Abstract: A planetary gear box (and method of assembly), where the gear box includes a sun gear, a plurality of planet gears, a ring gear, a plurality of planet pins, an axially forward carrier plate and an axially rearward carrier plate. Each planet pin is fixed respectively at its axially forward end on the axially forward carrier plate and at its axially rearward end on the axially rearward carrier plate of the planetary gear box. The planet pin is of two-part design and forms a radially outer pin part and a radially inner pin part, which are connected to one another in a manner precluding relative rotation therebetween, wherein the radially outer pin part forms a bearing with the planet gear, and only the radially inner pin part is fixed at its axial ends to the forward and rearward carrier plates.

Abstract: A gearbox assembly includes a plurality of planet gears. At least one planet gear of the plurality of planet gears includes a layshaft that supports a first stage planet gear and a second stage planet gear. The at least one planet gear is characterized by a Radial Stage Distance greater than or equal to 30 millimeters and less than or equal to 100 millimeters. The Radial Stage Distance is Rrm1?Rrt2. Rrm1 is a first stage rim inner radius of the first stage planet gear and Rrt2 is a second stage root radius of the second stage planet gear.

Abstract: An acoustic monitoring system and method for the health status of an offshore wind turbine and an ocean wave are provided. The acoustic monitoring system includes a first laser transmitter, a second laser transmitter, a telephoto camera provided at a hub, a vibration detection sensor provided on a tower of a wind turbine, and four acoustic detection sensors arranged at an interval of 90° along the circumference of the tower. The first and second laser transmitters are arranged at the bottom of a nacelle of the wind turbine and emit laser lights vertically downward. The first laser transmitter, the second laser transmitter, the telephoto camera, the vibration detection sensor, and the acoustic detection sensors are connected to a data acquisition and conversion module through a transmission module. The acoustic monitoring system combines laser light detection with acoustic signal feature detection to improve stability and safety of the offshore wind turbine.

Abstract: A rotor blade is a rotor blade to be attached to a rotor shaft rotatable about an axis, and includes a blade body extending in a radial direction with respect to the axis and having a blade-shaped cross-section orthogonal to the radial direction; a fillet portion provided on a radial outer side of the blade body and having a hollow portion formed therein; a shroud provided on a radial outer side of the fillet portion and extending in a circumferential direction; and a seal fin projecting from the shroud to an outer circumferential side and extending in a direction intersecting the blade body when viewed from the radial direction. A wall thickness on a suction side of the fillet portion is greater than a wall thickness on a pressure side of the fillet portion on a leading edge side of the blade body as demarcated by an intersection portion between the blade body and the seal fin serving as a boundary.

Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

Abstract: Disclosed is a blade shell section of a wind turbine blade, such as wind turbine blade with a flatback section. The blade shell section extends in a longitudinal direction from a first shell section position to a second shell section position. The blade shell section comprises a first laminate layer forming the outer surface of the blade shell section and a second laminate layer forming the inner surface of the blade shell section. The blade shell section further comprising a first shell section and a corner shell section between the contour shell section and the flatback shell section.

Abstract: A gearbox assembly for a turbine engine including a drive shaft and a fan shaft. The gearbox assembly includes a first gear, a second gear, and a planet pin. The first gear is coupled to the drive shaft. The second gear is supported by a planet carrier. The planet carrier is coupled to the fan shaft. Torque is transferred from the drive shaft to the fan shaft through the gearbox assembly. The planet pin is disposed within the second gear. A planet pin shape of the planet pin includes a contoured portion that is characterized by a contoured portion deflection that is greater than or equal to ?4.2e-03 inches and less than or equal to ?1.2e-05 inches.

Abstract: Ceiling fans typically include a motor including a rotor and a stator, blades, a downrod, and a mounting assembly for suspending the fan from a structure. The mounting assembly includes fasteners and brackets to secure the ceiling fan to the structure. The bracket receiving the downrod is fastened to a plate that is secured to the ceiling.

Abstract: A main beam for wind turbine blade, comprising: one or more carbon fiber pultruded bodies, wherein, each carbon fiber pultruded body comprising one or more carbon fiber pultruded sheets, the carbon fiber pultruded sheets are stacked along the thickness direction and are formed by curing a first infusion material, wherein a glass fiber infusion material is arranged between every two carbon fiber pultruded sheets; one or more inlays, which are arranged adjacent to the carbon fiber pultruded body in a direction perpendicular to the thickness direction of the main beam; one or more overlays, which cover the carbon fiber pultruded bodies and/or the inlays on both sides in the thickness direction of the main beam; and a second infusion material, which impregnates carbon fiber pultruded bodies, the inlays and the overlays.

Abstract: A deposited material sensor is arranged, in a flow path of a gas from an inlet port to an outlet port, on an upstream side or a downstream side of a predetermined flow path position where a cause of disruption to operation of the vacuum pump is to occur. In addition, the deposited material sensor detects a presence or absence of deposited material at the arrangement position of the deposited material sensor, and the arrangement position of the deposited material sensor is a position where a thickness of the deposited material at the predetermined flow path position assumes a predetermined thickness that corresponds to a maintenance time of maintenance for suppressing the cause when a detection state of the deposited material sensor changes from deposited material absent to deposited material present.

Abstract: A method of operating a wind turbine generator comprising a plurality of blades, the method comprising iterating the following steps: comparing an indicated rotor speed with a rotor speed target to determine a rotor speed error; generating a modified rotor speed error by applying a control factor to the rotor speed error; controlling the pitch angle of the blades via a pitch control system in accordance with the modified speed error; and altering the control factor in dependence on a size of the indicated rotor speed.

Abstract: A mount is for attaching an accessory to a fan including a downtube. The mount includes a receiver adapted for connecting to the downtube. A retainer is adapted to receive the accessory. The retainer is adapted to support and rotate about the receiver so as to position the accessory in a desired orientation. Related methods of attaching an accessory to a fan are also disclosed.

Abstract: A turbofan engine has a primary duct, in which there flows a primary flow at a primary pressure and a secondary duct, which radially surrounds the primary duct and in which there flows a secondary flow at a secondary pressure. The primary duct includes at least one compressor configured to compress the primary flow, a turbine driving the compressor in rotation and a combustion chamber designed to receive, at an inlet, the primary air flow compressed by the compressor. The turbomachine further includes a cooling circuit extending between the compressor and the turbine. The cooling circuit has an air flow rate regulating device arranged upstream of the turbine and having at least one valve that is configured to move between an open position and a closed position, located between the compressor and the combustion chamber in the primary duct and the pressure (PS) in the secondary duct.

Abstract: A hoist for lifting at least a portion of a gas engine assembly includes a support member including an upper portion, a lower portion, and a connecting portion extending therebetween. The hoist also includes an elongate member coupled to the lower portion of the support member and extending substantially orthogonally to the lower portion, and at least one bracket slidably engaged with the elongate member and axially translatable along a length of the elongate member. In addition, the hoist includes a plurality of linkage members coupled to the at least one bracket, where each linkage member of the plurality of linkage members is configured to attach to at least a portion of the gas engine assembly.

Abstract: Accelerators, methods of manufacturing accelerators, and gas turbine engines are provided. For example, an accelerator for a gas turbine engine defines a radial direction and an axial direction and comprises an annular outer wall, an annular inner wall, an annular channel defined between the outer and inner walls, and a plurality of vanes disposed within the channel. The channel has an inlet for ingress of a cooling fluid and an outlet for egress of the cooling fluid. Each vane extends from the outer wall to the inner wall adjacent the outlet, which is angled such that an exit angle of the cooling fluid is nonzero with respect to both the radial and axial directions. The accelerator may be manufactured using an additive manufacturing method. The accelerator outlet may be disposed immediately upstream of a first turbine rotor blade stage of a gas turbine engine to direct the cooling fluid thereto.

Abstract: A fan includes a motor, a rotatable hub coupled to the motor, and at least one fan blade. The at least one fan blade includes a first end coupled to the rotatable hub, a second end, a leading edge, a trailing edge, a passage extending from the first end to the second end, and a winglet attached to the second end. At least one flexible strap extends through the passage of the at least one fan blade. The flexible strap is coupled at a first end to the rotatable hub and coupled at a second end to the winglet, such as to an inner portion thereof within the passage.

Abstract: A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction.

Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.

Abstract: A turbofan engine having one or more heat exchangers tied to an accessory gearbox is provided. The accessory gearbox is mechanically coupled with a spool, and a hydraulic pump is mechanically coupled with the accessory gearbox. The one or more heat exchangers have a heat exchanger capacity defined by a product raised to a half power, the product being determined by multiplying a resultant heat transfer surface area density of the one or more heat exchangers by a heat conductance factor that relates an accessory gearbox heat load, a power of the hydraulic pump, a diameter of a fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 23.9 and 97.7 for a rotational speed of the spool between 7,500 and 35,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 4,000 m2/m3 and 13,000 m2/m3.

Abstract: A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.