Abstract: Surgical methods and related medical devices for treating glaucoma are disclosed. The method comprises trabecular bypass surgery, which involve bypassing diseased trabecular meshwork with the use of a seton implant. The seton implant is used to prevent a healing process known as filling in, which has a tendency to close surgically created openings in the trabecular meshwork. The surgical method and novel implant are addressed to the trabecular meshwork, which is a major site of resistance to outflow in glaucoma. In addition to bypassing the diseased trabecular meshwork at the level of the trabecular meshwork, existing outflow pathways are also used or restored. The seton implant is positioned through the trabecular meshwork so that an inlet end of the seton implant is exposed to the anterior chamber of the eye and an outlet end is positioned into fluid collection channels at about an exterior surface of the trabecular meshwork or up to the level of aqueous veins.

Abstract: A centrifugal ventilator fan, which has improved fan performance and lower noise. A first outlet angle, on an upstream end of the fan, is less than a second outlet angle. Additionally, the first outlet angle is equal to zero degrees or greater and five degrees or less, while the second outlet angle is equal to thirty degrees or greater and forty five degrees or less. Furthermore, a first inlet angle, on an upstream end, is greater than a second inlet angle, on the opposite end. The first inlet angle is equal to sixty-five degrees or greater and ninety degrees or less, and the second inlet angle is equal to fifty-five degrees or more and seventy-five degrees or less.

Abstract: A method enables a variable vane assembly for a gas turbine engine to be coupled to an engine casing. The variable vane assembly includes a bushing assembly and at least one variable vane that includes a platform and a vane stem. The method comprises coupling a first bushing to the engine casing in a press fit, coupling a second bushing to the variable vane, and coupling the variable vane to the engine casing such that at least a portion of the first bushing is between the engine casing and the second bushing, and such that at least a portion of the second bushing is between the first bushing and the vane stem.

Abstract: A multi-bladed tail rotor assembly is disclosed that provides higher aerodynamic performance, damage tolerant design with 10,000-hour life expectancy, and which requires low maintenance through the use of composites and elastomerics. The tail rotor hub assembly includes two stacked yoke assemblies having multi-bladed teetering rotors, each mounted on a single drive mast. Each yoke assembly includes a yoke hub having a transverse bore therethrough, a bearing assembly disposed within the bore, and retention means for aligning and securing the bearing assembly within the bore. Each bearing assembly includes a trunnion portion having trunnion arms that extend outwardly from a trunnion body portion, and an elastomeric bearing disposed about each trunnion arm. The tail rotor assembly utilizes a composite twist strap flexure to accommodate collective pitch control integral with each rotor blade.

Abstract: A guide vane is adapted to be mounted in an annular fluid-conveying duct of a gas turbine engine, and has an aerofoil part which extends radially across the duct when the guide vane is thus-mounted. On a transverse cross-section relative to the direction of intended fluid flow across the aerofoil part, at least a portion of the aerofoil part is S-shaped.

Abstract: The invention relates to a device for immobilizing blades in the peripheral slot of a turbomachine disk. Said blades comprise roots of the hammer head type adapted to be introduced into said slot through a loading window and held in said slot by collaboration of shape with the sidewalls thereof. Said immobilizing device is adapted to be introduced into said slot through said loading window and comprises a locking element arranged in a space separating two adjacent blade roots. Said locking element is adapted to be raised up into a lock housing formed in the sidewalls of said slot under the action of a radial manipulating screw the head of which rests against the bottom of the slot, a radial clearance being provided between the bottom of the slot and the underside of the blade roots, and said screw head being restrained in a radially outward direction by said two adjacent blade roots.

Abstract: A wind turbine with an array of rotors arranged at various heights. Each rotor is optimized for the height at which it is located. Optimization of each rotor could include selection of rated power, solidity, tip speed, blade twist, blade taper, or rotor diameter. Each rotor can also be operated in a manner that is optimized for the wind speed it experiences. Optimized operation parameters could include blade pitch angle or rotor speed.

Abstract: A centrifugal pump wherein a threaded ring is secured in its position by way of a pressure body which presses it against the axial abutment of a pump shaft and which is screwed axially to the end of the pump shaft. The threaded ring is seated loosely on the pump shaft and by a thread which is provided in a front hub region of the pump impeller and into which the thread of the threaded ring is screwed.

Abstract: A compressor casing structure in the region of a rotor blade ring through which there is an axial flow, having a multiplicity of axial grooves which extend from a first radial plane upstream of the blade-tip inlet edges into a second radial plane between the blade-tip inlet edges and the blade-tip outlet edges and have groove cross sections with parallel side walls. The center axes of the groove cross sections have, at the upstream groove ends, from the opening to the groove base, an angle of inclination with a circumferential component counter to the direction of movement of the blade. The center axes of the groove cross sections have, at the downstream groove ends, an angle of inclination with a circumferential component in the direction of movement of the blade.

Abstract: A turbine nozzle includes a row of vanes in corresponding segmented outer and inner bands. The inner band of each segment includes a retention flange. A nozzle support includes forward and aft flanges defining a retention slot receiving the retention flange. The retention flange includes a radial lug trapped axially in the retention slot, and a tangential lug at an opposite circumferential end disposed on the forward flange. The aft flange includes an outer hinge, and the retention flange further includes an inner hinge for cradle mounting the retention flange in the nozzle support.

Abstract: A compressor in which an electric motor and a compressing mechanism are accommodated in a case, a main shaft and an auxiliary shaft of a rotating shaft of the motor are supported by a radial plain bearing and a rolling bearing with a predetermined clearance given to the rotating shaft in an axial direction, a flange portion that contacts with a main-shaft receiving member of the radial plain bearing to align the rotating shaft with the compressing mechanism is provided on the main shaft, and preload toward the side of the rolling bearing is given to the rotating shaft. In this constitution, a prevention member for preventing contact and/or collision of the rotating shaft with the main-shaft receiving member is provided between opposing faces of the flange portion and the main-shaft receiving member.

Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (62) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (62) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine (10) but has unimpaired stiffness and penetration resistance.

Abstract: An improved connection of blades (12) on a rotor disc (22) of a gas turbine, of the type in which a root (10) of each blade (12) is inserted in a seat (20) of the disc (22) which is complementary to the blade, wherein the root (10) is in the shape of an overturned isosceles triangle, with the two sides which converge at the base each having a grooved profile such as to form a series of teeth (14) and with a lower end (16) of the root (10) which is formed by the joined connection of the two lower teeth (14) of the two sides of the root (10), the teeth (14) of the root (10) corresponding to grooves (24) in the seat (20) and the lower end (16) of the root (10) corresponding to an end groove (26) in the seat (20).

Abstract: The present utility model relates to an improved mounting mechanism for ceiling fan outer casing. The ceiling fan outer casing is fixed on the support of the motor through mounting members, the mounting members comprising a pair of convex fixing members and a pair of concave fixing members corresponding to and matched in use with said convex fixing members, on each of said convex fixing members is provided a pair of protruding elements transversely spaced and arranged in parallel, the upper end of said two protruding elements is each provided at one outward side with a hook respectively, on each of said concave fixing members is provided a receiving groove which has one end opening and is inverted “Y” in shape receiving said convex fixing members, the two opposite sides of one end of said receiving groove are provided respectively with recessed portions matched with said hooks.

Abstract: Ceiling fan energy consumption efficiency is enhanced with fan blades that have an angle attack that decreases from root end to tip end at higher rates of decrease nearer their tip ends than at their root ends.

Abstract: The invention comprises a metering plate which is assembled to an impingement insert for use in the nozzle of a gas turbine. The metering plate can have one or more metering holes and is used to balance the cooling flow within the nozzle. A metering plate with multiple holes reduces static pressure variations which result from the cooling airflow through the metering plate. The metering plate can be assembled to the insert before or after the insert is inserted into the nozzle.

Abstract: A compressor in a turbocharger has a compressor impeller in an inflow passage and an outflow region downstream of the compressor-impeller outlet edge. The outflow region is assigned a connecting passage, a stabilizing chamber and an outflow passage, the connecting passage being arranged with a lateral offset with respect to a longitudinal center axis of the stabilizing chamber.

Abstract: A turbine blade arrangement includes rotating blades respectively provided with a leg which can be respectively inserted into a groove on the outer circumference of a turbine disk in a radial, positive fit and which are respectively provided with a profiled section which has a lateral platform located in an end area on the side of the disk. At least one part of the platform is joined to the turbine disk by way of a retaining element which is independent from the leg of the blades in order to extend the profiled sections of the rotating blades.

Abstract: A wind or water flow energy converter comprising a wind or water flow actuated rotor assembly. The rotor comprises a plurality of blades, wherein the blades of are variable in length to provide a variable diameter rotor. The rotor diameter is controlled to fully extend the rotor at low flow velocity and to retract the rotor as flow velocity increases such that the loads delivered by or exerted upon the rotor do not exceed set limits.

Abstract: The second stage nozzle has an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X and Y values are in inches and define airfoil profile sections at each distance Z and Z is a non-dimensional value from 0 to 1 convertible to Z distances in inches by multiplying the Z values of Table I by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The X and Y distances may be scalable to provide a scaled-up or scaled-down airfoil for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.100 inches.