141 results about "Ullage" patented technology

The utility model relates to the technical field of fans, in particular to a fan balancing structure, which is characterized in that counter weight is adjusted through the design of circular array balancing columns on a disc, so that when an impeller rotates, dynamic balance can be ensured, the balancing precision is improved, and through the design of an arc-shaped gradually-expanded blocking wall along the disc, the balancing precision is improved. The width of the blocking wall is gradually increased in the rotating direction of the impeller, airflow can be guided to be smoothly transited to the air guide cavity from the containing cavity, impact between the airflow and the wall face of the volute and generation of local vortexes are reduced, turbulence noise is lowered, the airflow is prevented from flowing backwards into the containing cavity, vibration caused by collision between the impeller and the airflow is avoided, and dynamic balance of the impeller is guaranteed. Meanwhile, the divergent structure is matched with the airflow diffusion rule under the centrifugal force effect of the impeller, energy loss is reduced, and the fan efficiency is improved.

The utility model belongs to the technical field of cranes, particularly relates to a mast crane with good durability, and provides the following scheme aiming at the durability problem: the mast crane comprises a track, the upper surface of the track is fixedly connected with a push block; a base is mounted on the outer surface of the track in a sliding manner; the upper surface of the base is fixedly connected with a mast crane body; an observation window is arranged on the outer surface of the base; a guide groove is formed in the lower surface of the base; mounting frames are fixedly connected to the outer surfaces of the two sides of the base; a cleaning brush is fixedly connected to the inner surface of the mounting frame; a liquid storage tank is arranged on the inner surface of the base; the upper surface of the base is fixedly connected with a guide shell. Through the arrangement of the liquid storage tank, the track is automatically lubricated, the friction loss is reduced, and the durability is improved; and through arrangement of a cleaning brush, dust on the surface of the rail can be cleaned through the cleaning brush, and meanwhile lubricating oil on the surface of the rail can be evenly smeared.

The invention relates to a flight outfield engine ground oil seal system, and belongs to the technical field of flight outfield guarantee. A flight outfield engine ground oil seal system comprises an APU test bed, an auxiliary oil tank, an engine, an APU control board and an oil seal vehicle. The APU body is fixed on the rack by the APU test bed; the auxiliary fuel tank is communicated with the nitrogen charging vehicle, fuel in the auxiliary fuel tank is pressurized by nitrogen pressure provided by the nitrogen charging vehicle, and fuel is supplied to the APU and the engine; the engine and APU console 5 is connected with the APU to control the working states of the APU and the engine; oil seal pipe connectors of the oil seal vehicle are connected with oil seal connectors of the left engine and the right engine respectively. Compared with the prior art, the method has the following advantages that related resources of a flight outfield are utilized, manpower resources are saved, loss of an aircraft and an engine in the engine disassembling and assembling process is avoided, and unnecessary working time of the engine is shortened; the oil sealing work does not need to be completed specially by stopping an airplane, and the oil sealing cost of an engine returned to a factory is also saved.

The utility model belongs to the technical field of unmanned pallets, and particularly relates to an electric flow guide cover suitable for an unmanned transportation container pallet, which comprises a flow guide cover arranged above a vehicle body, the flow guide cover is of a streamline structure, and a rotating shaft is arranged at the bottom of the flow guide cover; the two ends of the rotating shaft are movably sleeved with lower shaft seats, and the lower shaft seats are fixedly arranged on the upper surface of the head of the vehicle body. Electric push rods are arranged on the two sides of the flow guide cover and can stretch out and draw back, the upper ends of the electric push rods are fixedly arranged on the upper middle portion of the flow guide cover through bearings, and the lower ends of the electric push rods are fixedly arranged on the side face of the vehicle body through bearings. The flow guide cover is arranged to be of a streamline structure to dredge air flow on the vehicle head and the two sides, wind resistance can be reduced, and power loss can be reduced; in addition, the controller controls the electric push rod to push the flow guide cover to incline forwards, container hoisting operation is facilitated, the flow guide cover is put down backwards when operation is not carried out, the windward area can be reduced, and wind resistance is further reduced.

The utility model relates to the technical field of undercarriages, in particular to a modular undercarriage with a strong stability mechanism, which comprises a bearing frame, two adjusting plates are fixedly connected to one side of the bearing frame and are symmetrically arranged, an auxiliary bearing frame is fixedly mounted at one end of the bearing frame, and a plurality of auxiliary bearing frames are fixedly mounted at the other end of the bearing frame. The surface of the adjusting plate is rotatably connected with a mounting plate, the surface of the mounting plate is fixedly connected with a first shock absorption supporting column, the first shock absorption supporting column is hollow, and the inner wall of the first shock absorption supporting column is slidably connected with a vertical rod. Kinetic energy generated when the aircraft lands on the runway is converted into electric energy to be transmitted to the super-capacitor module to be stored, so that energy which is originally consumed and wasted in the braking process is recycled, cyclic utilization of the energy is achieved, the overall energy utilization efficiency of the aircraft is improved, dependence on external energy is reduced to a certain degree, and the operation cost is reduced.

The utility model discloses a front landing leg supporting structure of a bridge girder erection machine, which relates to the technical field of bridge construction, and comprises a structure main body and a front landing leg body, the upper side of the structure main body is fixedly connected with a vertical rod, and the front landing leg body is placed at the upper end of the vertical rod in an abutting manner; the upper side of the structure body is slidably connected with two sets of symmetrically-arranged supporting seats, the upper ends of the supporting seats are provided with step faces, the plane layers of the step faces are provided with first clamping grooves and second clamping grooves, the bottom of the front supporting leg body is provided with a sliding positioning mechanism, and the two sides of each supporting seat are fixedly connected with hanging rings. Mounting seats are fixedly connected to the center and two ends of the upper side of the structure main body, and stretching mechanisms are mounted on the upper sides of the mounting seats. The device can assist the bridge girder erection machine in lifting the front supporting leg, on one hand, the power loss of the bridge girder erection machine is reduced, an auxiliary effect is achieved, on the other hand, it can be guaranteed that the front supporting leg is kept in a balanced and stable state in the lifting process, and the construction safety in the lifting process of the front supporting leg of the bridge girder erection machine is greatly improved.

The utility model relates to a warmer with a long blowing distance. The hot air conveying distance of an existing warmer is short, and the use experience is affected. The air conditioner comprises a shell, a circulating fan and an air duct are arranged in the shell, an air inlet of the air duct is communicated with an outlet of the circulating fan, an air outlet of the air duct is exposed out of the surface of the shell and communicated with an indoor space, and a plurality of unit channels with the same orientation are formed in the air outlet by arranging air guide grilles. Airflow in the air channel is divided into multiple strands of linear air beams through the unit channels, so that the airflow conveying distance is increased. The air guide grille is arranged at the air outlet, air flow from the air duct is divided and forms multiple linear air beams in the same flow direction, the adjacent air beams flow in the same direction and do not interfere with each other, kinetic energy loss is effectively reduced, the conveying distance is increased by increasing the flow speed of the air flow, and the use experience is improved.

The invention discloses an active anti-swing and all-directional lifting appliance micro-motion system, relates to the technical field of cranes, solves the problems of efficiency loss and safety risk caused by lifting appliance swing of a traditional container crane, repeated correction cost of alignment deviation, adaptive fault of precision speed and automation requirements and the like, and comprises a crane carriage and a special lifting appliance, the hoisting trolley is connected with the winding system, the winding system comprises a plurality of steel wire ropes, the special lifting appliance comprises a lifting appliance upper frame and a plurality of steel wire rope fixing devices, the steel wire ropes are connected to the corresponding steel wire rope fixing devices, and corresponding moving devices are connected between the steel wire rope fixing devices and the lifting appliance upper frame. And the moving device drives the steel rope fixing device and the lifting appliance upper frame to move relatively. Through a winding system and a plurality of moving devices, a combined system of active anti-swing and omni-directional lifting appliance micro-motion is completed, and the dual effects of swing suppression and fine alignment are achieved.

The application relates to the technical field of pipeline dredging, and particularly discloses a flushing and twisting type waterwork pressure measuring pipe silt blocking and cleaning device and a silt cleaning method, which comprises a fixed chassis, the top of the fixed chassis is provided with an annular opening structure, and movable universal wheels are arranged at the bottom of the fixed chassis; the top of the fixed chassis is fixedly connected with a supporting mechanism; a first fixed plate is fixedly connected with a booster delivery pump at the top; and a first connecting pipe is connected with the water outlet of the booster delivery pump. The silt cleaning mode combining cutting and twisting with high-pressure flushing is adopted, the silt cleaning efficiency is greatly improved, the connecting assembly is arranged, quick disassembly and sealing are realized, the pressure stability is guaranteed without loss, the pressure leakage is avoided to affect the silt cleaning efficiency, the supporting mechanism is arranged, accurate limiting and protection are provided for silt cleaning operation, and the operation stability and safety are improved.

The application provides a flapping-wing aircraft sensing and control integrated test support platform based on cooperation of three mechanical arms, and belongs to the technical field of robot test equipment. The flapping-wing aircraft sensing and control integrated test support platform comprises a motor, a fixed support mechanism, a rotary driving mechanism, a transmission connecting mechanism and a working assembly. The motor is arranged in the fixed support mechanism, the rotary driving mechanism is arranged at the top of the fixed support mechanism, the working assembly is arranged at the top of the rotary driving mechanism, the motor is connected with the rotary driving mechanism through the transmission connecting mechanism and provides power for the rotary driving mechanism, the transmission connecting mechanism is used for transmitting power of the motor, and the rotary driving mechanism is used for driving the working assembly to rotate. The flapping-wing aircraft sensing and control integrated test support platform can realize multi-degree-of-freedom attitude control of flapping-wing aircraft test, can simulate a test environment under different wind speed conditions, has reasonable wire layout, can separate power supply of high-power equipment and conventional power equipment, improves power supply efficiency, reduces line loss, is stable in driving, accurate in movement, and accurate and reliable in test data.

The application discloses a kind of high-efficiency omni-directional decoupling annular vector tilt-rotor aircraft and control method thereof, aircraft includes fuselage, fuselage driving gear set, four tilting mechanisms, four annular vector tilt-rotor power groups and electronic equipment etc.Parts.The aircraft described in the application can realize six degrees of freedom omni-directional pose decoupling flight, the attitude angle is omni-directional arbitrary angle in it, including roll angle, pitch angle and yaw angle, can realize arbitrary attitude hovering and flight of aircraft.The aircraft described in the application solves the controllable attitude angle limit of conventional variable tilt-rotor mechanism from structure, improves the ability of complex space activity of aircraft, and fundamentally solves the problem of power offset and power redundancy, reduces energy loss, improves power efficiency, prolongs endurance time, and is suitable for application scenarios requiring strong anti-interference and air physical interaction capability, and has important significance and value in the future.

A luggage handle, comprising a handle part and a connecting part; the connecting part is embedded in both ends of the handle part; the connecting part comprises a fixed shell, a pull rod, a spring group and a base assembly arranged in the fixed shell; one end of the pull rod is connected with the handle part; the other end is connected with the base assembly; the upper end of the spring group is fixed on the inner wall of the fixed shell, and the lower end is detachably mounted on the base assembly; by pulling the handle part upward, the pull rod is driven to move upward, so that the spring group is compressed from bottom to top to realize elastic stretching. The elastic stretching luggage handle of the present application, compared with the traditional stretching handle made of rubber material, uses rigid plastic, stainless steel and other materials that are not easy to wear and tear, greatly reduces the probability of handle aging and damage, and at the same time ensures the strength requirement in the stretching process; a plurality of springs are used to realize the stretching and retracting function, fully ensuring the comfortable feeling in the lifting process.

The application discloses a kind of full closed tank car oil unloading device, including unloading tank, the input end of the unloading tank is fixedly connected with unloading hose, the output end of the unloading tank is equipped with unloading pump, and unloading tank is connected with the output end of oil tank car by unloading hose;The top side of the unloading tank is fixedly connected with air pipe assembly;The full closed tank car oil unloading device is set by the setting of each component of the top side of unloading tank, and the inner cavity of unloading tank and the inner cavity of oil tank car are communicated by unloading hose and air pipe assembly, so that it is an entire closed space between cavity, and negative pressure is formed in tank car due to the suction effect of unloading pump during oil unloading, and positive pressure is formed with unloading tank, at this time, due to the rise of liquid level, the gas space on the inside upper part of unloading tank is compressed to cause the breathing valve to open and escape oil gas, the loss of this part of oil gas is re-entered into oil tank car through air pipe assembly, and after unloading tank reaches pump starting liquid level, exhaust valve is closed, and unloading pump is input into gathering and transportation system together, to form full closed oil unloading.

This invention relates to the technical field of wind power generation, and proposes a method, system, and device for automatically adjusting the weight of wind turbine blades. The method includes acquiring wind speed data v and blade size data; confirming the total vibration damping loss of the blade; confirming the total friction loss of the hub bearing; confirming the total power loss of the system; solving for the optimal value of the total power loss; calculating the first-order partial derivative of the total power loss of the system with respect to the mass of a single counterweight; setting the partial derivative to 0 to solve for the optimal counterweight mass of the i-th cavity; controlling the corresponding solenoid valve of each cavity to inject the target amount of liquid into each cavity. This invention calculates the optimal counterweight of the cavity in real time, enabling on-demand liquid injection and discharge, avoiding the problems of vibration and instability caused by light blades at high wind speeds, and the problem of blades not fully utilizing wind energy and reducing power generation due to heavy blades at low wind speeds.

The application discloses a general structure of a cross-domain vehicle, which comprises a flight unit autonomous folding and unfolding structure and a tail fixed shaft propeller mounting structure. The flight unit autonomous folding and unfolding structure is mounted in front of a rear propeller of a boat body and is controlled through a rudder mounted on the boat body. Rotation of the rudder drives rotation rods and connecting rods to move, so that the connecting rods of the flight unit are unfolded. After unfolding, the rotation rods connected with the rudder are positioned in grooves and the unfolded structure is triangular and stable. The vehicle control cabin sends signals to realize folding and unfolding of the flight unit through control of the rudder. The purpose of autonomous folding and unfolding of the flight unit is achieved, and the lift generated by the flight unit is transmitted to the boat body without loss. The tail fixed shaft propeller is connected with the vehicle boat body through a connecting component. The connecting component is at a fixed angle with the center line direction of the boat body, so that the tail of the fixed shaft propeller is inclined inward. The thrust of different propellers is controlled, and the purpose of high-efficiency differential control is achieved.

The utility model provides a steerable aircraft undercarriage folding and unfolding structure, which relates to the technical field of aircraft undercarriages, and comprises a steering undercarriage assembly, the steering undercarriage assembly comprises a folding and unfolding rack, a hydraulic push rod, a connecting arm and a steering wheel, the hydraulic push rod is rotatably connected in the folding and unfolding rack, the steering wheel is rotatably connected on the connecting arm, and the connecting arm is connected with the hydraulic push rod; in the mounting assembly, a mounting plate is matched with four rotatable buffering mounting pieces which are distributed in a rectangular shape, vibration generated during operation of the aircraft can be effectively buffered, loss of parts is reduced, the service life of the aircraft is prolonged, the weight of the mounting plate is reduced through load reducing holes, and the structural strength of the mounting plate is ensured through reinforcing rods; and in the deformation assembly, arc-shaped elastic steel and auxiliary elastic steel cooperate with each other, flexible deformation and energy absorption can be achieved when the aircraft is subjected to external force or steers, and the landing stability and impact resistance of the aircraft are enhanced.

The invention discloses a method for quickly repairing an abraded inner hole of a split bearing seat, which comprises the following steps of: A1, cleaning the bearing seat, and cleaning the surface of the bearing seat; a2, loss measurement: measuring the inner diameter of the bearing seat to obtain the abrasion loss of an inner hole; a3, a repair value is determined, and the machining size is determined according to the abrasion loss; a4, bearing seat mounting surface machining is conducted, specifically, the bearing seat mounting surface is machined according to the repair value; a5, bearing seat combination, wherein the upper bearing seat combination and the lower bearing seat combination are arranged on machining equipment; a6, bearing seat inner hole machining is conducted, and the bearing seat inner hole is machined; a7, positioning pin holes are machined, specifically, the positioning pin holes of the upper bearing seat and the lower bearing seat are machined; a8, machining end cover mounting holes, wherein the end cover mounting holes in the two sides of the bearing seat are machined; and A9, the height of the bearing seat is adjusted, a base of the bearing seat is heightened, and the height of the machined bearing seat is the same as that of the bearing seat before machining. According to the method, the inner hole of the bearing seat can be quickly repaired after being abraded, so that the production loss caused by shutdown maintenance is reduced.

The utility model discloses an axial motor, a heat dissipation system and a flight device, the axial motor is applied to the heat dissipation system and the flight device, the axial motor comprises a stator assembly, the stator assembly comprises a support main body and a separator plate assembly, and the support main body is provided with a shaft hole and an annular groove communicated with the shaft hole; the partition plate assembly is located in the shaft hole, and at least part of the partition plate assembly is embedded in the annular groove; the space defined by the partition plate assembly and the inner wall of the annular groove forms a liquid flowing channel, and at least part of the liquid flowing channel extends in the radial direction of the annular groove. The cooling liquid is circularly injected into the liquid flowing channel, so that redundant heat generated by the operation of the stator assembly can be effectively taken away, the temperature of the stator assembly is reduced, the heat loss of each operation part of the axial motor is reduced, and the service life of the axial motor is further prolonged.

The invention belongs to the technical field of magnetic suspension motors, and discloses a magnetic suspension bearing optimization design method and system based on electromechanical thermomagnetic multi-physics field coupling. The method comprises the following steps: determining an optimization target taking improvement of bearing capacity and rigidity, reduction of iron core loss, reduction of temperature rise and reduction of volume as a core, selecting key structure parameters as optimization variables, and setting constraint conditions of volume, rotor mode, iron core flux density saturation, temperature rise, loss and bearing capacity of key positions of a stator and a rotor; an overall group optimization (HSO) algorithm is adopted, multi-objective optimization is achieved through population initialization, coefficient calculation based on root mean square (RMS) fitness, position updating driven by overall population information, selection based on simulated annealing and a self-adaptive variation mechanism, and the optimization effect is verified through finite element simulation and prototype testing. According to the method, the performance indexes of the magnetic suspension bearing are effectively balanced, and the optimization efficiency and the design reliability are improved.

Apparatuses, kits, and methods for enhancing handling of a sample cylinder of liquified petroleum gas may include a housing, a first mounting station, and a second mounting station. The first mounting station may include a first mounting fixture connected to the housing and configured to attach to the sample cylinder, and the second mounting station may include a second mounting fixture connected to the housing and configured to attach to an expansion chamber. A first valve may provide fluid flow from the sample cylinder to a waste destination or fluid flow from a source of pressurized gas to the sample cylinder. A second valve may provide fluid flow from the sample cylinder to the expansion chamber and a third valve may provide fluid flow from the expansion chamber to a waste destination.

The invention provides a ducted thruster thrust testing device and testing method. The thrust testing device comprises an air duct type mounting base, an axial linear moving platform, a ducted fan, an air inlet pipe, an air outlet pipe, an auxiliary fan and a pull pressure sensor assembly. The ducted fan comprises a ducted shell and a core assembly, the core assembly comprises a supporting guide vane, an impeller and a motor assembly, a linear cylindrical guide rail assembly is arranged between the supporting guide vane and the ducted shell, and the thrust value of the core assembly can be independently measured through the arrangement of the linear cylindrical guide rail assembly. The thrust value of the core assembly is compared with the overall thrust value of the ducted fan, and the influence of the ducted shell on the thrust is evaluated; if the overall thrust value is larger than the thrust value of the core assembly, it is indicated that the thrust of the ducted shell is increased; if the overall thrust value is smaller than the thrust value of the core assembly, it shows that the duct shell causes energy loss.

The invention provides a portable test box for imported gyroscopes. A power supply module, and a phase sequence detection module, a power supply indication module, a transformer assembly, a signal measurement module and a 24-core circular connector which are connected with the power supply module through a state switching module are arranged in a box body. The method can separate from other equipment of a heading system to independently test imported gyroscopes, does not need to depend on a whole machine or a heading system core assembly, can directly detect the gyroscopes, and quickly judges whether faults are derived from gyroscope parts or not; the problems that an existing imported helicopter gyroscope test depends on other equipment, fault positioning is slow, test precision is low, maintenance resources are consumed, and normal parts are possibly consumed are solved, the functions of phase sequence detection, power state indication, angle signal resolving display and skew state monitoring are achieved, fault positioning efficiency and test precision are improved, and the test cost is reduced. And the fault positioning time is greatly shortened, the maintenance resource consumption and the normal part loss risk are reduced, and the safety and continuity of the operation of the imported helicopters are guaranteed.

The utility model discloses a quick cold pressing device for steel door production, which relates to the technical field of quick cold pressing devices and comprises a cold pressing device body, a workbench, a door leaf, a partition buffer plate and a tray, and the cold pressing device body is mounted at the top of the workbench. According to the cold pressing device, the door leaves are stacked and attached to the tray in advance through the alignment curing assembly, then the tray is limited and positioned at the top of the workbench through the limiting and positioning assembly for stable cold pressing, and the problems that according to an existing cold pressing device, materials such as the door leaves need to be manually stacked one by one, the time consumed in the loading and positioning process of the materials in the device is long, and the working efficiency is high are solved. Position deviation easily occurs in manual operation, repeated adjustment and correction are needed, time loss of a loading link is aggravated, a traditional process is low in curing speed, long-time waiting is needed due to lack of a rapid fixing mechanism after material stacking, the idling rate is high, the production takt is stopped, and the actual effective processing time of equipment is greatly shortened due to double factors. And the production efficiency of a cold pressing link is seriously restricted.

The invention discloses a dynamic lubrication characteristic analysis method for a sliding shoe pair of an aviation fuel plunger pump. The method comprises the following steps: 1, constructing a piston shoe pair kinematics and dynamics model; 2, establishing a piston shoe pair oil film pressure negative feedback regulation model, and constructing a piston shoe pair lubrication model according to the piston shoe pair kinematics and dynamics model established in the step 1; 3, solving the kinematics and dynamics model, established in the step 1, of the sliding shoe pair and the lubrication model, established in the step 2, of the sliding shoe pair; 4, based on the sliding shoe pair oil film lubrication model established in the above step and a solving method, conducting model simulation on the sliding shoe pair oil film lubrication characteristics under different plunger pump working conditions, analyzing the influences of working condition parameters of the rotating speed and the outlet pressure on the sliding shoe pair oil film thickness, the pressure distribution oil film and other lubrication characteristics, friction loss and leakage flow, and calculating the sliding shoe pair oil film lubrication characteristics. And obtaining the dynamic lubrication characteristics of the piston shoe pair of the aviation fuel plunger pump. The method has the characteristics of high prediction accuracy and high stability.

The utility model discloses a rolling type triggered liquid level sensor, which relates to the technical field of liquid level sensors, and comprises an outgoing line, a rocker arm, a pin shaft, a sensor base, a flexible circuit contact plate, a sealing adhesive and a thick film resistor substrate, the upper end of the thick-film resistor substrate is sealed and closed by the sealing mucilage glue, and a rolling mechanism is arranged on one side of the upper end of the thick-film resistor substrate and connected with the rocker arm in a matched mode; the liquid level sensor is triggered in a rolling mode. Through meshing transmission of the gear and the rack and rolling contact of the roller on the flexible circuit contact plate, friction loss is greatly reduced, and signal stability is improved; the flexible circuit contact plate, the sealing adhesive and the thick-film resistor substrate are seamlessly attached, so that deformation and sealant pulling are reduced, and the service life is prolonged; the dense tooth number design of the gear improves the walking precision and ensures the liquid level detection accuracy; the device is compact in overall structure, suitable for corrosive environments such as oil and high in reliability.

The invention discloses a universal aircraft spherical fire extinguishing bottle fixing device which comprises a supporting frame, a lifting mechanism, a lateral clamping mechanism and a connector positioning mechanism, the lifting mechanism is installed in the supporting frame in a liftable mode, and the lateral clamping mechanism is composed of at least two clamping assemblies oppositely arranged on the two sides of the supporting frame. The connector positioning mechanism is arranged on the top face of the supporting frame. An operator can complete cutting work through one key only by electrically controlling an operating system, so that the labor intensity is reduced; the cutting path and the cutting depth can be quantified, and the cutting quality is high; notches are smooth, fine grinding is not needed after cutting, and the cutting efficiency is high; loss of the boss is small, and the service life of the fire extinguishing bottle is prolonged; cutting personnel can be qualified for cutting work only by equipment use training, so that the training cost is reduced; the CNC machining center is mature in technology, stable in cutting quality and high in safety; the device is easy to use, convenient to repair and maintain, easy to upgrade and reconstruct, and high in practicability.

The utility model discloses a high-speed refrigerated centrifugal machine, which relates to the field of refrigerated centrifugal machine structures and comprises a fixed seat, a centrifugal chamber arranged in the fixed seat, a driving component arranged in the fixed seat, a rotating head rotatably arranged in the centrifugal chamber and connected with the driving component, and a refrigeration component arranged on the fixed seat and capable of realizing cooling in the centrifugal chamber. The rotating head comprises a rotating seat, the rotating seat is connected with the driving assembly, a plurality of placing grooves are annularly formed in the top of the rotating seat, a refrigeration ring groove is coaxially formed in the bottom of the rotating seat, and connecting grooves are formed in the sides, close to the refrigeration ring groove, of the placing grooves and connected with the refrigeration ring groove; according to the high-speed freezing centrifugal machine, sufficient buffer protection can be provided for a sample, meanwhile, the cooling capacity generated by the refrigerating assembly can be quickly transferred to the sample in the containing groove, the transfer loss is reduced, and the freezing efficiency is improved.

The utility model discloses a light-load starting and lubricating oil distribution type heavy-load sliding bearing device which comprises a sliding bearing seat, a detachable electromagnet and a novel bearing bush. The detachable electromagnet is located over the sliding bearing seat. The novel bearing bush is positioned in the sliding bearing seat; the detachable electromagnet is started before the shaft works, suction force to the shaft is generated, the pressure of the shaft to the bearing bush under the gravity effect is reduced, and abrasion to the bearing bush in the starting process of the shaft is reduced; through the oil groove structural design, the oil groove sectional area of the seriously-abraded end of the bearing bush is relatively large, so that lubricating oil is reasonably distributed according to working conditions, heat dissipation of local seriously-abraded places of the bearing bush is accelerated, the oil film thickness is maintained, and local abrasion is reduced; through the offset oil hole design, the design position is offset to the maximum oil film thickness position of the bearing bush, and the central axis position of the oil hole is vertically downward, so that the distribution of lubricating oil on the bearing bush is accelerated, the oil pressure part is converted into bearing rotation power, the energy loss is reduced, and meanwhile, the bearing bush bearing area stress is reduced.

A combined fuel level sending unit and fuel fill limit vent valve configured for use with a fuel tank is disclosed including a sending unit rod having a first end and a second end defining a length and a plurality of sensors disposed along its length mounted to a valve body which includes a first valve port, including a receptacle and a valve seat, and a second valve port, mounted to the valve body, in fluid communication and defining an inner sidewall and an outer sidewall. An ullage float comprising a magnet is also slidably mounted on the sending unit rod between the first end and a sealing ledge on the valve seat so that the ullage float fits within the receptacle and valve seat in the valve body. It comprises a magnet configured to interact with the plurality of sensors to provide an indication of a level of fuel in the fuel tank.

The application discloses a kind of mute energy-saving fan, it is related to fan field, the noise pollution is serious to the background technology proposed, traditional blade generates up to 85dB above aerodynamic noise;Ordinary ball bearing friction loss can occupy a part of whole machine energy consumption, and the problem of low energy efficiency, the following scheme is presented, including the aluminum alloy shell being equipped with flange at both ends, the outer polyurethane foam layer is covered outside shell, sound-absorbing layer is arranged in shell, sound-absorbing layer includes fixed ring, inner polyurethane foam layer is covered on the outer wall of fixed ring and two shock-absorbing rubber rings respectively fixedly arranged on the outer wall of fixed ring both ends, flow guide ring is fixedly arranged in fixed ring, foam aluminum is arranged outside flow guide ring, fixed mechanism is arranged in fixed ring, and fixed mechanism includes mounting ring.The application can effectively suppress the noise generated when fan operates, improve the mute effect, can improve motor energy efficiency through the synergistic effect of airflow optimization and vibration reduction, and further reduce noise.