Abstract: A wind turbine for generating electrical power, the turbine having a rotor assembly comprising a hub, a rim and a plurality of blade members extending between the hub and rim, and at least two anemometers mounted at stationary locations relative to the rotor assembly or on the rotor assembly itself, wherein the pitch of individual blade members is adjustable in response to differences in wind speed detected by the anemometers as the rotor assembly rotates.

Abstract: A pressure relief device includes a main body and at least two air control units. The main body has at least one passage therein and two outlets formed at upper and lower ends of the passage. A lid is pivotally connected to each of the outlets. The two air control units are each disposed in the passage close to the lid. An air control device drives the air control units to open/close the lid which is adapted to open/close the passage.

Abstract: To provide a horizontal axis wind turbine capable of reducing flutter, and by extension, reducing the load on the wind turbine, without controlling the yaw, regardless of the direction of the wind relative to the nacelle. When the wind speed is above a specific value, the yaw angle of the nacelle is held constant, the blade pitch angle is controlled according to the yaw angle Y of the wind direction relative to the nacelle, and the rotor is allowed to rotate freely. Even when the yaw angle of the nacelle is held constant, allowing the rotor to rotate freely makes it possible to reduce the load by avoiding flutter.

Abstract: Method for the emergency braking of a wind power plant, in which at least one rotor blade of the wind power plant is adjusted into its feathering position, wherein a first phase, in which the at least one rotor blade is adjusted with a first speed, and a second phase, in which the at least one rotor blade is adjusted as of a predetermined first blade pitch angle with a second speed, which is increased until a maximum speed is reached and/or until a second determined blade pitch angle is reached.

Abstract: A wind power generation system includes a wind turbine at a wind turbine location, a measuring device for providing a wind condition signal at a test location, a sensor for providing a wind condition signal at the wind turbine, and a controller. The controller is configured for receiving the wind condition signals, using a wind correlation database and the wind condition signal at the test location for providing a wind condition estimation at the wind turbine location, obtaining a difference between the wind condition signal at the wind turbine location and the wind condition estimate at the wind turbine location, and using the difference for adjusting the wind condition signal at the wind turbine location.

Abstract: Operations of a turbine to generate energy from a relatively slow fluid flow, such as wind and water, are described. The turbine has a plurality of foils rotating about a central axis at a rotational velocity, each of the foils having a length and a foil axis parallel to the length and the central axis with each of the foils rotatable about its foil axis. From determinations of a velocity of the fluid flow, and angular location of each foil and the rotational velocity about the central axis, an attack angle of each foil is controlled with respect to the direction of fluid flow about the foil axis responsive to the velocity of the fluid flow, the angular location of the foil and the rotational velocity as the foil rotates about the central axis.

Abstract: An apparatus and method for producing high output and low cost/time, sustainable energy (e.g., wind or water) via natural currents that is environmentally friendly and includes a gravity-assisted equalizing control system is provided. Wings with a large surface area can be included in the design, as well as an optional counterbalance system that synchronizes the wings' position and speed with a mechanical leverage point on the body of the device. When a fluid flows past wings of the device, the fluid flow induces motion in the wings, which causes a shaft to move, creating torque at the generator. The outcome is a coordination of harmonizing the wings pitch angle to the natural frequency of a fluids specific velocity. The device can adapt itself to the velocity of the surrounding fluid through a rotational sweeping control system that produces a more streamlined profile to maximize reliability.

Abstract: A turbine for use with a turbine generator, the turbine including at least one turbine blade for positioning in a flowpath, a hub mounting the at least one turbine blade, and a rotatable shaft in operational communication with the hub via a hinge assembly, an axis of the hub being independent of an axis of the shaft. The hinge assembly is disposed between the shaft and the hub and configured to adjust an angle therebetween. A controller assembly is configured to adjust at least one operational characteristic of the hinge assembly during turbine operation. In one embodiment the operational characteristic is a teeter angle of the hinge assembly. In one embodiment operational characteristic is a stiffness or damping force. Methods for using and controlling a fluid turbine are also disclosed.

Abstract: Described herein is an improved wind turbine with a dynamic blade configuration.

Abstract: A system for determining wind turbine tower base torque loads including a controller configured to determine a torque load of a base of a tower of a wind turbine according to a computation of an effective height of the wind turbine multiplied by a wind force upon a rotor of the wind turbine, and generate a control signal representing the torque load. A method for determining wind turbine tower base torque loads including determining a torque load of a base of a tower of a wind turbine according to the foregoing computation, and generating a control signal representing the torque load.

Abstract: A method for operating a wind power plant, in which the wind power plant (10) has a multiplicity of components, but at least one rotor (18) with at least one rotor blade (22) and a generator for converting the mechanical energy of the rotor (18) into electrical energy and possibly a tower (14) on which the rotor (18) is arranged. Counterforces which counteract forces acting on the component (22), particularly wind loads, can be introduced into at least one component during the movement of rotation of the rotary blade (22).

Abstract: A vertical-axis wind turbine which has a central rotary tower upon which are fixed substantially vertical blades. The blades are capable of rotating and moving radially relative to the central tower, the movement of each blade being independently controlled based on the conditions to which it is constantly subjected so as to optimize the overall performance of the wind turbine.

Abstract: A wind turbine having at least one rotor blade attached to a rotor hub is provided, wherein the wind turbine further includes at least one sensor disposed at or near the rotor blade, the sensor being adapted to detect an aerodynamic condition of the rotor blade.

Abstract: A blade-pitch-angle control device includes a memory unit in which predetermined parameters that affect the load fluctuation of blades, azimuth angles, and pitch-angle command values are stored in association with each other; an azimuth-angle detecting unit that detects the azimuth angle of each of the blades; a parameter-detecting unit that detects the predetermined parameters; a command-value receiving unit that receives pitch-angle command values for each of the blades from the memory unit, the pitch-angle command values being selected on the basis of the azimuth angle of each blade detected by the azimuth-angle detecting unit and the predetermined parameters detected by the parameter-detecting unit; and a pitch-angle-control command-value generating unit that generates pitch-angle-control command values for individually controlling the pitch-angle of each blade on the basis of the pitch-angle command values and a common-pitch-angle command value.

Abstract: A horizontal axis wind turbine includes: a rotor having a hub and at least two or more blades; a nacelle for pivotally supporting the rotor through a rotating shaft connected to the hub; a tower for supporting the nacelle; and an independent pitch control unit capable of independently controlling pitch angles of the blades, respectively, wherein the independent pitch control units control the pitch angles so that all the blades are made in a full feather position in case of a wind speed not less than a predetermined value, and subsequently controls the pitch angles of the respective blades so as to be sequentially reversed one by one, and further subsequently, carries out control so that the wind turbine idles in an all-blade negative feather position where the pitch angles of all the blades are reversed.

Abstract: The transducers are incorporated in or laminated to wind blades and electrically connected to a self-powered electrical circuit. The transducers in combination with the self-powered electrical circuit improve the wind blades' response to changing wind conditions by reducing loads, at least until the turbines pitch axis system can alter the lie of the blades. Thus, when there is a change in wind conditions, the resultant twisting or bending of the wind blade during the impact of the wind (gust) on the wind blade is used to extract energy from the transducers. This energy is then transferred to the electrical circuit which in turn sends a signal back to the transducers to actuate them so as to resist the imposed load.

Abstract: A method for limiting loads in a wind turbine by using measured loads or wind speed to increase the minimum pitch angle for extended periods. The minimum pitch angle will be allowed to relax down to the default when load excursions diminish. The method will allow turbines to capture more energy by operating in higher wind speeds and/or utilizing larger rotors without additional loss of fatigue life.

Abstract: Condition-based monitoring functionality using sensors that monitor wind turbine component movement. A main shaft flange displacement sensor system can be used to provide signals used to perform fatigue assessment of the wind turbine rotor blades as well as drive train components. Output signals from the main shaft flange displacement sensor system are used to perform fatigue assessment, failure trending, diagnostic analysis, etc.

Abstract: The claimed and disclosed systems and methods are directed to providing measures and possible ways of protecting a wind power installation in a wind park from wind conditions that may potentially cause damage or even result in the failure of at least one of the wind power installations. The wind is monitored in at least one region of the wind park and based on the monitored wind readings; the rotor blades of at least some of the wind power installations may be adjusted to avoid detrimental damage thereto. This protection may be balanced with contemporaneously determining whether other, non-impacted wind installations can be contemporaneously operated at or near their maximum possible energy yield. At least one wind power installation may have a SODAR system mounted thereon to detect the wind in a region of the wind power installation.

Abstract: A fan and a fan blade are provided for allowing airflow through the fan blade in a fan failure condition. The fan blade includes a peripheral member defining an opening. A flexible cover member is attached to the peripheral member for covering the fan blade opening during normal operation of the fan. The flexible cover member is hingeably attached to the peripheral member for movement away from the peripheral member enabling airflow through the fan blade opening in a fan failure condition.

Abstract: Device and system for the automatic control of a helicopter. The automatic control device (6) comprises a vertical objective law (A) in respect of the pitching axis, which automatically determines a control command (UT1) for operating the tilting of the disk of main rotor of the helicopter, a speed limitation law (B) for limiting the airspeed of the helicopter with respect to at least one limit value, detection means (10) for automatically detecting whether the airspeed reaches the limit value, and toggling means (11) for, in order to select the objective law (A, B) whose control command (UT1, UT2) is used for the pitching axis, automatically toggling from the first law (A) to the second law (B), when the detection means (10) detect that the airspeed has reached the limit value.

Abstract: A windmill includes a freely rotatable revolution shaft, a plurality of pairs of pivotal support rods provided at the revolution shaft, and wind receiving blades respectively and rotatably set between the pivotal support rods with wind receiving blade shafts. The windmill is applied to the driving of a lifting pump, a generator and the like by employing revolution driving force. An anemometer/anemoscope measures wind velocity and direction. A servo motor controls the direction of the wind receiving blades based on the detected velocity and direction. Various methods of control are also provided.

Abstract: Method and apparatus for controlling an aircraft engine with a single, manually-operable lever includes structure and function for generating a pilot thrust command from the single lever. A processor is coupled to the single lever and (i) receives the generated pilot thrust command, (ii) receives a plurality of detected ambient air flight conditions, (iii) receives a plurality of detected engine performance parameters, (iv) determines first and second engine control commands based on the received pilot thrust command, the detected ambient air flight conditions, and the engine performance parameters, and (v) outputs first and second output signals respectively corresponding to the first and second engine control commands. Preferably, the engine control commands comprise propeller RPM and engine inlet manifold air pressure commands, and the detected ambient air flight conditions comprise air speed and altitude.

Abstract: Method and apparatus for controlling an aircraft engine with a single, manually-operable lever includes structure and function for generating a pilot thrust command from the single lever. A processor is coupled to the single lever and (i) receives the generated pilot thrust command, (ii) receives a plurality of detected ambient air flight conditions, (iii) receives a plurality of detected engine performance parameters, (iv) determines first and second engine control commands based on the received pilot thrust command, the detected ambient air flight conditions, and the engine performance parameters, and (v) outputs first and second output signals respectively corresponding to the first and second engine control commands. Preferably, the engine control commands comprise propeller RPM and engine inlet manifold air pressure commands, and the detected ambient air flight conditions comprise air speed and altitude.

Abstract: A propeller pitch control apparatus for an aircraft in which the vector sum of the aircraft forward speed and the propeller rotational tip speed is a selected fraction of the speed of sound, the fraction based on percent power and altitude, to maximize efficiency and minimize noise.

Abstract: A device (10) is disclosed for intercepting the input of a system (23) of an internal combustion engine (12) normally provided to a solenoid valve (22) for actuating a fan clutch (20) when rotation of a fan (16) is desired. The input is received by terminals (42, 43) and is conditioned and passed on to a timer (96) and a controller (97). A vacuum switch (24) senses whether the fan (16) is rotating and provides a second input to the controller (97). In the event that an input is provided by the system (23) and the time delay signal has been provided by the timer (96) and also in the event that an input is provided by the system (23), the time delay has expired, and the second input is provided by the vacuum switch (24), the controller (97) provides an actuation output to terminals (71, 73) connected to the solenoid valve (22) by use of actuation provisions (98) to actuate the fan clutch (20).

Abstract: A propeller control system (1) includes a propeller controller (6) the gain of which is set by a look up table (2) in response to airspeed data supplied by an airspeed detector (4). By varying the gain of the propeller controller (6) an overall system gain can be maintained as the gain of a propeller (7) varies with airspeed.

Abstract: The invention relates to improvements to helicopters with coaxial rotors, of convertible type in particular, consisting of at least two contra rotative rotors carrying blades for lifting and propelling, the fuselage having an axis parallel to the axes of the rotors and wherein each rotor consists of a nave carrying arms radially arranged, the arms carrying a coating with a propeller blade section, movable in incidence through whirling on to said arms. The naves are axially displaced along and rotatably supported about a shaft coaxial with the fuselage axis and comprising a structural support member of the fuselage.

Abstract: An analog mixer for a helicopter rotor control system mounted for tilting motion about a variable tilt axis and connected to the rotor control swashplate to cause synchronous tilting and including means to impart tilt generating control inputs to the analog mixer, and means to vary the position of the analog mixer tilt axis as a function of helicopter speed to thereby vary the phase angle of the helicopter rotor without imparting control inputs to the rotor control swashplate.

Abstract: A control for a helicopter having dual, coaxial, counterrotating rigid rotors which varies the cyclic control phase angle of each rotor in flight as a function of vehicle forward speed to thereby control the coupling of lateral cyclic pitch with longitudinal cyclic pitch so as to introduce differential cyclic pitch inputs which automatically produce aerodynamic moments in each rotor to minimize maneuver generated gyroscopic precession moments, which also produce optimum lateral lift vector displacement for all flight speeds.