3309 results about "Nacelle" patented technology

A wind energy plant with a nacelle, a rotor, which features at least one rotor blade adjustable in its blade pitch angle, a central control device for controlling the wind energy plant and a control unit disposed in the rotor for controlling the blade pitch angle of the at least one rotor blade, wherein the central control device and the control unit in the rotor can exchange data with each other via a data link, which comprises at least one first sending and receiving device at the nacelle side and at least one second sending and receiving device at the rotor side, wherein a wireless network connection with a safety-oriented communication protocol is provided between the at least one first sending and receiving device and the at least one second sending and receiving device, and that one monitoring- and communication device at a time is associated to the first and / or the second sending and receiving device, which can monitor the function of the sending and receiving device and initiate a predetermined action in the case of an error.

An aircraft thermal management system comprising a high temperature loop and a low temperature loop. The high temperature loop is configured to manage a temperature of a fuel cell stack in a nacelle using a nacelle heat exchanger. The low temperature loop is configured to cool a number of heat loads in a nacelle using a heat capacity of liquid hydrogen.

The invention discloses an energy-saving control method and system for an airplane ground air conditioning unit, and belongs to the technical field of air conditioning system energy saving.The method comprises the steps that internal and external environment parameters of a cabin are collected in real time, temperature prediction is conducted based on the internal and external environment parameters of the cabin, and a predicted temperature change curve is constructed; running state parameters of the aircraft ground air conditioning unit are called, dynamic energy-saving control is carried out in combination with the predicted temperature change curve, and an energy-saving control strategy is formulated; cabin internal variable parameters are introduced to optimize the energy-saving control strategy, and an optimized energy-saving control instruction set is generated; and the optimized energy-saving control instruction set is executed for cooperative driving, cooling circulation is conducted according to the cooperative driving result, and self-adaptive energy-saving control over the aircraft ground air conditioning unit is achieved. The technical problems of high energy consumption, unstable temperature control and low equipment operation efficiency caused by the lack of precise response capability of an air conditioning unit to dynamic changes of internal and external environments of a cabin in the prior art are solved.

An aircraft includes a battery pack mounted inside the aircraft, a vent coupled between the battery pack and a surface of the aircraft to at least partly define a vent path between the battery pack and the surface of the aircraft, and a burst membrane located in the vent path. The vent may be coupled to a rear upper portion of a wing or to an outboard side of a nacelle. The aircraft may also include a flexible coupling between the vent and the surface of the aircraft. The aircraft may also include a fairing over a vent outlet to provide a smooth surface for the vent outlet. The battery pack may include battery modules and an enclosure, the battery modules and the enclosure defining paths along which discharge from a thermal event can flow towards the vent.

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

The invention belongs to the technical field of wind tunnel tests, and particularly relates to a precession simulation device for a spiral flutter wind tunnel test. According to the invention, the design problem of the rotor craft spiral flutter wind tunnel test device is solved, and the key influence parameters and influence rules of the spiral flutter of the aircraft are researched by designing the precession motion simulation device of the rotor craft. Rotation of the rotor wings can be realized in the wind tunnel, and the rotating speed of the rotor wings is adjusted through the motor. Meanwhile, pitching and deflection modal decoupling of the rotating shaft of the rotating system is achieved, and pitching and deflection modal frequencies are independently adjustable; meanwhile, the axis of the pitch axis and the axis of the yaw axis coincide, so that pitching and yaw freedom degree coupling precession motion can be achieved under the effect of gyroscopic moment. Meanwhile, nacelle rotating mass rotational inertia, nacelle weight and mass center position adjustment can be achieved; and finally, the rotating speed of the rotating mass such as the rotor wing and the propeller hub can be adjusted through a speed adjusting motor, matching of the rotating speed and the incoming flow speed is guaranteed, and the spiral flutter state is achieved.

The invention discloses a high-integration-level and efficient-cooling external rotor motor ducted fan system, which belongs to the technical field of ducted fans and comprises a motor stator winding and a fan external rotor integrated part integrally formed by fan blades and a motor external rotor turntable, the integrated shell is integrally formed by a motor inner stator sleeve, a ducted nacelle, a motor controller main shell and a plurality of groups of ducted stationary blades; a cooling structure is mounted on the integrated shell; a motor stator winding is fixedly connected to the outer wall of one end of the integrated shell, the front flow guide cover is fixedly connected to the fan outer rotor integrated part, and the rear flow guide cover is installed at the other end of the integrated shell. And the integrated shell is rotationally connected with the fan outer rotor integrated piece. The system is low in noise, high in integration level, high in system reliability, high in system cooling efficiency, high in power level compatibility and high in expandability.

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

A heat exchanger system for an aircraft comprises nacelle having an inlet and an outlet, a nacelle heat exchanger within the nacelle, and a fan system within the nacelle. Air flows into the nacelle through the inlet and out of the nacelle through the outlet. The nacelle heat exchanger is configured to transfer heat away from a coolant using the air in an airflow to the nacelle heat exchanger. The fan system is configured to increase the airflow to the nacelle heat exchanger.

A manned aircraft having wing parts, an internal combustion engine which is connected via a shaft to a left thrust nacelle and to a right thrust nacelle, which are pivotable from a vertical position for a hovering flight phase into a horizontal position for the forward flight phase, and having a left thrust unit and a right thrust unit which are driven by electric motors, and having a control unit which carries out a moment-dynamic flight control and which controls the thrust units to generate thrust for the hovering flight phase and at least partially stops them for the forward flight phase.

An aircraft propulsion assembly that has a nacelle with a front opening and a rear opening, a propeller driven by an electric motor, a fuel cell supplying the electric motor with electric current, an inner channel arranged in the nacelle between the front opening and the rear opening. The electric motor and the fuel cell are disposed in the inner channel. A motorized fan is arranged at the rear part so as to draw in the air present in the inner channel and expel it to the outside through the rear opening. A control unit controls the motorized fan. With such an arrangement, the outside air cools the inside of the nacelle and the dihydrogen is evacuated.

The invention discloses a high-heat-dissipation integrated ducted fan electric propulsion system, which belongs to the technical field of ducted fans and comprises a motor controller, a motor, a motor front bearing, a motor rear bearing, a front fairing, a rear fairing and an integrated fan rotating shaft integrally formed by fan blades and a motor rotating shaft. The integrated nacelle motor shell is integrally formed by a motor shell, a ducted nacelle and a plurality of groups of ducted stationary blades; cooling devices are mounted on the motor shell and the motor controller; the cooling device comprises a cooling water channel and a water cooling cavity; a cooling water channel is arranged on the motor shell; the motor controller is provided with a water cooling cavity, and the cooling water channel is communicated with the water cooling cavity; the front fairing is connected to the left end of the integrated fan rotating shaft, and the rear fairing is connected to the right end of the motor controller. The integrated level is high, the size and the weight are reduced by reducing connecting parts, and the power density is high; the system reliability is high; the system cooling efficiency is high; and the power level compatibility and the expandability are high.

The invention belongs to the technical field of engine nacelle part production, and particularly relates to an intelligent welding system and method for an engine nacelle combined type air inlet fairing. An inner spoiler moving groove and an outer spoiler moving groove are machined in the air inlet duct casting blank borne by the air inlet duct positioning assembly through the inner cutting assembly and the outer cutting assembly correspondingly, and the air inlet duct casting blank is formed into an air inlet duct component; a first clamping feeding assembly, a second clamping feeding assembly, a third clamping feeding assembly and a fourth clamping feeding assembly are used for feeding an inner reinforcing part, a heating part, a noise reduction and sound absorption part preassembled with a spoiler assembly and an annular cover plate into a cavity of the air inlet channel component, and the fed parts are welded and fixed into the cavity of the air inlet channel component through a welding assembly; in this way, intelligent welding and assembling operation of the combined air inlet fairing can be achieved, and the combined air inlet fairing has the advantages of being high in structural strength, good in noise reduction and sound absorption effect and capable of achieving automatic deicing of the lip and air inlet distortion control.

The utility model discloses an engine nacelle, which is applied to the field of aircraft manufacturing, is used for improving the structural strength of an aircraft engine nacelle, and comprises a front firewall, a rear firewall, an upper firewall, a front section skin, a middle section skin, a rear section skin and a mounting frame, a second through hole is formed in the rear firewall; the upper firewall is arranged between the front firewall and the rear firewall, the front end of the upper firewall is connected with the front firewall, the rear end of the upper firewall is connected with the rear firewall, the mounting frame and the U-shaped reinforcing beam are both of a U-shaped structure and are both located on the front side of the front firewall, and the mounting frame is arranged above the U-shaped reinforcing beam; the rear end of a front-section lower wall plate of the front-section skin is connected with the U-shaped reinforcing beam; the front ends of a middle-section left wall plate, a middle-section right wall plate and a middle-section upper wall plate of the middle-section skin are connected with the mounting frame; and the outer sides of the upper firewall, the front firewall and the rear firewall are coated with the middle-section skin.

The invention relates to a wind power cabin equipment quality evaluation and maintenance decision-making method based on reinforcement learning, and belongs to the field of wind turbine generator operation and maintenance. According to the method, the state degradation model of the wind power cabin is established by using the Markov decision process, and the state transition probability is estimated in combination with the dynamic integrated probabilistic neural network, so that the prediction accuracy is improved. Weibull distribution parameter estimation is carried out on the fault data of the subcomponents of the wind turbine cabin through the grey model, life reliability analysis of the components is completed, then a reliability function of the wind turbine cabin is obtained, and equipment quality evaluation is achieved. According to the method, a maintenance method combining post maintenance and opportunity maintenance is adopted, an objective function of a maintenance decision model is established according to a component reliability function and a maintenance cost model, and an optimal maintenance strategy is solved by using an AD3QN algorithm, so that the minimum maintenance cost is realized, and the operation efficiency and economic benefits of the wind power plant are improved.

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3 that is defined byVGVG⁢B.VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes the gearbox assembly, a fan, a combustor that generates combustion gases, a turbine, a nacelle that surrounds the fan, and a steam system. The combustor and the turbine define a core air flowpath. Core air flows through the core air flowpath. The steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath to add mass flow to the core air. A bypass ratio of the gas turbine engine is in a range of 18:1 to 100:1.

The invention provides a vacuum bag packaging method for composite material forming, and belongs to the technical field of aero-engine nacelle composite material autoclave forming. After the prepreg is laid, a layer of strippable cloth is laid on the prepreg; air-permeable felt strips fixed to the upper surface of the mold are arranged between the side edges of the prepreg and the air exhaust holes, air-permeable wool top felts are arranged on the two sides of the prepreg, the length direction of the air-permeable felt strips extends in the length direction of the prepreg, and the upper surfaces of the air-permeable felt strips and the side faces, back to the prepreg, of the air-permeable felt strips are covered with first adhesive demolding cloth; the upper surface of the mold is covered with a vacuum bag, the vacuum bag is covered with prepreg, breathable felt strips, strippable cloth and air exhaust holes, and the surface of the vacuum bag is connected with the upper surface of the mold in a sealed mode; and placing the mold in an autoclave for molding. By means of the treatment scheme, the maintenance cost of the mold air exhaust hole is reduced.

The invention relates to the technical field of welding clamps, in particular to a cabin equipment outfitting welding clamp and a clamping method thereof.The cabin equipment outfitting welding clamp comprises a guide rail, two sliding blocks capable of synchronously and oppositely moving are slidably clamped to the guide rail, a second limiting rod is arranged on the guide rail, a sliding plate is slidably clamped to the sliding blocks, and the second limiting rod is movably sleeved with the sliding plate; an elastic receding assembly is arranged between the sliding block and the sliding plate, the sliding plate can slide on the sliding block when pushed by external force through the elastic receding assembly, a sleeve arranged on the second limiting rod in a sleeving mode is embedded into the inner side of the sliding plate in a clamped mode, and the sleeve and the second limiting rod are matched through a first linkage mechanism. The sleeve rotates when sliding on the second limiting rod; according to the thin-wall fitting-out pipe fitting clamping device, radial and axial synchronous constraint of the thin-wall fitting-out pipe fitting can be achieved, the thin-wall fitting-out pipe fitting is not prone to loosening or deformation in the welding process, meanwhile, coaxial welding is kept, and the welding seam quality is improved.

A vertical take-off and landing (VTOL) aircraft provides transportation to users of a network system. The network system may include multiple aircraft or other types of vehicles to provide multi-model transportation. An aircraft may include a fuselage, a truss coupled to the fuselage, and multiple distributed electric propellers coupled to the truss. The distributed electric propellers may be positioned on at least two different planes. The fuselage may include a cabin having one or more seats for the passengers arranged in a configuration that has a compact footprint, provides legroom, provides visibility to surroundings of the aircraft, or facilitates convenient ingress or egress of passengers. The aircraft may open a port cabin door and starboard cabin door for simultaneous ingress or egress of passengers.

The invention discloses a vehicle-mounted unmanned aerial vehicle cabin and a vehicle, the vehicle-mounted unmanned aerial vehicle cabin comprises a shell, the shell comprises an outer shell and an inner plate, the inner plate is located below the outer shell, a drainage channel is formed between the inner plate and the outer shell, the inner plate is provided with a drainage port communicated with the drainage channel, and the outer shell is provided with an air inlet opposite to the drainage channel; the air inlet assembly is located at the air inlet and connected with the shell. According to the vehicle-mounted unmanned aerial vehicle cabin, liquid entering through the air inlet can flow into the drainage channel and is drained out of the vehicle-mounted unmanned aerial vehicle cabin through the drainage opening of the drainage channel, and therefore the liquid is prevented from invading the internal structure of the vehicle-mounted unmanned aerial vehicle cabin. Meanwhile, the air inlet assembly is located at the air inlet and connected with the shell, so that the air inlet assembly prevents part of liquid from invading the internal structure of the vehicle-mounted unmanned aerial vehicle cabin through the air inlet, and the vehicle-mounted unmanned aerial vehicle cabin better gives consideration to the waterproof performance and the heat dissipation capacity.

The invention discloses a wind turbine blade flutter characteristic calculation method based on joint simulation, and relates to the technical field of wind power generation. The method comprises the following steps: S1, reading structural body data of a wind turbine blade, and extracting parameters such as a spanwise position, an airfoil profile coordinate and aerodynamic characteristics of the blade; s2, full-automatic parametric modeling of the blade is achieved through a parametric modeling tool, and a related input file is generated; s3, based on an unsteady blade element momentum theory, aerodynamic force and torque responses of the blade at different spanwise positions are calculated step by step; s4, standardized calculation steps are packaged through a programmed method, personal errors are reduced, and calculation efficiency is improved; s5, designing a cabin interface, a tower interface and a floating platform interface, and realizing flexible data interaction and expansion among modules; and S6, dynamic response analysis is combined, and flutter characteristics of the wind turbine in a complex load environment are simulated. According to the method, the calculation process of wind turbine blade flutter characteristic analysis is accelerated, and the analysis precision and the calculation efficiency are improved. Through programmed and modular design, the flutter simulation of the wind turbine blade can be quickly and accurately completed, and a scientific basis is provided for structural optimization of the blade and safety design of a wind turbine system.

A guide vane assembly for a nacelle of a gas turbine engine includes a forward vane and an aft vane. The aft vane is located aft of the forward vane and forward of a plurality of fan blades. The forward vane defines a fixed pitch angle and the aft vane is movable between a first pitch angle and a second pitch angle.

A turbofan engine defining an axial direction and a longitudinal centerline along the axial direction is provided. The turbofan engine includes: a fan section having a fan, the fan comprising a plurality of fan blades; a turbomachine drivingly coupled to the fan, the turbomachine comprising a compressor section with a low pressure compressor, a turbine section with a low pressure turbine, a reduction gearbox, and an outer casing, the low pressure turbine drivingly coupled to the low pressure compressor across the reduction gearbox; an outer nacelle surrounding the fan and at least a portion of the turbomachine; an outlet guide vane extending between the turbomachine and the outer nacelle at a location downstream of the plurality of fan blades, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip.

An aircraft seat connector for mounting an aircraft seat to a mounting rail provided at a floor of an aircraft cabin comprises: a seat connection element for being mounted to the aircraft seat; and a base element for being mounted to the mounting rail. The base element comprises a seat coupling portion which is configured for receiving a mating portion of the seat connection element in at least two different spatial orientations, with the seat coupling portion thus allowing for arranging the seat connection element on the base element in at least two different spatial orientations.

A wind turbine installation system and a method for installation of an offshore or onshore wind turbine including a tower is provided. The system includes at least one winch and a winch control system, the winch has a winch motor and a bi-directional rotational spool with a strap, wherein the winch is placed on an installation vessel or on the ground, wherein said the strap is provided with attachment for attachment to a tower, a nacelle or a fundament of the wind turbine and for applying a controlled pull on the tower, nacelle or fundament. A control system is controllably connected to the winch motor for controlling spool rotation in order to induce counter movements to the registered oscillations occurring in the tower and thereby stabilize the tower.

The invention provides a blade clearance value and imbalance real-time monitoring method and device based on an RTK technology, and relates to the technical field of wind generating set monitoring. The method comprises the following steps: acquiring position coordinates and elevation information of RTK monitoring equipment on the top of a fan cabin and position coordinates and elevation information of RTK monitoring equipment on three blades of a fan by adopting an RTK technology; analyzing the correlation among the clearance distance, the elevation difference and the horizontal distance in the rotating process of the three blades of the fan; according to the mutual relation of the clearance distance, the elevation difference and the horizontal distance, the clearance distance of the three blades of the fan in the rotating process is calculated through a sampling statistics mechanism method; and according to the clearance distance, the balance state among the three blades of the fan is obtained. According to the invention, the clearance distance of the blade at each rotation position and the balance state of the impeller can be monitored in real time.

The invention discloses a floating type offshore wind turbine aerodynamic load calculation method based on a frequency domain method. The method comprises the steps that a state derivative is determined based on a blade element momentum theory quasi-steady-state assumption, and a dynamic inflow model is used for correction; establishing a pneumatic-elastic coupling two-degree-of-freedom linear dynamic model; establishing a wind wheel kinetic model; establishing a control model according to a floating type offshore wind turbine pitch angle control strategy, a torque control strategy and a floating body motion feedback control strategy; based on the pneumatic-elastic coupling two-degree-of-freedom linear dynamic model, the wind wheel dynamic model and the control model, pneumatic additional mass and pneumatic additional damping are obtained; pneumatic exciting force acting on the hub when the position of the cabin is fixed is obtained; and based on the pneumatic additional mass, the pneumatic additional damping and the pneumatic exciting force, an overall linear dynamic model of the fan is established and solved, and overall response is obtained. According to the method, the calculation result precision can be improved while the calculation efficiency is ensured, and a technical support is provided for accelerating the simulation efficiency of the offshore wind turbine.

The invention belongs to the technical field of aircraft design, and particularly relates to an integrated tilting power system integrated with hydrogen fuel cell motor electric control and an aircraft. Comprising a tilting mechanism connected with a machine body; the integrated motor and controller is fixedly connected with the tilting mechanism and located at the end, close to the upstream of the incoming flow, of the tilting mechanism; the tilting rotor wing is mounted at one end, close to the incoming flow upstream, of the integrated motor and controller; the hydrogen fuel cell is fixedly connected with the tilting mechanism and is positioned at one end, close to the downstream of the incoming flow, of the tilting mechanism; the nacelle shell wraps the tilting mechanism, the integrated motor, the controller and the hydrogen fuel cell; the nacelle outer heat dissipation fins wrap the nacelle in the circumferential direction; and the tilting mechanism, the integrated motor and controller and the liquid cooling radiating pipeline of the hydrogen fuel cell exchange heat with the radiating fins outside the nacelle.

Wind turbine installation method the installation method including: providing a nacelle (2) at a wind turbine erection site, said nacelle (2) comprising: a main unit (20), arranged to be connected to the wind turbine tower (3), and configured for housing a rotor-supporting assembly of the wind-turbine: at least one auxiliary unit (21, 22) housing an operative component (34) forming part of the power conversion assembly, wherein: the main unit (20) and the auxiliary unit (21, 22) are separate units configured to be connected by a unit fixation structure at an interface, and wherein the operative component (34) is supportable directly on the main unit (20), said method further including: receiving a said main unit (20) and an auxiliary unit (21, 22) and an operative component (34) to said site of erection of the wind turbine, attaching to said main unit (20) the said auxiliary unit (21, 22) and said operative component (34). and attaching a lifting yoke (50) to the main unit (20) and hoisting the main unit (20) together with the auxiliary unit (21, 22) by means of a crane attached to the lifting yoke (50), wherein the auxiliary unit (21, 22) is supported and lifted by the main unit (20) during the hoisting, and installing the main unit (20) and the attached auxiliary unit (21, 22) at the tower top.

The invention discloses a six-degree-of-freedom pneumatic load simulation system of an offshore floating type fan and a control method, and belongs to the field of offshore wind power generation technologies and fan test equipment. The simulation system comprises a wave flow simulation device installed at the forefront of a wave pool, a floating platform fixed in the middle of the wave pool through a mooring anchor chain, a tower installed on the floating platform, a cabin installed at the top of the tower, a six-degree-of-freedom load sensor installed between the cabin and the tower, and a fixed support installed at the right front of the cabin. A plurality of groups of variable-speed fans are mounted on the fixed bracket and are connected with the controller through a brushless electronic speed regulator mounted in the cabin; a crane is installed on the upper portion of the wave pool, a data acquisition box, a visual camera and an upper computer are installed on the top of the crane, the visual camera is connected with the data acquisition box through a synchronous triggering device, and the data acquisition box is connected with the upper computer. According to the method, the high-precision six-degree-of-freedom pneumatic load can be generated, and the dynamic performance of the marine floating type fan can be accurately evaluated.