89 results about "Turbofan" patented technology

The invention relates to a method for manufacturing an outer shroud for an intermediate casing of a turbofan engine made of composite material, comprising: - making a fibrous fabric (140) in the form of a strip by means of three-dimensional or multilayer weaving; - winding the fibrous fabric (140) in a plurality of superimposed layers (141, 142, 143, 144) on a mandrel (200) whose profile corresponds to the profile of the outer shroud to be manufactured, so as to obtain a fibrous preform whose shape corresponds to the shape of the outer shroud to be manufactured; - densifying the fibrous preform using a matrix. During the step of winding the fibrous fabric (140) on the mandrel, a fabric strip (150) is placed between one or more adjacent turns of the fibrous fabric, wherein the fabric strip (150) has a structure that is different from the three-dimensional weaving and has a width in the axial direction (D A ) that is less than the width of the fibrous fabric (140).

A turbofan engine and a bleed air door arrangement for reducing the effects of rain on engine performance. The bleed air door arrangement includes a bleed air window, a valve plate, and a grid; the bleed air window is configured in an intermediate casing between an outer and an inner duct, through the intermediate casing; the valve plate extends upstream from a downstream edge of the bleed air window into the inner duct to open the bleed air window; the grid extends from the valve plate into the inner duct to break up water droplets in the inner duct.

This invention relates to a turbine wind turbine generator, comprising a frame, a turbine fan, and a power conversion output module. The frame is hollow and interconnected on all four sides. The turbine fan includes a central shaft pivotally mounted within the frame and a blade assembly disposed on the central shaft. The blade assembly includes a plurality of blades extending axially along the central shaft. The power conversion output module is connected to the central shaft. When exposed to wind, regardless of wind direction, airflow can enter the frame of the turbine wind turbine generator and contact the blades of the blade assembly, causing the turbine fan to rotate. The power conversion output module converts the power generated by the rotation of the central shaft into electricity and outputs it. Therefore, the turbine wind turbine generator does not need to rotate with the wind direction, reducing unnecessary energy loss and improving the efficiency of power generation.

A turbofan engine for an aircraft includes a fan, one or more sensors for providing sensor data indicative of an excitation load, and a fan actuation system. The fan has a plurality of fan blades coupled to a fan shaft having one or more fan bearings. The fan actuation system is disposed within a fan hub and includes one or more actuators for rotating the fan blades about the pitch axis and one or more radial thrust bearings. The fan actuation system is characterized by a fan actuation system length envelope in a range from 8.5 to 24 and given byNFB×DFTLAXIAL×(RTBNFB).NFB is a number of the fan blades, DFT is a fan tip diameter of the fan blades, RTB is a thrust bearing radius of the radial thrust bearings, and LAXIAL is an axial length from a fan hub tip to the fan bearings.

The application belongs to the technical field of aviation electromechanical systems, and discloses an airborne energy supply system based on engine waste heat recovery and an operation method thereof, wherein the system uses the waste heat of engine exhaust gas to heat a closed cycle unit, and the closed cycle unit converts heat energy into electric energy to supply power to an airplane; the closed cycle unit comprises a closed cycle gas circuit, an SCO2 compressor, an SCO2 turbine and a generator, the gas in the closed cycle gas circuit circulates under the drive of the SCO2 compressor, drives the SCO2 turbine to operate, and drives the generator to generate power, and the gas in the closed cycle gas circuit absorbs the waste heat of the engine exhaust gas before entering the SCO2 turbine to become high-temperature gas. The application can recover the waste heat of the exhaust gas of the airplane turbofan engine to generate power and provide airborne energy for the airplane, and compared with the traditional airplane auxiliary power device, the application avoids the supply of airplane fuel.

The application provides a combined power system based on a methanol fuel cell auxiliary power device and a turbofan main engine, which is applied to the field of aviation power technology and comprises a fuel supply system, a heat exchanger, a preheater, a methanol fuel cell auxiliary power device system and a turbofan engine core system; the fuel supply system is connected with the methanol fuel cell auxiliary power device system and the heat exchanger respectively; the heat exchanger and the methanol fuel cell auxiliary power device system are connected with the preheater; and the preheater is connected with the turbofan engine core system. The methanol fuel cell auxiliary power device can utilize the electric power generated by the fuel cell to drive an electric auxiliary turbocharger to generate high-pressure gas when the main engine is started, so that the high-pressure gas is led to the combustion chamber of the main engine and the combustion efficiency is improved; on the other hand, the electric power generated by the fuel cell can be utilized to preheat the fuel led to the main engine, so that the atomization quality of the fuel is improved and the combustion efficiency is further improved.

The application relates to the field of general structure design of an aero-engine, and discloses an aero-engine duct airflow distribution mechanism and a control method thereof. The bleed air structure and the flow path control structure are integrated in the rotating casing and the support plate structure of the inner and outer ducts. In the turbofan mode, the leading edge and the trailing edge of the corresponding support plate of the outer duct and the inner duct are matched, so that the duct flow is smooth. In the turbojet mode, the inner and outer duct flow passages are blocked, and the outer duct airflow is guided into the inner duct. The application can support the demand that the variable flow path aero-engine works in the turbofan engine mode at low flight speed and works in the turbojet mode at high flight speed, widen the flight speed domain of the conventional turbofan engine, realize the consideration of high economy at low speed and large thrust at high speed, and effectively reduce the structural complexity of the engine.

This application belongs to the field of turbofan engine starting design technology, specifically involving a turbofan engine backwind starting method, including: Step 1, identifying whether the turbofan engine is starting under high-speed backwind conditions by whether the low-pressure rotor reverses; if the low-pressure rotor reverses, the turbofan engine is identified as starting under high-speed backwind conditions; Step 2, after identifying that the turbofan engine is starting under high-speed backwind conditions, determining the wind pressure resistance PdX of the turbofan engine starting under high-speed backwind conditions by the low-pressure rotor reverse rotation speed and the correspondence between the low-pressure rotor reverse rotation speed and wind pressure resistance; Step 3, after the low-pressure rotor changes from reverse rotation to forward rotation under the starter motor, reducing the nozzle throat area A8, adjusting the nozzle exit area A9 and vector angle δA9 to shield the nozzle throat, increasing the ignition speed to ignite the turbofan engine, and increasing the fuel supply speed to supply fuel to the turbofan engine, thereby starting the turbofan engine.

The utility model discloses a curve Huang wind force conveying system, including roots blower, one side of roots blower is provided with pipeline, one side of pipeline is provided with shock absorber, concave support frame is set in the top of pipeline, the inside of concave support frame is provided with hopper, the utility model discloses through starting roots blower and makes it run under stable speed, can form stable airflow in conveying system, provides basic condition for material stable conveying, simultaneously, through opening rotation mechanism and adjusting frequency control material from hopper into the speed of pipeline, avoid the problem of pipeline blockage caused by feeding speed too fast, through the material under the action of conveying airflow, with the cooperation of pipeline and conveying pipe into the tank, reduce the resistance and energy loss in the conveying process, in the conveying process, operating personnel can observe the operating parameter of roots blower in real time, such as current, air pressure etc, be convenient for operating personnel to discover potential problem in time.

The name of the invention is hybrid turbofan engine and solid oxide fuel cell propulsion system and related methods. A hybrid propulsion system utilizes a liquid natural gas solid oxide fuel cell in a practical manner suitable for an aircraft that avoids the use of heavy batteries, provides transient response times suitable for use in an aircraft, and / or simplifies a reactant pre-processing system using a compressor and turbine operably coupled to the solid oxide fuel cell. Such a hybrid propulsion system for an aircraft can include a liquid natural gas solid oxide fuel cell, an electric motor driven by electrical power from the solid oxide fuel cell, a gearbox operably coupled to the electric motor, and a turbofan engine configured to produce thrust for the aircraft. The turbofan engine can be configured to provide electrical power and shaft power, and can include a ducted fan operably coupled to the electric motor by the gearbox, the ducted fan driven by mechanical power from the gearbox and the electric motor.

1. The name of the design product: Handheld turbine fan (X211). 2. The use of the design product: For handheld turbine fan. 3. The design points of the design product: In shape. 4. The picture or photo that best indicates the design points: Perspective view.

The application discloses an aero-engine hot-end component full-life-cycle management method and system, and belongs to the technical field of aero-engines.The system constructs a full-life-cycle closed loop system of material gene optimization-precision forming process-service health monitoring-life prediction and active repair, can realize service life improvement of more than 200% of the aero-engine hot-end component, and improves the production yield rate from the conventional 60% in the industry to more than 90%.The application fills the core short board of short life, poor reliability and low yield rate of the aero-engine hot-end component in China, breaks through the core technical bottleneck of the "industrial crown pearl" of the aero-engine, and is 100% domestically produced and controllable in material and process, and can be widely applied to scenes such as army armed helicopter turboshaft engines, military unmanned aircraft turbojet / turbofan engines and the like.

This utility model relates to the field of fan technology, and more particularly to an embedded booster fan with a remote control. The technical solution includes a housing, in which a booster fan is installed. It also includes an air inlet located on one side of the housing, a filter screen disposed within the air inlet, a fixing frame fixedly installed on the housing to one side of the filter screen, a protective net disposed within the fixing frame, and plug-in plates fixedly installed at the upper and lower ends of the protective net. The plug-in plates have limiting grooves that match the limiting plates. This utility model achieves protection for the filter screen, intercepts large particulate impurities, reduces the load on the filter screen, minimizes physical damage to the filter screen, and automatically cleans and collects dust adhering to the filter screen, preventing filter screen blockage and increased air resistance, thus improving ventilation efficiency.

The utility model discloses an embedded computer heat abstractor relates to heat abstractor field, including fan shell, turbofan and turbofan blade, the turbofan movable mounting is in the inside of fan shell, and turbofan blade fixed mounting is in the outside of turbofan blade, the both sides integration of first fin and second fin has in the outside of fan shell, and first fin is located one side at second fin, the top of fan shell is provided with fin slot. The utility model air is driven under the turbofan blade and penetrates fin, realizes forced convection heat dissipation, and the heat dissipation efficiency is greatly promoted, and the fin slot with the heat dissipation fin of annular design allows heat conduction ring and heat conduction copper pipe to install at any angle, adapts to the narrow or irregular space layout of embedded computer, and the compatibility of promoting device is compatible, and the heat conduction ring is detachable connection through the installation buckle and fan shell, and the heat dissipation assembly part can be independently disassembled, and is convenient for maintenance or replacement.

The application discloses a turbofan engine coupling device, which comprises a coupling structure connected between a fan of a turbofan engine and a rotor of the turbofan engine; the coupling structure comprises a rotor shaft, a fan shaft structure and a floatable coupling piece; one end of the rotor shaft is connected with the rotor of the turbofan engine; the fan shaft structure is sleeved on the outer surface of the rotor shaft at one end close to the rotor shaft, and the other end of the fan shaft structure is adapted to be connected with the fan of the turbofan engine; the floatable coupling piece is installed at the connecting position of the rotor shaft and the fan shaft structure, and the floatable coupling piece comprises rollers and first and second shaft rings oppositely arranged on both sides of the rollers; the first shaft ring is connected with the rotor shaft, and the second shaft ring is connected with the fan shaft structure. The structure can make the axial force of the turbine and the axial force of the fan shaft structure and the rotor shaft counteract each other, can reduce the axial load borne by the rotor shaft and the fan shaft structure, and is favorable for the reliability and service life of the engine shaft system.

This application provides a ground functional test method for a cross-medium engine, comprising: step 1, verifying the initial state function of the flow channel sealing system; step 2, verifying the nitrogen purging function of the combustion chamber; step 3, verifying the rotation function of the underwater combustion chamber; step 4, verifying the cold-state purging function; step 5, verifying the control function of the compressor cooling water; step 6, verifying the fuel supply function of the main combustion chamber; step 7, verifying the function of the flow channel sealing system; step 8, verifying the over-speed shutdown function, over-temperature shutdown function, speed limiting function, and temperature limiting function of the controller; and step 9, verifying the switching function of the engine operating state. This application solves the problem of missing verification methods for some systems in the ground functional test method for turbofan engines during the guidance of ground functional tests for cross-medium engines.

A gas turbine engine includes a drive turbine, a fan, and a gearbox. The fan has a fan blade defining a leading edge fan radius RFan_LE and a trailing edge fan radius RFan_TE, and the fan defining a leading edge hub radius RHub_LE and a trailing edge hub radius RHub_TE. The gearbox mechanically couples the drive turbine to the fan. The gas turbine engine defines a Fan Leading Edge to Trailing Edge Compression Factor (FLTCF) greater than or equal to 1.05 and less than or equal to 1.8. The drive turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage divided by the annular exit area of a forward-most rotating stage. In some instances, the area ratio is within a range of 2.0-6.5. Additionally (or alternatively), the low-pressure turbine includes an area-EGT ratio within a range of 1.05-1.6.

The utility model discloses a kind of clean towel processing's disinfection device, it is related to cleaning equipment technical field, including receiving seat and steam generator, the upper surface of the receiving seat is fixedly connected with steam disinfection chamber, the inner wall of the steam disinfection chamber is provided with separation hanger, the outer wall of the receiving seat is fixedly connected with the outer wall of steam disinfection chamber close to top end by circulation air pipe, including rotating rod, the outer wall of the rotating rod is fixedly connected with ring stand.The utility model is rotated by driving motor, ring stand and turbofan of rotating rod, the airflow generated makes steam circulate in steam disinfection chamber, in combination with the design of steam lance and breathable bottom net, ensure that steam can evenly contact each part of towel, effectively improve the uniformity and effect of disinfection, avoid disinfection dead angle, circulation air pipe realizes the recycling of steam, reduce the waste of steam, reduce energy consumption, compared with traditional steam disinfection equipment, more energy saving and environmental protection.

This invention relates to the field of indoor environmental monitoring devices, specifically an intelligent indoor environmental monitoring device and its monitoring method. The device includes a monitoring unit with a bracket fixedly mounted at its bottom via bolts for stable support. A monitoring shell is fixedly mounted inside the monitoring unit, and a sampling receiving cover is fixedly mounted on the outer surface of the monitoring shell. Multiple sets of blower motors are fixedly mounted inside the monitoring unit, and each blower motor's output end is fixedly connected to a turbofan. This invention constructs a dynamic flow field through a distributed monitoring unit, utilizing a relay transmission mechanism of blower and suction to forcibly drive the originally still indoor air into directional circulation. Compared to traditional passive diffusion-based monitoring, this solution eliminates monitoring blind spots (such as corners and behind furniture), enabling the monitoring data to accurately reflect the overall indoor environmental conditions. Especially in large spaces or complex partitioned environments, the spatial representativeness of the sampling data is improved.

The utility model discloses a kind of fibreboard polishing devices, including polishing work area, and polishing wheel processing assembly is arranged in polishing work area;Polishing wheel processing assembly includes electric linear guide rail, electric sliding block slidingly connected in the front of electric linear guide rail and tray fixed in the front side of electric sliding block, the right side of tray is fixed with water tank, the right side of water tank is fixed with booster water pump, and booster water pump is connected with several atomizing nozzles by delivery pipe, and the left side position of the inner chamber of tray is fixed with multiple micro turbofan fans.The utility model is set on the basis of polishing machine and sets polishing wheel processing assembly, and the polishing wheel after polishing is cleaned using booster water pump and atomizing nozzle, and the impurities remaining on polishing surface can be effectively removed, so as to avoid the influence of impurities on polishing quality;Micro turbofan fan can also be used to blow the polishing wheel, which not only blows away the impurities cleaned, but also speeds up air flow to cool the polishing wheel, prolonging the service life of the polishing wheel.

The application belongs to the field of main fuel control, and particularly relates to a main fuel control method for preventing a turbofan engine from turning down, comprising the following steps: setting a slow-speed high-pressure rotor speed deviation value, obtaining a current high-pressure rotor speed in real time, comparing the current high-pressure rotor speed with the slow-speed high-pressure rotor speed set value to obtain a deviation between the current high-pressure rotor speed and the slow-speed high-pressure rotor speed set value; obtaining a current slow-speed high-pressure rotor speed deviation value, determining a corrected acceleration oil flow rate according to an acceleration oil correction amount; obtaining the corrected acceleration oil flow rate, controlling the engine to obtain a new slow-speed high-pressure rotor speed deviation value; judging whether the new slow-speed high-pressure rotor speed deviation value meets a rotor speed deviation threshold value, and if yes, exiting the main fuel control. The method can timely find a rotor speed abnormality decrease condition and identify a turning-down risk of the engine, and when the engine has the turning-down risk, the acceleration oil flow rate is corrected to ensure that the engine can sufficiently increase the oil supply amount and avoid the engine from turning down.

The utility model relates to flowmeter device technical field discloses a flowmeter with prevent blocking structure, including measuring pipe, the both ends fixedly connected with flange of measuring pipe, the outside fixed communication of measuring pipe has filter component, the top fixedly connected with mounting seat of measuring pipe, the top of mounting seat is provided with flowmeter, the inside of measuring pipe is provided with fixed axle, the both ends fixedly connected with bearing of fixed axle, the outside fixedly connected with turbofan of bearing, the inboard fixedly connected with scraper of turbofan, the outside fixedly connected with ring of fixed axle. In the utility model, through the cooperation of turbofan, bearing, scraper and fixed axle, when using the device, the fluid is used to impact turbofan to make turbofan rotate and drive scraper to rotate, the inner wall of measuring pipe is cleaned, the inner wall can be cleaned when using, need not to stop cleaning, improve work efficiency, prolong the service life of equipment.

A fluid cooler for installation in a bypass duct of a turbofan gas turbine engine and associated methods are provided. The fluid cooler includes an inlet duct, a heat exchanger and an outlet duct. The inlet duct includes an inlet protruding into the bypass duct to receive a portion of the bypass air into the inlet duct. The heat exchanger is in fluid communication with the inlet duct. The heat exchanger facilitates heat transfer between a fluid and the portion of bypass air received into the inlet duct. The heat exchanger defines a general flow direction for the portion of bypass air that is different from the main flow direction of bypass air inside the bypass duct. The outlet duct conveys the portion of bypass air from the heat exchanger back to the bypass duct.

This invention relates to the field of aero-engine technology and discloses a design method and system for the torsional vibration of a low-pressure turbine shaft of an aero-engine. It performs segmented torsional stiffness calculations on the low-pressure turbine shaft based on its actual structure. The torsional frequency analysis of the low-pressure turbine shaft is performed after fully considering the torsional stiffness, polar moment of inertia of the fan rotor, and polar moment of inertia of the low-pressure turbine rotor. This method eliminates the need to rebuild a simulation model to complete the margin analysis between the torsional frequency of the low-pressure turbine shaft and the vibration frequencies generated by all engine components. It is more suitable for the needs of rapid iteration in multiple rounds of design, enabling rapid evaluation and optimization of the torsional vibration frequency of the low-pressure turbine shaft in the early stages of engine design. This guides the structural design of the low-pressure turbine shaft, ensuring that the torsional vibration frequency of the turbofan engine's low-pressure turbine shaft meets design requirements and that torsional resonance does not occur within the operating speed range, thus shortening the overall design cycle.

The utility model relates to air conditioner fan -coil technology field especially, and more particularly to a fan -coil with air purification function, including fan -coil main part, the fixed mounting of the coil on fan -coil main part has the shell, the shell covers the periphery of the coil, the fixed mounting of double -shaft motor has in fan -coil main part, the two -way output shaft of double -shaft motor and fan -coil main part inside turbine fan impeller shaft are linked, still including the primary filter screen of setting in the shell both sides of fan -coil main part, the purification frame is set up to the primary filter screen of setting in the shell both sides of fan -coil main part, the primary filter screen is set up to the primary filter screen of setting in the shell both sides of fan -coil, the purification frame is set up to the primary filter screen of setting in the shell both sides in fan -coil main part, the purification frame is set up to the primary filter screen of setting inside the shell both sides in fan -coil main part, the purification frame is set up to the purification frame of setting in the shell both sides in fan -coil main part, the purification frame is set to the purification frame of setting in the shell both sides in fan -coil main part, the primary filter screen is set up to the primary filter screen of the setting in the shell both sides in fan -coil main part, the purification frame is set up in the primary filter screen of the setting in the shell both sides in fan -coil main part, and the primary filter screen is set up to the primary filter screen of the setting in the shell both side in fan -coil main part.

The application discloses a middle gear spiral combination for a reducer and a turbofan engine, which comprises a gear shaft with a pinion, a left shaft neck and a right shaft neck, and a large gear cooperating with the pinion to reduce transmission. The large gear and the pinion are both spiral gears, and the pitch circle diameter of the large gear is larger than that of the pinion. The middle gear spiral combination further comprises a connecting adjustment structure, the large gear is screwed on the outer circle of the gear shaft through the connecting adjustment structure, and is positioned between the pinion and the right shaft neck. The "Y" shaped reducer of the application can adjust the angle of the middle gear spiral combination, so that all the transmission tooth surfaces can be normally engaged without interference, and the effective transmission of power is facilitated. The "Y" shaped transmission scheme of the application divides the power flow into two parts, the radial pressure of the tooth surface is reduced to one half, the directions of the pressure vectors of the tooth surface are different, the vector sum is smaller than the sum of the values, the bearing life is prolonged, and the gear strength margin of the engine is improved.

The application provides a wing-body fusion back support engine reverse thrust device capable of inhibiting air intake distortion, which comprises a ring-shaped reverse thrust vane located on the inner side of a back support engine nacelle cover and reverse thrust flow guiding plates located on the two side surfaces of a back support engine nacelle support. When reverse thrust is needed, with the increase of the unfolding angle of the flow guiding plates, the hindering effect of the flow guiding plates on the forward movement of the reverse thrust air flow is more and more significant, so that the air intake quality of the turbofan engine during the reverse thrust work is ensured; in addition, the flow guiding plates also have the interference effect on the air flow similar to that of a spoiler, so that the form resistance is increased, which is beneficial to the faster deceleration of the airplane. The application effectively solves the adaptability problem of the reverse thrust device and the wing-body fusion back support engine, inhibits the occurrence of air intake distortion, strengthens the braking effect of the reverse thrust device, and guarantees the flight safety of the wing-body fusion back support engine layout.

A turbofan engine includes a turbo-engine, a fan, and a double gearbox assembly. The turbo-engine includes a compressor section, a turbine section, and a combustor in fluid communication with the compressor section and the turbine section. The turbine section includes a low-pressure turbine having a low-pressure shaft and a plurality of low-pressure turbine stages. The fan has a fan shaft drivingly coupled to the low-pressure shaft through the double gearbox assembly. The double gearbox assembly includes a first stage gear assembly coupled to the low-pressure shaft and an interstage shaft, a second stage gear assembly coupled 100 to the interstage shaft, and an output shaft coupled to the fan shaft. The double gearbox assembly is characterized by a Double Gearbox Engine Parameter (DGEP) in a range from 150 to 650 kilograms, the DGEP being given byk×S×∑ i=12⁢(Pfan×106×zi376×ωring⁢ i×nplanetsi×Rring⁢ i2×π×Rring⁢ i2zi2×(18.5×zi+85.5625)).

An acoustic turbine fan airfoil apparatus is disclosed. An example apparatus includes a platform of a turbofan engine, the platform including a perforation to receive an acoustic wave; an acoustic cavity protruding from a first side of the platform, the acoustic cavity aligned with the perforation in a radial direction defined by the turbofan engine, the acoustic cavity to attenuate the acoustic wave; and an airfoil protruding from a second side of the platform opposite the first side of the platform.