Abstract: An airfoil or vane for a combustive power plant includes an inner core formed from a first composite material having discontinuous fibers. An outer sleeve is formed from a second composite material having continuous fibers. The first composite material is different from the second composite material. The outer sleeve generally surrounds and is bonded or otherwise connected to the inner core. A method of fabrication includes injecting or otherwise introducing thermoplastic fiber composite material including chopped or otherwise discontinuous fibers into a mold to form the core and platforms of an airfoil assembly. The injected thermoplastic fiber composite material is then cured in the mold. The cured thermoplastic fiber composite material is then removed from the mold. A layup including one or more surface plies of a thermoset continuous fiber composite material is then applied to the core material. The surface plies are then compressed and cured in a mold.

Abstract: A balance weight for a turbine rotor includes: (a) a block-like centerbody; (b) a pair of resilient spring arms extending laterally from opposite sides of the centerbody, the centerbody and the spring arms collectively defining an arcuate shape; and (c) at least one locating structure extending from a radially outer surface of the balance weight.

Abstract: A stator assembly for a turbine engine is disclosed. The stator assembly has a stator support ring, a plurality of stator vanes protruding radially inwardly from the stator support ring, and at least one bleed port disposed on the stator support ring between at least two adjacent stator vanes of the plurality of stator vanes. The at least one bleed port defines an oblong profile having a first end terminating near a leading edge of a first stator vane of the at least two adjacent stator vanes, and a second end, substantially opposed from the first end, terminating near a trailing edge of a second stator vane of the at least two adjacent stator vanes. The profile may be concave toward a suction sidewall of the second stator vane of the at least two adjacent stator vanes.

Abstract: A method for repairing a hub pitch gear assembly. The method includes providing a ring assembly for adjusting a pitch angle of a wind turbine blade having a plurality of gear teeth. A segment of the ring assembly is removed, the segment including at least a portion of at least one gear tooth, to form a repair cavity. A repair segment configured to mate the repair cavity is provided and the repair segment is directed into the repair cavity and fastened in position. A repaired pitch gear assembly and wind turbine are also provided.

Abstract: A centrifugal blowing apparatus for reducing flow-induced noise is disclosed. The apparatus includes a blower housing having a scroll section formed about a rotational axis and an exhaust section extending from the scroll section. The scroll section includes an opening defining an inlet configured to draw in air and the exhaust section defines an outlet in fluid communication with the inlet. The scroll section commences with a reduced cross-sectional area defining a cutoff and expands to an increased cross-sectional area. An impeller is disposed in the opening of the scroll section about the rotational axis and includes an outer surface having impeller blades radially disposed thereon. The impeller blades rotate to direct a flow of air from the inlet through the scroll section to the outlet. A plurality of indentations is formed along an inner surface of the scroll section at the cutoff.

Abstract: Embodiments of the present invention include a method and system for carrying out vapor-phase lubrication of a component, such as a bearing for example. The method and apparatus can be applied to a turbine engine. The method includes the step of directing a first stream of fluid containing atomized lubricant to the component at a first velocity. The system provides a first fluid injection system configured to perform the first step. The method also includes the step of directing a second stream of fluid at a second velocity less than the first velocity to the component. The second stream is for controlling a temperature of the component. The system provides a second fluid injection system configured to perform the second step. Both of the directing steps are carried out concurrently.

Abstract: An airfoil structure, shim, and retention member combination includes an airfoil structure, a retention member and a shim. The airfoil structure may define a first recess. The retention member may define a second recess. The first and second recesses may define a cavity. The shim may include a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity.

Abstract: A system is provided for monitoring radial motion of a rotating shaft of a turbocharger. The turbocharger includes a compressor and a turbine coupled to opposing ends of the shaft. The system includes a thrust collar including a cylindrical portion and a flange configured to radially extend from one end of the cylindrical portion. The thrust collar is configured to rotate with the shaft. A sensor is positioned within a separation of an outer surface of the thrust collar flange, and the sensor is configured to monitor the separation as indicative of the radial motion of the shaft. Additionally, a method is provided for monitoring radial motion of a rotating shaft of a turbocharger.

Abstract: A method for controlling load reduction for a wind turbine rotor with rotor blades comprising an aerodynamic active element responsive to a control signal for modifying its setting is provided. The loads acting on the rotor blades in relation to the rotor's azimuth are detected and individual control signals based on a PI control system are established. Each individual control signal is a complex number containing an amplitude defining the degree of modification of the respective setting and an angle defining the phase of the modification of the respective setting with respect to the rotor's azimuth. The angle of the complex number is corrected by a phase correction factor. The elements are provided with the individual control signals. The input to the PI-control system is a complex load vector.

Abstract: A pneumatic turbine motor air chamber drives a pneumatic turbine to rotate through compressed air. The pneumatic turbine has a ring extended from inside thereof that has a plurality of barriers and forms a housing space to hold a speed regulator. The pneumatic turbine also has an air intake coupling hole leading to the housing space and at least one air discharge vent communicating with an air passage to discharge the compressed air. The ring is integrally formed with the pneumatic turbine to enhance operation steadiness of the pneumatic turbine.

Abstract: A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centered on the axis of a turbomachine. Pressure and suction surfaces of neighboring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row of aerofoil members includes at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan. The endwall at each sectoral passage has a non-axisymmetrical cross-section formed by a region that, in meridional section, is convexly profiled immediately adjacent the pressure surface and a region that, in meridional section, is concavely profiled immediately adjacent the suction surface.

Abstract: Embodiments of the present disclosure relate to a turbine which includes an outer shell, an inner shell connected to and surrounded by the outer shell in generally concentric relation therewith, at least one turbine rotor housed within the inner shell, a plurality of nozzles and shrouds carried by the inner shell, a plurality of connecting elements engaging between the inner and outer shells aligning the inner shell about the rotor, and at least one compliant support. Embodiments of the present disclosure also relates a method of configuring the securing arrangement between the inner shell and the outer shell of a turbine.

Abstract: The invention relates to a wind turbine including at least two blade units. Each blade unit has a pitch controlled wind turbine blade and at least one pitch bearing including at least one outer ring, at least one center ring and at least one inner ring. The wind turbine further includes a hub comprising a mount area for each of the blade units (31). The mount area comprises at least two concentric load transferring surfaces for attaching the blade unit, via the at least one pitch bearing. The invention further relates a hub and a use hereof.

Abstract: A high-pressure turbine of a turbomachine, including at least one upstream guide vane element and an impeller mounted so as to rotate inside ring sectors attached to an annular support which is suspended from an outer casing, the upstream guide vane element including, at its radially inner end, a mechanism for attachment to an inner casing and, at its radially outer end, a mechanism for pressing axially on a fixed element of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.