Abstract: Examples of the present disclosure generally relate to wind turbine blades configured to minimize or eliminate buildup of ice on the blades. In order to maintain an ice free surface on a wind turbine blade, one or more ETH panels are embedded in the wind turbine blade to heat the wind turbine blade. One or more busbars are electrically connected to each of the one or more ETH panels for conducting electrical power to the ETH panels. The busbars may be disposed in an overlapping configuration to provide uniform heating of the wind turbine blade.

Abstract: An anterior part of a nacelle of an aircraft propulsion unit having an air inlet lip at the front end, an internal structure and an external panel extending the air inlet lip, and an annular rigidifying frame having an external peripheral edge connected to the external panel is disclosed. The anterior part of the nacelle includes a shock-absorbing element connected rigidly on the one hand to an internal peripheral edge of the rigidifying frame and on the other hand to the internal structure.

Abstract: A wind turbine blade (10, 610) for a rotor of a wind turbine (2) having a substantially horizontal rotor shaft is described. A surface mounted device (70, 70?, 170, 270, 370, 470, 570, 670, 770) is attached to a surface of the wind turbine blade (10). The surface mounted device (70, 70?, 170, 270, 370, 470, 570, 670, 770) is attached to the surface of the wind turbine blade (10, 610) via at least a first attachment part (77, 77?), which is connected to a part of the surface mounted device (70, 70?, 170, 270, 370, 470, 570, 670, 770). The attachment part (77, 77?) comprises a flexible housing (80, 80?, 680, 780) that forms a cavity (81, 81?, 681, 781) between at least the housing (80, 80?, 680, 780) and the surface of the wind turbine blade (10, 610). The cavity (80, 80?, 680, 780) is filled with an adhesive that provides an adhesive bonding to the surface of the wind turbine blade (10, 610).

Abstract: A balance weight assembly for a rotor blade of a rotorcraft. The balance weight assembly includes a balance weight pocket formed by a balance weight tray and a cover. The balance weight tray has an upper surface including a lip region extending outwardly from a projected region with an outboard boss. A balance weight receiving cavity is recessed from the upper surface and contains a plurality of balance weights. The projected region is disposed within an opening in a hollow blade spar such that the outboard boss of the balance weight tray has a contact relationship with an outboard surface of the opening. The cover is coupled to the balance weight tray such that the lip region of the balance weight tray and at least a portion of the cover have a clamping relationship with the blade spar, thereby coupling the balance weight pocket to the blade spar.

Abstract: A yaw sensor for a wind turbine comprises a plurality of rotary switches, each configured to be coupled to a yaw drive gearbox of a wind turbine nacelle, the rotary switches each being operable to activate and deactivate respective associated electrical contacts in dependence on an amount of yaw rotation of the nacelle relative to a start position. Each electrical contact is active at a plurality of first yaw rotation ranges with respect to the start position, and inactive at a plurality of second yaw rotation ranges with respect to the start position, the first and second yaw rotation ranges being interleaved.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has an elongated seal body having a seal face that bounds a gas path and an opposed impingement face. The seal body defines an internal cavity extending in a circumferential direction between opposed mate faces and extending in a radial direction between walls of the seal body defining the seal and impingement faces. A baffle divides the internal cavity into at least a first region and a second region. The first region has a first section extending transversely from a second section. The first section has a component in the radial direction, and the second section has a component in an axial direction such that the second region is defined between the baffle and the walls of the seal body defining the seal face. A method of sealing is also disclosed.

Abstract: A rotorcraft having a rotor system including a yoke, a plurality of grip assemblies, each of which is hingedly attach a rotor blade to the yoke, a plurality of flap stops, each flap stop attached to a respective grip assembly, a channel bounded by an upper and lower retaining surfaces, and a droop ring slideably disposed in the channel of the droop limiting system. The droop ring has a body with an inner surface, an outer surface, and a first end surface between the inner surface and the outer surface. The droop ring further has a first wear element removably disposed at the first end surface and extending above the first end surface and spaces the first end surface apart from the channel. Each flap stop is arranged to contact the outer surface of the droop ring and limit a downward droop of the respective rotor blade.

Abstract: A sealing ring element of a turbomachine includes: a sealing portion with a first area and a second area, with the inner surface of a first area being at the same radial distance from the axis of the turbomachine. The sealing portion includes an annular cavity which opens into an inner surface of the second area and extends into the first area, the annular cavity defining an upstream lateral wall and/or a downstream lateral wall forming an angle which is strictly between 0 and 90°.

Abstract: A wind turbine blade includes a lengthwise portion that extends between a root region and a tip region of the wind turbine blade. The lengthwise portion includes a cross section in which a first region surrounds a second region. The densities of the first and second regions vary with the first density being greater than the second density. The lengthwise portion includes a surface layer that bounds the first region, forms an exterior surface, and is configured to resist environmental degradation. At least one structural element extends longitudinally through the first region and is configured to reinforce the blade during use of the wind turbine. The lengthwise portion of a wind turbine blade may be made through an additive manufacturing process by depositing a main body in a plurality of layers. Each layer may be deposited in a plane generally parallel to a longitudinal axis of the lengthwise portion.

Abstract: A guide vane arranged in an air flow from a fan of an twin-spool aircraft engine, the aerodynamic part of the vane including an internal lubricant cooling passage partly delimited by an extrados wall and an extrados wall of the vane. The passage is equipped with a heat conduction matrix compressed between the walls and separating a first lubricant circulation space from a second lubricant circulation space. Furthermore, the matrix defines firstly first contact elements of the intrados wall formed in the first space and between which the lubricant from the first space will circulate, and secondly second contact elements of the extrados wall formed in the second space and between which the lubricant from the first space will circulate.

Abstract: An inertia weight assembly positionable within a receiving portion of a rotor blade for use on a rotorcraft. The inertia weight assembly includes a weighted core and a casing having a closed outboard end and forming a cavity. The weighted core is disposed in the cavity such that the casing at least partially encloses the weighted core. The weighted core is formed from a first material and the casing is formed from a second material that is dissimilar to the first material. The casing provides an interface between the weighted core and the receiving portion of the rotor blade. The second material is more bondable to the receiving portion of the rotor blade than the first material.

Abstract: The present invention includes a rotor-blade span-balancing system, including a span-balance pocket in a surface of a rotor blade; a cover operably configured to cover the span-balance pocket, wherein the cover is operably configured to be substantially flush with the surface of the rotor blade surface when covering the span-balance pocket, and wherein the cover includes a cover boss for reacting centrifugal force of the cover into the rotor blade; and one or more span-balance weights attached to the cover to span-balance the rotor blade.

Abstract: A rotor blade having a suction side and a pressure side for a wind power installation, comprising: a rotor blade root of a hub region for the attachment of the rotor blade to a rotor hub, and a rotor blade tip arranged toward that side of a tip region which is averted from the rotor blade root. In the region of the hub region, the rotor blade has, at least in part, a thickness profile which has a thorn-like extension at its trailing edge, wherein, in the region of the hub region, the thickness profile has, at least in part, a first thorn-like extension at the trailing edge at the suction side, and a second thorn-like extension at the trailing edge at the pressure side, and, in the region of the hub region, the thickness profile has, at least in part, a flow stabilizer and/or a vortex generator on the suction and/or pressure side.

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor having a hub carrying a plurality of blades, the hub rotatable about a longitudinal axis, and a seal extending outwardly from the hub to establish a sealing relationship with a plurality of vanes distributed about the longitudinal axis. A flow guide assembly is secured to an engine static structure such that a flow path is defined between the hub and the flow guide assembly. The flow path has an inlet portion defined along the seal and an outlet portion, and the flow guide assembly includes an acoustic liner that extends along the flow path.

Abstract: A centrifugal well pump assembly has a non-rotating diffuser between upper and lower rotating impellers. The upper impeller has a cylindrical skirt on a lower side that rotates within a diffuser receptacle. The lower impeller has a cylindrical balance ring on an upper side that rotates within a diffuser cavity. Impeller sleeves are bonded to the skirt and balance ring. Diffuser sleeves are bonded to the diffuser receptacle and cavity. The diffuser sleeves are of a harder material than the impeller sleeves. Each of the impeller sleeves has upper, intermediate and lower circumferential rows of inserts. Each insert has a face flush with the impeller sleeve and is in sliding engagement with one of the diffuser sleeves. The inserts in the intermediate row may be rotationally staggered relative to the inserts in the upper and lower rows to create serpentine flow paths for well fluid leakage.

Abstract: The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a disk (21), a first blade (20) being mounted on the external periphery of the disk (21), the first blade (20) comprising a platform (25) and a support (27), a second rotor module (3), connected to the first rotor module (2) by means of at least two attachments (22) and comprising a second blade of smaller length than the first blade (20), and a damping device (4) attached to the attachment (22) between the first (2) and the second (3) rotor module so as to dampen their vibrational movements during operation, and comprising: a head (40) comprising a first radial external surface (42) supported with friction against the platform (25), and two attachment feet (41) extending on either side of the support (27) of the first blade (20).

Abstract: A fan device includes a driving device, a fan wheel, and a locking fastener. The driving device includes a shaft. The fan wheel defines a shaft hole to receive the shaft. The locking fastener has a thermal expansion coefficient same as a thermal expansion coefficient of the shaft.

Abstract: A turbine blade retention system includes a turbine blade including a blade section and a blade platform on which the blade section is attached, the blade platform including a forward angel wing and an aft angel wing, the forward angel wing including a front blade seal groove, a disk configured to receive a plurality of the turbine blades, the disk including a front disk seal groove and an aft disk seal groove, a front seal plate, and an aft seal plate, wherein the front seal plate is slidably connectable to the turbine blade and the disk via the front blade seal groove and the front disk seal groove, and the aft seal plate is removably connectable to the turbine blade and the disk via the aft disk seal groove and a lower wall formed on the aft angel wing.

Abstract: A flange of a blade root platform is separated from an adjacent edge of the blade by a groove that prevents direct transmission of forces created by the bolted attachment of the platform flange to the adjacent part of the blade and reduces stress concentrations.

Abstract: A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein is provided. The plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: TVA, TVB, TVC, TVD and TVE of Table 1.