Abstract: A layered body, which has a change in texture derived from zirconia, particularly a change in translucency and is suitable as a dental prosthetic member, a precursor thereof, or a method for producing these. The layered body has a structure in which two or more layers containing zirconia containing a stabilizer are layered, the layered body including at least: a first layer containing zirconia having a stabilizer content of higher than or equal to 4 mol %; and a second layer containing zirconia having a stabilizer content different from that of the zirconia contained in the first layer. At least one layer contains one or more elements capable of coloring zirconia.

Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle at 100% span is greater than the stagger angle at 50% span.

Abstract: A gas turbine engine actuation system includes a gas turbine engine, an actuation device, an actuator, and a power source. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and a rotating shaft. The actuation device is operable with the compressor section, combustion section, turbine section, or a combination thereof. The actuator is operationally coupled to the actuation device and includes an electric actuator configured to convert electrical current into mechanical power. The power source is configured to supply electrical current to the actuator, alone or in tandem with a hydraulic actuator.

Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is translatable relative to the nacelle along the fore-aft direction.

Abstract: A fan includes an impeller rotating on a central axis, an impeller housing, a motor located on one side in an axial direction of the impeller and driving the impeller to rotate, and a motor housing. The impeller housing is provided with an air inlet. The fan further includes a pre-pressing portion expanding radially inward from an edge of the air inlet. The pre-pressing portion includes a pressing portion located on another side in the axial direction of the impeller and pressing, from the another side in the axial direction, an end portion of the impeller on the another side in the axial direction, and at least two connection portions connected between an outer periphery of the pressing portion and the edge of the air inlet. The connection portions are disposed obliquely with respect to the axial direction.

Abstract: A blower for an HVAC system, the blower includes a housing with an intake and an outlet, a fan or blower wheel disposed within the housing and configured to draw air into the housing via the intake and to exhaust air from the housing through the outlet, and an adjustable cutoff plate configured to be moved between at least a first position defining a first cutoff angle and a second position defining a second cutoff angle.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extending from a nozzle ring though slots in a shroud, are shaped on one side to as to substantially conform to the profile of the surface of the slot, whereby a close connection can be formed between the vane and the slot to inhibit leakage of gas between the vane and the slot surface.

Abstract: A vane arm connection system for a gas turbine engine, includes a vane stem having a flatted head; a vane arm having a claw engaging the flatted head; and a load spreader having a spreader body defining structure engaging the flatted head, and at least one extension extending laterally from the spreader body.

Abstract: A variable vane actuation system for a gas turbine engine includes a stem section, along an axis, the stem section includes a groove; a vane arm comprising a claw section received at least partially into the groove; a clip mounted to the claw section; and a fastener fastened to the stem section along the axis to retain the clip and the vane arm to the stem section.

Abstract: A thermal module including a first body, a second body, a first fan assembly, a second fan assembly, and a shaft is provided. The first body and the second body are slidably connected to each other and form an accommodating space together. The first fan assembly is disposed in the accommodating space and has a first hub and a plurality of first fan blades. The first hub is connected to the first body. The second fan assembly is disposed in the accommodating space and has a second hub and a plurality of second fan blades, and the second hub is connected to the second body. The first hub and the second hub overlap each other. The shaft is pivotally disposed in the first body and the second body and is engaged with the first fan assembly and the second fan assembly.

Abstract: Aspects of the disclosure regard an exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel, a centerbody arranged in the flow channel, at least two struts connecting the centerbody to the nozzle wall, a thrust reverser unit, and a plurality of actuators, wherein each actuator is associated with a strut for displacing the strut in the axial direction. The struts are connected to a structure of the outer nozzle wall that forms part of the thrust reverser unit. For allowing axial relative movement between the struts and the outer nozzle wall, each strut includes a sliding element extending radially from the radial outer end of the strut, wherein the sliding element is arranged in a receiving slot that extends in the axial direction in the nozzle wall. It is provided that the sliding element comprises an interaction structure that interacts with one of the actuators for effecting relative axial movement between the strut and the nozzle wall.

Abstract: A centrifugal compressor includes a rotation shaft, a compressor impeller attached to one end of the rotation shaft, and a first wall surface and a second wall surface formed inside a housing so as to face each other in an axial direction. A diffuser is formed between the first wall surface and the second wall surface in the axial direction, and a wall portion separates the diffuser from an axial space inside the housing in which the rotation shaft extends. The wall portion includes at least one extraction hole that fluidly couples the diffuser to the axial spate and that is configured to extract a gas from the diffuser.

Abstract: An insect trap to entice and collect insects with UV light, and including a main body, a cross-fan, an insect filter, an insect collector detachably provided to the cross-fan, and a decoy UV LED installation unit coupled to a buttress above the main body and including a decoy UV LED module, in which the main body has an inlet port and a flow channel having an inclined shape and a curved shape extending from the inclined shape, the insect collector including an insect collector mesh through which air introduced into the main body is discharged, the decoy UV LED module includes at least one chip-on-board type UV LED chip or at least one UV LED package mounted on a support substrate, and the insect filter is detachably coupled to the inlet port and allows selective passage of insects therethrough.

Abstract: The invention relates to a turbocharger with a variable turbine geometry, comprising a turbine (1, 2, 5, 6, 7, 8, 9) with a turbine rotor (1) which is rotatably mounted in a turbine housing (2); the turbine (1, 2, 5, 6, 7, 8, 9) comprising a blade bearing ring (5) being arranged about a turbine axis (A); wherein the blade bearing ring (5) supports a number of blade shafts (6); wherein adjustable guide blades (7) are arranged at the blade shafts (6) on a front side of the blade bearing ring (5); wherein blade levers (8) are arranged at the blade shafts (6) on a rear side of the blade bearing ring (5); wherein an adjustment ring (9) is arranged coaxially with the blade bearing ring (5) and engages with the blade levers (8), a rotation of the adjustment ring (9) relative to the blade bearing ring (5) providing for an adjustment of the guide blades (7); wherein the adjustment ring (9) comprises at least one axially protruding bearing stop (10), the bearing stop (10) being provided by deformation of the adjustment

Abstract: The invention relates to a turbine comprising a turbine housing defining a volute having a substantially annular outlet opening, a turbine wheel, and an adjusting ring, rotatable about the turbine axis, which is arranged in the turbine housing radially between the volute and the turbine wheel, wherein the adjusting ring comprises a flow channel between a radially outer first peripheral opening and a radially inner second peripheral opening, and wherein the outlet opening is fluidically coupled to the turbine wheel by the flow channel. The outlet opening and the first peripheral opening have a path, variable in the axial direction, so that during a rotation of the adjusting ring, the outlet opening and the first peripheral opening are adjusted relative to each other in such a way that an overflow cross section between the outlet opening and the first peripheral opening is variably changeable.

Abstract: A turbine (1) for a conduit comprising a turbine unit (13) including a rotor (3), characterized in that the turbine (1) comprises a speed limiting device for said turbine unit (13), which device comprises at least one flexible element (4) connected to the turbine unit (13), so as to limit the flow rate of the fluid passing through the rotor (3) in order to limit the rotational speed of the rotor (3) of the turbine unit (13).

Abstract: A dryer appliance, as provided herein, may include a cabinet, a drum, a motor, an impeller, and a housing. The motor may be mounted within the cabinet. The impeller may be in mechanical communication with the motor to motivate rotation of the impeller about an axial direction. The impeller may be rotatable about the axial direction to urge a flow of air from the chamber of the drum to a vent of the cabinet. The housing may include a front panel and a rear panel. The front panel and the rear panel may be spaced apart along the axial direction by a housing cavity within which the impeller is positioned. The front panel may define an entrance upstream of the impeller. The rear plate may define a circular groove may extend rearward from the housing cavity and be concentrically aligned with a circumferential perimeter of the impeller.

Abstract: A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.

Abstract: The present invention discloses volute for a centrifugal fan, which comprises a volute tongue having an inner wall; wherein, the volute tongue has an enclosed noise-reducing chamber, the volute tongue has a plurality of holes for allowing the air flow to enter into the noise-reducing chamber; and a sound collector and a speaker are disposed in the noise-reducing chamber. In the present invention, during the use of the centrifugal fan, a gas flow can enter the cavity through the holes on the inner wall. The sound collector can acquire a noise signal and transmit it to a controller, and the controller calculates a noise-reduced audio signal according to the acquired signal and then controls the speaker to play the corresponding reduced noise according to the noise-reduced audio signal, so that the active noise reduction is realized. With such a structure, the vortex at the volute tongue is eliminated, thus the fan noise is reduced and the fan efficiency is improved.

Abstract: A multi-stage turboexpander and a method for generating mechanical power therewith are disclosed. The multi-stage turboexpander includes a casing and a shaft, arranged for rotation in the casing. The shaft is supported by a first bearing at a first shaft end portion and a second bearing at a second shaft end portion. A first radial impeller and a second radial impeller are arranged between the first bearing and the second bearing on the shaft for co-rotation therewith around a rotation axis.

Abstract: A pre-cooler system employs a powered pre-cooler fan assembly having a fan adapted to receive bypass engine fan air through an inlet plenum with an outlet guide vane array (OGVA) adapted to control airflow from the inlet plenum and fan, with a rotational power source operationally connected to the fan. A shroud directs airflow from the inlet plenum, fan and OGVA into a pre-cooler disposed downstream of the fan and OGVA.

Abstract: A fan coil unit, including: a blower including a volute, a wind wheel, and a motor; a fan housing; a heat exchanger; and a hydrostatic plate. The volute includes a first chamber, a first air inlet, and a first air outlet. The wind wheel is disposed in the first chamber of the volute. The motor includes an output shaft which extends into the first chamber and is connected to the wind wheel. The fan housing includes a second chamber, a second air inlet, and a second air outlet. The heat exchanger is disposed in the second chamber and is located between the second air inlet and the second air outlet. The volute further includes a volute tongue which is close to the first air outlet. The hydrostatic plate is connected to the volute tongue. The hydrostatic plate includes an upper end and a lower end.

Abstract: A vane arm assembly for a gas turbine engine includes a vane stem having a circumferential groove axially spaced from an outer end of the vane stem. The assembly also includes a vane arm defining an arm aperture that the vane stem is disposed within. The assembly further includes a mechanical fastener retaining an axial position of the vane arm in the axial direction. The assembly yet further includes a retention clip having a base portion and at least one clip arm, the base portion defining a clip aperture that the vane stem is disposed within, the base portion disposed within the circumferential groove of the vane stem to couple the retention clip to the vane stem, the at least one clip arm including a retention member engaged with the vane arm to provide redundant axial retention of the vane arm.

Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system comprising: a vane arm having a radially inward facing surface, a radially outward surface opposite the radially inward facing surface, a wedge projecting away from the radially inward facing surface, an aperture extending from the radially outward surface to the radially inward surface, and an interlocking feature located in the aperture and circumferentially opposite the wedge relative to the aperture; and a vane stem having a first end, a second end opposite the first end, a seat surface interposed between the first end and the second end, a primary portion extending from the first end to the seat surface, a secondary portion extending from the seat surface to the second end, and a stem notch configured to interlock with the interlocking feature of the vane arm.

Abstract: An exhaust gas turbocharger has a turbine with a turbine wheel. The turbine wheel is axially mounted in a turbine housing and has turbine blades, each with a leading edge for a flow of media. An adjustable guide grate with a plurality of stator vanes adjusts a flow cross-section relative to the leading edge of the turbine wheel. Each stator vane has a vane rear edge facing the turbine wheel. A plane is defined by a rotational axis of the turbine wheel and at least one point on the leading edge, wherein a projection of the leading edge onto the plane is axially inclined relative to the rotational axis of the turbine wheel at least in one region, and the stator vanes are arranged radially about the turbine wheel at least in the region.

Abstract: A highly efficient wind turbine is used to generate electricity from wind. The highly efficient wind turbine includes a cowling, a turbine wheel, a support shaft, and an electricity-generating unit. The cowling is mounted around the support shaft and is used to protect the turbine wheel and channel wind. The turbine wheel is mounted to the support shaft and generates rotational energy from wind. The electricity-generating unit is coupled to the turbine wheel and converts rotational energy from the turbine wheel into electricity. A front wind-channeling cone and a back wind-channeling cone are mounted on either side of the turbine wheel. The front wind-channeling cone directs wind towards the outside of the turbine wheel to maximize leverage. The back wind-channeling cone is used to reduce drag. A wind accelerator is mounted around the cowling and is used to optimize the efficiency of the turbine by accelerating airflow.

Abstract: A turbocharger, with a turbine and compressor housing connected to a bearing housing. An inflow housing of the turbine and bearing housing are connected via a fastening device mounted to a flange of the inflow housing with a first section and partially overlaps a flange of the bearing housing with a second section. Between the inflow housing and the bearing housing, flanges of a nozzle ring and of a sealing cover are clamped. Adjoining surfaces contacting one another in a region of a first, second, and/or a third contact clamping region are hardened.

Abstract: A turbocharger (10) comprising: a rotating shaft (14); a turbine wheel (12); a turbine housing (31); a scroll flowpath (34) having gas flowing therethrough that rotates and drives the turbine wheel (12); a nozzle flowpath (35) that guides gas radially inwards from the scroll flowpath (34) and supplies gas to the turbine wheel (12); and a vane (53) that adjusts the amount of gas introduced in the nozzle flowpath (35). The vane (53) comprises a guide section (60) that guides the gas flow (F) in the turbine wheel (12) radially inwards.

Abstract: An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, and the stationary element has a plurality of vanes configured to impart a change in tangential velocity of the working fluid opposite to that imparted by the rotating element acted upon by the rotating element. The system includes an inlet forward of the rotating element and the stationary element.

Abstract: The gas turbine has a plurality of inlet guide vanes each having a blade having a leading edge, a trailing edge, a span extending along the leading edge, and pivot members at opposite ends of the leading edge, and being pivotally mounted across the radial-to-axial intake via the pivot members, the pivot axis extending axially across a radial portion of the radial-to-axial intake. The plurality of inlet guide vanes include a plurality of first inlet guide vanes, and a plurality of second inlet guide vanes, the second inlet guide vanes having a trailing edge recess differing from the corresponding portion of the first inlet guide vanes. During operation, when the inlet guide vanes are pivoted past a given angle toward the tangential orientation, a radial flow of gas is allowed through the trailing edge recesses to avoid or impede vortex whistle.

Abstract: There is provided a variable vane apparatus including: a housing portion; a plurality of vane gear portions configured to rotate and provided on the housing portion to be spaced apart from one another; a plurality of variable vane portions connected to the plurality of vane gear portions; a drive gear portion configured to transfer power to the plurality of vane gear portions; and a connection gear portion arranged between the plurality of vane gear portions and configured to transfer power amongst the plurality of vane gear portions.

Abstract: A centrifugal compressor having a stator which is designed as an inlet stator, in particular for a compressor, with at least one vane having a vane airfoil around which a fluid can flow, with a plurality of vanes arranged in the form of a ring, with an adjustment device for adjusting the vane, wherein a curvature of a profile center line of the vane airfoil has at least one inflection point.

Abstract: An air conditioner, including: a housing (10) having an air inlet (11) and an air outlet (12); a centrifugal fan (20) rotatably disposed in the housing (10), the centrifugal fan (20) including a plate portion (21) and blades (22) disposed on the plate portion (21); a heat exchanger (30), the heat exchanger (30) being disposed in the housing (10); and a slidable support portion (40) disposed in the housing (10) to support the centrifugal fan (20).

Abstract: A variable turbine geometry assembly is provided for controlling flow of exhaust gas to a turbine wheel of a turbocharger. The variable turbine geometry assembly includes a base structure, vanes, vane levers, and an adjustment ring. The vanes are distributed circumferentially around the base structure and are pivotable relative to the base structure to vary an effective inlet area. The vane levers are for pivoting the vanes. The vane levers each include an inner portion coupled to one of the vanes and an outer portion extending from the inner portion. The adjustment ring is selectively rotatable about a central axis to pivot the vanes. The adjustment ring includes apertures that are each associated with and have received therein the outer portion of one of the vane levers. The outer portion of each of the vane levers includes an outer surface that is non-parallel with the central axis.

Abstract: A pump (1, 101) includes a pump housing (2, 102) having an intake opening (5, 105) and a plurality of outlet openings (6, 106). A pump wheel (9, 109) is accommodated in the housing (2, 102) in a rotationally drivable manner to effect a fluid stream from the intake opening (5, 105) to the respective outlet opening (6, 106). An adjustable ring element (13, 113) is provided radially outside the pump wheel (9, 109) and inside the housing (2, 102). The adjustable ring element (13, 113) enables the fluid stream through the respective outlet opening (6, 106) to be regulated.

Abstract: The present disclosure relates to a variable compressor that may include a housing, a recirculation slit, a bladder, and a pressure providing device. The recirculation slit is formed in an inlet port of the compressor housing so as to discharge a portion of a fluid flowing into the inlet port to the outside of the inlet port and then reintroduce the portion of the fluid into the inlet port. The bladder is installed to expand and contract so as to change a cross-sectional area of the recirculation slit. The pressure providing device is disposed to expand and contract the bladder.

Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of leading edge radius to maximum thickness is between 0.40 (r/Tmax) and 0.45 (r/Tmax) and a ratio of leading edge radius to axial chord length is between 0.17 (r/bx) and 0.27 (r/bx).

Abstract: Systems and methods include actuation system of turbomachinery that include an actuator configured to control pitch of vanes of the turbomachinery and a positioner configured to position the actuator to control the pitch. The actuation system also includes a controller system communicably coupled to the positioner. The controller system is configured to drive the positioner based at least in part on a set point of the turbomachinery and obtain data from the positioner indicating an amount of force used for a target pitch. Using the data, the controlling system derives an operating condition for the turbomachinery and controls the turbomachinery based at least in part on the operating condition of the turbomachinery.

Abstract: In the present disclosure, an example method is provided. The example method may comprise operating a pumped thermal system in a charging cycle at a first compression ratio, wherein the pumped thermal system comprises a working fluid circulating through, in sequence, a compressor system, a hot side heat exchanger, a turbine system, and a cold side heat exchanger, wherein the working fluid is in thermal contact with a hot thermal storage (“HTS”) medium in the hot side heat exchanger and the working fluid is in thermal contact with a cold thermal storage (“CTS”) medium in the cold side heat exchanger. The example method may also comprise operating the pumped thermal system in a discharging cycle at a second compression ratio different than the first compression ratio.

Abstract: An adjustment ring (50) is configured to facilitate vane (30) position adjustment in a variable turbine geometry turbocharger (1), and is formed of an assembly of one or more first ring portions (60) that are formed of a first material, and one or more second ring portions (61) that are formed of a second material. The first material has different material properties than the second material. In some embodiments, high-wear portions of the adjustment ring (50) can selectively and cost-effectively be formed of wear-resistant material while remaining portions are formed of a conventional material. A cost-effective method of manufacturing multi-piece adjustment rings (50) is described.

Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.

Abstract: According to an embodiment of the present invention, a tidal power generator may comprise: a plurality of channel levees which are arranged spaced apart from each other so as to form a channel having a constant width and which have a plurality of installation grooves, each being formed by recessing the surface facing the channel, wherein a tidal current can move forward/backward in the channel; a first water collection levee extending from the front end of the channel levees with reference to a movement direction of the tidal current and having a peak shape of which the width is gradually reduced towards the front side of the channel; a second water collection levee extending from the rear end of the channel levees with reference to the movement direction of the tidal current and having a peak shape of which the width is gradually reduced towards the rear side of the channel; and a waterwheel module which is inserted and installed in the installation groove and can generate power using movements of the tidal

Abstract: Systems and methods for controlling stators of a compressor of a gas turbine engine are provided. The stators and rotatable blades may be included in a stage of the compressor. The rotatable blades may be configured to rotate about an axial axis of the compressor, and each of the stators is rotatable about a corresponding vane axis that extends radially outward from the axial axis of the compressor. Electric motors may be coupled to the stators, where each of the electric motors is configured to individually rotate a corresponding one of the stators in the compressor. A motor controller may be configured to cause the electric motors to rotate the stators in unison or individually.

Abstract: There is disclosed an aero gas turbine engine comprising a compressor and an array of variable inlet guide vanes for the compressor. The angle of the variable inlet guide vanes is controlled by scheduling, the scheduling comprising a first component invoked for engine ground start and a second component invoked for engine in-flight windmill start at least under particular flight conditions. The angle of the variable inlet guide vanes required by at least a portion of the second component is greater than the angle of the variable inlet guide vanes required by at least a portion of the first component.

Abstract: A support ring is connected to a first nozzle ring by multiple connecting pins. An outer cutout is formed at a region on an outer side in a radial direction at a rim on an axially one side of each first attachment hole in the first nozzle ring. An inner cutout is formed at a region on an inner side in the radial direction at the rim on the axially one side of each first attachment hole in the first nozzle ring. An outer cutout is formed at a region on an outer side in the radial direction at a rim on an axially other side of each pin hole in the support ring. An inner cutout is formed at a region on an inner side in the radial direction at the rim on the axially other side of each pin hole in the support ring.

Abstract: A regulator assembly, comprising a vaned diffuser, a motor, a driving gear engaged with a driven gear, the driven gear having rectangle-shaped through holes thereon, the rectangle-shaped through holes disposed and extending along an axis of the driven gear, and a regulating mechanism including a regulator, a supporting member, wherein the regulator is sleeved on the supporting member, and wherein the vaned diffuser is fixed on the supporting member, and regulator sliding members fixed to the regulator through the rectangle-shaped through holes of the driven gear, whereby the motor is configured to drive the driving gear to rotate, the driving gear is configured to drive the driven gear to rotate, the driven gear is configured to push the regulator sliding members to move, and the regulator sliding members are configured to drive the regulator to rotate relative to the vaned diffuser, thus driving the regulator to move along its axis.

Abstract: An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes.

Abstract: A runner vane of an axial hydraulic machine according to embodiments described herein includes a center-side vane part provided on a radial center side and defined by a center-side camber line, and a boss-side vane part provided at a side edge on a side of a runner boss and defined by a boss-side camber line. As determined by the flow direction of a turbine, a curvature of an upstream side portion of the boss-side camber line is larger than a curvature of an upstream side portion of the center-side camber line. An upstream end of the boss-side vane part is positioned on a side of a rotation direction of a runner in comparison with an upstream end of the center-side vane part when viewed toward a downstream side along a rotation axis line of the runner.

Abstract: A gas turbine engine variable guide vane has a fixed portion on an upstream side, a movable flap on a downstream side and a transfer slot between a fixed portion trailing surface and a movable flap leading surface. The movable flap has opposite pressure and suction sides along a chord line between leading and trailing edges, and is rotatable about an axis along a movable flap span over a range of angular positions between open and closed. The trailing surface has a substantially U-shaped profile with first and second branches respectively partially around the pressure and suction sides. The transfer slot has inlet and exhaust ports respectively on the pressure and suction sides. In the closed position the suction side contacts the second branch closing the exhaust port, and in the open position the second branch directs a first air flow through the transfer slot tangentially over the suction surface.

Abstract: A fan assembly and a method of assembling a diffuser collar in the fan assembly are disclosed. The fan assembly includes an impeller including a plurality of blades. The impeller has an impeller diameter. A duct is configured to receive an outflow provided by the impeller. The duct has a duct exit diameter that is larger than the impeller diameter. The fan assembly further includes a diffuser collar extending from the impeller toward a duct exit. The diffuser collar is configured and arranged to radially expand the outflow provided by the impeller. The diffuser collar has a first diameter at a first edge disposed a first distance from the impeller. A contour extends from the first edge toward a second edge having a second diameter. The second edge is disposed a second distance from the impeller. The first distance is smaller than the second distance, the first diameter is smaller than the second diameter, and the first and second diameters are smaller than the duct exit diameter.