1052 results about "Turbofan" patented technology

The invention discloses a turbofan engine operation monitoring method and system based on digital twinning, belongs to the technical field of turbofan engine monitoring, and aims to solve the problems that weak fault signals such as early cracks and abrasion are difficult to extract and the prediction precision of a multi-source fault propagation path is low under a strong noise background. An original operation signal is collected through a sensing array, and is processed by an adaptive resonance demodulation chain to generate a demodulation signal. The method comprises the following steps: carrying out time-frequency transformation on a demodulation signal, constructing an initial candidate feature set by combining feature frequency prior matching actual measurement and theoretical feature frequency, and generating an independent feature set by fusing multi-scale decoupling network separation features of digital twin constraints; for independent features, effective causal pairs are screened by adopting a physical coupling relationship combining Granger causal analysis and digital twinborn simulation, a dynamic Bayesian network is constructed to simulate fault propagation, a posterior probability is calculated through digital twinborn verification and Monte Carlo simulation, early warning is triggered, and a maintenance decision is generated. And weak signal extraction and accurate fault prediction under strong noise are realized.

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan that defines a plurality of fan wakes; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a pylon fairing dihedral, wherein the pylon fairing dihedral is in a direction opposite the incoming fan flow swirl and associated sheared profiles of fan wakes upon arrival at the pylon leading edge.

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan defining a fan diameter; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a leading edge and including a first inflection point along the leading edge, the first inflection point defining a first radius of curvature that is less than 5 times the fan diameter and greater than 0.1 times the fan diameter.

The invention discloses a turbofan engine compressor blade crack multi-modal monitoring system, and belongs to the field of multi-modal monitoring, and the system comprises a multi-modal acquisition module which obtains the multi-modal data of each compressor blade, carries out the dynamic filtering denoising and temperature compensation preprocessing, completes the time axis alignment, and carries out the data reconstruction and feature extraction; and constructing a multi-modal feature vector. And the triggering module carries out preliminary abnormality diagnosis according to the judgment result, judges whether the blade is abnormal or not through a key feature threshold, determines whether to trigger depth evaluation or not by combining a periodic threshold, identifies a potential crack blade and generates an excitation decision. And when an excitation decision is executed, the intelligent diagnosis module monitors the strain gradient change to perform excitation monitoring, compares the vibration characteristics of a potential crack blade with the vibration characteristics of a contrast blade, judges whether a crack exists or not, and realizes multi-stage early warning, so as to solve the problem that the crack of the turbofan engine compressor blade is difficult to quickly detect in real time in the prior art. And safe and stable operation of the engine is guaranteed.

The invention relates to a fan module of a turbine engine with a variable pitch mechanism, the turbine engine and a pitch adjusting method. The fan module comprises fan blades and a propeller pitch adjusting rocker arm. The fan blades are installed on the fan installation hub through a bearing, and the fan blades are connected with the propeller pitch adjusting rocker arm at the same time; the hydraulic actuating device comprises a piston and an actuating cylinder body, the piston can reciprocate in the actuating cylinder body, and the propeller pitch adjusting rocker arm is matched with the piston of the hydraulic actuating device; the fan installation hub is fixedly connected with the fan input shaft, and the actuator cylinder body is fixed to the fan input shaft; the safety locking mechanism is matched with the piston; the fan module has a first state, a second state and a third state.

The invention discloses a real-time early warning method for oscillation combustion of an afterburner, and the method comprises the steps: employing a network structure in which Fourier series is simplified and then the Fourier series is introduced into a Kolmogorov-Arnold network (Kolmogorov-ArnoldNetworks, KAN), proposing a Cosine Kolmogorov-Arnold network (CosKAN), and in combination with an anomaly detection idea, proposing a new algorithm which is named as an anomaly detection Kolmogorov-Arnold network (AD-KAN). Specifically, the algorithm can learn feature distribution of all normal sample points in an unsupervised manner, map the feature distribution to a high-dimensional space, and autonomously learn an early warning boundary through a minimum surrounding ellipsoid to realize early warning of afterburner oscillation combustion. In order to verify the feasibility of the method, a test is carried out on a certain type of turbofan aero-engine ground test bench, and the result shows that the AD-KAN method has excellent performance in precision, real-time performance, early warning performance and robustness. Therefore, the method has good early warning performance, and real-time early warning of aero-engine afterburner oscillation combustion can be effectively achieved.

The invention relates to the technical field of wind power generation, and particularly discloses a duct double-turbine supercharged windmill which comprises a duct and a blade type rotating structure arranged in the duct. The duct sequentially comprises a first contraction section, a first straight section, a second contraction section and a second straight section in the air flow direction, and the diameter of the first straight section is larger than that of the second straight section. The blade type rotating structure comprises a rotating shaft, a first-stage turbine and a second-stage turbine, the first-stage turbine and the second-stage turbine are arranged on the rotating shaft, the first-stage turbine and the second-stage turbine are correspondingly arranged on the first straight section and the second straight section respectively, and the rotating shaft is connected with the generator through a transmission structure. Structural improvement is carried out through the blade type rotating structure and the duct, the turbofan located at the front end drives the turbofan located at the rear end to rotate, and therefore the wind energy utilization rate is increased.

A turbofan engine defining an axial direction and a longitudinal centerline along the axial direction is provided. The turbofan engine includes: a fan section having a fan, the fan comprising a plurality of fan blades; a turbomachine drivingly coupled to the fan, the turbomachine comprising a compressor section with a low pressure compressor, a turbine section with a low pressure turbine, a reduction gearbox, and an outer casing, the low pressure turbine drivingly coupled to the low pressure compressor across the reduction gearbox; an outer nacelle surrounding the fan and at least a portion of the turbomachine; an outlet guide vane extending between the turbomachine and the outer nacelle at a location downstream of the plurality of fan blades, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip.

Laser cutting equipment for precision equipment sheet metal machining relates to the field of sheet metal machining and comprises a laser cutting head, a cutting table mechanism, a gantry hoisting mechanism and a cutting cleaning mechanism, and the cutting cleaning mechanism and the laser cutting head are both arranged on the gantry hoisting mechanism. The gantry hoisting mechanism comprises a transverse guide rail and a vertical guide rail which are arranged on the cutting table mechanism, the cutting and cleaning mechanism comprises a flow guide cover and a turbofan assembly arranged on the inner side of the flow guide cover, and the turbofan assembly is used for cleaning the laser cutting part. The surface of the sheet metal part of the cutting part of the laser cutting head is cleaned, in the moving process of the laser cutting head, the turbofan assembly on the inner side of the flow guide cover rotates and grinds the surface of the sheet metal part, residual oil stains, dust particles and rust are reduced, residues on the surface of the sheet metal part are reduced, the turbofan assembly rotates to rub the surface of the sheet metal part, and the surface of the sheet metal part is protected. Dirt on the surface of the sheet metal part is cleaned in time, the cutting face is prevented from being rough, and the cutting precision is improved.

An engine system for an aircraft includes a first turbofan engine and a second turbofan engine. The first turbofan engine includes a first low-pressure shaft, a first fan having a first fan shaft, and a counterclockwise gearbox assembly. The first fan shaft is drivingly coupled to the first low-pressure shaft through the counterclockwise gearbox assembly. The first low-pressure shaft rotates in a counterclockwise direction. The first fan shaft rotates in the counterclockwise direction such that the first fan rotates in the counterclockwise direction. The second turbofan engine includes a second low-pressure shaft, a second fan having a second fan shaft, and a clockwise gearbox assembly. The second fan shaft is drivingly coupled to the second low-pressure shaft through the clockwise gearbox assembly. The second low-pressure shaft rotates in the counterclockwise direction. The second fan shaft rotates in a clockwise direction such that the second fan rotates in the clockwise direction.

The invention provides a robot welding machine, and belongs to the technical field of welding robots, the robot welding machine comprises a robot body, and further comprises a shunting heat conduction assembly and a supporting cleaning assembly; protective gas forms focused gas flow through shunting and secondary shunting, and gas flow sprayed by the cooling channel and the permeable plate is uniformly mixed under the guidance of a conical space at the front end of the nozzle, so that the concentration distribution of the protective gas above a molten pool is consistent, and the welding seam quality is improved; trace moisture in the protective gas is treated under the action of centrifugal force of the turbofan, and water vapor generated by falling and evaporation of water drops is guided to the periphery of the gas hood and cannot intrude into a molten pool area; the heat conduction cylinder rotates to enable airflow to sweep the whole surface of the contact tube, local overheating and heat dissipation dead angles are avoided, and the normal working temperature of the contact tube is guaranteed; the airflow can clean splashing particles attached to the outer side of the contact tube and the inner wall of the nozzle, the scraping arm can be tightly attached to the cleaning face in the rotating process and can abut against the contact tube, the deformation possibility of the contact tube is reduced, and the continuity and stability of the welding process are guaranteed.

A turbofan engine defining a circumferential direction is provided. The turbofan engine includes a turbomachine; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes each defining a span, the spans of the plurality of outlet guide vanes being nonuniform along the circumferential direction.

The present application relates to the field of wind power generation technology, and discloses a ducted double turbocharged windmill, which comprises a duct and a blade type rotating structure arranged in the duct. The duct comprises a first contraction section, a first straight section, a second contraction section and a second straight section in sequence along the wind direction, and the diameter of the first straight section is greater than that of the second straight section. The blade type rotating structure comprises a rotating shaft, a primary turbine and a secondary turbine arranged on the rotating shaft, the primary turbine and the secondary turbine are arranged in the first straight section and the second straight section respectively, and the rotating shaft is connected with a generator through a transmission structure. The present application improves the structure of the blade type rotating structure and the duct, and realizes that the turbine fan at the front end drives the turbine fan at the rear end to rotate, so as to improve the wind energy utilization rate.

The utility model relates to the technical field of fans, in particular to a turbofan. The device comprises a shell, and the shell comprises an upper shell and a handle; the motor and the impeller are arranged in the upper shell; the circuit board is arranged in the handle; an air guide opening is formed in the connecting position of the upper shell and the handle, the upper shell is communicated with an inner cavity of the handle through the air guide opening, and the air guide opening is suitable for guiding part of airflow in the upper shell to the inner cavity of the handle. According to the air guide opening, when the turbofan works, part of air flow penetrating through the upper shell can be guided into the inner cavity of the handle, heat dissipation is conducted on electronic devices in the handle, and the internal temperature is prevented from being too high.

A turbofan engine defining an axial direction and a longitudinal centerline along the axial direction is provided. The turbofan engine including: a fan section having a fan, the fan comprising a plurality of fan blades; a turbomachine drivingly coupled to the fan, the turbomachine comprising an outer casing; an outer nacelle surrounding the fan and at least a portion of the turbomachine; an outlet guide vane extending between the turbomachine and the outer nacelle at a location downstream of the plurality of fan blades, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip; and an inlet pre-swirl feature attached to or integrated into the outer nacelle at a location upstream of the plurality of fan blades.

The invention relates to the technical field of aircrafts, and particularly provides a turbine engine system and an aircraft, the turbine engine system comprises a main propulsion channel, an auxiliary channel, a turbine engine, a precooler, an air turbine and a radiator; the end, away from the main air inlet, of the main propelling channel is connected with a first exhaust nozzle. The precooler and the turbine engine are located in the main propulsion channel. The end, away from the auxiliary air inlet, of the auxiliary channel is connected with a second exhaust nozzle. The air turbine and the radiator are located in the auxiliary channel. The precooler is provided with a first channel for a heat exchange working medium to flow, the radiator is provided with a second channel for the heat exchange working medium to flow, an outlet of the first channel is communicated with an inlet of the second channel, and an outlet of the second channel is communicated with an inlet of the first channel, so that the heat exchange working medium circularly flows between the first channel and the second channel; therefore, the regeneration and self-sustaining of the heat sink are realized while the air inlet temperature of the engine is reduced, and the long-endurance operation of the engine is ensured.

The invention belongs to the technical field of turbofan engine silencing acoustic liner design, and particularly relates to a turbofan engine silencing acoustic liner acoustic impedance determination method comprising the following steps: 1, calculating silencing acoustic liner acoustic resistance rn influenced by high sound intensity; 2, calculating the acoustic resistance rg of the silencing acoustic liner influenced by the tangential flow; 3, considering the influence of high sound intensity and tangential flow, and according to the relative magnitude of the sound particle speed amplitude Vo and the main flow speed Vg in the small hole, calculating the sound resistance r of the sound reduction acoustic liner in a segmented manner; 4, calculating a noise reduction acoustic liner tail end correction coefficient delta under the comprehensive influence of tangential flow and high sound intensity; step 5, considering the comprehensive influence of tangential flow and high sound intensity, and calculating the acoustic reactance x of the silencing acoustic liner; and step 6, integrating the acoustic resistance r and the acoustic resistance x of the silencing acoustic liner, and calculating the acoustic resistance z of the silencing acoustic liner.

The invention provides a heat-electricity coupling driven indirect cooling and heat regeneration mixed exhaust turbofan engine, and belongs to the technical field of aero-engines, the heat-electricity coupling driven indirect cooling and heat regeneration mixed exhaust turbofan engine comprises an engine body, and an indirect cooling and heat regeneration heat exchange system, a transmission system and an electric propulsion system are arranged in the engine body; the electric propulsion system is connected with the transmission system and drives the transmission system to do work, the transmission system and the electric propulsion system are both arranged at the middle section position of the engine body, and the indirect cooling heat regeneration heat exchange system is arranged at the head section position and the tail section position of the engine body. According to the heat-electricity coupling driven intercooling regenerative mixed exhaust turbofan engine, the solid oxide fuel cell is introduced, so that the thermodynamic cycle effective work of the engine is increased, the overall energy utilization rate of a propulsion system is remarkably improved, an optimal power supply degree design value interval is provided, and the power supply degree design value interval is optimized. And a design reference basis is provided for reasonable thermal-electric energy distribution of the corresponding propulsion system configuration in the design stage.

The invention relates to the technical field of fluid mechanics, in particular to an efficient simulation method and system for turbofan engine compressor blade sand dust erosion. The efficient simulation method for sand dust erosion of the blades of the turbofan engine compressor comprises the following steps of performing unsteady calculation on a full-stage and full-ring airflow field of the compressor until the airflow field converges, and extracting airflow field data of moving blade and stationary blade areas of each stage; according to the airflow field absolute speed data of each stage of moving blade area, obtaining airflow field relative speed data of each stage of moving blade area; setting the particle size, the initial flow, the initial position and the initial speed of sand dust at an inlet of the gas compressor; after entering the gas compressor, the sand dust sequentially passes through each stage of stationary blade and movable blade area in the gas compressor at a corresponding movement speed, and the absolute speed data and the relative speed data of the airflow field of each stage of movable blade and stationary blade area are combined to obtain the real-time movement track of the full-stage and full-ring sand dust in the gas compressor. Further obtaining the position, angle and speed of the impact point of the sand dust and the blade, and finally obtaining the erosion abrasion loss of the blade.

The invention discloses a transformer short-circuit impedance testing device, and relates to the technical field of impedance testing instruments.The transformer short-circuit impedance testing device is characterized in that a lifting mechanism is connected between a first box body and a second box body, a filter belt is connected between the first box body and the second box body, and under the control of the lifting mechanism, the filter belt is connected with the first box body; the first box body and the second box body can be separated from each other to be opened, and in cooperation with filtering isolation after the filter belt is unfolded and driving of cooling fans and turbofans in the first box body and the second box body to airflow, it can be guaranteed that internal heat dissipation is efficient and stable when the device is unfolded for use; the first box body and the second box body are closed under the control of the lifting mechanism, and the box cover is used for covering and locking, so that the device can be folded into a totally-closed box body structure during transportation and carrying, and efficient protection during transportation and carrying and efficient heat dissipation during use are both considered; and the flexibility and the stability of the device in the long-time use process are improved to a certain extent.

A turbofan engine includes a fan and a fan actuation system. The fan has a plurality of fan blades. Each of the plurality of fan blades is rotatable about a pitch axis. The fan actuation system includes one or more actuators for rotating the plurality of fan blades about the pitch axis and one or more thrust bearings. The fan actuation system is characterized by a fan actuation system envelope in a range of 300 to 1860. The fan actuation system envelope is given byNFB×DFT×Mcruise(RTBNFB),where NFB is a number of the plurality of fan blades, DFT is a fan tip diameter of the plurality of fan blades, Mcruise is a Mach number of the turbofan engine at cruise operating conditions, and RTB is a thrust bearing radius of the one or more thrust bearings.

The utility model discloses a double-air-duct turbofan which comprises a shell, an air outlet and a partition piece are arranged on the outer side of the shell, and the partition piece divides the air outlet into a first air outlet and a second air outlet which are isolated from each other up and down; first and second air inlets are respectively formed in the upper and lower ends of the shell; the motor assembly is mounted in the shell; the turbine fan blade is installed on the motor assembly, a partition plate is arranged in the middle of the turbine fan blade, and the turbine fan blade is divided into an upper turbine fan body and a lower turbine fan body which correspond to the first air inlet and the second air inlet respectively through the partition plate; the partition plate corresponds to the partition piece, and a first air channel is formed among the first air inlet, a first airflow channel in the upper turbine fan body and the first air outlet. A second air channel separated from the first air channel is formed among the second air inlet, a second airflow channel in the lower turbine fan body and the second air outlet. Double air inlet and double air outlet can be achieved through the first air channel and the second air channel which are separated from each other, and the function and the effect of two turbofans are achieved through one turbofan.

The invention discloses a hydrogen fuel cell-based extended-range vertical take-off and landing fixed-wing unmanned aerial vehicle, which comprises an unmanned aerial vehicle body and an extended-range power supply system arranged in the unmanned aerial vehicle body, the range-extended power supply system comprises a high-gas-state hydrogen cylinder, a pressure valve, a lithium battery, a hydrogen fuel cell, a DC-DC voltage stabilization module, an electric brushless turbofan and an FCU system control module, the high-gas-state hydrogen cylinder is connected with a hydrogen inlet of the hydrogen fuel cell through the pressure valve, and the electric brushless turbofan is connected with an oxygen inlet of the hydrogen fuel cell. The DC-DC voltage stabilizing module is connected with the hydrogen fuel cell, the lithium battery is used for providing peak power for the vertical take-off and landing stage of the unmanned aerial vehicle and providing basic circuit power supply for starting of the whole machine, and the FCU system control module is in communication connection with the pressure valve, the hydrogen fuel cell, the DC-DC voltage stabilizing module and the electric brushless turbofan. The problems that an existing unmanned aerial vehicle is short in endurance, slow in charging, high in pollution, high in maintenance cost, prominent in endurance and load contradiction and the like can be effectively solved.

A turbofan engine defining an axial direction and a longitudinal centerline along the axial direction is provided. The turbofan engine includes: a fan section having a fan, the fan comprising a plurality of fan blades; a turbomachine drivingly coupled to the fan, the turbomachine comprising a compressor section with a low pressure compressor, a turbine section with a low pressure turbine, a reduction gearbox, and an outer casing, the low pressure turbine drivingly coupled to the low pressure compressor across the reduction gearbox; an outer nacelle surrounding the fan and at least a portion of the turbomachine; an outlet guide vane extending between the turbomachine and the outer nacelle at a location downstream of the plurality of fan blades, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip.

The utility model relates to the technical field of sand blasting protection, in particular to a metal mold sand blasting protection tool which comprises two shells, a limiting assembly and a fixing assembly. The limiting assembly comprises a plurality of threaded rods, a plurality of limiting blocks and a plurality of first handles and is used for enabling the two shells to be close to each other and limiting the shells, and the effect that the protection tools are combined into a whole for protection is achieved; and the fixing assembly comprises two containing blocks, two third handles, two turbofans, a plurality of supporting rods and a plurality of fixing heads, the metal mold is fixed into the protection tool, and sand blasting work is assisted. Compared with the prior art, the problems that in the prior art, a mold needs to be frequently matched for clamp replacement, the sand blasting grinding area is small, and the efficiency is low are solved.

The invention discloses a high-low pressure rotor with a bearing sharing a cavity and a turbofan engine, which comprise a low pressure rotor, a high pressure rotor, a supporting assembly, a first lubricating oil nozzle and a second lubricating oil nozzle, the supporting assembly comprises a front bearing seat provided with a front bearing cavity, a first bearing which is arranged in the front bearing cavity and supports the low-pressure rotor, a second bearing which is arranged in the front bearing cavity and supports the low-pressure rotor, a third bearing which is arranged in the front bearing cavity and supports the high-pressure rotor, and a rear bearing seat provided with a rear bearing cavity. The fourth bearing is arranged in the rear bearing cavity and used for supporting the high-pressure rotor; the fifth bearing is arranged in the rear bearing cavity and used for supporting the low-pressure rotor; the sixth bearing is arranged in the rear bearing cavity and used for supporting the low-pressure rotor; compared with the prior art, the motor has the characteristics of few parts, simple structure, compact axial size, small vibration and high reliability, is convenient for controlling the weight of an engine and reducing the cost of the engine, and is suitable for wide popularization and application.

The invention discloses a fuel cell-turbofan engine hybrid power system for a cross-medium aircraft, and relates to the technical field of aero-engines, the system comprises a solid oxide fuel cell, a turbofan engine, a lithium battery, an energy management module, a motor, a propeller, a reforming hydrogen production device and a medium self-adaptive oxidant supply subsystem. In an air flight mode, the system adopts autothermal reforming hydrogen production, a fuel cell and a turbofan engine to cooperatively work, a high-efficiency low-oil-consumption low-speed cruise and high-thrust acceleration mode is provided, and meanwhile, a lithium battery is charged. In the underwater submerging and water surface sailing mode, a turbofan engine flow channel is closed, steam reforming hydrogen production is adopted, a hybrid power system composed of a fuel cell and a lithium battery is used for driving a propeller, the fuel cell provides stable power, and the lithium battery meets the instantaneous high-power requirement. The system solves the problems that a traditional power system is low in efficiency, poor in cruising ability, single in working mode and the like.

The utility model discloses a lubricating oil interruption test device for a turbofan engine. The lubricating oil interruption test device comprises a lubricating oil tank, a lubricating oil pump, a low-pressure compressor, a high-pressure compressor and an intermediate case positioned between the low-pressure compressor and the high-pressure compressor, the gas supply device is used for supplying gas to the lubricating oil pump during the test and comprises a gas supply pipeline; the oil supply test device comprises a mounting support, a three-way switching valve mounted on the mounting support, a first oil supply pipeline and a second oil supply pipeline, the three-way switching valve comprises a first communication port, a second communication port and a third communication port, the first communication port of the three-way switching valve is connected with an air supply pipeline, and the second communication port of the three-way switching valve is connected with a second oil supply pipeline. The first oil supply pipeline is connected between a second communication port of the three-way switching valve and the lubricating oil tank, the second oil supply pipeline is connected between a third communication port of the three-way switching valve and the lubricating oil pump, and the three-way switching valve is provided with a first valve position communicated with the first communication port and the third communication port and a second valve position communicated with the second communication port and the third communication port. And the mounting bracket is mounted on the intermediate case.

The invention discloses a turbofan engine fault detection method based on a variational neural anomaly detection architecture, and relates to the technical field of aero-engine fault detection and diagnose.The method comprises the steps that multi-element sensor data of a turbofan engine in the flight state is obtained, data preprocessing is carried out, and the data of the multi-element sensor data is obtained; obtaining a turbofan engine sensor fault diagnosis data set; the method comprises the following steps: constructing a turbofan engine fault diagnosis model based on variational neural anomaly detection and a unified multi-task joint optimization objective function, training the fault diagnosis model by using a turbofan engine sensor fault diagnosis data set, and realizing iterative updating of parameters through the unified multi-task joint optimization objective function; and collecting real-time multi-sensor data of the turbofan engine in a flight state and inputting the real-time multi-sensor data into the trained fault diagnosis model, and evaluating the operation state of the engine in real time. The method effectively improves the fault diagnosis accuracy of the turbofan engine, and guarantees the operation safety of the aero-engine.

The invention relates to the technical field of mixing and kneading in prebaked anode production, in particular to a dust collection system for production and processing of a mixing and kneading pot, which comprises a rack, a dust collection box, an exhaust pipe and a transmission assembly. A mixing and kneading pot is arranged on the rack, and a mixing and kneading mechanism is arranged in the mixing and kneading pot; the dust collection box is arranged on the rack, a cloth bag dust removal assembly and a blowing pipe are arranged in the dust collection box, an ash hopper is arranged at the bottom of the dust collection box, an ash discharge pipe is arranged at the bottom of the ash hopper and inserted into the mixing and kneading pot, a rotary drum is rotationally arranged in the ash discharge pipe, an ash receiving groove is formed in the rotary drum, and an air guide pipe communicating a dust removal area with the interior of the mixing and kneading pot is arranged on the dust collection box; the exhaust pipe is arranged on the dust collection box and communicated with the back flushing area, and a turbofan is rotationally arranged in the exhaust pipe; the transmission assembly is in transmission connection with the mixing and kneading mechanism, the rotary drum and the turbofan. The mixing and kneading pot and the dust collecting box are communicated in a circulating mode, dust generated in the discharging process is collected and reused, the raw material matching quality is improved, and meanwhile the working environment is optimized.