Abstract: A method for modifying a multistage compressor (101) involves exchanging the rotor blades of the first compressor rotor blade row (LA1) for modified rotor blades which have an identical blade leaf profile (121) to the original rotor blades and the blade angle (B?11) of which is different from the blade angle (B?10) of the original rotor blades. Furthermore, the blades of at least one further blade row (LAN, LEN) arranged downstream of the second compressor stage are exchanged for modified blades which have an identical blade leaf profile (125, 126) to the original blades and the blade angle (B?N1, B?N1) of which is different from the blade angle (B?NO, B?NO) of the original blades. The method makes it possible to increase the mass flow of a compressor and essentially maintain the stability reserve against stall.

Abstract: Systems and methods are provided for cooling bearings or other objects. Such cooling may be accomplished by expanding a compressed gas in a cooling channel surrounding a bearing and allowing the expanded air to come into direct contact with the bearing. Expanding a compressed gas in local proximity of the bearing takes advantage of the Joule-Thompson expansion of gas, resulting in a substantial drop in gas temperature, thereby maximizing the cooling potential of the gas being directly applied to the bearing. Cooling bearings in this manner extends their operational life and enables them to operate at the desired speeds. A housing may be provided for receiving a compressed gas, expanding the compressed gas to a predetermined pressure, enabling the expanded gas to directly contact the bearing, and exhausting the expanded gas.

Abstract: A turbofan engine of the invention is provided with a fan first-stage moving blade for taking an air therein, and a spinner rotationally driving the fan first-stage moving blade, the spinner has a spiral blade extending spirally to an outer side in a radial direction, sucking the air from a front face of the spinner and supplying the air to the fan first-stage moving blade. Further, the fan first-stage moving blade and the spinner are integrally coupled, and the spiral blade and the fan first-stage moving blade are formed such that blade surfaces are smoothly connected.

Abstract: A vibration-isolating fixing mechanism for a fan frame. The mechanism, configured to couple the fan frame to first fastening portions of a casing, includes: coupling portions protrudingly disposed on two installation surfaces of the fan frame; positioning brackets each having second fastening portions and through-holes; resilient elements each circumferentially disposed between each coupling portion and each through-hole and extending to two through-hole-corresponding sides of each positioning bracket; and coupling elements coupled to the coupling portions respectively, positioned on one side of each resilient element facing away from the fan frame, and configured to position the positioning brackets and the fan frame relative to one another. Axial vibration isolation is achieved by insertion of the coupling portions into the through-holes circumferentially disposed with the resilient elements and by resilient contact between each resilient element and each coupling element.

Abstract: A multi-segment wind turbine blade comprises at least two blade segments. A first spar cap segment is attached to a first blade segment and a second spar cap segment is attached to a second blade segment. The first and second spar cap segments are configured to form a scarf joint. First and second spar cap brackets are attached in locations of the first and second spar cap segments, respectively, selected to facilitate alignment of the first and second spar cap segments at the scarf joint. At a field site, the first and second spar cap segments are bonded after fastening the first and second spar cap brackets.

Abstract: A cooling fan for rotating machine having a sufficient cooling performance, mass production performance and easiness in mounting is provided.

Abstract: A CMC wall (20F) may be attached to a metal wall (22F) by a plurality of bolts (28A, 28B, 28C) passing through respective holes (24A, 24B, 24C) in the CMC wall (20F) and holes in the metal wall (22F), clamping the walls (20F, 22F) together with a force that allows sliding thermal expansion but does not allow vibrational shifting. Distal ones of the holes (24A, 24B) in the CMC wall (20F) or in the metal wall (22F) are elongated toward a central one of the bolts (24C) or at alternate angles to guide differential thermal expansion (20T) of the CMC wall (20F) versus the metal wall (22F) between desired cold and hot geometries. A second CMC wall (20R) may be mounted similarly to a second metal wall (22R) by pins (39A, 39B, 39C) that allow expansion of the CMC component (201) in a direction normal to the walls (20F, 20R).

Abstract: The invention provides a fuel cell compressor system that comprises a motor, including a motor shaft driven by the motor; a drive housing at least partially surrounding the motor shaft; a first gear set driven by the motor shaft; a carrier torque tube driven by the first gear set; and an impeller. The impeller includes an impeller shaft driven by the second gear set, so that the impeller shaft is configured to rotate at a speed greater than motor speed. Embodiments of the invention may also be used with a multi-stage compressor that allows, for example, first and second impellers to rotate at different speeds. Embodiments of the invention may also include removal of a gear set driving the carrier torque tube or the impeller shaft, so that the impeller shaft speed is divided between one or more bearings supporting the carrier torque tube and one or more bearings supporting the impeller shaft.

Abstract: Device for converting kinetic energy contained in a fluid, into mechanical energy, coupled to an either gaseous or liquid fluid mass outlet secondary conduit, constituted by a fixed main conduit receptor of said fluid mass and a movable conduit coaxially attached to an axial flow rotor and associated to an outer supporting frame, including this assembly a flange abutting with said fixed conduit; both conduits are assembled by a fitting device comprising a lid, sealing washers, bearings and retaining ring acting on spacing sleeves and a locking nut; the movable conduit attached to the rotor rotates along its axis and coaxial to said fixed conduit without a major axial displacement; within said rotor it is lodged a hub and a deflector capable of directing the fluid's flow toward passages within the hollow blades and their corresponding exits at the end of each blade, constituting each one of said exit outlets an ejector means for the fluid, thereby achieving the rotational movement of the rotor on its axis; att

Abstract: An assembling member disposed on a heatsink fan in pairs for detachably disposing the heatsink fan on a fixed frame is provided. The assembling member includes a jointing part and an operating part. The jointing part matches with the fixed frame, and extends a plurality of fastening pins capable of being hooked at the assembly holes of the heatsink fan. The operating part is extended from one end of the jointing part, and passed and grasped by human fingers, so as to hook the jointing part on the heatsink fan. Thus, the heatsink fan is mounted on the fixed frame only by hooking the operating part through human fingers.

Abstract: Actuator for adjusting pitch angle of a rotor blade of a wind turbine rotatably mounted on a rotor hub, comprising a first drive element connectable with the rotor blade, a second drive element in meshing engagement with said first drive element, a lubricating device for lubricating the two drive elements and lubrication controller. A rotor with a rotor hub, on which at least one rotor blade is rotatably mounted, with actuator adjustable pitch angle. A wind turbine comprising such rotor and such actuator. Selective lubrication of zero teeth of the gear stage of the actuator considers the rotary position of the drive elements of the gear stage with respect to each other. The lubricating device includes a lubricant passage to selectively supply portion of first drive element and/or portion of second drive element meshing therewith depending on engagement position of drive elements or rotary position of rotor blade.

Abstract: A turbine airfoil of a gas turbine engine, the airfoil constructed from a spar and shell, in which the spar includes a root with a plurality of spar cooling air supply channels extending toward the tip and having impingement holes formed along the spar to provide impingement cooling to the shell, and the shell includes a plurality of shell return channels extending from the tip toward the root to channel the impingement cooling air to collector cavities located in the root. With a plurality of spar supply channels and shell return channels, a serpentine flow cooling circuit with multi-impingement cooling of the shell is produced. The cooling air supplied to the spar is discharged out exit holes in the trailing edge in one embodiment, or out exit holes and leading edge film cooling holes in a second embodiment. The spar and shell are bonded together using a low pressure and high temperature bonding process that includes thin sheets containing boron.

Abstract: Resting element (10) for a compressor or turbine comprising a first cantilever resting portion (20) and a second fixing portion (30) to a case of the compressor or turbine by means of a series of screws (60), the second fixing portion (30) comprises a third end portion (32) externally axial symmetrical and also a fourth counter-portion (36) situated between the third portion (32) and the first resting portion (20) to prevent the disengagement of a hauling rope.

Abstract: This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal between turbine blade disks and the surrounding ring seal without causing excessive wear to the blade tips. The abradable coating system includes columns of an abradable material. Thus, interference between the blades and the abradable coating system causes the individual columns to break off at the base. This abrasion mechanism may reduce blade wear and spalling of the coating system when compared to conventional coatings.

Abstract: A gas turbine engine includes a high-pressure compressor having an impeller and an impeller baffle having a generally annular body, the impeller baffle spaced apart from a back face of an impeller to create an airspace therebetween, the airspace communicating between an impeller exit and an apparatus to be pressurized, the impeller baffle including a plurality of generally radially-disposed ribs extending into the airspace for diminishing the velocity of air swirling in the airspace.

Abstract: The invention relates to a device for adjusting the centring of a turbo-engine pivoting vane control ring, comprising a control ring (26) centred on a longitudinal axis (X-X) of the turbo-engine and provided with a plurality of tapped holes (36) running in a radial direction and a plurality of pad holders (32), each comprising a threaded rod (34) screwed into one of the ring's tapped holes (36), each pad holder (32) holding, at an inner end, a pad (30) intended to come into contact with a cylindrical shell (28), coaxial with the ring. The control ring (26) comprises, in addition, a plurality of slots (38) running in a tangential direction, each slot (38) communicating with one of the ring's tapped holes (36) The device comprises means (40, 42a, 42b) of pinching, in a longitudinal direction, each of the slots (38) in such a way as to lock the pad holders (32) in position.

Abstract: A VAWT wind engine includes a support structure, an articulating rotor mounted on the support structure for rotation about a vertically extending axis, and at least one airfoil on the rotor for rotor-powering purposes. The articulating rotor is mounted in a manner enabling tilting movement of the rotor during rotation so that the airfoil produces rotor rotation and rotor tilt as the airfoil orbits the rotational axis. At least one mechanical linkage is included to actively vary airfoil pitch according to rotor tilt. The partially articulating rotor of a teetering-rotor embodiment seesaws up and down about a horizontally extending pivotal axis. The fully articulating rotor of another embodiment supports three airfoils as it tilts in any direction by virtue of a gimbal or other rotor hub assembly providing a 360-degree swiveling action, while furling hinges help protect the airfoils against damaging winds during wind engine shutdown.

Abstract: A turbine blade, including an intrados wall, an extrados wall, at least one first radial trailing edge cavity, at least one second radial cavity upstream of the trailing edge cavity, an internal wall separating the radial cavities and with at least one channel connecting the cavities to one another, the channel being oriented in an axis intersecting the internal surface of the intrados wall.

Abstract: A ceiling fan scent holder and placement handle which allows a user to distribute fragrance or aromatic substances into the air by using ceiling fans is provided. Said scent holder comprises a lune-shaped piece with an interior channel into which is placed a scent packet, vent holes in each side of a scent holder, and a magnet affixed to the holder top or holder bottom. Said scent holder may be removably placed inside a bracket well of a blade mounting bracket or removably attached to other parts of a ceiling fan via said magnets or also using hook and loop fasteners. A placement handle, comprising a telescopic handle with rotatable arm having at least one magnet affixed between or to prong located at the arm's distal end, may be used to easily place or attach a scent holder in a user-determined ceiling fan location.

Abstract: A turbine airfoil with a thermal barrier coating applied to the surface for protection from a hot gas flow, where the TBC includes a plurality of micro-tubes extending from a cooling hole in the airfoil substrate and passing through the TBC to provide both reinforcement to and cooling of the TBC. The micro-tubes extend out from a separate hole and open onto the surface of the TBC, or a plurality of micro-tubes extends from a common hole and spread out from the hole. The micro-tubes are formed from nickel or another high temperature resistant material and have a diameter of about 0.009 inches.