Abstract: A rotor-wing assembly includes a motor, a propeller, and a connection assembly connecting the propeller to the motor. The motor includes a rotating portion. The connection assembly includes a locking member and a reinforcing member arranged between the propeller and the motor. The locking member locks the propeller to the rotating portion. A first end of the reinforcing member is mounted at the rotating portion. A second end of the reinforcing member opposite to the first end is engaged with the locking member, to reinforce the locking member to lock the propeller to the rotating portion.

Abstract: An unmanned aerial comprises: a motor and a propeller assembly connected to the motor comprising: a first structure fixed to the motor, having a cylindrical wall defining an inner space, with a helical slit formed through the cylindrical wall; a second structure comprising a cylinder portion, a part of which is rotatably positioned in the inner space, and at least one protruding portion protruding from the outer surface of the cylinder portion to the outside of the cylindrical wall through the helical slit; and a propeller comprising a cylindrical hub engaging with the cylinder portion of the first structure, rotating blades extending from the cylindrical hub, and at least one rib extending from the cylindrical hub toward the motor, the propeller being configured such that at least a part of the rib detachably engages with the first structure by the at least one protruding portion of the second structure.

Abstract: Systems and methods for blade attachment are proved. The systems and methods include an aircraft system having a rotor hub including a blade connector and a composite blade including a lug fitting assembly. The lug fitting assembly includes a fitting core including a lug fitting aperture, a lug bushing coupled within the lug fitting aperture, and an outer fitting substantially surrounding the fitting core.

Abstract: A Ceramic Matrix Composite (CMC) platform for an airfoil of a gas turbine engine includes a CMC platform segment which at least partially defines an airfoil profile.

Abstract: A propeller blade retention system and method of manufacture are disclosed. Because of the design, a truly integral hub is able to house a set of variable pitch blades. Each hub socket establishes a substantially cylindrical interface with its respective blade, making the blade slidably receivable for installation. Each blade is allowed axial rotation, and held inside the socket by a set of angular contact bearings. A snap ring locks the blade against coming back out of the socket. An O-ring is provided in the interface to create a fluid seal. The hub alone accomplishes all of the required load-bearing and weather-seal functions.

Abstract: Anti-ovalization tool for introduction into a wind turbine blade root comprising two or more rigid bodies connected to one another along their side edges with distances in between them and together forming a substantially cylindrical body, wherein the distances between the rigid bodies are adjustable. The invention is further related to the method of reducing ovalization of a wind turbine blade root and to the use of a tool comprising two or more rigid bodies as an anti-ovalization tool.

Abstract: A rotor blade assembly is disclosed herein. The rotor blade assembly includes a composite blade portion extending a length from a root to a tip. A leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root. The rotor blade assembly also includes a base portion fixed to the composite blade portion proximate to the root. The rotor blade assembly also includes a sheath extending around the composite blade portion. The sheath is positioned along the length adjacent to the base portion and between the root and the end point of the leading edge.

Abstract: A method for reducing bearing stress in a composite structure is disclosed. A composite structure comprises at least one coupling hole for coupling to the composite structure, and at least one bushing structure is coupled to the at least one coupling hole. A metal bushing retainer structure is coupled to the at least one bushing structure and the composite structure.

Abstract: A method of assembling a blade extension assembly for use with a wind turbine. The method includes removing a tip end of a tip portion of a rotor blade and coupling a tip wall to the tip portion. The tip wall extends between a first sidewall and a second sidewall and includes a plurality of slots defined therein. A blade extension assembly is coupled to the tip portion.

Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has an end portion extending between a reference section and a radially outer end of the blade with respect to a rotation axis of the blade; the rotation axis is outside the blade and crosswise with respect to the longitudinal axis; the length of the chord at the end portion decreases from the reference section to the radially outer end; and the leading and trailing edges are joined at the radially outer end.

Abstract: A blade wheel consisting of sheet metal for use in motor vehicle refrigerant pumps has blades that are cut out of a disk and pitched and base disk segments that lie adjacent to the blades and remain between the latter. The blade wheel is formed by at least two different blade wheel elements which are provided with cut out, pitched blades, are interconnected in a fixed manner and are arranged so that their respective base disk segments are offset in relation to one another, forming a gap therebetween, the elements thus forming a common bottom disk. A hub sleeve is provided in the center of one of these blade wheel elements (the hub disk), and the center of the other blade wheel element or elements (the bore disk or disks) is provided with a hub sleeve receiving bore, which can be pushed onto the casing of the hub sleeve.

Abstract: A rotor blade for a wind turbine is disclosed. The rotor blade includes a flange section configured to connect the rotor blade to a rotor hub; and an airfoil section extending outward from the flange section. The flange section is comprised of a carbon reinforced polymer.

Abstract: A vane assembly for a gas turbine engine comprising an axial loading element disposed between a mounting element of the vane ring and a cooperating portion of the supporting structure, such as to generate a load force therebetween in an axial direction. The axial load force limits unwanted relative movement between the vane ring and the supporting structure during operation of the gas turbine engine.

Abstract: A fan includes a frame, a stator and a rotor. The stator is disposed in the frame, and the rotor is disposed in the frame and coupled with the stator. The rotor includes a connecting element, an impeller and a shaft. The connecting element has a flange. The impeller is disposed on a periphery of the connecting element. The flange is embedded with the impeller. One end of the shaft is connected to the connecting element and the impeller is rotated when the shaft rotates.

Abstract: A fan and a rotor structure thereof. The rotor structure has a case, an upper linking structure, a lower structure, and a rotating shaft. The case has an opening at the axle center. The upper linking structure has a fixing portion and a threaded portion. The minimum radius of the fixing portion is longer than the radius of the opening. The threaded portion is disposed in the opening. The lower linking structure has a thread corresponding to the threaded portion. The upper linking structure and the lower linking structure is screwed together to secure the case therebetween. The rotating shaft is fixed in the upper linking structure or the lower linking structure.

Abstract: A boot provides for removable attachment to a tail rotor assembly to flexibly protect the interior of the tail rotor blade assemblies. The boot includes a first fastener strip mounted adjacent a first boot edge and a second fastener strip mounted adjacent a second boot edge. The first and second fastener strips are “hook and loop” material to removably attach the edges which permits relatively uncomplicated installation and removal of the boot.

Abstract: A bearing structure for the blade of cooling fan, comprises a hollow cylindrical body and an outward extended seat whose diameter is larger than the body. The seat has a recess at the bottom. The body forms a long cavity and upward flange. This bearing is placed in the hub of the cooling fan; the blade rotor shaft is inserted into the cavity of the bearing, and the flange of the body works as a C-clamp buckling the round groove on the blade rotor shaft to confine the motion of the rotor shaft. The bearing design renders easy fabrication and assembly, good dust shield to keep the dust off the rotor and reduce the rotary friction and resistance to the minimum. In addition, the magnetic force is limited for the self-adjustment, which further alleviates the frictional resistance sop the service life the cooling fan is extended longer.

Abstract: This device for mounting a propeller blade in a hub, of the type in which a blade base is mounted in rotation in a hub housing by means of at least two bearings and where a preloading device permitting axially preloading the two bearings comprises a holding ring mounted between one of the two bearings and hub so as to allow an axial displacement of ring relative to hub, in that holding ring is mounted rotatingly between bearing and hub by means of rolling elements and helical tracks arranged to drive an axial displacement of ring during rotation of this ring, means being provided to cause ring to rotate according to a predefined law.

Abstract: An advertising ceiling fan includes a motor seat, a plurality of blade support brackets, and a plurality of support tubes. Each of the blade support brackets is secured with a sleeve having two through holes. Each of the support tubes has one end formed with two positioning holes each aligning with a respective through hole. Each of the support tubes includes two elastic members each having a first end formed with a protruding stub extended through a respective one of the two positioning holes and a respective one of the two through holes. Thus, the support tube is mounted on and detached from the respective blade support bracket easily and conveniently, thereby facilitating quick replacement of the advertising paper.

Abstract: A boat propeller comprises a hub formed of a front cylindrical member and a rear cylindrical member. The hub is provided in the joining place with a plurality of receiving cavities which are arranged equiangularly and circularly. Each cavity is provided removably with an angle setting member which is joined with the hub. A plurality of blades are joined with the outer periphery of the hub such that the inner ends of the blades are inserted into the cavities and are located by the angle setting members. Under the circumstance that the shapes of the hub and the blades remain unchanged, the blade pitch in relation to the hub can be changed by the angle setting members of various shapes.

Abstract: A bearing arrangement, for example, for a variable pitch propeller, has a fluid operated actuator (42, 34, 40) for causing relative movement between bearing surfaces of races (12, 32) so as to preload bearings (30) held there between. Mechanical locking means (34, 36, 38) is provided to maintain the bearings under preload when the fluid pressure is released from the actuator.

Abstract: A fan blade mounting system for large air-moving fans includes a radially extending hub strut, a blade root member pivotally coupled to an end of the hub strut for receiving a blade skin, and a tube end located between the blade root member and the hub strut. A pair of resilient mounts are utilized in the blade root member to effectively pivotally couple the blades to the hub, thus relieving most of the vertical bending moment transferred to the hub and eliminating critical frequencies associated with the fan. The hub strut is connected to the hub of the fan by a stud having right- and left-handed threads and a wall thickness adjacent to the threads sufficient for distributing the stresses substantially uniformly on the threads, thereby improving fatigue resistance. The resilient mounts comprise a metal core and metal sleeve with a resilient elastomeric layer between the core and sleeve. The sleeves are connected to the blade root member and the cores of the two mounts are clamped to the tube end.

Abstract: A propeller blade retention assembly for use with a propeller having a hub rotatable about a propeller axis, is disclosed. The assembly includes a blade receiver for mounting the blade to the hub and an internal surface of a hub arm for interfacing the receiver with the hub. The receiver is positioned in the hub arm and is non-integral with the blade and the hub arm internal surface. A retention mechanism is used for retaining the blade receiver to the hub arm while allowing relative rotatable motion therebetween. A preload device is provided for preloading the retention mechanism prior to centrifugal loading during propeller blade operation. The blade is separable from the blade receiver without disturbing the operability of the retention mechanism.

Abstract: A structure and method for transferring load, particularly bending load, from a blade to a blade hub, such as for use in a wind turbine device, is provided. In one embodiment, the structure includes two or more spaced-apart annular rings, respectively contacting the inner surface of a blade root end, and the outer surface of a hub spindle, with a web extending therebetween.

Abstract: A marine propeller includes a series of releasably affixed blades which allow pitch adjustment. The blades are each secured to different blade disks which are positioned in hub wells and held by positioning pins. The method describes how the blades, which are each attached to blade disks at preselected positions can be released, rotated and reaffixed. The disk can then be rotated in the opposite direction on the hub in a smaller increment, to provide more or less pitch as needed.

Abstract: A propeller comprises a hub (1) rotatable about a propeller axis and formed with a hub barrel (1) with a central hub axis that extends radially of the propeller axis, a blade (9) having a support assembly (3) at its inner end received within the hub barrel (1) and including at least one bearing (11,16) that supports the blade (9) for rotation about the hub axis, a locking recess (7,25,33) formed at least in part in the support assembly (3) and at least in part in the hub barrel (1) and a key element (26) located within the locking recess (7,25,33) to restrain radial outwards movement of the blade (9) along the hub axis. The key element (26) is insertable into and retractable from the locking recess (7,25,33) while the inner end of the blade (9) is assembled in the hub barrel (1). The locking recess (7,25,33) extends circumferentially within the hub barrel (1), and the key element (26) is flexible to follow the recess when inserted.

Abstract: A propeller blade cuff having a root end and a first annular flange at the root end, and a wind turbine generator hub having a second annular flange to be attached to the first flange comprising a clamp ring having multiple sections, the sections having flange-receiving and clamping grooves, each extending part way about the annular flanges; and fastener structure interconnecting the ring sections to exert adjustable tension for adjustably retaining the flanges in the grooves.

Abstract: To ensure retentioin of the blade tongue 16 of a prop-fan blade 10 within a receiving slot 24 in the disc arm 20 of the fan hub 4 even under the high centrifugal forces exerted on the blade 10 while rotating at high rpm, at least one pair of retaining pins 30 and 40 are provided. First seating grooves 32 and 42, respectively, are provided on opposite faces 15 and 17 of the blade tongue 16 and holes 34 and 44 are drilled transversely through the disc arm 20 so as to form corresponding second seating grooves 36 and 46, respectively, on opposite side walls 26 and 28 of the slot 24. The first and second seating grooves are arranged opposite of and parallel to each other such that each pair of grooves 32 and 36 form a retention channel between the first face 15 of the tongue 16 and the opposed side wall 26 of the slot 24 and aligned with the holes 34 and 44 for receiving the retaining pins 30 and 40 thereby locking the blade tongue within the slot 24.

Abstract: In an arrangement for mounting a shrouded pivotable propfan blade at a rotor, the propfan blade is held in a dovetail mounting of a blade carrier and, by using a first securing device is fixed with respect to axial movements of the propfan blade. The blade carrier is secured with respect to radial movements by means of a second securing device, which is accessible from the outside. This permits a simple and fast mounting and demounting of the propfan blades.

Abstract: The present invention relates to fixed-angle keying pieces for blades of axial fans each having a U-shaped cross section, the internal surface of which perfectly fits the profile of the blade while the external surface of the same has a plane side face which rests on a supporting plate, the keying piece being obtained as a continuous extruded section which is subsequently cut to a desired size.

Abstract: A fiber reinforced thermoplastic propeller is attached to a metallic rotor by an integral shank at the base of the propeller. By virtue of the manufacture of the shank and the propeller as an integral construction, improved transmission of centrifugal forces especially where the propeller and hub have greatly different cross-sections can be effected while simultaneously reducing weight. Attachment of the shank to the hub is made through a connection by which pre-stress can be applied to the propeller to assist in resistance of lateral impact force.

Abstract: In an impeller for use in an axial flow fan and having blades (5) which are adjustable during operation of the fan, each blade (5) is, through a blade shaft (7) connected to a hub (1) designed as a compact unit.The blade shaft (7) and an axial thrust bearing device (9) on which the blade (5) is journalled in such a manner that it can, through a control mechanism, be pivoted about its axis for controlling the blade angle, are retained axially in a bearing housing (8) screwed into a threaded bore (18) in the periphery of the hub (1).For adjusting the radial distance between the periphery of the hub (1) and the blade tip the thrust bearing device (9) is held against a closed end of the bearing housing (8) by a spring (43) and a nut (14) screwed onto a threaded portion (15) of the blade shaft (7) and lockable in an arbitrary position by a lock screw (16).

Abstract: Axial flow fan blade roots (1) are rotatably journalled to blade shafts (4) by bayonet plug and socket couplings. The socket recesses (30, 31) provide an axial play for the plug cam portions (28, 29). Screws (34, 35) extending through the blade root (1) have shoulders (43) abutting spring members arranged between the root and the shaft to thus bias the blade outwardly and establish frictional engagement between the bayonet coupling cam portions and recesses.

Abstract: There is disclosed a blade and mounting means particularly useful in the construction of axial flow compressors where blades of airfoil configuration are mounted in blade carriers so as to be removable and replaceable by manipulation of nuts on adapters arranged radially, which adapters include tubular bodies having frusto-conical heads mounted in mating sockets in the carrier or carriers, the blades have portions positioned in the adapters and tightening of the nuts causes the adapters to grip the blades and fix them in adjusted positions, a seal to reduce losses being formed on the blades for use in those cases where such losses may be critical.