Abstract: A sealing element (30) for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure (38) comprising a plurality of radially inwardly projecting walls (40). The walls may be abradable and may define cells (44) for receiving an abradable sealing material.

Abstract: A ceiling fan includes a rotatable motor seat, and multiple blade racks. The motor seat is provided with multiple retaining studs and multiple locking screws. Each of the multiple blade racks includes an arcuate mounting plate secured on the motor seat. The mounting plate of each of the multiple blade racks has a first end provided with a retaining hook rested on a respective one of the multiple retaining studs, and has a second end provided with a locking hook locked on a respective one of the multiple locking screws. Thus, the blade racks may be assembled and disassembled easily, conveniently and rapidly.

Abstract: A rotor blade arrangement includes a rotor blade with a hollow blade chamber therein, and a flap module removably arranged and secured in the blade chamber. The flap module includes a module housing received in the blade chamber, an actuator arranged in the housing, a flap pivotably arranged at an edge of the housing, and a power transmission linkage connecting the actuator to the flap. The module housing is inserted through an opening into the blade chamber, so that the flap protrudes and forms a continuation of the aerodynamic contour of the blade. The flap may be a trailing edge flap at the trailing edge or a leading edge nose flap at the leading edge of the blade. The flap module does not change the center of gravity of the blade. The entire flap module can be easily removed from the blade for adjustment, inspection, maintenance, repair or replacement.

Abstract: A gas friction pump, including a housing having a suction opening, a gas outlet opening, and a plurality of rotatable and stationary components arranged in the housing and having a pump-active structure for pumping gases and maintaining a pressure ratio, and an additional gas inlet formed as a longitudinal opening extending, in a longitudinal direction thereof, over a portion of an outer edge of a rotatable component.

Abstract: An impeller for a fuel pump for supplying fuel to an automotive engine from a fuel tank includes an impeller body with a plurality of vanes having a front side and a back side extending radially outward therefrom. A plurality of partitions are interposed between the vanes and extend a radially shorter distance than the vanes. The partitions and the vanes define a plurality of vane grooves. Each of the vanes includes a root which is adjacent the impeller body and a distal end. The vanes have a thickness which varies such that the vanes are thickest at the root and gradually become thinner as the vanes extend outward to the distal end. A ring portion is fitted around the impeller and connected to the distal ends of the vanes such that a plurality of extending fuel flow passages are formed between the vanes, the partitions, and the ring portion.

Abstract: A thoracentesis device having a hypersensitive dual spring indication mechanism for visually alerting the user of any contact to internal body organs by the blunt tip distal end of the device once the it as been inserted inside a patient's body. The thoracentesis device includes a handle and an outer needle fixedly attached thereto having a sharp distal end for penetrating a chest cavity wall and a conduit that is in communication with a cavity defined inside the handle. A dual spring-loaded inner needle is slidably disposed inside the conduit of the outer needle with the inner needle being operably is associated with a large spring that imparts a sufficient distal spring force to fully extend the blunt tip distal end of the inner needle beyond the sharp distal end of the outer needle and a small spring for imparting a smaller spring force thereto.

Abstract: A pump assembly 1, 33, 200 adapted for continuous flow pumping of blood. In a particular form the pump 1, 200 is a centrifugal pump wherein the impeller 100, 204 is entirely sealed within the pump housing 2, 201 and is exclusively hydrodynamically suspended therein as the impeller rotates within the fluid 105 urged by electromagnetic means external to the pump cavity 106, 203. Hydrodynamic suspension is assisted by the impeller 100, 204 having deformities therein such as blades 8 with surfaces tapered from the leading edges 102, 223 to the trailing edges 103, 224 of bottom and top edges 221, 222 thereof.

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 control device for use in unmanned model aircraft for a constant speed propeller is disclosed. The device comprises a propulsion engine coupled to the propeller. The rotational speed of the propulsion engine is regulated through an automatic change of the angle of attack of the propeller and a manual or automatic adjustment of the throttle. It also comprises an electric servomotor device, a power transmission and a controller. The servomotor device is positively coupled to the propeller via the power transmission. The controller controls the servomotor device. The variable angle of attack of the propeller is adjusted by the power transmission from the servomotor device and the propulsion engine, manually by an operator or automatically by the controller.

Abstract: A seal assembly is provided for use in a hydraulic actuator of the type including a cylinder, a piston movably disposed in the cylinder, and a piston rod connected to the piston and extending from an end of the cylinder. The seal assembly comprises a seal member formed of a material impervious to hydraulic fluid and having an inner edge and an outer peripheral edge. The inner edge of the seal member defines a central opening which is larger than the outside diameter of the piston rod for receiving the rod. The outer edges of the seal member are attached adjacent the end of the cylinder so that the inner edge of the seal member is radially spaced from the outside diameter of the piston rod and the seal member forms a fluid impervious wall for preventing hydraulic fluid from contacting the elastomeric portion of the bearing assembly.

Abstract: A manually guided suction device or blower is provided that has a housing in which is formed a spiral blower path in which is disposed an impeller that is rotatably driven by a drive motor. The spiral blower path has an air-conveying air inlet and an air-withdrawing outlet. A connector is provided for the detachable connection of an air-conveying connection conduit, whereby when the connection conduit is mounted it overlaps with the connector, which is secured to the housing, over a prescribed axial length. To achieve a mechanically secure connection, an annular sealing element is held in a groove in a surface of the connector or connection conduit in the overlap region, wherein over the entire circumference thereof, the sealing element projects beyond such surface.

Abstract: The invention relates to a guide vane (17) for a turbomachine (1), in particular a gas turbine guide vane, in which the platform (48) has a separating region (50), which is embodied as a separate component. This has, in particular, advantages with respect to the simplification of cast blade/vane (17) in terms of manufacturing technology, with respect to the variability of a material selection, the quality of a protective coating to be applied and efficient cooling.

Abstract: A turbine apparatus for providing support peripherally for a turbine rotor having either a vertical or horizontal axis of rotation. The present invention includes a plurality of blades distributed about the rotor, the blades across their width being shaped and angularly pitched to the flow of air therebetween to effect rotation of the rotor and the blades defining a peripheral boundary of the rotor. A support system for the blades includes a support ring concentric with the turbine axis of rotation and adjacent to the peripheral boundary of the rotor. A support mechanism for each blade includes a support assembly mounted in rotational supporting association with the support ring so that the mass and forces generated by each blade is substantially supported at the peripheral boundary of the rotor by the support ring.

Abstract: A blade assembly for a windmill includes an output shaft with a first cross-shaft and a second cross-shaft operatively mounted relative to the output shaft. The first cross-shaft and the second cross-shaft include a first end and a distal end. A first blade is mounted on the first end of the first cross-shaft and the first cross-shaft is rotated by the first blade to impart rotation to the output shaft. A second blade is mounted on the distal end of the first cross-shaft and the first cross-shaft is rotated by the second blade to impart rotation to the output shaft. Stops are positioned on the first cross-shaft for limiting the rotation of the first cross-shaft relative to the output shaft. A third blade is mounted on the first end of the second cross-shaft and the second cross-shaft is rotated by the third blade to impart rotation to the output shaft.

Abstract: An air cleaner includes a centrifugal fan runner equipped with backward blades, a core plate connected to an axis of a motor; and a side plate being opposing the core plate. The backward blades, being inclined in an anti-rotational direction thereof, are provided at a distance in a circumferential direction, and the backward blades are bent in a position at distance of about ½-1/(3.5) of a length of the blade from an outer periphery thereof, so that an outlet portion thereof is inclined into a direction of rotation of the blade. An outlet angle of the outlet portion with respect to a tangential direction on an outer periphery of said side plate lies from about 40 degree to about 60 degree.

Abstract: A balloon for a balloon catheter and a method of manufacture The method entails providing a polymeric tubular member having an inner lumen and a longitudinal axis. An incompressible fluid is introduced into the inner lumen at a predetermined volumetric flow rate, expanding the polymeric tubular member to a desired outer diameter. The volumetric flow rate of fluid may be predetermined to not over-inflate the balloon. The balloon is blown slower because no initial pressure need be exceeded, so higher blow up ratios may be achieved without sacrificing any strength of the balloon. The balloons embodying features of the invention have thinner walls, yet maintain the same physical and mechanical properties of a thicker walled balloon manufactured in today's methods. Therefore, the process of the invention will lead to lower profile balloon catheters for balloon catheters with the same outer diameter balloon on them.

Abstract: A molecular vacuum pump (1) includes a stator unit (9) which has a stator blade package including one or more rows of stator blades (42), and a rotor unit (8) which has rotor blade package including one or more rows of rotor blades (41). The rotor blades (41) and the state blade (42) intermesh with each other in the functionally assembly state. The rotor blades 941) include slots (61) whose arrangement, depth and width are selected such that the stator unit (9) and the rotor unit (8) may be screwed together or unscrewed from one another. Alternatively, the stator blades (42) include slots (61) whose arrangement, depth and width are selected such that the stator unit (9) and the rotor unit (8) may be screwed together or unscrewed from one another.

Abstract: A blade assembly is provided for installation in a rotor wheel slot having a slot neck in communication with a slot base cavity having first and second slot flank walls and a slot floor. The blade assembly comprises a blade element having an airfoil portion and a base portion configured for insertion into the rotor wheel slot through the slot neck. The blade assembly also comprises at least one filler piece configured for insertion into the rotor wheel slot through the slot neck. The at least one filler piece is also configured for positioning intermediate the base portion and the first slot flank wall to secure the base portion within the rotor wheel slot.

Abstract: A method and apparatus carrying the method for sealing a radial gap between coaxial inner and outer rotating shafts of a gas turbine engine includes using a radial seal as a main seal to seal the gap for a normal engine operation condition, and using an axial seal as a back-up seal for a double seal of the gap. The radial seal provides a seal which meets relatively restrictive leakage requirements for the normal engine operation condition and the axial seal provides a back-up seal which meets less restrictive leakage requirements but is much more tolerant of radial displacement and vibration between the coaxial inner and outer rotating shafts. Thus, an engine operable condition is ensured under abnormal conditions, such as bird strikes, in which the coaxial relationship between the inner and outer rotating shafts are affected by unbalancing forces caused by the bird strike, thereby causing a failure of the radial seal.

Abstract: A transition duct with a thermally free aft frame for use in a gas turbine engine is disclosed. The transition duct includes an aft frame that is thermally free through the use of a plurality of retention lugs, bushings, and bulkhead assemblies. The aft frame is allowed to adjust from thermal changes as a result of relative sizing between the bushings and retention lugs of the aft frame. An additional feature of this invention is the use of radially extending ribs along the sidewalls of the aft frame, to form an interlocking sealing means with adjacent transition ducts to reduce the amount compressor air leakage into the turbine inlet.