Abstract: The rotary airfoil 100 defines a cross section and a span, wherein the cross section is a function of the point along the span (e.g., spanwise point) and defines an upper surface and a lower surface at each spanwise point. The rotary airfoil 100 also defines, at a cross section, a lift coefficient (CL) that is a function of the angle of attack at which the airfoil is rotated through the air. The system can optionally include: a rotor hub to mount the rotary airfoil, a tilt mechanism to pivot the rotary airfoil between a forward configuration and a hover configuration, and a pitching mechanism to change the angle of attack of the rotary airfoil 100.

Abstract: A device and a method of controlling blade instabilities of a wind turbine is provided. The method including the following steps: defining at least one preliminary overspeed threshold value; defining a fluttering rotor speed at and above which a predetermined fluttering of at least one of the blades occurs, the fluttering rotor speed is defined as a function of the pitch angle and/or as a function of the wind speed; setting a final overspeed threshold value to be equal to or smaller than a minimum rotor speed of the at least one preliminary overspeed threshold value and the fluttering rotor speed at the actual pitch angle and/or at the actual wind speed; and controlling the rotor speed to not exceed the final overspeed threshold value.

Abstract: Disclosed is a suction damping case. A refrigerant introduced into the suction damping case flows for a predetermined period of time at reduced pressure and speed, and then is discharged to the outside of the body, so that a damping function can be made. When the suction damping case is coupled to a rear housing, a hook and an embossing prevents the suction damping case from being separated.

Abstract: The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing (23) comprising: —an annular shell (29) with axis A; —an annular element (24; 253, 254) attached to the inside of the shell (29), the annular element comprising a body (25) made of NIDA-type cellular material and comprising a downstream portion (252) covered with an abradable material (26), and an upstream portion (251) without abradable material, the body (25) extending in a continuous manner from the upstream portion (251) to the downstream portion (252), the method comprising: —manufacturing the annular element in the form of a continuous annular body, —cutting the annular body into segments (253, 254), —attaching the segments to the shell, and —depositing the abradable material (26) onto the inside surface (25a) of the downstream portion (252).

Abstract: A suction throttling valve adjusts flow of a process gas through an inlet flowline. A compressor pressurizes the process gas. An outlet flowline flows the process gas from the compressor. An anti-surge flowline branching from the outlet flowline directs a first portion of the process gas from the outlet flowline back to the inlet flowline. The anti-surge flowline is connected to the inlet flowline intermediate of the suction throttling valve and the compressor. An anti-surge control valve adjusts flow of the first portion of the process gas through the anti-surge flowline to the inlet flowline. A bypass flowline provides an alternative flow path for a second portion of the process gas flowing through the anti-surge flowline to the inlet flowline around the suction throttling valve. A bypass control valve adjusts flow of the second portion of the process gas through the bypass flowline.

Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.

Abstract: A novel lightweight high efficiency wind generator with low noise and low vibrational levels comprising a vertical mast with a rotation element mounted at the top of the mast, with a frame attached to the rotation element with its bottom, such that the rotation element provides axial rotation of the frame in the range from 0° to 360°, is disclosed. The frame comprises a three-dimensional truss frame construction with traverses, to which at least one rigid closed elliptical base is attached. The at least one elliptical base carries a guide rail with grooves, the guide rail comprises at least one pair of rollers in the grooves which can rotate and roll in the grooves along the entire closed circuit of the elliptical base. Along the entire contour of the elliptical base blades are radially fixed and arranged in one plane using carriages.

Abstract: A stator assembly for a torque converter includes a body, a one-way clutch, and a washer. The body is rotatable about an axis and has a cavity defined by an axial wall radially spaced from the axis and a radial wall extending radially inward from the axial wall. The one-way clutch is disposed in the cavity. The washer includes a thrust surface, a supporting surface, and an axial retention feature. The thrust surface faces away from the cavity. The supporting surface directly contacts the one-way clutch. The axial retention element is configured to connect to the axial wall of the body.

Abstract: An axial fan includes a housing, an upper motor, and a lower motor. The housing includes an upper housing and a lower housing. A lower peripheral wall of the lower housing includes first engaging portions and lower protruding pieces. The lower protruding pieces oppose the first engaging portions in an axial direction and protrude axially upward from an axially upper surface. An upper peripheral wall of the upper housing includes upper engaging claws and upper notch grooves. The upper engaging claws extend axially downward from an axially lower surface, and include a second engaging portion that engages with the first engaging portion in a lower end portion. The upper notch grooves are notched axially upward from the axially lower surface radially inward of the upper engaging claw. At least a portion of the lower protruding pieces is located in the upper notch grooves.

Abstract: A measurement system for an aircraft gas turbine engine includes an instrumentation hub disposed about a rotational axis. The instrumentation hub includes at least one probe. The measurement system further includes a shield hub disposed about the rotational axis and positioned axially adjacent the instrumentation hub. The shield hub includes at least one shield configured to be radially aligned with the at least one probe of the instrumentation hub. The shield hub is rotatable about the rotational axis independent of the instrumentation hub. The at least one shield is axially translatable between a first axial position and a second axial position. The at least one shield in the first axial position is axially aligned with the at least one probe. The at least one shield in the second axial position is axially separated from the at least one probe.

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.