Abstract: A turbomachinery includes a labyrinth seal (2) to prevent unstable vibration of a rotor formed by dividing the seal into segments (7) in a circumferential direction and combining the segments (7) whose comb teeth (5) differ in height. The labyrinth seal (2) preferably includes two kinds of segments (7) whose comb teeth (5) differ in height for each kind of segment, and the segments (7a) of the greater comb tooth height are arranged in a certain reference direction on a cross section right-angled to a rotational axis, and in a direction opposite to the reference direction, and the segments (7b) of the smaller comb tooth height are arranged in a direction right-angled to the reference direction, and in a direction opposite to that right-angled to the reference direction.

Abstract: A turbine rotor blade an open cavity and a series of vortex chambers formed along the pressure and suction side walls to form a cooling air path from the leading edge, along the pressure side wall toward the trailing edge, and then from the trailing edge along the suction side wall to be discharged at the leading edge region on the suction side wall as film cooling air. The vortex chambers and feed slots connected adjacent vortex chambers are enclosed with a thin thermal skin to form a thin airfoil wall.

Abstract: A power-generation system is provided. The system includes a plurality of vertical axis wind turbines (VAWTs). Each VAWT includes an upstanding support structure, a central shaft positioned along a central axis of the VAWT, a plurality of struts extending from the central shaft, and a plurality of blades, each blade positioned at an end of a corresponding strut and oriented substantially vertically. The VAWTs are grouped in sets that are arranged in rows, and are separated from each adjacent VAWT by a distance of approximately one rotor diameter.

Abstract: A wind turbine and methods for controlling wind turbine thrust are disclosed. In one embodiment, the method includes measuring a tilt angle of a wind turbine in a loaded position using a measuring device. The wind turbine includes a tower, a nacelle mounted on the tower, a rotor coupled to the nacelle, and a plurality of rotor blades coupled to the rotor. The method further includes comparing the tilt angle to a predetermined tilt angle for the wind turbine and, if the tilt angle exceeds the predetermined tilt angle, adjusting a pitch of at least one of the plurality of rotor blades such that the tilt angle is less than or equal to the predetermined tilt angle.

Abstract: A turbine rotor blade with near wall cooling that provides full coverage film cooling for the leading and trailing edges. A first layer of chordwise extending cooling channels are formed on a spar, and a second layer of chordwise extending cooling channels are formed over the first layer to provide near wall cooling. Open ends of the two layers of channels on both pressure and suction side walls of the blade open into a leading edge slot and the trailing edge wall sides to discharge film cooling air.

Abstract: A lightning protection system for a wind turbine blade or aircraft wing includes a glass-reinforced fiber or carbon-reinforced wind turbine blade or aircraft wing having a tip region, a suction side, a pressure side, a leading edge and a trailing edge. A substantially planar sheet of conductive or semi-conductive material is disposed internal to the blade tip region or wing tip region and between the suction side and pressure side. The sheet operates during a lightning discharge to form an electric field control mechanism causing the lightning discharge to attach to the tip region. The sheet is in electrical communication or galvanic connection with a conductive or semi-conductive path such that the electric field control mechanism and the path together operate to protect the wind turbine blade or aircraft wing from damage caused by the lightning strike in the tip region of the wind turbine blade or aircraft wing by controlling an electric field in the tip region caused by the lightning strike.

Abstract: A seal assembly for a gas turbine engine is provided that includes a seal support member, at least one knife edge seal blade member, and at least one cooling member. The seal support member is configured for rotation within the gas turbine engine around an axial centerline of the engine. The support member has a thickness extending between a first surface and a second surface. The blade member extends outwardly from the first surface of the support member. The blade member has a central portion that extends between a base end and a distal knife edge end. The base end is attached to the first surface of the seal support member. The cooling member extends outwardly from the second surface, and is oppositely aligned with the blade member.

Abstract: An inner shroud assembly includes an aft core segment mountable to a forward core segment to support a multiple of vanes for rotational movement relative thereto. A shroud backing plate segment engageable with the aft core segment and at least one fastener which passes through the shroud backing plate, the aft core segment and the forward core segment.

Abstract: A larger and highly twisted and tapered turbine rotor blade with a cooling circuit having a 3-pass horizontal flow serpentine circuit in a lower end of the airfoil, a 3-pass vertical flow serpentine circuit in the middle region of the airfoil, and a plurality of radial cooling channels in the upper end of the airfoil all connected in series to provide cooling for the airfoil.

Abstract: A rotor of a turbomachine is provided. The rotor includes at least first and second rotor portions and at least first and second blades. The first and second rotor portions are configured to rotate about an axis. The first and second rotor portions have first and second rim portions, respectively, which are spaced a predetermined distance apart from one another and have a perimetrical slot therebetween. The first and second rim portions have first and second dovetail slots, respectively, extending therethrough communicating with the perimetrical slot. The first and second blades have first and second dovetail portions, respectively. The first dovetail portion is disposed in one of the first and second dovetail slots, and the second dovetail portion is disposed in the other of the first and second dovetail slots. The perimetrical slot has a sufficient size to pass the first and second blades therethrough when the first and second blades are removed from the rotor.

Abstract: Provided is a vane tip clearance management structure for a gas turbine which allows a vane tip clearance to be confirmed easily at the time of completing assembly. For this purpose, there are provided: a casing (3) rotatably supporting a rotor (2); stator vane retainer rings (11, 12, and 13) and a turbine vane ring (16) provided to have predetermined clearances from tips of rotor vanes (10 and 15) fitted in multiple steps to the rotor (2) inside in the radial direction of the casing (3); guide frames (26) penetrating the casing (3), the stator vane retainer rings (11, 12, and 13) and the turbine vane ring (16) in the radial direction and being supported by stepped portions (21a, 22a, 23a, and 24a); and rods (25) movably supported by the guide frames (26) and abutting on the tips of the rotor vanes (10 and 15). Clearances (C1 and C2) are measured based on the amounts of movement of the rods (25) relative to the guide frames (26).

Abstract: A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.

Abstract: A method for optimizing energy production in a wind turbine includes pitching a plurality of rotor blades to a full operational angle, and utilizing an active flow control device in accordance with a generator speed and a rotor blade pitch setting to facilitate maintaining a predetermined generator rated power level.

Abstract: Blade insert arranged inside the blade walls so that the joint between the insert and composite (1) is a double shear joint. The insert is made up of two defined parts, the head (3, 3?) and the body, which are joined together by joint elements (5) that define a double wall body (6, 6?). The joint between the insert and pultruded material (2) is made with an adhesive chemical joint (9). After making the joint, the assembly made up by the inserts and pultrusion profiles (2) is fitted into the blade walls during its manufacturing process and material curing.

Abstract: A metal vane core or strut (64) is formed integrally with an outer backing plate (40). An inner backing plate (38) is formed separately. A spring (74) with holes (75) is installed in a peripheral spring chamber (76) on the strut. Inner and outer CMC shroud covers (46, 48) are formed, cured, then attached to facing surfaces of the inner and outer backing plates (38, 40). A CMC vane airfoil (22) is formed, cured, and slid over the strut (64). The spring (74) urges continuous contact between the strut (64) and airfoil (66), eliminating vibrations while allowing differential expansion. The inner end (88) of the strut is fastened to the inner backing plate (38). A cooling channel (68) in the strut is connected by holes (69) along the leading edge of the strut to peripheral cooling paths (70, 71) around the strut. Coolant flows through and around the strut, including through the spring holes.

Abstract: An apparatus and system for counteracting wind gusts and other high load situations in a wind turbine includes the use of one or more gust counteracting devices configured to extend an air deflector outwardly from a surface of a turbine rotor blade. The air deflector may subsequently be retracted into the rotor blade once the wind gust has subsided or once the load falls below a certain threshold. Mechanisms for extending and retracting the air deflector may include pneumatic or hydraulic systems and/or electromechanical devices. Air deflectors are generally configured to normalize air flow around the rotor blade so that the risk of potential damage to components of the wind turbine is minimized. In one arrangement, the gust counteracting device may be located at a leading section of the turbine blade. Additionally or alternatively, the device may be modular in nature to facilitate the removal and replacement of the device.

Abstract: A method of attaching particles to a substrate, comprising the steps: providing a substrate having a surface providing an interlayer on the surface which conforms to the surface of the substrate, forming a melt pool in the interlayer, depositing a material within the melt pool, allowing the material to solidify, applying a powder containing dispersed particles to the solidified material, and applying heat to attach the dispersed particles to the substrate.

Abstract: A braking mechanism is provided that is suitable for an expansion turbine that rotates at high speed. Upper end salient poles 26a and 26b are formed in two opposite places on the outer peripheral upper end of a rotating shaft 12, and lower end salient poles 28a and 28b are formed in two opposite places on the outer peripheral lower end of the rotating shaft 12 such that they are staggered in the vertical direction with respect to the upper end salient poles 26a and 26b. A casing 22 is provided in a location facing an outer periphery of the rotating shaft 12, and an excitation coil 30 is provided on the casing 22 for forming a magnetic path between the upper end salient poles 26a and 26b and the lower end salient poles 28a and 28b. By rotation of the rotating shaft 12, and by the magnetic path formed by the excitation coil 30, eddy currents are generated in the casing 22.

Abstract: A cold air buffer supply tube for a gas turbine engine includes a tube body having a first tube end and a second tube end. A fitting is secured to the first tube end, and a metering cap is secured to the tube second end. The metering cap includes a cap body having a peripheral wall with a plurality of holes to direct flow from an air supply into a bearing compartment for the gas turbine engine.

Abstract: A variable coolant pump for a cooling circuit of an internal combustion engine. The variable coolant pump includes a pump head having an inlet, an annular channel and an outlet; a pump housing rotatably supporting a pump shaft having an axial end; a pump blade wheel mounted on the axial end of the pump shaft and disposed in the pump head; and a plurality of adjustable guide blades arranged concentrically about the pump blade wheel between the annular channel and the pump blade wheel. Each adjustable guide blade has two longitudinal sides and outer edge and includes a first pivot, a second pivot and a third pivot. The first and second pivots extend at right angles to a respective one of the two longitudinal sides in a vicinity of the outer edge. The first and second pivots define an axis of rotation and rotatably support the respective guideblade in the pump head about the axis of rotation.