Fluid reaction surfaces (i.e., impellers) inventions 04/06

20060088414 - Device to measure the axial displacement of the tip of the blades of a turbomachine for tests on the ground, and a process for using the device: The invention concerns a device for measuring the axial displacement of the blades of a turbomachine rotor, for tests on the ground. This device is characterised by the fact that it includes means for the taking and transmitting of images, and which is suitable for being installed opposite to the...

20060088415 - Deployable lighter-than-air wind rotor for intermittent wind loads: A deployable lighter-than-air wind rotor for intermittent wind loads consists of inflatable blades attached to a tether via a hub. The tether is fixed to the hub. Inflated and sent aloft during windy conditions, the rotor (blades and hub) twists the tether to transmit rotational force to the tether's power-take-off....

20060088416 - Gas turbine rotor blade: A rotor blade for a gas turbine, in particular a turbojet, the blade comprising an airfoil, a platform connecting the airfoil to a blade root and having at least one stiffener extending under the downstream portion of the platform, together with means for cooling the blade by a flow of...

20060088417 - Two-outlet electromechanical motor: The present invention relates to an electromechanical motor (M) provided with an actuator (A) having an outer casing (30-30′-30″) surrounding a stator (20-20′) possessing a coil (24). The rotor (10) is also disposed inside the stator (20-20′). The invention is remarkable in that the actuator has two distinct and independent...

20060088418 - Fan assembly and method: Fans according to some embodiments of the present invention include a spider, a central hub coupled to the spider, and two or more fan blades. One or more fan design features can be employed (alone or in combination) in the fans of the present invention, including the use of spider...

20060088419 - Rotor assembly retaining apparatus: A rotor stage (13, 14, 15, 17, 18, 19) of a gas turbine engine (10) comprises an annular retaining plate (38) capable of preventing axial movement of blades (30). The retaining plate (38) is secured to the disc (32) via a bayonet arrangement (49). A locking assembly (48) is provided...

20060088420 - Turbine blade tip squealer and rebuild method: A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge. The first...

20060088421 - Method for increasing operating efficiency of the rotor blade of an aerogenerator (variants): The invention relates to wind energy, in particular to wind energy devices converting wind energy into electrical, mechanical, hydraulic or other form of energy. The technical result consisting in enhancing the effectiveness of a WED by increasing the moment on the shaft of the rotor, is provided as a result...

20060083611 - Butt connection for hollow profile members: A butt connection of divided hollow profile members, which is suitable in particular for rotor blades of wind power installations, comprises a multiplicity of straps which are arranged along the join and which bridge over same and which are respectively fixed with their ends to one of the profile members...

20060083612 - Apparatus and methods for cleaning cooling slot surfaces on a rotor wheel of a gas turbine: The cleaning system includes a plurality of generally dovetail-shaped slot blocks having a slot along a radial inner side, an abrasive media or belt and a backing tube. Upon insertion of the blocks into the dovetail slots of a rotor wheel and aligning the block slots with the cooling slot,...

20060083614 - Airfoil with large fillet and micro-circuit cooling: A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which partially defines a fillet cavity therebehind, and cooling air is provided to the fillet cavity and is then routed to the outer surface by...

20060083613 - Impingement cooling of large fillet of an airfoil: A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which, together with an impingement rib, defines a fillet cavity therebetween, and cooling air is provided to flow through impingement holes in the impingement rib...

20060083615 - Pitch drive system for a wind turbine: A pitch drive system for a wind turbine is provided which comprises a regulation drive for regulating the pitch of a rotor blade of the wind turbine during normal operation, the regulation drive comprising at least one drive train, and an emergency drive for pitching the rotor blade in case...

20060083616 - Ornamental wind turbine apparatus: This three dimensional ornament is designed to be suspended in outdoor situations where it is free to rotate in the wind and thereby enhance the aesthetic qualities of the area in which it is deployed and to make the wind velocity visible. The ornament is a turbine type section with...

20060083617 - Helicopter vibration control system and rotary force generator for canceling vibrations: A helicopter rotating hub mounted vibration control system for a helicopter rotary wing hub having a periodic vibration while rotating at a helicopter operational rotation frequency. The helicopter rotating hub mounted vibration control system includes an annular ring rotary housing attachable to the helicopter rotary wing hub and rotating with...

20060083618 - Hydraulic or pneumatic machine with tilting blades: This invention refers to a hydraulic or pneumatic machine with tilting blades, running either as an engine on a fluid flow or on pressure fluid or as a pump or a compressor. The hydraulic or pneumatic machine on a fluid flow according to the invention consists of a cylindrical casing...

20060083619 - Dual counterweight balancing system: A system for balancing a rotatable gas turbine engine component. The system includes two balance rings that are coupled to the component by mating splines on the respective item. Each of the rings has a mass asymmetry that is indexable relative to the primary component to achieve the imbalance correction....

20060083620 - Cooling system for a seal for turbine vane shrouds: A seal for sealing a seal groove in a shroud of a turbine vane. The seal may include a cooling system configured to pass cooling fluids through a cooling fluid supply port in a shroud, through a cooling system in which the cooling fluids contact the shroud and the seal,...

20060083621 - Rotor of a turbo engine, e.g., a gas turbine rotor: A rotor of a turbo engine, e.g., a gas turbine rotor, has a rotor base member, the rotor base member having a groove extending in the circumferential direction of the rotor base member, and having a plurality of rotor blades, each rotor blade having a blade, a blade root and...

20060078430 - Ram air turbine over-speed protection using redundant yoke plate linear bearings: An improved ram air turbine for generating emergency aeronautical supplemental power with a plurality of concentric or nested linear bearings for supporting a speed governor yoke plate on a speed governor shaft comprising a movable sleeve that supports the yoke plate and rides on the governor shaft....

20060078431 - Apparatus and method for mounting a ceiling fixture: An apparatus and method for mounting a fixture to a ceiling according to which a tubular retainer extends in an opening of an arm and a fastener extends through the retainer and is retained by the retainer. The fastener is adapted to engage a device at the ceiling to mount...

20060078432 - Coating system and method for vibrational damping of gas turbine engine airfoils: A coating system and coating method for damping vibration in an airfoil of a rotating component of a turbomachine. The coating system includes a metallic coating on a surface of the airfoil, and a ceramic coating overlying the metallic coating. The metallic coating contains metallic particles dispersed in a matrix...

20060073013 - Application of abnormal event detection technology to fluidized catalytic cracking unit: The present invention is a method for detecting an abnormal event for process units of a Fluidized Catalytic Cracking Unit. The method compares the operation of the process units to a statistical and engineering models. The statistical models are developed by principle components analysis of the normal operation for these...

20060073014 - Air foil shape for a compressor blade: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S-16S, 1R-17R, and IGV. Wherein X and Y are distances in inches which, when...

20060073015 - Gas turbine airfoil film cooling hole: A gas turbine airfoil (1) with a pressure sidewall and a suction sidewall (6) comprises several internal cooling passages, through which cooling air flows, and several film cooling holes (7) that extend from the internal cooling passages to the outer surface (11) of the suction sidewall (6). According to the...

20060073016 - Gas turbine airfoil leading edge cooling construction: A gas turbine airfoil with a pressure sidewall (6) and a suction sidewall (7) extends from a root (2) to a tip (3) and from a leading edge (4) to a trailing edge (5). It comprises several film cooling holes with exit ports (8). The film cooling holes have a...

20060073017 - Stepped outlet turbine airfoil: A turbine airfoil includes an internal cooling circuit between opposite pressure and suction sidewalls. The pressure sidewall includes a row of outlet slots for the circuit separated by converging partitions. Each slot includes an inlet, throat, and diverging outlet. Each of the partitions includes a step in a converging sidewall...

20060073018 - Fan: A fan assembly has a central metallic element and a polymeric fan. The polymeric fan has a hub carrying the central metallic element and has a plurality of blades extending from the hub. The central metallic element has a central longitudinal aperture and a lateral surface. The central metallic element...

20060073019 - Axial-flow thermal turbomachine: The invention relates to an axial-flow thermal turbomachine having a metallic rotor (1), in which rotor blades (3) made of an intermetallic compound are mounted in a circumferential groove to form a row of blades. The invention is characterized in that at least two rotor blades (3′) which are at...

20060073020 - Spring clamping clip: The use of spring clamping clips (1) between two adjacent guide vane shafts (21, 22) leads to a defined force on the bearing points of the guide vane in the guide bush. The seating force, resulting from the clamping force and the flow-related lift/drift forces, of the guide vane in...

20060073021 - Remotely accessible locking system for turbine blades: Embodiments of the invention relate to an axial locking system for a row of blades in a turbine engine. While achieving the desired axial restraint, the system is configured to allow remote manipulation of the locking system. For example, a locking system provided on the upstream side of a row...

20060073022 - Frequency tailored thickness blade for a turbomachine wheel: A method is provided for determining a blade topology that reduces the effects of vibratory stress on a turbomachine blade having a plurality of discrete locations, wherein each discrete location has a thickness. The method includes the steps of creating a computational model of the blade, using the computational model...