Abstract: The aerodynamically shaped, symmetrical cross-sectional profile for the struts or the fairing (7) of struts and service lines in the bypass duct and the core-flow duct of a turbofan engine is defined by a course of the local thickness (T) and a position of maximum thickness (PMT) on both sides over the central chord (C) extending from the leading edge (LE) to the trailing edge (TE) of the strut or fairing (7). In order to avoid flow separations the course of the local thickness (T) between the position of maximum thickness (PMT) and a trailing-edge position (PTE), which is at 95 percent of the chord length, has a first turning point (WP1) with a trailing-edge thickness (TET) and a subsequent second turning point (WP2).

Abstract: A heat dissipating assembly includes a heat dissipating member, a bracket and a locking member. A male connector is coupled to the heat dissipating member with a cable. The bracket includes two securing plates. Each securing plate defines a positioning hole. A locking member is secured to the heat dissipating member and includes a board body. Two locking portions are located on the board body and engaged in the positioning holes. The locking member defines a through opening. Two first locking blocks and two second locking blocks are located on the locking member. The cable is received in the through opening, and the male connector is inserted through the through opening and secured both between the first locking blocks and between the second locking blocks.

Abstract: A rotor assembly for use with a turbine engine. The rotor assembly includes at least one rotor disk that includes an inner surface that defines a dovetail groove. At least one turbine bucket is coupled to the rotor disk. The turbine bucket includes an airfoil that extends outwardly from a dovetail. The dovetail is inserted at least partially within the dovetail groove. A tang assembly extends from one of the inner surface of the rotor disk and the dovetail. the tang assembly minimizes a rotation of the turbine bucket with respect to the rotor disk.

Abstract: An assembly includes a fan and a heat sink for detachably fixing the fan. The fan includes a pair of first and a pair of second sidewalls, with two pair of rims respectively extending from the first and second sidewalls. Ends of the rims of the first sidewalls, which are directed toward and are adjacent to a same one of the second sidewalls, each have a latch flange. Ends of the rims of the second sidewalls, which are directed toward and are adjacent to a same one of the first sidewalls, each have a latch flange. The heat sink includes a channel for slidably receiving one pair of rims of the first or second sidewalls, a blocking member disposed at one end of the channel to block a corresponding sidewall of the fan, and a latch member disposed at the other end of the channel to latch the corresponding latch flanges.

Abstract: A wind turbine and a method of controlling yawing of a wind turbine are provided. A nacelle is mounted rotatable around a first axis by an adjustable yaw angle and a hub is mounted rotatable around a rotational axis. The hub includes a blade rotating around the rotational axis, the blade defining a rotor plane perpendicular to the rotational axis. A channel of the wind turbine has an opening, the opening being located at a predefined distance to the rotor plane. At least one component of incoming wind is guided through the opening and into the channel as air flow. A measuring device is provided for measuring the air flow, the measuring device being connected to a controller. The controller detects a yaw angle error between a direction of the incoming wind and the rotational axis, the yaw angle error being used to adjust the yaw angle of the nacelle.

Abstract: A wind turbine rotor blade assembly includes a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension is attached along the trailing edge and includes a first strip member having a span-wise attachment section attached to pressure side, and a second strip member having a span-wise attachment section attached to the suction side. Each of the first and second strip members has an outboard edge and an extension section that projects chord-wise beyond the trailing edge. The extension sections are adhesively attached to each other outboard of the trailing edge along a span-wise length of the first and second strip members and define an adhesively bonded closure edge of the edge extension. A method is also provided for forming an edge extension on a wind turbine rotor blade.

Abstract: An inducer with an exterior housing and/or interior hub that incorporates grooves or vanes that are helical in nature and in counter rotation with respect to the rotation of the blades of the inducer, which grooves or vanes capture fluid rotating with the inducer blades and use that rotation to guide the fluid up along paths formed by the grooves or vanes and into an impeller, pump or other device.

Abstract: A composite blade has a root and a tip in a spanwise direction and a leading edge and a trailing edge in a chordwise direction. The composite blade includes a three-dimensional woven preform having weft yarns and warp yarns. The weft yarns extend in the spanwise direction of the composite blade. The warp yarns interweave the weft yarns and extend in the chordwise direction of the blade.

Abstract: A combining structure for the decorating shell of a ceiling fan includes an outer shell and a decorating cover. The bottom of the outer shell has a connecting hole. The rim of the connecting hole is formed upward with at least two opposite notches. Each of the notches is bent downward with a blocking rim that gradually converges. The decorating cover has an annular shape, and is mounted on the bottom of the outer shell. The inner rim of the decorating cover is protruded upward with an inner rim wall that goes through the connecting hole of the outer shell. The outer surface of the inner rim wall is protruded outward with a protruding part for each of the notches on the outer shell. The protruding parts go through the notches and urge and position on the blocking rim at the bottom of the outer shell.

Abstract: A method of assembling a crank arm (100, 200, 300) and vane assembly for a variable nozzle without requiring metallurgical bonding. In accordance with one aspect of the invention, the method comprises the steps of providing a vane assembly comprising a vane (120, 220, 320) joined to a vane shaft (110, 210, 310) that extends from the vane and terminates in a distal end (112, 212, 312), providing a recess (114, 214, 314) in an outer surface of the vane shaft at a location between the vane and the distal end, providing a crank arm (100, 200, 300) having an aperture (102, 202, 302) therein, inserting the distal end (112, 212, 312) of the vane shaft into the aperture (102, 202, 302) until the recess (114, 214, 314) in the vane shaft is inside the aperture, and causing a retaining member (104, 204, 304) associated with the crank arm (100, 200, 300) to engage the recess (114, 214, 314) in such a manner as to fasten the crank arm to the vane shaft in a substantially immovable manner.

Abstract: A trailing edge cooling circuit for a turbine rotor blade, which includes a radial flow cooling channel that supplies cooling air for the T/E region of the blade. Three radial flow cooling channels are located adjacent to one another and connected to the radial flow cooling supply channel, each discharging through an opening along the T/E just underneath the blade tip. The radial flow cooling channels in the T/E region are connected together by rows of metering holes in the middle spanwise height of the blade that produce mixing of the cooling air flowing upward toward the blade tip and improve the cooling effectiveness of the cooling air. A row of exit holes along the T/E discharge cooling air from the third radial flow cooling channel.

Abstract: A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.

Abstract: A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region and a second region having a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages.

Abstract: A blower comprising: a snail-shaped base, a snail-shaped cover, blades and a motor, wherein the snail-shaped base and the snail-shaped cover form a exhaust channel, the blades are horizontally provided in the exhaust channel, the snail-shaped cover above the blades is provided with an air intake channel formed by a motor mounting chamber and a motor cover, and the motor is vertically disposed in the air intake channel and connected to the blades therebelow. The blower is structurally scientific and concise. When the blower operates, air is taken in and provides effective heat dissipation for the motor, and there is a sufficient distance between the motor and the ground surface, and waterproof designs of the sealed capacitor junction box and both ends of the motor can perform an excellent waterproof function.

Abstract: A cover disk (1) for a closed rotor of a radial flow machine or diagonal flow machine for defining a flow channel has a wall thickness which has a local maximum along the profile mean line of the meridional cross section of the cover disk between a first front side (2) and a second front side (3) of the cover disk. An outer surface (1.2) of the cover disk remote of the flow channel has in the area of this local maximum a convex curvature with a radius (R2.2) whose ratio (R2.2/D2) to an outer diameter (D2) of the rotor is within a range of 0.05 to 0.5 (0.05?R2.2/D2?0.5).

Abstract: An elastomer material seal for an interleaved platform between two adjacent blades in a turbomachine rotor is disclosed. The seal is of elongate shape and includes transversely a contact part, an attachment part, and a flexible part between the attachment part and the contact part. The seal is noteworthy in that it further includes a local reinforcement of the flexible part, to avoid the tearing that would result from centrifugal forces on the seal. The local reinforcement of the flexible part includes at least one transverse rib on the flexible part.

Abstract: There is provided a compressor device in which resonance in a circulating channel is reduced so that an increase in noise generated from the compressor device is prevented. The compressor device includes: a plurality of blades rotated about a rotation axis; an air inlet extending along the rotation axis and introducing air to the blades; a circulating channel disposed on a circumference centered on the rotation axis and communicating between the air inlet and the shroud of the blades; and a strut extending radially centered on the rotation axis and dividing the circulating channel. Resonance frequencies determined from circumferential lengths in the circulating channels divided by the strut are higher than a noise frequency determined from the rotational speed of the blades and the number of blades.

Abstract: The object is to facilitate the installation of a contra-rotating propeller on a mother ship. Disclosed is a contra-rotating propeller unit in which a predetermined part on the rear side of an inner shaft (12) is supported by a contra-rotating rear bearing (36) provided in a boss (13a) of a front propeller (13), and which includes an inner fixing tool (50) detachably attached to a tip of an outer shaft (11) to temporarily support a predetermined part on the front side of the inner shaft (12), and a contra-rotating thrust bearing (40) provided in the boss (13a) of the front propeller (13) to receive the thrust load from the outer shaft (11) to transmit the thrust load to the inner shaft (12).

Abstract: The present invention relates to the prevention of deformations in an aerodynamic profile caused by lack of resistance to the bending moment forces that are created when such a profile is loaded in operation. More specifically, the invention relates to a reinforcing element inside an aerodynamic profile and a method for the construction thereof. The profile is intended for, but not limited to, use as a wind turbine blade, an aerofoil device or as a wing profile used in the aeronautical industry.

Abstract: In one aspect, a rotor hub assembly for a wind turbine is disclosed. The rotor hub assembly may generally comprise an inner hub including a plurality of hub segments assembled together and a hub enclosure including a plurality of enclosure segments assembled together. The hub enclosure may be configured to at least partially enclose the inner hub. In addition, the rotor hub assembly may include a plurality of support members extending between the inner hub and the hub enclosure.