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: 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 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: 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: 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 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 system includes an airfoil disposed inside an engine assembly that includes a pressure side and a suction side that are coupled together at a leading edge and a trailing edge. The airfoil extends a radial length away from a central axis of the engine assembly between a hub end and a tip end. The airfoil includes a sweep feature disposed at the leading edge that is shaped to alter the air inside the engine assembly. Altering the air inside the engine assembly reduces a surface unsteady pressure level on the airfoil. The system includes a fan frame assembly comprising an inner and outer surface. The hub end is coupled with the inner surface and the tip end is coupled with the outer surface. The airfoil is integrated with the fan frame assembly such that the airfoil increases a structural load supporting capability of the fan frame assembly.

Abstract: A blower assembly includes a fan assembly configured to rotate about an axis and having a fan inlet ring that at least partially defines a fan inlet and a fan outlet. The blower assembly also includes a frame assembly coupled to the fan assembly and a recirculation damper coupled to the frame assembly. The recirculation damper and the fan inlet ring define an axial gap therebetween to reduce recirculation of an airflow discharged from the fan outlet.

Abstract: An arrangement for intentionally mistuning a cavity formed adjacent an impeller in a turbomachine, the arrangement including at least two bladed elements defined within a perimeter of a casing wall adjacent the impeller, wherein the bladed elements are configured to mistune cavity acoustic modes to minimize acoustic pulsations in the cavity.

Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

Abstract: A control system operable includes a modified primary control parameter for an aircraft, the control system includes: a primary control parameter leg configured to output a demand in an aircraft primary control parameter; a primary control parameter compensation leg configured to receive a change in absolute levels and/or spatial distributions of swirl angle and/or fan pressure at a primary control parameter relative to a reference and convert the change into the primary control parameter; a processor adapted to receive the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; compare the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; and generate a modified primary control parameter for the aircraft.

Abstract: A pump includes an axial inducer. The axial inducer includes a housing that has an internal surface that defines an axial fluid passage. A rotor is disposed about a central axis in the fluid passage. The rotor includes at least one blade that defines at least one blade tip. The internal surface of the housing defines a plurality of grooves adjacent the at least one blade tip. The grooves are elongated in a circumferential direction.

Abstract: An impeller includes Z blades, where Z is an integer equal to 5 or more, arranged in a circumferential direction of the impeller and extending radially, pitch angles between adjacent blades being all different. In terms of an arbitrary pitch angle ?, when a pitch angle ?1 adjacent to the pitch angle ?, and a pitch angle ?2 adjacent to the pitch angle ?, different from the pitch angle ?1, satisfy a relation, ?1<?2, a pitch angle ?1 different from the pitch angle ? adjacent to the pitch angle ?1 and a pitch angle ?2 adjacent to the pitch angle ?2, different from the pitch angle ?, satisfy a relation, ?2<?1.

Abstract: Devices, systems, and methods for making gas turbine engine component with high cycle fatigue performance include selecting target airfoils while detuning other airfoils. The selective detuning can reduce resource intensity for realistic testing during build. Conforming detuning masses can reduce the need for outside resources.

Abstract: A guide vane airfoil for placement in a flow path portion of a turbomachine is provided, which, relative to a flow pattern in flow path portion, has a leading edge and, downstream thereof, a trailing edge, as well as a suction side and a pressure side; relative to a longitudinal axis of the turbomachine, viewed in the axial direction, in a radially inner portion, forming a first angle ? with a circular arc about the longitudinal axis, and, in a radially outer portion, a second angle ? with a circular arc about the longitudinal axis. The guide vane airfoil is inclined in the outer portion, thus ??90°, in terms of absolute value, being >0° (|??90°|>0°), and the guide vane airfoil being more highly inclined in the outer portion than in the inner portion, thus ??90°, in terms of absolute value, being >??90° (|??90°|>??90°).

Abstract: An electronic device with a fan assembly is disclosed. The fan assembly includes an impeller and an insert separated from the impeller by a gap. The fan assembly increases airflow by rotationally driving the impeller. For a sufficient rotational speed of the impeller, the airflow reaches a level that provides a force that displaces the insert. The displacement may include movement and/or compression of the insert. As a result of the displacement, the gap between the impeller and the insert increases. The increased gap reduces the pressure and associated noise that is otherwise caused by the airflow. When the rotational speed of the impeller reduces or ceases, the insert returns to its initial position. In this manner, the fan assembly includes a self-adjusting gap that changes based on the airflow.

Abstract: A gas turbine engine for an aircraft has an engine core comprising turbine, compressor, and core shaft connecting the turbine to the compressor, the turbine being the lowest pressure turbine of the engine, and having turbine blades, and the compressor being the lowest pressure compressor of the engine; fan located upstream of the engine core; and gearbox that receives an input from the core shaft and outputs drive to the fan. The engine core further has three bearings arranged to support the core shaft, the three bearings having two rearward bearings located downstream of the leading edge of the lowest pressure turbine blade of the turbine at the root of the blade, and/or, when the turbine comprises four sets of turbine blades, downstream of the trailing edge of a turbine blade of the third set of turbine blades from the front of the turbine, at the root of the blade.

Abstract: A fan frame body with damping structure and a fan thereof. The fan frame body includes a fan frame main body having a first opening, a second opening, a flow way and a base section. The first and second openings are respectively positioned at the upper and lower ends of the fan frame main body. The flow way is disposed between the first and second openings in communication with the first and second openings. The base section is disposed at the second opening. A bearing cup and multiple static blades are perpendicularly disposed on the base section. Two ends of the static blades are respectively connected with the base section and the fan frame main body. Multiple damping structures are annularly disposed on an inner wall of the fan frame main body. The damping structures are raised body structures or recess structures.

Abstract: A method of health monitoring of a gas turbine engine includes mounting a detection system configured to detect an aeromechanical damping characteristic of a row of airfoils of a gas turbine. An actual aeromechanical damping characteristic of the row of airfoils is measured with the detection system. An output signal is generated indicative of the actual aeromechanical damping characteristic of the row of airfoils. A current flutter characteristic is determined based on the output signal indicative of the actual aeromechanical damping characteristic of the row of airfoils. An airfoil health monitoring system for gas turbine engine and a gas turbine engine are also disclosed.

Abstract: A nacelle inlet may comprise an aft bulkhead, an attachment ring extending in an aft direction from the aft bulkhead, an acoustic liner disposed radially inward from the attachment ring, the acoustic liner comprising a proximal skin, a distal skin, and a core disposed between the proximal skin and the distal skin, and a shroud extending longitudinally between a forward side of the shroud and an aft side of the shroud and extending circumferentially between a first end of the shroud and a second end of the shroud, wherein the shroud defines a plenum disposed between the acoustic liner and the shroud, the plenum is in fluid communication with the core via perforations in the distal skin. The plenum may serve to attenuate low frequency noise known as “buzz saw” tones and/or alleviate pressure resonance conditions that may cause structural damage to the engine fan blades.

Abstract: A fan assembly includes a shrouded fan rotor (18) having a plurality of fan blades (22) extending from a rotor hub (24) and rotatable about a central axis (20) of the fan assembly and a fan shroud (26) extending circumferentially around the fan rotor (18) and secured to an outer tip diameter of the plurality of fan blades (22). A stator assembly (28) is located downstream of the fan rotor (18), relative to an airflow (14) direction through the fan assembly. The stator assembly (28) includes a plurality of stator vanes (30) extending between a stator hub (32) and a stator shroud (34). A flow control ring (36) is positioned between the fan rotor (18) and the stator assembly (28) to block radial flow migration in an axial spacing between the fan rotor and the stator assembly resulting from a radial flow component of an airflow (14) exiting the fan rotor (18).

Abstract: A gas turbine engine for an aircraft has an engine core comprising turbine, compressor, and core shaft connecting the turbine to the compressor, the turbine being the lowest pressure turbine of the engine, and having turbine blades, and the compressor being the lowest pressure compressor of the engine; fan located upstream of the engine core; and gearbox that receives an input from the core shaft and outputs drive to the fan. The engine core further has three bearings arranged to support the core shaft, the three bearings having two rearward bearings located downstream of the leading edge of the lowest pressure turbine blade of the turbine at the root of the blade, and/or, when the turbine comprises four sets of turbine blades, downstream of the trailing edge of a turbine blade of the third set of turbine blades from the front of the turbine, at the root of the blade.

Abstract: A seal device according to the embodiment includes a seal fin provided between the rotation body and the stationary body and extending in a circumferential direction of the rotation body, and a swirl brake fin provided on the stationary body upstream of the seal fin. The swirl brake fin reduces a circumferential velocity component of the working fluid. The swirl brake fin has a negative pressure surface provided on a side of a rotation direction of the rotation body and a positive pressure surface provided on an opposite side to the negative pressure surface. The positive pressure surface extends in a direction opposite to the rotation direction of the rotation body from radially outward toward radially inward.

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 structural subassembly for a compressor of a turbomachine, which has a rotor having a plurality of blades, which extend radially in a flow path of the turbomachine, and a compressor casing, which forms a flow path boundary, which delimits the flow path through the turbomachine radially on the outside. In this subassembly, the compressor casing has casing structuring adjoining the rotor. It is envisaged that the compressor casing has a plurality of circumferential segments, which extend in the circumferential direction, wherein only one or only some of the circumferential segments forms or form casing structuring.

Abstract: A motor-fan assembly includes a motor assembly having a rotatable shaft extending therethrough and a working fan assembly having at least one working fan rotated by the rotatable shaft. The motor-fan assembly includes a motor cover that substantially encloses the motor assembly. The motor assembly provides a cover opening extending therethrough and the rotatable shaft extends through the opening. The motor-fan assembly also includes a cooling fan assembly with at least one cooling fan rotated by the rotatable shaft which fan draws cooling airflow over the motor assembly. A motor vent cover is coupled to the motor cover with the at least one cooling fan therebetween. The motor vent cover has a cooling air outlet through which cooling airflow is exhausted.

Abstract: A gas turbine engine includes a case assembly and a stator segment. The case assembly defines a first slot having a first surface and a second surface. The stator segment includes a shroud body axially extends between a first body end and a second body end. A first flange extends into the first slot. The first flange has a first flange first side, a first flange second side, a first flange first surface and a first flange second surface each circumferentially extending between the first flange first side and the first flange second side. A first portion of the first flange first surface engages the first surface. A second portion of the first flange first surface. A third portion of the first flange first surface is spaced apart from the first surface.

Abstract: A case for an industrial air blower provides noise-reducing foam baffles and vibration absorbing ductile mounting components, mitigating the substantial noise and vibration generated by the blower in operation. Configurable for use of the blower either as pressurized air supply or vacuum source, the case provides circulation of blower inlet air or vacuum outlet air around the blower motor, thereby aiding cooling of the blower motor, reducing the risk of overheating. When configured for use as a pressurized air supply, blower inlet air is heated by the blower motor, the blower thereby providing a heated pressurized air supply suitable for drying wet or water damaged surfaces. Embodiments provide caster wheels and handles for easy transport. Embodiments also provide a pressure relief valve or manometer cut-off to prevent blower overload from excessive pressure.

Abstract: A fan device includes a fan frame, an impeller, a plurality of cushion components, a plurality of first fasteners and a plurality of second fasteners. The fan frame includes a first frame body and a second frame body. The first frame body has a plurality of first engagement parts. The second frame body has a plurality of second engagement parts. The impeller is rotatably disposed on the fan frame. The cushion components are respectively located on different sides of the fan frame. The first fasteners are respectively disposed through the cushion components and engaged with the first engagement parts of the first frame body. The second fasteners are respectively disposed through the cushion components and engaged with the second engagement parts of the second frame body.

Abstract: A method for manufacturing an impeller of a rotary machine, the impeller including at least one vane limiting an inner channel, which is at least partly closed, the method includes successively manufactured the impeller of several material layers by a build-up process from a powder. The powder is applied in each case to a processing plane for the production of each material layer, and then a solid material layer is produced from the powder by a selective energy input, and structural orientation is determined for the impeller, according to which the impeller is built up in layers, and the structural orientation is defined by a first and a second angle, which angles describe the relative position of the impeller to the processing plane.

Abstract: There is disclosed a diffuser pipe assembly having: a plurality of diffuser pipes circumferentially distributed around the central axis and configured for diffusing a flow of compressed air received from an impeller, the diffuser pipes having a diffuser conduit for directing the flow of compressed air, the diffuser conduit curving between an inlet end and an outlet end along a conduit axis, the diffuser conduit having a baseline surface, a first subset of the diffuser pipes having aero-dampers protruding from the baseline surfaces of their diffuser conduits such that the diffuser pipes of the first subset have a natural vibration frequency different than a natural vibration frequency of at least a second subset of the diffuser pipes.

Abstract: A fluid supercharging device, comprising: a rotating shaft; a vane disc coaxially fixed to the rotating shaft; a plurality of fan blades fixed around a perimeter of the vane disc; the back side of the fan blades being provided with at least one fluid guiding inlet, an end of the back side distal from the vane disc is provided with a fluid guiding outlet, a fluid channel communicating the fluid guiding inlet with the fluid guiding outlet is provided along a lengthwise direction inside the fan blades; the fan blades rotate to generate a centrifugal force such that a fluid flows into the fluid channel via the fluid guiding inlet on the back side, and flows out of the fluid guiding outlet along the lengthwise direction of the fan blades.

Abstract: A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.

Abstract: A centrifugal blood pump without a mechanical bearing comprises a pump casing (1), an impeller (9) arranged in the pump casing rotatably about the central axis and freely movable axially and radially within a limited clearance. The impeller has permanent magnets or permanently magnetized magnetic regions (N/S) which cooperate with an electromagnetic drive to set the impeller rotating. A circular wall (12) or circularly arranged wall sections are provided within the pump casing, their inner surfaces defining a radial clearance together with the outer circumference of the impeller to form a hydrodynamic radial bearing for the impeller.

Abstract: An engine, having a first, second, third and fourth quasi-stage, each with a stator and a downstream rotor, wherein a particular blade/vane solidity in the center section is in the first quasi-stage, at least 1.04 and at most 1.16 for the stator and at least 1.46 and at most 1.67 for the rotor; in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor; in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor; in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.

Abstract: A contra-rotating fan structure includes a first base, a first fan, a second base, and a second fan. The first fan is rotatably disposed on the first base and includes a first hub. The first hub has a first largest width. The second fan is rotatably disposed on the second base and includes a second hub. The second hub has a second largest width. The first base and the second base are located between the first fan and the second fan. The second largest width is greater than the first largest width.

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.