837 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 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 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 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.

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.

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 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 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.

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 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 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.

Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and / or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas solid oxide fuel cell, a motor driven by electric power from the solid oxide fuel cell, a gearbox operatively coupled to the motor, and a turbofan engine configured to generate thrust for the aircraft. The turbofan engine may be configured to provide electric power and shaft power and may include a duct fan that is operatively coupled to the motor via the gearbox, with the duct fan being driven by mechanical power from the gearbox and by the motor.

The invention discloses multistage duct turbofan power generation equipment, and relates to the technical field of power generation equipment. The ducted shell comprises a first ducted shell body and a second ducted shell body which are coaxially arranged in a communicating mode. The flow guide assembly is arranged in the first duct shell and used for guiding external airflow into the second duct shell; the positioning assembly is arranged in the duct assembly; and the middle shaft is arranged in the duct assembly through a positioning assembly. Aiming at the pain points of structural fatigue, shaking and space waste caused by one-way torque conduction when a conventional wind driven generator is mounted on a mobile platform, a conformal integrated duct design is adopted, and a two-stage turbofan, a planetary reverse rotation mechanism and a permanent magnet generator are coaxially integrated, so that air flow shrinks in a trumpet-shaped duct to accelerate pre-swirl flow guide, and the flow guide efficiency is improved. The contra-rotating turbofan is further driven to do work synchronously, the torque is completely self-counteracted, high tip speed ratio operation can be achieved at the low wind speed, and efficient and zero-reaction-torque power generation in the narrow space of the mobile platform is achieved.

The invention discloses a quick starting system and method for a small turbofan engine. The quick starting system and method are suitable for the quick starting requirement of the small turbofan engine under the high-altitude flight condition. The system comprises a gunpowder starting unit arranged at the turbine end and a smoke and fire ignition unit arranged at the gas compressor end, the gunpowder starting unit directly injects high-temperature and high-pressure gas to the tip of a turbine blade through a gas generator, a flow guide bent pipe and a starting jet nozzle penetrating through an outer culvert structure, and blowing starting of an engine rotor is achieved; the smoke and fire ignition unit introduces flames into a specific area of a combustion chamber through a solid gunpowder barrel and a flame transfer bent pipe, and ignition reliability is ensured. The method comprises the steps of starting preparation, gunpowder excitation, ignition triggering, starting termination and the like, and rapid and reliable starting of the engine is achieved through the synergistic effect of the two. By means of the design, the requirements of a low-cost small turbofan engine for small size, low cost, high reliability and high performance of a quick starting system are met.

The utility model relates to a middle cover plate with an air guide system. An air outlet is formed in the outer edge of the top of the middle cover plate with the air guide system; the middle cover plate with the air guide system is provided with an air suction channel; the outer end of the air suction channel is communicated with the air outlet. The air outlet can discharge harmful gas detained below the middle cover plate, so that the harmful gas is prevented from hurting workers during maintenance of the workers. And the turbofan provides air suction and exhaust power for the air outlet.

A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

The invention relates to the technical field of trestle construction platforms, in particular to an offshore lamplight trestle construction platform which comprises a supporting column, a bridge floor is detachably installed at the upper end of the supporting column, limiting seats are fixedly connected to the upper end and the lower end of the supporting column, the outer surface of the supporting column is sleeved with a movable barrel, the outer surface of the supporting column is further sleeved with a balance weight ring, and the balance weight ring is located below the movable barrel. The outer surface of the movable cylinder is sleeved with an auxiliary ring, the outer surface of the auxiliary ring is rotationally provided with a plurality of extension rods, the outer surfaces of the extension rods are sleeved with floating belts, the floating belts can float above the sea level, the movable cylinder automatically ascends and descends along with the sea level under the buoyancy action of the floating belts, and the communication cylinder is kept in isobaric communication with an external water body. The water column pressure formed in the rising process of sea waves and tides can automatically drive the turbofan in the driving barrel to rotate, so that continuous mechanical energy output can be achieved without additional power, and then the cleaning ring is driven to circularly clean the outer surface of the supporting column.

1. Name of the designed product: fan (B4 turbine fan). 2. Use of the designed product: for fan. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: perspective view.

The invention provides an aero-engine thermal jet flow FT-IR spectrum enhancement classification method, and the method carries out the infrared spectrum detection of six different types of aero-engine tail jet thermal jet flows including two types of turbojet and turbofan, serves as the basis of engine recognition and data source input, and is more scientific in classification. Meanwhile, aiming at the problem that the CNN method has overfitting on the existing spectral data set, the invention provides an FTIR-SpectraGAN method, new data is generated through the existing data, the classification capability of the network in various aspects is improved, and higher classification accuracy is achieved.

The invention provides a vehicle-mounted wind power ducted turbofan power generation device, which relates to the technical field of wind power clean power generation and comprises a ducted turbofan power generator device, a power generator management control system, an auxiliary power motor power input control component and a power generator power output control component, the ducted turbofan generator device comprises a double-funnel duct, a turbine pressurizing compressor installed on the front portion of the double-funnel duct and a turbine generator installed on the rear portion of the double-funnel duct, and the input end of the ducted turbofan generator device is connected with the auxiliary power motor power input control component. The output end is connected with the generator power output control part, and the ducted turbofan generator device auxiliary power motor power input control part and the generator power output control part are both connected with the generator management control system. According to the invention, continuous real-time cost-free clean power supply can be provided for running vehicles and ships.

The invention relates to the field of electric capstan, and discloses an electric capstan device which comprises a rack and a protective shell, a motor is arranged at the top of the rack, the output end of the motor is connected with the input end of a speed reducer fixedly connected to the interior of the protective shell, and the protective shell is fixedly connected to the top of the rack. The output end of the speed reducer is fixedly connected with a rope twister and used for driving the rope twister to rotate forwards or reversely, a wire arranging assembly is installed at one end of the rack, a blower is installed at one end of the wire arranging assembly, the blower is fixedly connected to one end of a protective shell, and the blower provides power for the wire arranging assembly through a transmission assembly. And a filter screen is arranged on the front side of the protective shell. By combining the design of a turbofan and an air blowing box in the wire arranging assembly, the device can effectively take away heat generated in the operation of the equipment and discharge the heat through airflow circulation, so that the stability of the equipment is improved, and the service life of the equipment is prolonged.

The invention discloses a small turbofan engine hydrogen low-pollution combustion chamber and a combustion method, the combustion chamber is used for dividing air at an inlet of the combustion chamber into three paths to enter a main combustion area for combustion, and the combustion chamber comprises a main combustion chamber inner casing, an inner flame tube, an outer flame tube and a main combustion chamber outer casing which are sequentially sleeved from inside to outside; a main combustion chamber head is arranged at one end, connected with the inner flame tube, of the outer flame tube; the wall surfaces of the outer flame tube and the inner flame tube at the other end are respectively provided with a large discharge mixing hole and a small discharge mixing hole for air to enter; the head of the main combustion chamber is provided with a hydrogen collecting cavity and a Tesla valve mixer which are connected, one end of the hydrogen collecting cavity is connected with a hydrogen supply pipeline, and the other end of the hydrogen collecting cavity is communicated with a plurality of Tesla valve channels in the Tesla valve mixer. The Tesla valve mixer is utilized, mixing strengthening is achieved on the basis of transverse jet flow and cross jet flow combination, efficient mixing of hydrogen and air is achieved under the constraint of the limited size of the head of the main combustion chamber, hydrogen lean-burn micro-premixed combustion is completed, and emission of nitrogen oxide is reduced.

The utility model relates to the technical field of electronic equipment, and discloses an accelerator card, which comprises a radiating plate, a turbofan and a radiator, and the turbofan and the radiator are arranged on the same side of the radiating plate along the length direction of the radiating plate; the radiator comprises a first heat dissipation module and a second heat dissipation module, the first heat dissipation module and the second heat dissipation module are adjacently arranged in the width direction of the heat dissipation plate, and the first heat dissipation module and the second heat dissipation module are each composed of a plurality of fins arranged at intervals; the radiator is provided with a heat dissipation channel, the heat dissipation channel penetrates through the first heat dissipation module and the second heat dissipation module, and a preset distance is formed between the heat dissipation channel and the turbofan; and an air outlet of the turbofan faces the first heat dissipation module, and the turbofan is used for generating cooling air, so that the cooling air is blown to the first heat dissipation module and is blown to the second heat dissipation module from the first heat dissipation module through the heat dissipation channel. The utility model aims to improve the heat dissipation effect of the acceleration card and enhance the heat dissipation performance of the electronic equipment.

The invention relates to a multi-physics field simulation method and device, equipment, a storage medium and a program product. The method comprises the following steps: constructing a geometric model of the whole turbofan engine and each component, carrying out grid discretization on a physical space of the geometric model to obtain a grid system of the geometric model, and determining spatial distribution of each physical field according to a discretization control equation set of a plurality of physical fields of the grid system, and determining simulation results of the whole machine and each part of the turbofan engine on the basis of the spatial distribution of each physical field, so that modeling can be performed for the whole machine and each part of the turbofan engine, and tight coupling simulation of multiple physical fields is realized on the basis of geometric models of the whole machine and each part of the turbofan engine. And the simulation precision and accuracy are improved.