Abstract: A pump apparatus includes: a rotational shaft; a hub portion mounted to the rotational shaft; a centrifugal pump vane mounted to a circumferential surface of the hub portion; an annular disc portion mounted to a tip end of the centrifugal pump vane; and an axial turbine blade mounted to an outer circumferential surface of the annular disc portion. A liquid flow passage through which a liquid flowing from a first side toward a second side in an axis direction of the rotational shaft flows into the centrifugal pump vane is formed at a radially inner side of the annular disc portion, and a gas flow passage through which a gas flowing from the second side toward the first side passes through the axial turbine blade is formed at a radially outer side of the annular disc portion.

Abstract: A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade.

Abstract: A guide blade arrangement (20) for a turbomachine (1), including a guide blade airfoil (22) and a platform (21). The guide blade airfoil (22) is situated at a side (21.1) of the platform (21) facing the gas channel, an opposite side (21.2) of the platform (21) facing away from the gas channel being contoured at least in one area (30.1, 30.2) with elevations (25) and depressions (26) that follow one another in the circumferential direction (23) in relation to a longitudinal axis (2) of the turbomachine (1), and the elevations (25) and depressions (26) at the side (21.2) facing away from the gas channel being set via a platform thickness (31), taken radially in each case, that is variable in the circumferential direction (23) and that repeatedly increases and decreases with a continuous profile.

Abstract: Examples disclosed herein include a fan blade of a gas turbine engine. The disclosed fan blade includes a main body having a leading edge and a trailing edge. The fan blade includes a leading edge guard covering the leading edge and a leading section of the main body adjacent to the leading edge. The leading edge guard includes a plurality of leading edge guard segments consecutively arranged in a spanwise direction along the leading edge of the fan blade. Each of the plurality of leading edge guard segments are oriented at an angle relative to a root of the fan blade. Each of the plurality of leading edge guard segments includes a nose portion coupled to the leading edge and a wing portion coupled to opposing sides of the leading section of the main body.

Abstract: A shaft power transfer system includes a first mechanical clutch mechanism operably coupling a high-pressure shaft to a low-pressure shaft. The first mechanical clutch mechanism transfers power from the high-pressure shaft to the low-pressure shaft at a predefined first speed transient condition. The system further includes a second mechanical clutch mechanism that operably couples the low-pressure shaft to the high-pressure shaft. The second mechanical clutch mechanism transfers power from the low-pressure shaft to the high-pressure shaft at a predefined second speed transient condition where the predefined first speed transient condition is different than the predefined second speed transient condition.

Abstract: The present invention provides a method for producing a steam turbine member that is highly superior in smoothness. The present invention provides a method for producing a steam turbine member including a cladding layer forming step of forming a cladding layer from a powdered material containing a metal in a region of a base material in which corrosion easily occurs, and a surface heating step of heat-melting a surface of the cladding layer.

Abstract: A scroll casing of a centrifugal compressor includes a scroll part forming a scroll passage of the centrifugal compressor. The scroll part has a near-circular scroll cross-section which includes a first arc portion extending from a connection position with a hub-side passage surface of a diffuser passage of the centrifugal compressor (first position) to a one-direction side (side toward fourth position), a second arc portion formed on the one-direction side of the first arc portion so as to include at least a part of a region between an outermost end in the radial direction (second position) and an innermost end in the radial direction (fourth position), and a third arc portion formed on the one-direction side of the second arc portion so as to include an end position of the scroll part on the one-direction side (fifth position) and satisfies a relationship of R2>R3, where R2 is a curvature radius of the second arc portion, and R3 is a curvature radius of the third arc portion.

Abstract: A wind-turbine-blade-pitch system for a wind turbine comprises at least one electric motor which can be configured to be addressed by an inverter. The inverter can be configured to be addressed by a rectifier. The rectifier and the inverters are configured to be arranged locally separated from each other in the wind-turbine-blade-pitch system. The power distribution device and at least one power-storage system are connected via one or more electrical supply lines. The power distribution device can be configured to supply the at least one electric motor with electrical energy from the power storage system, via the one or more electrical supply lines.

Abstract: Disclosed is a wind turbine blade and a method for its manufacture. The wind turbine blade comprises an upwind side shell part, a downwind side shell part, a leading edge and a trailing edge. A flatback web is arranged at the trailing edge, which couples the upwind side shell part with the downwind side shell part, wherein the flatback web comprises at least one U-shaped end section with a recess, into which the upwind side shell part and/or the downwind side shell part is inserted and bonded to the U-shaped end section by an adhesive.

Abstract: Techniques for controlling the yaw of a wind turbine system by controlling a plurality of yaw drive actuators. When the yaw drive actuators are applying the same torque to all the motors, this can lead to some motors overspeeding, if the motor is not engaged when the yaw system is activated. Therefore, if the actual motor speed reference of a yaw drive actuator is higher than a specific motor speed reference, then an output signal to reduce the actual motor speed reference is applied to the yaw drive actuators with an actual motor speed reference higher than the specific motor speed reference.

Abstract: A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.

Abstract: The compressor section can have a centrifugal impeller operable to rotate around an axis, the centrifugal impeller having blades, a compressor inlet oriented towards the front and axially relative the axis, a compressor outlet oriented radially outwardly relative the axis, a diffuser having a diffusion flow path, a diffuser inlet in fluid flow communication with the compressor outlet, a diffusion flow path between a rear wall and a front wall; a collector extending circumferentially around the axis, having a collector inlet in fluid communication with the diffuser outlet, and a collector outlet; and hollow structural members protruding rearwardly from the rear wall, the hollow structural members being circumferentially interspaced from one another, each hollow structural member having a length extending radially along the rear wall and having an internal conduit extending radially inwardly along the length.

Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.

Abstract: Provided is a method for monitoring one or more wind turbines in a wind farm, each wind turbine having a rotor with rotor blades which are rotatable around a rotor axis, wherein one or several times during the operation of the wind farm a process is performed that includes i) obtaining a digital image of the respective rotor blade, the image being a current image taken by a camera looking at the respective rotor blade; ii) determining one or more operation characteristics of the respective rotor blade by processing the image by a trained data driven model, where the image is fed as a digital input to the trained data driven model and the trained data driven model provides the one or more operation characteristics of the respective rotor blade as a digital output.

Abstract: A rotor blade in an embodiment includes: a suction surface side projecting portion projecting from a suction surface on a leading edge side at a blade tip of the blade effective portion; and a pressure surface side projecting portion projecting from a pressure surface on a trailing edge side at the blade tip of the blade effective portion. The suction surface side projecting portion includes: a leading edge side end surface including a contact surface that comes into contact with the pressure surface side projecting portion of the adjacent rotor blade and a non-contact surface that does not come into contact with the pressure surface side projecting portion of the adjacent rotor blade during rotation; a groove portion formed from the non-contact surface to the trailing edge side; and a joining member joined to the groove portion, the joining member being formed of an erosion-resistance material.

Abstract: A rotor blade retention assembly includes a central hub, a rotor blade including an upper outer surface, a lower outer surface, a blade hole, and a proximal end coupled to the central hub, a strap member extending along a portion of the rotor blade such that a distal end receiving portion extends into the blade hole, and a retainer assembly disposed within the blade hole and coupled to the strap member. The retainer assembly includes an upper bushing and a lower bushing slidably disposed within the blade hole. The upper bushing includes a counterbored portion. The retainer assembly also includes an outboard blade pin disposed within the distal end receiving portion and includes a blade pin inner cavity.

Abstract: A method for controlling a wind turbine, and an associated wind turbine, includes receiving a wind direction signal indicative of an instantaneous wind direction at the wind turbine and receiving a signal indicative of an instantaneous wind speed at the wind turbine. A rate of change of the wind direction at the wind turbine and a rate of change of wind speed at the wind turbine are determined. A control signal for a pitch system for blades of the wind turbine is determined based on the rate of change of the wind direction and the rate of change of wind speed. The pitch of the blades is then changed with the pitch system based on the control signal to reduce loads on the wind turbine from changes in the wind direction simultaneous with changes in the wind speed.

Abstract: An air-conditioning apparatus includes: a centrifugal air-sending device including a fan and a scroll casing having a tongue portion and a discharge portion, and a housing having a housing suction port and a discharge portion. A trailing edge of a blade located closest to a wall portion of the housing is a first trailing edge portion, and a leading edge of a blade located closest to the tongue portion is a first leading edge portion. In a first region, a boundary portion located closest to the tongue portion is located between first and second straight lines. The first straight line passes through a rotation axis of the fan and the first trailing edge portion, the second straight line is parallel to the first straight line and passes through the first leading edge portion, and the first region forms part of the housing suction port close to the tongue portion.

Abstract: A crank and linkage assembly for a component of a turbocharger includes a linkage and two cranks each including a pin whose outer surface defines a pin groove. Each end of the linkage defines a through bore for receiving one of the pins. At each end of the linkage, a plurality of fingers are integrally formed and of one piece with the linkage, the fingers extending parallel to, and circumferentially spaced about, the through bore axis. The fingers are elastically bendable such that the hooks move away from the bore axis and such that a restoring force of each of the fingers acts in a direction to bend the hooks back toward the bore axis. The assembly can be assembled by a push-to-connect process in which each pin is advanced into the respective through bore until the hooks snap into the respective pin groove.

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a pressure side, a suction side, and a mean line. First and second ribs each connect the pressure side and the suction side. Each of the first and second ribs define a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel there between. The continuous cooling channel has a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. The pressure side portion and the suction side portion each have a cross-sectioned shape selected from an L-shape, a T-shape, and an l-shape.