Abstract: A power converter having a boosting mechanism with a multi-shaft vertically stepped turbine includes: a shaft sleeve, a water inlet end base, an outer sleeve, a plurality of first stepped turbine units, a plurality of first shaft rods, a plurality of second stepped turbine units, a plurality of second shaft rods and a third shaft rod. The first stepped turbine unit is located above the second stepped turbine unit. The second stepped turbine units and the first stepped turbine units rotate in opposite directions. During a drainage process, water flows move in opposite directions and collide with each other to increase a water pressure. Due to the increase in the water pressure, rotational speeds of the first stepped turbine units and the second stepped turbine units increase, and rotational speeds of the first shaft rods and the second shaft rods correspondingly increase.

Abstract: A system and method for controlling rotor dynamics at a rotor assembly. The system includes a magnetic actuator and a controller. The magnetic actuator is positioned in magnetic communication with the rotor assembly and is configured to obtain a measurement vector corresponding to the rotor assembly and a measurement vector indicative of a rotor dynamics parameter. The magnetic actuator is further configured to selectively output an electromagnetic force at the rotor assembly. The controller is configured to store and execute instructions.

Abstract: A system of connectable aerial vehicles. The system includes a plurality of aerial vehicles that each include a platform, one or more rotors operatively connected to the platform, and a power source that supplies power to the one or more rotors. The plurality of aerial vehicles are configured to operate in air, and operate in water while connected to form a floating platform. The floating platform is configured to support an object with at least a portion of each of the plurality of aerial vehicles configured to form a segment of the floating platform.

Abstract: Control of a wind turbine in a stop process where a stop controller is used to pitch the blades at a number of pre-set pitch rates including a first pitch rate and a second pitch rate. The stop controller is arranged to access desired pitch angles of the stopping process and add an envelope band to the desired pitch angles. In the stop process, pitching at a selected pitch rate among the number of pre-set pitch rates is performed, and the pitch rate is changed according to criteria to keep the pitch value within the envelope band.

Abstract: A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

Abstract: A propeller includes a rotatable hub and at least two propeller blades coupled to the rotatable hub. Each of the propeller blades is formed from a combination of a first material having a negative Poisson's ratio (NPR) and a second material having a positive Poisson's ratio (PPR). The first material and the second material can be layered or can be formed as a matrix with one of the first or second material embedded in the other. In a layered configuration, a layer of the first material is positioned between adjacent layers of the second material, and the layers can be connected by tabs of NPR material. The combination of the NPR and PPR materials improve the strength and impact resilience of the propeller blades compared to conventional materials.

Abstract: A method for controlling a wind power installation having a rotor operated with variable speed and having rotor blades that are adjustable in their blade angle. The installation is controlled in a partial-load range by an open-loop operating-characteristic control, which uses an operating characteristic. The operating characteristic presets a relationship between the rotational speed and a generator state variable to be set that is a generator power or torque. A value of the generator state variable preset by the operating characteristic is set in dependence on a detected speed. The installation is controlled in a full-load range by a closed-loop pitch control, in which the rotational speed is controlled to a speed setpoint value by adjusting the blade angles. In a presettable range of the partial-load range and/or in a transitional range from the partial-load range to the full-load range, the installation is controlled by a speed-power control.

Abstract: A system for measuring displacements of a blade root of a rotor blade of a wind turbine includes a hub, and a rotor blade coupled to the hub by a pitch bearing. The system further comprises a reference plane and at least one displacement sensor. The reference plane is configured to move with the rotor blade as the rotor blade moves relative to the hub while the displacement sensor is fixed to the hub and the displacement sensor is configured to detect a displacement of the reference plane relative to the hub without physical contact. Alternatively, the reference plane has a fixed position with respect to the hub while the displacement sensor is fixed to the rotor blade and the displacement sensor is configured to detect a displacement of the reference plane relative to the rotor blade without physical contact.

Abstract: A flow turbine rotor whose operation is based on aerodynamic profiles with leading and trailing edges clearly defined by their construction, adapted for nominal operation at specific speed blade speed greater than 1.5 of the incoming wind speed, characterized in that the angle angle ?, measured as a shift in the blade rotation axis (1) between the angular position of the blade trailing edge, from ¼ to ½ of the rotor height is at least 20 percent smaller than the angle ?, measured as a shift in the blade rotation axis (1) between the angular position of the trailing edge of the blade, from ½ to ¾ of the height of the rotor.

Abstract: A fluid supply system for a gas turbine engine includes a first component and a second component. A fluid fitting has a fluid junction. The fluid junction includes a first fluid port in fluid communication with and configured to supply a first cooling fluid to the first component. The fluid junction includes a second fluid port in fluid communication with and configured to supply a second cooling fluid to the second component. A primary pipe is fluidly connected to the fluid fitting. A flow meter is arranged upstream from the fluid junction and is configured to receive a cooling supply fluid from a fluid source. Thee flow meter is a wall having an orifice and a surface that is radiused and convex facing into the cooling supply fluid. A secondary pipe is secured to the fluid fitting and is configured to supply the second cooling fluid to the second component. A turbine section includes the first and second components.

Abstract: The present invention relates to control of a wind turbine in a stop process in response to a rotor stop signal. The rotor stop process comprises the steps of prior to receipt of the rotor stop signal, generating a stored pitch angle signal by storing pitch angle signals for at least a fraction of a rotor revolution, and determining at least one periodic component of the stored signal. The rotor blades of the wind turbine are controlled towards a feathering position using a pitch control signal containing the at least one periodic component.

Abstract: A rotor includes a base member including a first side, a second side opposite the first side, and a central opening passing through the first side and the second side. The second side includes an outer circumferential edge having a first dimension and the central opening having an inner circumferential edge having a second dimension. A plurality of blades extend outwardly from the first side. The plurality of blades extend about the central opening. A fuse element is formed in the second side and extends along one of a radial direction and a circumferential direction. The fuse element has a length that is less than the first dimension.

Abstract: A flange arrangement includes a power shaft, a flanged hub connected detachably to the power shaft, and a stop member configured to detachably hold the flanged hub on the power shaft and to exert a disassembly force on the flanged hub so as to be able to rotate about a rotation axis of the power shaft.

Abstract: A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.

Abstract: An outflow region of a compressor. The outflow region comprises a flow channel delimited by a side wall at a shroud side and a side wall at a hub side. The side wall at the hub side has, in a region of the compressor wheel outlet, a contour configured such that, in a flow direction, the cross-sectional areas of the flow channel decrease, pass through a minimum and increase again. In the region of the compressor wheel outlet, the flow channel has a length L which extends from a compressor wheel outlet edge to a diffuser blade inlet edge of a diffuser region. The diffuser region adjoins the region of the compressor wheel outlet and has multiple diffuser blades. A compressor with the outflow region according to the invention, and to a turbocharger having the compressor.

Abstract: A turbine with an associated shaftless electric generator includes a rotor and a stator; a mounting plate rotatable with the rotor and a void along a central axis of the rotor. A plurality of blades extend from the mounting plate. Adjustable bearings are interposed between the rotor and the stator, the adjustable bearings being configured to support the mounting plate and the plurality of blades. A threaded adjustor rod located in the void may be manipulated to adjust tension on the adjustable bearings.

Abstract: A two degrees of freedom actuator for example for multi-bladed rotor of an aircraft with at least two blades that are driven in rotation about a main rotation axis by primary actuator, and a secondary actuator that is arranged to rotate each of said blades about the respective blades' longitudinal axis, with a synchronization means that is operatively arranged for driving the secondary actuator based on an azimuth of the rotor about the main axis for obtaining a determined cyclic pitch of a given amplitude for each blade depending on the azimuth of the rotor.

Abstract: A method for operating a wind turbine determines reliability of an azimuth measurement system by measuring loads with load sensors during operation of the wind turbine. Based on the measured loads, in-plane moments generated on the blades at a rotational speed frequency of the rotor are determined. The azimuth measurement system has reduced reliability if the angular phase of the in-plane moments at the rotor rotational speed frequency of the rotor deviates from an angular phase measured by the azimuth measurement system by more than a first threshold value. The method generates a warning signal or changes operation of the wind turbine when it is determined that the azimuth measurement system has reduced reliability.

Abstract: An apparatus for mitigating vortex-shedding vibrations or stall-induced vibrations on one or more rotor blades of a wind turbine during standstill includes at least one positioning element located between a blade tip section and a blade root section thereof. The positioning element is adapted for wrapping around at least a portion of the rotor blade. The apparatus also includes at least one airflow modifying element coupled to the positioning element and defining a height relative to a surface of the rotor blade. Additionally, the apparatus includes at least one securing element operably coupled to the positioning element for temporarily securing the airflow modifying element to the rotor blade.

Abstract: A method and an apparatus for dynamically determining a yaw control precision. The method comprises: during a predetermined time period, collecting a plurality of wind speed data and a plurality of wind direction data, and processing the collected plurality of wind speed data and plurality of wind direction data; on the basis of the processed wind speed data and wind direction data, establishing a model of the corresponding relationship between wind speed, wind direction angle change, yaw control precision, yaw fatigue, and power loss; and, on the basis of the current wind speed data, wind direction data, predetermined yaw fatigue range, and predetermined power loss range, by means of the corresponding relationship model, determining the yaw control precision corresponding to the current wind speed and current wind direction angle change.