Abstract: A cleaner according to the present disclosure comprises: a body; a suction head connected to one side of the body so as to suction foreign matter from a surface to be cleaned; and a motor assembly received in a motor case formed inside the body, so as to generate suction force, wherein: the motor assembly comprises a motor, an impeller disposed on one side of the motor and connected to the motor so as to introduce air, and a vibration isolator coupled to the other side of the motor and having a plurality of support protrusions protruding from the outer circumferential surface thereof; and the coupling between the plurality of support protrusions and the motor case causes the motor assembly to be spaced apart from the motor case.

Abstract: A system includes an exhaust collector tunnel (32) configured to mount inside an exhaust collector (30) of a gas turbine (12). The exhaust collector tunnel (32) has a tunnel wall (33) configured to extend around a turbine shaft (17, 19) of the gas turbine (12). The tunnel wall (33) has a variable diameter (98) along at least a portion of a length of the exhaust collector tunnel (32).

Abstract: The telescopic hydrokinetic turbine system is a device meant for lifting the burden of manufacturing, installing, and maintaining hydrokinetic systems in the water. The device attempts to overcome the issues faced by present day hydrokinetic systems. To accomplish this, the device includes a light weight and easy to carry and install design, a telescopic pillar to align itself with the tide direction or even to leave the body of water for maintenance. Electrical parts are not submerged but instead remain onshore in a small cabin or housing. Further, by adding the use of multiple diffusers, the water flowing into the turbine is made smoother and the overload of water is able to be evacuated and swiped by the fins. The diffusers increase the blades working capacity while homogenizing the water flow and avoiding the phenomena of vibrations and cavitation, thereby increasing efficiency.

Abstract: A method for optimizing the blade axis position of a water pump under all operating conditions which includes determination of multiple calculation conditions within the range of all the operating conditions of the water pump, three-dimensional modeling and mesh generation of the calculation area of the flow field of the water pump at multiple blade angles, numerical simulation of the flow field and calculation and determination of blade hydraulic torques under multiple conditions, determination of the range of the position of the blade resultant hydraulic pressure action line and an optimal blade axis position under all the operating conditions, determination of the small region of the optimal blade axis position under all the operating conditions, determination of the optimal blade axis position, and comparison of the blade hydraulic torques before and after optimization of the blade axis position.

Abstract: Wind baffles are provided at a side discharge vent of a cabinet containing a heating, ventilation, air conditioning, and refrigeration (HVACR) system. The wind baffles include two or more baffles joined to a support frame. The baffles have a leading edge towards ambient environment surrounding of the cabinet and a trailing edge towards an interior of the cabinet, and the leading edge has a perimeter greater than a perimeter of the trailing edge. The baffles may surround each successive baffle. The baffles may be concentric The wind baffles may be located between ambient environment surrounding of the cabinet and a fan near the side discharge vent. The fan may be a variable-speed fan.

Abstract: A gas turbine engine having an interdigitated turbine assembly including a first turbine rotor and a second turbine rotor, wherein a total number of stages at the interdigitated turbine assembly is between 3 and 8, and an average stage pressure ratio at the interdigitated turbine assembly is between 1.3 and 1.9. A gear assembly is configured to receive power from the interdigitated turbine assembly, and a fan assembly is configured to receive power from the gear assembly. The interdigitated turbine assembly and the gear assembly are together configured to allow the second turbine rotor to rotate at a second rotational speed greater than a first rotational speed at the first turbine rotor. The fan assembly and the gear assembly are together configured to allow the fan assembly to rotate at a third rotational speed less than the first rotational speed and the second rotational speed.

Abstract: An air-sending device includes a propeller fan, a bell mouth surrounding an outer periphery of the propeller fan, a fan grille disposed downstream of the bell mouth and including a plurality of first crosspieces. An edge of the air outlet of the bell mouth includes a varying portion whose distance from a rotation axis of the propeller fan varies. In a cross-section of any of the plurality of first crosspieces that is perpendicular to a longitudinal direction of the any of the plurality of first crosspieces, a virtual line segment connecting an upstream side end portion and a downstream side end portion is defined as a first virtual line segment. At the portions of the plurality of first crosspieces disposed on the inner circumference side of the varying portion, the angle between a virtual line segment parallel to the rotation axis and the first virtual line segment is changed.

Abstract: A diffuser pipe has a tubular body extending from an inlet to an outlet and increasing in cross-sectional area from the inlet toward the outlet. The outlet has a radially inner wall, a radially outer wall, and side walls joining the radially inner wall to the radially outer wall. The outlet has an elliptigon shape in which both the radially inner wall and the radially outer wall are curved. A radius of curvature of the radially outer wall is different from a radius of curvature of the radially inner wall.

Abstract: A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3° and 15°.

Abstract: A computer implemented method for the prediction of the surge point of a compressor includes: generating a plurality of meshes: a compressor inlet mesh, at least a compressor rotor stage mesh, and a compressor outlet mesh, representing a plurality of exit guide vanes and an exit nozzle and extending up to a final nozzle exit area; assembling the plurality of meshes to obtain the CFD domain; specifying boundary conditions of the computational domain; specifying atmospheric pressure conditions at the final nozzle exit area; computing compressor inlet mass flow rate and compressor pressure ratio; checking if the numerical stability limit is not reached, as a result of the numerical stability limit not being reached: decreasing dimensions of the final nozzle exit area; generating again the compressor outlet mesh; repeating the steps of specifying atmospheric pressure at the final nozzle exit area, the step of computing, and the step of checking.

Abstract: An agricultural multi-row sprayer system is provided having a chassis, a tank coupled to the chassis to accommodate a sprayable mixture to be applied to rows of a crop, a first sprayer arrangement coupled to the chassis and arranged to spray the mixture from a first interrow area located between a set of adjacent rows of the crop, and a second sprayer arrangement coupled to the chassis and selectively deployable to spray the mixture from a second interrow area located between an overlapping set of adjacent rows of the crop. The sprayer system may include a linkage arrangement having a distal end that supports the second sprayer arrangement and an input link movably coupled to the chassis, which is controllably manipulable to selectively deploy the second sprayer arrangement to the second interrow area.

Abstract: A liquid heating pump includes an impeller chamber having an impeller, which can be rotatably driven, and a diffusor chamber and/or pressure chamber arranged axially downstream in the flow direction and having a stationary diffusor. A heating device is associated with the diffusor and/or pressure chamber. The diffusor has a main body, in particular in the shape of a circular cylinder. The main body has a front wall on which a guide blade portion is arranged which axially protrudes in a direction of the impeller into a liquid ejection region of the impeller arranged around an outer periphery of the impeller and which extends away from the liquid ejection region outwardly toward an axial outer casing of the main body, which axial outer casing is arranged radially further outwardly than the liquid ejection region of the impeller.

Abstract: An integrated structure of a return device and a pressure diffuser, and a centrifugal compressor are provided. The structure includes a pressure diffuser portion and a return device portion integrally molded with the pressure diffuser portion. The pressure diffuser portion is configured to form a pressure diffusion flow channel. The return device portion has a return channel. The return channel is in communication with the pressure diffusion flow channel, and is configured to guide gas from the pressure diffusion flow channel. The structure of the present invention eliminates a need of independently installing a return device and a pressure diffuser, and eliminates connection seams caused by assembly and misalignment caused by accumulated errors. Therefore, gas can smoothly flow through the pressure diffusion flow channel into the return channel, such that a gas flow is well guided, and the gas flow uniformity is better.

Abstract: A turbine is equipped with a turbine rotor (21), a turbine casing, a turbine blade (24), a turbine stator and a diffuser (4A). The diffuser (4A) is equipped with an inner cylinder (41) extending along an axis, an outer cylinder covering the inner cylinder (41) from an outer circumferential side and forming an exhaust flow path (C) between the inner cylinder (41) and the outer cylinder. The inner cylinder (41) is equipped with an inclined surface (51) extending from an inner side to an outer side in the radial direction centering on the axis as going from one side to the other side in the direction of the axis. The inclined surface (51) is disposed to intersect an extension (55) obtained by extending platforms (54) of a plurality of turbine blades (24) to the other side in the direction of the axis, in a cross sectional view including the axis.

Abstract: A motor includes a motor body, a bracket installed in the motor body, a rotating shaft, a bearing accommodated inside the bracket and supporting the rotating shaft, and a bearing supporter defining a plurality of pores. The bracket and the bearing define a bearing heat dissipation flow path between an outer surface of the bearing and an inner surface of the bracket, and the bearing heat dissipation flow path is configured to pass air therethrough. The bearing supporter is disposed in the bearing heat dissipation flow path, and the bracket defines a bracket through-hole configured to discharge air that has passed through the plurality of pores of the bearing supporter.

Abstract: The air fan with ice compartment is a thermal transfer device. The air fan with ice compartment is an enclosed structure that forces an air flow over a thermally treated mass, such as ice pack, and discharges the processed air flow into the atmosphere. The air fan with ice compartment comprises a base, a fan assembly, a fan control, an over chamber, and a lid. The fan assembly mounts on the base. The over chamber mounts over the fan assembly and the base. The lid and the fan control mount on the over chamber. The fan control controls the operation of the fan assembly. The fan assembly forces the air flow through the space enclosed by the over chamber and the base.

Abstract: A fan frame of an axial-flow fan is provided to reduce the vibration generated during the rotation of the impeller that is transmitted to the outside of the axial-flow fan via the fan frame. The fan frame includes a housing, a base and a plurality of connection members. The base includes a shaft-coupling portion. Each of the plurality of connection members includes two ends respectively connected to the housing and the base. Each of the plurality of connection members is defined with an extension line passing through the two ends of the connection member. Each of the plurality of connection members includes a first bending portion and a second bending portion. The first bending portion extends around a first notch, and the second bending portion extends around a second notch. The extension line extends through the first and second notches.

Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: An exhaust duct for a gas turbine engine has an annular inlet conduit having an inlet axis. At least two outlet conduits branch off from the inlet conduit along respective outlet centerlines that are distinct from one another. The outlet centerlines when projected onto a projection plane perpendicular to the inlet axis are spaced apart from the inlet axis so as not to intersect the inlet axis.

Abstract: A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.

Abstract: An exhaust hood for a steam turbine includes a bearing cone; an annular flow guide; and an external casing surrounding the bearing cone and the flow guide. Meridional shapes of the flow guide at respective circumferential positions are shapes obtained by rotating one representative shape around an upstream end of the representative shape in a meridional plane and by reducing or maintaining a radial length of the representative shape. A circumferential distribution of inclination angles of an upstream end of the flow guide with respect to a center axis of a turbine rotor of the steam turbine has representative inclination angles at respective representative positions in the circumferential direction. The circumferential distribution between the representative positions is defined by a linear interpolation. Each representative position is a position where the inclination angles change from increasing or decreasing to decreasing or increasing, or from constant to increasing or decreasing.

Abstract: A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction.

Abstract: A computer-implemented method for designing a gas turbine exhaust diffuser includes a computer identifying an initial diffuser design and performing a design refinement process. The design refinement process includes generating a new diffuser design by modifying the initial diffuser design according to one or more objective functions and one or more design constraints. A fluid velocity pattern associated with the new diffuser design is determined and used to compute particle tracing lines through an internal portion of the new diffuser design. The particle tracing lines are grouped into particle line bundles extending longitudinally within the new diffuser design and an average path is computed for each particle line bundle. Then, for each respective average path, a rigid tube capable of channeling gases through the internal portion of the new diffuser design is generated and added to the new diffuser design.

Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

Abstract: A diffuser for a gas turbine including a support structure and a liner connected by holders. The liner includes a plurality of adjacent segments with overlapping borders. The overlapping borders are clamped to one another and slidingly rest one above the other.

Abstract: A turbine bucket includes an entry dovetail; an airfoil portion extending from the entry dovetail, the airfoil portion having a leading edge, a trailing edge, a pressure side and a suction side. Radially inner- and outer-span shrouds are provided on each of the pressure side and the suction side, the part-span shrouds each having hard faces adapted to engage and slide relative to corresponding part-span shrouds on adjacent buckets.

Abstract: A centrifugal air blower includes a casing having a spiral scroll, an impeller contained in the casing, an inlet side panel having an inlet, and a motor-fixing side panel fixing a motor. The centrifugal air blower further includes a first triangle wall and a second triangle wall at a discharge outlet opposite to a tongue. The triangle wall where air velocity inside the casing is slower is shaped with a longer vector component (length B) in the direction from the discharge outlet to the impeller than the other triangle wall. This configuration makes the air velocity near the discharge outlet uniform and suppresses a decrease of static pressure, an increase of power consumption, and turbulent flow noise.

Abstract: The invention relates to a cooling fan module for a motor vehicle, having a fan impeller which has a multiplicity of fan impeller blades which are connected to one another via a fan impeller outer ring, having a frame, on which the fan impeller is mounted, having an annular reverse flow guide device, which has an inner ring and an outer ring and which is designed to de-spin a reverse flow between the inner ring and the outer ring and to mix said reverse flow with the slot flow between inner ring and fan impeller outer ring.

Abstract: The present application provides a radial diffuser exhaust system for use with a gas turbine engine. The radial diffuser exhaust system may include a radial diffuser positioned within an asymmetric exhaust collector. The asymmetric exhaust collector may include a closed end chamber and an exhaust end chamber. The closed end chamber may have a first size, the exhaust end chamber may have a second size, and the first size may be smaller than the second size.

Abstract: An airflow assembly, includes a plenum, a barrel, a fan support, a fan assembly, and a plurality of ribs. The plenum includes an opening structure defining a plenum opening. The barrel extends in a downstream direction from the opening structure, and defines a barrel space and a downstream edge. The fan support is at least partially positioned within the barrel space. The fan assembly is supported by the fan support and includes (i) a motor and (ii) a blade assembly configured to rotate about an axis. Each of the ribs extends between (i) the opening structure or the barrel and (ii) the fan support. The downstream direction is parallel to the axis. An upstream direction is opposite of the downstream direction and parallel to the axis. A plane intersects the axis and is perpendicular to the axis.

Abstract: There is provided an air blowing device that is easy to carry and is convenient, the air blowing device that has little adverse effect on the blowing function and is configured to be able to disperse electrically-charged particles while ensuring safety. A fan 4 coupled to an output shaft 33a of a motor 33 is rotated by the motor 33 to send air. The motor 33 is housed in a motor housing portion 3, and a fan cover rear separate body 72 in the shape of a flange, the fan cover rear separate body 72 covering an outer edge portion of the fan 4 and a lateral part of the fan 4 on the side where the motor 33 is located, is fixed to an end of the motor housing portion 3 on the side where the output shaft 33a is located.

Abstract: A steam turbine exhaust hood includes an exhaust hood section, and a butterfly plate arranged in the exhaust hood section. The butterfly plate includes a complex curvilinear cross-sectional profile having a first section that extends between a first end portion and a middle portion, and a second section that extends between the middle portion and a second end portion. One of the first and second sections is formed from at least two curvilinear segments including at least one curvilinear segment having a positive curvature and at least one curvilinear segment having a negative curvature.

Abstract: An electronic enclosure includes a chassis with a fan base and a fan module. The fan base and fan module are disposed so that the fan module may installed in the fan base in a first configuration to provide front-to-rear air flow within the enclosure, or the fan module may be detached from the fan base, turned and reinserted into the fan base in a second configuration to provide rear-to-front air flow within the enclosure. The fan base is provided with two power connectors, one of which mates with the fan module in the first configuration and the second one of which mates with the fan module in the second configuration.

Abstract: A centrifugal pump is provided capable of pumping liquid volume flow rates of at least 20 m3/sec. The pump includes a centrifugal impeller rotatable about an axis and operable to direct a liquid towards a concrete volute arranged around the impeller. The pump further includes fixed fin-like elements arranged between the impeller and the volute. The elements form a discontinuous barrier around the impeller and are effective to reduce uneven radial thrusts exerted by the water on the centrifugal impeller, while limiting the water flow rate in a simple and economic manner.

Abstract: The present document describes a centrifugal ceiling fan. The fan comprises a casing, a motor and a centrifugal propeller. The casing comprises an upper surface comprising an air inlet and a lower surface comprising an air outlet. In an embodiment, the lower surface has a round bowl-like shape including a plurality of openings defining the air outlet. The propeller comprises a shaft and a plurality of blades provided around the shaft. The blades may be curved to push the air in all directions between a first direction substantially perpendicular to the rotation shaft and a second direction substantially parallel to the rotation shaft in order to evenly ventilate the room. The fan may include a heating element for heating the air as it exits from the fan.

Abstract: An exhaust-gas supply device (1) of a turbine wheel (2) of an exhaust-gas turbocharger (3), having a two-channel turbine housing (4) and an exhaust manifold (7) which can be connected to an internal combustion engine (8), which exhaust manifold (7) has a first manifold channel (9) which connects first cylinders (Z1, Z4) of the internal combustion engine (8) so as to form a first manifold exhaust-gas path length, and a second manifold channel (10) which connects second cylinders (Z2, Z3) so as to form a second manifold exhaust-gas path length, to generate virtually identical overall exhaust-gas path lengths of the two channels.

Abstract: In a multi-blade centrifugal fan in which an impeller is provided in a scroll casing in a freely rotatable manner, the scroll casing is provided with an axially expanded portion that forms an air channel at a bottom surface thereof which is expanded in a rotation-axis direction at a radially outer side of an annular flange portion which supports the impeller; and is provided, in a region of an outlet between a tongue portion and a spiral-end portion of the scroll casing in the axially expanded portion, with a protrusion that protrudes radially outward from a radially inner side surface by a predetermined amount so as to directly face an airflow in a circumferential direction.

Abstract: Embodiments of the invention provide a hydraulic isolator to split a volute of a pump into two compartments. The hydraulic isolator is positioned within the volute and includes an inlet positioned around a volute inlet channel of the pump, and an outlet positioned adjacent to an outlet channel of the pump. The hydraulic isolator also includes a toroidal portion to at least partially surround an impeller of the pump.

Abstract: Propulsion unit (11) for propulsion and maneuvering of a maritime vessel, which includes a nozzle (12) exhibiting a curved following edge (12) at outlet of the nozzle (12), which results in that length of the nozzle (12) is longer in upper part of the nozzle (12) and shortest at the outermost points of a horizontal central axis through the nozzle (12), when the nozzle (12) is seen from behind.

Abstract: A fan assembly includes a channel structure and a centrifugal fan. The channel structure includes a housing and at least a slit. The housing has an accommodating space and a flow channel adjacent to each other. The slit is extended along the flow channel. The flow channel is communicated with the outside of the housing via the slit. The centrifugal fan is disposed in the accommodating space. The centrifugal fan draws air along an axial direction and generates an airflow. The airflow flows into the flow channel along a radial direction, and flows out to the outside of the housing via the slit.

Abstract: Provided is a uni-axial multi-stage radial gas expander which has a high degree of reliability and which can sufficiently cope with the conditions of a high pressure and a high pressure ratio. Two or more radial gas expander sections (11A, 11B) formed of two-or-more-stage impeller vanes (14a to 14h) arranged between bearings (21a, 21b) on a rotor shaft (13) consisting of a single shaft are housed in a signal casing (10).

Abstract: A spring seal includes a split body portion with a first leg and a second leg that extend away from a plane and a projection portion which extends from the split body portion within the plane.

Abstract: A high pressure turbine includes a vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

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

Abstract: A compressor includes plural first vanes provided on a shroud side of a diffuser path, and plural second vanes provided on positions of a hub side opposed to the first vanes. The compressor also includes a slide vane mechanism that projects the second vanes into and draws in the second vanes from the diffuser path via the slits of the hub side wall part plate according to a load of the compressor. When the slide vane mechanism projects the second vanes into the diffuser path, end faces of the first vanes and end faces of the second vanes are opposed to each other at the vicinity of the center of the diffuser path.

Abstract: A turbine vane for a gas turbine engine may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.

Abstract: An inlet port 4 and an outlet port 5 which are open in a body housing 2, an air-blowing pathway 20 disposed inside the body housing 2, making the inlet port 4 and the outlet port 5 communicate with each other, and also having a plurality of divisional pathways 22 obtained by division with partition plates 21, an air-blowing fan 7 disposed upstream from the divisional pathways 22 inside the air-blowing pathway 20, a removable inner cover 10 covering the divisional pathways 22 and having an inner surface which forms a side wall of the air-blowing pathway 20, and a removable exterior cover 9 covering the inner cover 10 to form an outer surface of the body housing 2 are provided, and the inner cover 10 has marking portions 11 formed on an outer surface along the partition plates 21.

Abstract: A fan assembly includes a fan and a number of airflow guiding members. The fan includes an end board on which a number of airflow guides may be pivoted out to a horizontal position by airflow pressure but which fall back to a vertical position when the fan is not working, to effectively seal the vent when an airflow is not present.

Abstract: A turbo machine (1) comprises a casing (2) and a first volute tongue (12), an impeller (3) with at least one vane (4), and a flow splitter plate (5) comprising a second volute tongue (13) for splitting a flow of a fluidic medium produced by the impeller. The flow splitter plate comprises at least one opening (10) connecting the first surface (8) and the second, opposite surface (9) so as to reduce or eliminate vibrations.

Abstract: An inner combustion chamber casing of a turbomachine, which is intended to be placed downstream of a centrifugal compressor, is provided. The casing has the shape of a disc, pierced by a central circle, and includes on its disc at least one guide vane of the drawn-off air. The guide vane extends longitudinally over the disc between the periphery of the disc and the central circle and spreads out axially from the disc so as to form with the downstream face of the centrifugal compressor a guide channel for the air which is drawn off upon exit from the said compressor. The guide vane has a curved shape orienting in a radial direction at the level of its most central end.