Abstract: The present invention relates to an adjustment assembly for the adjustment of adjustable blades or vanes of a turbomachine, having an adjustment ring for coupling to the adjustable blades or vanes of a blade or vane ring and having an adjusting mechanism, which has a coupling rod for coupling to a further blade or vane ring as well as a lever and a push rod, wherein the lever is rotatably mounted at a pivot and has a load arm as well as a force arm, wherein the load arm of the lever is coupled to the push rod and its force arm is coupled to the coupling rod, on different sides of the lever, so that an offset of the coupling rod via the lever and the push rod is converted to a rotation of the adjustment ring around the ring axis thereof.

Abstract: A turbine stator vane includes: a vane body which includes: an airfoil portion which has a serpentine flow passage inside thereof, the serpentine flow passage including a plurality of cooling flow passages and a plurality of turn-back flow passages; a shroud disposed on at least one of a tip end side or a root end side, in the vane height direction, of the airfoil portion; and a lid portion fixed to the airfoil portion. The lid portion forming the turn-back flow passage and being provided as a separate member from the airfoil portion. The lid portion has an inner wall surface width formed to be greater than the flow-passage width of the cooling passage formed in the airfoil portion, and a minimum value of a thickness of the lid portion is smaller than a thickness of a part of the shroud to which the lid portion is mounted.

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: This steam valve includes a valve casing, a valve body, a valve stem, an actuator, a heat buffer member, a link mechanism, and a link base. The heat buffer member includes: a heat buffer plate separated toward a leading end side from the valve casing in an axial direction in which the valve stem extends; and a support column that fixes the heat buffer plate to the valve casing so as to be incapable of relative movement. The actuator includes: an actuator casing; and an actuator rod that extends in the axial direction from in the actuator casing and that moves in the axial direction with respect to the actuator casing. The link base is fixed to the heat buffer member and extends from the heat buffer member in an axial perpendicular direction that is perpendicular to the axial direction. The actuator casing is fixed to the link base.

Abstract: Disclosed is a wind turbine blade comprising a first blade section extending along a longitudinal axis from a root end to a first end and a second blade section extending along the longitudinal axis from a second end to a tip end. The wind turbine blade comprising a spar beam configured for connecting the first blade section and the second blade section. The first blade section comprises a first down conductor and the second blade section comprises a second down conductor. The wind turbine blade comprises a conductive connector element for electrically connecting the first down conductor and the second down conductor.

Abstract: A turbomachine includes a shroud and a hub spaced apart from the shroud to channel an airflow along a direction. The turbomachine includes a plurality of airfoils coupled between the shroud and the hub. At least one airfoil of the plurality of airfoils includes a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side. The turbomachine includes at least one local vortex generator array defined on the suction side so as to extend onto the hub or the shroud. The at least one local vortex generator array is defined downstream of the leading edge.

Abstract: A method of operating a wind turbine generator comprising a plurality of blades, the method comprising iterating the following steps: comparing an indicated rotor speed with a rotor speed target to determine a rotor speed error; generating a modified rotor speed error by applying a control factor to the rotor speed error; controlling the pitch angle of the blades via a pitch control system in accordance with the modified speed error; and altering the control factor in dependence on a size of the indicated rotor speed.

Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

Abstract: An extendable wind turbine blade for being extended in length during operation thereof, the wind turbine blade having an exterior surface with a root region and an airfoil region and comprising a first blade segment including a first portion of the exterior surface, a second blade segment including a second portion of the exterior surface, and a connection mechanism connecting the blade segments, and being configured to bring the wind turbine blade to a retracted state, in which the portions of the exterior surface are flush and adjoining, when the wind turbine blade operates above a threshold rotational speed and to bring the wind turbine blade to an extended state, in which the portions of the exterior surface are disconnected and the blade length is at least 101% of the blade length in the retracted state, when the wind turbine blade operates below the threshold rotational speed.

Abstract: An appliance includes a tub defining a wash chamber, and a centrifugal pump in fluid communication with the wash chamber. The centrifugal pump includes a motor housing, a motor disposed in the motor housing, and a fluid impeller coupled to the motor. A diffuser housing assembly includes a first diffuser housing portion and a second diffuser housing portion. The first diffuser housing portion includes a groove and the second diffuser housing portion includes an extrusion. A diffuser vane is positioned on the motor housing. The diffuser vane engages in the groove of the first diffuser housing portion. The extrusion of the second diffuser housing portion encloses the diffuser vane into the diffuser housing assembly.

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.