Abstract: An energy capture device is disclosed. The energy capture device, notably, comprises a turbine and a static velocity increasing device, surrounded by an enclosure. The turbine is configured to receive air that has been sped up by the static velocity increasing device. The turbine is then able to convert the energy of fluid movement into electricity.

Abstract: An internal combustion engine for producing mechanical drive power by combustion of a fuel. The internal combustion engine includes two or three rotary pistons which are rotationally fixedly connected to an output shaft and rotatably arranged in a respective annular cylinder, and at least one passage between the annular cylinders and a respective movable shut-off slide valve for periodically closing the cylinders adjacent to the passage.

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes fan blades defining a corresponding fan area (AFAN). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and includes radially-extending vanes arranged in a circumferential array with at least one vane including a heat transfer element for heat transfer from a first fluid contained within each element to an airflow passing over a surface of each heat transfer element before entering the fan assembly inlet. Each heat transfer element extends axially along the corresponding vane, with a swept heat transfer element area (AHTE) being the wetted surface area of all heat transfer elements in contact with the airflow. A Fan to Element Area parameter FEA of AHTE/AFAN lies in the range of 47 to 132.

Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, an inlet duct, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter D, and the heat exchanger module comprises a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into the fan assembly. In use, the first fluid has a maximum temperature of 80° C., and the heat exchanger module transfers at least 300 kW of heat energy from the first fluid to the airflow.

Abstract: A turbofan gas turbine engine includes heat exchanger module, fan assembly, compressor, turbine and exhaust modules. The fan includes a plurality of fan blades. The heat exchanger in fluid communicates with the fan assembly by an inlet duct, and the heat exchanger includes a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger is divided between a set of vane airflows and a set of channel airflows. Each vane airflow has a vane mass flow rate FlowVane, and each channel air flow has a channel mass flow rate FlowChan. Each hollow vane includes, an inlet, heat transfer, and exhaust portions, with the inlet portion comprising a diffuser element and the heat transfer portion including at least one heat transfer element. The diffuser element causes FlowVane to be lower than FlowChan.

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.

Abstract: An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid cooling flow prior to an entry of the entire fluid cooling flow into the fan module.

Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D), and the heat exchanger module comprises a plurality of heat exchanger elements. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, with the heat exchanger module having an axial length along a central axis between an upstream-most face of the heat exchanger elements and a downstream-most face of the heat exchanger elements. The axial length is in the range of 0.1*D to 5.0*D.

Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D). The heat exchanger module comprises a plurality of heat transfer elements. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The inlet duct has a fluid path length along a central axis of the inlet duct between a downstream-most face of the heat transfer elements and an upstream-most face of the fan assembly. The fluid path length is less than 10.0*D.

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module includes a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels.

Abstract: An aircraft propulsion system comprises an engine, a propeller drive shaft drivingly engaged with the engine, a propeller for propelling an aircraft and a fan driving cooling air along a flow path in thermal communication with the engine. The engine may be an internal combustion engine or other engine type having heat rejection requirements and the fan may facilitate cooling of the engine. The propulsion system may have a pusher configuration.

Abstract: The disclosure concerns variable valve timing of a four-stroke ICE. The ICE comprises: an exhaust valve and an intake valve an exhaust camshaft an intake camshaft and a cylinder arrangement. The cylinder arrangement comprises a combustion chamber a cylinder bore and a piston. The control arrangement is configured to: perform a first sequence of changes in the timings of the exhaust and intake camshafts in order to arrive from a first camshaft timing setting at a second camshaft timing setting based on a first current maximum cylinder pressure within the combustion chamber around top dead centre fire and/or around to dead centre gas exchange.

Abstract: A phaser system is provided. The system includes a first gear connected to a first plate, and a second gear connected to a second plate. A phaser assembly includes at least one piston plate, and axial displacement of the at least one piston plate is configured to adjust a phase between the first gear and the second gear. A hydraulic fluid actuator assembly is also provided that includes a hydraulic fluid circuit including an advance chamber defined on a first side of the at least one piston plate and a retard chamber defined on a second side of the at least one piston plate. A valve selectively pressurizes the advance chamber or the retard chamber such that the at least one piston plate is axially displaced.

Abstract: A method for operating a vehicle having a gasoline engine includes determining a density of a gasoline to be combusted in the gasoline engine, determining a stoichiometric air demand, determining a critical temperature from the density of the gasoline to be combusted and the stoichiometric air demand, and adapting countermeasures to prevent vapor bubbles based on the determined critical temperature.

Abstract: An engine assembly comprising an internal combustion engine having a combustion chamber; an intake manifold for supplying air to the combustion chamber; a fuel injector for supplying fuel to the combustion chamber; an exhaust manifold for receiving exhaust gas released from the combustion chamber and a rotatable drive shaft, wherein combustion of fuel in air within the combustion chamber results in rotation of the drive shaft. The engine assembly further comprises a turbocharger system comprising a turbine and a compressor, wherein the turbine is configured to receive exhaust gas from the exhaust manifold, to recover energy from the exhaust gas, and to release the exhaust gas via a turbine outlet; and wherein the compressor is configured to receive energy from the turbine and thereby to compress air for use in combustion of fuel in the combustion chamber.

Abstract: Systems and methods for determining degradation of a cylinder deactivation mechanism are described. In one example, engine data generated while an engine is operation with all of its cylinders active is used to correct engine data generated while one or more engine cylinders are deactivated to improve detection of a degraded cylinder deactivation mechanism.

Abstract: A misfire determination period is set to a predetermined range of a crank angle. A CPU performs: a calculation process of calculating an average value of a torque of an output shaft of an internal combustion engine in the misfire determination period; a misfire determining process of determining that a misfire has occurred when the calculated average value is less than a prescribed threshold value; and a process of setting the whole misfire determination period to a period in a positive torque range which is a range of a crank angle at which the torque of the output shaft is equal to or greater than zero at the time of normal combustion in which a misfire does not occur.

Abstract: A CPU determines that there is a misfire when a relative magnitude of a rotation fluctuation amount ?T30[0] related to a cylinder subject to the determination in relation to a rotation fluctuation amounts ?T30[4] of the previous combustion cycle is greater than or equal to the determination value ?th. However, during the execution of a catalyst warm-up process, the CPU uses, in the comparison, the relative magnitude of the rotation fluctuation amount ?T30[0] in relation to the average ?T30ave[0] of the smallest five of the rotation fluctuation amounts ?T30[4] to ?T30[40] from the past ten combustion cycles.

Abstract: The objective is to provide an internal-combustion-engine controller that can diagnose, at low cost and in real time, respective combustion states of a subsidiary-chamber-type internal combustion engine. An internal-combustion-engine controller according to the present disclosure controls an internal combustion engine having a main combustion chamber and a subsidiary combustion chamber from which a combustion gas is injected into the main combustion chamber through an orifice provided between the main combustion chamber and the subsidiary combustion chamber to ignite a fuel-air mixture in the main combustion chamber; the internal-combustion-engine controller includes an ion detector that detects an ion in the in the subsidiary combustion chamber and a diagnosis and control device that controls fuel supply to the internal combustion engine and diagnoses a combustion state in the main combustion chamber or in the subsidiary combustion chamber, based on an amount of an ion detected by the ion detector.

Abstract: A leakage detector for fuel vapor treatment device is configured to diagnose a leakage of a fuel vapor in a vapor path based on an internal pressure change of the vapor path with the vapor path functioning as a closed space. The leakage detector performs the leakage diagnosis of the vapor path by correcting the effect of the pressure of the fuel vapor with regards to the internal pressure change. The leakage detector comprises a vaporization promoting device and is configured to determine whether the fuel vapor in the gas space of a fuel pump has reached a saturated state.

Abstract: Various systems and methods are provided for adjusting operating parameters of an internal combustion engine. In one example, a system may include adjusting an amount of advance of a fuel injection timing of a plurality of fuel injectors of an internal combustion engine relative to top dead center (TDC) responsive to engine output demand, where, as the engine output demand increases, the amount of advance first decreases and then increases. In this way, an amount of vehicle emissions may be decreased while an amount of fuel consumption is decreased.

Abstract: An engine controller controlling an engine including an occlusion reduction catalyst in an exhaust device includes a fuel injection controller that controls a fuel injection amount of an injector, an EGR controller that controls an EGR device, a sulfur purge determiner that determines whether sulfur purging of the catalyst is to be performed, and a sulfur purge controller that executes sulfur purge control if the sulfur purging is performed. The sulfur purge control involves performing a fuel injection to achieve a rich air-fuel ratio at an inlet of the catalyst and prohibiting the exhaust-gas introduction. The sulfur purge controller executes sulfur-purge standby control when a sulfur-purge standby condition is satisfied, and resumes the sulfur purge control when the condition becomes non-satisfied after starting the sulfur-purge standby control.

Abstract: An apparatus for processing a groove on an interior circumference of a cylinder bore may include, a holder formed with bolt holes on a lower surface, a frame having a fixing end, a mounting end, and a supporting end, the fixing end being formed with slots corresponding to the bolt holes, an inner slip ring mounted on an exterior circumference of a lower end portion of the holder and connected an electrical cable, an outer slip ring externally installed on the inner slip ring allowing a slip, a motor mounted on the mounting end of the frame, connected to the inner slip ring through the electrical cable, and having a rotation shaft rotatably supported by the mounting end and the supporting end, and a cutting tip coupled with the rotation shaft of the motor through a tip holder mounted on the rotation shaft.

Abstract: A cylinder head (1) disclosed herein includes a cylinder head main body (10) having an intake port (3) communicating with a combustion chamber (2) of an engine; and an insulation member (20) being arranged at an inner side of the intake port (3), made of resin, and formed into an annular shape. A step part (14) is formed at a downstream side of the insulation member (20) in a flow direction of intake air in the intake port (3) such that the intake port (3) has a cross section perpendicular to the flow direction at the downstream side smaller than a cross section perpendicular to the flow direction at an upstream side of the flow direction; and an annular seal member (21) that seals a space between the insulation member (20) and the step part (14) is arranged between the insulation member (20) and the step part (14).

Abstract: A cylinder head assembly includes a cast cylinder head and a turbocharger housing integrally cast with the cylinder head. The integrated cylinder head and turbocharger housing includes: (i) a compact low wetted area to provide an uninterrupted flow path pointed directly at a catalyst face to facilitate achieving cold start emissions targets, (ii) a casting core assembly with specific core geometry and steps for assembly to enable core assembly while meeting all cylinder head and integrated turbine housing functional requirements, (iii) an oxygen sensor disposed pre-turbine in an integrated exhaust manifold, and (iv) a fully integrated PCV make-up air system.

Abstract: A piston may include a splitting internal cooling runner, an end portion recessed inward to form a combustion chamber, and an annular internal cooling runner at least partially surrounding the combustion chamber. A wall of the annular internal cooling runner may partially protrude in a direction away from the end portion to form an annular splitting portion which divides the annular internal cooling runner into an outer half cavity and an inner half cavity.

Abstract: An internal combustion engine includes a one-piece cylinder block casting, a flywheel supported for rotation at a front block end, and a back gear train supported for rotation at a back block end. Cast-in pump inlet and outlet passages are formed in the cylinder block casting and open in a pump mounting face at the back block end. An oil pump is clamped to the pump mounting face and includes a pump inlet and a pump outlet fluidly connected, respectively, to the cast-in pump inlet passage and the cast-in pump outlet passage.

Abstract: An internal combustion engine and a head gasket are provided. The internal combustion engine includes a block having at least one cylinder, a head joined to the block at a head interface, a cooling fluid circulation passage extending at least partially through the head and the block and having a first portion disposed in the head and a second portion disposed in the block, a head gasket having a plate extending across the head interface and separating the first portion of the cooling fluid circulation passage from the second portion of the cooling fluid circulation passage, and a plurality of orifices extending through the plate. The plurality of orifices is aligned with the cooling fluid circulation passage and is configured to control a flow of cooling fluid circulating between the first portion of the cooling fluid circulation passage and the second portion of the cooling fluid circulation passage.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a forward thrust duct and a thrust reverser system. The thrust reverser system includes a thrust reverser duct, a bullnose ramp and a plurality of protrusions. The bullnose ramp is adapted to provide a transition from the forward thrust duct to the thrust reverser duct when the thrust reverser system is in a deployed configuration. The protrusions are bonded or formed integral with the bullnose ramp. Each of the protrusions is adapted to interact with boundary layer fluid flowing along the bullnose ramp from the forward thrust duct into the thrust reverser duct when the thrust reverser system is in a deployed configuration.

Abstract: The subject matter of this specification can be embodied in, among other things, an actuator apparatus includes an output member configured to actuate between a first positional configuration and a second positional configuration, a source fluid reservoir, a fluid velocity resistor configured to provide a predetermined resistance to fluid flow, a fluid velocity fuse configured to flow fluid flows having a first predetermined range of fluid velocities and to block fluid flows having second predetermined range of fluid velocities, and a fluid actuator assembly configured to urge fluid flow from the source fluid reservoir through the fluid velocity resistor and the fluid velocity fuse based on actuation of the output member.

Abstract: An aircraft comprises a machine body which encloses a turbofan gas turbine engine. The turbofan gas turbine engine includes a heat exchanger module, fan assembly, compressor module, turbine module, and exhaust module. The heat exchanger module communicates with the fan assembly by an inlet duct. The heat exchanger module includes first heat transfer elements that transfer heat energy from a first fluid within the transfer elements to an airflow passing over a surface of the transfer elements before entry of the airflow into a fan assembly inlet. The first fluid contained within transfer elements has a temperature, and the airflow passing over the transfer element surface has a temperature. The turbofan gas turbine engine further includes at least one second heat transfer element, with the or each second heat transfer element transfers heat energy from the first fluid to a second fluid.

Abstract: A rocket motor and rocket motor feed system are disclosed. The rocket motor feed system includes a sonic choke which passively regulates the mass flow rate of gaseous propellant passing through the sonic choke. An injector is provided and isolates the upstream feed line of the rocket motor feed system from a combustor. Regenerative cooling circuits are disclosed. Self-pressurised gaseous propellants may be used with the rocket motor and rocket motor feed system. Suitable propellants are disclosed. Bi-propellants may be used. The sonic choke may provide a ratio of oxidiser:fuel to a combustor. Rocket motor feed systems with separate fuel and oxidiser branches are also disclosed. A rocket motor utilising such a feed system is disclosed.

Abstract: An internal combustion engine system includes an engine, an air intake system configured to provide intake air to the engine, and an exhaust system configured to receive exhaust gas from the engine. The engine system further includes a secondary air system including a pump, an exhaust gas recirculation (EGR) system, and a valve system operably associated with the secondary air system and the EGR system. The valve system is configured to operate in a secondary air mode where the pump is utilized to supply secondary air to the exhaust system, and an EGR mode where the pump is utilized to supply EGR to the air intake system.

Abstract: The present invention relates to a method and a control unit for avoiding condensation of humidity in an intake system of an internal combustion engine after engine switch off. Condensed liquid in the intake system of the stopped engine can lead to icing, corrosion and a hydrostatic lock at the next engine start. To prevent such an engine damage, it is necessary to determine if and in which amount condensed liquid occurs in the cooled intake system and to initiate appropriate actions to eliminate the liquid therefrom. The present invention predicts the occurrence of condensation in the intake system of the cooled engine and initiates corrective measures at engine switch off and during the cooling down period.

Abstract: A bent section (71) is provided. An intake gas outlet (71B) downstream of the bent section (71) is connected to an intake manifold (11C). A throttle valve (47A) is disposed in the vicinity of and upstream of an intake gas inlet (71A) upstream of the bent section (71). An EGR pipe (13) is connected to the bent section (71). A rotation shaft (48) of the throttle valve (47A) is provided so as to be perpendicular to a first plane (75) including an inlet side intake pipe axis (72A) passing through the intake gas inlet (71A) and an outlet side intake pipe axis (72B) passing through the intake gas outlet (71B).

Abstract: An electric water pump with a control panel mounted in the middle of the water pump is disclosed, including a water pump volute casing, a water pump impeller, a pump cover, a water pump control panel, a rotor, a rotor cover, a housing, a rear bearing, a stator, a thrust ring, and a front bearing. The water pump volute casing is mounted on a surface at a front end of the pump cover. The water pump control panel is mounted on a surface at a rear end of the pump cover. An end opening of the rotor cover is sleeved on an outer circumference of a boss at the rear end of the pump cover.

Abstract: An engine control system includes: a normalization module configured to normalize, to within a predetermined range of values, a spark timing of an engine and at least one other parameter of the engine, thereby producing a normalized spark timing and at least one normalized other parameter, respectively; a processing module configured to generate a sigmoidal spark timing by applying, to the normalized spark timing, one of (a) a sigmoidal function and a sinusoidal function; and an estimation module configured to estimate a torque output of the engine based on the normalized spark timing and the at least one normalized other parameter using a mathematical model.

Abstract: A fluid flow actuated tool including a housing, a tool and an actuating mechanism. The housing includes a housing interior. The housing interior receives a flow of fluid. The actuating mechanism includes a fluid wheel structure. The fluid wheel structure is connected to the tool. At least a portion of the fluid wheel structure is arranged in the flow of fluid for rotating the fluid wheel structure. The tool is actuated based on rotation of the fluid wheel structure.

Abstract: A rotor blade for a wind power installation, which extends in a longitudinal direction with a profile course from a blade connector to a blade tip, wherein the profile course contains at least one profile, comprising: a suction side and a pressure side, a relative profile thickness of greater than 25%, a profile chord, which extends between a leading edge and a trailing edge of the profile and has a length which defines the profile depth, a mean line which extends at least partially below the profile chord, a convex region which extends on the suction side from the trailing edge, and a convex region which extends on the pressure side from the trailing edge, wherein the convex region on the pressure side defines a rounded transition region of the pressure side to the trailing edge.

Abstract: A wind turbine blade includes a first blade portion and a second blade portion coupled together by a connection joint. A first spar cap is associated with an upper shell half and a second spar cap is associated with the lower shell half of each of the first and second blade portions. A shear web extends between the first spar cap and the second spar cap of each of the first and second blade portions. The shear web is terminated away from a joint interface at which the first and second blade portions meet, and there is no shear web extending in a longitudinal direction across the joint interface. The shear web extending between the first spar cap and the second spar cap is branched in the longitudinal direction toward the first and second blade interfaces of the first and second blade portions respectively.

Abstract: A rotor blade for a wind turbine includes at least one blade segment with at least one shell member defining an airfoil surface. The shell member(s) includes a sandwich panel configuration having one or more inner skin layers, a core material, and one or more outer skin layers. The outer skin layer(s) includes one or more first fibers, whereas the inner skin layer(s) includes one or more different second fibers. Further, the first fiber(s) of the outer skin layer(s) have a higher elastic modulus than the second fiber(s) of the inner skin layer(s).

Abstract: In a vertical rotor apparatus that rotates in response to a moving fluid, a shaft defines an axis of rotor rotation. Rotor blades are longitudinally aligned in parallel with the shaft and each rotor blade defines an axis of blade rotation. A sensor generates a signal when any of the rotor blades are within rotor azimuthal angles of blade stall regions. A controller generates blade pitch information for the blade stall regions and an actuator, which is mechanically coupled to each of the rotor blades, alters blade pitch about the axis of blade rotation in accordance with the blade pitch information.

Abstract: A method for controlling a wind turbine having a rotor with at least two rotor blades, a 1P individual blade controller for individually adjusting the rotor blades in cycles about the respective longitudinal axis of the rotor blades using a first rotor assembly, and partial and full load ranges which adjoin each other in a nominal operating point.

Abstract: Aspects of the present invention relate to controlling a wind turbine having a tower damping system actuable to control components of vibrational movement of the tower, a side-side component of a vibrational movement of the tower in a horizontal plane; and a fore-aft component of the vibrational movement of the tower in the horizontal plane are determined; and a control signal based on the side-side and fore-aft components is determined such that the tower damping system produces a force that increases or decreases the vibrational movement of the tower such that the side-side and fore-aft components are substantially equal.

Abstract: A method of manufacturing a rotor blade component for a rotor blade of a wind energy installation, a rotor blade component, and a wind energy installation comprising such a rotor blade component. The method includes manufacturing a layer system including a first layer of a first material and a second layer of a second material. The second material has a smaller modulus of elasticity than the first material, and the second layer extends at least partially along the first layer. The layer system is beveled at least at one end with the aid of at least one separation process such that the second layer projects beyond the first layer at the at least one end of the layer system. The layer system is connected to at least one other such layer system so as to form the rotor blade component.

Abstract: A method of forming a wind turbine foundation includes providing an anchor cage in an excavation pit, the anchor cage including an upper flange, a lower flange, and a plurality of anchor bolts extending therebetween. A first cementitious material is directed into the excavation pit so that the anchor cage becomes at least partially embedded in the material, which is allowed to cure to form a rigid body. A connecting element is selectively engaged with the upper flange and an actuating element is positioned in operative relation with the connecting element, the connecting and actuating elements positioned in non-contact relation with the anchor bolts. The actuating element is actuated relative to the connecting element to raise the upper flange from the rigid body into a leveled position. A second cementitious material is directed into a space beneath the raised upper flange and is allowed to cure to form a support layer.

Abstract: Provided is a transport assembly for use in the transport of a large heavy load, including a frame unit realized to lie on a load platform of a transport vehicle; a number of first load-positioning beams, wherein a first load-positioning beam is realized to span a single frame unit; and/or a number of second load-positioning beams, wherein a second load-positioning beam is realized to span a pair of adjacent frame units; and a part adapter realized to engage with a load-positioning beam and to engage with the load. The embodiments further describe a method of securing a large heavy load on a load platform during a transport maneuver.

Abstract: The present invention relates to a method of determining an induction factor between the rotor plane (PR) and a measurement plane (PM), involving measuring the wind speed in at least two measurement planes (PM), determining the wind speed in rotor plane (PR) by use of a Kalman filter from the measurements, and a step of measuring the induction factor by use of an adaptive Kalman filter from the measurements and the wind speed in rotor plane (PR).

Abstract: The present disclosure relates to methods and systems for determining fatigue loads in a wind turbine. Such a method may comprise obtaining operational metadata representative for an operational situation, and determining whether the operational metadata corresponds to operational metadata from one of a plurality of previously defined operational situations for which fatigue loads are known, the plurality of previously defined operational situations being stored in an operational situations database. If the operational metadata representative for the operational situation substantially corresponds to operational metadata from the stored previous operational situation, then the fatigue loads for the stored previously define operational situation are summed to historically accumulated fatigue loads to determine total accumulated fatigue loads. Methods for registering an operational situation in a wind turbine are also provided.

Abstract: A method of protecting a wind turbine having a set of blades, each blade having a set of loci suitable for placement of a corresponding set of lightning receptors, against lightning strikes, includes applying to each blade a coating that surrounds at least one lightning receptor locus of the set, wherein the coating comprises paint in which has been mixed a conductive powder having a concentration by weight in the coating sufficiently low as to prevent formation of a conductive path through the coating but sufficiently high as to foster ionization of air along the coated exposed surface.