Abstract: Implementations of an enhanced axial air mover system address various issues such as drying performance, transportability, storage, use, and assembly. Some implementations include ergonomic positioning of a carrying handle relative to positioning of a fan-assembly to make the system easier to carry. Enclosures with variable diameter profiles increase air flow performance. A floor edge allows for flush positioning of the air mover's outlet to improve flow of air. Various supports and engagement members allow for horizontal and/or vertical engagement of a plurality of the air movers for storage or increased air moving capacity for a given application. An alignment guide assists with positioning of the air mover with respect to a room wall to enhance air flow within the room. A cord retaining system provides an enhanced approach for securing the air mover's electrical cord. Grill guards have slotted ends to assist with assembly of the air mover.

Abstract: In various implementations, a plug fan assembly may include a plug fan housing and a blower wheel. The plug fan housing may include angled corner(s) and/or a flared portion. The plug fan may be utilized in an air conditioning system.

Abstract: Systems are provided for increasing the power to be extracted from a wind stream by a wind turbine, including placing a duct and nozzle system, or cluster of such systems, up-stream of the wind turbine. In certain embodiments, the nozzles are convergent and the blades of the wind turbine are embedded in a narrower cylinder thereof.

Abstract: The present invention concerns a rotary compressor for compressing a gaseous medium, comprising an impeller (2), a drive unit (3) and a magnetic coupling (4) comprising a rotating inner rotor (41), a rotating outer rotor (42) and a can (43), wherein the inner rotor (41) is connected to the impeller (2), wherein the impeller (2) comprises a continuous solid portion (25), wherein a first row (21) and a second row (22) of blades (23) are provided at the outer circumference of the solid portion (25) of the impeller, the first and second row of blades being separated by a circumferential middle wall (20), and wherein the blades (23) of the first row (21) are offset in circumferential direction relative to the blades (23) of the second row (22).

Abstract: A shroud comprises a frame having a main opening delimited by a main wall and at least one secondary opening delimited by a secondary opening, for the passage of a cooling air flow; a ventilator mounting system associated with the frame to support the ventilator at the main opening; a panel for closing the secondary opening, connected to the frame and movable, by rotation, between a lowered position and a raised position; the shroud comprises a pin, defining the axis of rotation of the panel, extending through the secondary opening and having a first and a second end respectively connected to a first and a second section of the secondary wall, opposite each other, a pair of hooks being provided in the panel for connection to the pin.

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.

Abstract: A turbocharger for an internal combustion engine having a housing, an impeller arranged in the housing interior having an impeller shaft and being mounted in a bearing block, and an intermediate element between the impeller and the bearing block. The housing includes at least one flow channel for feeding or discharging a fluid to or from the impeller, and the intermediate element includes a wall section that delimits a least a section of at least one of the flow channels.

Abstract: A casing treatment for a fan or compressor stage 10 of a gas turbine engine comprises circumferential grooves 16A, 16B, 16C, 16D and 16E which extend in a series disposed between the leading edges 20 and trailing edges 22 of blades 6 of a fan or compressor stage 10. The grooves 16 vary in depth d in order to optimise the stall margin of the fan or compressor stage 10 while preserving peak efficiency.

Abstract: An annular nozzle for a ceiling fan includes an inner wall defining a bore having a bore axis, an outer wall extending about the inner wall, an air inlet for receiving an air flow, and an air outlet section extending between the inner wall and the outer wall. The air outlet section defines an air outlet for emitting the air flow. An interior passage extends about the bore axis for conveying the air flow to the air outlet. The air outlet section is configured to emit the air flow away from the bore axis.

Abstract: A ventilation assembly, particularly for a vehicle, has a cowl with a conduit for air flow. The conduit has a first portion and a second portion having a smaller diameter and a joining portion joining the first and second portions. A fan is disposed in the conduit. The fan has an impeller with a peripheral ring having a lip. An annular passage is formed between the ring and the conduit. The lip has a substantially frusto-conical shape; and the joining portion of the conduit has a substantially frusto-conical shape, with an inclination angle (?) at least approximately corresponding to that of the lip of the impeller. The inclination angle (?) is between 115° and 145°.

Abstract: An electronic device includes a chassis, a circuit board, and a fan module. The chassis includes a side plate defining an opening. The circuit board is located inside the chassis and includes a first connector. The fan module includes a fan and a cage enclosing the fan. The fan includes a second connector. The cage includes a first receiving member. Two latch portions are formed on opposite ends of the first receiving member. Each latch portion includes at least one block. The latch portions are deformable to allow the fan module to be placed inside the chassis through the opening. The at least one block abutting against an inner surface of the side plate. The second connector of the fan is electrically coupled to the first connector of the circuit board.

Abstract: An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

Abstract: A detachable portable debris removal apparatus designed to attach to a shaft, such as a golf club. The apparatus includes a housing having an internal cavity containing a motor, a fan, and a power supply to operate said motor, turning the fan. The apparatus further includes a control switch to selectively turn the apparatus on and off. Two openings in the housing permit a flow of air through the internal cavity when the motor is operated. The apparatus further includes an attachment member configured to attach to a shaft. The attachment member can be integrated into the housing or attached to an outside surface of the housing. The apparatus can further include a collection assembly disposed within the internal cavity to collect debris drawn into the housing. The collection assembly can be optionally removable from the internal cavity, permitting the apparatus to function optionally as a blower or a vacuum.

Abstract: A rotating inlet cowl for a turbine engine, having a rotation axis and for which the forward end is arranged to be eccentric relative to this rotation axis. Furthermore, a forward cone of the cowl is truncated by a truncation surface defining the forward end of the inlet cowl.

Abstract: A serial fan frame assembly structure includes a first fan frame and a second fan frame. The first fan frame has a first and a second retainer, as well as a first and a second receiving slot; and the second fan frame has a first and a second receiving recess, as well as a first and a second post. The first and second retainer are configured for correspondingly engaging with the first and second recesses, while the first and second posts are configured for correspondingly engaging with the first and second receiving slots, so that the first and the second fan frame can be quickly assembled together in a manner capable of reducing vibration during the operation of a serial fan.

Abstract: A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.

Abstract: A sound-proofed helicocentrifugal fan includes a helicocentrifugal propeller associated with a motor, housed in a casing formed by a central piece and respective end pieces, which pieces are perforated with holes distributed over the entire surface except for the area around the propeller. A sound-absorbing blanket surrounds the casing, and an outer casing is disposed around the entire assembly.

Abstract: A turbocharger assembly includes a center housing rotating assembly, which comprises a center housing, bearings housed in the center housing, a shaft rotatably supported in the bearings, and compressor and turbine wheels affixed to opposite ends of the shaft; an engine cylinder head and a housing member formed together as a one-piece integral structure, wherein the housing member defines a compressor volute that receives compressed air from the compressor wheel, a turbine volute for receiving exhaust gas from the engine, a turbine nozzle for directing exhaust gas from the turbine volute into the turbine wheel, and a turbine contour; a compressor contour plug that defines an axial inlet for the compressor and a compressor contour; and a wastegate unit operable for allowing exhaust gas to bypass the turbine wheel when the wastegate unit is open and preventing exhaust gas from bypassing the turbine wheel when the wastegate unit is closed.

Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.

Abstract: A turbomolecular pump includes a drag pump unit constituted with a rotational cylinder portion disposed at a rotor and a fixed cylinder (24) disposed via a gap on an outer circumferential side of the rotational cylinder portion. The fixed cylinder (24) includes: a cylinder upper portion (240a) locked to a base (1); and a cylinder lower portion (240b) connected to a discharge downstream side of the cylinder upper portion (240a) via a groove (243) formed so that a break occurs when the rotational cylinder portion (32) breaks and a broken rotational cylinder portion (32) collides with the fixed cylinder (24) subjecting the fixed cylinder (24) to a rotational torque working in a direction matching the direction in which the rotational cylinder portion (32) rotates.

Abstract: A blade (1) for a tail anti-torque device of a helicopter, said device comprising a ducted rotor (13). The blade (1) has an assembly of sections, a leading edge (2) and a trailing edge (3); a stacking line (4) of the profiles extending at a distance lying in the range 25% to 50% of the chord (C). The stacking line (4) presents a shape that is curved having successively from the root (5) to the end (6) of the blade a back sweep, a forward sweep, and a last back sweep; and a chord (C) that becomes larger going towards the end (6) of the blade (1) over at least the end profile (1a).

Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier, a ceramic blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and the ceramic blade track to locate the ceramic blade track relative to the annular metallic carrier. The cross-key connection includes a plurality of keys and a plurality of corresponding keyways.

Abstract: A compressor includes a cylindrical casing, a bundle 3 which includes a tubular stationary member and a rotor accommodated into the stationary member, and is inserted into an inner portion of the casing, and a roller 11 configured to roll on an inner circumferential surface of the casing while supporting the bundle 3 when the bundle 3 is inserted into the inner portion of the casing along an axial direction. An outer circumferential surface 23 of the roller 11 is formed in a continuous convex curved surface so that a curvature radius of an end side along a rotating shaft 21 of the roller 11 is smaller than a curvature radius of a center.

Abstract: A fan includes a motor mechanism and a plurality of fan blades. The motor mechanism includes a base, a bearing, a rotor and a stator. The base has an axial tube. The bearing is disposed in the axial tube. The rotor has an axle. The axle is inserted into the bearing and has a recess structure. The stator is sleeved on the axial tube and includes an upper insulated frame. The upper insulated frame has a resilient cantilever structure. The resilient cantilever structure is extended into the recess structure. The fan blades protrude from a periphery of the rotor.

Abstract: A fan frame includes a blade holder, a pair of ventilation plates, and at least one side plate. The pair of ventilation plates is attached to opposite sides of the blade holder along a first direction and includes a pair of securing blocks. The at least one side plate is attached to the blade holder along a second direction substantially perpendicular to the first direction and located between the pair of ventilation plates. The pair of mounting slots is defined in the at least one side plate and engaged with the pair of securing blocks, thereby securing the pair of ventilation plates and the at least one side plate to the blade holder.

Abstract: A nacelle for a turbojet engine has a longitudinal axis and a rear section including an annular vein formed by a wall of a fixed internal structure and a wall of an external structure. The nacelle includes a device for modulating the cross-section of a space formed by the annular vein. The device includes an injector to inject an auxiliary flow of a gas so as to vary the orientation or speed of the auxiliary flow, a suction orifice for drawing in part of the injected auxiliary flow, and an internal auxiliary flow return area in one or more walls.

Abstract: The disclosure relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space for the circulation of a main air flow. The nacelle includes a device for modulating the cross-section of the space and has means for injecting an auxiliary flow of a gas by means of an induced ejector effect; suction means for drawing in the injected auxiliary flow; and an internal auxiliary flow return area in one or more walls, the area being configured to allow the circulation of the injected auxiliary flow and the drawn-in auxiliary flow and to bring part of the injected auxiliary flow into contact with the main air flow. The internal return area includes an outer front part forming an area in which the thickness of the internal return area is reduced.

Abstract: A blower apparatus includes a blower casing; an elastic member for mounting a mounting portion that projects on an outer circumferential portion of the blower casing, to a blower support member disposed on the inlet side of the mounting portion; and a flange portion provided on the inlet side of the mounting portion. At least three elastic members are disposed in the same plane that is almost orthogonal to a rotation shaft, and adhesion surfaces are provided on both ends, in the rotation shaft direction, of each elastic member. The mounting portion is fixed to one of the adhesion surfaces, and the blower support member is fixed to the other of the adhesion surfaces. The flange portion is provided so as to oppose the blower support member through a gap having a thickness less than a thickness, in the rotation shaft direction, of the elastic member.

Abstract: A mounting device for mounting a fan includes a base board and two fixing assemblies. The fan includes two opposite boards. The base board forms four rods. Each fixing assembly includes a receiving member and an engaging member. The receiving member includes a first pole capable of extending through a corresponding one of the boards and a first block abutting against an outer surface of the board. The engaging member includes a second pole capable of extending though the other one of the boards to be engaged in the first pole, and a second block abutting against an outer surface of the other board. Each of the first and second blocks defines a fixing hole through which a corresponding one of the rods is capable of extending.

Abstract: An aerodynamic element for an aircraft nacelle is provided that includes a fixed shroud and an intake lip axially movable relative to the shroud. The aerodynamic element is flexible and has a substantially cylindrical general shape and defines an upstream portion attached to the inner wall of the intake lip of the nacelle, and a downstream portion bearing radially against an inner face of the shroud. The downstream portion of the element includes a ring shaped bead protruding towards an outside of the aerodynamic element and an end blade which, at rest, is tilted towards the outside of the aerodynamic element in a direction of its free end.

Abstract: An apparatus comprising: (a) a bladeless rotatable element with a smooth outer surface, said rotatable element connected to a drive mechanism; and (b) a dynamo powered by said drive mechanism so as to output an electric current.

Abstract: Implementations of an enhanced axial air mover system address various issues such as drying performance, transportability, storage, use, and assembly. Some implementations include ergonomic positioning of a carrying handle relative to positioning of a fan-assembly to make the system easier to carry. Enclosures with variable diameter profiles increase air flow performance. A floor edge allows for flush positioning of the air mover's outlet to improve flow of air. Various supports and engagement members allow for horizontal and/or vertical engagement of a plurality of the air movers for storage or increased air moving capacity for a given application. An alignment guide assists with positioning of the air mover with respect to a room wall to enhance air flow within the room. A cord retaining system provides an enhanced approach for securing the air mover's electrical cord. Grill guards have slotted ends to assist with assembly of the air mover.

Abstract: A fan with a nozzle mounted to a base plate, wherein the base plate has on its rear wall a mounting device with an upper and lower holding device for mounting the fan on a top-hat rail. The upper holding device and the lower holding device reach over an upper edge or a lower edge respectively of the top-hat rail in the mounted state and are arranged offset from one another in a direction running parallel to the longitudinal axis of the top-hat rail in the mounted state of the fan.

Abstract: Implementations of an enhanced axial air mover system address various issues such as drying performance, transportability, storage, use, and assembly. Some implementations include ergonomic positioning of a carrying handle relative to positioning of a fan-assembly to make the system easier to carry. Enclosures with variable diameter profiles increase air flow performance. A floor edge allows for flush positioning of the air mover's outlet to improve flow of air. Various supports and engagement members allow for horizontal and/or vertical engagement of a plurality of the air movers for storage or increased air moving capacity for a given application. An alignment guide assists with positioning of the air mover with respect to a room wall to enhance air flow within the room. A cord retaining system provides an enhanced approach for securing the air mover's electrical cord. Grill guards have slotted ends to assist with assembly of the air mover.

Abstract: A turbocompressor that is suitable for conveying a multi-phase mixture, comprising a housing having a guiding device and comprising a shaft having at least one impeller, wherein the turbocompressor has an expansion chamber through which the multi-phase mixture can flow on the suction side and a contraction chamber arranged downstream is provided.

Abstract: A fan casing for a turbofan engine including an annular casing component of composite material including a body portion having an outwardly directed stiffening flange at one end, the stiffening flange being connected to the body portion by a radially outwardly stepped region, the fan casing also including a metallic ring which is coaxial with the annular casing component, the metallic ring being situated at least partially within the stepped region and being secured to the annular casing component.

Abstract: An object is to provide a turbine and a turbine rotor blade in which it is possible to ensure the strength of the turbine rotor blade and to improve the performance thereof. The turbine includes: rotor blades that rotate about a rotational axis in a main flow channel of a casing; stator vanes that are disposed in the casing; a tip shroud that is disposed at a radially-outward end of each of the rotor blades and whose length in the direction along the rotational axis is reduced as the distance from the rotor blade increases; and a cavity portion that is formed at a position in the casing facing the rotor blades and in which the tip shroud is accommodated. An inclination angle of the inner periphery of the tip shroud is larger than an average inclination angle that is an inclination angle of the inner periphery of the casing, averaged from the trailing edge of the stator vanes disposed at the upstream side of a main flow to the cavity portion disposed at the downstream side of the main flow.

Abstract: A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of compressing the supersonic airflow into a subsonic airflow, direct the subsonic airflow around the engine, and then expand the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag.

Abstract: The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an “S” and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.

Abstract: A portable fan includes a casing having an air inlet and a first connector, and an air outlet having a second connector. A filter unit includes a third connector, which is substantially the same as the second connector, for co-operating with the first connector to removably connect the filter unit to the casing, a filter which is located upstream from the air inlet when the filter unit is connected to the casing, and a fourth connector, which is substantially the same as the first connector, for co-operating with the second connector to removably connect the air outlet to the filter unit. This can allow the air outlet to be connected either directly to the casing, or to an optional filter unit which is connected to the casing.

Abstract: A fan module includes a housing and at least one impeller. The housing includes first and second air channels. The housing further includes an axial air inlet in communication with the first air channel and a radial air inlet in communication with the second air channel. The housing further includes at least one radial air outlet in communication with the first and second air channels. The at least one impeller draws external air into the housing via the axial air inlet or the radial air inlet and expels air out of the housing via the at last one radial air outlet. By such an arrangement, external air can be guided into the fan module via different directions, providing an enhanced cooling effect.

Abstract: A ventilation fan arranged to reduce vibrations includes an impeller rotating around a center axis, a motor portion arranged to rotate the impeller, a motor supporting portion arranged to support the motor portion, and a housing arranged to accommodate the impeller and the motor portion. The motor supporting portion includes a substantially disk-shaped base portion, and a substantially cylindrical bearing holding portion axially extending with the center axis as the center. At least the base portion is made from resin. On the surface of the base portion, a plurality of recessed portions which are axially recessed are arranged in the form of a net, a staggered pitch, a grid, or a honeycomb. A flat portion of the base portion excluding the recessed portions does not have a continuous region extending in a straight line radially from the center of the base portion.

Abstract: Implementations of an enhanced axial air mover system address various issues such as drying performance, transportability, storage, use, and assembly. Some implementations include ergonomic positioning of a carrying handle relative to positioning of a fan-assembly to make the system easier to carry. Enclosures with variable diameter profiles increase air flow performance. A floor edge allows for flush positioning of the air mover's outlet to improve flow of air. Various supports and engagement members allow for horizontal and/or vertical engagement of a plurality of the air movers for storage or increased air moving capacity for a given application. An alignment guide assists with positioning of the air mover with respect to a room wall to enhance air flow within the room. A cord retaining system provides an enhanced approach for securing the air mover's electrical cord. Grill guards have slotted ends to assist with assembly of the air mover.

Abstract: In certain embodiments of the present disclosure, a turbine casing assembly is described. The turbine casing assembly includes an inner casing and an outer casing surrounding the inner casing. The outer casing has a first outer casing section and a second outer casing section that join together along a flange. A bolt extends through the flange and joins together the first outer casing section and the second outer casing section. The turbine casing assembly further includes a pin. The pin has a segment defining an opening therethrough. The pin extends through the inner casing and the outer casing and supports the inner casing relative to the outer casing. The bolt passes through the opening defined by the pin.

Abstract: A fan includes a main body, an end wall connected an end of the main body, and a power connector. The main body defines a receiving space extending through the end wall in a bottom. The receiving space includes two sidewalls defining two slide slots. The power connector includes a first end surface forming a pole, and a second end surface forming a connecting portion. Opposite ends of the pole are engaged in the slide slots. When the power connector is received in the receiving space, the connecting portion is perpendicular to the end wall and faces downward. When the power connector is moved out of the receiving space, the power connector can be pivoted to be fixed to the end wall, to allow the connecting portion to be parallel to and face away from the end wall.

Abstract: A wind turbine is provided with turbine blades mounted for axial rotation about an axis. The blades are surrounded by a shroud to define an axial air passage. A conical ring is attached to the shroud and includes vanes for directing the airflow. Plates are attached to the shroud at a position radially outward from the shroud forming an air passage between the shroud and the plates. The plates have gaps between the adjacent plates so that air exiting the downstream opening of the shroud and air moving through the axial air passage between the shroud and the plates are mixed and a portion of the mixed air exits through the gaps. The wind turbine includes photovoltaic cells to increase the electricity generated by the wind turbine.

Abstract: A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170.

Abstract: The invention relates to a compressor for a turbine engine including a casing (4), at least one compressor stage consisting of a stationary blade (2) impeller and a mobile blade (1) impeller positioned upstream from said stationary blade (2) impeller, and cavities (5) made in said casing opposite the through-path of the mobile blades (1), said cavities having a length L2 measured axially and being shifted upstream relative to the blades (1) so as to generate an overlap with a length L1, characterized in that the lengths L1 and L2 are respectively between 35% and 50% and between 80% and 90% of the axial chord Cax measured at the outer end of the blades (1), and in that the cavities (5) do not in communication with one another.

Abstract: A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.