Abstract: There is disclosed a fan assembly including a fan rotor including a hub and fan blades. The fan blades have a leading edge and a trailing edge. A fan stator downstream of the fan rotor relative to a direction of an airflow through the fan assembly. The fan stator includes vanes extending between radially inner ends and radially outer ends. A flow recirculation circuit has an inlet downstream of radially inner ends of the vanes of the fan stator and an outlet upstream of radially inner ends of the vanes. A recirculation stator has a plurality of stationary guide vanes circumferentially distributed around the axis and located in the flow recirculation circuit between the inlet and the outlet A method of operating the fan assembly is also disclosed.

Abstract: A method for exhaust waste energy recovery at the reciprocating gas engine-based polygeneration plant which includes supplying this plant with any on-site available methaneous gas, converting from 15 to 30% of supplied gas into electric or mechanical power and producing a liquefied methaneous gas (LMG) co-product from the other 85-70% of supplied gas, and thereby obviates a need for any specialized refrigeration equipment, refrigerants and fuel for LMG co-production at a rate of 0.4-0.6 ton/h for each MW of engine output and makes possible to increase the LMG co-production rate up to 0.9-1.1 t/MWh at the sacrifice of a fuel self-consumption minimized down to 1-2% of the amount of gas intended for liquefaction.

Abstract: A steam turbine system (200) includes a steam turbine (60) in which a main flow path (C) through which a main steam flows is formed, and a saturated steam generation portion (210) that is configured to generate a saturated steam. The saturated steam generation portion (210) is configured to feed the saturated steam into a wet region (C1) in which the main steam in the main flow path (C) is in a wet state via a hollow portion formed inside a stator vane (650) of the steam turbine (60). The stator vane (650) has a plurality of supply ports that are formed such that the hollow portion is configured to communicate with the main flow path (C), and a discharge amount of the saturated steam increases from an inner circumferential side toward an outer circumferential side in a blade height direction.

Abstract: A turbomachine comprising an engine body and an annular nacelle. The nacelle has an air intake comprising an outer skin, an inner skin, an air intake lip connecting the outer and inner skins together, and an annular frame connecting the outer and inner skins together. The turbomachine comprises a system for de-icing the air intake having an air bleeding port for bleeding a flow of hot air from the engine body, and two interconnected heating systems. An inner skin heating system receives the hot air flow to heat, by means of a gas-liquid heat exchanger, a heat transfer liquid contained in a hydraulic circuit arranged in part in the heat exchanger and in the inner skin. An air intake lip heating system diffuses the flow of hot air, once it has passed through the inner skin heating system, through the annular frame to heat the air intake lip.

Abstract: Gas turbine engine (GTE) compressor sections and compressor intake ducts are provided having Soft Foreign Object debris (SFOD) endwall treatments, which reduce peak damage to GTE components in the event of SFOD ingestion. In embodiments, the GTE compressor section includes a compressor rotor and a compressor intake duct. The compressor intake duct includes an intake flow passage, which extends through compressor intake duct to the compressor rotor. A first duct endwall extends around a centerline of the flow passage to bound a peripheral portion of the intake flow passage. An SFOD endwall treatment includes topological features formed in or otherwise provided on the first duct endwall. The topological features of the SFOD endwall treatment are configured such that SFOD impacting the topological features is directed in a radially inward direction toward the flow passage centerline prior discharge of the SFOD from the intake flow passage and into the compressor rotor.

Abstract: A turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath; a fuel delivery system for providing a flow of fuel to the combustion section; and a waste heat recovery system. The waste heat recovery system includes a heat source exchanger in thermal communication with the turbine section, the exhaust section, or both; a heat sink exchanger in thermal communication with the fuel delivery system, the core air flowpath, or both; a thermal transfer bus including a thermal transfer fluid and extending from the heat source exchanger to the heat sink exchanger; and a pump in fluid communication with the thermal transfer bus downstream of the heat source exchanger and upstream of the heat sink exchanger for increasing a temperature and a pressure of the thermal transfer fluid in the thermal transfer bus.

Abstract: A method for manufacturing an acoustic element of a sound absorption structure including at least one cylindrical, conical or truncated conical chamber obtained from a flat preform shaped and then assembled in order to obtain the cylindrical, conical or truncated conical shape of the chamber. This manufacturing method makes it possible to obtain an acoustic element that has thin walls and is made from a material suited to its environment. An acoustic element obtained using the manufacturing method, a sound absorption structure comprising at least one such acoustic element and an aircraft powerplant comprising at least one such structure are also described.

Abstract: Disclosed herein are apparatus, assemblies, and methods for mitigating thermal bow in the rotor of an engine at start-up. One apparatus includes a control module that facilitates operating the rotor prior to starting the engine and an acceleration module that facilitates accelerating the rotor to at least a threshold speed prior to starting the engine. An assembly includes a start-up device coupleable to the rotor and configured to start the rotor and a start-up module coupled to the start-up device in which the start-up device and the start-up module are configured to coordinate operations to accelerate the rotor to at least a threshold speed prior to starting the aircraft engine. One method includes transmitting a control signal to control the rotor prior to starting the engine and commanding the start-up device to accelerate the rotor to at least a threshold speed prior to starting the engine.

Abstract: A brush seal for a rotating machine, intended to be disposed between a first part and a second part of the rotating machine, the first and second parts being movable relative to each other about an axis, extending along an axial direction, the brush seal comprising a body intended to be attached to the first part, and a brush attached to the body, intended to be in contact with the second part, wherein the brush comprises at least a first group of bristles and a second group of bristles, at least one parameter of the bristles of the first group of bristles being different from the corresponding parameter of the bristles of the second group of bristles.

Abstract: An aerofoil and an aerofoil assembly, in particular an aerofoil with improved stagnation zone cooling and an aerofoil assembly comprising such an aerofoil. The aerofoil is an aerofoil for a gas turbine engine comprising a pressure surface, a suction surface, a leading edge, a trailing edge, a stagnation zone located in the region of the leading edge, and an elongate channel running along the leading edge at the stagnation zone.

Abstract: A planet-carrier for a mechanical reduction gear of a turbine engine, in particular of an aircraft, this planet-carrier having a rotation axis and comprising axes for guiding the planet gears that are arranged around and parallel with the rotation axis, each guiding axis having a general tubular shape of which the outer periphery comprises only two coaxial and adjacent cylindrical tracks of the respective rollers of two annular rows of rollers, wherein each axis has an inner periphery that is substantially bi-conical and comprising two coaxial and adjacent frustoconical surfaces, these inner frustoconical surfaces converging towards one another and extending respectively radially inside the tracks.

Abstract: A lubricating oil distributor for a turbine engine mechanical reduction gear, for example of an aircraft, has an annular shape about an axis X and is formed of one single part. The distributor includes first and second independent oil circuits, the first oil circuit having a first oil inlet connected by a first annular chamber to several oil outlets distributed over a first circumference C1 about the axis X, and the second oil circuit having a second oil inlet connected by a second annular chamber to several oil outlets distributed over a second circumference C2 about the axis X, the first and second circumferences having different diameters.

Abstract: The invention concerns a shaft component, which can be connected or is connected to the input or output side of a gear box in a gas turbine engine, in particular an aircraft engine, wherein the shaft component has partially a region comprising fiber reinforced plastic, the fibers in this region being arranged only in an angular range of +/?40° to 50°, in particular of +/?42° to 48°, most particularly +/?45°, in relation to the main axis of rotation of the shaft component. The invention also concerns a method for producing a shaft component and a gas turbine engine.

Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.

Abstract: An electronic controller for an engine and a propeller, a control system and related methods are described herein. The control system comprises the controller having a first channel and a second channel independent from and redundant to the first channel. Each channel comprises a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command and at least one propeller control command. Each channel also comprises a protection processor configured to receive second engine and propeller parameters and to output, based on the second engine and propeller parameters, at least one engine protection command and at least one propeller protection command. The control system comprises sensors for measuring the parameters of the engine and/or the propeller and effectors configured to control the engine and the propeller.

Abstract: An electronic controller for an engine and a propeller, a control system and related methods are described herein. The controller comprises a first channel and a second channel independent from and redundant to the first channel. Each channel having a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command comprising instructions for controlling an operation of the engine and at least one propeller control command comprising instructions for controlling an operation of the propeller.

Abstract: A system and a method for automatically controlling an exhaust brake of a vehicle may automatically operate an exhaust brake by automatically recognizing a downhill condition during vehicle traveling. The system and method may automatically operating the exhaust brake by determining whether a current vehicle speed is equal to or greater than a speed limit of a speed limit device together with automatically recognizing a downhill condition, thereby achieving safe traveling together with providing traveling convenience of a driver upon downhill traveling.

Abstract: A throttle assembly for an engine includes a remote control throttle lever, a manual throttle control lever, and a throttle return spring. The remote control throttle lever is configured to operate the throttle assembly and the engine based on a force received from an external device. The manual throttle control lever is configured to operate the throttle assembly and the engine based on a force received from a user input at an input portion of the manual throttle control lever. An abutment portion of the manual throttle control lever is spaced from the input portion of the manual throttle control lever and configured to abut the remote control throttle lever. The throttle return spring is configured to bias the remote control throttle lever against the abutment portion of the manual throttle control lever in an opposite direction of the force received from the external device.

Abstract: Methods and systems are provided for improving fuel economy by opportunistically lowering engine idle speed below a base idle speed when electrical loads are not present. A hydraulic brake pressure is increased when the idle speed is raised, in anticipation of vehicle propulsion. The brake pressure counteracts any creep torque and unintended vehicle acceleration resulting from the rising engine idle speed.

Abstract: Techniques are disclosed herein that provide for controlling torque in a vehicle. In some embodiments, desired torque values are generated and are compared to an amount of torque currently being generated by an engine. If a different amount of torque is desired, an engine speed target is altered in a linear fashion, and then converted back to a torque request to be provided to an engine ECU for implementation. Techniques disclosed herein may cause changes in torque demand to be limited in such a way to cause predictable and smooth changes in engine speed, even when engine speed and torque do not have a linear relationship to each other.

Abstract: A method for controlling a supercharging system for an internal combustion engine, the supercharging stage including a compressor and a turbine, and the turbine being settable with the aid of a VTG driving circuit. The method including: detecting an operating state setpoint variable, setting a maximum VTG control criterion for implementing the torque increase by an increase in a boost pressure. The setting of the maximum VTG control criterion comprising: ascertaining a setpoint boost pressure; ascertaining a VTG setpoint position as a function of the setpoint boost pressure; ascertaining an actual exhaust gas back pressure; ascertaining an actual exhaust gas pressure downstream from the turbine; ascertaining a maximum exhaust gas back pressure, taking into account the actual exhaust gas pressure downstream from the turbine; determining the VTG control criterion, based on the difference between the actual exhaust gas back pressure and the maximum exhaust gas back pressure.

Abstract: A method and system for controlling temperature in an exhaust gas routing system of an internal combustion engine is provided. The exhaust gas routing system includes an exhaust gas manifold, an exhaust gas turbine which includes an electric machine arranged downstream of the exhaust gas manifold in the exhaust gas stream, an aftertreatment system arranged downstream of the exhaust gas turbine, and a control means configured to control the operation of the electric machine to adapt an operating mode of the exhaust gas turbine between motor operating, regeneration operating and neutral operating modes control means (50) such that the temperature of the aftertreatment system is controlled based on a target temperature.

Abstract: A control method of a vehicle having an exhaust gas recirculation (EGR) system includes efficiently controlling a temperature of recirculated exhaust gas and, even when the temperature of recirculated exhaust gas excessively increases, damage to hardware, such as an intake manifold or parts of the exhaust gas recirculation system can be prevented. The control method includes: detecting the temperature of exhaust gas recirculated to an engine intake system by the EGR system; entering into a protection mode so as to control the temperature of the recirculated exhaust gas; determining a correction value such that the controller controls the temperature of the recirculated exhaust gas; and correcting an engine control value by using the determined correction value and controlling an engine according to the corrected engine control value.

Abstract: A method for performing a regeneration cycle for regenerating a diesel particulate filter of a transport refrigeration system. The method includes increasing an air intake throttling level of an engine intake air flow by reducing an air control valve area. The method also includes supplementing the temperature increase of the air intake throttling by energizing an engine preheater.

Abstract: An engine start control device includes an pass determination section that performs a pass determination process of determining, based on a rotation state of the engine output shaft, whether a piston in a cylinder of the engine can pass over a compression top dead center for a rotation drop period in response to an occurrence of the start request. The engine start control device also includes a start control section that when it is determined that the piston cannot pass over the compression top dead center, starts driving of the motor in a low reaction force period to start the engine, the low reaction force period being a period in which a reaction force applied to the piston by a cylinder internal pressure in the cylinder is a predetermined value or less.

Abstract: An engine abnormality detection device for detecting variation of a combustion state of each of a plurality of cylinders of an engine, the engine abnormality detection device includes: a rotation information acquisition part configured to obtain rotation information related to a rotation state of the engine; a frequency analysis part configured to perform frequency analysis of the rotation information, the frequency analysis part being configured to calculate a component of fNe and a component fcyl through the frequency analysis of the rotation information, where fNe is a frequency of a single cycle of the engine and fcyl is a frequency of pulsation of the engine; and a detection part configured to detect variation of exhaust energy of each cylinder on the basis of the component of fNe and the component of fcyl.

Abstract: A method for self-generating an engine-specific model in an engine health monitoring system is provided. The method comprises generating a generic engine model including a generic physics-based model for each of a plurality of engine components in the specific engine; capturing a plurality of observed engine component parameters for each of the plurality of engine components and a plurality of observed environmental parameters during one or more pre-planned training missions; and training an engine-specific model using the plurality of observed engine component parameters and the plurality of environmental parameters captured during the one or more pre-planned training missions, wherein the engine-specific model includes an engine-specific physics-based model for each of the plurality of engine components in the specific engine.

Abstract: A torque monitoring device monitors the occurrence of an abnormal torque state causing an estimated torque as an estimated value for an actual torque of an internal combustion engine to differ from an engine-requested torque required of the internal combustion engine and includes: a discrete value setup unit configured to increase a discrete value correspondingly to increase in a difference quantity between the estimated torque and the engine-requested torque; an accumulation unit configured calculate an accumulation value of the discrete value; and a determination unit configured to determine that the abnormal torque state occurs when the accumulation value becomes larger than or equal to a predetermined abnormality determination threshold value.

Abstract: A method of exercising a generator includes detecting a temperature of the generator by a temperature sensor, if the temperature of the generator is above a predetermined temperature, activating, by a controller, a starter motor of the generator, and performing, by the controller, an exercise test, and if the temperature of the generator is below the predetermined temperature, not activating, by the controller, the starter motor.

Abstract: Provided are a flow volume control device capable of securing a strength withstanding a high fuel pressure, and a method for manufacturing the flow volume control device. A fuel injection valve 1 includes a movable element 102 and a nozzle holder 101 that is positioned on the outer peripheral side of the movable element 102 and holds the movable element 102 inside in a radial direction. The nozzle holder 101 is molded using precipitation hardening stainless steel as a material. In addition, the manufacturing method includes forging and molding a material by forging using the precipitation hardening stainless steel as the nozzle holder 101, performing solution thermal treatment on the material after the forging and molding step, and performing precipitation hardening thermal treatment on the material after the solution thermal treatment, and finishing and molding the material after the precipitation hardening thermal treatment.

Abstract: A control device for an engine is provided. A cavity formed in a crown surface of a piston of the engine includes a first cavity part disposed in a radially center area, a second cavity part disposed radially outward of the first cavity part, and a connecting part connecting these two parts. The control device causes a fuel injection valve to perform a first injection in which fuel is injected at a timing when the piston is located at an advancing side of CTDC and an injection axis thereof intersects with the connecting part, a second injection in which fuel is injected toward the first cavity part at a retarding side of the first injection, and a middle injection in which fuel is injected at a timing between the first and second injections, for a period shorter than each of the first and second injections.

Abstract: An engine control device is provided. A fuel injection valve performs a pre-injection and a main injection on a retarding side of the pre-injection so that pressure waves resulting from combustions caused by the injections cancel each other out. The control device secures a fuel injection amount to be supplied to a combustion chamber in one cycle by at least the pre-injection, the main injection, and a middle injection. The control device causes the fuel injection valve to perform the pre-injection at a timing when a piston is located at an advancing side of compression top dead center for premix combustion, to start the main injection during a combustion period of the fuel injected by the pre-injection for diffuse combustion, and to perform the middle injection at a timing between the other two injections with a fuel injection amount less than the other injections.

Abstract: An insert for a cylinder liner which is capable of trapping heat in the combustion chamber is provided. The insert extends circumferentially around a center axis and longitudinally from an upper end to a lower end. The insert includes an inner portion presenting an inner surface facing the center axis and an outer portion presenting an outer surface facing away from the center axis. The inner portion is formed of an iron-based material, such as steel, and the outer portion is formed of a material having a thermal conductivity of not greater than 3.5 W/mK, for example ceria stabilized zirconia. The inner and outer portions each present a thickness, and the thickness can form a gradient between the upper end and the lower end of the insert. For example, the thickness of the outer portion can be greater at the upper end than at the lower end of the insert.

Abstract: A gasoline direct injection (GDI) engine may include: a cylinder block having a cylinder; a cylinder head having an intake port, an intake valve opening and closing the intake port, an exhaust port, and an exhaust valve opening and closing the exhaust port; a piston reciprocating in the cylinder; a combustion chamber defined by the cylinder head, the piston, and an inner wall surface of the cylinder; and a fuel injector injecting a fuel into the combustion chamber. In particular, the combustion chamber is divided into an intake side where the intake port and the intake valve are located, and an exhaust side where the exhaust port and the exhaust valve are located, and a nozzle of the fuel injector is mounted in the cylinder head toward the exhaust side.

Abstract: A structure of a combustion chamber for an engine includes a crown surface of a piston, a combustion chamber ceiling surface, an injector and an ignition plug provided on the combustion chamber ceiling surface, and an intake opening and an exhaust opening opened in the combustion chamber ceiling surface. A side where the intake opening is opened is defined as an intake port side, and a side where the exhaust opening is opened is defined as an exhaust port side. An ignition portion of the ignition plug is disposed on the intake port side. The ignition plug is ignited at a timing after the piston passes a compression top dead center. The injector is disposed on the center portion, and is configured to inject fuel toward the exhaust port side. A cavity is provided on the crown surface. A reverse squish flow generation portion is provided in the combustion chamber.

Abstract: An exhaust casing for a gas turbine engine comprises a shroud configured to surround an exhaust cone, and a heat shield attached to the shroud. The heat shield has a first end and a second end axially spaced apart from each other. A gap is defined radially between the shroud and the heat shield. The gap is configured to enclose at least a portion of an interface defined between at least one strut and the shroud. The exhaust casing is configured to surround the exhaust cone and configured to be connected to the exhaust cone via the at least one strut.

Abstract: A drive shaft component, which can be connected or is connected to the input side of a gear box in a gas turbine engine, in particular an aircraft engine, characterized in that the drive shaft component has partially a region including fiber reinforced plastic, the fibers in this region being arranged only in an angular range of +/?40° to 50°, in particular of +/?42° to 48°, most particularly +/?45°, in relation to the main axis of rotation of the drive shaft component. The invention also concerns a method for producing a drive shaft component and a gas turbine engine.

Abstract: An internal combustion gas engine (2) is disclosed. It includes a cylinder arrangement (4) and a first compressor (6) for compressing a gaseous fuel and air mixture. The at least one cylinder arrangement (4) forms a combustion chamber (8) and includes an intake arrangement (10) for intake of charge gas, a sparkplug (12), and a pre-chamber (14). The engine (2) comprises a second compressor (16) for compressing a gaseous medium, and a pressure reducer (18). An outlet (20) of the first compressor (6) is arranged in parallel with an outlet (22) of the second compressor (16). The outlet (20) of the first compressor (6) is connected to the pre-chamber (14). The outlet (20) of the first compressor (6) and the outlet (22) of the second compressor (16) are connected to the pressure reducer (18). An outlet (24) of the pressure reducer (18) is connected to the intake arrangement (10).

Abstract: A fuel injection system (4) for an internal combustion engine has a low-pressure pump for delivering fuel from a fuel tank. The fuel is fed upstream of an injector (11) of the fuel injection system (4) to a mixing device (14). The mixing device (14) has a mixer housing (18) with a fuel connection (15) for receiving fuel and with at least one coolant connection (17; 28; 33) for receiving a coolant. For the purpose of bringing about efficient mixing of the fuel and the coolant, before a collision of a fuel jet (40) of the fuel and a coolant jet (41) of the coolant, the two fluid jets (40, 41) are formed to be at least partially aligned in the same direction.

Abstract: An evaporated fuel processing device that determines whether a normal state is established, by using pressures by a pressure detector while the evaporated fuel processing device shifts between: a first state where a purge passage is opened by a first valve, air passage is opened by a second valve, the purge passage is closed by a third valve, and a pump stops; a second state, after the first state, where the purge passage is opened by the first valve, the air passage is opened by the second valve, the purge passage is closed by the third valve, and the pump is operating; and a third state which takes place after the second state and where the purge passage is opened by the first valve, the air passage is closed by the second valve, the purge passage is closed by the third valve, and the pump stops.

Abstract: A canister includes a plurality of activated carbon layers for adsorbing vaporized fuel and a purge pump for introducing purge air into the canister to cause purge gas containing the vaporized fuel to flow out of the canister. At least a part of the purge pump is placed in the chamber defined between the activated carbon layers.

Abstract: A system for sustainable generation of energy, comprising at least one device for converting natural power into useful energy, and at least one internal combustion engine or heat engine. The internal combustion engine or heat engine may be connected to a gas cleaning device for fuel or heat supply. A method for sustainable generation of energy, comprising the steps of generating a first amount of useful energy by converting natural power; and generating a second amount of energy by operating at least one internal combustion engine or heat engine, wherein the internal combustion engine or heat engine is driven by fuel or heat derived from cleaning a waste gas.

Abstract: A method for manufacturing a waterproof felt duct may include (a) laminating a waterproof film on one side of a first nonwoven fabric and laminating a second nonwoven fabric on the waterproof film laminated on the first nonwoven fabric to form a laminated body; (b) forming a waterproof felt base material by thermally adhering the laminated body; (c) cutting the waterproof felt base material into a desired shape; (d) molding a duct while surrounding the waterproof felt base material cut into the desired shape around the external surface of a molding jig having a worm gear shape; (e) heat-treating the molded duct; (f) cooling the heat-treated duct; and (g) ejecting the cooled duct from the molding jig.

Abstract: A fuel injector is described which is able to be preassembled in a receiving opening of a fuel-distributor line in a loss-proof manner in a structural unit in the form of a fuel charge assembly for transport to the final assembly at the vehicle manufacturer. A radial support disk for preventing the loss of the fuel injector is disposed on the inflow-side end of the inlet pipe by press-fitting the radial support disk in the receiving opening. The fuel injector is particularly suitable for the direct injection of fuel into a combustion chamber of a mixture-compressing internal combustion engine having externally supplied ignition.

Abstract: There is described a method for and system for starting at least one engine from a twin engine installation.

Abstract: Low cost Pumped Hydro Energy Storage (PHES) sites have already been exploited; new PHES sites now cost $2 million per MW. A very large number of sites exist, not only on the coast but all over the land mass of all continents, that have an altitude difference of 100 m between two levels, where 1 to 5 million tonnes of solid can solid can safely be stored at both high and low levels. Thus solids like sand, crushed rock and soil can be used to provide virtually unlimited gravitational energy storage. Pumping slurry of solid/water to an upper level creates energy storage. When required, solid in slurry form flows down to the lower level, through a turbine. The turbine runs a generator releasing electrical energy. A relatively small amount water is recycled indefinitely create more slurry and transfer solid up/down as needed making solid pumped hydro feasible even in deserts.

Abstract: A method of coating an area of a wind turbine rotor blade comprises: defining an area to be coated on a surface of the blade, applying a first plurality of strips of masking tape to the surface of the blade proximate a first edge region of the defined area such that each strip is arranged adjacent to at least one other strip of said first plurality of strips, spraying a coating layer onto the defined area up to an innermost strip such that the innermost strip defines an edge of the coating layer, removing the innermost strip(s) to expose an uncoated region of the defined area between the edge of the coating layer and an innermost remaining strip and spraying a further coating layer over the previous coating layer and over the uncoated region up to said innermost remaining strip.

Abstract: To solve the problem of a mis-calibration of a wind turbine a computer-implemented method for re-calibrating at least one yaw-angle of a wind turbine starting from an initial yaw-angle calibration of said wind turbine, based on determining a turbulence intensity estimation value (20) related to said appropriate yaw-angle (10), wherein the turbulence intensity (TI) being a ratio of wind speed deviation to average wind speed over a pre-determined period of time. Further, to solve the problem of a mis-calibration of a wind turbine a system for re-calibrating at least one yaw-angle of a wind turbine based on above re-calibration method. Further, to solve the problem of a management of a wind park below optimum a computer-implemented method for wind park optimization based on simulation calculation including turbulence intensity estimation values (20) estimating said at least one effecting wind turbine (101,102,103) to suffer from wake from said at least one effected wind turbine (100,101,102).

Abstract: The present invention relates to operation of a wind turbine using a power storage unit, such as a rechargeable battery, to power a group of power consuming units during grid loss. The wind turbine comprises a number of power consuming units being grouped into at least a first group and a second group, a first electrical converter for connecting the generator to the electrical grid, and a second electrical converter for connecting the electrical generator to the power storage unit. Upon detecting an occurrence of the grid loss, the generator is operated to ensure sufficient power of the power storage unit to operate the first group of power consuming units.

Abstract: The object of the invention is a system recording the collisions of flying animals (9) with wind turbines (1) and indicating where they fell on the ground, which comprises a wind turbine (1) composed of a tower (2), a nacelle (3), a rotor (4) with blades (5) and a sensor unit comprising one sensor (6) and peripheral devices of the sensor, characterised in that the sensor (6) mounted on the nacelle (3) and/or tower (2) of the wind turbine (1) is a LIDAR sensor or a 3D light field camera or a 3D radar scanning the space around the wind turbine (1) in the field of view (7) of the sensor (6). The object of the invention is also the method of application of the above described system for recording the collisions of flying animals (9) with wind turbines (1) and indicating where they fell on the ground and the application of the system.