Abstract: A fixed-wing aircraft at least includes at least one vortex generator movable through an outer surface of the aircraft between a retracted state and a fully extended state by at least one electric motor, the at least one electric motor being exclusively adapted to actuate this at least one vortex generator, and including an electronic control unit adapted to control operation of the at least one electric motor for actuation of the at least one vortex generator.

Abstract: A device configured to generate an air flow, the device including: a compressor; an air flow duct arranged to convey a flow of air generated by the compressor; a gas-filled cavity disposed beside the air flow duct; a wall separating the air flow duct and the cavity, the wall including at least one aperture; and an acoustic resistive screen covering and held in tension over the aperture of the wall. The screen is in fluid contact with air in the air flow duct and gas in the cavity and is configured to resist air flow between the duct and the cavity. The resistive screen and the cavity together define a noise-damping resonator.

Abstract: A fan includes a rotor; a stator; a first bearing assembly disposed at a radial outer side of an end of the rotor; and an impeller including an impeller body, where the impeller body is provided with a receiving cavity for receiving the first bearing assembly; and one end of the first bearing assembly is disposed in the receiving cavity, and the rotor, the first bearing assembly and the impeller body are disposed coaxially.

Abstract: A heat source unit for a heat pump having a refrigerant circuit, the heat source unit having: an outer casing including a bottom plate; and a compressor assembly accommodated in the outer casing, the compressor assembly including a compressor of the refrigerant circuit of the heat pump including a compressor housing, a support plate supporting the compressor, the support plate being mounted via dampers to the bottom plate, and a compressor casing enclosing the compressor and the compressor housing. A damping mechanism is arranged between the compressor and the support plate, and the compressor casing is fixed to the support plate out of contact with the compressor housing.

Abstract: A balancing and sealing piston system for an integrated motor compressor is described. The system comprises a balancing piston designed to be mounted on a shaft of a motor compressor to compensate for the differential pressure applied to the impellers of the compression section of the motor compressor, and a sealing device surrounding the balancing piston and designed to be mounted on a case of the motor compressor to seal part of the compression section. The system further comprises a gas extraction port, the axial position of which is determined such that the pressure value of extracted gas is equal to a predetermined value that is less than the value of the discharge pressure.

Abstract: A resonator insert (14) is provided for coaxial and sectionally radially spaced insertion in an intake pipe of a turbocharger (10). The resonator insert (14) has a tube section (141) with a wall having circumferentially extending, axially adjacent through-slots (142). The wall of the tube section (141) carries at least one radially outwardly directed, axially extending lamella (144) crossing the through-slots (142). A turbocharger with an upstream resonator also is provided.

Abstract: Disclosed examples include an airfoil comprising: a pressure side and a suction side that are coupled together at a substantially radial trailing edge of the airfoil, wherein the substantially radial trailing edge is downstream from a leading edge, the leading edge including a sweep feature of a variable chord length, the variable chord length to include: a first increase in chord length and a decrease in chord length along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and a second increase in chord length along the radial length from the hub end to the opposite tip end, the second increase different than the first increase.

Abstract: Disclosed herein is a blade for a turbine comprising a blade cover; a blade body; and a layer of adhesive disposed between the blade cover and the blade body; where the layer of adhesive comprises a first adhesive region and a second adhesive region; where the first adhesive region comprises an adhesive that is chemically different from an adhesive used in the second adhesive region.

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan case and a fan track liner. The fan case that extends circumferentially about an axis. The fan track liner extends circumferentially at least partway about the axis and is coupled with the fan case. The fan track liner includes an abradable section and a core section located radially outward of the abradable section. The core section defines a triply periodic minimal surface geometry.

Abstract: An acoustically insulated machine including a source of noise positioned within a housing, a first insulation member positioned within the housing and including a first porous sound absorbing layer and a first dense layer, and a second insulation member positioned within the housing and including a second porous sound absorbing layer and a second dense layer. The first insulation member being is positioned closer to the internal source of noise than the second insulation member and the first insulation member being spaced apart from the second insulation member such that an air gap is formed between the first insulation member and the second insulation member.

Abstract: A turbofan engine defining a circumferential direction is provided. The turbofan engine includes: a turbomachine, the turbomachine defining a pylon attachment location along the circumferential direction; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes including NOGV number of outlet guide vanes, the plurality of outlet guide vanes including a first outlet guide vane and a second outlet guide vane adjacent the first outlet guide vane, the first and second outlet guide vanes defining a gap spacing greater than 360 degrees divided by NOGV, and the pylon attachment location positioned outside of between the first and second outlet guide vanes along the circumferential direction.

Abstract: An electronic system includes a fan module, a reference microphone, a micro speaker module, and an active noise cancellation controller. The micro speaker module provides a noise-cancellation signal according to a micro speaker control signal for canceling the noises generated during the operation of the electronic system. The reference microphone outputs a wide-band noise signal associated with the operation of the fan module. The active noise cancellation controller outputs a virtual error signal according to a first transfer function between the reference microphone and a physical microphone when the fan module operates with a predetermined fan speed, a second transfer function between the micro speaker module and the physical microphone when the fan module is not in operation, and the wide-band noise signal. The active noise cancellation controller provides the micro speaker control signal according to a synchronization signal, the wide-band noise signal and the virtual error signal.

Abstract: A method and system for noise cancellation is disclosed. In one embodiment, the method may include receiving, from a first sensor, a first signal indicative of a noise generated by an equipment. The first sensor may be configured to generate the first signal indicative of the noise generated by the equipment. The first sensor may be positioned in proximity to the equipment. The method may further include generating a noise cancellation signal based on the first signal and triggering a speaker to generate a sound corresponding to the noise cancellation signal, wherein the speaker is positioned in proximity to the equipment.

Abstract: Disclosed is a leading edge protection element for a wind turbine blade, the leading edge protection element extending in a longitudinal direction between a first edge and a second edge and extending in a transverse direction between a third edge and a fourth edge, the leading edge protection element having a first surface and a second surface. The leading edge protection element comprising a film layer having a first film surface and a second film surface, the first film surface forming the first surface of the leading edge protection element, wherein the film layer comprises a metal material. The leading edge protection element comprising a rubber layer of a rubber material having a first rubber surface and a second rubber surface, the second rubber surface forming the second surface of the leading edge protection element, wherein the second film surface and the first rubber surface are bonded to each other.

Abstract: The present disclosure relates to a two-vane pump for wastewater and a design method of a two-vane pump for wastewater using machine learning, and more particularly, a design method of a two-vane pump using machine learning capable of having efficiency of a target head and performing optimal design for sizes of solids that can pass through and a two-vane pump for wastewater according to the machine learning.

Abstract: An air pump device includes an electric pump unit including a pump mechanism and a motor configured to drive the pump mechanism, a case housing the electric pump unit, and a vibration-proof member interposed between the electric pump unit and the case. The vibration-proof member is a plate-shaped member made of an elastic resin material and is wound around the electric pump unit to wrap the electric pump unit therein. A part of the vibration-proof member is sandwiched between the electric pump unit and one of facing surfaces that are inner surfaces of the case and face each other inside the case. Another part of the vibration-proof member is sandwiched between the electric pump unit and the other one of the facing surfaces.

Abstract: A compressor includes a rotation shaft which rotates around an axis, an impeller which press-feeds a fluid from one side in an axial direction toward an outward side in a radial direction by rotating together with the rotation shaft, a casing which surrounds the rotation shaft and the impeller and in which an exit flow channel for introducing a fluid press-fed from the impeller is formed, and an acoustic liner which is provided so as to face the inside of the exit flow channel in the casing. The acoustic liner has a plurality of open hole portions which are arranged with intervals therebetween, and acoustic spaces which communicate with the open hole portions and are independently provided for the respective open hole portions.

Abstract: The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing (23) comprising: —an annular shell (29) with axis A; —an annular element (24; 253, 254) attached to the inside of the shell (29), the annular element comprising a body (25) made of NIDA-type cellular material and comprising a downstream portion (252) covered with an abradable material (26), and an upstream portion (251) without abradable material, the body (25) extending in a continuous manner from the upstream portion (251) to the downstream portion (252), the method comprising: —manufacturing the annular element in the form of a continuous annular body, —cutting the annular body into segments (253, 254), —attaching the segments to the shell, and —depositing the abradable material (26) onto the inside surface (25a) of the downstream portion (252).

Abstract: Acoustic structures for a gas turbine engine are disclosed. In various embodiments, the acoustic structures comprise a panel in the form of a cellular structure having a plurality of cells; and a housing configured to house the cellular structure, the housing including a first rail configured for attachment to a static structure within the gas turbine engine and a second rail configured for attachment to the static structure. In various embodiments, the acoustic structures comprise a liner in the form of a non-segmented or two-piece structure configured to extend about the inner barrel of a nacelle structure. The disclosed panels and liners are configured to maximize the operational area of the acoustic structures by eliminating obstructions from adjacent flow paths.

Abstract: A structure is provided that includes a perforated first skin, a second skin and a core. The core includes a first sidewall, a second sidewall, a first baffle and a second baffle. The core forms a plurality of cavities vertically between the perforated first skin and the second skin. The first baffle is connected to the perforated first skin at a first baffle first end. The first baffle is connected to the second skin at a first baffle second end by a first moveable joint. The second baffle is connected to the perforated first skin at a second baffle first end. The second baffle is connected to the second skin at a second baffle second end. A first of the cavities extends laterally between the first sidewall and the second sidewall. The first cavity extends longitudinally between the first baffle and the second baffle.

Abstract: A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The casing may itself at least in part define an annular gap that functions as a nozzle for the rocket booster, with protruding tabs on the casing aiding in maintaining a uniform height of the annular gap. The rocket booster may be mechanically coupled to an object protruding from the back of a fuselage of a flight vehicle, such as a missile. For example, the rocket booster may be placed around an aft turbojet nozzle of the flight vehicle. This allows the rocket booster to be used in situations where primary propulsion must be running both before and after (and perhaps during) the firing of the rocket booster.

Abstract: A foreign object debris (FOD) detection system for a gas turbine engine comprises a light detection and ranging (LiDAR) sensor assembly. The LiDAR sensor assembly is configured to scan a pre-determined volume within an inlet of the gas turbine engine. The inlet may be defined by a nacelle of the gas turbine engine. The LiDAR sensor assembly may comprise a single transceiver, a transmitter and a receiver, a plurality of transmitters and a receiver, or a plurality of receivers and a transmitter.

Abstract: An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise: a first shroud configured to be disposed around a rotor of the UAM vehicle, the first shroud comprising: a radially inner wall configured to be spaced radially outward from a blade tip of a rotary blade of the rotor, the radially inner wall including a perforated portion; and a hollow chamber defined by an internal surface of the first shroud and the radially inner wall.

Abstract: A ceiling fan module with an energy dissipation function and a configuration method thereof are disclosed. The ceiling fan module includes a fan rack, a fan and an energy dissipation assembly. The energy dissipation assembly passes through the fan rack and the fan and connects the fan rack and the fan; the energy dissipation assembly includes steel cables (3), high-damping vibration attenuation rings, fasteners and balancing weights; two high-damping vibration attenuation rings are sleeved on one steel cable, and the two high-damping vibration attenuation rings are respectively located at two ends of the steel cable; the high-damping vibration attenuation rings are mounted on the fan rack and the fan and separate the fan rack from the fan; the fasteners are mounted on the steel cables and are located on outer sides of the high-damping vibration attenuation rings and the fan rack.

Abstract: A propeller fan assembly that generates lower sound pressure during operation and minimizes blade deflection without sacrificing performance. The blades of the propeller fan comprise silencer seeds located on the suction side of the blades, closer to the leading edge and the tip of the blades. The silencer seeds are sized in increasing face area and form an array with areas increasing with each row. The propeller fan assembly also comprises a dual hub comprising more than one circumferential layer concentric with the axial fan's hub. Multiple circumferential layers provide significant additional support to the blades during operation. This minimizes blade deflection and preserves the performance of the blade as intended. The overall fan and orifice assembly uses a unique assembly method that allows for wide flexibility and permits use of motors of different types and sizes seamlessly with this propeller fan assembly.

Abstract: A cover for a compressor defines an accommodating space configured to receive the compressor. The cover includes a first cover that is configured to be spaced apart from an outer surface of the compressor and that define a first portion of the accommodating space, and a second cover that is detachably attached to the first cover and configured to be spaced apart from the outer surface of the compressor and that defines a second portion of the accommodating space. The first cover and the second cover are configured to reduce transmission of noise generated from the compressor to an outside of the accommodating space.

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. A row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths. A method of operation for a gas turbine engine is also disclosed.

Abstract: A rotor shroud for a rotary machine in a cabin air compressor includes a disk portion centered on a central axis of the rotor shroud, a frustoconical portion extending from the disk portion, a flared portion extending from the frustoconical portion, and a variable lattice structure in an interior of the rotor shroud. The variable lattice structure includes a first region of the rotor shroud having a first lattice structure and a second region of the rotor shroud having a second lattice structure. The second lattice structure of the second region is denser than the first lattice structure of the first region. The second region is a deflection region, a stress region, or an energy containment region of the rotor shroud.

Abstract: A gas turbine engine according to an aspect of the present disclosure includes, among other things, a propulsor section, a compressor section including a first compressor and a second compressor, and a turbine section including a first turbine and a second turbine. The first compressor includes a plurality of arrays of airfoils defining a plurality of compressor stages. A number of airfoils in each downstream array of the plurality of arrays is a factor (F) of a number of airfoils in a respective immediately upstream array of the plurality of arrays. The factor (F) is between 1.19 and 1.55 for each of the downstream arrays of the first compressor.

Abstract: A power transmission system includes a shaft, a stator disposed within the shaft and substantially concentric with the shaft; and at least one supporting element positioned between the stator and the shaft and configured to support the shaft on the stator to reduce a vibration of the shaft and allow the shaft to rotate relative to the stator. A gas turbine engine including the power transmission system is also described.

Abstract: Disclosed fans include an impeller and a guide device. The impeller is configured to generate an air flow path having an upstream direction and a downstream direction, and the guide device is positioned in the flow path located on an upstream side of the impeller. The guide device is configured as an intake grid having flat webs having branches and node points, and the webs form a plurality of flow channels configured as grid cells. The webs extend either between two branches or between one branch and a border area and each branch may include three webs that meet. In one configuration, flow channels include channels having a honeycomb cross section. In other example, flow channels may have a rectangular, pentagonal, and/or hexagonal shape. The fan further includes an inlet nozzle having an inlet area, and the guide device is located upstream from the inlet area of the inlet nozzle.

Abstract: A shroud unit has multiple stay members for supporting an electric motor, which rotates a fan unit having multiple blade members. Each of the blade members is inclined with respect to a radial direction of the fan unit in a predetermined circumferential direction. The stay members include a first stay member and multiple second stay members. Each of the second stay members is inclined with respect to the radial direction in a circumferential direction opposite to the predetermined circumferential direction. The first stay members is inclined with respect to the radial direction in the predetermined circumferential direction. The first stay member is located at a position overlapping with one of air-flow areas of a circular opening formed in the shroud unit, when viewed it in a direction along a rotational center axis of the electric motor.

Abstract: Disclosed examples include a retrofit fan frame assembly, comprising: a leading edge adjustment component coupleable to an airfoil, the leading edge adjustment component of variable chord length, the variable chord length to increase and then decrease along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and an attachment mechanism configured to couple the leading edge adjustment component to a leading edge of the airfoil.

Abstract: A cooling fan creating a more stable airflow for heat-removing purposes, with reduced noise of operation, comprises a rotor hub and preferably an odd number of blades mounted on periphery of the rotor hub in unequal intervals. Adjacent blades are configured with different shapes, reducing the noise generated during operation without affecting the cooling effect.

Abstract: A noise abatement system for internal combustion engines comprising: a containment body (12) equipped with an inlet hole (6) for the entry of exhaust gases from an internal combustion engine, a plurality of expansion chambers (10) placed in sequence and separated by parallel dividing partitions (13), each equipped with a through-hole (4) for the passage of gases placing in fluid communication two neighboring expansion chambers (10); said expansion chambers (10) having two opposing through-holes (4), one as gas inlet and one as gas outlet. A rotating shaft (9) is integrated in a rotating turbine (1), along an axis comprising the center of gravity of the expansion chambers (10) up to an opposite end of the containment body (12), said rotating shaft (9) having placed around said axis and on said shaft (9) rotary fins (3) which open and close the through-holes (4) between expansion chambers (10) alternately and generating a swirling movement of the flow of gas entering each expansion chamber (10).

Abstract: A three-bladed impeller providing a cooling airflow in air, with increased heat-dissipating efficiency and reduced noise includes a hub and three blades, the blades are arranged around the hub. Each blade is arched along its axial length from the front of fan to the back and also arched radially from the hub end of each blade to the outside tip. The back edge of each blade includes first and second slots, arranged alternately, the width of each first slot is ?1, the width of each of each second slot is ?2, the comparative sizes between ?2 and ?1 are in a ratio range of 1.6:1 to 1.8:1 (?2:?1).

Abstract: A compressor comprising: a stator assembly comprising a plurality of stator elements; a rotor assembly comprising a shaft to which is mounted at least one bearing, a permanent magnet and an impeller; a support body; and an outer can comprising an air inlet. The support body comprises a hollow elongate central part to which is mounted the at least one bearing, and inside which the magnet is positioned, the elongate central part comprising a plurality of openings, and the air inlet of the outer can is axially aligned at least partially with the plurality of openings in the elongate central part.

Abstract: A centrifugal fan includes a housing and an impeller. The housing includes a sidewall, and the sidewall includes a tongue portion. The impeller includes a fan hub and a plurality of blades. The fan hub is rotatably disposed in the housing, and the tongue portion has an inner contour line on a reference plane. The blades connect to the fan hub. Each one of the blades has an end surface facing the sidewall. The end surface has an outer contour line on the section of the blade. Any two adjacent blades have different outer contour lines. The outer contour line of at least one first blade of the plurality of blades is parallel to the inner contour line. The outer contour line of at least one second blade of the plurality of blades is not parallel to the inner contour line.

Abstract: A blower unit, particularly for an apparatus for assisting respiration, comprises a housing (2), an impeller (1) accommodated in an impeller chamber (3) in the housing (2), and a motor (12), connected to the impeller (1) via a shaft (15), which is accommodated in a motor chamber (13) in the housing (2). The motor (12) is fixed between walls (14, 18) of the motor chamber (13) by means of buffers, with at least one of the buffers being a sealing ring (16) which separates the shaft (15) from a passage for cooling air (33) which, in radial section, extends annularly around the motor (12).

Abstract: A compressor housing for a turbocharger may include an outer volute having an outer volute inner surface with a clamp groove defined therein, and an inner volute having an inner volute outer surface and an axially facing surface. The inner volute is inserted into the outer volute through the outer volute inner surface with the inner volute outer surface facing the outer volute inner surface. The inner volute is positioned with the axially facing surface disposed axially inward of the clamp groove. A clamp plate includes a radially outward portion inserted into the clamp groove and a radially inward portion extending downward past the inner volute outer surface. The clamp groove and the axially facing surface engage the clamp plate to retain the inner volute within the outer volute when an axial load is applied to the inner volute.

Abstract: A vane arc segment includes an airfoil fairing that has an airfoil wall that defines a fairing platform and a hollow airfoil section. A spar has a spar platform adjacent the fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg is spaced from the airfoil wall in the hollow airfoil section such that there is a first gap. The spar platform is spaced from the fairing platform such that there is a second gap. A support platform is secured to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. There is a spring seal between the spar platform and the fairing platform. The spring seal biases the airfoil fairing toward the support platform and seals the first gap from the second gap.

Abstract: This invention relates to a noise reducing device and a wind turbine blade comprises such a noise reducing device. The noise reducing device comprises noise reducing elements projecting from a base part towards a second end. Airflow modifying elements projects further from the base part towards a first end. The noise reducing elements and airflow modifying elements are arranged on opposite sides of the base part and preferably have different dimensions and/or shapes.

Abstract: A forced-draft pre-mix burner device has a housing that conveys air from an upstream cool air inlet to a downstream warm air outlet. A heat exchanger warms the air prior to discharge via the warm air outlet. A gas burner burns an air-gas mixture to thereby warm the heat exchanger. A fan mixes the air-gas mixture and forces the air-gas mixture into the gas burner. The fan has a plurality of blades having sinusoidal-modulated blade spacing.

Abstract: An air inlet (3) for a nacelle (2) for an aircraft (1) includes at least one acoustic panel (5), adapted to lower noise generated by the engine (21) to which the air inlet (3) is connected. At least one lip (6) defines the profile upon which an airflow flowing into the air inlet (3) acts. If necessary, at least one engine ring (4) is adapted to allow the air inlet (3) to be connected to an engine (21) of the nacelle (2). If necessary, at least one outer barrel (7) is adapted to define the outer shape of the air inlet (3) upon which an airflow acts. The air inlet (3) is manufactured as one single piece, made of a composite material.

Abstract: A blower apparatus includes an impeller and a casing that accommodates the impeller. The casing includes an upper wall including an intake port, a lower wall, a side wall that includes an exhaust port, and a tongue portion connected to the upper wall. The side wall includes a first side wall, and a second side wall disposed downstream in a rotational direction of the impeller relative to the first side wall via the exhaust port. The tongue portion extends from the second side wall toward the first side wall, and includes a lower portion opposed to the lower wall. The lower portion includes a first lower portion on the base end side and a second lower portion on the tip side. A distance between the first lower portion and the lower wall is shorter than a distance between the second lower portion and the lower wall.

Abstract: The present disclosure relates to a drainage device and a dishwasher having the same. The drainage device includes a drain pump including a drain port for discharging water, a drain pipe guiding discharge of water discharged from the drain pump, an air chamber in which the drain pump is connected to an upper portion thereof and the drain pipe is connected to a lower portion thereof, and an air pump configured to inject air into the air chamber, thereby more surely blocking the backflow of water to the drain pump by air injected into the air chamber through the air pump.

Abstract: The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

Abstract: A fan includes a motor, an impeller and a stator. The fan defines an air flow passage between an air inlet and an air outlet. The fan has a mode of operation and an arrangement such that, in use, the trajectory of the air flow through the air inlet is up to 360° in a direction which is generally perpendicular to the axis of rotation of the impeller. The trajectory of the air flow through the air outlet is up to 360° in a direction which is generally perpendicular to the axis of rotation of the impeller, and the air flow through the air flow passage turns generally 180°. The fan has a mode of constant operation, and, in this mode, the operating point of the fan falls with the stall region of the fan characteristic.

Abstract: This disclosure provides an air moving device with blade tip of variable curvature. The axial air moving device includes a hub and a plurality of blades. The blades are connected with the hub, and each blade is configured by stacking multiple wing sections continuously. Each blade includes a blade root and a blade tip. The span position of the blade at the blade root is defined as 0, and at the blade tip is defined as 1. The blade angle is defined by the nose-tail line of the wing section and the rotation direction of the axial air moving device. The blade angle of the wing section at the blade tip of the blade is at least 10 degrees less than the blade angle of the wing section at the span position of 0.8 of the blade.

Abstract: A fairing for a power generation machine, the fairing comprising: a first layer comprising a metallic material and defining a first surface and a second opposite surface, the first layer being configured to enable the fairing to be coupled to the power generation machine; and a second layer comprising a composite material and defining a first surface and a second opposite surface, the second layer being coupled to the first layer, the second surface of the second layer defining an external surface of the fairing.