Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane.

Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.

Abstract: The invention relates to an axial-flow turbomachine blading comprising a semi-circular row of blades extending radially. Each blade comprises a airfoil and lateral branches or lateral legs. Each branch has an end joined to the airfoil and an end opposite the airfoil. The blading comprises a first shroud segment connected to at least two opposite ends of two adjacent branches of two adjacent blades and/or of the same blade so as to connect the airfoils to the shroud segment via the lateral branches of the airfoils. The blading also comprises a second shroud segment concentric with the first shroud segment. The segments are connected to one another via the airfoils and the branches. The blading forms a rigid casing and is provided by additive manufacturing with a titanium-based powder.

Abstract: An access system for a hub of a wind turbine, wherein the hub comprises a first flange for mounting a first rotor blade, a second flange for mounting a second rotor blade and a third flange for mounting a third rotor blade is provided. The hub comprises a first opening, a second opening and at least a third opening, each of the openings being suitable for accessing an interior of the hub from outside of the hub. The access system comprises a first ladder with a plurality of first rungs, the first ladder extending inward from the first opening, a second ladder with a plurality of second rungs, the second ladder extending inward from the second opening, and a third ladder with a plurality of third rungs, the third ladder extending inward from the third opening.

Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.

Abstract: A turbine engine assembly is provided. The assembly includes a booster compressor that discharges a flow of first compressed air at a first temperature, and a high-pressure compressor (HPC). The HPC receives a first portion of the flow of first compressed air and discharges the first portion at a second temperature higher than the first temperature such that a flow of second compressed air is formed. The assembly also includes a heat exchanger (HEX) that receives a second portion of the flow of first compressed air from the booster compressor and a first portion of the flow of second compressed air from the HPC such that heat is transferred therebetween. The HEX discharges the first portion of the flow of second compressed air at a third temperature lower than the second temperature and higher than the first temperature such that a flow of cooled bleed air is formed.

Abstract: Double blade airfoils and related systems are disclosed. The double blade design may efficiently use a minimal amount of material yet achieve exceptional aerodynamic efficiencies well above the previously understood theoretical maximum. The disclosed designs may operate at lower wind speeds than those known in the art. Furthermore, the balance of forces generated by the disclosed designs may also reduce the stress felt by the airfoils and rotor, enhancing the longevity of the system.

Abstract: Method of manufacturing an impregnated metal insert for a wind turbine blade root, the insert comprising an outer surface and an open end adapted to receive a fastening element for attachment to a wind turbine rotor hub, wherein the method comprises covering the insert outer surface with one or more resin pre impregnated fiber layers, and heating for curing such that a resin impregnated fiber layer adheres to the outer surface of the insert. The disclosure is further related to the method of manufacturing a portion of a wind turbine blade.

Abstract: A device for bleeding compressor air in a turbofan engine includes a low-pressure compressor of a primary duct, a fan stator arranged in a secondary duct downstream of a fan, and an arrangement for discharging compressor air from the low-pressure compressor into the secondary duct. The arrangement includes air guiding devices to guide compressor air into the secondary duct upstream of the fan stator relative to the flow direction in the secondary duct, past the stator vanes of the fan stator in a separate duct in the axial direction and is only mixed with the air of the secondary duct downstream of the fan stator. The separate duct is formed by a plurality of hollow structures extending in the longitudinal direction each between two adjacent stator vanes of the fan stator, with the hollow structures having a closed circumference in cross-section.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes a plurality of nodes, a plurality of branches that extend between the plurality of nodes, and a plurality of passages extending between the plurality of nodes and the plurality of passages. Further, at least one of the branches is non-circular in cross-section.

Abstract: The subject application relates to blade root wedging lock in a circumferential groove in a rotor such as the drum of an axial turbomachine compressor. The body (32) of the lock includes a solid portion (38) designed to be housed in the groove and having two opposite bearing surfaces (40) and at least one circumferential wedging surface (42). The body (32) further includes an upper portion (36) in the shape of an elongated generally vertical chamber designed to be flush with the upper surfaces of the platforms of adjacent blades when the lock is correctly positioned. This chamber (36) is truncated (44) so as to reduce its length in a direction perpendicular to the circumference, corresponding to the axis of rotation of the rotor. The lock can thus be accommodated in a narrow groove without decreasing the diameter of the clamping screw passing through the hole (34). The subject application also relates to a rotor and a turbomachine equipped with the lock.

Abstract: A gas turbine compressor including a guide vane (1), a moving vane (2), in particular downstream, and a bleed channel (3) having an upstream channel wall (3.1), which merges into an annular space (5), an axially opposite downstream channel wall (3.2) having an inlet edge (3.3), which is rounded in particular, and a bleed channel outlet, the downstream channel wall enclosing with an axis of rotation of the compressor a first angle (?) which increases in the flow direction (x).

Abstract: A gas turbine engine comprises a fan drive turbine for driving a gear reduction, which drives a fan rotor. A lubrication system supplies oil to the gear reduction. An oil tank is relatively small. The lubrication system operates to allow oil to remain in the oil tank for a dwell time of less than or equal to five seconds. A method of designing a gas turbine engine is also disclosed.

Abstract: A drivetrain for a horizontal axis wind turbine includes a main shaft, and a main bearing housing having a main body at least partly enclosing the main shaft and extending from a first end to a second end, a distance from the second end to the rotor attachment flange being larger than a distance from the first end to the rotor attachment flange. The main bearing housing: carries the main shaft via a first bearing and a second bearing, a distance between the second bearing and the rotor attachment flange being larger than a distance between the first bearing and the rotor attachment flange; has a first seat for the first bearing, and a second seat for the second bearing; and includes a seat flange extending from the main body at least partly radially inwards, the second seat being located on a distal end of the seat flange.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: The invention regards a method for controlling the pitch angle of at least one wind turbine blade in a rotor connected to a main shaft on a wind turbine, the method comprises the steps of determining; a first component of the wind vector which is upwind, horizontal and aligned with the main shaft direction and, a second component of the wind vector which is upwind, perpendicular to the first component of the wind vector, wherein the first component of the wind vector and the second component of the wind vector are determined by use of at least one ultrasonic sensor mounted on the rotor, whereby the pitch angle is controlled based on the first component of the wind vector and the second component of the wind vector.

Abstract: Vertical electrical energy generators are described. A vertical wind turbine system contains one or two vertical turbines, paired aside each other, and a frontal fluid flow diverter for diverting of the running fluid flow, as well as a cover, which covers the upper part of the turbine(s). The system includes an additional rear fluid flow diverter, which is installed behind one or both turbines and is configured so as to divert fluid flow running above the cover to the rear part of the turbine(s), creating secondary fluid flow in the blades of the turbine(s).

Abstract: The present invention relates to a wind turbine with blade pitch system with an angle between the longitudinal direction of the blade and axis of rotation of the bearing of the blade pitch system, disposing the driving plate of the blade pitch system between the blade and the bearing of the blade pitch system.

Abstract: Apparatus for housing a rotatable component and exchanging heat and methods for manufacturing the same are disclosed. The apparatus includes a first casing and a second casing spaced apart from the first casing and defining a gap therebetween. The apparatus also includes a cooling fluid manifold coupled to a source of a cooling fluid, and a stack of plates coupled to the first and second casings and extending therebetween to fill the gap. The first and second casings and the stack of plates define at least a portion of a pressurized containment area therein. Further, the stack of plates includes a bore in which the rotatable component is received and defines process fluid flowpaths configured to direct process fluid to and/or from the rotatable component. The stack of plates is in fluid communication with the cooling fluid manifold and transfers heat from the process fluid to the cooling fluid.

Abstract: A wind turbine blade with a noise reducing device in the form of a serrated trailing edge, whereby said serrated trailing edge comprises stiffening ribs is provided. In one embodiment, the diameter of the stiffening ribs gradually decreases towards the outer end of the trailing edge. In a further embodiment, the stiffening ribs have rounded edges. In still a further embodiment, the serrated trailing edge has teeth, whereby a tooth is provided with a stiffening rib. In another embodiment, a wind turbine including a tower is provided, wherein an electrical generator with a rotor shaft and a hub to which wind turbine blades are connected, and wherein the wind turbine comprises wind turbine blades.