Abstract: A mount is for attaching an accessory to a fan including a downtube. The mount includes a receiver adapted for connecting to the downtube. A retainer is adapted to receive the accessory. The retainer is adapted to support and rotate about the receiver so as to position the accessory in a desired orientation. Related methods of attaching an accessory to a fan are also disclosed.

Abstract: The disclosure concerns a wind turbine, comprising: a hub with a hollow cylindrical region with a mean circumference UN; at least one rotor blade mounted rotatably on the hub, with a blade laminate which extends in the longitudinal direction of the rotor blade and at least in portions forms a hollow cylinder with a mean circumference UR; and at least one blade bearing for mounting the rotor blade on the hub, with a first bearing ring which is arranged on the hub side and connected by means of a first flange connection to a rotor hub flange formed on a rotor-blade side end portion of the hub, wherein the first flange connection has at least one hub longitudinal bolt which is arranged on a circumference UNB coaxially to the blade bearing; and a second bearing ring which is arranged on the rotor blade side and connected by means of a second flange connection to a rotor blade flange formed on a hub-side end portion of the rotor blade, wherein the second flange connection has at least one rotor blade longitudinal

Abstract: An airfoil for a gas turbine engine. The airfoil includes a unique cooling path for a coolant, routing the coolant through a cooling cavity, through a column of crossover passages and through a pin array near a trailing edge of the airfoil. The crossover passages produce impingement cooling and the pin array produces convective cooling. This combination of impingement cooling and convective cooling results in increased cooling of the airfoil and better aeromechanical life objectives.

Abstract: Nozzle segment assemblies for gas turbine engines include an outer band, inner band, and at least one airfoil body between the outer band and inner band. The airfoil body includes an outer end extending through the outer band and having an outer end reinforced wall portion engaging with the outer band and an inner end extending through the inner band and having an inner end reinforced wall portion engaging with the inner band. A thickness of the outer end and inner end reinforced wall portions are each greater than a thickness of a central wall portion of the airfoil body to reduce stresses in the airfoil body. The outer band, the inner band, and the airfoil bodies are ceramic matrix composite (CMC) materials. Direct mounting of the airfoil bodies to the inner and outer hangers of the nozzle further reduce stress.

Abstract: A method for upgrading a gas turbine, the method includes: a) removing all guide vanes of the first guide vane stage; b) replacing the removed guide vanes of the first guide vane stage with new or reconditioned guide vanes, wherein blade platforms of the new or reconditioned guide vanes are provided with cooling air bores which fluidically connect a cooling air supply duct to the annular gap and open into the annular gap, and wherein the cooling air bores are arranged in such a manner that more cooling air bores open into regions of an annular gap that are arranged radially inwards from leading edges of the guide vanes than in other regions of the annular gap.

Abstract: A vane for a turbine engine includes a body in the form of an aerodynamic profile formed by a shell produced from a composite material formed from a three-dimensional textile of reinforcement fibres consolidated by a hardened resin. The shell forms a pressure surface and a suction surface of the vane connected to each other while forming on one side a leading edge and on the opposite side a trailing edge of the vane, and a core including a core body surrounded by the shell. The core is produced from non-porous plastics material, and the core body is in the form of an aerodynamic profile and delimits at least one closed cavity of the core.

Abstract: A method for controlling heating of rotor blades of an aerodynamic rotor of a wind turbine, wherein, the heating of the rotor blades is initiated, if icing of the rotor blades is expected, wherein according to an icing criteria, if icing is expected is evaluated depending on a determined ambient temperature, a determined relative humidity, and a determined wind speed, each defining a determined weather parameter, and further according to the icing criteria, if icing is expected is evaluated depending on a temporal change of at least one of these weather parameters and/or of at least one other weather parameter.

Abstract: A turbine blade in a gas turbine engine includes an airfoil extending in a radial direction. The airfoil has an outer wall delimiting an airfoil interior. The outer wall includes a pressure sidewall and a suction sidewall joined at a leading edge and a trailing edge in a longitudinal direction. A turbulator is disposed in the airfoil interior. The turbulator includes a first row having at least two turbulator ribs spaced apart in the longitudinal direction. The turbulator includes a second row extending in the radial direction from the first row and having at least two turbulator ribs spaced apart in the longitudinal direction.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement an integrated stator-fan frame assembly. An integrated fan exit stator-fan frame strut assembly for a gas turbine engine includes a fan exit stator portion having an airfoil including a leading edge and a trailing edge, and a fan frame strut portion including a leading edge and a trailing edge, the leading edge of the fan frame strut portion aerodynamically integrated with the trailing edge of the fan exit stator portion.

Abstract: A composite component for a gas turbine engine includes a body including a composite material. Furthermore, the composite component includes a connection feature integrally woven to the body. Additionally, the connection portion includes a composite material. Moreover, the composite material of the body and the composite material of the connection feature include alternating layers of fiber tows integrally woven together.

Abstract: According to an embodiment of the present disclosure, a ceiling fan includes a shaft coupled to a ceiling or a wall surface, a housing cover provided at a central axis thereof with a shaft and receiving a motor assembly and an electronic unit, and a blade coupled to the housing cover. The electronic unit is provided in a multi-stage.

Abstract: The present disclosure provides a rotating propeller design that maintains a high efficiency and reduces noise. The design provides an unloaded tip zone of positive lift starting prior to an end of the tip with negligible, if any, positive lift that is counterintuitive to the purpose of a propeller. The unloaded tip zone decreases the strength of a tip vortex and reduces induced drag. The result is a significant reduction in noise while maintaining substantially high mechanical efficiency, even with an optional increase in RPM to compensate for the reduced lift without requiring a longer propeller. At least one propeller design can break the beta angle from the propeller hub with a different beta angle at a first location from the hub and then also break the beta angle at a second location further from the hub into the unloaded tip zone to form a double break propeller.

Abstract: A turbofan engine has a primary duct, in which there flows a primary flow at a primary pressure and a secondary duct, which radially surrounds the primary duct and in which there flows a secondary flow at a secondary pressure. The primary duct includes at least one compressor configured to compress the primary flow, a turbine driving the compressor in rotation and a combustion chamber designed to receive, at an inlet, the primary air flow compressed by the compressor. The turbomachine further includes a cooling circuit extending between the compressor and the turbine. The cooling circuit has an air flow rate regulating device arranged upstream of the turbine and having at least one valve that is configured to move between an open position and a closed position, located between the compressor and the combustion chamber in the primary duct and the pressure (PS) in the secondary duct.

Abstract: An energy conversion unit for converting wind energy into electrical energy includes at least one rotor with a substantially horizontal axis of rotation, having a plurality of rotor blades extending radially to the axis of rotation, wherein the rotor has a flow direction which corresponds to the axis of rotation, a wall to be arranged next to a traffic route for vehicles which can move on the traffic route in a direction of travel and the movement of which causes an air flow, wherein the wall has a receptacle in which the rotor is arranged, wherein the receptacle has an opening on a side surface of the wall to be directed towards the traffic route, and wherein the axis of rotation of the at least one rotor is oriented substantially perpendicular to the direction of travel.

Abstract: A hoist for lifting at least a portion of a gas engine assembly includes a support member including an upper portion, a lower portion, and a connecting portion extending therebetween. The hoist also includes an elongate member coupled to the lower portion of the support member and extending substantially orthogonally to the lower portion, and at least one bracket slidably engaged with the elongate member and axially translatable along a length of the elongate member. In addition, the hoist includes a plurality of linkage members coupled to the at least one bracket, where each linkage member of the plurality of linkage members is configured to attach to at least a portion of the gas engine assembly.

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 turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.

Abstract: A rotor blade for a wind power installation, which extends in a longitudinal direction with a profile course from a blade connector to a blade tip, wherein the profile course contains at least one profile, comprising: a suction side and a pressure side, a relative profile thickness of greater than 25%, a profile chord, which extends between a leading edge and a trailing edge of the profile and has a length which defines the profile depth, a mean line which extends at least partially below the profile chord, a convex region which extends on the suction side from the trailing edge, and a convex region which extends on the pressure side from the trailing edge, wherein the convex region on the pressure side defines a rounded transition region of the pressure side to the trailing edge.

Abstract: Accelerators, methods of manufacturing accelerators, and gas turbine engines are provided. For example, an accelerator for a gas turbine engine defines a radial direction and an axial direction and comprises an annular outer wall, an annular inner wall, an annular channel defined between the outer and inner walls, and a plurality of vanes disposed within the channel. The channel has an inlet for ingress of a cooling fluid and an outlet for egress of the cooling fluid. Each vane extends from the outer wall to the inner wall adjacent the outlet, which is angled such that an exit angle of the cooling fluid is nonzero with respect to both the radial and axial directions. The accelerator may be manufactured using an additive manufacturing method. The accelerator outlet may be disposed immediately upstream of a first turbine rotor blade stage of a gas turbine engine to direct the cooling fluid thereto.