Abstract: A system includes an isobaric pressure exchanger (IPX) configured to exchange pressure between a first fluid and a second fluid. The IPX includes a rotor configured to rotate about a longitudinal axis of the rotor. The rotor forms rotor ports arranged substantially symmetrically around the longitudinal axis at a distal end of the rotor. The IPX further includes an end cover configured to be disposed at the first distal end of the rotor. The end cover forms end cover ports. The rotor ports are arranged for hydraulic communication with the end cover ports. The IPX further includes an insert disposed between two of the rotor ports or between two of the end cover ports.

Abstract: An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.

Abstract: A subsea fluid pressure-increasing machine includes an elongated member that is rotatable about a longitudinal axis. The machine also may include a plurality of impellers each having a leading edge, a trailing edge, a suction side, and a chord line defined by a line between the leading and trailing edges. Each impeller is fixedly mounted to the member such that a chord angle defined by an angle between the chord line and the rotation direction is less than or equal to a stall angle at which a maximum force is exerted on a fluid in a direction primarily parallel to the longitudinal axis when the member is rotated in the rotation direction. At least some of the impellers comprise one or more features that effectively reduce a pressure peak or specific loading of the suction side such that the axial length of the impeller is configured to be reduced without exceeding a desired specific load.

Abstract: Provided is an axial fan including: a motor; and an impeller for sending air in an air-blowing direction, wherein the impeller includes: a base covering the motor; and plural blades mounted on an outer peripheral surface of the base, a wind receiving surface of the blade includes a concave portion recessed toward a downstream side in the air-blowing direction, a bottom point of the concave portion is located downstream in the air-blowing direction relative to a first imaginary line perpendicular to the air-blowing direction, the first imaginary line being drawn in a radial direction from a joint position of the blade where the wind receiving surface and the outer peripheral surface of the base merge, and the bottom point is displaced from inward to outward in the radial direction, in going from upstream to downstream in the air-blowing direction, until reaching a radially central part of the blade.

Abstract: The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall grouping together the active-surface (17) and passive-surface (18) walls in the region of this tip to define the bottom (23) of a bathtub tip shape located at the tip of the blade, the method comprising a moulding step implementing a core defining the bathtub tip shape. According to the invention, there is a step of adding metal to the bottom (23) of the bathtub tip by means of a Direct Laser Additive Manufacturing (CLAD) method, to deposit material onto the bottom of the bathtub tip to form therein an inner partition (28) supported by the bottom thereof (23).

Abstract: A fan guard for a fan container includes a housing and a plurality of wings. The housing has a hollow interior defined by a cylindrical inner surface. The housing extends longitudinally between a first housing end and a second housing end. The plurality of wings is positioned within the hollow interior of the housing. Each wing of the plurality of wings extends radially, from a center of symmetry of the cylindrical inner surface to the cylindrical inner surface. Each wing of the plurality of wings is radially curved between the first housing end and the second housing end.

Abstract: A pressure exchanger (1) including a housing (2), a drive shaft (3) and a cylinder drum (4) rotatably arranged in the housing (2) is described, the cylinder drum (4) including two front faces and at least one cylinder (5) between the front faces, wherein the housing (2) includes a port flange (7, 8) at each end of the cylinder drum (4) and at least at one end of the cylinder drum (4) a pressure shoe (18) is arranged between the cylinder drum (4) and the port flange of this end. Such a pressure exchanger should be operated in a cost-effective manner. To this end an adjustable stop arrangement (19) is arranged between the pressure shoe (18) and the cylinder drum (4).

Abstract: The present utility model provides a fan cover shell and an air conditioning unit having the same. The fan cover shell includes an outer frame; multiple annular auxiliary reinforcement ribs, arranged from the center of the fan cover shell towards the outer frame; and multiple main reinforcement ribs, respectively extending from the center of the fan cover shell to the outer frame and intersecting with the auxiliary reinforcement ribs to form multiple ventilation grills; the main reinforcement rib forms a multi-section curve, and any adjacent curves of the multi-section curve bend towards a reverse direction. According to the fan cover shell of the present utility model, a better air guide effect is achieved by optimizing the main reinforcement ribs.

Abstract: An axial flow fan for use with a vehicle cooling system includes a hub defining an axis of rotation, and at least five blades supported on the hub. Each blade includes a leading edge, a trailing edge opposite the leading edge, a pressure side extending between the leading edge and the trailing edge, a suction side opposite the pressure side, a tip, and a root opposite the tip along a blade length. A solidity of the axial flow fan, measured as a percentage of an annular flow area between an outer diameter of the hub and an outer diameter of the tips of the blades projected onto a plane perpendicular to the axis of rotation that is occupied by the blades, is less than 40%.

Abstract: A passive elastic teeter bearing for an aircraft rotor, including, rotatably arranged on an rotational axis of said rotor, a teeter beam, configured for attaching the rotor which has rotor blades, with the teeter beam being configured for performing a teetering motion, and having two pairs of first lugs arranged at opposite ends thereof at a distance with respect to the rotational axis; and a hub piece located below the teeter beam, the hub piece having two arms that extend outwardly in a radial direction, each having a second lug arranged at a distance with respect to said rotational axis. Each second lug is located between the two lugs of a respective pair of first lugs, and respective connecting pins pass through the first and second lugs on either side of the rotational axis. A pair of elastic bushings are arranged on each connecting pin between a first one of the first lugs and the second lug and between a second one of said first lugs and the second lug, respectively.

Abstract: A shroud hanger assembly or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger, for example having a forward hanger portion and a rearward hanger portion. A cavity is formed between the parts; wherein a shroud may be positioned which is formed of a low coefficient of thermal expansion material. The hanger and shroud may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud is positioned within the hanger opening or cavity, one of the forward and rearward hanger portions may be press fit or otherwise connected into the other of the forward and rearward hanger portion.

Abstract: A fan blade comprising a blade body spanning from a blade root to a blade tip in a longitudinal direction and a fluid passageway formed within the blade body and extending from the blade root to the blade tip. The blade body spanning from a leading edge to a trailing edge in a lateral direction. The fluid passageway allowing fluid to flow out of the blade.

Abstract: A propeller fan includes: a rotation-axis part that serves as a center of rotation; and a plurality of blades provided on an outer circumferential side of the rotation-axis part, the plurality of blades being joined to adjoining blades at leading edges and trailing edges thereof. A first rib projecting towards the center of rotation of the rotation-axis part to surround the rotation-axis part, and second ribs projecting towards the center of rotation to extend from the rotation-axis part toward the first rib are provided on pressure surfaces of the plurality of blades. Among ends of the second ribs in the direction of the center of rotation, the ends distant from the pressure surfaces project away from the pressure surfaces farther than an end of the first rib distant from the pressure surfaces, among the ends of the first rib in the direction of the center of rotation.

Abstract: Pressure exchange devices, systems, and related methods may include a tank, a piston, a valve device, and one or more sensors for monitoring a position of the piston in the tank.

Abstract: A centrifugal compressor (P) is provided with: a casing (10) which forms an impeller inlet flow path (11), an impeller flow path (12), an impeller outlet flow path (13), and a scroll (14); and an impeller (3) which is arranged in the impeller flow path (11), wherein the casing (10) is provided with a casing body (15) and a heat conduction inhibiting part (16) which is disposed to heat conduction paths to the impeller inlet flow path (11) from at least the impeller outlet flow path (13) and the scroll (14) so as to inhibit heat conduction to the impeller inlet flow path (11) from at least the impeller outlet flow path (13) and the scroll (14).

Abstract: The disclosure relates to a component for a turbine engine with a heated airflow and a cooling airflow. The component includes a wall separating the heated airflow from the cooling airflow. The wall can have a heated surface confronting the heated airflow and a cooled surface confronting the cooling airflow. The component can also include a baffle with a set of cooling holes.

Abstract: A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

Abstract: A negative hinge offset rotor head for a coaxial helicopter, the rotor head having two or more flapping rotor blades having outer and inner tips, the inner tips rotatably attached to a hinge attachment rotated by a driveshaft where the driveshaft is positioned between the rotor blades and the rotor blades' respective hinge attachment.

Abstract: A propeller. The blades of the propeller are characterized by a blade center axis which corresponds to a generator line of a cone to which the blade, or blade thrust surface, conforms. The propeller hub is fixed to the blade at the root, in line with the blade center axis, such that the hub axis and blade center axis lie in the same plane, and the leading edge of the blade is positioned forward (referring to the upstream direction of movement caused by the propeller) of the trailing edge of the blade.

Abstract: A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (rhub) to a tip defining a 100 percent span position (rtip) and a plurality of span positions therebetween (r?[rhub, rtip]). The hub has a negative hade angle (?) with respect to the rotational axis at an axial position coincident with the leading edge of the blades.