Abstract: The present disclosure relates to a two-vane pump for wastewater and a design method of a two-vane pump for wastewater using machine learning, and more particularly, a design method of a two-vane pump using machine learning capable of having efficiency of a target head and performing optimal design for sizes of solids that can pass through and a two-vane pump for wastewater according to the machine learning.

Abstract: An air pump device includes an electric pump unit including a pump mechanism and a motor configured to drive the pump mechanism, a case housing the electric pump unit, and a vibration-proof member interposed between the electric pump unit and the case. The vibration-proof member is a plate-shaped member made of an elastic resin material and is wound around the electric pump unit to wrap the electric pump unit therein. A part of the vibration-proof member is sandwiched between the electric pump unit and one of facing surfaces that are inner surfaces of the case and face each other inside the case. Another part of the vibration-proof member is sandwiched between the electric pump unit and the other one of the facing surfaces.

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: The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing (23) comprising: —an annular shell (29) with axis A; —an annular element (24; 253, 254) attached to the inside of the shell (29), the annular element comprising a body (25) made of NIDA-type cellular material and comprising a downstream portion (252) covered with an abradable material (26), and an upstream portion (251) without abradable material, the body (25) extending in a continuous manner from the upstream portion (251) to the downstream portion (252), the method comprising: —manufacturing the annular element in the form of a continuous annular body, —cutting the annular body into segments (253, 254), —attaching the segments to the shell, and —depositing the abradable material (26) onto the inside surface (25a) of the downstream portion (252).

Abstract: Acoustic structures for a gas turbine engine are disclosed. In various embodiments, the acoustic structures comprise a panel in the form of a cellular structure having a plurality of cells; and a housing configured to house the cellular structure, the housing including a first rail configured for attachment to a static structure within the gas turbine engine and a second rail configured for attachment to the static structure. In various embodiments, the acoustic structures comprise a liner in the form of a non-segmented or two-piece structure configured to extend about the inner barrel of a nacelle structure. The disclosed panels and liners are configured to maximize the operational area of the acoustic structures by eliminating obstructions from adjacent flow paths.

Abstract: A structure is provided that includes a perforated first skin, a second skin and a core. The core includes a first sidewall, a second sidewall, a first baffle and a second baffle. The core forms a plurality of cavities vertically between the perforated first skin and the second skin. The first baffle is connected to the perforated first skin at a first baffle first end. The first baffle is connected to the second skin at a first baffle second end by a first moveable joint. The second baffle is connected to the perforated first skin at a second baffle first end. The second baffle is connected to the second skin at a second baffle second end. A first of the cavities extends laterally between the first sidewall and the second sidewall. The first cavity extends longitudinally between the first baffle and the second baffle.

Abstract: A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The casing may itself at least in part define an annular gap that functions as a nozzle for the rocket booster, with protruding tabs on the casing aiding in maintaining a uniform height of the annular gap. The rocket booster may be mechanically coupled to an object protruding from the back of a fuselage of a flight vehicle, such as a missile. For example, the rocket booster may be placed around an aft turbojet nozzle of the flight vehicle. This allows the rocket booster to be used in situations where primary propulsion must be running both before and after (and perhaps during) the firing of the rocket booster.

Abstract: A foreign object debris (FOD) detection system for a gas turbine engine comprises a light detection and ranging (LiDAR) sensor assembly. The LiDAR sensor assembly is configured to scan a pre-determined volume within an inlet of the gas turbine engine. The inlet may be defined by a nacelle of the gas turbine engine. The LiDAR sensor assembly may comprise a single transceiver, a transmitter and a receiver, a plurality of transmitters and a receiver, or a plurality of receivers and a transmitter.

Abstract: An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise: a first shroud configured to be disposed around a rotor of the UAM vehicle, the first shroud comprising: a radially inner wall configured to be spaced radially outward from a blade tip of a rotary blade of the rotor, the radially inner wall including a perforated portion; and a hollow chamber defined by an internal surface of the first shroud and the radially inner wall.

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: A propeller fan assembly that generates lower sound pressure during operation and minimizes blade deflection without sacrificing performance. The blades of the propeller fan comprise silencer seeds located on the suction side of the blades, closer to the leading edge and the tip of the blades. The silencer seeds are sized in increasing face area and form an array with areas increasing with each row. The propeller fan assembly also comprises a dual hub comprising more than one circumferential layer concentric with the axial fan's hub. Multiple circumferential layers provide significant additional support to the blades during operation. This minimizes blade deflection and preserves the performance of the blade as intended. The overall fan and orifice assembly uses a unique assembly method that allows for wide flexibility and permits use of motors of different types and sizes seamlessly with this propeller fan assembly.

Abstract: A cover for a compressor defines an accommodating space configured to receive the compressor. The cover includes a first cover that is configured to be spaced apart from an outer surface of the compressor and that define a first portion of the accommodating space, and a second cover that is detachably attached to the first cover and configured to be spaced apart from the outer surface of the compressor and that defines a second portion of the accommodating space. The first cover and the second cover are configured to reduce transmission of noise generated from the compressor to an outside of the accommodating space.

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. A row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths. A method of operation for a gas turbine engine is also disclosed.

Abstract: A rotor shroud for a rotary machine in a cabin air compressor includes a disk portion centered on a central axis of the rotor shroud, a frustoconical portion extending from the disk portion, a flared portion extending from the frustoconical portion, and a variable lattice structure in an interior of the rotor shroud. The variable lattice structure includes a first region of the rotor shroud having a first lattice structure and a second region of the rotor shroud having a second lattice structure. The second lattice structure of the second region is denser than the first lattice structure of the first region. The second region is a deflection region, a stress region, or an energy containment region of the rotor shroud.

Abstract: A gas turbine engine according to an aspect of the present disclosure includes, among other things, a propulsor section, a compressor section including a first compressor and a second compressor, and a turbine section including a first turbine and a second turbine. The first compressor includes a plurality of arrays of airfoils defining a plurality of compressor stages. A number of airfoils in each downstream array of the plurality of arrays is a factor (F) of a number of airfoils in a respective immediately upstream array of the plurality of arrays. The factor (F) is between 1.19 and 1.55 for each of the downstream arrays of the first compressor.

Abstract: Disclosed fans include an impeller and a guide device. The impeller is configured to generate an air flow path having an upstream direction and a downstream direction, and the guide device is positioned in the flow path located on an upstream side of the impeller. The guide device is configured as an intake grid having flat webs having branches and node points, and the webs form a plurality of flow channels configured as grid cells. The webs extend either between two branches or between one branch and a border area and each branch may include three webs that meet. In one configuration, flow channels include channels having a honeycomb cross section. In other example, flow channels may have a rectangular, pentagonal, and/or hexagonal shape. The fan further includes an inlet nozzle having an inlet area, and the guide device is located upstream from the inlet area of the inlet nozzle.

Abstract: A power transmission system includes a shaft, a stator disposed within the shaft and substantially concentric with the shaft; and at least one supporting element positioned between the stator and the shaft and configured to support the shaft on the stator to reduce a vibration of the shaft and allow the shaft to rotate relative to the stator. A gas turbine engine including the power transmission system is also described.

Abstract: A shroud unit has multiple stay members for supporting an electric motor, which rotates a fan unit having multiple blade members. Each of the blade members is inclined with respect to a radial direction of the fan unit in a predetermined circumferential direction. The stay members include a first stay member and multiple second stay members. Each of the second stay members is inclined with respect to the radial direction in a circumferential direction opposite to the predetermined circumferential direction. The first stay members is inclined with respect to the radial direction in the predetermined circumferential direction. The first stay member is located at a position overlapping with one of air-flow areas of a circular opening formed in the shroud unit, when viewed it in a direction along a rotational center axis of the electric motor.

Abstract: Disclosed examples include a retrofit fan frame assembly, comprising: a leading edge adjustment component coupleable to an airfoil, the leading edge adjustment component of variable chord length, the variable chord length to increase and then decrease along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and an attachment mechanism configured to couple the leading edge adjustment component to a leading edge of the airfoil.

Abstract: A cooling fan creating a more stable airflow for heat-removing purposes, with reduced noise of operation, comprises a rotor hub and preferably an odd number of blades mounted on periphery of the rotor hub in unequal intervals. Adjacent blades are configured with different shapes, reducing the noise generated during operation without affecting the cooling effect.

Abstract: A noise abatement system for internal combustion engines comprising: a containment body (12) equipped with an inlet hole (6) for the entry of exhaust gases from an internal combustion engine, a plurality of expansion chambers (10) placed in sequence and separated by parallel dividing partitions (13), each equipped with a through-hole (4) for the passage of gases placing in fluid communication two neighboring expansion chambers (10); said expansion chambers (10) having two opposing through-holes (4), one as gas inlet and one as gas outlet. A rotating shaft (9) is integrated in a rotating turbine (1), along an axis comprising the center of gravity of the expansion chambers (10) up to an opposite end of the containment body (12), said rotating shaft (9) having placed around said axis and on said shaft (9) rotary fins (3) which open and close the through-holes (4) between expansion chambers (10) alternately and generating a swirling movement of the flow of gas entering each expansion chamber (10).

Abstract: A three-bladed impeller providing a cooling airflow in air, with increased heat-dissipating efficiency and reduced noise includes a hub and three blades, the blades are arranged around the hub. Each blade is arched along its axial length from the front of fan to the back and also arched radially from the hub end of each blade to the outside tip. The back edge of each blade includes first and second slots, arranged alternately, the width of each first slot is ?1, the width of each of each second slot is ?2, the comparative sizes between ?2 and ?1 are in a ratio range of 1.6:1 to 1.8:1 (?2:?1).

Abstract: A compressor comprising: a stator assembly comprising a plurality of stator elements; a rotor assembly comprising a shaft to which is mounted at least one bearing, a permanent magnet and an impeller; a support body; and an outer can comprising an air inlet. The support body comprises a hollow elongate central part to which is mounted the at least one bearing, and inside which the magnet is positioned, the elongate central part comprising a plurality of openings, and the air inlet of the outer can is axially aligned at least partially with the plurality of openings in the elongate central part.

Abstract: A blower unit, particularly for an apparatus for assisting respiration, comprises a housing (2), an impeller (1) accommodated in an impeller chamber (3) in the housing (2), and a motor (12), connected to the impeller (1) via a shaft (15), which is accommodated in a motor chamber (13) in the housing (2). The motor (12) is fixed between walls (14, 18) of the motor chamber (13) by means of buffers, with at least one of the buffers being a sealing ring (16) which separates the shaft (15) from a passage for cooling air (33) which, in radial section, extends annularly around the motor (12).

Abstract: A centrifugal fan includes a housing and an impeller. The housing includes a sidewall, and the sidewall includes a tongue portion. The impeller includes a fan hub and a plurality of blades. The fan hub is rotatably disposed in the housing, and the tongue portion has an inner contour line on a reference plane. The blades connect to the fan hub. Each one of the blades has an end surface facing the sidewall. The end surface has an outer contour line on the section of the blade. Any two adjacent blades have different outer contour lines. The outer contour line of at least one first blade of the plurality of blades is parallel to the inner contour line. The outer contour line of at least one second blade of the plurality of blades is not parallel to the inner contour line.

Abstract: A compressor housing for a turbocharger may include an outer volute having an outer volute inner surface with a clamp groove defined therein, and an inner volute having an inner volute outer surface and an axially facing surface. The inner volute is inserted into the outer volute through the outer volute inner surface with the inner volute outer surface facing the outer volute inner surface. The inner volute is positioned with the axially facing surface disposed axially inward of the clamp groove. A clamp plate includes a radially outward portion inserted into the clamp groove and a radially inward portion extending downward past the inner volute outer surface. The clamp groove and the axially facing surface engage the clamp plate to retain the inner volute within the outer volute when an axial load is applied to the inner volute.

Abstract: A vane arc segment includes an airfoil fairing that has an airfoil wall that defines a fairing platform and a hollow airfoil section. A spar has a spar platform adjacent the fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg is spaced from the airfoil wall in the hollow airfoil section such that there is a first gap. The spar platform is spaced from the fairing platform such that there is a second gap. A support platform is secured to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. There is a spring seal between the spar platform and the fairing platform. The spring seal biases the airfoil fairing toward the support platform and seals the first gap from the second gap.

Abstract: This invention relates to a noise reducing device and a wind turbine blade comprises such a noise reducing device. The noise reducing device comprises noise reducing elements projecting from a base part towards a second end. Airflow modifying elements projects further from the base part towards a first end. The noise reducing elements and airflow modifying elements are arranged on opposite sides of the base part and preferably have different dimensions and/or shapes.

Abstract: A forced-draft pre-mix burner device has a housing that conveys air from an upstream cool air inlet to a downstream warm air outlet. A heat exchanger warms the air prior to discharge via the warm air outlet. A gas burner burns an air-gas mixture to thereby warm the heat exchanger. A fan mixes the air-gas mixture and forces the air-gas mixture into the gas burner. The fan has a plurality of blades having sinusoidal-modulated blade spacing.

Abstract: An air inlet (3) for a nacelle (2) for an aircraft (1) includes at least one acoustic panel (5), adapted to lower noise generated by the engine (21) to which the air inlet (3) is connected. At least one lip (6) defines the profile upon which an airflow flowing into the air inlet (3) acts. If necessary, at least one engine ring (4) is adapted to allow the air inlet (3) to be connected to an engine (21) of the nacelle (2). If necessary, at least one outer barrel (7) is adapted to define the outer shape of the air inlet (3) upon which an airflow acts. The air inlet (3) is manufactured as one single piece, made of a composite material.

Abstract: A blower apparatus includes an impeller and a casing that accommodates the impeller. The casing includes an upper wall including an intake port, a lower wall, a side wall that includes an exhaust port, and a tongue portion connected to the upper wall. The side wall includes a first side wall, and a second side wall disposed downstream in a rotational direction of the impeller relative to the first side wall via the exhaust port. The tongue portion extends from the second side wall toward the first side wall, and includes a lower portion opposed to the lower wall. The lower portion includes a first lower portion on the base end side and a second lower portion on the tip side. A distance between the first lower portion and the lower wall is shorter than a distance between the second lower portion and the lower wall.

Abstract: The present disclosure relates to a drainage device and a dishwasher having the same. The drainage device includes a drain pump including a drain port for discharging water, a drain pipe guiding discharge of water discharged from the drain pump, an air chamber in which the drain pump is connected to an upper portion thereof and the drain pipe is connected to a lower portion thereof, and an air pump configured to inject air into the air chamber, thereby more surely blocking the backflow of water to the drain pump by air injected into the air chamber through the air pump.

Abstract: The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

Abstract: A fan includes a motor, an impeller and a stator. The fan defines an air flow passage between an air inlet and an air outlet. The fan has a mode of operation and an arrangement such that, in use, the trajectory of the air flow through the air inlet is up to 360° in a direction which is generally perpendicular to the axis of rotation of the impeller. The trajectory of the air flow through the air outlet is up to 360° in a direction which is generally perpendicular to the axis of rotation of the impeller, and the air flow through the air flow passage turns generally 180°. The fan has a mode of constant operation, and, in this mode, the operating point of the fan falls with the stall region of the fan characteristic.

Abstract: This disclosure provides an air moving device with blade tip of variable curvature. The axial air moving device includes a hub and a plurality of blades. The blades are connected with the hub, and each blade is configured by stacking multiple wing sections continuously. Each blade includes a blade root and a blade tip. The span position of the blade at the blade root is defined as 0, and at the blade tip is defined as 1. The blade angle is defined by the nose-tail line of the wing section and the rotation direction of the axial air moving device. The blade angle of the wing section at the blade tip of the blade is at least 10 degrees less than the blade angle of the wing section at the span position of 0.8 of the blade.

Abstract: A fairing for a power generation machine, the fairing comprising: a first layer comprising a metallic material and defining a first surface and a second opposite surface, the first layer being configured to enable the fairing to be coupled to the power generation machine; and a second layer comprising a composite material and defining a first surface and a second opposite surface, the second layer being coupled to the first layer, the second surface of the second layer defining an external surface of the fairing.

Abstract: A heat-exchange apparatus is provided, including a first heat exchanger, a second heat exchanger, a third heat exchanger and a fourth heat exchanger. The first heat exchanger is thermally separated from the second heat exchanger. The third heat exchanger is thermally connected to the first heat exchanger. The fourth heat exchanger is thermally connected to the second heat exchanger, wherein a first air flow passes through the first heat exchanger and the second heat exchanger to be divided into a first divergent flow and a second divergent flow, the first divergent flow flows on a surface of the first heat exchanger, the second divergent flow flows on a surface of the second heat exchanger, the first divergent flow does not flow on the surface of the second heat exchanger, and the second divergent flow does not flow on the surface of the first heat exchanger.

Abstract: Provided is an electric blower configured to include a centrifugal impeller provided with an intermediate blade, which reduces pressure loss inside an air path on a large air volume side and achieves high efficiency. In the electric blower, a first rotor blade and a second rotor blade each include an inner circumferential edge facing a central portion of a hub and connecting an upper edge and a lower edge. The inner circumferential edge of the second rotor blade includes a first portion connected to the lower edge, a second portion connected to the upper edge, and a third portion. The third portion is located between the first portion and the second portion. Among the first portion, the second portion, and the third portion, the first portion is located closest to an outer circumferential portion of the hub in a direction along a surface portion.

Abstract: A wind flow generating device adapted to a hand dryer includes an electric motor provided with a motor housing and a driving shaft, a wind barrel including a bowl, a rotatable fan blade connected with the driving shaft for generating an airflow, and a guide frame fixed to the motor housing. An air outlet gap is jointly defined by the motor housing and the bowl, the guide frame includes a support ring fixed to the motor housing, and a plurality of guide vanes formed on the support ring at intervals and extending along a surface of the motor housing. Any adjacent two of the guide vanes define a guide channel along the motor housing. An inlet and an outlet of each guide channel are positioned on different contour lines of the motor housing, and each guide channel guides the airflow to be discharged from the air outlet gap.

Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.

Abstract: An axial flow impeller includes a hub and a blade at the hub. A blade edge of the blade includes a blade root edge, a front blade edge, a blade top edge, and a rear blade edge connected sequentially. The blade includes a divider strip arranged between the front blade edge and the rear blade edge and connecting the blade root edge and the blade top edge. At a same circumference, a ratio between a circumferential span from the divider to the front blade edge and a circumferential span from the front blade edge to the rear blade edge is equal to or greater than 0.2 and equal to or smaller than 0.4, a thickness of the divider strip is greater than thicknesses of other portions of the blade, and a thickness of the rear blade edge is smaller than a thickness of the front blade edge.

Abstract: Examples herein relate to fan bodies with pressure regulating chambers. For instance, in some examples a fan body can define an outlet, an inlet, a fan chamber that is in fluidic communication with the inlet and the outlet, and a hollow pressure regulating chamber having an opening that is in fluidic communication with the fan chamber.

Abstract: A mechanical connection system is provided that includes a ceramic skin panel, at least one bushing, and at least one bolt. The ceramic skin panel includes a first surface, a second surface, and at least one aperture extending between the first surface and the second surface. The aperture has an axial centerline, a chamfered portion contiguous with the first surface, and an axial portion contiguous with the second surface. The chamfered portion includes a tapered surface disposed at a first angle such that a line extending along the tapered surface intersects the axial centerline at a plane of the second surface. The bushing has a housing and a collar. The housing is configured to mate with the chamfered portion of the aperture disposed within the ceramic skin panel. The collar is configured for engagement with the housing.

Abstract: An inline axial flow fan includes a first fan including a first impeller, a first motor portion, and a first case, and a second fan including a second impeller, a second motor portion, and a second case, the first fan and the second fan being positioned in sequence from one axial side to another axial side. The first case and the second case are accommodated in a housing, and only one of the first case and the second case includes multiple slits that connect the inside and the outside of the first case and the second case in the radial direction.

Abstract: A turbomachine for an aircraft comprising a thermo-acoustic system associated with a fluid circuit allowing the turbomachine engine to be supplied with fluid, the thermo-acoustic system comprising an exchanger connected to the fluid circuit and through which the fluid that is to be cooled passes, an acoustic noise-attenuation structure forming, in full or in part, a wall of the duct of a fan duct, the structure being situated some distance from the exchanger, and a pulsating heat pipe comprising a tube extending between the exchanger and the acoustic noise-attenuation structure, the tube having a serpentine form with a plurality of elbows bent over at 180° housed alternately in the exchanger and the structure.

Abstract: The invention relates to a straightening assembly for an air flow of a turbomachine, comprising two respectively coaxial radially inner and outer shrouds (30), between which extend the vanes (32) made of composite material attached, at a first end portion (42) thereof, to the radially inner shroud and at a second end portion (44) thereof, to the radially outer shroud (30), with the vanes (32) comprising a useful portion extending between the two end portions (42, 44). According to the invention, for each vane (32) in a plane perpendicular to the axis of the radially inner and outer shrouds (30), a straight line passing through a junction between said first and second end portions (42, 44) and the useful portion forms, with a radius of the radially inner shroud passing through the junction between said first end portion and the useful portion of said vane (32), an angle ? such that 0°<??90°.

Abstract: A rotating electric machine includes a rotating shaft, a rotor fixed on the rotating shaft, a stator arranged to radially face the rotor, and a housing having a tubular part. The tubular part has the stator assembled thereto on a radially inner or radially outer side thereof. Moreover, the tubular part has an inner wall portion and an outer wall portion that are radially spaced from and radially face each other. Between the inner wall portion and the outer wall portion, there is formed an annular coolant passage through which coolant flows. On an external surface of the tubular part of the housing on an opposite radial side to the stator, at least one elongate protrusion is formed, in an axial range where the at least one elongate protrusion radially overlaps the coolant passage, to extend obliquely or parallel to an axial direction of the rotating shaft.

Abstract: A heat dissipation fan suited for being assembled in an electronic device is provided. The heat dissipation fan includes a hub and a plurality of fan blades disposed at and surrounding the hub. The fan blade has ductility and flexibility, and any two fan blades next to each other are in different thickness.

Abstract: An intermediate turbojet case comprises a hub that supports removable panels and bleed lines, the hub comprising a flank provided with openings, each bleed line having an upstream end engaged in an opening in the flank and a downstream end terminated by a base plate through which it is fixed to an internal face of a removable panel by way of screws, each removable panel having a front edge at which it is fixed to an external lip of the hub by screws. At least one removable panel comprises a downstream edge supporting a retaining element close to the internal face to hold the base plate in contact with the internal face during a phase in which the removable panel is fixed to the hub by screwing, this phase preceding attachment of the base plate to the removable panel by screwing.

Abstract: A geared turbofan engine includes a first rotor, a fan, a second rotor, a gear train, a fan casing, a nacelle and a plurality of discrete acoustic liner segments. The fan is connected to the first rotor and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train connects the first rotor to the second rotor. The fan casing and nacelle are arranged circumferentially about a centerline and define a bypass flow duct in which the fan is disposed. The plurality of discrete acoustic liner segments with varied geometric properties are disposed along the bypass flow duct.