35 results about "Turbojet" patented technology

The unmanned wheeled vehicle, the control method and the control system thereof can assist the unmanned wheeled vehicle to overcome the obstacle and get rid of the predicament when the unmanned wheeled vehicle is trapped by the obstacle, thereby improving the adaptability of the unmanned wheeled vehicle to the complex terrain and improving the maneuverability of the unmanned wheeled vehicle. The unmanned wheeled vehicle comprises an unmanned vehicle main body structure, an auxiliary power system connected with the unmanned vehicle main body structure and configured to assist the unmanned vehicle main body structure to overcome the obstacle, wherein the auxiliary power system comprises a turbojet system, an unmanned vehicle state detection system configured to detect the state of the unmanned vehicle main body structure, and a control system electrically connected with the unmanned vehicle state detection system and the auxiliary power system and configured to control the auxiliary power system according to the state detection result of the unmanned vehicle state detection system.

This invention relates to the field of underground coal mining technology and discloses an explosion-proof high-energy dynamic current power generation device for underground coal mines based on non-contact turbojet technology. The device includes a pipeline, with a support frame fixedly connected to the inner ring of the pipeline. A transmission rod is rotatably connected to the inner ring of the support frame, with one end fixedly connected to a housing. A main rotor is mounted on the other end of the transmission rod. A support plate is fixedly connected to one side of the inner ring of the pipeline, and a generator is fixedly connected to one side of the outer wall of the support plate. An active bevel gear is connected and fixedly attached to the input end of the generator. Based on wind power meter readings, an electric push rod is used to disengage the corresponding main rotor from the slave rotor. Compressed air inside the pipeline then drives the housing to rotate, generating electricity. If the wind power meter reading is insufficient, a branch pipe is opened to output water from a power waterwheel, which then drives the waterwheel to rotate, generating electricity. This allows for flexible switching based on actual conditions.

The invention belongs to the field of afterburners of aero-engines, and particularly relates to an afterburner oil supply device. The oil supply device comprises an oil supply main body, a fuel oil flow channel is formed in the oil supply main body and comprises two or more fuel oil flow channel sections which are sequentially communicated, an inlet of one fuel oil flow channel section is communicated with an oil supply pipeline, a plurality of oil spraying holes are formed in the oil supply main body, and the oil spraying holes are communicated with the fuel oil flow channel sections. The fuel injection holes are communicated with the corresponding fuel runner sections; the fuel oil supply assemblies are in one-to-one correspondence with the fuel oil flow channel sections, and all the fuel oil supply assemblies are arranged in the corresponding fuel oil flow channel sections respectively. The radial partition oil supply and combustion requirements of the afterburner can be met, and better afterburner oil-gas mixing and combustion effects are provided; and the structure design is more flexible, and finer fuel injection control and a more accurate oil-gas matching effect can be achieved.

The invention discloses a water-air dual-purpose engine. The engine takes air or water as a combustion medium; the engine includes: a medium introduction part for introducing a combustion medium into the engine; the trapped vortex combustion part is used for accommodating the fuel and the combustion medium under the condition that the combustion medium is air, so that the fuel is combusted; the metal powder combustion part is used for accommodating fuel and a combustion medium under the condition that the combustion medium is water, so that the fuel is combusted; and the substance spraying part is used for spraying substances generated by combustion out of the engine so as to generate traction force. According to the water-air dual-purpose engine, the two different propelling modes of turbojet and metal powder water stamping are integrated, the two propelling modes are compatible at the same time according to different environments and working conditions, and the working states are synchronously switched during environment switching so as to adapt to combustion media corresponding to the different environments; therefore, the engine can provide power for the aircraft in different propulsion modes in the air environment and the water environment respectively, and the stability of fuel combustion is kept.

The application discloses a hyperplane climbing track group intelligent optimization method, which comprises the following steps: constructing a hyperplane climbing section dynamics equation, and obtaining to-be-optimized parameters in the hyperplane climbing section dynamics equation; designing a hierarchical cost function considering multiple constraints and turbojet, subsonic ramjet and supersonic ramjet three power mode switching Mach numbers; and optimizing the cost function through a chicken swarm algorithm, thereby completing the hyperplane climbing track group optimization. The hyperplane climbing track parameter optimization is performed through the improved chicken swarm algorithm, the suitable power mode switching Mach number is selected while the complex constraints of the hyperplane climbing section are met, the climbing scheme capable of significantly shortening the climbing time and total fuel consumption is obtained, and the problem that the track is difficult to optimize under the hyperplane cross-power mode and long-time window climbing condition is solved.

1. Name of the product in this design: Thrust Test Platform for Turbojet and EDF Engines. 2. Purpose of this design: This design is used to measure the thrust ratio of the EDF engine thrust test platform. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

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.

The invention discloses a hybrid electric engine using electric supercharging and indirect cooling. The engine is based on a turbojet or turbofan core engine. An electric supercharging indirect cooling device and a turbine power generation device are additionally arranged on a core engine and are installed at the front end and the rear end of the engine respectively. The electric supercharging intercooling device comprises an electric supercharging channel with a contracted flow channel, an electric driving fan is used in the channel for supercharging, the fan is a wide-pressure-ratio working fan, a motor for driving the fan is located in the center of the flow channel at the rear end of the fan, the flow channel is narrowed after the motor passes through the electric supercharging fan, and a compact intercooler is installed on the rear portion of the flow channel. A flange is arranged at the casing behind the intercooler and is connected with a shell of the core engine; the rear-end turbine power generation device is connected with an outlet of the core engine through a flange, the rear-end device is provided with an adjusting device and divides a duct into an inner duct and an outer duct, the inner duct is provided with a turbine, the turbine is connected with a power generator through a force transmission shaft perpendicular to the direction of a flow channel after passing through a direction changing device, and the power generator is installed outside the flow channel of the device.

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 invention discloses a method for analyzing the transient characteristics of multi-ducted engine casings under complex loads, belonging to the field of aero-engine technology. This method analyzes the structure and operation of a multi-ducted variable cycle engine, classifying it into three turbofan modes and one turbojet mode. Based on an aerodynamic thermodynamic configuration model, component-level modeling is performed using MATLAB software, generating component-level modeling data. A common set of working equations is established using the modeling data, and the solution is obtained through iterative solving using the Broyden quasi-Newton method. The ultimate aerodynamic loads of the casing system under typical operating conditions are calculated. Combined with the engine flight envelope, 12 typical altitude and Mach number states are selected to solve for the ultimate operating points and analyze the transient load characteristics. This invention can accurately capture the transient response characteristics of multi-ducted engine casing systems under complex load conditions, improving analysis accuracy and efficiency, providing a theoretical basis for the design optimization and reliability assessment of casing systems, and has significant engineering value.

1. Name of the product in this design: Central Controller. 2. Purpose of this design: To control the operation of a turbojet snowplow and to display real-time dynamic information feedback from the turbojet snowplow. 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 application provides a nuclear energy electric supercharged jet propulsion system and belongs to the field of aviation power. The nuclear power propulsion system of the traditional turbine engine type solves the problems that the working processes of a compressor and a turbine influence each other, the matching of the compressor and the turbine is relatively difficult, the performance of the propulsion system under variable working conditions is poor, and the arrangement of a heat exchanger in a closed cycle nuclear power system is relatively complex and the flow resistance of the heat exchanger is relatively large. The nuclear energy electric supercharged jet propulsion system comprises a regenerator, a cold end inlet connected with an outlet of a helium-xenon compressor, a cold end outlet connected with a cold end inlet of a heater, a hot end outlet of a first heat exchanger connected with a hot end inlet of a fuel heat exchanger, a second heat exchanger, a hot end inlet of the second heat exchanger connected with a circulating working medium outlet of a reactor system, a fuel tank, a discharge port of the fuel tank connected with the cold end inlet of the fuel heat exchanger through a fuel valve, and an engine shell, wherein air from the compressor outlet flows through the first heat exchanger and the second heat exchanger in sequence. The nuclear energy electric supercharged jet propulsion system is mainly used for the propulsion system of aviation equipment.

The present application belongs to the field of optimal control technology, and particularly relates to a combined power boost reusable spacecraft climbing segment trajectory optimization method, aiming at the problem that in the existing trajectory optimization of the climbing segment of the reusable spacecraft, the processing of the thrust is idealized, and the speed improvement effect and the height improvement effect are not matched; on the basis of the classical Gauss pseudospectral method, in order to improve the speed of solving the non-smooth problem, in the polynomial degree and collocation point correction, the adaptive decision method is introduced based on the curvature of the control variable on the time period, the traditional Gauss pseudospectral method is combined with the finite element method, and the method of increasing the interpolation polynomial degree or increasing the time interval is used for correction. Under the premise that the turbojet and ram work together, the distribution mode of the action time and the thrust size of the two is proposed, and the distribution scheme of the combined thrust is given.

A turbojet manned aircraft based on vector control belongs to the field of aircraft. In order to solve the problems of complex attitude adjustment and large amount of calculation in existing manned aircraft. The two vector power units in the present invention are arranged along the x-axis direction and symmetrically installed on the left and right sides of the fuselage, and provide thrust for the navigation and attitude adjustment of the aircraft; the man-machine fixing unit and the fuel tank are arranged along the y-axis direction and are respectively installed on the front and rear sides of the fuselage, and the man-machine fixing unit is fixed on the operator's body to achieve the fixation of the aircraft and the operator; the fuel tank is respectively connected to the two vector power units and provides endurance fuel for the two vector power units; the main control unit is installed on the fuselage 1 and is respectively electrically connected to the two vector power units to achieve the control of the thrust vector of each vector power unit, thereby achieving the control of the thrust vector of the aircraft. The present invention is mainly used for personnel transportation.

The utility model relates to the field of bearing devices, and discloses a special bearing for a low-altitude turbojet aircraft, which comprises an outer ring, a filling port is arranged on the side wall of the outer ring, an oil storage tank is arranged inside the outer ring, second grooves are respectively arranged on two sides of the inner side wall of the outer ring, a plurality of lubricating ports are respectively arranged on the inner side walls of the two second grooves in a circumferential array mode, and the lubricating ports are communicated with the oil storage tank. A plurality of rollers are slidably connected to the inner side walls of the two second grooves correspondingly, a sealing plug is slidably connected to the inner side wall of the filling port, an inner ring is arranged on the inner side wall of the outer ring, and first grooves are formed in the two sides of the side wall of the inner ring correspondingly. According to the special bearing for the low-altitude turbojet aircraft, the two rows of parallel pin rollers are arranged in the outer ring, so that higher rotation precision and lower vibration level are achieved, and the oil storage tank is formed in the outer ring, so that material performance reduction or bearing failure caused by overheating is prevented.

The invention belongs to the technical field of aero-engine testing, and discloses a magnetic levitation supported wide-range high-precision small aero-engine thrust measuring rack. A movable frame module and a fixed frame module of the thrust measuring rack are both of a horizontally-placed flat plate structure, a small turbine jet aero-engine test piece to be measured is fixed to the upper portion of the movable frame module, and the fixed frame module is fixed to a test bench base. The movable frame module and the fixed frame module are supported through four vertical supporting cylinders arranged at the four corners. A pair of vertical floating magnetic steel assembly and fixed magnetic steel assembly is arranged in each supporting cylinder; and a multi-gear range selection module and a multi-gear in-situ calibration module are also fixed on the upper surface of the fixed frame module. The thrust measuring rack is wide in thrust measuring range, large in measuring range ratio, high in measuring efficiency, high in calibration precision, high in calibration efficiency and good in economical efficiency, can meet the thrust measuring requirements of the wide-range small turbine jet aero-engine, and has engineering practical value.

A long-range heavy-lift turbojet-powered manned vertical take-off and landing aircraft layout, comprising: a riding cockpit, telescopic variable-span wings, landing gears, turbojet thrust vectoring lift engine compartments, and a turbojet thrust engine. The riding cockpit, as a structural body, is located at the center of the aircraft; the bottom of the riding cockpit is connected to the telescopic variable-span wings; four turbojet thrust vectoring lift engine compartments are vertically arranged at the front, rear, left and right corners of the cockpit connected to the telescopic variable-span wings; the turbojet thrust engine and an air intake / exhaust duct thereof are horizontally embedded in the middle area between the wings in the front-back direction; and the landing gears are arranged on two sides of the turbojet thrust engine. The telescopic variable-span wings consider the take-off and landing stability and the cruise economy requirements by means of telescopic change; in addition, by additionally providing end plates at wing tips, the cruise flight induced resistance can be reduced, and the wing tips can be prevented from being scratched. The present invention considers heavy-lift / long-range flight capability, controllability and stability, and achieves pilot-aircraft attitude decoupling; and a pilot can control the aircraft attitude on the basis of body sensing, such that the operation requirement for the pilot is low.

The application belongs to the field of turbojet afterburner, and particularly relates to an afterburner oil supply device. The oil supply device comprises: an oil supply main body, an oil flow channel is formed in the oil supply main body, the oil flow channel comprises two or more oil flow channel sections which are sequentially communicated, an inlet of one of the oil flow channel sections is communicated with an oil supply pipeline, a plurality of oil injection holes are formed in the oil supply main body, and the oil injection holes are communicated with corresponding oil flow channel sections; and oil supply assemblies which are one-to-one corresponding to the oil flow channel sections, each oil supply assembly is arranged in a corresponding oil flow channel section. The application can match the radial partition oil supply and combustion requirements of the afterburner, provide better oil-gas mixing and combustion effects of the afterburner, and has a more flexible structure design, so that more fine fuel injection control and more accurate oil-gas matching effects can be realized.

1. Name of the designed product: propeller (turbojet). 2. Use of the designed product: hand propeller for toy kayak. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: perspective view.

The invention provides a deep learning-based turbojet manned aircraft visual positioning method and system, and belongs to the field of aircraft visual positioning. The invention aims to solve the problems of motion blurring of a visual camera and IMU noise time-varying caused by vibration of dozens of or hundreds of Hertz and strong maneuverability of a turbojet aircraft due to acceleration and deceleration and jet coupling of the turbojet aircraft. The method comprises the following steps: extracting point-line features from a left-eye visual image based on a neural network model of point-line joint feature detection, carrying out inter-frame point-line feature matching, judging whether the left-eye visual image is a key frame or not, if so, inputting a right-eye image, and carrying out binocular feature stereo matching; and if not, carrying out position and attitude calculation on the turbojet manned aircraft, and then constructing a factor graph for optimization. According to the method, the binocular image is only adopted in the key frame for estimation so as to ensure the algorithm real-time performance of the turbojet manned aircraft, and estimation is carried out based on the point-line features so as to ensure the high-speed robustness of the turbojet manned aircraft.

A variable cycle engine comprises a supersonic air inlet channel and a low-bypass-ratio turbofan engine, and the rear portion of the supersonic air inlet channel is connected with an adjustable axial symmetry air inlet channel which is composed of an actuating system and an adjusting piece controlled by an adjusting machine in a sealing cover and is not connected with the turbofan engine. During operation after starting, according to the working scene of the engine, an actuating system and an adjusting machine are controlled, and the opening degree of an adjusting piece is changed, so that the area of an opening of an adjustable axial symmetry air inlet channel is increased during takeoff and subsonic flight, the air inlet bypass ratio of the engine is increased, and the engine works in a turbofan state with the maximum bypass ratio; during climbing, acceleration and supersonic flight, the area of an opening of the adjustable axial symmetry air inlet channel is reduced, the air inlet bypass ratio of the engine is reduced, the engine works in a small-bypass-ratio turbofan or near-turbojet state, the performance of the low-bypass-ratio turbofan engine under different working conditions is improved, high thrust and low oil consumption are maintained, and the structure of the engine is not changed.

1. Name of the designed product: toy (turbojet fire engine 8693). 2. Use of the designed product: for toys. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: perspective view.

The invention relates to a turbomachine turbine comprising a casing (12) carrying a distributor (13) extending circumferentially around an axial direction, in which: – this distributor is formed of several bladed sectors (22, 23, 24) each comprising a radially external platform (26, 27, 28) and a radially internal platform with several blades (14) extending radially from the internal platform to the external platform (26, 27, 28); – the casing (12) has an internal groove (29) of revolution, with several distinct ring sectors (32, 33, 34) each engaged in this internal groove (29) and extending radially towards the interior of the casing (12); – each ring sector (32, 33, 34) axially blocks at least one bladed sector (22, 23, 24). Figure for the summary: Figure 5

A propulsion system comprising a turbojet with a fan casing and a central casing, a pylon with an upper spar, a front wall and on either side of a vertical median plane, a fitting rigidly fixed to the rigid structure, a cylindrical pin as one with the fan casing and inserted in a hole of the upper spar, a shackle with at the vertical median plane, an upper articulation between the shackle and the front wall and on either side of the vertical median plane, a lower articulation between the shackle and the central casing, and two reaction rods disposed on either side of the median plane, where each rod is articulated, at a front end, on the central casing, and, at rear end, on the fitting.

An injector for a de-icing device for an air intake of an aircraft turbojet nacelle. The injector including a peripheral member internally defining a passage duct. The peripheral member including a peripheral mouth configured to inject a peripheral hot air flow so as to circulate a flow of fresh air in the passage duct from upstream to downstream. The peripheral member including an inner guide wall located downstream of the peripheral mouth. The peripheral member including a plurality of members for rotating the hot air flow during the injection thereof.

The present application belongs to the field of aero-engine testing technology, and discloses a magnetic levitation supported wide-range high-precision small aero-engine thrust measuring bench. The movable frame module and the fixed frame module of the thrust measuring bench are both horizontally placed plate structures, the movable frame module is fixed with a small turbojet aero-engine test piece to be measured on the top, and the fixed frame module is fixed on the test bench base; the movable frame module and the fixed frame module are supported through four vertical support cylinders arranged at four corners; a pair of vertical floating magnetic steel assemblies and fixed magnetic steel assemblies are respectively arranged in each support cylinder; and a multi-gear range selection module and a multi-gear in-situ calibration module are further fixed on the upper surface of the fixed frame module. The thrust measuring bench has a wide thrust measuring range, a large range ratio, high measuring efficiency, high calibration accuracy, high calibration efficiency and good economy, and can meet the requirements of wide-range small turbojet aero-engine thrust measurement, and has engineering practical value.

The utility model relates to the technical field of nitrogen heating, in particular to an HOT N2 system nitrogen heating body which comprises a vertically-arranged heating unit, a nitrogen channel is formed in the heating unit, a cold nitrogen inlet is formed in the outer side of the top of the heating unit, and a hot nitrogen pipeline is arranged at the bottom of the heating unit. A high-temperature ball valve and a one-way valve are arranged on the hot nitrogen pipeline, a temperature control thermocouple is arranged on one side of the hot nitrogen pipeline and located between the high-temperature ball valve and the heating unit, a turbojet accessory is arranged at the output end of the hot nitrogen pipeline, the one-way valve is located between the turbojet accessory and the high-temperature ball valve, and a temperature measuring unit is arranged on the outer side of the bottom of the heating unit. The one-way valve is used for preventing gas from flowing back to the heating unit. The temperature control thermocouple is installed at the front end of the one-way valve and close to the gas outlet in the bottom of the heating unit, the turbojet accessory and the temperature control thermocouple are separated through the one-way valve and the high-temperature ball valve, poison gas in a pipeline is not prone to backflow and leakage, and the gas leakage risk of the nitrogen heating body is reduced.

The invention provides a high-speed starter generator rotating shaft structure with an energy storage and self-starting structure, which belongs to the field of thermal power devices and comprises a controllable power coupler, a magnetic suspension bearing, a high-speed permanent magnet motor, a turbojet, a heat exchanger and a controller system. The turbojet drives the permanent magnet motor through the transmission shaft, and the motor outputs electric energy. When the control system is switched to an energy storage state, the controllable power coupler is rapidly disconnected, the driving shaft is not connected with the transmission shaft any more, a high-speed motor rotor maintains short-time high-speed idling by means of original kinetic energy, next-time rapid connection and self-starting are facilitated, a magnetic suspension bearing is used in the high-speed motor to rotate a rotating shaft, axial and radial active adjustment of the motor can be achieved, and the service life of the motor is prolonged. And the heat exchanger is arranged at the tail part of the turbojet, so that the heat of the combustion tail gas can be fully utilized, and the power generation efficiency of the high-speed starting generator is improved.

The application belongs to the technical field of engine control, and particularly relates to a starting and accelerating section oil supply method for an aero turbojet and turbofan engine. The method comprises the following steps: S1, acquiring an engine high-pressure conversion speed in real time; S2, when the engine high-pressure conversion speed exceeds a preset ignition speed, and after the engine is successfully ignited, determining an oil supply amount for a first accelerating stage based on an upper limit oil-gas ratio control law; and S3, when the engine high-pressure conversion speed reaches a preset open-closed loop conversion speed, selecting a lower one from the oil supply amount determined based on the upper limit oil-gas ratio control law and the oil supply amount determined based on an acceleration oil supply law, selecting a higher one from the lower selection result and an oil supply amount determined based on a lower limit oil-gas ratio control law, and taking the higher selection result as an oil supply amount for a second accelerating stage. The application can ensure the consistency of ground starting time, and can also ensure the ground starting reliability when there are differences in different atmospheric environments or starter individuals.

1. The name of the design product: multifunctional turbojet snowplow. 2. The use of the design product: for snow removal work on roads. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view.