Abstract: Method for controlling a rotor blade adjustment device (14) of a wind turbine or water hydroelectric powerplant (1), wherein the rotor blade adjustment device (14) has a drive (20) which is connected to a rotor blade (8) which is subjected to a flow of wind or water and has the purpose of rotating the rotor blade (8) about a rotor blade axis (15) relative to a rotor hub (7) on which the rotor blade (8) is mounted so as to be rotatable about the rotor blade axis (15), and an electromagnetic brake (34) which is connected to the rotor blade (8) and has the purpose of blocking rotation of the rotor blade (8) about the rotor blade axis (15), wherein the brake (34) is actuated in order to change its activation state at a brake activation time (tB), wherein the drive (20) is actuated to change its driving state at a drive activation time (tA) which has a predetermined chronological offset (?tV) with respect to the brake activation time (tB), and wherein an electric current (IB) which flows through the brake (34) is

Abstract: A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal.

Abstract: Aspects of the disclosure are directed to a system associated with an engine of an aircraft comprising: a duct, an inlet coupled to the duct, and a fence coupled to the inlet or located upstream of the inlet. In some embodiments, the system further comprises a valve body coupled to the duct. In some embodiments, the valve body includes at least one valve that is configured to rotate between a closed state and an open state.

Abstract: A fan blade with improved structure includes a hub, a plurality of blades. The hub has a lateral side having two ends, one of which is formed a top side and the other end is extended to form an extended section, and a plurality of connecting slots located on the periphery of the extended section. Each blade has a first end correspondingly engaged in respective connecting slot and a second end. With these arrangements, the fan blade with improved structure can increase structural strength of thin fan blades and be easy to connect the hub to the blades.

Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through the at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.

Abstract: High cycle fatigue (HCF) in a turbine wheel of a sector-divided dual volute turbocharger, particularly a turbocharger where the tongue-to-blade gap is as small as from 1-3% of the wheel diameter, is reduced using a turbine wheel with (blade stiffness/backwall stiffness×100) between 41 and 44.

Abstract: A variable geometry turbocharger includes a turbine having a variable nozzle unit, and a compressor. The variable nozzle unit has: a unit main body part that is fixed to a turbine housing and rotatably supports a plurality of nozzle vanes; a drive ring that transmits a driving force to the plurality of nozzle vanes; and a drive ring support member that is fixed to the unit main body part and rotatably supports the drive ring. The drive ring support member is formed by one member and has: base end side parts that regulate movement of the drive ring in a radial direction; tip end side parts that regulate movement of the drive ring to the compressor side; and turbine side receiving parts that regulate movement of the drive ring to the turbine side in the direction of a rotational axis.

Abstract: An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.

Abstract: A fan system includes a motor, a rotatable hub, and a plurality of fan blades. Each of the fan blades includes a substantially rigid spine member, a resilient leading edge member, and a resilient trailing edge member. The leading edge member and trailing edge members are removably coupled with the spine member, such that different leading edge members and different trailing edge members may be chosen to customize the leading and trailing edges of the fan blades. Each fan blade may have more than one type of leading edge member or more than one type of trailing edge member. The leading edge member and trailing edge member may each be coupled with the spine member by urging the leading edge member and trailing edge member in a direction that is substantially perpendicular to the longitudinal axis defined by the spine member.

Abstract: A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.

Abstract: A fan casing assembly for a turbine engine including a casing having an annular fan cooler. The annular fan cooler includes first and second connection assemblies to fix movement of the fan cooler during engine operation, while permitting circumferential thermal growth of the fan cooler without suffering from high cycle fatigue.

Abstract: The present invention relates to an improved structure of fan blades, which comprises a hub, a connecting part, and a plurality of fan blades. The connecting part has a coupling section and a plurality of slits. The connecting part is sleeved around the perimeter of the hub through the coupling section. The slits are circularly disposed close to the perimeter of the connecting part. The fan blades individually have a first end and a second end; the first ends are individually embedded in the slits and combined with the connecting part. Be means of the present invention, the disadvantage of the combination through a non-integrated structure of the fan blades and the hub in the prior art can be overcome.

Abstract: A turbomachinery rotor blade is provided having an aerofoil body, and a hole penetrating the aerofoil body from a suction surface to a pressure surface thereof. The hole is suitable to receive a lacing wire. The blade further has a protrusion from the suction or pressure surface. The protrusion extends in a downstream direction from a downstream side of the hole and/or extends in an upstream direction from an upstream side of the hole, thereby disturbing the suction or pressure surface to locally thicken the aerofoil body adjacent the hole. The maximum radial extent of the protrusion in the radially outward direction of the blade is radially coterminous with the outboard side of the hole, and the maximum radial extent of the protrusion in the radially inward direction of the blade is radially coterminous with the inboard side of the hole.

Abstract: An exemplary embodiment of the present techniques provides a system for decreasing a temperature of a fluid. The system includes an axial flow expander for expanding gas flowed in a direction along an axis thereof. The axial flow expander includes: an outer casing made as a unified structure having an inlet port and an outlet port. An inner casing is fixed inside the outer casing. A rotor shaft is accommodated inside the inner casing, and is aligned with the axis. A number of bearings allow the rotor shaft to rotate around the axis. Moving blades protrude from the rotor shaft and are arranged inside the gas passage in an alternating fashion with a number of stator vanes. The inner casing, the rotor shaft, the bearings, the stator vanes, and the moving blades are integrally assembled, and inserted into the outer casing in the direction along the axis.

Abstract: A hydrokinetic energy conversion system (1) comprising a turbine device (2) comprising a rotor (3) displaying a rotational axis (O), which turbine device is arranged to operate with the rotational axis in an inclined orientation vis-à-vis an incoming body of water (W), and which rotor comprises a blade (10) which is arranged to interact with the incoming body of water such that rotational energy is imparted to the rotor. The blade comprises a first, convex surface (12), a second, concave surface (13) and a free, distal edge (E) where the first surface and the second surface meet. The curvature of the second surface, when viewed in a plane orthogonal to the rotational axis, is such that a maximum depth (Dmax) of the second surface, when measured from a straight line intersecting the rotational axis and the distal edge, is at least 35% of the distance between the rotational axis and the distal edge.

Abstract: The invention concerns a hydraulic adjusting device (1, 35) having at least two leakage paths (24, 25) which are connected by a transition channel (27), a sealing arrangement (18) which leads back to a working chamber (10) being provided in one of the leakage paths (24, 25) in delimiting manner relative to the working chamber (10) of the adjusting device (35).

Abstract: A hollow blade of a gas turbine engine has a sacrificial elongated damper disposed slideably in a chamber for minimizing modes of vibration during operation. The chamber is defined between two opposing surfaces generally spanning radially outward from an axis of the engine and a face facing radially inward. The damper is constructed and arranged to make loaded contact with the face via a centrifugal force created by rotation of the engine.

Abstract: One or more techniques and/or systems are disclosed for a cutter/grinder system that can be engaged with a pump. The cutter/grinder system can comprise an axial cutting operation and a radial cutting operation, comprising a rotary cutter that has both radial and axial cutting edges. The rotating cutter can be operably engaged with a stationary cutter apparatus, non-movably engaged with a pump, where the stationary cutter apparatus comprises both an axial cutting operation and a radial cutting operation, comprising both radial and axial cutting edges. The system can facilitate reduction of a size of solids that may be entrained in a target fluid.

Abstract: A turbofan engine is provided. The turbofan engine includes a nacelle housing including a radially outer wall and a radially inner wall that defines an interior cavity within the nacelle housing. The turbofan engine also includes a fan assembly positioned at least partially within the interior cavity. A flow passage is defined between the radially outer wall and the radially inner wall for channeling a flow of air therethrough. The flow passage is configured to couple a portion of the interior cavity upstream from the fan assembly in flow communication with an ambient environment exterior from the radially outer wall.

Abstract: The present disclosure is directed to an impingement insert for a gas turbine engine. The impingement insert includes an insert wall having an inner surface and an outer surface spaced apart from the inner surface. A nozzle extends outwardly from the outer surface of the insert wall. The nozzle includes an outer surface and a circumferential surface. The insert wall and the nozzle collectively define a cooling passage extending from the inner surface of the insert wall to the outer surface of the nozzle. The cooling passage includes an inlet portion, a throat portion, a converging portion extending from the inlet portion to the throat portion, an outlet portion, and a diverging portion extending from the throat portion to the outlet portion. The cooling passage further includes a cross-sectional shape having a semicircular portion and a non-circular portion.