312 results about "Ullage" patented technology

The invention relates to the technical field of sealing test, in particular to a sealed cabin heating system for high-temperature rotary dynamic sealing test and a test device. The device comprises a sealed cabin, a circulating pipeline is connected between a liquid inlet and a liquid outlet of the sealed cabin, and a circulating pump and a heater are mounted on the circulating pipeline; a high-level tank is further connected to the circulating pipeline so as to supplement liquid into the circulating pipeline when the liquid in the circulating pipeline is lost; the circulation pipeline or the sealed cabin is connected with a pressure relief pipeline, and a sealing valve is installed on the pressure relief pipeline. According to the invention, the burden and energy consumption of the heater are reduced, and the method also has the advantages of high medium temperature rise rate, short regulation time efficiency and high precision.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a fuel cell stack auxiliary power unit (APU) and a first tank arranged to store liquid hydrogen with an ullage. A first fuel line includes a first pump and a first vaporiser and transports hydrogen from the first tank to combustion apparatus of the engine during operation of the propulsion system. A second fuel line includes a second fuel pump and a second vaporiser and transports hydrogen from the first tank to the fuel cell stack APU. A duct connects the second fuel line at a position thereon between the second vaporiser and the fuel cell stack to the ullage of the first tank, providing for pressure in the first tank to be maintained therein as liquid hydrogen within the first tank is depleted, thus avoiding cavitation of liquid hydrogen within the first fuel pump.

The retracting and releasing mechanism comprises a retracting and releasing bin, a propeller body is connected to the interior of the left side of the retracting and releasing bin, a propeller is connected to the bottom of the propeller body, and a bin door is rotationally arranged at the bottom of the right side of the retracting and releasing bin through a rotating shaft; the fixed column is installed on the inner wall of the rear side of the collecting and releasing bin, the outer side of the fixed column is sleeved with a circular plate, and the circular plate is slidably connected with spray pipes used for cleaning at equal angles; and the rotary cleaning mechanism is arranged on the rear side of the collecting and releasing bin and on the circular plate, and the rotary cleaning mechanism cleans the propeller by driving a spray pipe to move and rotate, so that corrosion loss caused by seawater and attached microorganisms is reduced. According to the retracting and releasing mechanism for the lifting type thruster, after the thruster is retracted, the spraying pipe can be driven to blow air to remove water from a propeller of the thruster in a rotary opening and closing mode, and then corrosion loss of the thruster caused by seawater and attached microorganisms is reduced.

The invention belongs to the field of aero-engines, and discloses a low-pressure casting process design method for a fuel regulator and the fuel regulator. According to the method, modeling is conducted on the fuel regulator to obtain a three-dimensional model of the fuel regulator; based on the three-dimensional model of the fuel regulator, numerical simulation is conducted on the liquid lifting, mold filling and cooling solidification processes of the casting to predict metallurgical defects of the casting, the metallurgical defects of the casting are analyzed, and a simulation result is obtained; and optimizing low-pressure casting process parameters or / and a process based on an analog simulation result to finally obtain a low-pressure casting process optimization scheme of the fuel regulator. By adopting the method, the forming quality of the complex casting is improved, the blindness of trial-manufacturing depending on experience in the traditional process is reduced, and the product percent of pass is improved while the research and development period is shortened; and the cost loss caused by defect repair is greatly reduced, and a systematic process guarantee is provided for efficient and precise manufacturing of the aero-engine fuel regulator.

The invention relates to the technical field of undercarriages, in particular to a folding undercarriage device of a low-altitude aircraft, which comprises an aircraft body, a pesticide spraying mechanism for crop fertilization is arranged on the aircraft body, a height-adjustable undercarriage mechanism is arranged at the lower end of the aircraft body, and a landing buffer mechanism is arranged on the undercarriage mechanism. The landing buffering mechanism is used for reducing impact on the undercarriage mechanism at the moment of landing, a linkage auxiliary mechanism is arranged on the aircraft body, the undercarriage mechanism comprises a fixing plate body, and the fixing plate body is detachably installed on the aircraft body. By arranging the undercarriage mechanism and adopting a dynamic folding design, after taking off, the second-stage frame body retracts to drive the telescopic joint to be shortened, so that the overall height is reduced, air turbulence during flight can be effectively reduced, meanwhile, the first-stage frame body rotates to be parallel to the fuselage, the cross sectional area of the undercarriage mechanism is greatly reduced, and the overall height is reduced. And the wind resistance loss during high-speed flight can be obviously reduced.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

The invention discloses a low-resistance bonding ceramic tube coating material and a coating method thereof, and relates to the field of steel tube coatings, and the low-resistance bonding ceramic tube coating material comprises a bottom layer material, a ceramic hybrid layer material and a hydrophobic functional material. According to the low-resistance bonding ceramic tube coating material and the coating method thereof, through coating of the bottom layer material, the ceramic hybrid layer material and the hydrophobic functional material, a coated steel tube can have natural resistance to corrosive media such as acid, alkali and salts, and even under the long-term complex working condition, the corrosion resistance of the steel tube is greatly improved. The roughness of the inner wall of the pipe can still be stably maintained within the range of 20-100 microns, the surface smoothness is 5-20 times that of a traditional pipe in the initial service stage, the friction coefficient of fluid and the pipe wall can be greatly reduced, the fluid can more easily form a laminar flow state, energy loss is effectively reduced, and the service life of the pipe is prolonged. And the composite material can be applied to the fields with extremely high requirements on energy consumption and stability, such as ships, airplanes, high-speed rails, ocean engineering, petrochemical engineering, sewage treatment, long-distance water delivery and the like.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

The invention relates to the technical field of control boxes, and discloses a main control box based on industrial control, which comprises a box body, an aviation socket arranged on one side of the box body, jacks annularly formed in the aviation socket, contacts arranged in the jacks, mounting seats arranged in the jacks, contacts arranged at the top of the mounting seats, and plugs arranged on the aviation socket, the plug is arranged in the box body, the contact pins are arranged on the plug, the devices are arranged in the box body, and the cleaning component is arranged in the jack. When the cleaning part works, extra power is not needed, the contact pin cleaning part is driven to rotate along the spiral hole through mechanical thrust generated when the plug is plugged in and pulled out, linear motion is converted into rotary scraping, cleaning while plugging is achieved, and the problems of energy consumption and structure complexity of a traditional active cleaning scheme are solved. By scraping dust and an oxide layer in real time, the fluctuation of contact resistance can be effectively controlled, and compared with a traditional aviation socket, the electric conduction loss and the heating risk are remarkably reduced.

The invention discloses an airfoil aerodynamic configuration adjusting method and device and a medium. Relates to the field of airfoil design, and solves the problems of high experiment cost and long iteration period caused by airfoil design optimization through a wind tunnel experiment. Geometric characteristics of the airfoil profile are converted into mathematical parameters through CST parameterization, airfoil profile performance data are rapidly obtained in combination with a preset selective neural network model, and the processes of physical model manufacturing, repeated blowing testing, CFD simulation, finite element analysis and the like in a traditional wind tunnel test are replaced. Hardware cost of wind tunnel equipment operation and maintenance, model processing and the like does not need to be invested, and material loss and time waste caused by physical model modification are also avoided. Besides, parameter disturbance, gradient optimization and geometric screening based on normal distribution are all realized through a computer algorithm, single-group parameter optimization can be quickly realized, and airfoil performance requirements under different working conditions can be quickly responded, while a traditional wind tunnel test needs several hours to several days for a single test, and the test needs to be rearranged after model modification.

The invention discloses an electromechanical multi-professional module integral lifting device and a construction method, and belongs to the field of lifting devices. The electromechanical multi-professional module integral lifting device comprises a moving seat, positioning frames are fixedly connected to the two sides of the top of the moving seat, the electromechanical multi-professional module integral lifting device further comprises a bearing bracket vertically sliding along the positioning frames, a lifting assembly is arranged on the moving seat, and the lifting assembly is used for pulling the bearing bracket to vertically slide along the positioning frames; the positioning block is fixed at the bottom of the movable seat, and the two sides of the positioning block are rotationally connected with movable wheels; through the repulsion effect of a magnetic plate and a piston plate and the arrangement of a first spring, circulating spraying of a lubricating agent is achieved, the friction effect borne by the lifting cable is reduced, the durability of the lifting cable is improved, the lifting safety is ensured, meanwhile, the situation that pollution is caused by dripping of excessive lubricating agent is avoided, recycling of the excessive lubricating agent is achieved, and the cost is reduced. The loss of the lubricant is effectively reduced, and the energy-saving effect is improved.

The utility model relates to a high-strength stable type gear which comprises a gear body, air bags are fixedly connected in tooth grooves of the gear body, exhaust holes are formed in the side of the gear, air outlet holes are formed in the sides, close to the axis of the gear body, of the air bags, and sealing plates are connected to the sides, close to the outer portion of the gear body, of the exhaust holes. The side, away from the exhaust hole, of the sealing plate is connected with a ventilation pipe. The utility model relates to the technical field of gears. When the high-strength stable gear is used, the gear body is continuously meshed with the corresponding gear, so that the air bag is extruded, air flow can be quickly blown to a tooth groove, to be meshed, of the gear body, and then centrifugal force of the gear body is matched; and dust impurity particles and metal particles in the tooth grooves in the gear body are separated from the tooth grooves, so that the loss during meshing of the gear body and the gear is reduced, and the service life of the gear body is prolonged.

The eVTOL aircraft tail thrust motor connecting structure is characterized in that a motor support comprises a motor base of an annular structure, a motor is arranged on the motor base, and a propeller is arranged on the motor; the motor base comprises a first step, a second step is arranged at the front end of the first step, the thickness of the first step is larger than that of the second step, and a motor connecting edge connected with a motor is arranged at the rear end of the first step. Two receding grooves are formed in the inner wall of the motor base, a plurality of connecting ribs connected with the first step and the second step at the same time are arranged on the outer wall of the motor base, the rear half sections of the connecting stringers correspond to the connecting ribs in a one-to-one mode and are connected with the connecting ribs and the second step at the same time, and the front half sections of the connecting stringers are connected with a horizontal tail on the machine body. The invention has the beneficial effects of improving the damage safety, ensuring the stability of the thrust line, reducing the flight attitude fluctuation, reducing the maintenance cost, reducing the power loss of the motor, improving the cruising ability, reducing the stress of the connecting part, prolonging the service life of the structure and the like.

The invention discloses an adjustable assembly type geosyncline device which comprises a fixed support, a mounting table located above the fixed support, a lifting structure used for adjusting the distance between the mounting table and the fixed support and a driving mechanism used for driving the lifting structure to conduct adjustment. The lifting structure comprises an inserting groove formed in the upper portion of the fixed support and an inserting rod which is rotatably connected to the lower portion of the mounting table and inserted into the inserting groove with the inserting depth adjustable, the height adjusting device can meet the requirements of different ground environments, height adjustment is conducted according to the mounting heights of different wallboards, the requirements of various supporting heights are met, and the practicability is high. And on-site secondary adjustment can be carried out, so that the purposes of reducing the assembly time and reducing the loss of assembly materials are achieved, and high popularization value is achieved.

The invention relates to the technical field of aero-engine gas flow path sealing, and discloses a labyrinth type multi-stage brush type sealing device which comprises a rotor runway and a multi-stage brush type sealing structure. The rotor runway comprises a plurality of convex parts and a plurality of concave parts, and the convex parts and the concave parts are sequentially and alternately connected in the first direction to form a concave-convex structure; the multi-stage brush type sealing structure comprises a plurality of brush type sealing units, part of the brush type sealing units abut against the protruding parts, and part of the brush type sealing units abut against the concave parts. The multi-stage brush type sealing is arranged, so that the pressure resistance of the sealing device is improved; and meanwhile, the rotor runway forms a concave-convex structure through sequentially and alternately connecting a plurality of convex parts and a plurality of concave parts, and is matched with a multi-stage brush type sealing structure to form a labyrinth sealing effect, so that double sealing is formed, a leakage flow path is increased, leakage energy loss is effectively increased, the leakage amount is greatly reduced, and the sealing performance of the whole device is improved.

The application belongs to the technical field of aircraft deicing, and discloses a reconfigurable intelligent aircraft deicing system and method. The hidden deicing liquid nozzle unit sprays deicing liquid on different deicing yard areas divided by different pressure nozzle assemblies to perform aircraft engine deicing operation; the deicing detection unit adopts image recognition technology to collect the ice and snow coverage area, thickness and type of the aircraft body in real time, and determines the aircraft model and parking position; the deicing waste liquid detection unit detects the physical property parameters of the deicing waste liquid during deicing operation in real time; the intelligent control unit controls the flow, temperature, pressure and angle of the nozzle assembly with the same pressure in real time, so as to optimize the deicing efficiency; the deicing liquid supply unit, deicing liquid conveying unit and deicing liquid recovery unit jointly supply and recycle the deicing liquid without interruption. The application greatly improves the deicing efficiency of the aircraft, greatly avoids the possibility of secondary icing of the aircraft, and maximally avoids the invalid energy loss.

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.

A multi-angle oil stirring loss test system for an aviation oil-cooled high-power high-rotating-speed motor comprises a pitch angle overturning test board, an upper computer control table, a cooling and lubricating system, a frequency conversion cabinet, a lubricating oil circulating system and a measurement and control cabinet, and the pitch angle overturning test board comprises an overturning angle control system, a bearing seat, a dragging system and a supporting frame. The system can accurately simulate the pitching flight attitude of an aircraft, exposes the heat dissipation and lubrication failure risk of the motor in advance, and guarantees the flight safety. The device has good vibration resistance and accurate angle control capability, and is adaptive to various motor cooling modes and types; and by adopting a modular design, the structure is simple, the maintenance is convenient, and data support can be provided for optimization and improvement of the aviation oil-cooled motor.

The present application discloses a steering device and its design method, a liquid level measurement system and method, relating to the technical field of liquid level measurement. The steering device includes a plane reflecting surface and a parabolic reflecting surface. The present application utilizes the combined technology of the plane reflecting surface and the parabolic reflecting surface to extend the parabolic focusing steering device technology that could only be used on vertical tanks to spherical tanks, sausage tanks and other special-shaped tanks, so that the main beam of the mechanical vibration wave emitted by the probe installed at any position and at any angle on the tank body all becomes a parallel beam without divergence loss and vertically shoots upward to the liquid surface in the tank, and focuses and reflects the liquid surface echo to the probe, increasing the intensity of the echo signal, achieving the effects of stable and accurate measurement of the liquid level in the tank, and moreover, the volume of the steering device can be reduced.

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 application relates to the technical field of railway sewage treatment, in particular to a fan unit. The application provides a fan unit which comprises a connecting pipe and components such as a fan. The parallel and inclined channel design of the connecting pipe can guide the stable flow of gas, reduce energy loss, and the slope of the inclined channel can promote the gathering of water vapor to the separator to improve the separation efficiency; the through hole is located at the end of the inclined channel close to the separator, a local negative pressure is formed when the fan is started, the gas passes through the separator is accelerated, and the water vapor is condensed and separated by using the flow rate difference, so that the first pipe body is prevented from being blocked; the axial direction of the fan is adapted to the inclined direction of the inclined channel, the air extraction direction is consistent with the airflow, so that the resistance is reduced and the vacuum establishment is accelerated.

The utility model relates to an energy-saving high-air-volume fan which comprises a volute and a wind wheel, an air outlet is formed in the volute, the wind wheel is arranged in an inner cavity of the volute in a rotating mode, and an air inlet is formed in the position, corresponding to the wind wheel, of the volute. A gap between the inner wall of the volute and the wind wheel forms an air duct, the air duct is divided into a first air duct body, a second air duct body, a third air duct body, a fourth air duct body and a fifth air duct body, the first air duct body, the second air duct body, the third air duct body, the fourth air duct body and the fifth air duct body are communicated, and the first air duct body is communicated with the air outlet; the gap between the inner wall of the volute and the wind wheel is divided into a plurality of communicated air ducts (the first air duct to the fifth air duct), the flowing path of airflow is optimized, and turbulence and loss of the airflow are reduced. Particularly, the size of each air duct is precisely designed, so that the ratio of the size of each air duct to the diameter of the wind wheel is smaller than 1, the efficiency of the wind wheel is effectively improved, and larger air volume output is realized.

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 present invention relates to a cleaning device, which includes a shell, a working device and a pneumatic component. A accommodating chamber is formed in the shell; the working device is arranged in the accommodating chamber, and the working device and at least one side inner wall of the accommodating chamber are spaced apart to form an exhaust duct; a first exhaust port is provided on the pneumatic component, and a second exhaust port connected to the exhaust duct is provided on the shell, and the first exhaust port is connected to the second exhaust port through the exhaust duct. The airflow generates a certain amount of airflow loss in the exhaust duct, which reduces the airflow flow rate and then reduces the noise of the airflow, thereby improving the comfort of use of the cleaning device. At the same time, when the airflow flows in the exhaust duct, the airflow can take away the heat of the driving device, reduce the temperature of the driving device and thus reduce the wear of the driving device, thereby ensuring the life of the driving device. The practicality and comfort of use of the cleaning device are further improved.

The stirring device comprises a stirring tank body, a rack is assembled at the top end of the stirring tank body, a motor speed reducer is assembled on the rack, a coupler is assembled at the driving end of the motor speed reducer, and a stirring shaft is assembled on the motor speed reducer through the coupler; a bearing box is assembled between the stirring tank body and the rack, a chassis is assembled on the bearing box, a sealing sleeve is assembled at the upper end of the chassis, and the stirring shaft penetrates through the sealing sleeve and the chassis and extends into the stirring tank body; a sealing top plate is assembled at the upper end in the stirring tank body, a bearing is assembled in the center of the sealing top plate, and a shaft seat is assembled in the center of the bottom end of the stirring tank body; according to the cage type filter stirring device, material sealing of stirring equipment is facilitated, the environment is better optimized, meanwhile, energy loss is reduced, the service life of the equipment is prolonged, a large amount of installation and maintenance time is also saved, efficiency is improved, and cost is saved.

The application discloses a high-efficiency complex curved volute design method, which comprises the following steps: carrying out collaborative design on a centrifugal impeller, a vaneless diffuser and a volute; selecting initial design parameters of the volute; selecting a circular cross-section design of the volute according to the principle of momentum conservation; carrying out initial design of the volute according to gas conditions at an outlet of the vaneless diffuser; establishing a flow channel fluid model of the volute from a three-dimensional model of the volute; calculating a flow field of the flow channel fluid model; coupling calculation of the flow channel fluid model of the volute and a fluid model of the centrifugal impeller from the three-dimensional model of the volute; and obtaining comprehensive aerodynamic efficiency η of the centrifugal impeller and the volute; and judging whether the comprehensive aerodynamic efficiency η meets design requirements until the design requirements are met. The design method can make the aerodynamic efficiency between the volute and the centrifugal impeller reach an optimal matching state, improve energy conversion efficiency of an aerodynamic system and reduce energy loss of the volute.