355 results about "Inlet channel" patented technology

According to the electronic cigarette sensor with the partition wall structure, a partition wall, a step and a Z-shaped air inlet channel are formed in an injection molding cavity of a lead frame, the high step is provided with an air inlet channel penetrating through the high step and the bottom wall of the lead frame, the air inlet channel is in an inverted Z shape, the high step is further provided with a micro-electro-mechanical sensor, and the micro-electro-mechanical sensor is arranged on the bottom wall of the lead frame. A low step is arranged at the position, away from the high step, in the cavity, and protective nets are arranged on the upper cover and the lower cover. The lead frame is provided with a circular cavity, the height of the bottom of the circular cavity is slightly higher than that of the star-shaped bonding pad, the circular cavity is in a concave semi-wrapping state, and good sealing performance and good mounting welding performance during mounting of the formed electronic cigarette sensor are facilitated. A partition wall is further arranged in the cavity, the ASIC chip and the micro-electro-mechanical sensor are isolated through the partition wall, the micro-electro-mechanical sensor is protected from being polluted by manufacturing procedures, tobacco tar and the like, and a sealed oil-proof air channel is provided for the oil-proof cotton.

The invention provides a heat preservation box capable of rapidly replacing a cold source. The heat preservation box comprises a box body and cold storage plates; the box body is provided with a box door, a cold storage area, a control area and a cold source area are arranged in the box body, the cold storage area is separated from the control area and the cold source area through a middle partition board, and the control area and the cold source area are separated through a side partition board; a backflow partition board is arranged in the cold source area, the cold source area is divided into a cold source cavity and a backflow cavity through the backflow partition plate, the cold source cavity communicates with the lower portion of the backflow cavity, a plurality layers of cold sourceframes used for containing the cold storage plates are arranged in the cold source cavity, and the cold source cavity communicates with the cold storage area through an air inlet channel; an exhaustfan is arranged on the air inlet channel, the cold storage area communicates with the backflow cavity through a backflow channel, and an air blower is arranged on the backflow channel; a control module is arranged in the control area, a first temperature sensor is arranged in the cold storage area, the exhaust fan, the air blower, and the first temperature sensor are electrically connected with the control module; and box body, the middle partition plate and the side partition plate are all made of vacuum composite plates. According to the heat preservation box, the replacement efficiency of the cold source is improved.

The invention discloses a single-action pressure reduction diaphragm type pressure flow amplifier in the field of industrial flow control. The single-action pressure reduction diaphragm type pressure flow amplifier comprises a machine body, a valve core, a flexible diaphragm, an exhaust assembly, a large pressure reduction device and a small pressure reduction device. An adjusting cavity, an air inlet cavity, an air outlet cavity, an air inlet channel and an air outlet channel are formed in the machine body, the air inlet channel is communicated with the air inlet cavity, the air outlet cavity is communicated with the air outlet channel, the valve core is arranged between the air inlet cavity and the air outlet cavity, the valve core is pushed through the flexible diaphragm and the exhaust assembly, and the compressed air flow and pressure intensity between the air inlet cavity and the air outlet cavity can be adjusted; when the pressure intensity of the adjusted air is relatively low, the small pressure reducing device is used for reducing pressure; and when the pressure intensity is high, the large pressure reducing device is used for reducing pressure. The diaphragm structure design is adopted, the flow and the pressure intensity of compressed air are adjusted through reciprocating motion of the flexible diaphragm, the pressure intensity of the adjusted air is reduced through the two pressure reducing devices, and the diaphragm structure can be better suitable for application scenes where the pressure intensity of the adjusted air is high.

The utility model discloses a high-speed large-maneuvering target drone, which relates to the field of unmanned aerial vehicles and comprises a drone body, wings, a horizontal tail, a vertical tail and an air inlet channel. The fuselage can reduce resistance to a great extent to realize high-speed flight; the wings adopt sweepback upper single wings to reduce the resistance during high-speed flight, the problem of overlarge transverse stability caused by sweepback and high placement of the wings can be avoided through the downward reverse design, and meanwhile, the wings can be integrally disassembled and assembled and have better operability and convenience; the control efficiency of a full-motion horizontal tail is high, and the heading stability under a large-angle-of-attack attitude can be improved through the design of the inverted-V-shaped tail; the vertical fin without the control surface can improve the course stability and ensure the matching property of the transverse course stability, and is light in structural weight and small in flight resistance; the bearing separation channel type air inlet channel can avoid landing damage of the air inlet channel in the parachute landing recovery process, and meanwhile the requirements for high total pressure recovery, low air inlet distortion, radar stealth and the like are met.

The invention discloses a section shape control method applied to a three-dimensional inward-turning adjustable air inlet channel, and belongs to the field of air inlet channel molded surface pneumatic design, and the method comprises the following steps: step 1, optimization design of an inward-turning reference flow field; based on a given incoming flow design working condition, a preliminarily optimized inward rotation reference flow field is obtained; 2, optimization design of the profile of the inward-rotation adjustable air inlet channel is carried out; an inlet capture molded line and an adjustable section control constraint of the air inlet are given, and the inward turning air inlet meeting the requirement is obtained through streamline tracking in the inward turning reference flow field in the first step by combining an optimization tool and utilizing an optimization algorithm; 3, profile adjustment design is conducted, specifically, profile adjustment design is conducted at the position of a set rotating shaft straight line on the basis of the inward rotating air inlet channel generated in the step 2; according to the scheme, the inward rotation air inlet channel generated directly through streamline tracking has the characteristic that the section molded line is approximately a straight line at the specified section, and the problem that in the prior art, an original streamline tracking molded surface needs to be changed to be matched with adjustable design is solved.

The invention relates to the technical field of auxiliary power systems, in particular to a manufacturing method of an air supply device of an auxiliary power system. The method comprises the steps that a high-pressure air pressure distribution area under the working state of an auxiliary power system air supply device is obtained; determining a positioning surface and a sealing surface of the air supply device of the auxiliary power system according to the distribution area; the assembly tolerance of the auxiliary power system air supply device is determined according to the positioning face and the sealing face; an air inlet channel shell, an air inlet air pocket, an air inlet channel outer ring, an air inlet volute, a labyrinth ring, a locking unit and a rotor are machined according to the assembly tolerance; and an auxiliary power system air supply device is assembled, so that the air inlet channel shell, the air inlet air pocket, the air inlet channel outer ring and the air inlet volute sequentially abut against one another in the axial direction, the labyrinth ring is pressed between the outer side ring face of the outer sealing barrel and the inner side ring face of the volute positioning barrel, and a stepped pressure relief cavity is formed between every two adjacent pressure relief ring gears. Therefore, the problem that the air inlet end shell of the auxiliary power system is very difficult to position and seal well is solved.

The invention belongs to the technical field of hypersonic flight vehicle control, and particularly relates to a hypersonic flight vehicle protection control method considering non-starting of an air inlet channel. The method specifically comprises the steps of establishing a quasi-one-dimensional nominal mechanism model to describe flow field changes of an isolation section and a combustion chamber; adopting a physical information neural network to construct a reduced-order model as a real-time agent of the quasi-one-dimensional model; designing a dual extended Kalman filtering algorithm to realize joint online estimation of model parameters and blind area states, and introducing shock wave position pseudo measurement to form multi-loop feedback; a dual-channel fusion early warning system of a model channel and an intelligent sensor channel is constructed, and robust early warning is realized through adaptive weight; and designing a continuous adaptive model prediction controller, and dynamically adjusting a control strategy according to risk indexes and parameter uncertainty to realize active protection control.

The invention discloses a rotor type gas energy engine and a working method thereof, and the rotor type gas energy engine comprises a rotor shell which is internally provided with a cylindrical rotor chamber; the rotor is arranged in the rotor chamber and comprises a rotor shaft and at least one rotor wing arranged on the rotor shaft, and the rotor chamber is divided into rotor cavities with the same number as the rotor wings by the rotor; the airflow inlet and outlet channel comprises at least one air inlet channel and at least one air outlet channel which are arranged on the rotor shell and are equal in number; the compressed air source mechanism is connected with the air inlet channel; and the electric control system is used for controlling start and stop of the air inlet valve and the exhaust valve and the air flow provided by the compressed air source mechanism so as to be matched with rotation of the rotor to complete a working cycle through the three processes of air inlet, acting and exhaust. The rotor type gas energy engine is small in vibration, low in noise, selectable in low speed, medium speed and high speed, fast in stepless speed regulation response, and capable of effectively improving work efficiency, meeting the requirements of low rotating speed, high torque and other different rotating speeds and torques, and achieving stable operation of the engine.

The present application relates to the technical field of household appliances, and provides a gas water heater, which comprises a bottom shell, the bottom shell being provided with an opening; a burner, the burner being installed on the bottom shell; and a cover plate assembly, the cover plate assembly being installed on the bottom shell and covering the opening, the cover plate assembly comprising a first cover plate and a second cover plate, the second cover plate being located between the burner and the first cover plate, the cover plate assembly being provided with an air inlet channel between the first cover plate and the second cover plate, the first cover plate being provided with a first air inlet opening communicating with the air inlet channel, and the second cover plate being provided with a second air inlet opening at a position away from the first air inlet opening, the second air inlet opening communicating the air inlet channel with an air inlet of the burner. The gas water heater provided by the present application is provided with a multi-layer cover plate structure, each layer of the cover plate can weaken the internal noise, and the cavity between the cover plates forms a long air inlet channel, which can greatly increase the path length of the noise along the air inlet channel to propagate outward, effectively improve the transmission loss of the noise to propagate outward, and greatly reduce the flow channel resistance.

The invention provides a concentric circle rotor type internal combustion engine and a design method thereof. One or more air cylinders are arranged on the peripheral side of the rotor shell, a main oil sprayer and a spark plug are arranged in each air cylinder, and a transition air channel is arranged between each air cylinder and the rotor chamber; the rotor is arranged in the rotor chamber; the air inlet channel is arranged on the air cylinder and is used for introducing compressed air into the air cylinder; the fuel cylinder is arranged on the rotor shell and communicates with the transition air channel, and an auxiliary fuel injector is arranged in the fuel cylinder; the transition valve is arranged on the side, close to the air cylinder, of the communicating portion of the transition air channel and the rotor shell. When the transition valve is closed, the combustion chamber is divided into an ignition cylinder and a main combustion space, fuel is constantly supplied in the ignition cylinder according to theoretical mixed gas, fuel is supplied in the main combustion space according to lean mixed gas, and the fuel quantity changes along with working conditions. Various fuels can be used, ignition is stable, the multi-rotor type can achieve torque superposition, the anti-overturning performance is improved, and high power and low oil consumption are achieved under the condition that the height is not increased and the rotating speed of an original single rotor is not changed.

The invention provides an air-breathing aircraft for long-term flight in an upper atmosphere, and relates to the technical field of aircrafts in the upper atmosphere, the air-breathing aircraft comprises an aircraft body, the aircraft body is provided with an air-breathing electric propulsion system, the outer contour of the aircraft body is cylindrical, and an air inlet channel is arranged in the center of the aircraft body; the air inlet channel comprises a gradually-shrinking conical inlet pipeline, an inwards-concave gradually-shrinking compression pipeline, a cylindrical ionization acceleration pipeline and a gradually-expanding conical outlet pipeline which are sequentially arranged from front to back. The solar cell wings are arranged on the outer side of the aircraft body, the solar cell wings are forward-swept trapezoidal wings, and the solar cell wings can supply power to the air suction type electric propulsion system; the problem that in the prior art, technical defects exist in the aerodynamic configuration design of how to achieve thrust and resistance balance of an aircraft flying for a long time in the upper atmosphere is solved.

The invention discloses a gas compressor test device and method, and belongs to the field of gas compressor tests.The gas compressor test device comprises a driver, and a driving shaft of the driver is used for being connected with a main shaft of a gas compressor; the unloading assembly comprises a balance drum, a high-pressure gas supply unit, an exhaust unit and an adjusting valve, the balance drum is used for being connected with a main shaft of the gas compressor and used for being connected with an impeller on the main shaft of the gas compressor, the high-pressure gas supply unit is used for being communicated between the balance drum and the impeller, and the exhaust unit is used for being communicated with the side, away from the impeller, of the balance drum; an inlet temperature sensor, an inlet pressure sensor and a flow sensor are arranged in the double-twisted-wire air inlet channel; an outlet temperature sensor and an outlet pressure sensor are arranged in the annular outlet throttler; and a controller. The technical effects of the invention lie in that the device not only facilitates the independent test of the related gas compressor, but also facilitates the small axial force of the impeller of the gas compressor borne by the thrust bearing.

The air inlet functional lip component of the unmanned aerial vehicle comprises a functional lip, the outer end of a functional lip body is provided with an outer side connecting part, and the inner end of the functional lip body is provided with an inner side connecting part; the outer side connecting part comprises an elastic shifting piece fixed to the outer end of the functional lip body, the free end of the elastic shifting piece is provided with a locking block, and the locking block is matched with a locking groove formed in the outer wall of the air inlet channel; the inner side connecting part comprises a positioning pin, and the positioning pin is matched with a positioning sleeve on the inner wall of the air inlet channel; the locking block on the elastic shifting piece is pressed to the inner side of the outer wall of the air inlet channel, moves forwards and then is inserted into the locking groove to be locked, so that the positioning pin is inserted into the positioning sleeve while the functional lip body and the outer wall of the air inlet channel are fixed, and the functional lip body and the inner wall of the air inlet channel are fixed. The component can realize quick disassembly and assembly, connection stability and sealing performance of the lip, and the maintenance efficiency and reliability of the unmanned aerial vehicle are improved. The invention further discloses an unmanned aerial vehicle which has the same advantages.

The application provides a self-cooling air-breathing radio frequency plasma electric thruster, which comprises an air inlet channel, an ionization chamber and a nozzle, the air inlet channel is divided into a main air inlet channel and a secondary air inlet channel, the main air inlet channel is communicated with the ionization chamber, a cooling flow channel is arranged on the periphery of the ionization chamber, the secondary air inlet channel is communicated with a gas guide channel, the gas guide channel is communicated with the cooling flow channel through a cooling flow channel inlet, and the cooling flow channel is communicated with the ionization chamber through a cooling flow channel outlet; the gas taken by the main air inlet channel directly enters the ionization chamber to be ionized, the gas taken by the secondary air inlet channel is guided to the cooling flow channel inlet through the gas guide channel, enters the cooling flow channel through the cooling flow channel inlet, cools the ionization chamber, and then enters the ionization chamber through the cooling flow channel outlet to be ionized, and the two gas flows entering the ionization chamber are accelerated through the nozzle after being ionized, so that the thruster generates thrust. The cooling design provided by the application has the advantages of simple structure and high energy utilization rate.

This invention provides an active flow control method and system based on intelligent algorithms. The method includes: determining the number of inlet parameter sets for a typical flight state point, constrained by simulation economy and sampling efficiency; performing numerical simulations according to the number of inlet parameter sets to obtain dataset 1, with inlet parameters as independent variables and flow field characteristics as dependent variables; obtaining dataset 2, with flight state as independent variables and flow field characteristics as dependent variables, through numerical simulation for a certain set of inlet parameters; constructing a proxy model of inlet flow field characteristics for a typical flight state point using deep learning based on dataset 1; constructing a proxy model of inlet flow field characteristics for a wide-speed-domain flight state based on the proxy model of inlet flow field characteristics for the flight state point, using a transfer learning algorithm and dataset 2; constructing an environment-agent interaction model based on a deep reinforcement learning algorithm, using the proxy model of inlet flow field characteristics for a wide-speed-domain flight state as the environment model for deep reinforcement learning; setting optimization termination conditions based on the environment-agent interaction model, and obtaining a control sequence with continuously optimal inlet performance under different flight states through deep reinforcement learning. This invention can stably adapt to flight scenarios with a wide speed range and a large airspace, and achieve real-time optimal control of the air intake flow field under a wide speed range, solving the problem of poor generalization ability of traditional methods under different operating conditions.

The utility model discloses a vibration atomizer with an adjustable air passage, which comprises a shell, a battery support fixedly connected in the shell, a control assembly arranged on the battery support and a vibration motor connected with the control assembly, an air adjusting mounting cavity communicated with the air inlet channel is formed in one side of the battery bracket; the air adjusting assembly is connected to the air adjusting mounting cavity in a clamped mode, a first air inlet hole matched with the air inlet channel in position is formed in one side of the shell, and the air adjusting assembly comprises an air adjusting piece and an air adjusting fixing piece; a first air channel is arranged on the air adjusting fixing piece and communicated with the first air inlet hole and the air inlet channel. The cigarette cartridge is detachably connected with the battery support, and the cigarette cartridge is provided with an atomizing core assembly. According to the air inlet structure, the air inlet amount can be adjusted through the air adjusting assembly, meanwhile, small-air-amount operation can be conducted when the air adjusting assembly is closed, the air inlet structure is optimized, and cost is reduced.

This invention relates to an ultrasonic-assisted laser cleaning device for the inner wall of an air intake using negative pressure adsorption, belonging to the field of aircraft maintenance and surface treatment. It includes: a housing with an opening on one side of its working surface, and a flexible sealing member circumferentially disposed around the opening; a laser cleaning head disposed inside the housing; an ultrasonic amplitude transformer arranged in a ring around the laser cleaning area; an ultrasonic transducer connected to the ultrasonic amplitude transformer; a negative pressure suction unit connected to the housing for creating a negative pressure airflow field within the housing; and a high-pressure gas injection unit disposed opposite to the negative pressure suction unit for assisting in the formation of the airflow field. The ultrasonic amplitude transformer has a ring-shaped structure and is arranged in a ring array on the inner wall of the housing, with the ultrasonic transducer mounted thereon, converting electrical signals into ultrasonic vibrations via piezoelectric ceramics. This invention, by combining ultrasonic technology with laser cleaning, can adapt to cleaning areas with different radii of curvature, thereby achieving all-position cleaning.

The present invention discloses a liquid-gas jointly controlled sequential automatic bottle-changing infusion set, which includes a first flow channel, a rear flow channel, and a liquid-gas joint controller arranged between the first flow channel and the rear flow channel. The first flow channel is connected to a first medicine bottle and an intravenous injection needle. The upper end of the rear flow channel is connected to a medicine bottle at the rear, and the lower end is connected to the first flow channel below the liquid-gas joint controller after passing through the liquid-gas joint controller. The liquid-gas joint controller is provided with an air inlet channel, and the air inlet channel bifurcates in the liquid-gas joint controller to form a prior airway and a rear airway leading to the outside of the liquid-gas joint controller. The prior airway is connected to a prior medicine bottle, and the rear airway is connected to a medicine bottle at the rear. When the liquid-gas joint controller opens the rear flow channel, the prior airway is synchronously closed, and all prior medicine bottles stop admitting air, so that the remaining liquid medicine in all prior medicine bottles is forced to stop flowing downward. Its advantages are as follows: it can realize simultaneous hanging of multiple medicine bottles and sequential automatic bottle-changing drip infusion; it can avoid excessive mixing of the liquid medicine in the rear medicine bottle with the residual liquid medicine in the prior medicine bottle during the drip infusion.

The utility model discloses a closing-in annular type air inlet channel forming die which comprises a bottom plate, a die body and a connecting plate, the die body is divided into a lower layer structure, a middle layer structure and an upper layer structure, and the lower layer structure, the middle layer structure and the upper layer structure are fixedly connected; the lower layer structure is formed by splicing six lower die bodies, and the lower die bodies are fixed on the bottom plate; the middle-layer structure comprises a middle body and a plurality of middle mold bodies, and the middle mold bodies are wound into a circle and fixed to the periphery of the middle body; the upper layer structure is composed of three upper die bodies, inserts are arranged on the two sides of the upper layer structure, and the inserts and the upper die bodies are fixedly connected with the connecting plate. According to the utility model, the mold main body is arranged into a structure of splicing a plurality of mold bodies, so that the normal use of the mold during material paving can be ensured, each mold body can be detached and independently taken out for demolding in the demolding stage, and the mold bodies are small in size and can be easily taken out from the small-caliber ends of the air passages, thereby completing rapid demolding and ensuring the demolding quality.

The invention relates to the technical field of aircraft structure design, in particular to an air inlet channel mounting structure and a design method. Comprising an air inlet channel and a peripheral structure, the air inlet channel is formed by connecting an air inlet channel lip and an air inlet channel inner channel, a lip turnup is designed on the air inlet channel lip in the main direction of airflow, and an air inlet channel clamping groove is formed in the lip turnup. The peripheral structure is formed by connecting a peripheral structure channel and a peripheral structure flange, a peripheral structure buckle is arranged at the tail end of the peripheral structure flange, the air inlet channel inner channel and the peripheral structure channel are combined in a sleeved mode, and the peripheral structure buckle is clamped in the air inlet channel clamping groove to achieve butt joint installation. The number of assembly connecting parts is greatly reduced, and the number of assembly part connecting points is reduced. And too large operation space is not needed.

The utility model provides an atomization bomb and an electronic atomization device. The atomization bomb comprises a pot body, an upper cover and an adjusting mechanism. The pot body is provided with an opening end and a containing cavity which is communicated with the opening end and used for containing an atomizing medium; the upper cover covers the open end and is provided with a first air inlet channel, a second air inlet channel and an air outlet channel which are mutually spaced and are respectively communicated with the outside and the accommodating cavity; the adjusting structure is slidably connected to the upper cover and used for adjusting the communication state of at least one of the first air inlet channel and the second air inlet channel and the outside. When the first air inlet channel is communicated with the outside, external air flows to the other end from the opening end of the accommodating cavity along the middle part through the first air inlet channel; when the second air inlet channel is communicated with the outside, external air flows to the other end from the opening end of the accommodating cavity along the inner circumferential side through the second air inlet channel; and gas in the accommodating cavity is discharged outside through the gas outlet channel. The atomization bomb can work in multiple air inlet modes, and a user can conveniently and flexibly select and use the atomization bomb.

The invention discloses a distributed discharge-bypass pressurization coupled wide-area ramjet engine and a working method thereof, and belongs to the field of wide-area ramjet engines, the distributed discharge-bypass pressurization coupled wide-area ramjet engine comprises a bypass pressurization flow channel and a dual-mode ramjet combustion chamber flow channel, and the dual-mode ramjet combustion chamber flow channel comprises a fixed geometric air inlet channel; the bypass supercharging flow channel comprises a distributed drainage hole communicating with the compression face side of the fixed geometric air inlet channel, and a drainage cavity, a first Laval nozzle, a bypass supercharging chamber, a second Laval nozzle and a bypass exhaust nozzle which communicate with the distributed drainage hole in sequence. According to the distributed discharge-bypass supercharging coupled wide-area ramjet engine and the working method thereof, by arranging the bypass supercharging flow channel, the problem of structure and control complexity and difficulty caused by adjustable parts in integrated adjustment of the engine is solved, meanwhile, the starting capacity and thrust gain under the low Mach number are increased, and the starting efficiency is improved. And the engine has the wide-speed-range working capacity.

The invention discloses an inverse design method for a dual-mode internal contraction combined air inlet channel, and relates to a hypersonic air inlet channel of an aircraft. Comprising the following steps: designing a bimodal basic flow field based on a high / low-speed modal cruise Mach number as a design point; the inlet shape design of the air inlet channel is combined with the flight-launch integrated matching requirement; designing an air inlet compression molded surface by a streamline tracking technology; designing the optimal position of the rotating shaft of the splitter plate based on the maximum splitting control efficiency; designing a flow distribution plate rotation angle according to a flow distribution requirement in a flight envelope; the expansion effect caused by rotation of a turbine channel splitter plate and the compression effect generated by area shrinkage in a shared flow channel are comprehensively considered; and a turbine channel and a stamping channel are designed to be separated from each other. The dual-mode conversion adaptability of the internal contraction combined air inlet channel is remarkably improved, and the flow distribution requirements of all channels under different flight working conditions are met.

The application discloses a turbofan engine inlet temperature simulation temperature field online monitoring method, which comprises the following steps: expanding the temperature field section of the engine inlet channel according to the polar coordinates, dividing the temperature field section into m parts along the circumferential direction clockwise and dividing the temperature field section into n equal parts along the radial direction, so as to obtain an m*n grid area, each grid area represents the temperature value of a unit body, and the temperature value of each unit body is obtained; the radial average temperature of each angular position and the surface average temperature of the temperature field section are obtained according to the temperature value of each unit body; the circumferential range of the high-temperature zone is determined according to the distribution of the area-weighted radial average value measured at different radii on the aerodynamic interface along the circumferential direction, the average value of the airflow temperature in the high-temperature zone is calculated, the temperature field unevenness and the temperature distortion intensity are calculated according to the average value of the airflow temperature in the high-temperature zone, and at least one of the circumferential range of the high-temperature zone, the average value of the airflow temperature in the high-temperature zone, the temperature field unevenness and the temperature distortion intensity is displayed in real time.

The utility model discloses a profiling air inlet prefilter, which belongs to the technical field of air inlet pipelines of engines and comprises a shell component consisting of a first shell and a second shell, and the first shell and the second shell are welded to form a closed cavity. An air inlet channel inlet is formed in one end of the cavity, and an air outlet and a dust discharging unit are arranged at the other end of the cavity; and a filtering and separating unit is arranged in the cavity. According to the prefilter with the profiling air inlet channel, through the design of the dust discharging unit, the filtering and separating unit and the profiling flow channel, the particle separating efficiency is improved, the air inlet resistance is reduced, the maintenance frequency of the air filter is reduced, and the energy consumption and the cost are reduced.

The utility model provides a double-runner volute, and belongs to the technical field of turbocharger casting processes. A double-flow-channel volute comprises a body and a cross gate, the body is composed of four volutes fixed to the cross gate, a riser is fixedly installed on an air inlet flange on one side of each volute and fixedly connected with the cross gate, a sprue cup is arranged in the middle of the cross gate, and a first air inlet channel and a second air inlet channel are formed in each volute. A middle partition plate is arranged between the first air inlet channel and the second air inlet channel, the first air inlet channel and the second air inlet channel form a vortex chamber in the volute, and an exothermic riser is fixedly installed on the surface of the volute and fixedly connected with the cross gate. By arranging the exothermic risers and additionally arranging the riser sleeves, feeding can be increased, the problems of center spacer suction nest and shrinkage porosity are solved, and meanwhile the product yield is increased; a round hole is formed in the volute, and by adjusting the matching structure of the cladding core and the core head of the runner core, the situation that a coating of the core head of the runner core falls into a cavity in the core assembling process, and an R arc slurry hole is caused can be avoided. And one chilling block is arranged in the volute, so that the surface of the sand core can be prevented from loosening.

The utility model discloses an intake and exhaust adjustable volute, which comprises a volute body provided with a first air inlet and a first air inlet passage, the first air inlet is communicated with the first air inlet passage, and is characterized in that the volute body is also provided with a second air inlet and a second air inlet passage, the second air inlet is communicated with the second air inlet passage, and the second air inlet passage is communicated with the second air inlet passage. The control unit is used for controlling waste gas to flow into the second gas inlet channel, and the control unit is matched with the second gas inlet and / or the second gas inlet channel. The turbine lag phenomenon of the engine in the starting stage is effectively relieved.

The application discloses an air inlet channel landing buffer device for aircraft parachute recovery, and relates to the technical field of aircraft recovery. The air inlet channel lip assembly is at least partially made of a first energy-absorbing material, is detachably connected to the belly of the fuselage of the aircraft, and is in communication with the main body of the air inlet channel located inside the fuselage. The lower edge of the air inlet channel lip assembly is lower than the lower skin of the belly of the fuselage, and is configured to be in contact with the ground before other parts of the fuselage when the aircraft lands at a predetermined landing attitude angle, and to absorb the first impact energy by deforming or being destroyed. The energy-absorbing support assembly is at least partially made of a second energy-absorbing material, and is detachably connected between the air inlet channel lip assembly and the mounting base inside the fuselage. While realizing the basic function of the air inlet channel, the application effectively overcomes the problems of slow inflation, easy breakage, high cost and poor controllability of the traditional airbag buffer mode, and embodies significant functional integration and technical economy.

This invention relates to a wide-range, high-precision flow blocking cone, comprising an upstream connector, a flow cylinder, a low-pressure connector, and a blocking cone. The upstream connector is located at one end of the flow cylinder, and the blocking cone is coaxially located at the other end of the flow cylinder via the low-pressure connector. The flow area between the flow cylinder and the blocking cone exhibits a pattern of initial contraction followed by expansion. The side of the blocking cone away from the flow cylinder is connected to a motor via a motor output shaft. The blocking cone and the motor are situated in a low-pressure environment. The invention also provides a method for using the aforementioned wide-range, high-precision flow blocking cone. This method divides flow measurement into two stages: a calibration stage and a usage stage. The calibration stage is conducted in a system with uniform incoming flow and a known flow rate. The usage stage involves directly connecting the device to be measured flow. This method can adjust the back pressure at the inlet outlet and suppress errors caused by upstream flow field distortion, thereby improving the accuracy of flow measurement.

The present invention discloses an S-shaped flow channel active flow control variable parameter testing system, comprising a curved section and straight sections connected at both ends of the curved section, wherein a replaceable plug-in plate is detachably installed on the curved section, and a mounting slot is provided on the replaceable plug-in plate at a position to be tested; a replaceable fluid oscillator is installed in the mounting slot, and the replaceable fluid oscillator is detachably connected to the mounting slot; the jet outlet of the replaceable fluid oscillator faces the flow channel inside the curved section; the system can realize the replacement of the position to be tested by replacing the replaceable plug-in plate and the mounting slots at different positions on the replaceable plug-in plate, and simultaneously realize the change of factors such as the jet angle, the number of actuators, and the spacing by replacing the replaceable fluid oscillator, so that the system can quickly and conveniently adjust various influencing parameters affecting the active flow control inside the S-shaped air inlet channel.