5919 results about "Nacelle" patented technology

The invention relates to a high voltage overhead transmission line line-inspection unmanned aerial vehicle photoelectric detection device belonging to the technical field of power line inspection. The invention aims at solving the problem of single technology of the existing overhead transmission line line-inspection. The high voltage overhead transmission line line-inspection unmanned aerial vehicle photoelectric detection device mainly comprises an unmanned aerial vehicle, a GPS (global position system) inertial integrated attitude azimuth detection device, a damping device, a rotation detection nacelle, a ground data receiving processor and a controller. The high voltage overhead transmission line line-inspection unmanned aerial vehicle photoelectric detection device is characterized in that the GPS inertial integrated attitude azimuth detection device is arranged at the inner part of the unmanned aerial vehicle; the rotation detection nacelle is hung below the unmanned aerial vehicle by the damping device; a photoelectric stabilized platform is installed in the rotation detection nacelle; flexible combination of any two or more of a visible light camera, an ultraviolet ray imager and a full-digital dynamic thermal infrared imager and a laser ranging device are borne on the photoelectric stabilized platform; and the rotation detection nacelle is provided with a visible window. With the adoption of the high voltage overhead transmission line line-inspection unmanned aerial vehicle photoelectric detection device, a high voltage transmission line can be monitored, and a comprehensive and precise high voltage overhead transmission line line-inspection task is realized by combining interchange among a plurality of sensors.

An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle.

A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.

A wind energy turbine includes a tower, a nacelle rotatably supported by the tower, a rotor rotatably supported by the nacelle, and at least one unit to be cooled and arranged in the tower and / or the nacelle. The unit is adapted to be cooled by a cooling medium flowing in a cooling circuit from the unit to at least one heat exchanger. The at least one heat exchanger is located outside of the tower and / or nacelle and configured to be cooled by ambient air.

A floating wind turbine platform includes a floatation frame (105) that includes three columns (102, 103) that are coupled to each other with horizontal main beams (115). A wind turbine tower (111) is mounted above a tower support column (102) to simplify the system construction and improve the structural strength. The turbine blades (101) are coupled to a nacelle (125) that rotates on top of the tower (111). The turbine's gearbox generator and other electrical gear can be mounted either traditionally in the nacelle, or lower in the tower (111) or in the top of the tower-supporting column (102). The floatation frame (105) includes a water ballasting system that pumps water between the columns (102, 103) to keep the tower (111) in a 10 vertical alignment regardless of the wind speed. Water-entrapment plates (107) are mounted to the bottoms of the columns (102, 103) to minimize the rotational movement of the floatation frame (105) due to waves.

An engine nacelle inlet lip includes both acoustic treatment and electric heating for ice protection. The inlet lip has a composite outer skin and a composite inner skin, with the composite outer skin having at least one integrated heater element embedded in the composite material. An acoustic cellular core positioned between the outer and inner skin acts to attenuate fan noise from the engine. Covering the outer skin and overlying the acoustic core is a perforated erosion shield having a first set of openings that pass entirely thorough its thickness. The composite outer skin includes a second set of openings such that sound waves can pass from an inner barrel portion of the inlet lip through the erosion shield, outer skin, and heater element to the underlying acoustic cellular core.

A wind turbine capable of driving multiple electric generators having a ring or shroud structure for reducing blade root bending moments, hub loads, blade fastener loads and pitch bearing loads. The shroud may further incorporate a ring gear for driving an electric generator. In one embodiment, the electric generator may be cantilevered from the nacelle such that the gear on the generator drive shaft is contacted by the ring gear of the shroud. The shroud also provides protection for the gearing and aids in preventing gear lubricant contamination.

A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area.

A translating cowl composed of two sub-structures forms the thrust reverser for a turbofan engine. The two sub-structures form the rear part of a nacelle, are translatable, and have operative and inoperative modes of operation. The operative mode is used for direct or reverse thrust operation of the engine and the inoperative mode is used for access to the engine.

A tower comprises a base tower member fixed on a base in the ground, a lower tower member hingedly connected at a lower end thereof with an upper end of the base tower member through a hinge and swinging between a lying position and a standing position, a first stage connecting tower member connected at a lower end thereof with an upper end of the lower tower member, a second stage connecting tower member connected at a lower end thereof with an upper end of the first stage connecting tower member, and a third stage connecting tower member connected at a lower end thereof with an upper end of the second stage connecting tower member. Thus formed tower is raised swingingly around the hinge from the lying position to the standing position. A nacelle includes a tower penetrating hole through which the tower vertically penetrates and is formed by a plurality of nacelle sections divisible around the tower penetrating hole. After the tower is built, a plurality of nacelle sections are collected around the tower and are connected with each other while the nacelle is penetrated by the tower. Then, the nacelle is lifted up along the tower in that state and fixed to the top end of the tower.

A VTOL vehicle including a fuselage with two foldable wings, two tiltable nacelles attached to the wings, a vertical stabilizer, a horizontal stabilizer, and two auxiliary thrusters. Each nacelle contains a system of vanes located at the rear opening thereof, and actuators are provided for extending and retracting the vanes in conjunction with nacelle tilting mechanisms to deflect the airflow over a predetermined range of angles from the horizontal. Each nacelle also contains two rotary engines, each of which directly drives a fan. The fans face each other and operate in counter-rotating directions at the same rotational speed. An alternative embodiment includes two additional nacelles attached to the fuselage instead of having the auxiliary thrusters. A redundant computerized flight control system maintains stability of the vehicle as it transitions from one flight mode to another.

A wind turbine with a drive train connecting a drive unit with a generator assembly is provided. The generator assembly includes a first generator with a first stator and a first rotor, the first rotor being directly connected to the drive train, and at least a second generator indirectly coupled to the drive train via a gear box. Further, a drive train assembly, a wind turbine nacelle system, a method for converting rotational energy into electrical energy, a method of building a nacelle and methods of re-equipping a wind turbine are provided.

A self-supporting, submersible generating plant for producing electricity from ocean currents, consisting of two counter-rotating, rear-facing turbines with a plurality of rotor blades extending radially outward from two separate horizontal axis that convey the kinetic energy from the two side-by-side, counter-rotating turbine rotors through separate gearboxes to separate generators that are housed in two watertight nacelles that are located sufficiently far apart to provide clearance for the turbine rotors. The two generators and their gearboxes serve as ballast and are located far below a streamlined buoyancy tank that extends fore and aft above and between them. A combination of a leverage system and a pressure-controlled system adjusts the hydrodynamic lifting forces to maintain constant depths. There are systems to purge the ballast water to facilitate the recovery of both individual submersible power plants and a group of many submersible power plants.

The invention relates to methods of constructing and operating a wind turbine, said methods comprising the steps of lifting a wind turbine nacelle and tower sections with the use of an external lifting system, and using a lifting system to propel said nacelle vertically up and down said tower sections. The external lifting mechanism comprises a guide rail and guide car onto which tower sections are loaded for horizontal movement, a foundation structure joined to a tower section hoist mechanism containing clamps, and a nacelle holding mechanism. A nacelle includes a tower penetrating hole through which said tower vertically penetrates. Tower sections are provided with a plethora of guide rails positioned around said tower extending from the lower end to the upper end of said tower sections, said guide rails contain removable toothed racks meshing with said lifting system to propel said nacelle vertically up and down said tower sections.

A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

This invention is directed to nacelles and nacelle components for use in aircraft engines. The nacelles and components comprise composite material containing carbon fiber. The carbon fiber comprises from 0.1 to 20 percent by weight nanoreinforcement material.

A thermal management system locates a separate engine heat exchanger and generator heat exchanger into an engine nacelle pylon that is split to provide independent control of both a generator cooling circuit and an engine cooling circuit. A variable exhaust nozzle is provided downstream of each heat exchanger as each has different thermal and heat rejection requirements such that intake air is minimized and maximum thrust is produced in response to the current generator load and engine heat rejection.

A wind turbine is provided that minimizes the size of the drive train and nacelle while maintaining the power electronics and transformer at the top of the tower. The turbine includes a direct drive generator having an integrated disk brake positioned radially inside the stator while minimizing the potential for contamination. The turbine further includes a means for mounting a transformer below the nacelle within the tower.

An aircraft engine nacelle comprises: (a) an inlet lip and a skin having internal and external surfaces; (b) a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; and (c) an electrically powered de-icing system located on the external surface of the nacelle skin and in electrical connection to a power source. A method for de-icing and abating noise from an aircraft nacelle comprises: (a) providing a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; (b) providing an electrically powered de-icing system on the external surface of the nacelle skin; and (c) applying an electric current to the electrically powered de-icing system. The nacelle skin may be a perforated skin, and the de-icing system comprises a wire mesh bonded to the external surface of the perforated skin. The method and nacelle permit the use of noise abatement structures such as acoustic panels for noise reduction while advantageously avoiding detrimental high temperatures associated with conventional de-icing systems.

The invention discloses a special photoelectric nacelle of a power patrol unmanned helicopter, which comprises an airborne part and a ground part, wherein the airborne part comprises a fixed part which is positioned in the upper part, a rotatable part which is positioned in the lower part and a servo control assembly; the rotatable part comprises a gyroscope stable rotating tower; the fixed part comprises an electronic control cabin; cables between the electronic control cabin and the gyroscope stable rotating tower are connected by a conducting slide ring which can support the gyroscope stable rotating tower to rotate by nx360 degrees; and the airborne part of the photoelectric nacelle is suspended on the helicopter by a vibration reducing device and communicated with a flight control system of the helicopter. The special photoelectric nacelle is a photoelectric task load with compact structure and high performance, can meet the requirement for remote power patrol, has self-stabilizing function and self-tracing function, can shoot a target to be traced from an image in real time, transmit the target to a ground control vehicle by a radio transmission system on an aerial carrier and is convenient for a patrol parson to directly master the scene condition to improve the efficiency of power patrol.

A wind turbine or rotor load control compensates for moment imbalance in a wind turbine that includes a rotor having at least two variable pitch blades. The apparatus includes a conventional pitch command logic developing a nominal rotor blade pitch command signal and a moment sensor. The moment sensor can be one or more of a nacelle overturning moment sensor, and a turning moment sensor. An output of this is used as a moment signal. Conversion logic is connected to the moment signal with an output of the conversion logic being calculated individual pitch modulation commands for each of the blades. A combining logic is connected to receive the calculated individual blade pitch modulation commands and to receive a nominal pitch command. An output of the combining logic is individual combined blade pitch commands for each of the blades. The individual combined blade pitch commands are generated by modulating the nominal command signal by a respective blade pitch modulation command which includes compensation for instantaneous moment deviations of the wind turbine.

Interior architectural structures and lighting for aircraft, particularly commercial passenger airplanes. Light diffusers and ceiling panels in a “wing-shape” and other secondary panels are utilized to create different interior designs and structures. A permeable secondary panel is utilized in one passenger cabin in order to provide a more private-type space. An enlarged ceiling arch with blended curves forming a “wing-type” configuration provides a more spacious cabin arrangement. Other features include air and light diffusers, passenger service modules, a “shelf”-like configuration and lighting above the airplane entrance / exit door, and bulkheads and monuments positioned at various positions in the cabin.

A wind turbine with a sensor that measures the out-of-plane deflection of the blades and a controller that uses the signal from the sensor to determine the risk of a tower strike. The controller takes any necessary action to prevent a tower strike when it determines that the risk of a strike is high. The sensor can include strain gages or accelerometers mounted on the blades or it can include a fixed sensor mounted on the side of the tower to measure tower clearance as the blade passes by. The control action taken can include pitching blades, yawing the nacelle, or stopping the turbine. The controller is preferably a fuzzy logic controller.

Apparatus (20) for aerial transport includes a cabin (24) for containing a load and one or more cables (30), attached so as to suspend the cabin below a hovering aircraft (22). An elevator mechanism (32) is coupled to raise and lower the cabin on the one or more cables. A control unit (56) is coupled to receive an input from at least one cabin sensor (38, 40, 48, 50, 60, 62) that is indicative of the disposition of the cabin relative to the terrestrial target (26), and to control the elevator mechanism responsively to the input so as to bring the cabin into with a predetermined position relative to the terrestrial target while the aircraft is hovering.

A nacelle (55) for a gas turbine engine (10), the engine (10) comprising accessories (34) mounted to a fan casing (28) and a core engine (9), the nacelle (55) substantially surrounds the engine (10) and comprises an intake (12) and a thrust reverser unit (31). The thrust reverser unit (31) is formed by two generally C-shaped portions (31a, 31b). The thrust reverser unit (31) is openable to provide access to the accessories (34) and the core engine (9). The nacelle (55) further comprises a fan containment casing (33) that is integral with the intake (12).