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: 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 fan with airfoil blades is provided for a regenerative air vacuum street sweeper. The blades are formed using cut and pressed upper and lower panels which are welded at a forward edge to a rod to form the airfoil leading edge and welded at the rear edges to form the airfoil trailing edge. Pins extend laterally outwardly from the rod for mounting each blade in corresponding holes in the front and rear plates of the fan housing. The side edges of the blade are welded to the plates at a 9-11° angle of attack. The airfoil blades allow for reduced size, horse power, noise, and manufacturing and shipping costs.

Abstract: A rotary fan system with dual rotation axes, wherein a driving arm rotates about a first axis, and trailing arm rotates about a second axis.

Abstract: A fan wheel and a radiator of a motor vehicle, the fan wheel having a hub to which a number of fan blades is connected. The fan blades each have a stabilizing structure of a first material, which is surrounded by means of a respective body of a second material.

Abstract: A electric motor assembly includes an electric motor and a fan assembly coupled to the electric motor and configured to rotate therewith about an axis. The fan assembly includes a hub including a core ring, a first inner ring circumscribing the core ring, and a first plurality of circumferentially-spaced ribs extending between the core ring and the first inner ring. The hub also includes a second inner ring circumscribing the first inner ring and a second plurality of circumferentially-spaced ribs extending between the first inner ring and the second inner ring, and a plurality of circumferentially-spaced blades coupled to an outer periphery of the hub.

Abstract: The present invention provides a blower with reduced noise. The blower comprises a blower main body incorporating a centrifugal fan. The blower main body is configured to suck air from both sides of the blower main body by rotation of the centrifugal fan. The centrifugal fan includes a support plate having a rotation center and a plurality of blades provided on each of a first surface and a second surface of the support plate. A position of at least part of the plurality of blades on the first surface and a position of at least part of the plurality of blades on the second surface are misaligned in a circumferential direction, and/or a number of the plurality of blades on the first surface differs from a number of the plurality of blades on the second surface.

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 centrifugal fan includes an impeller with a base expanded radially, vanes arranged circumferentially, extending from a radially inner side to a radially outer side, and ends thereof at one axial side being connected to the base, and a ring portion connecting ends of the vanes at the other axial side. The vanes include first vanes and second vanes, when viewed axially, the lengths of the second vanes are larger than the lengths of the first vanes, the first vanes and the second vanes are circumferentially arranged alternatingly. Gaps are provided between radially outer ends of the first vanes and the second vanes that are circumferentially adjacent to each other, and sizes of circumferentially adjacent ones of the gaps are different from each other.

Abstract: An interstage throttle for a centrifugal compressor includes a flow guide plate, a throttle ring, a drive ring, and linkage assemblies. The flow guide plate includes guide vanes that form channels that direct working fluid in between stages of the compressor. The linkage assemblies connect the drive ring to the throttle ring such that rotation of the drive ring moves the throttle ring in an axial direction. Teeth of the throttle ring partially block the channels when the throttle ring is in an extended position. A method of operating a centrifugal compressor includes directing the working fluid discharged from the first stage to a second stage via channels in a interstage throttle. A centrifugal compressor includes a first stage with a first impeller, a second stage with a second impeller, and an interstage throttle fluidly connecting the first stage to the second stage.

Abstract: A ceiling fan includes: a column; a hub case which is coupled to the column and rotatable with respect to the column; and a plurality of blades disposed in the hub case, wherein each of the blades comprises: an upper blade having one end coupled to the hub case; a lower blade which has one end coupled to the hub case and is spaced apart from the upper blade; and an end tip connecting the other end of the upper blade and the other end of the lower blade.

Abstract: A ceiling fan module with an energy dissipation function and a configuration method thereof are disclosed. The ceiling fan module includes a fan rack, a fan and an energy dissipation assembly. The energy dissipation assembly passes through the fan rack and the fan and connects the fan rack and the fan; the energy dissipation assembly includes steel cables (3), high-damping vibration attenuation rings, fasteners and balancing weights; two high-damping vibration attenuation rings are sleeved on one steel cable, and the two high-damping vibration attenuation rings are respectively located at two ends of the steel cable; the high-damping vibration attenuation rings are mounted on the fan rack and the fan and separate the fan rack from the fan; the fasteners are mounted on the steel cables and are located on outer sides of the high-damping vibration attenuation rings and the fan rack.

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: 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: An axial fan for an outdoor unit of an air conditioner is provided. The axial fan may include at least one blade connected to a hub. The at least one blade may include a blade inner portion, a blade outer portion provided outside of the blade inner portion in a radial direction, and a blade connector that connects the blade inner portion and the blade outer portion as a curved surface, thereby improving noise and increasing an air volume.

Abstract: A fan unit includes a centrifugal fan, an air flow volume detector, and a main body casing housing the centrifugal fan and the air flow volume detector. The centrifugal fan includes a fan casing and a rotor. The air flow volume detector includes main body, and a probe that detects an air flow volume equivalent quantity equivalent to an air flow volume provided by the centrifugal fan. The fan casing includes a bell mouth defining an air inlet and having a convex surface. A distance from the probe to the surface of the bell mouth is larger than 0 and smaller than one third of a radius of the air inlet. A thermal air velocity sensor detects, as the air flow volume equivalent quantity, an air velocity of air flowing through the air inlet not connected to a duct by measuring an amount of heat dissipated from the probe.

Abstract: A centrifugal compressor impeller includes a plurality of blades on a front side that extend from a first axial side to an outer radial end of the impeller. The centrifugal impeller includes a back side having a nonlinear backwall. The backwall can include a flat area hear a bore of impeller, a flat area near a tip of the impeller, and a convex surface between the flat areas of the bore and the tip. In some forms the impeller further includes a concave surface between the convex surface and the tip to form an s-shape. A transition or inflection point can denote the change from convex to concave. The convex and/or concave surfaces can take any variety of forms such as constant radius sections and/or compound curves.

Abstract: A bladed disc system for a turbine engine having a disk portion and a plurality of blade portions which are associated with a stator section and an intercavity sealing portion, disc portion shaped such that blade portions are able to fit within firtree slot in disc portion, blade portion having aerofoil section and root section, aerofoil section having portion shaped such that they extend proximate to intercavity sealing portion, disc portion extending from portion that connects with drum to outer edge at which blade portions are connected with disc portion having width transition region in which thickness of disc increases from point at which disc connects to drum to outer edge at which it holds blade portions, and wherein width transition region has curved width transition region with radius r, and an overhanging portion which extends into the intercavity spacing between the width transition region and the intercavity sealing portion.

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.

Abstract: The present invention relates to an assembly for a turbomachine, comprising: a first rotor; a second rotor, and a damper (2) configured to damp a displacement of the first rotor relative to the second rotor, the damper comprising: a first portion (21) bearing against the first rotor and having a first thickness, a second portion (22) bearing against the second rotor and having a second radial thickness, and a third portion (23) connecting the first portion (21) to the second portion (22) and having a third radial thickness, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness.