Abstract: Provided is a brush assembly for transferring lightning current between a first structure and a second structure, which brush assembly includes a holder realized for mounting to one of the two structures; a recess formed in the holder, which recess is shaped to accommodate a brush and to expose a first brush face; and a first displacement means arranged to move the first exposed brush face against a surface of the first structure; and wherein the recess is shaped to also expose a second brush face, and the brush assembly further includes a second displacement means arranged to move the second exposed brush face against a surface of the second structure. Further provided is a lightning protection circuit of a wind turbine; and a wind turbine.

Abstract: A vertical pump features a shaft having an end with an impeller arranged thereon and rotates about an axis; a stationary bushing having an axial bushing surface, a radial bushing surface, and a central bushing bore; and a thrust balance drum that includes a central balancing drum bore to receive the shaft, that couples to the shaft so as to rotate about the axis, that includes an axial balance drum surface and a radial balance drum surface, and that is arranged in the central bushing bore of the stationary bushing with the axial balance drum surface positioned with respect to the axial bushing surface to define an axial clearance, and with the radial balance drum surface positioned with respect to the radial bushing surface to define a radial clearance. In operation, the thrust balance drum balances thrust loads produced by the impeller.

Abstract: A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.

Abstract: A compressor of a gas turbine engine includes a rotor and a stator located downstream of the rotor. The stator has a plurality of vanes each with an airfoil extending span-wise between a root proximate an inner hub of the stator and a tip. A fillet is disposed at the leading edge of the root of the airfoil, and extends between a pressure side surface of the airfoil and the inner hub.

Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along the span. The frangible airfoil portion includes an exterior surface. The exterior surface at least partially defines at least one fusion cavity at least partially defining the frangible line. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span. The residual airfoil portion meets the frangible airfoil portion at the frangible line. As such, the frangible airfoil portion deforms or partially or fully detaches relative to the residual airfoil portion at the frangible line following an event creating imbalance.

Abstract: In an aspect, a pump is provided and includes a pump housing having a pump inlet and a pump outlet. An impeller is rotatably supported in the pump housing for rotation about an impeller axis, and has an impeller inlet configured for drawing in liquid during rotation of the impeller, and an impeller outlet configured for discharging liquid in a generally radial direction. A diverter is pivotally connected in an impeller outlet receiving chamber in the pump housing. The diverter is movable between a first position in which it provides a first restriction to flow out from the pump housing and a second position in which it provides a second restriction to flow out from the pump housing that is greater than the first restriction. In the first position, the diverter forms at least a portion of a volute around at least a portion of the impeller.

Abstract: A method of manufacturing a variable vane mechanism includes arranging a vane and a spacer between a first support structure and a tool member of a tool. The method also includes abutting a first inner surface of the first support structure against a first side surface of the vane and a second side surface of the vane against an opposing surface of the tool member, leaving a control surface of the spacer projecting from the first support structure at a predetermined distance. The method further includes fixedly attaching the spacer to the first support structure with the control surface of the spacer projecting from the first support structure at the predetermined distance. The method further includes abutting a second support structure on the control surface of the spacer to define a gap between the first support structure and the second support structure with the vane disposed within the gap.

Abstract: A blade outer air seal retention assembly may comprise a forward retention ring and an aft retention ring coupled to the forward retention ring. The forward retention ring may comprise a first shiplap flange extending aft from the forward retention ring. The aft retention ring may comprise a second shiplap flange extending forward from the aft retention ring.

Abstract: A wind turbine includes a wind direction sensor, a yawing system, and a control system for yawing the wind turbine rotor relative to the wind. The control system measures a wind direction parameter by the wind direction sensor Over time a group of data sets is obtained and a wind direction offset is determined from the group of data sets which is used to adjust the wind direction parameter. The adjusted wind direction parameter is then used in the controlling of the wind turbine.

Abstract: The present disclosure relates to a control device of an annular row of variable-pitch vanes for an aircraft engine. The device may include an annular row of actuating levers which each may include a first end attached to a pivot of one of the vanes and a second end connected to a control ring in rotation about an axis of rotation. The control ring may include at least one annular series of articulated links, wherein the second end of each lever carries a pivot connection articulating two successive links of the annular series about a single axis, the single axis extending in a direction substantially parallel to the axis of rotation.

Abstract: The present disclosure relates to a flow generating device for a heating, ventilation, and/or air conditioning system. The flow generating device includes a housing having a channel defining a flow path of a fluid and a fan blade having a rotational axis extending through the channel, where the fan blade is configured to rotate to force the fluid along the flow path. A portion of the fan blade axially protrudes beyond the channel in a direction generally aligned with the flow path and a winglet extends from the portion of the fan blade.

Abstract: A centrifugal blower includes an outer rotor, and a turbo fan. The turbo fan includes blades, an other end plate, and a cylinder portion. The cylinder portion is located inside the other end plate, and is fixed to the outer rotor. A surface of the outer rotor configures a rotor guide surface that guides an air flow toward a channel provided between adjacent blades. Each blade has a leading edge side portion located radially inside the cylinder portion. An outer end portion of the rotor guide surface in the radial direction is located at the same position in the axial direction as a one side cylinder end portion of the cylinder portion in the axial direction, in a state where a rotor contact portion of the outer rotor and a blade contact portion of the leading edge side portion are in contact with each other.

Abstract: A rotor blade for a wind turbine, wherein the rotor blade includes serrations along at least a portion of the trailing edge section of the rotor blade is provided. The serrations include a first tooth and at least a second tooth, wherein the first tooth is spaced apart from the second tooth. Furthermore, the area between the first tooth and the second tooth is at least partially filled with a plurality of comb elements, wherein the comb elements are arranged substantially parallel to each other and in substantially chordwise direction of the rotor blade such that generation of noise in the trailing edge section of the rotor blade is reduced. The rotor blade is further characterized in that it includes a plurality of ridges including a first ridge and at least a second ridge for manipulating an airflow which is flowing along the ridges.

Abstract: An output assembly for an accessory system of a gas turbine engine includes a first rotating member extending along an axis and including a mechanical connector for coupling the output assembly to an accessory system. The output assembly also including a second rotating member extending along the axis, the second rotating member coupled to the first rotating member at a first axial position and at a second axial position, the second rotating member coupled to the first rotating member at the second axial position through a one-way clutch. Additionally, the first rotating member of the output assembly further includes an extension member extending at least partially between the first axial position and the second axial position, the extension member including a designed fail point.

Abstract: A fan wheel structure includes a hub provided with a plate member and a plurality of blades. The plate member is located around the hub and has an upper side and a lower side. The blades are arranged on the upper side of the plate member and respectively have a connecting end connected to the hub as well as a free end. The blades respectively include a backward-curved section, a middle section and a forward-curved section. The backward-curved section is located adjacent to the connecting end and connected to the upper side of the plate member; the forward-curved section is located adjacent to the free end; and the middle section is connected at two opposite ends to the backward-curved section and the forward-curved section. And, an air passage is formed on the upper side of the plate member between any two adjacent backward-curved sections.

Abstract: A method of fabricating a filler body for a blade of a rotor. In addition, such a method comprises a succession of steps of adding material layer by layer, each step consisting in making a new layer of material on a preceding layer of material made in the preceding step, at least one of the steps consisting in making an openwork layer of material presenting a plurality of openings, the succession of steps of adding material layer by layer generating openwork layers of material, each having a closed outline, the respective closed outlines of the openwork layers of material touching mutually in pairs and forming a closed envelope of the filler body for the blade.

Abstract: A guide bearing system including a pad adjuster to traverse at least one bearing in a direction to adjust a radial clearance. The system can further include a sensor for measuring deviations in the radial clearance. In some embodiments, the guide bearing system includes a controller that receives a distance signal from the sensor measuring the radial clearance and signals the pad adjuster to traverse the at least one bearing to compensate for the deviations in the radial clearance.

Abstract: A heating, ventilating, and air conditioning (HVAC) system that includes a fan. The fan includes a plurality of blades coupled to a hub. A shroud is coupled to the plurality of blades, wherein the shroud focuses a flow of air along a rotational axis of the fan and reduces the flow of the air radially outward from the fan.

Abstract: A rotor assembly includes a plurality of rotor disks that each have a rim portion. The plurality of rotor disks includes a first rotor disk and at least one first bleed air passage that extends through a forward rim portion of the first rotor disk. At least one second bleed air passage that extends through an aft rim portion of the first rotor disk.

Abstract: A web locating device for locating a shear web at a predefined location on an inner surface of a wind turbine blade shell is described. The base comprises a base and a first guide structure. The base is for securing to the inner surface of the blade shell at a predefined position on the inner surface and the first guide structure projects from the base. The first guide structure has a first guide surface arranged to guide a mounting portion of the shear web towards the predefined location on the inner surface of the wind turbine blade shell. The base of the device includes one or more alignment features for aligning with one or more reference features at the predefined position on the inner surface of the blade shell. Also described are a wind turbine blade, and a method of making a wind turbine blade.