173 results about "Inlet channel" patented technology

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 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 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 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 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 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 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.

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 invention discloses a single-action high-precision pressure flow amplifier in the field of industrial flow control. The single-action high-precision pressure flow amplifier comprises a valve core, an air inlet cavity, an air outlet cavity, an adjusting cavity, an air inlet channel, an air outlet channel and an IP air channel. The air inlet channel communicates with the air inlet cavity, the air outlet cavity communicates with the air outlet channel, and the adjusting cavity communicates with the IP air channel. Adjusting air flows into the adjusting cavity from the IP air channel to push the flexible diaphragm to deform, the flexible diaphragm pushes the valve core to enable the air inlet cavity to be communicated with the air outlet cavity, and input air sequentially flows through the air inlet channel, the air inlet cavity, the air outlet cavity and the air outlet channel to become output air. A part of output air flows through the first pressure stabilizing device, a part of input air flows through the second pressure stabilizing device, and the pressure intensity of the output air is automatically stabilized at a preset value. The two pressure stabilizing devices are arranged, the pressure intensity of output air can be automatically adjusted, and the application range is wider.

The invention belongs to the technical field of engines, and particularly relates to an intelligent air inflow adjusting system suitable for an opposed-piston two-stroke hydrogen engine and a control method. The first transition mechanism is arranged at the inlet end of the air inlet channel inlet; the air inlet pipes fixedly communicate with the outlet end of the air inlet channel inlet, and the air inlet pipes are arranged in an array mode in the circumferential direction; the second transition mechanism is arranged at the communicating end of the air inlet pipe and the inlet of the air inlet channel; the flow guide mechanism is arranged between the air inlet pipe and the engine cylinder; and the section valve groups are in one-to-one correspondence with the air inlet pipes and are movably arranged at the outlet ends of the air inlet pipes. Through optimal design of structural parameters of the air channel and the flow guide plate, high-flow-speed and low-resistance stable flow in the air inlet channel is achieved; through flexible control of the air inlet turning plate, accurate and efficient control over the air inlet amount, the air flow speed and the air flow direction is achieved.

The application belongs to the field of aviation environmental control system design, and particularly relates to a bidirectional-ejection-based aircraft heat exchange system. The system comprises a ram air inlet channel, a heat exchanger and an air circulator. The ram air inlet channel comprises a ram air inlet section (1), a transition ejection section (4) and a ram air outlet section. The heat exchanger comprises an air-liquid heat exchanger (2), a first air-air heat exchanger and a second air-air heat exchanger. The air circulator comprises a first air circulator and a second air circulator. The bidirectional-ejection-based aircraft heat exchange system utilizes the principle of constant entropy ejection to limit the ram air flow entering the left and right ram air outlet channels, and integrates the cold side of the heat exchanger with the ram air inlet channel, and matches the dynamic pressure brought by the ram air with the flow resistance of the heat exchanger group, thereby effectively avoiding problems such as fan overspeed, windmill effect and surge of the air circulator.

The air inlet channel structure comprises a speed reducer, an air compressor, a combustion chamber and an exhaust nozzle which are sequentially connected, the air compressor comprises an air inlet casing, a cooling air channel is arranged on the air inlet casing, one end of the cooling air channel is communicated with the speed reducer, and the other end of the cooling air channel is communicated with the outside of the air inlet casing. A negative pressure pipe is further arranged on the speed reducer, and the free end of the negative pressure pipe is communicated with the exhaust nozzle; the air inlet casing comprises a front casing body and a rear casing body which are connected with each other, an air inlet flow channel is arranged between the front casing body and the rear casing body, a front pressurizing cover is arranged on the rear casing body, a rear pressurizing cover is arranged on the front pressurizing cover, the front pressurizing cover and the rear pressurizing cover are buckled with each other to form a pressurizing cavity, and an air compression impeller is arranged in the pressurizing cavity in a matched mode. When the air compression impeller rotates, air flow is sucked into the pressurization cavity from the air inlet flow channel and enters the combustion chamber after being pressurized by the air compression impeller. And the structure linkage is high, the assembly precision is high, the heat dissipation and air inlet efficiency is excellent, maintenance is convenient, and work is stable.

The application discloses an air inlet channel structure applied to a high-power aircraft power system, which comprises a speed reducer, a compressor, a combustion chamber and a tail nozzle which are sequentially connected, the compressor comprises an air inlet casing, a cooling air channel is arranged on the air inlet casing, one end of the cooling air channel is communicated with the speed reducer, the other end of the cooling air channel is communicated with the outside of the air inlet casing, a negative pressure pipe is further arranged on the speed reducer, and the free end of the negative pressure pipe is communicated with the tail nozzle; the air inlet casing comprises a front casing and a rear casing which are connected with each other, an air inlet flow channel is arranged between the front casing and the rear casing, a front pressure-increasing cover is arranged on the rear casing, a rear pressure-increasing cover is arranged on the front pressure-increasing cover, the front pressure-increasing cover and the rear pressure-increasing cover are buckled with each other, an internal pressure-increasing cavity is formed, a compressor impeller is arranged in the pressure-increasing cavity in cooperation, when the compressor impeller rotates, air flow is sucked into the pressure-increasing cavity from the air inlet flow channel, and enters the combustion chamber after being pressurized by the compressor impeller. The structure has the advantages of strong linkage, high assembly precision, excellent heat dissipation and air inlet efficiency, convenient maintenance and stable work.

The invention belongs to the technical field of nacelle air inlet duct resistance reduction, and relates to a nacelle air inlet duct resistance reduction structure and method.The nacelle air inlet duct resistance reduction structure comprises an inner annular flexible film section embedded in the inner wall of a nacelle air inlet duct, and the front edge and the rear edge of the inner annular flexible film section are in sealed connection with adjacent inner wall steps through bonding layers; the outer annular flexible film section is embedded in the outer wall of the nacelle air inlet channel, and the front edge and the rear edge of the outer annular flexible film section are in sealed connection with the adjacent outer wall steps through bonding layers respectively; under the action of aerodynamic load, the flow velocity gradient and the adverse pressure gradient of a near-wall area of the surface are passively adjusted through the structural flexibility and deformation response of different positions of the surface of the inner and / or outer annular flexible film section, so that the shear stress and friction resistance of airflow to the surface are reduced.

The invention belongs to the technical field of internal combustion engines, and provides a double-air-inlet-channel gas engine suitable for multiple fuels and an air inlet control method of the double-air-inlet-channel gas engine. The double-air-inlet-channel gas engine suitable for multiple fuels comprises an engine air cylinder, a piston, an air inlet channel and at least two kinds of gas inlet channel modules capable of being switched. The piston is arranged in the engine cylinder and does linear motion along the engine cylinder; the engine cylinder is provided with a cylinder cover, and the air inlet channel and the fuel gas inlet channel module are arranged on the cylinder cover. Each fuel gas inlet channel module has a cross sectional area suitable for being matched with a preset target gas fuel, and the cross sectional area is obtained through calculation based on the physical characteristics of the target gas fuel so as to ensure that the mass flow of fuel entering an air cylinder meets the requirement of the ideal air-fuel ratio under the standard working condition. The multi-fuel adaptability, the heat efficiency and the emission level of the engine are remarkably improved, meanwhile, the structure is simple, and the implementation cost is low.

The invention provides a metal middle core rod and a manufacturing method thereof, and belongs to the technical field of core rod machining. The metal middle core rod comprises a core rod body and a core rod head, the core rod head is arranged at one end of the core rod body, a stress reducing mechanism is arranged in the core rod body and comprises an air inlet channel, a first heat dissipation channel and a first channel, the air inlet channel is formed in an inner cavity of the core rod body and used for introducing high-pressure air, a spiral air return channel is further formed in the inner cavity of the core rod body, and the first heat dissipation channel is communicated with the first channel. And an exhaust nozzle is arranged on the surface of the core rod body, and the exhaust nozzle is communicated with the air return channel. According to the invention, the temperature in the temperature sensing cavity is gradually increased through the arrangement of the stress reducing mechanism, so that the bimetallic strip is deformed and bent downwards, the sliding plate and the cross are pushed to gradually move upwards, the first channel is gradually conducted by the first sealing plate, and the cooling liquid can enter the first heat dissipation channel for liquid cooling heat dissipation; the larger the cooling liquid flow in the first heat dissipation channel is, the heat dissipation effect is guaranteed, and the thermal stress on the surface of the core rod body is reduced.

This invention discloses a reverse design method for the optimal coupling shock wave system of internal and external compression in a two-dimensional mixed-pressure inlet, comprising the following steps: S1, assigning initial values ​​to known design parameters; S2, estimating the total turning angle of external compression and obtaining the corresponding total turning angle of internal compression; S3, using the design parameters obtained in steps S1 and S2, employing the Oswatitsch equal-intensity shock wave theory and the prediction-correction-iteration method to design the optimal shock wave system for external compression, obtaining the external compression outlet flow field parameters; S4, using the design parameters obtained in steps S1-S3, employing the Oswatitsch equal-intensity shock wave theory and the prediction-correction-iteration method to design the optimal shock wave system for internal compression, obtaining the internal compression outlet flow field parameters; S5, determining whether the internal compression outlet Mach number obtained in step S4 meets the standard. If it does, the design ends; otherwise, steps S2-S4 are repeated until the internal compression outlet Mach number meets the standard. This invention achieves automatic optimization of the optimal coupling shock wave system of internal and external compression in reverse design, with a simple process and clear physical meaning.

The utility model relates to a pneumatic hammer which comprises a body comprising an air inlet channel; the cylinder is connected with the body and comprises a first chamber, a second chamber and a spacing part which is radially spaced between the first chamber and the second chamber, the spacing part comprises a through hole, and the through hole is communicated with the first chamber and the second chamber; the working piece is arranged at one end of the cylinder; the valve group is accommodated in the second cavity and comprises a seat part and a valve piece which is movably arranged on the seat part, the valve piece comprises a base part and a side bulge which is transversely connected to the base part, and the valve piece can move to seal or not seal the through hole; and the piston is movably accommodated in the first cavity.

The utility model provides wide -bodied aircraft air inlet channel overhauls work platform, including platform base, the head one end of platform base is fixed with the parallel arrangement's outer extension pole, the top of platform base is fixed with the stand, is installed with the inclined arrangement's cat ladder structure between stand and platform base, the inner side wall of stand is slidably installed with the lifting column through a plurality of guide wheels, is provided with the ladder pole between lifting column, the top of lifting column is fixed with the top platform, is fixed with the top frame between top platform and lifting column, is installed with the lifting adjusting device between top platform and platform base. This work platform can be used for aircraft air inlet channel overhauls, can conveniently integral removal to the position of need overhauls, and conveniently carries out the platform height's adjustment according to the overhauls height, to enhance the adaptability of use, has effectively improved the overhauls efficiency, has reduced the overhauls operation intensity.

The utility model discloses a guide plate detection jig for an automobile air inlet channel, relates to the technical field of guide plate detection jigs, and solves the problems that the shape of a guide plate is not planar, the two ends of the guide plate and the central part are not positioned on the same axis, and the guide plate cannot be damaged after the two ends of the guide plate are oppositely clamped and extruded by using clamping blocks on the two sides. The device solves the problem that the use efficiency of the device is reduced due to inaccurate detection data caused by the fact that the position of a clamped flow guide plate can be temporarily fixed after the flow guide plate is clamped, but under the influence of wind power, the position of the clamped flow guide plate has a position risk, and the device comprises a base and a moving block, and moving grooves are symmetrically formed in the top face of the base; moving blocks oppositely move until the side walls of the moving blocks are attached to the side wall of a flow guide plate, meanwhile, a first screw moves relative to the position of a pressing plate until the pressing plate is tightly attached to the side wall of the flow guide plate, and a third fixing plate is matched, so that the position of the placed flow guide plate can be stable.

The invention provides a semiconductor process chamber which comprises a chamber body and a gas inlet component, the chamber body is provided with a first protective gas channel, the gas inlet component is provided with a first gas inlet channel and a second gas inlet channel, the first gas inlet channel is communicated with the interior of the chamber body and used for conveying reaction gas into the chamber body, and the second gas inlet channel is communicated with the interior of the chamber body. The second gas inlet channel communicates with the interior of the cavity body through a first protection gas channel and is used for conveying first protection gas into the cavity body through the first protection gas channel, and the first protection gas channel is used for enabling the first protection gas conveyed into the cavity body to be distributed between the inner peripheral wall of the cavity body and reaction gas in the cavity body. According to the semiconductor process chamber provided by the invention, on one hand, the maintenance period can be prolonged, the normal operation time can be prolonged, the maintenance cost can be reduced, and on the other hand, the possibility of abnormal particle conditions can be reduced, so that on one hand, the production cost can be reduced, and on the other hand, the stability of semiconductor process results can be improved, and the process yield can be improved.

The utility model provides an oxygenation pump air drum and supercharging equipment, including base and elastic air bat, the base is provided with first connecting part, the elastic air bat is provided with second connecting part, the first connecting part is internally provided with a groove body 1, the base and the elastic air bat form a closed space, the groove body 1 is internally provided with an air inlet hole and an air outlet hole, and the air inlet hole and the air outlet hole are communicated with each other. An air inlet hole and an air outlet hole are formed in the two sides of the base, an air inlet channel and an air outlet channel are further formed in the base, a first elastic piece covering the air inlet hole is arranged in the first groove body, and a second elastic piece covering the air outlet hole is arranged in the air outlet channel. The device is convenient to disassemble and assemble, reasonable in component connection, simple in operation when the components are maintained or replaced, firm, tight and stable in elastic sealing clamping connection of the annular groove and the convex ring, excellent in sealing performance, simple in overall structure, capable of preventing gas leakage, capable of reducing the failure rate and capable of providing stable and efficient oxygenation support, and the special connecting structure and the elastic sealing material clamping block are applied.

The invention discloses an aero-engine air inlet passage secondary flow prediction method based on a neural network. The method comprises the steps that an air inlet passage physical model containing suction holes is established, and grids are divided; setting boundary conditions required for solving; performing numerical simulation to obtain flow field data under different working conditions, calculating mass flow under a suction hole blocking condition and a corresponding surface dimensionless sound velocity flow coefficient, and constructing a training data set; training and constructing a traffic prediction model based on a neural network; re-establishing a simplified air inlet channel physical model without suction holes and dividing grids; and calling a flow prediction model to predict a dimensionless sound velocity flow coefficient of the simplified air inlet physical model, and reversely calculating actual suction mass flow, and applying the actual suction mass flow as a boundary condition to a suction hole area corresponding to the simplified air inlet physical model to realize equivalent numerical simulation of the suction effect. According to the method, calculation efficiency and prediction precision are both considered, and integration can be carried out in a CFD solver to support air inlet parameterization design and rapid performance evaluation.

The application discloses an ice-preventing structure of a particle separator and an aero-engine. The particle separator comprises a central body coaxially arranged with an air intake casing, an outer shell and a separation lip. An air inlet channel is formed between the central body and the outer shell. The separation lip is arranged at the tail end of the particle separator and in the air intake casing. The separation lip comprises a first outer wall and a first inner wall. The central body comprises a second inner wall and a second outer wall. A main flow channel front end is formed between the first inner wall and the outer wall of the central body, and the main flow channel front end is communicated with the air inlet channel and the air intake casing. A cleaning flow channel is formed between the first outer wall and the inner wall of the outer shell. The separation lip is used for separating the airflow of the air inlet channel and then guiding the airflow to the cleaning flow channel and the main flow channel respectively. The ice-preventing structure comprises an air bleed structure arranged in the air intake casing and used for guiding the ice-preventing gas to the separation lip. The air bleed structure is also used for guiding the ice-preventing gas into the interlayer channel between the second inner wall and the second outer wall.

The utility model discloses a special crane for an airport engine air inlet channel, which comprises a base mechanism, a main beam, a pulley yoke, a support, a cantilever, a lifting hook, a lifting cylinder, a winch system, a hoisting steel wire rope and a lifting steel wire rope, one end of the main beam is connected with the base mechanism, the pulley yoke is correspondingly arranged at the other end of the main beam, and one end of the support and one end of the cantilever are correspondingly connected with the other end of the main beam. The lifting cylinder and the winch system are correspondingly arranged on the base mechanism; two ends of a lifting steel wire rope are respectively connected with the lifting cylinder and the other end of the main beam; one end of the hoisting steel wire rope is correspondingly connected with the winch system, and the other end correspondingly bypasses the pulley to be connected with the cantilever; and the lifting hook is correspondingly arranged on the hoisting steel wire rope. The electric vehicle is simple in structure and convenient to operate, can realize a manual function or an electric function, can adapt to different types of airports, and meets the use requirements of the airports.