Abstract: A rotor blade for a gas turbine engine includes an airfoil section and a root section extending along a longitudinal direction between an upstream surface and a downstream surface. The root section further extends along a radial direction between an inner surface positioned at an inner end of the root section and an outer end coupled to the airfoil section. Moreover, the root section extends along a circumferential direction between a first side surface and a second side surface. Furthermore, the root section defines a longitudinal centerline extending along the longitudinal direction and positioned equidistant from the inner surface and the outer end in the radial direction. The root section includes a first portion formed from a composite material and a second portion formed from a metallic material, with the longitudinal centerline extending through the second portion of the root section.

Abstract: An oil collector for a torque transmission device of an aircraft turbine engine, this oil collector being configured to collect sprayed oil, wherein it includes at least one wall formed at least in part by a mesh structure, and at least one recovery device located at one end of the wall and configured to recover the oil captured by the wall and intended to flow from this wall to the recovery device.

Abstract: A turbine rotor in an embodiment is configured by joining a rotor component member and a rotor component member together by bolt fastening with an abutting end surface of the rotor component member and an abutting end surface of the rotor component member abutting on each other. The turbine rotor includes: a cylindrical recessed portion that is formed at the abutting end surface and is recessed in an axial direction; an axial passage bored from a bottom surface of the cylindrical recessed portion in the axial direction; an introduction passage introducing the cooling medium into the axial passage; a discharge passage discharging the cooling medium from the axial passage; and a sealing member that is arranged in the cylindrical recessed portion and seals one end of the axial passage.

Abstract: An air pump is delineated for an inflatable product that can be selectively connected thereto. The inflatable product includes a shell located on a side wall. The shell includes an internal chamber for selective placement of the air pump and an air valve for selective communication with the air pump. When the air pump is located in the internal chamber it can be moved to switch between a first position and a second position. The air pump includes an air inlet and an air outlet such that the air inlet is in communication with the air valve in the first position to deflate the inflatable product and the air outlet is in communication with the air valve in the second position to inflate the inflatable product. The air pump can also be used externally via manual connection between the air inlet or the air outlet and other inflatable products.

Abstract: A dynamically controlled cooling device for targeted cooling of a moving or stationary user includes a fan, which is rotationally mounted to a base, and a targeting device, which is in possession of the user. A first actuator is attached to the base and is operationally engaged to the fan to selectively rotate the fan. A control module is operationally engaged to the first actuator and the fan. The control module comprises a first receiver, which is Global Positioning System (GPS) enabled, and a second receiver. The targeting device comprises a third receiver, which is GPS enabled, and a transmitter. The first receiver and the third receiver receive coordinates of the fan and the user, respectively. The transmitter relays the coordinates of the user to the control module, whereupon the control module to actuates the fan and the first actuator to direct a stream of air onto the user.

Abstract: A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a radially outer beam operatively coupling the shoe to the base. The seal yet further includes a radially inner beam operatively coupling the shoe to the base, wherein one of the radially inner beam and the radially outer beam is oriented to be angled relative to the other of the radially inner and outer beam.

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 profiled structure for an aircraft or turbomachine is elongated in a direction in which the structure has a length exposed to an airflow and includes serrations defined by successive teeth and depressions. The serrations may be transverse to a leading edge and/or a trailing edge of the profiled structure and in the direction of elongation. Along the profiled leading edge and/or profiled trailing edge, the successive teeth and depressions may extend only over a part of the length exposed to the flow. The amplitude and/or spacing of the teeth may vary monotonically except for the few teeth nearest each end of the part, with a remaining part of the length being smooth.

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 assembly includes an internal housing having an outer internal housing, and an inner internal housing partially disposed within the outer internal housing. The inner internal housing defines an internal cavity, and has a curved exterior surface. Stator blades extend between the inner internal housing and the outer internal housing.

Abstract: An elongate air delivery assembly having a housing extending between two end caps. The housing includes a plurality of exit vents from which airflow is provided in a consistent sheet at a uniform velocity, and the housing is rotatable about a central longitudinal axis to change a direction of the airflow. A method of improving plant cultivation includes positioning one or more elongate air delivery systems adjacent rows of plants such that the sheet of air generated by the elongate air delivery system is directed horizontally across the plants underneath their plant canopy.

Abstract: An airfoil arrangement for a gas turbine engine may include a clearance device using a shape memory alloy movable to provide clearance between an airfoil and one or more other components of the gas turbine engine. The clearance device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second convex sides that join the leading end and the trailing end. The first and second convex sides span in a longitudinal direction between first and second ends. The first and second convex sides define lateral bounds of an internal core cavity, and the first and second convex sides converge toward each other at each of the first and second ends such that the internal core cavity constricts at the first and second ends. A multi-piece baffle is disposed in the internal core cavity and has a shape that is complementary to the first and second convex sides.

Abstract: A propeller (1) and a respective use method are described, comprising a cylindrical casing (3), a hub (2) couplable to an engine and rotatably mounted at least partially in the cylindrical casing of the propeller, and at least one blade (4) rotatably pivoted to the cylindrical casing. The hub (2) is rotatable with respect to the cylindrical casing of the propeller, or vice versa, to adjust the fluid dynamic pitch of the at least one blade (4). The propeller further comprises at least one elastic element (8) interposed between the hub (2) and the cylindrical casing (3) and it is characterized in that the elastic element (8) is preloaded to prevent its deformation until the resistant torque opposing the propeller rotation is lower than the torque generated by the preload of the elastic element (8), wherein said at least one blade is arranged on at least one first fixed fluid dynamic pitch before the deformation of the elastic element (8) begins.

Abstract: A pump includes a housing which forms a suction chamber and a discharge chamber therein; a suction nozzle which is disposed in one side of the housing, and communicates with the suction chamber; a discharge nozzle which is disposed in the other side of the housing, and communicates with the discharge chamber; a partition wall which partitions the suction chamber and the discharge chamber, and has a communication hole, which communicates the suction chamber and the discharge chamber, that is formed at a central portion; and a plurality of baffles which are disposed inside the suction chamber, and guide fluid introduced through the suction nozzle to the communication hole, wherein the plurality of baffles have different lengths and are separated apart from each other in a circumferential direction in an upper side of the partition wall.

Abstract: A fan frame includes a metal base and a frame body. The metal base has a center portion, a plurality of supporting portions with strip shapes and a plurality of wing portions. Each of the supporting portions has a head end, a middle part and a tail end. The head end connects to a peripheral part of the center portion. The wing portions extend outwardly at an angle from the middle parts of the supporting portions, respectively. The frame body has a frame wall. The wing portions are partially at least covered by the frame body. Another fan frame is also disclosed.

Abstract: An onboard system and a method for draining an aeroengine. The onboard system comprises a buffer tank having an admission passage for admitting under gravity fluid coming from the aeroengine, a primary tank situated above the buffer tank and having an emptying passage for emptying the fluid coming from the aeroengine, and a lift circuit connecting the buffer tank to the primary tank in order to transfer the fluid coming from the aeroengine from the buffer tank to the primary tank.

Abstract: A cleaner reduces noise. The cleaner includes a motor, a fan including a number Z of blades and rotatable at a rotational speed N, indicating revolutions per minute, about a rotation axis by the motor, a cover having an inlet located frontward from the fan, and a number V of ribs located in the inlet. The ribs extend in a radial direction from the rotation axis and are arranged in a circumferential direction about the rotation axis. The fan is rotatable to produce noise having a frequency fNZ of 20,000 Hz or higher, and fNZ=(m?k×V)×N/60 and m=n×Z+k×V, where n is an order, m is an integer, and k is an integer.

Abstract: In an aspect there is disclosed, a fan arrangement for a duct, the fan arrangement including a housing having an inlet and an outlet adapted to communicate air with the duct and an axially rotatably driven impeller supported within the housing between the inlet and the outlet. The impeller includes a hub carrying a plurality of blades that span in a radial direction outwardly of the hub, the plurality of blades being shaped to urge air between the inlet and the outlet. The plurality of blades may have a tip solidity ratio in the range of about 0.8 to 1.2, and each of the plurality of blades may have a twist angle between a root and a tip thereof in the range of about 15 to 30 degrees and a substantially constant thickness. An impellor, a blade, ventilation system and related methods are also disclosed.

Abstract: A fan impeller includes a hub, a shaft, a metal housing and a plurality of blades. The outer periphery of the hub has a curved surface. The shaft is disposed in the hub and connected to the hub. The metal housing has an annular shape and is disposed in the hub. A magnetic ring is disposed at the inner side of the metal housing. The blades are disposed around the outer periphery of the hub. The blades are projected along an extension direction toward the shaft to define projection areas thereof, and the projection area of a top and a bottom of any one of the blades is partially overlapped with other two adjacent blades. A distance between an outer edge of each blade and a rotational axis of the fan decreases proximate the top of the blade and then increases towards the bottom of the blade.