Abstract: A continuously variable valve timing apparatus may include a camshaft, a first and a second cam portions having two cams formed thereto, of which the camshaft is inserted thereinto, and of which relative phase angles with respect to the camshaft are variable. First and second inner brackets transmit rotation of the camshaft to the first and second cam portions respectively. First and second slider housings having first and second inner brackets are rotatably inserted thereinto, respectively, and have relative positions with respect to the camshaft that are variable. A cam cap rotatably supports the first and second cam portions together with a cylinder head, and the slider housings are slidably mounted thereto. A control shaft is disposed parallel with the camshaft and selectively moves the first and the second slider housings, and a control portion selectively rotates the control shaft so as to change positions of the inner brackets.

Abstract: A wind turbine rotor blade may generally include a blade root, a blade tip opposite the blade root and a body shell extending between the blade root and the blade tip. The body shell may include a pressure side and a suction side extending between a leading edge and a trailing edge and may define an outer shell surface. The rotor blade may also include a leading edge cap coupled to the body shell at the leading edge. The leading edge cap may be formed from a fiber-reinforced composite including an inner surface extending directly adjacent to the body shell along a portion of the outer shell surface and an outer surface opposite the inner surface. The fiber-reinforced composite may include a plurality of fibers surrounded by a thermoplastic resin material, with the thermoplastic resin material extending throughout the fiber reinforced composite from the inner surface to the outer surface.

Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor disk comprises a first elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the first elongated body. The first elongated body defines a slot that extends axially therethrough. The damper pin further includes a second elongated body having a generally arcuate top portion. The second elongated body is at least partially disposed within the slot and is slideably engaged in an axial direction with the first elongated body.

Abstract: A gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, a body having a first outer face meeting a second outer face at an intersection, the body having a plurality of apertures extending from an opening in the first outer face to an opening on the second outer face; and a coating filling at least a portion of the plurality of apertures.

Abstract: A method of assembling gas turbine engine front architecture includes positioning a first shroud and a first shroud portion radially relative to one another. Multiple vanes are arranged circumferentially between the first shroud and the first shroud portion. A second shroud portion is secured to the first shroud portion about the vanes. The first and second shroud portions provide a second shroud. The vanes are mechanically isolated from the first and second shrouds.

Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially aligned with and axially spaced from a second end portion and a retention pin that is coaxially aligned with and disposed between the first end portion and the second end portion. The retention pin couples the first end portion to the second end portion. The damper pin further includes a plurality of rings coaxially aligned with and disposed along the retention pin between the first end portion and the second end portion. The first end portion, the second end portion and the plurality of rings define a generally arcuate outer surface of the damper pin that is configured to contact with a groove defined between the adjacent turbine blades.

Abstract: A gas turbine engine includes a rotating stage of blades. A circumferential array of blade outer air seal segments are arranged radially outward of the blades. Adjacent blade outer air seal segments provide a circumferential gap. Facing ends of the adjacent blade outer air seal segments include surfaces. A gap seal engages the surfaces and obstructs the circumferential gap. A biasing member is configured to urge the gap seal radially inward toward the surfaces.

Abstract: A variable pitch fan for gas turbine engine is provided. The variable pitch fan includes a plurality of fan blades rotatably coupled to a disk and an actuation assembly for changing a pitch of each of the plurality of fan blades. The actuation assembly generally includes an actuation member operably connected to at least one of the plurality of fan blades and a pin. The pin is movable between a first position in which the pin is positioned at least partially in a channel defined in the actuation member, and a second position. The pin blocks movement of the actuation member relative to the pin past a range defined by the channel when in the first position. The actuation assembly further includes a retraction system for selectively engaging the pin in moving the pin from the first position to the second position.

Abstract: The present invention relates to a water extraction system comprising a flow cell comprising a membrane; said membrane comprising an active layer comprising immobilized aquaporin water channels and a support layer, and said membrane having a feed side and a non-feed side; and an aqueous source solution in fluid communication with the feed side of the membrane.

Abstract: A compound engine assembly with an inlet duct having an inlet surrounded by an inlet lip including at least one conduit extending therethrough, a compressor, an engine core including at least one internal combustion engine, a turbine section having a turbine shaft in driving engagement with the engine shaft, and an exhaust conduit providing a fluid communication between the outlet of the turbine section and the conduit(s) of the inlet lip. An exhaust duct and ant exhaust conduit providing a fluid communication between the outlet of the turbine section and the exhaust duct may also be provided. The internal combustion engine(s) may be rotary engine(s). A method of driving a rotatable load of an aircraft is also discussed.

Abstract: A wind turbine includes a hub sub-system comprising a main hub and a shaft adapted to rotate about an axis, and a plurality of turbine blades having a pitch angle. The blades are adapted to drive the rotation of the hub sub-system to a first speed. The wind turbine further includes a pitch drive sub-system including a driving element adapted to rotate about the axis at a second speed, and further adapted to control the pitch angle of the turbine blades in relation to a difference between the first speed and the second speed. A slip enhanced generator enables the hub sub-system to rotate at a different speed than the pitch drive sub-system. The difference in speed is governed by a slip function. The wind turbine further includes an active control system adapted to control the second speed of the driving element.

Abstract: A method of making a wind turbine blade incorporating a lightning protection system includes providing a blade mold; arranging a protruding element in the mold; arranging an electrically conductive layer over the protruding element; arranging one or more structural layers and/or structural components over the conductive layer; consolidating the layers under vacuum to form a blade shell having the conductive layer proximate an outer surface of the shell; separating the protruding element from the blade shell to define a recess with the conductive layer extending into the recess; providing an electrical component adjacent an inner surface of the shell; and electrically connecting the conductive layer to the component. An end portion of the connecting member is housed in the recess such that a surface of the connecting member abuts the conductive layer inside the recess.

Abstract: The present subject matter is directed to a rotor blade assembly for a wind turbine having a pultruded component at an interface of a shear web and a spar cap. More specifically, the rotor blade assembly includes an upper shell member having an upper spar cap configured on an internal surface thereof and a lower shell member having a lower spar cap configured on an internal surface thereof. A shear web extends between the spar caps along a longitudinal length of the blade. Further, the shear web includes a first end and a second end. The first end is secured to the upper spar cap at a first interface and the second end is secured to the lower spar cap at a second interface. In addition, the shear web includes at least one pultruded component configured at either or both of the first or second interfaces between the first and second ends and the upper and lower spar caps, respectively.

Abstract: A variable-pitch vane including a plurality of propeller blades (2). Each blade has a variable pitch according to a blade rotational axis (A1) and a root (201). A plurality of rotor connecting shafts (6), each shaft having a foot (602) and a head (601). The root (201) of each blade is mounted on the head (601) of a rotor connecting shaft via a pivot (8) in such a way as to allow each blade (2) to rotate according to the blade rotational axis (A1), in which each blade (2) has a blade pitch, such that the blade rotational axis (A1) is inclined relative to a radial axis (A2) passing through the foot (602) of the corresponding shaft.

Abstract: A one-handed, forearm-braced paddle has a blade at one end and a forearm brace at the other interconnected by a central shaft portion. The shaft has a rigid control handle that has a base end fixed to the shaft, and, extends from the shaft to a hand grip portion. The hand grip is shaped to allow a user to clench it, and is thereby radially spaced away from the shaft to further allow the user to apply longitudinal leverage on the blade, or else give the user leverage with the application of a twisting torque on the blade. The control handle is furthermore goose-necked shaped and arching away from the forearm brace so that the user's fingers are relatively unimpeded by any of the shaft, blade, or base portions of the control handle.

Abstract: An article includes a body that has a first section and a second section bonded with the first section. The first section is formed with a first material that has a first microstructure and the second section is formed of a second material that has a second, different microstructure.

Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.

Abstract: A rotor blade for a wind turbine may generally include a first blade component formed from a first fiber-reinforced composite including a first thermoplastic resin material and a second blade component configured to be coupled to the first blade component at a joint interface. The second blade component may be formed from a second fiber-reinforced composite including a second thermoplastic resin material. The second fiber-reinforced composite may include a low fiber region and a high fiber region, with the low fiber region having a fiber-weight fraction that is less than a fiber-weight fraction of the high fiber region. In addition, the first thermoplastic resin material of the first fiber-reinforced composite may be welded to the second thermoplastic resin material contained within the low fiber region of the second thermoplastic composite to form a welded joint at the joint interface between the first blade component and the second blade component.

Abstract: Light weight fan blades for turbofan jet engines are disclosed. The fan blades may be fabricated from an aluminum alloy. To enhance the hardness of the leading edge of the fan blade, a titanium sheath may be attached to the leading edges of the fan blades. To prevent galvanic coupling between the titanium and the aluminum, a polymeric liner may be disposed between the protective titanium sheath and the aluminum fan blade. The liner may be fabricated from a polymer material, such as a polyimide or another high performance polymer.

Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially spaced from a second end portion and a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion. The first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin. The top portion is configured to contact with a groove defined between the adjacent turbine blades.