595 results about "Turbofan" patented technology

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 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 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 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.

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 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 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 provides an engine flight thrust estimation method fusing adversarial self-coding and sparse attention, and belongs to the crossing field of aerospace engineering and artificial intelligence. The method comprises the following steps that ground test run data and flight state data of the turbofan aero-engine are collected and preprocessed, and steady-state sensor data are obtained; inputting the steady-state sensor data and the corresponding working condition label into the trained adversarial auto-encoder for feature extraction to obtain a potential feature vector; s3, inputting the potential feature vector into a sparse attention module to obtain a fusion feature; inputting the fusion features into a multi-scale time sequence modeling module, and obtaining multi-scale fusion features through time sequence feature extraction of the multi-scale time sequence modeling module; and inputting the multi-scale fusion features into a trained thrust regression module to obtain an aero-engine flight thrust estimated value. The method can achieve the precise estimation of the thrust in the flight state, and has a remarkable practical engineering application value and a deployment prospect.

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).

The invention relates to a turbofan engine based on a multi-stage fan, which belongs to the technical field of aviation turbofan engines and comprises an inner duct, an outer duct, a high-pressure compressor system, a low-pressure compressor system, a high-pressure turbine, a low-pressure turbine and a multi-stage fan module. The high-pressure turbine drives the high-pressure compressor through the first transmission shaft, and the low-pressure turbine drives the low-pressure compressor and the multi-stage fan module through the second transmission shaft. And the multi-stage fan module comprises at least three stages of fans, transmits power and performs speed regulation and direction conversion through a gear set arranged on a second transmission shaft, so that the rotation directions of the odd-stage fans and the even-stage fans are opposite, and the rotation speeds of the odd-stage fans and the even-stage fans meet a certain proportional relation. The thrust load of the fan is dispersed to multiple stages of fan blades, so that the load of the fan blades is effectively reduced, the total thrust and the propulsive efficiency of the engine are improved, and meanwhile, the noise is favorably reduced.

1. Name of the product in this design: Handheld brushless turbine fan. 2. Purpose of this design: for blowing air, cooling, and heat dissipation. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the key design points: Design 1 3D view. 5. Design 1 is designated as the basic design.

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 application belongs to the field of aero-engine technology, and specifically relates to a method and apparatus for simulating aircraft bleed air during sustained test of a turbofan engine, wherein the inlet temperature T1 and inlet pressure P1 of the engine are preset to a range; Step S2: Calculate the aircraft bleed air volume W fy The range, the total bleed air temperature T of the aircraft fy The range and total bleed air pressure P fy Range; Step S3: Calculate the cold diameter D of the bleed air nozzle. fy Range; Step S4: Select the cold-state diameter D of the bleed air nozzle fy An aircraft bleed air volume verification test was conducted to obtain the bleed air volume W for the test. fyr When the induced draft volume W in the experiment fyr The requirements are met, and the cold-state diameter D of the expiratory air nozzle is adopted. fy When the induced draft volume W in the experiment fyr If the requirements are not met, return to step S4; ensure that the calculation error of the aircraft bleed air volume is within the required range, and obtain the actual bleed air volume of the engine in various states to the maximum extent through test program design. This test method has the advantages of simple test method, low test cost and high replacement efficiency.

The invention relates to the technical field of new energy vehicles, in particular to a lithium battery and ultrahigh-pressure air energy storage and power generation hybrid new energy vehicle structure which comprises an axle sleeve body, an ultrahigh-pressure air energy storage and power generation system and a running power generation system. An air filter screen is arranged at one end of the air storage chamber, and the other end of the air storage chamber is connected with an air inlet cover of the air pressurizing chamber; the motor is fixedly arranged in the air pressurizing chamber, the turbofan shaft is rotationally arranged on the motor, and the two ends of the turbofan shaft extend out of the motor; the two ends of the turbofan shaft are fixed to the fixing frame through bearing seats, and the turbofan blades are fixedly arranged on the turbofan shaft. By improving the structure of the lithium battery and ultrahigh pressure air energy storage power generation hybrid power new energy vehicle, the new energy vehicle has the advantages that the structural design is reasonable, the available space of the vehicle is fully utilized, and the driving mileage can be greatly increased, so that the problems and defects in the prior art and equipment are effectively solved.

Device and methods for guiding bleed air in a turbofan gas turbine engine are disclosed. The devices provided include louvers and baffles that guide bleed air toward a bypass duct of the turbofan engine. The louvers and baffles have a geometric configuration that promotes desirable flow conditions and reduced energy loss.

The application discloses a turbofan engine inlet temperature simulation temperature field online monitoring method, which comprises the following steps: expanding the temperature field section of the engine inlet channel according to the polar coordinates, dividing the temperature field section into m parts along the circumferential direction clockwise and dividing the temperature field section into n equal parts along the radial direction, so as to obtain an m*n grid area, each grid area represents the temperature value of a unit body, and the temperature value of each unit body is obtained; the radial average temperature of each angular position and the surface average temperature of the temperature field section are obtained according to the temperature value of each unit body; the circumferential range of the high-temperature zone is determined according to the distribution of the area-weighted radial average value measured at different radii on the aerodynamic interface along the circumferential direction, the average value of the airflow temperature in the high-temperature zone is calculated, the temperature field unevenness and the temperature distortion intensity are calculated according to the average value of the airflow temperature in the high-temperature zone, and at least one of the circumferential range of the high-temperature zone, the average value of the airflow temperature in the high-temperature zone, the temperature field unevenness and the temperature distortion intensity is displayed in real time.

The invention relates to the technical field of motor heat pipe heat dissipation, in particular to a high-voltage motor heat pipe modular extensible combined cooling device which comprises a main body shell and a high-voltage motor, the high-voltage motor comprises a motor monomer, the motor monomer is located in the main body shell, and an adjustable heat pipe cooling mechanism for conducting heat dissipation on the motor monomer is arranged on the side face of the main body shell. The adjustable heat pipe cooling mechanism comprises two second through holes symmetrically formed in the side face of the main body shell, first through pipes are fixedly connected to the positions, in the two second through holes, of the main body shell correspondingly, first fixing shells are fixedly connected to the ends of the two first through pipes correspondingly, and a second connecting plate is fixedly connected to the end of the main body shell; the end part of the second connecting plate is provided with a turbofan heat dissipation mechanism for dissipating heat of the motor single body; when the motor single body normally runs, the first fixing body does not make direct contact with the side face of the motor single body, so that the adjustable heat pipe cooling mechanism is prevented from being axially shaken by the motor single body for a long time, and the reliability of the device is improved.

The invention relates to a turbofan engine having a fixed structure, a fan, a fan casing surrounding the fan, an outer nacelle arranged around the fan casing and mounted hinged on the fixed structure, and a deployment system (250) for moving the outer nacelle from a closed position to an open position, and the deployment system has a guide rail (252) fastened around the fan casing, a slider (254) movable along the guide rail (252) and having a shoe (258), an activation system for moving the slider (254) and the shoe (258) in one direction or in the other direction along the guide rail (252) alternately, and an arm (264) having one end mounted hinged on the shoe (258) and the other end mounted hinged on the outer nacelle. Such motorized deployment system makes it possible to save space and mass of the turbofan engine.

The invention discloses a manned aircraft, and belongs to the technical field of aircrafts, the manned aircraft comprises a rack, the rack is provided with a human body fixing device and at least two turbofan assemblies, and the human body fixing device is used for fixing a human body on the rack; the turbofan assembly is connected to the tilting shaft in a tilting mode through a turbofan tilting shaft, the rotating shaft is connected to the rack, the rack drives the turbofan tilting shaft to rotate with the tilting shaft as the axis through a rotating motor, and the turbofan assembly is driven by a tilting motor to tilt with the turbofan tilting shaft as the axis. According to the invention, the rotatable and tiltable rim fan is matched with the telescopic wings for driving, so that the utilization efficiency of energy and the space efficiency of flight are improved. The driving force of the rim fan is applied to the peripheral rim, and a traditional middle motor driving mode is omitted. Due to the fact that no middle driving motor hinders airflow and wake flow distortion, thrust can be improved through a smooth and continuous flow channel in the whole duct, the motor in the center is eliminated, an important noise source is removed, and noise of the whole fan is reduced.

The invention relates to the technical field of aero-engines, in particular to a turbofan engine and an aircraft, the turbofan engine comprises an air inlet channel, a center cone, a precooler, a core machine and a flow channel adjusting mechanism, and the air inlet channel comprises an outer duct and an inner duct; the central cone is arranged at the front end of the turbofan engine; the precooler is arranged behind the central cone and is cylindrical, and the side wall of the precooler can be communicated with the outer duct and the inner duct so that airflow can pass through the precooler and can be cooled; the core machine is arranged behind the precooler, a plurality of mixing holes are formed between the core machine and the precooler, and the mixing holes can communicate with the outer duct and the inner duct so that airflow can pass through the mixing holes; the flow channel adjusting mechanism is arranged on the outer duct and can open and close the precooler and the mixing hole so as to control the flow direction of airflow between the outer duct and the inner duct. Through combination of the precooler and the flow channel adjusting mechanism, targeted precooling of air flow in the inner duct is achieved, and meanwhile cold source waste and pressure loss of air flow in the outer duct are avoided.

The utility model discloses an integrated novel turbofan which comprises an air duct, a fan arranged at one end of the air duct, and a heating assembly arranged in the air duct and right opposite to the fan. One end of the air duct is provided with a wind generating accommodating groove for accommodating the fan, and the other end of the air duct is provided with an air outlet which is integrally contracted outwards. According to the novel integrated turbofan provided by the utility model, the fan and the air duct are made into an integrated structure, so that the fan and the air duct are tightly matched, the air duct can guide air, an air deflector is not needed, and the novel integrated turbofan is low in production cost, smooth in air duct, low in wind resistance coefficient, high in air speed, low in noise and more beneficial to use.

1. Name of the product in this design: Handheld Turbine Fan (X503). 2. Purpose of this design: For use in handheld turbine fans. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

The utility model relates to the technical field of radiators, in particular to a side-blown graphics card air-cooled radiator which comprises a bottom plate and a shell, a turbofan and a heat conduction assembly are arranged in a containing space, the heat conduction assembly comprises a heat conduction bottom plate, a heat conduction top plate and a plurality of radiating fins, and the bottom plate of the heat conduction bottom plate is provided with an attaching portion. An air outlet is formed in the side wall of the shell, an air inlet is formed in the top of the shell, a connecting piece is arranged on the outer side of the bottom plate, and a wiring port is formed in the end, located on the turbofan, of the bottom plate. Through the design that the turbofan is combined with the heat conduction assembly with the unique layout, airflow can enter from the top air inlet, passes through the heat dissipation fins and then is exhausted from the air outlet in the side face, hot air is prevented from being directly blown to adjacent display cards, the heat dissipation effect under the configuration of multiple display cards is effectively improved, and the heat dissipation efficiency is improved. It is guaranteed that each display card can operate in a relatively low-temperature and stable environment, and meanwhile the practicability and compatibility of the display card are further improved through the connecting pieces and the wiring ports.

The application provides a kind of semi-automatic gas cutting machine operation platform, belongs to cutting machine technical field. Including installation base, the top of installation base is provided with turnover platform, the side of turnover platform is provided with control module, the side of turnover platform is provided with sliding module. The application is provided with flue gas collection assembly, in the suction process of self-priming pump, negative pressure air flow drives the rotation of turbofan, the heat-resistant block outside the heat-resistant rope hits the metal hot particles in dust and impurities during swinging, avoids the deposition of metal impurities at the bottom of collection tank or adsorption on the inner wall, ensures the cleanliness inside the collection tank, prevents the blockage of pipeline connection port, ensures the normal operation of flue gas collection system, avoids the splash of metal impurities to the outside of transmission mechanism, causes the damage of transmission part, reduces the maintenance frequency and cleaning cost of equipment, prolongs the service life of equipment.

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.

The invention discloses an assembled turbofan type heat exchanger, and relates to the technical field of heat exchangers. Comprising a first heat exchange water inlet assembly provided with a cold flow water inlet and a hot flow water outlet, and a second heat exchange water inlet assembly provided with a cold flow water outlet and a hot flow water inlet. The standard heat exchange unit assembly is arranged between the first heat exchange water inlet assembly and the second heat exchange water inlet assembly to communicate with the first heat exchange water inlet assembly and the second heat exchange water inlet assembly, and the first heat exchange water inlet assembly and the second heat exchange water inlet assembly are detachably connected with the standard heat exchange unit assembly. The first heat exchange water inlet assembly, the second heat exchange water inlet assembly and the standard heat exchange unit assembly are each internally provided with a cold flow spiral channel which communicates with one another, and the first heat exchange water inlet assembly, the second heat exchange water inlet assembly and the standard heat exchange unit assembly are each internally provided with a hot flow spiral channel which communicates with one another. The cold flow spiral channels and the hot flow spiral channels are arranged in a staggered mode, and the heat exchange effect is improved on the basis that it is guaranteed that the heat exchanger is convenient to disassemble, assemble and clean.