally rotated. The stroke adjusting block and the stroke adjusting sleeve are radially and slidably cooperated. An external portion of the stroke adjusting block is firmly cooperated and fixed with a concentric cam. One side of the concentric cam forms top contact cooperation with a slide block. The slide block is linked and cooperatively connected to a main valve core of the reversing valve. By using the steam-turbine large hydraulic valve performance life test device, the driving mechanism drives the main valve core of the reversing valve to carry out left and right reciprocating motion. The device is suitable for performance testing of the reversing valve.

The invention discloses a phase difference hydraulic tightening and loosening type clamp device, and belongs to the technical field of fatigue testing devices. The phase difference hydraulic tightening variable clamp device comprises a handle and a rotating shaft connected with the handle in a matched mode, wherein the rotating shaft is coaxially provided with a cam I and a cam II, a phase difference is arranged between the cam I and the cam II, and the cam I and the cam II are synchronously provided with an opening A stable pressure maintaining area and an opening B stable pressure maintaining area; and the device further comprises an reversing valve and a clamping tool. According to the technical scheme of the phase difference hydraulic tightening and loosening type clamp device, when the reversing valve is reversed to a reversing opening A, hydraulic oil enters a piston chamber II, a push plate moves leftward, and a clamping plate is loosened; and when the reversing valve is reversed to a reversing opening B, the hydraulic oil enters a piston chamber I, the push plate moves to the right, and the clamping plate clamps. The device has simple and convenient use.

The invention discloses an axial flow fan three-dimensional impeller with leaf vein structures and arc cylindrical splitter blades. The axial flow fan three-dimensional impeller comprises a hub and further comprises curved-twisted blades and splitter blades, wherein a shaft sleeve is fixed on the hub by a connecting piece; the curved-twisted blades and splitter blades are fixedly connected onto the hub; the curved-twisted blades comprise suction surfaces and pressure surfaces; wing grooves are formed in the tops of the curved-twisted blades; leaf vein shaped grooves are formed in upper half parts of the pressure surfaces of the curved-twisted blades; the wing grooves are communicated with the leaf vein shaped grooves through air outlets; small wing protrusions are arranged at the tails of the suction surfaces of the curved-twisted blades; parabolic pinholes are formed in the curved-twisted blades; a splitter blade is arranged between every two adjacent curved-twisted blades; and the height of each splitter blade is smaller than one half of that of the curved-twisted blade.

The invention discloses a two-dimensional primary and secondary compensation spray rotation steam pipe fast-switching device and belongs to the technical field of petrochemical equipment. The two-dimensional primary and secondary compensation spray rotation steam pipe fast-switching device comprises a first valve body. The first valve body is internally provided with a first valve rod, wherein thefirst valve rod is movably matched with the first valve body in a sealed manner. The rear portion of the first valve rod is provided with a first rear valve plate. A valve body cavity is divided intoa first valve cavity A and a first valve cavity B through the first rear valve plate. A second valve body of the same structure is arranged at the outer side of the first valve body in a matched manner. The device further comprises a reversing valve connected with the first valve body and the second valve body. The front end of the first valve rod is provided with a first valve disc. The first valve disc extends into a pipe cavity and is matched with or separated from a first pipe opening in a sealed manner. The two-dimensional primary and secondary compensation spray rotation steam pipe fast-switching device is provided with bidirectional parallel valves and achieves synchronous driving, and fluid in the pipe can be thoroughly intercepted; and the device is good in reliability, high in stability and safe and convenient to use. Under the combined action of a main valve element and a rotary push small valve, the labor intensity is remarkably lowered, and the work efficiency is improved.