Abstract: A centrifugal slurry pump impeller including a back shroud and a front shroud each with opposed inner and outer faces and an outer peripheral edge and a central axis, a plurality of pumping vanes extending between the inner main faces of the back and front shroud, each pumping vane including opposed main side faces, a leading edge in the region of the central axis and a trailing edge in the region of the outer peripheral edges of the back and front shrouds with a passageway between adjacent pumping vanes, each passageway including a blended region between each of the main side faces of the pumping vanes and the inner faces of the front and back shrouds wherein a surface of the inner face of at least one of the front and back shrouds includes a raised portion located between the blended regions of adjacent pumping vanes.

Abstract: Disclosed is a multi-phase abradable coating including a ceramic matrix and a dislocator phase.

Abstract: A support system may secure a wind turbine above an angled roof. The angled roof may have a first angled surface, an opposite second angled surface, and a peak between the first angled surface and the second angled surface. The support surface may have a first weighted ballast located along a portion of the first angled surface and a second weighted ballast located along a portion of the second angled surface. The support system may have a connector extending between and connecting a portion of the first weighted ballast and a portion of the second weighted ballast. The connector may extend over the peak. The support system may have a mounting portion on the connector for securing a wind turbine to the connector. The first weighted ballast and the second weighted ballast may be sized and weighted to maintain the wind turbine above the peak during wind conditions.

Abstract: A main-body casing having an inlet port or an outlet port, a rotatable rotor shaft, and a rotor coupled to the rotor shaft are provided. A recess portion opened toward the inlet port is formed in the rotor and a fastening portion (a first shaft portion and a second shaft portion) of the rotor shaft is exposed to the recess portion. A cover portion, which is fastened to the fastening portion by a cover-portion fixing bolt and covers at least a part of the recess portion, is formed having a container shape and has a reinforcing portion located in a periphery of the fastening portion that prevents deflection by increasing rigidity. The cover portion also has a contact-pressure generating portion which is pressed by fastening to the fastening portion in a fastening direction and causes a contact pressure to be generated in the fastening direction.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.

Abstract: A propulsion assembly for an unmanned aerial vehicle (UAV), includes a motor, a propeller seat configured to be driven by the motor and to receive a propeller, and a sensor configured to collect sensing data useful for determining a type of the propeller disposed on the propeller seat and controlling the motor based on the type of the propeller.

Abstract: A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

Abstract: A wind turbine system includes: a ring gear; a yaw drive unit including a pinion gear meshing with the ring gear, the yaw drive unit being configured to rotate the pinion gear; a yaw brake unit configured to generate a braking force for inhibiting rotation of the ring gear; a load information acquiring unit configured to acquire an external load applied to the ring gear; and a control unit configured to release the braking force of the yaw brake unit when a rotational torque generated on the ring gear by the yaw drive unit has been larger than the external load acquired by the load information acquiring unit, in switching the ring gear from a stationary state to a rotating state.

Abstract: A planetary gear arrangement including a sun gear configured to rotate about an axis of rotation, a plurality of planet gears driven by the sun gear, a ring gear engaged with the plurality of planet gears and a plurality of journal pins arranged in the plurality of planet gears forming a converging gap and a diverging gap therebetween. Each journal pin has at least one longitudinal groove along an outer surface thereof, configured to guide oil on the outer surface when the oil is carried from the converging gap towards the diverging gap due to a revolving movement between a planet gear around a corresponding journal pin. A journal pin for supporting a gear and a gas turbine engine.

Abstract: A method for producing a hollow composite structure, such as a spar beam for use in a wind turbine blade, includes placing fiber reinforcement material around a mandrel within a mold, and curing the fiber reinforcement material. The mandrel is formed from a compressible material having a rigid neutral state with a rigidity to maintain a defined shape of the mandrel during lay up and curing of the fiber reinforcement material. Subsequent to curing, a vacuum is drawn on the mandrel to compress the compressible material so that the compressed mandrel can be drawn out through an opening in the composite structure, the opening having a size such that the mandrel could not be withdrawn through the opening in the rigid neutral state of the mandrel.

Abstract: The present invention relates to a shaft for a propulsion system configured to rotate a reducing mechanism about a rotational axis, the shaft comprising: —a first end configured to engage with an input gear of the reducing mechanism, —a first bellows and a second bellows, the first bellows and the second bellows being rotationally symmetrical about the rotational axis, the first bellows extending between the first end and the second bellows, and —a frustoconical body mechanically connecting the first bellows and the second bellows.

Abstract: The disclosure relates to devices, systems, and corresponding methods to be used in connection with agricultural planters. More particularly to a vacuum and generator system including a housing, a fan assembly within the housing, a generator, and a hydraulic motor. Some implementations include a voltage regulator or voltage regulation module. The system allow for adjustable fan control without affecting electrical output, integral cooling, and multi-level voltage output from a single generator. Additionally, the system provides greater efficiency in operating an agricultural implement.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gears, and a ring gear. The gear assembly is connected to an input shaft and an output shaft. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and is driven by the input shaft. A component of the gear assembly drives the output shaft. The gear assembly further comprises an output shaft reversal mechanism configured to reverse the rotational direction of the output shaft.

Abstract: Various implementations include, an out-of-plane feedback-type fluidic oscillator. including a first portion, a second portion, a middle portion coupled between the first portion and the middle portion, and an axis of rotation. The middle portion includes a first side, a second side opposite and spaced apart from the first side, and a middle plane, an interaction chamber, a fluid supply inlet, an outlet nozzle, a first feedback a channel, and a second feedback channel. The first side is coupled to the first portion, and the second side is coupled to the second portion. The first side, the second side, and the middle plane extend circumferentially around the axis of rotation. The middle plane is disposed equally distanced from the first side and the second side. The fluid stream oscillates as it flows through the interaction chamber such that the fluid stream oscillates as the fluid stream exits the outlet nozzle.

Abstract: A propeller safety device is provided. The propeller safety device is configured to insert a moving part of a propeller into a fixed part during a crash of an air mobility to allow a reduction in the total length of the propeller, thereby preventing the propeller from hitting the ground. Accordingly, a secondary accident due to fragments formed when the rotating propeller hits the ground is prevented.

Abstract: The invention relates to a planetary gear box, which has a sun gear, a plurality of planet gears, a ring gear, a plurality of plain bearing pins and an axially front carrier plate and an axially rear carrier plate. The plain bearing pin and the planet gear here configure a lubricated plain bearing which includes a plain bearing gap. Furthermore, the plain bearing pin, on the contact face thereof, configures a feed pocket which is provided and configured to receive oil and during the operation deliver oil in the circumferential direction to the plain bearing by way of a delivery edge. It is provided that the feed pocket is configured in the contact face of the plain bearing pin in such a manner that the delivery edge has a profile that deviates from a straight profile parallel to the longitudinal axis of the plain bearing pin.

Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.

Abstract: Disclosed is a turbomachine (10) with counter-rotating turbine for an aircraft, comprising: —a high-pressure body, —a low-pressure counter-rotating turbine (22), —a planetary-type mechanical epicyclic reduction gear (42), —a guide bearings (56-62) for the turbine shafts (36, 38), characterised in that said reduction gear (42) and certain of the bearings (60, 62) are housed in a lubrication chamber (86) supplied with oil and comprising dynamic seals (86a-86d), and in that the turbomachine comprises circuits (C1, C2) for pressurising these seals.

Abstract: The invention relates to a method for controlling a wind turbine during start up, from a non-producing operation mode to a power producing operation mode when limit cycles occur during start-up. Limit cycles are detected when a number of cut-in transitions or a number of cut-out transitions are detected. A cut-in transition is when the wind turbine fails starting up despite having the wind speed or rotor speed normally required to enter a power producing operation mode. A cut-out transition is occurring when the wind turbine is falling out of power producing operation mode after having entered the power producing operation mode.