Abstract: A turbine blade for a gas turbine engine, including: an airfoil, the having a leading edge, a pressure side, a suction side and a trailing edge; a plurality of internal cooling cavities including a leading edge cavity, a leading edge feed passage, pressure side cooling passages, suction side cooling passages and main body cavities; the leading edge cavity extending towards the suction side; a first crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage; and a second crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage, a centerline of the first crossover row of cooling passages is located closer to the pressure side than a centerline of the second crossover row of cooling passages and the centerline of the second crossover row of cooling passages is located closer to the suction side than the centerline of the first crossover row of cooling passages, and where

Abstract: A rotor-hub flap-measurement system includes a rotor hub operable to flap relative to a main-rotor axis, a flap-linkage arm, a first end of the flap-linkage arm rotatably coupled to the rotor hub, the flap-linkage arm responsive to flapping of the rotor hub, and a magneto-resistive sensor system rotatably coupled to a second end of the flap-linkage arm and responsive to movement of the flap-linkage arm.

Abstract: A turbomachine fan module includes a fan shaft and a lubrication chamber traversed axially by at least part of the fan shaft. The module further includes at least one first bearing configured to support and guide the fan shaft in rotation. The fan shaft has a first tubular part closed by a cover, wherein the first tubular part has a distal end and a proximal end that are opposite each other along a longitudinal axis X and an annular squealer cavity, formed in an inner surface of the fan shaft, between the distal end and the proximal end. The cover has a body extending along the longitudinal axis X and mounted in the first tubular portion so as to cover and sealingly close the annular squealer cavity.

Abstract: A drive assembly for a mechanical reducer for a turbomachine, in particular for an aircraft, includes planet gears, a planet carrier having at least one transverse wall, plain bearings for guiding the planet gears in rotation, and an oil supply circuit for the plain bearings. The planet carrier has collars for attaching the planet gears to the at least one transverse wall, and each of the planet gears includes at least one external cylindrical surface for forming an oil film with an internal cylindrical surface portion of each of the collars for forming said oil film.

Abstract: A ceiling fan or similar air-moving device can include a motor for rotating one or more blades to drive a volume of air about a space. The blade can include a body having an outer surface with a flat top surface and a flat bottom surface, and a side edge. A curved transition can extend between one of the flat top surface or the flat bottom surface, and the side edge. The side edge can be arranged at an angle.

Abstract: A pressure exchanger includes a rotor including rotor ducts that extend parallel to each other. The pressure exchanger further includes a flow divider that has a substantially flat shape and is located in the rotor ducts, where the flow divider partitions an inner space of one of the rotor ducts into flow paths configured to communicate fluid. The flow divider defines an aspect ratio of each of the plurality of flow paths, where the aspect ratio is a ratio of a width of one of the flow paths in a radial direction with respect to an axial length of one of the flow paths in the axial direction.

Abstract: A system for cooling a load coupling coupled to a gas turbine and disposed within an exhaust housing is provided. The system includes a shroud configured to be mounted about the load coupling, the shroud defining an inlet passage between the shroud and the load coupling and an outlet passage between the exhaust housing and the shroud. The system also includes a set of blades configured to couple to the load coupling. The set of blades are angled to draw air into the inlet passage as the set of blades rotate with the load coupling.

Abstract: A system for bleeding air from a core flow path of a gas turbine engine includes a bleed valve in a bleed air duct configured to receive bleed air from a first entrance point to the core flow path into the bleed air duct; a pressurized air valve in a pressurized air duct configured to receive pressurized air from a second entrance point to the core flow path, the pressurized air at a pressure greater than that received into the first entrance point; an eductor outlet from the pressurized air duct located in the bleed air duct; and a control system operable to control operation of the bleed valve and the pressurized air valve.

Abstract: Proposed is an airfoil wing-shaped aircraft including a body having a wing-shaped longitudinal cross-section and having an upper surface on which a shape of a concave curvature-surface portion is formed along a center axis in a streamwise direction, a fluid inlet being formed in each of the opposite lateral sides of a leading portion of the body, and a fluid output being formed in each of the opposite lateral sides of a tail portion of the body, wherein a duct connects the fluid inlet and the fluid outlet to each other.

Abstract: A gas turbine engine includes a propulsor section and a speed change mechanism for driving the propulsor section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers extending 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 propulsor section support bearing is mounted on a first axial side of the speed change mechanism and a second propulsor section support bearing is mounted on the bearing support on a second axial side of the speed change mechanism. The second propulsor section support bearing is a propulsor thrust bearing. Each of the plurality of fingers include a pin opening with a pin extending through the pin opening and into the epicyclic gear train.

Abstract: A Multi-Purpose Portable Fan, which may include a hand-held-style fan to enhance the atmosphere at an event while having a mobile device application, which may be able to summon aid when needed. The hand-held style fan may have located in a handle and/or otherwise lights, or a fan array with LED lights. The handle may be configured with a multi-position switch, a global positioning system-enabled location transmitter and/or receiver, at least one universal serial bus port, at least one solar panel, a battery status display, a wiring interface for LED lights and/or other included electronic devices, and a mobile device application interface. The mobile device application may include at least one interface such as a sign-in interface, a color-select interface, and a situation interface.

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.

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.