1521 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 relates to the field of precursor material drying, and provides a drying device capable of continuously processing a precursor material, comprising: a mounting table; the housing is fixedly arranged on one side of the upper part of the mounting table; a discharge hole is obliquely formed in the upper part; the air guide volute is fixedly connected to the lower end part of the housing, and an air inlet pipe is arranged at a volute tongue of the air guide volute; and the shunting turbofan is arranged in the air guide volute and consists of an upper side plate, a lower side plate and a plurality of arc-shaped fan blades which are uniformly arranged in the side plates at intervals. A precursor material is sprayed into the drying equipment in a mist shape through the spraying mechanism, continuous feeding of materials with different moisture contents is achieved for continuous processing, the phenomena of agglomeration and drying scaling of the materials when the materials enter the drying area of the equipment are effectively reduced, meanwhile, heat discharged during drying is recycled through the heat recovery pipe, and the energy consumption is reduced. And while the production energy consumption is reduced, the product granularity and granularity distribution are effectively controlled, and the drying uniformity is ensured.

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.

The invention relates to the technical field of heat storage equipment, in particular to heat storage and exchange integrated solid particle heat storage equipment which comprises a heat insulation barrel, a material containing barrel, a solid heat exchange pipe, a recovery pipe and a separation device. The material containing barrel is coaxial with the heat insulation barrel and located in the heat insulation barrel, and the material containing barrel is filled with solid particles. And the solid heat exchange tube is arranged in the material containing barrel. A turbofan is arranged in the recovery pipe, and the separation device is installed on the material containing barrel. According to the solid particle heat storage equipment integrating heat storage and heat exchange, by arranging the heat insulation barrel, the material containing barrel, the solid heat exchange pipe and the separation device, solid particles continuously and circularly flow in the heat storage or heat exchange process, the solid particles can make full contact with the solid heat exchange pipe, and then the heat exchange efficiency of the solid particles and the solid heat exchange pipe is improved; and the temperature of the solid particles is more uniform.

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.

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; 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, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip; and an accessory gearbox positioned at least partially inward of the outer casing of the turbomachine.

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 invention belongs to the technical field of aviation turbofan engine jet pipe control, and particularly relates to a jet pipe throat area adjusting method based on fan pressure ratio closed-loop control, which comprises the following steps: step 1, according to a jet pipe throat area design rule, calculating corresponding fan pressure ratios pifDem under different aviation turbofan engine air inlet temperatures and low-pressure conversion rotating speeds; and 2, when the aviation turbofan engine works, according to the corresponding fan pressure ratios pifDem, closed-loop control of the throat area S of the spray pipe and adjustment of the pressure ratio pif when the fan works under different air inlet temperatures of the aviation turbofan engine and the low-pressure conversion rotating speed of the aviation turbofan engine, the aviation turbofan engine is controlled.

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.

A turbofan engine includes a fan, a core turbine engine having an exhaust section, and a hydrogen-exhaust gas heat exchanger in flow communication with the exhaust section and hydrogen flowing along a hydrogen supply line. The hydrogen-exhaust gas heat exchanger defines a load capacity factor determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates characteristics of hydrogen, ambient air, and exhaust gas at takeoff, as well as a fan diameter of the fan and an overall pressure ratio of the turbofan engine. The load capacity factor is between 2.92 and 24 for the fan diameter being between 0.5 and 5 meters and the heat transfer surface area density being between 500 m2 / m3 and 13,000 m2 / m3.

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.

A turbofan engine includes a first spool including a first turbine, and a first tower shaft engaged to the first spool. A second spool includes a second turbine, and a second tower shaft is engaged to the second spool. A superposition gearbox includes a sun gear, a plurality of intermediate gears engaged to the sun gear, and is supported in a carrier and a ring gear circumscribing the intermediate gears. The first tower shaft or the second tower shaft drives one of the intermediate gears. A drive motor is engaged to drive the sun gear, an inner electric motor, a stator disposed radially outside of the inner electric motor, and an outer electric motor disposed radially outside the stator. A first load on the first spool and a second load on the second spool is adjusted by operation of at least one of the inner electric motor and the outer electric motor.

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.

An aircraft powerplant includes an engine having an output power shaft. The aircraft powerplant further includes a power transmission coupled to the output power shaft of the engine. The power transmission is configured to divide power output of the engine between a mechanical power output and an electrical power output. A majority of the power output from the engine is adjustable to output to either of the mechanical power output or the electrical power output. The aircraft powerplant further includes a propulsion mechanism coupled to the mechanical power output. The aircraft powerplant further includes a control system configured to cause the power transmission to deliver the majority of the power output of the engine to the propulsion mechanism to generate thrust or deliver the majority of the power output of the engine as electrical power output via the electrical power output.

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.