Abstract: A rotary pump housing having a cylindrical bore, a pumping chamber and a motor stator including an electrically conductive coil located within the housing and surrounding a portion of the cylindrical bore. A rotor has a cylindrical shaft with an impeller and one or more magnets located within the shaft that are responsive to the motor stator to drive actuation of the rotor. The housing bore is closely fitted to the outer surface of the shaft forming a hydrodynamic journal bearing with an annular clearance defining a leakage flow path. One or more of radial or axial thrust bearings may be provided to provide rotation stability to the rotor and flow within the leakage flow path. The relative orientation of positions of the inflow, outflow, and leakage flow paths may be varied within the pump, such as to accommodate different intended methods for implantation and/or use.

Abstract: A propeller, a propeller kit, a power assembly, a power kit and an unmanned aerial vehicle (UAV). The propeller includes a hub and at least two blades connected to the hub. The hub is detachably mounted on a corresponding drive apparatus by a mounting member corresponding to the hub, so that the propeller is mounted on the corresponding drive apparatus. A surface, facing the mounting member, of the hub is provided with a first fitting portion. A surface, facing the hub, of the mounting member is provided with a second fitting portion corresponding to the first fitting portion. The first fitting portion matches the second fitting portion. In the foregoing manner, a user can be prevented from incorrectly mounting a forward propeller and a counter-rotating propeller during the use of a quick-detachable propeller in the embodiments of the present application.

Abstract: A fan assembly with a digital display structure, including an upper housing and a lower housing, the upper housing is vertically installed on the lower housing; a liquid crystal display (LCD) screen and an LED light strip that are vertically installed on the upper housing and the lower housing, and the LCD screen is electrically connected to the LED light strip; a transmission bearing and a fan body that are vertically installed on the upper housing and the lower housing, the transmission bearing is vertically installed on a bracket, the fan body is vertically installed on the transmission bearing, and the transmission bearing is connected to the fan body to drive the fan body to rotate; a light-transmissive grid, which is located between the upper housing and the lower housing, and the light-transmissive grid is respectively connected to the upper housing and lower housing.

Abstract: A rotor blade is provided that includes an airfoil extending spanwise from a base to a tip. The airfoil extends longitudinally (e.g., chordwise) from a leading edge to a trailing edge. The airfoil extends laterally between a first side and a second side. The airfoil includes a body and a weight. The body includes a plurality of body layers. Each of the body layers includes fiber reinforcement within a body thermoplastic matrix. The weight includes a weight layer embedded within the body. The weight layer includes metal powder within a weight thermoplastic matrix.

Abstract: A method for commanding an upstream wind turbine in a wind farm having a plurality of spatially distributed wind turbines and a method for controlling the upstream wind turbine in the wind farm.

Abstract: A rotor blade, the rotor blade comprising a cavity and one or more nozzles for the expulsion of compressed air from the rotor blade cavity thereby resulting in rotation of the rotor blade. The rotor blade further comprises a pressure regulating arrangement, the pressure regulating arrangement being operable to release compressed air from the rotor blade cavity.

Abstract: A method of joining first and second blade components of a rotor blade includes arranging the first blade component and the second blade component together at an interface. The first and second blade components are formed of different materials having different stiffnesses. The method further includes providing a gap at the interface of the blade components. Further, the method includes securing the blade components together by at least partially filling the gap with a filler material. Moreover, the method includes further securing the blade components together via an infusion process, wherein, during the infusion process, additional filler material further fills the gap or covers at least a portion of the filler material. In addition, the method includes allowing the filler material(s) to cure. Thus, upon curing, the filler material(s)—smoothly transitions a load between the different materials of the blade components, thereby limiting an associated stress at the interface.

Abstract: Disclosed is a system for reducing blade tip vortex cavitation by controlling mass flow. The system reduces blade tip vortex cavitation that occurs around blades of a propulsive propeller of a ship when the propulsive propeller rotates to generate force required to propel the ship across the sea by forming a plurality of flow holes in the propeller blades and controlling mass flow through the plurality of flow holes, i.e., appropriately discharging water to the outside or suctioning outside water through the plurality of flow holes, thereby reducing underwater noise and vibration of the hull. The system includes a propeller, a water feeding pipe, a water supply/suction unit, and a controller.

Abstract: A fan system comprises a hub, a plurality of fan blades, a drive system, and a stationary tube. The hub is configured to rotate. The fan blades are mounted to the hub. The drive system comprises a rotatable hollow output shaft. The hollow output shaft is in communication with the hub, such that the drive system is operable to rotate the hub via the hollow output shaft. The stationary tube is inserted through the hollow output shaft. The stationary tube is configured to remain stationary as the hollow output shaft rotates. Wires and the like may be passed through the stationary tube, to reach an accessory mounted at the bottom of the stationary tube. The fan system may also include a detector, such as a heat detector, a smoke detector, or an accelerometer. The detector may power down the fan system in response to detecting certain conditions.

Abstract: A basic mechanism for converting fluid energy into mechanical energy is provided. A blade index plate, fluted disc hold-down devices, a rolling pressing wheel, bevel gears, a fluted disc, a gear, bearings and a stepping self-locking motor are disposed in a hub. First shaft passing holes annularly and uniformly distributed around the hub are formed in a penetrating manner in an annular steel belt. One end of a blade shaft extending out from a root end of each blade is fixedly connected with a blade seat, and the other end of the blade shaft extending out of a head end of each blade is assembled with the annular steel belt. The annular steel belt is correspondingly connected with and penetrated through the blade shaft. The head end of the blade is fixedly provided with a blade baffle plate.

Abstract: A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes two unique gear assemblies each configured to rotate one of the tip and hub segments.

Abstract: The invention proposes an aeronautical turbine engine assembly comprising an upstream casing (55) to which guide blading (48a) is fastened, and a downstream casing (58) to which a sealing element (62) provided with an abradable material for rotor blading is fastened. This assembly further comprises a shroud ring (66) placed between the upstream casing and the downstream casing and fastening means (68) for detachably fastening the shroud ring. In order to be fastened to the upstream casing, the guide blading (48a) of the turbine engine is mounted on a downstream hook (480b) of the upstream casing, without being hooked onto the shroud ring (66), and the downstream casing (58) has an upstream hook with which the sealing element (62) is engaged in order to be fastened to the downstream casing, or the shroud ring has an upstream hook on which the sealing element (62) is mounted so as to be fastened to the downstream casing.

Abstract: A multifunctional handheld fan is disclosed, including a fan main housing with two ends interpenetrated each other. A fan component is provided in the fan main housing, a lighting component is provided at an air outlet of the fan main housing, and a handle component is provided on an outer wall of the fan main housing. The handle component includes a connecting housing, and one end of the connecting housing is threaded with a handle housing. A battery is installed in the handle housing, and one end of the handle housing away from the connecting housing is provided with a flashlight component. By setting up the fan component, the lighting component and the flashlight component, so that the handheld fan of the present disclosure has the functions of blowing, lighting and flashlight, making it suitable for night use and thus is multifunctional.

Abstract: A ceiling fan includes an outer shield, a middle ring, a blade bracket, and a fan blade. The middle ring is pivotally connected to the outer shield and rotates relative to the outer shield. The blade bracket protrudes from the middle ring and has two guiding surfaces located on opposite sides of the blade bracket. The fan blade is combined with the middle ring by the blade bracket. The fan blade has an opening on an end close to the blade bracket. The fan blade further includes a housing, one or more supporting ribs, and two guiding limiting parts.

Abstract: An arrangement for influencing liquid flow comprises a first section selectively configurable to provide a vortex generator surface to induce vortices in the liquid flow. The arrangement further comprises a second section, wherein the first section and second section are movable relative to one another to provide the vortex generator surface.

Abstract: A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis. The first screen has a first screen axial width L1 extending from the front wall to the rear wall. The inlet guard further includes a second screen extending at least partially circumferentially about the central axis. The second screen is disposed radially outward of the first screen and axially overlaps the first screen. The second screen has a second screen axial width L2 less than the first screen axial width L1.

Abstract: Methods and systems for surge control in a compressor system. A recirculation valve position may be actuated in response to identified conditions of potential surge, determined from a compressor map. Recirculation valve position may be controlled by calculating distance of current operating state to a surge line and using proportional integral control to manage the distance. Compressor speed command may be derated in response to identified surge, determined from one of speed fluctuations of the compressor speed, or variance of a compressor speed tracking error.

Abstract: In one or more embodiments, one or more systems may comprise a fan housing for use in a portable chassis without a vent on a bottom cover. A plurality of tabs located proximate an opening in the bottom wall extend axially to provide support. In some embodiments, a disc is coupled to the plurality of tabs. In some embodiments, a ring is coupled to the plurality of tabs, wherein deflection of the ring positions the ring relative to a fan hub.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.

Abstract: A gas turbine engine includes a heat exchanger and an inlet shroud. The heat exchanger is configured to transfer heat. The inlet shroud is configured to be coupled with the heat exchanger upstream of the heat exchanger.