Abstract: A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.

Abstract: A system and method for inspecting fan blade clearances in a fan stator module are presented. The method includes rotating a fan rotor assembly that includes an attached bracket situated between adjacent fan blades connected to the fan rotor assembly. The bracket includes a laser module and an inclinometer configured to measure a circumferential position of the laser module. The method further includes projecting a laser beam from the laser module to the fan case to determine a distance measurement between the laser module and the fan case at multiple circumferential points around the fan case. The distance measurement and circumferential position data is processed by a computing device to determine a clearance distance between a fan blade and the fan case.

Abstract: A multi-layer braided article and a method of making the multi-layer braided article. The multi-layer braided article includes a braid extending along a first axis, wherein the braid is folded over itself to form a first layer and a second layer; and a wrapper laid over the first layer of the braid and extending circumferentially around the first axis, wherein the wrapper defines an edge of the first layer about which the braid is folded. The multi-layer braided article may form part of a blade for an aircraft. A sleeve may be provided around a conical portion of the article to connect the article to something else, such as a propeller hub, where the multi-layer braided article is formed as part of a blade. The sleeve may provide a primary or secondary load path.

Abstract: An inlet guide vane assembly for a centrifugal compressor includes a plurality of guide vanes, a drive structure coupled to the plurality of guide vanes, an actuator; and an actuation mechanism. Rotation of the drive structure is transitions the plurality of guide vanes from a first position to a second position. The actuation mechanism causes the drive structure to transition the plurality of guide vanes between the first and second positions based on operation of the actuator. The actuation mechanism imparts a first amount of rotational force to drive the drive structure when the guide vanes are in the first position, and a second amount of rotational force when the guide vanes are in the second position. The actuation mechanism provides a mechanical advantage to the actuator when the guide vanes are in the first positions as compared to when the guide vanes are in the second position.

Abstract: A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.

Abstract: A vortex-induced vibration (VIV) suppression system comprising: a vortex-induced vibration (VIV) suppression device dimensioned to be coupled to a tower of a wind turbine and operable to rotate about a tower of the wind turbine to suppress a vortex-induced vibration; and a drive member coupled to the vortex-induced vibration suppression device and operable to align the vortex-induced vibration suppression device with a nacelle of the wind turbine.

Abstract: A turbine blade includes: a platform; an airfoil portion extending from the platform in a blade height direction and having a pressure surface and a suction surface extending between a leading edge and a trailing edge; a blade root portion disposed on opposite side of the airfoil portion across the platform in the blade height direction and having a bearing surface; and a shank disposed between the platform and the blade root portion. The shank has: a first lateral surface having a first recess portion and disposed on a pressure surface side and along an extension direction of the blade root portion; and a second lateral surface having a second recess portion and disposed on a suction surface side and along the extension direction of the blade root portion.

Abstract: A core ring for a torque converter is disclosed herein. The core ring includes a plurality of through openings and a plurality of recesses each connected to a respective through opening of the plurality of through openings. The recesses are each dimensioned to receive a portion of a blade, and specifically a blade tip formed on an adjacent torque converter component.

Abstract: A method for detecting and reducing edgewise vibrations in a rotor blade of a wind turbine includes, for a given wind speed, determining a frequency or frequency band at which edgewise vibrations are producible in the rotor blade. The method determines an electrical characteristic of the pitch actuator that correlates to an increased torque required to hold a pitch angle of the rotor blade constant at the frequency or frequency band. During an operational power-production mode of the wind turbine, the electrical characteristic of the pitch actuator is monitored. Upon the electrical characteristic reaching a predefined limit value indicative of edgewise vibrations in the rotor blade, corrective action is initiated by the wind turbine controller to reduce or prevent the edgewise vibrations.

Abstract: A safety apparatus for containing an energy release from a rotor sub-assembly, the safety apparatus includes a plurality of containment members. The containment member has an elongate region defining a longitudinal axis; and at least two arms projecting away from the longitudinal axis of the elongate region; and at least one connecting member connected to at least two of the plurality of containment members. In use the at least one connecting member is configured to connect the safety apparatus to the sub-assembly and the plurality of containment members are configured to withstand an energy release from the sub-assembly.

Abstract: A bearing compartment seal for a gas turbine engine includes a seal ring that defines an axis and has a radially inward facing sealing surface. A seal runner is configured to rotate relative to the seal ring. The seal runner has a runner surface facing the radially inward facing sealing surface. A plurality of grooves are spaced circumferentially along the runner surface. The plurality of grooves have a length in an axial direction that is at least 50% of an axial length of the runner surface.

Abstract: A platform for a wind turbine, the platform including a lift beam for carrying a load of a transport cabin of a tower lift of the wind turbine is provided. By the lift beam being part of the platform, an easier installation of the platform and the lift beam is possible. Furthermore, less components are needed. Another advantage is that the lift beam is installed at a smaller height of the tower where the tower has a larger diameter compared to a conventional lift beam. This increases the available space for lift cables hanging from the lift beam.

Abstract: A centrifugal fan is disclosed and includes a lower case, an impeller and an upper case. The lower case includes a bottom plate and a sidewall. The impeller is disposed on the bottom plate. The upper case is assembled with the sidewall to form an outlet. The upper case is formed by stamping and includes a first plane, an inlet and a grille. When the impeller is rotated, an airflow flowing from the inlet to the outlet is formed. The grille is protruded outwardly from the first plane, and includes a connecting frame and plural ribs. A spacing height is formed between the connecting frame and the inlet. Each rib has a first end connected to the connecting frame and a second end connected to the first plane. A pair of notches are disposed adjacent to two opposite lateral edges of the second end of the corresponding rib, respectively.

Abstract: An aircraft uses trajectory-based control algorithms for blade pitch (or twist). This approach greatly enhances the ability of the actuator to accurately achieve the desired blade pitch and to track the commanded pitch position. An actuator includes an electronic rotor blade controller that converts communicated or desired changes in pitch (or similar parameter) to actual physical effects that match the desired changes as closely as possible. The controller preferably includes a motor drive circuit, such as an h-bridge, a communication circuit for connection to external commands, and a processor with associated enabling circuitry (e.g. memory, I/O) to coordinate and implement the control.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.

Abstract: Provided is a flange for connecting to a complementary flange, and wherein the flange includes a first flange-segment and a second flange-segment, wherein a) the first flange-segment includes a primary bolt circle including an annular arrangement of inclined openings; and a first annular connection face adapted to lie against a complementary second annular connection face of the second flange-segment; and b) the second flange-segment includes on two opposite sides annular connection faces adapted to lie against complementary annular connection faces; a primary aperture circle including an annular arrangement of openings; and a second body section with a secondary bolt circle including an annular arrangement of openings. Also provided is respective flange-segments, a method for manufacturing such flange and a tower construction.

Abstract: A bearing arrangement for a wind turbine including a bearing housing and a drive shaft, whereby the drive shaft is arranged within the bearing housing in an axial direction along a longitudinal axis of the bearing housing, the bearing arrangement further includes a downwind bearing and an upwind bearing, whereby the downwind bearing and the upwind bearing are arranged between the bearing housing and the drive shaft, wherein the downwind bearing and/or the upwind bearing is a radial bearing including multiple radial bearing pads, whereby each one of the multiple radial bearing pads is attached to one of a multiple radial bearing bodies of the radial bearing and the multiple radial bearing pads are arranged about the drive shaft is provided.

Abstract: A pump includes a housing, a process stream input, a process stream output, a power stream inlet, and a rotor. The rotor comprises an impeller, a shroud, and a turbine. The impeller comprises fluid motive elements positioned about a central axis of the rotor and extending outward to the shroud. The turbine comprises runners formed on an outwardly facing surface of the shroud of the rotor. The shroud extends radially about the fluid motive elements of the impeller. The rotor is rotatably supported within the housing. The runners cause the rotor to rotate when the power stream flows through a fluid path impinging the runners thereby transferring energy from the flow of the power stream received through a power stream inlet into rotational energy of the fluid motive elements of the impeller to propel the process stream from a process stream input out a process stream output.

Abstract: On an inner circumferential surface (25a) of a housing (25) opposed to an outer circumferential surface (37a, 37b) of an outer ring, toward a front side in a rotation direction (B) of a rotation shaft (21), a first groove (41H, 41I) is formed as a groove portion for guiding an oil (39) in a direction toward a first oil supply hole (41D, 41E).

Abstract: A damper position-limiting device is provided, which is mounted in a tower to limit the swing amplitude of a damper installed in the tower. The damper position-limiting device includes at least one web and a position-limiting ring. The web is provided with a mounting hole and at least one stress relief hole. A first side wall of the web has a first specified length along a circumferential direction of the inner wall of the tower, and is connected to the inner wall of the tower. The position-limiting ring is positioned within the mounting hole and connected to the mounting hole and is configured to accommodate an impacting plate of the damper.