Abstract: A fan motor includes: a housing, a rotation shaft oriented across an inner center of the housing, an impeller located at a first side of the rotation shaft, a rotor connected to the rotation shaft and spaced apart from the impeller in an axial direction, a stator that surrounds the rotor, a first bearing located at a first end of the rotation shaft, a second bearing that is located at a second end of the rotation shaft and that is configured to rotatably support the rotation shaft, and a first bearing housing that accommodates and supports the first bearing, that is fixed inside the housing, and that is configured to guide a flow of air introduced into the housing.

Abstract: Aircraft comprising a primary propeller driven in rotation by a motor, the motor having a first assembly and a second assembly movable in rotation relative to each other along an axis of rotation, the primary propeller being secured in rotation to one of said first assembly and second assembly, the first assembly and the second assembly being movable in translation relative to each other along a direction of translation defined by the axis of rotation, between a rest position and a service position, characterized in that said aircraft comprises a locking system, comprising a housing and an indexing element, the housing being formed in one among the first assembly and the second assembly, the indexing element being secured to the other among the first assembly and the second assembly, the locking system having an engaged configuration in which the indexing element is at least partially inserted into the housing.

Abstract: A scroll compressor includes a compressor housing, a high-pressure chamber, a low-pressure chamber, an oil return channel having an oil return throttle arranged therein, a driven eccentric unit, a fixed scroll, an orbiting displacement scroll arranged on the driven eccentric unit which interacts with the fixed scroll, a sliding disk arranged between the orbiting displacement scroll and the compressor housing, a back-pressure chamber arranged adjacent to the orbiting displacement scroll, and a gas connecting channel having a gas connecting throttle arranged therein. The oil return channel fluidically connects the high-pressure chamber with the low-pressure chamber. The gas connecting channel fluidically connects the back-pressure chamber with the high-pressure chamber. The oil return channel and/or the gas connecting channel extends through the sliding disk. The sliding disk includes the oil return throttle and/or the gas connecting throttle.

Abstract: A fan includes a hub and a plurality of fan blades. The hub has an axle center. The fan blades are disposed around the hub. Each of the fan blades has a bent portion, and the bent portions of the fan blades are extended along a surrounding direction surrounding the axle center. The hub is welded with the bent portion of each of the fan blades along the surrounding direction. As a result, the number of fan blades is maximized, the strength is simultaneously ensured to be enough, and the advantages of effectively enhancing the fan characteristics are achieved.

Abstract: A method for operating a cluster of a plurality of wind turbines is disclosed. For each of the wind turbines, one or more parameter values of a parameter being indicative for a condition occurring at the wind turbine are derived, based the measurements obtained by the wind turbine. In the case that a derived parameter value for a specific wind turbine exceeds a trigger value, measures for mitigating an effect of the condition at the specific wind turbine are initiated. The derived parameter values for the wind turbines of the cluster of wind turbines are compared to an expected distribution of the parameter values. In the case that a distribution of the derived parameter values differs from the expected distribution of the parameter values, the trigger value is adjusted, and the adjusted trigger value is subsequently applied when comparing the derived parameter values to the trigger value.

Abstract: A centrifugal compressor for a chiller includes a first stage impeller, a first stage diffuser, a second stage impeller, a second stage diffuser, and a second stage volute. The first stage impeller is arranged to receive refrigerant from an inlet. The second stage volute is disposed downstream of the second stage diffuser to receive the refrigerant after the refrigerant has been compressed. The second stage volute has a reverse overhung configuration.

Abstract: A compressor casing for a turbine engine, the casing comprising: a housing comprising a radially inner e surface; an upstream ferrule; and a downstream ferrule; each of the ferrules having a respective inner surface capable of defining an air stream, and each of the ferrules having an outer surface facing the inner surface of the housing, the ferrules being attached to the cantilevered housing and being axially arranged so as to be separated by an axial clearance. Additionally, a turbine engine comprising such a casing and a stage of variable-setting vanes.

Abstract: The present disclosure relates to wind turbine blades (22) configured to receive a peripheral device (250a, 250b, 250c) at a portion of the outer surface (211) of the blade (22), and wherein the wind turbine blade (22) is configured to magnetically couple to the peripheral device (250a, 250b, 250c). The present disclosure also relates to wind turbine blade assemblies (200) and methods (700) to provide the same.

Abstract: A fan is provided herein, including a housing, a hub, and a plurality of blades. The housing includes a top case and a bottom case. The hub is rotatably disposed between the top case and the bottom case in an axial direction. The blades extend from the hub in a radial direction, located between the top case and the bottom case. Each of the blades has a proximal end and a distal end. The proximal end is connected to the hub. The distal end is opposite from the proximal end, located at the other side of the blade, having at least one recessed portion. Each of the recessed portions form a passage for air.

Abstract: A blower includes a motor, a plurality of fans coaxially arranged in multiple stages, a housing having an inlet opening and a discharge opening, and a battery mounting part to which a battery is removably mountable. A rotational speed of the motor is within a range of 50,000 rpm to 120,000 rpm. A diameter of each of the fans is within a range of 30 mm to 70 mm. An area of the discharge opening is within a range of not less than an area of a circle having a diameter of 2.5 mm and not more than an area of a circle having a diameter of 10 mm. A blowing force of air discharged through the discharge opening is within a range of 1 N to 3 N.

Abstract: A heat dissipation fan includes a fan blade assembly. The fan blade assembly includes a plurality of fan blades and a plurality of silencers connected to the plurality of fan blades and evenly arranged along a rotation direction of the plurality of fan blades. A center of gravity of the plurality of silencers coincides with a rotation center of the heat dissipation fan. At least some fan blades of the plurality of fan blades have different contact surfaces with air.

Abstract: Some embodiments of the disclosure provide an air intake bypass recirculation structure with adjustable air entraining amount and controllable broadband noise which includes main body of the air intake bypass recirculation structure and an air entraining amount adjusting structure. In some examples, an air intake bypass recirculation cavity is formed in the main body of the air intake bypass recirculation structure. An air inlet of an air intake pipe and an air outlet of the air intake pipe are formed in two ends of the main body of the air intake bypass recirculation structure respectively. An airflow inlet of the air intake bypass recirculation structure and an airflow outlet of the air intake bypass recirculation structure are formed in the inner side of the main body of the air intake bypass recirculation structure. The air entraining amount adjusting structure is arranged in the air intake bypass recirculation cavity.

Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

Abstract: An abradable material for a rub strip of a gas turbine engine component includes a polymer matrix, and an organic or inorganic filler distributed through the matrix, wherein the abradable material has a compression spring rate profile including: less than 50,000 lb/in at ?65° F., less than 35,000 lb/in at room temperature, and less than 35,000 lb/in at 200° F.

Abstract: An air duct component includes first and second volute members arranged oppositely in a cross section perpendicular to an axis of a cross-flow impeller. An inner end of the first volute member includes a volute tongue. A cross-flow air duct formed between the first and second volute members includes a middle air duct section and an end air duct section arranged along an axial direction of the cross-flow impeller. The middle air duct section includes a middle air outlet duct located downstream of a vertical line that passes through the volute tongue and is perpendicular to the second volute member. The end air duct section includes an end air outlet duct located downstream of the vertical line. A cross-sectional area of the middle air outlet duct is larger than a cross-sectional area of the end air outlet duct.

Abstract: A motor-driven compressor, a housing structure for a motor-driven compressor, and a method of installing a soundproof cover on a motor-driven compressor are provided. A soundproof cover includes layers that include a first layer and a second layer. The first layer is placed over a housing, and the second layer is placed over the first layer. Each of the layers includes a first segment and a second segment. A second selection layer is located inward of a first selection layer. A boundary in the second selection layer is located above the boundary of the first selection layer.

Abstract: A compressor includes a rotation shaft which rotates around an axis, an impeller which press-feeds a fluid from one side in an axial direction toward an outward side in a radial direction by rotating together with the rotation shaft, a casing which surrounds the rotation shaft and the impeller and in which an exit flow channel for introducing a fluid press-fed from the impeller is formed, and an acoustic liner which is provided so as to face the inside of the exit flow channel in the casing. The acoustic liner has a plurality of open hole portions which are arranged with intervals therebetween, and acoustic spaces which communicate with the open hole portions and are independently provided for the respective open hole portions.

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 process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.