Abstract: A wind turbine system comprising a nacelle mounted on a tower, a rotor having a plurality of blades and a boundary layer control system configured to control airflow through blade surface openings in each of the blades. The wind turbine system includes a control system configured to perform at least one of the following: to monitor an operational speed parameter of the wind turbine, and to activate the boundary layer control system if it is determined that the 1 operational speed parameter exceeds a predetermined speed parameter threshold; to monitor tower motion and to activate the boundary layer control system based on a determination of excessive tower motion; to monitor for a wind turbine shutdown condition, and to activate the boundary layer control system if it is determined that a wind turbine shutdown condition has been identified; and to monitor the aerodynamic loads on the blades, and to activate the boundary layer control system also based on a determination of excessive blade loads.

Abstract: A dual-flow turbomachine generally includes a cooling and turbine clearance control system located in a primary air flow path of the turbomachine, supplied a scoop configured to take air from a secondary air flow path arranged around the primary air flow path through an air inlet of the scoop, where the scoop may further include one wall configured to be arranged in the extension of a wall of the secondary flow path, and further where the air inlet may be formed in and flush with the wall.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotatable shaft defining a longitudinal axis, and a bearing housing extending along the longitudinal axis to define a bearing compartment. The bearing housing has a first seal land defined along an inner diameter of the bearing housing, a seal carrier fixedly attached to an outer periphery of the shaft, and a seal member extending outwardly from the seal carrier. The seal member defines a plurality of helical grooves facing radially outward to establish a first sealing relationship with the first seal land, and each one of the helical grooves has a major component extending in an axial direction relative to the longitudinal axis. A method of sealing for a gas turbine engine is also disclosed.

Abstract: An airfoil piece includes a first vane platform, a second vane platform, and a hollow airfoil section that joins the first vane platform and the second vane platform. The hollow airfoil section includes a collar projection which extends past the first vane platform. The collar projection includes at least one radial tab projecting therefrom. An airfoil assembly and a method of assembling a vane are also disclosed.

Abstract: Disclosed herein is a gas turbine disk that includes a cooling target, and a disk unit having a main passage that is open to supply cooling air to the cooling target, and a plurality of unit passages that are open at an end of the main passage while each having a predetermined size.

Abstract: A centrifugal blower has a first housing section and a second housing section separated by a width of the centrifugal blower. The centrifugal blower also has an intake port extending through the first housing section and the second housing section along the width, and an outlet port formed by the first housing section and the second housing section. A dimension of the width continuously decreases as the outlet port is approached along a length of the centrifugal blower.

Abstract: A turbomachine stator element extends around a longitudinal axis and includes a first stator vane and a second stator vane circumferentially adjacent to the first stator vane. Each of the first and second stator vanes include a platform and a blade extending radially from the platform. The stator element also comprising at least one inter-platform seal, arranged between the platform of the first stator vane and the platform of the second stator vane. The inter-platform seal has a flat support provided with an upper surface on which there extends a fin.

Abstract: An axial compressor includes: a casing having a tubular shape; variable stator vanes each having a vane shaft as a swing center, provided in the casing as stator vanes or inlet guide vanes, and arranged in a circumferential direction of the casing; rotor blades provided on a trailing edges side of the variable stator vanes in the casing and arranged in the circumferential direction of the casing; and a plasma actuator configured to generate a plasma annularly distributed in the circumferential direction of the casing, the plasma actuator being attached on an inner circumferential surface of the casing and intersects with a clearance between each variable stator vane and the inner circumferential surface of the casing.

Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

Abstract: A stator assembly, at a compressor mid-plane in a gas turbine engine, to be mounted around a rotor disc, enables access to the rotor disc (e.g., for trim balancing), without requiring disassembly of the stator assembly and/or a compressor case in which the stator assembly is housed, via a removable stator vane. The stator assembly may comprise vane apertures, aligned along a radial axis, that hold the removable stator vane when inserted into the stator assembly, and provide a radial pathway to the rotor disc, when the removable stator vane is removed from the stator assembly. In addition, a case access assembly may seal the removable stator vane in place within a compressor case when engaged, and provide access to the removable stator vane and radial pathway through the compressor case when disengaged. This enables trim balancing of a mid-plane compressor rotor assembly through the stator assembly and compressor case.

Abstract: Provided is an aerodynamic structure for mounting to a surface of a wind turbine rotor blade, which aerodynamic structure includes a number of comb elements, a comb element including comb teeth arranged in a comb plane, wherein the comb plane of a mounted comb element is essentially perpendicular to the trailing edge of the rotor blade and to the airfoil surface of the rotor blade. A wind turbine rotor blade including at least one such aerodynamic structure, and a method of equipping a wind turbine rotor blade with such an aerodynamic structure, is also provided.

Abstract: The invention relates to a turbine engine (2) compressor shroud, comprising: first and second sections (130, 230) and respective flanges (131, 231), the flanges (131, 231) making it possible to hold the two sections (130, 230) together, the first section (130) comprising a cylindrical surface (137) forming a seat for an actuating device (136, 140, 166, 168, 170) for orienting stator blades (126), characterised in that the first shroud (130) comprises a tubular wall (132) axially overlapping both flanges (131, 231) and said cylindrical surface (137) is an outer surface of the tubular wall (132). The invention also relates to an assembly with the shroud (130, 230), the blade (126) and means (140) for actuating the orientation of the blade (126), the shroud being produced using the kit described above. The invention finally relates to a method for assembling a compressor with such an assembly.

Abstract: An impeller includes Z blades, where Z is an integer equal to 5 or more, arranged in a circumferential direction of the impeller and extending radially, pitch angles between adjacent blades being all different. In terms of an arbitrary pitch angle ?, when a pitch angle ?1 adjacent to the pitch angle ?, and a pitch angle ?2 adjacent to the pitch angle ?, different from the pitch angle ?1, satisfy a relation, ?1<?2, a pitch angle ?1 different from the pitch angle ? adjacent to the pitch angle ?1 and a pitch angle ?2 adjacent to the pitch angle ?2, different from the pitch angle ?, satisfy a relation, ?2<?1.

Abstract: An airfoil includes a first airfoil piece and a second airfoil piece that is bonded to the first airfoil piece at a joint. The first airfoil piece and the second airfoil piece are formed of aluminum alloys. At least one of the aluminum alloys is an aluminum alloy composition that has greater than 0.8% by weight of zinc. The joint includes a braze element of magnesium, zinc, or combinations thereof in a higher concentration than in other portions of the first airfoil piece and the second airfoil piece.

Abstract: A fixed vane turbocharger includes: an impeller; a housing including, inside thereof, an impeller housing space which accommodates the impeller, a scroll flow passage formed on a radially outer side of the impeller, and a communication flow passage which brings the impeller housing space and the scroll flow passage into communication; and at least one fixed vane unit disposed in the communication flow passage and fixed to a portion of the housing on an inner side of the scroll flow passage with respect to a radial direction of the impeller. Each of the at least one fixed vane unit includes at least two vane portions and a coupling portion coupling the two vane portions, and is formed of a single sheet metal member.

Abstract: The gas turbine engine can have an accessory gearbox having a sump; an oil tank; a user interface configured to generate a signal upon receiving a user input indicative of an oil measurement reading; and a pump configured to pump oil from the sump to the oil tank upon receiving the user input.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.

Abstract: A turbine blade includes a blade body including a top plate at a tip portion which is outside of a turbine rotor in a radial direction of the turbine blade and has an outer surface configured to face an inner circumferential surface of a casing, and a tip thinning which protrudes radially outward in the radial direction of the turbine blade from the outer surface of the top plate and extends from a leading edge side of the blade body to a trailing edge side of the blade body. A protrusion amount of the tip thinning based on the outer surface of the top plate is 0.25 times or more and 2.00 times or less a diameter of a discharge port of a cooling hole which passes through the top plate.

Abstract: A fibrous structure having the form of a band extending in a longitudinal direction (X) over a given length between a proximal part and a distal part and in a lateral direction (Y) over a given width between a first side edge and a second side edge, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns or strands extending longitudinally and a plurality of layers of weft yarns or strands extending laterally, wherein a first portion of the fibrous structure present between the proximal part and an intermediate part of the fibrous structure includes carbon fiber weft yarns or strands and wherein a second portion of the fibrous structure present between the intermediate part and the distal part includes glass fiber weft yarns or strands.

Abstract: A blade tip assembly for a wind turbine blade, comprising a conductive blade tip module, a receptor arrangement spaced from the conductive blade tip module, a coupler that electrically couples the conductive blade tip module to the receptor arrangement and an insulating member that insulates the coupler. The invention also can be expressed as a method for assembling a blade tip assembly for a wind turbine blade, the method comprising providing a blade tip module; providing the blade tip module with a coupler for electrically coupling the blade tip module to a down conductor of a lightning protection system; and encasing the coupler with an insulating member.