Abstract: A nacelle is disclosed. The nacelle may include an inner fixed structure (“IFS”) comprising a first half, the first half comprising a central barrel portion, wherein the first half includes a first member that extends radially outward from the central barrel portion and a second member that extends radially outward from the central barrel portion radially opposite the first member, a first support structure overlaid by a first composite material that extends axially along a confluence between the central barrel portion and the first member, the first support structure configured to contact a second half comprising a second central barrel portion, and a second support structure overlaid by a second composite material that extends axially along the confluence between the central barrel and the second member, the second support structure configured to contact the second half.

Abstract: A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing.

Abstract: A wind turbine yaw assembly has a yaw piston and a yaw bearing pad. A spring resides inside the yaw piston and applies spring pressure to the yaw bearing pad. A threaded yaw piston bushing applies adjustable pressure to the spring. The threaded yaw bushing has a plurality of at least three force adjustment screws distributed symmetrically about the threaded yaw piston bushing. The spring pressure is adjusted by tightening or loosening the plurality of force adjustment screws. This abstract is not to be considered limiting, since other embodiments may deviate from the features described in this abstract.

Abstract: A double-jet film cooling structure includes: an injection port, formed on a wall surface facing a high-temperature gas passage; a main passage as a straight round hole to supply cooling medium to the injection port; a pair of branch passages as straight round holes; and communication passages connecting the main passage to the branch passages. The main passage and the branch passages have same constant inner diameters. Each communication passages has an envelope surface obtained by continuously arranging straight round holes each passing a branch point and having the constant inner diameter. Transverse injection angles of the branch passages relative to gas flow along the wall surface are oriented in opposite directions. An angle between axial direction of the main passage and the wall surface is greater than an angle formed between axial direction of branch passage and the wall surface.

Abstract: A flap arrangement for a wind turbine rotor blade, which includes a leading edge, a trailing edge and a chord line between the leading edge and the trailing edge, is described. The flap arrangement includes a support portion and a flap portion which is passively moveable with respect to an angle between a surface normal of a surface of the flap portion and the chord line. The support portion and the flap portion are positioned relatively to each other such that the support portion provides a limit to the movement of the flap portion. Also described are a wind turbine rotor blade including the flap arrangement and a method of enhancing the aerodynamic performance of a blade.

Abstract: A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing is provided. The structure includes a shroud having a plurality of sectors, a plurality of radial arms each installed between two adjacent shroud sectors, and a plurality of fasteners for fastening the plurality of shroud sectors to the plurality of radial arms. The shroud sectors and radial arms form a skeleton for transmitting structural forces within the intermediate casing. The structure includes non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage. Each of the shroud sectors and radial arms is formed by a metal frame without mechanical discontinuity, each shroud sector metal frame defining at least one opening that is closed by a cover and each radial arm metal frame defining at least one orifice for receiving a closure plate.

Abstract: A variable geometry turbine has annular inlet passageway defined between a first surface of a radial wall of a movable wall mounted within a cavity and a facing wall of the turbine housing. The radial wall defines a second surface that opposes the first surface. The moveable wall member comprises an annular flange that extends axially into the cavity and supports a radial flange defining opposing third and fourth surfaces. The radial flange seals against an annular sleeve in the cavity to define a first area within the cavity which includes the radial second and third surfaces and a second area within the cavity which includes the radial fourth surface. The first and second areas are in fluid communication with regions of the annular inlet passageway which are respectively upstream and downstream of a radial vane passage.

Abstract: A gas turbine having a guide vane assembly (2) and a securing ring (1) for axially locking the guide vane assembly in position that has a radially outer rim (1A) which is configured in a housing-side groove (3.1), a radially inner rim (1B) which is configured outside of the groove, and a slot (10) which extends from the radially outer rim to the radially inner rim, and a first flank having a radially inner rim section (12) and an undercut portion (11), the radially inner rim section forming an angle (?) of at least 50° with the radially inner rim.

Abstract: A gas turbine casing made of organic matrix composite material includes reinforcement densified by an organic matrix defines an inside volume. On its inside face the casing has a structural part with a first face facing the inside face of the casing, and an opposite second face defining a flow passage portion. Recesses opening out into the inside volume of the casing are present between the inside face of the casing and the first face of the structural part facing the inside face of the casing. In the event of a fire, the recesses allow gas coming from degradation of the resin of the casing to be discharged into the flow passage.

Abstract: A gas turbine engine includes a core flow path that extends axially about an engine axis. A turbine section is arranged in the core flow path. A mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of the core flow path. The vanes and inner and outer flow path surfaces are provided by a unitary, one-piece cast structure. The inner flow path surface provides inlet and exit inner diameters relative to the engine axis. The outer flow path surface provides inlet and exit outer diameters relative to the engine axis. The inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter. A ratio of the exit outer diameter to the axial length is greater than 3.0 to 1.

Abstract: An end-wall component of the mainstream gas annulus of a gas turbine engine having an annular arrangement of vanes, the component including a cooling arrangement having ballistic cooling holes (33) through which, in use, dilution cooling air is jetted into the mainstream gas upstream of the vanes to reduce the mainstream gas temperature adjacent the end-wall, wherein the cooling holes are arranged in one or more circumferentially extending rows and wherein the axial position of the cooling holes in the or each row varies.

Abstract: A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19).

Abstract: A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface.

Abstract: An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.

Abstract: A cooling fan module includes a frame, and a fan impeller having a plurality of fan impeller blades is located in an opening of the frame. The fan impeller blades are connected to a base portion of an outer fan ring. A lip portion of the outer fan ring extends from the base portion radially outward, and a leading end of the lip portion is turned in direction to the downstream side of the frame. A recirculating flow guiding device includes a plurality of guide vanes located on an upstream side of the frame and around the opening of the frame. An air gap is provided between the outer fan ring and the frame. A recirculating flow travels from downstream side of the cooling fan module through the air gap, and is turned by the leading end of the lip portion into the recirculating flow guiding device.

Abstract: A control method for a wind turbine, in particular for a wind turbine blade is described. The control method makes use of the blade mode shapes, or natural vibration shapes, of the blade to detect the excitement level of the blade natural vibrations, and controls active lift devices on the blade in an effort to reduce the excitement levels, to reduce loading in the blade and the overall wind turbine structure. There is also provided a method of designing a wind turbine blade for use in such a method.

Abstract: A method of de-watering during intermittent dry running periods with a self-priming centrifugal pump is presented. Centrifugal pumps, as opposed to diaphragm pumps, are advantageous because they are less expensive and can provide greater capacity. The shaft seals are sensitive, however, to frictional heating when water flow is interrupted. In some situations, this fractional heating may desiccate self-priming. The inventive concept provides a continuous stream of pressurized water moving through the pump to cool the seal and sustain priming capability without substantially impairing the ability of the pump to resume wet operation.

Abstract: A sealing element for positioning radially outwardly of aerofoil blades of a gas turbine engine is provided. A radially inner surface region of the sealing element includes a seal structure having one or more inwardly projecting walls formed by additive layer, powder fed, laser weld deposition. The walls form a plurality of curved profile shapes which are arranged in a repeating pattern across the radially inner surface region. None of the walls intersects with any other wall. The curved profile shapes have no radii of curvature less than 0.5 mm.

Abstract: A fan assembly for gas assembly engine is disclosed. The fan assembly includes a rotor that is coupled to at least one fan blade. The fan assembly also includes a spinner that extends towards the rotor and the fan blades so that an edge of the spinner engages the fan blades. The edge of the spinner thereby serves as a grounding element for the fan blade. If the spinner is fabricated from a composite or a plastic material that is not sufficiently conductive for grounding purposes, the edge may be coated with a conductive material. Alternatively, the spinner may be fabricated from a metallic material, which would eliminate the need for a conductive coating on the edge that engages the fan blades.

Abstract: A method of operating a turbine assembly is provided. The method includes receiving a flow of air at a filter house that includes a first heat exchanger. The temperature of the air is controlled with the first heat exchanger by one of selectively cooling the air and by selectively heating the air. The air is then channeled from the first heat exchanger to a second heat exchanger to facilitate cooling the air.