Abstract: A rotor for an axial turbomachine includes a drum formed of several parts including: composite rings made of composite material and metallic rings interposed between the composite rings. The metallic rings carry the rotor blades. The metallic rings have an axial branch axially overlapping the composite rings and at least one radial branch in contact with the composite rings.

Abstract: A turbine casing comprises: a turbine casing body, which covers a rotor of a steam turbine from the outer side, and in which is formed an exhaust port through which steam is horizontally exhausted; an overhanging part that horizontally widens from the outer surface of the turbine casing body; and a support part that supports the overhanging part on a baseplate; the support part restraining vertical displacement of the overhanging part relative to the baseplate, and securing the overhanging part to the baseplate so as to allow the overhanging part to be horizontally deformed or displaced.

Abstract: A fairing for a power generation machine, the fairing comprising: a first layer comprising a metallic material and defining a first surface and a second opposite surface, the first layer being configured to enable the fairing to be coupled to the power generation machine; and a second layer comprising a composite material and defining a first surface and a second opposite surface, the second layer being coupled to the first layer, the second surface of the second layer defining an external surface of the fairing.

Abstract: A protective cover for a leading-edge of a wind turbine rotor blade is provided. The protective cover is pre-formed into a curved shape to accommodate at least a part of a leading-edge section including the leading-edge of the wind turbine rotor blade to be protected. The protective cover includes a pressure side section, a suction side section and a centerline in-between the pressure side section and the suction side section. The centerline runs in longitudinal direction of the protective cover. Thickness of the protective cover in a cross section of the protective cover in transverse direction has a thickness distribution corresponding to a standardized normal distribution.

Abstract: A convertible ducted fan engine having a shroud, a drive shaft connected to a mechanical fan, and a rotational drive motor configured to rotate the mechanical fan. An embodiment includes a linear drive motor configured to translate the drive shaft and mechanical fan in a direction parallel to a longitudinal axis of the shroud. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

Abstract: A turbomachine vane includes a blading made of composite material with fibrous reinforcement densified by a matrix and an integrated metal leading edge, the blading extending in a longitudinal direction, the leading edge being formed by a metal foil overmolded onto the blading, the foil having a lower wing and an upper wing which extend respectively on the lower and upper faces of the blading while matching an aerodynamic profile of the vane. One of the lower wing and the upper wing has a positioning portion extending in the longitudinal direction, the portion having a flat inner face and an increasing thickness away from the leading edge, and being housed in a correspondingly shaped groove in the blading.

Abstract: A turbocharger device includes a case having a turbine portion and a bearing portion connected to and extending from the turbine portion. The turbine portion defines a cavity that houses a turbine wheel and receives exhaust gas that rotates the turbine wheel. The bearing portion houses a shaft connected to the turbine wheel. The bearing portion has a radial thickness between an exterior surface and an interior surface. The interior surface defines a central channel. The bearing portion holds a bearing system that supports the shaft within the central channel. The bearing portion includes a lattice structure within the radial thickness. The lattice structure is a repeating three-dimensional array of frame segments connected to one another at junctions. The lattice structure engages a turbine back wall that is located between the turbine portion and the bearing portion. The lattice structure defines interstitial spaces between the frame segments.

Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device having a root surface, a plurality of position makers circumferentially disposed on the root surface, the plurality of position markers circumferentially spaced from one another and non-aligned with the longitudinal axis, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.

Abstract: A fan blade for an airplane turbojet, the blade including an airfoil extending axially between a leading edge and a trailing edge and including a plurality of airfoil sections stacked radially between a root section and a tip section. All of the airfoil sections situated between the root section and an airfoil section situated at a radial height corresponding to 30% of a total radial height of the airfoil possess a skeleton curve having a point of inflection.

Abstract: A fan including a main body with a vertical development with respect to a support base on which the main body is located in a condition of use. The fan has a rear longitudinal aperture, for the emission of a stream of air toward the outside, and also comprises an air suction and distribution unit, and a channeling element (20) positioned in proximity to the longitudinal aperture (16). The channeling element allows to divert the stream of air (W) so that it is conveyed toward a front part of the fan (10), at least partly following a profile (40) of an external surface (22) of the main body (12).

Abstract: A shear web foot for a wind turbine blade is described. The shear web foot extends longitudinally and comprises a base for attaching to an internal surface of the blade and first and second side walls. The side walls extend respectively from opposite longitudinal sides of the base. At least part of each side wall is inclined relative to the base and inclined towards the other side wall. A web-foot interior is defined at least in part by the base and the first and second side walls. One or more internal walls are located in the web-foot interior. The one or more internal walls extend between the base and the first and/or second side walls and are spaced apart from the first and second side walls to define a plurality of chambers within the web-foot interior.

Abstract: A boost compressor assembly may comprise an outer annular structure and a plurality of blades. Each blade in the plurality of blades may be moveably coupled to the outer annular structure. The plurality of blades may be configured to deploy in response to the boost compressor assembly rotating. The plurality of blades may be configured to retract when the boost compressor assembly stops rotating.

Abstract: A fan includes a main body with a vertical development with respect to a support base on which the main body is located in a condition of use. The main body defines an internal housing compartment.

Abstract: A method for protecting a wind turbine from extreme and fatigue loads associated with high wind speed events includes receiving, via a wind turbine condition estimator programmed in a turbine controller of the wind turbine, operating data indicative of current wind turbine operation. Further, the method includes determining, via the wind turbine condition estimator, a plurality of estimated wind turbine conditions at the wind turbine by solving a control algorithm having one or more equations using the operating data. The estimated wind turbine conditions include, at least, an estimated wind speed at the wind turbine and a loading proxy of the wind turbine. As such, the method includes implementing, via the turbine controller, a corrective action only when each of the estimated wind turbine conditions indicates that one or more loading conditions of the wind turbine exceeds a predetermined limit.

Abstract: A wind turbine (10) includes a main shaft (34) including a front end (34a), the front end (34a) including a first connecting structure (36). A rotor hub (22) includes a second connecting structure (40), wherein the second connecting structure (40) of the rotor hub (22) is fixed to the first connecting structure (36) of the main shaft (34). A plurality of blades (24) is coupled to the rotor hub (22). A rotor locking disc (32) is carried on the main shaft (34), the rotor locking disc (32) having an outer circumference (32a) and a plurality of recesses (50) on the outer circumference (32a), the recesses (50) having openings (50a) intersecting with the outer circumference (32a). At least one rotor locking pin (30) is movable between a disengaged position relative to at least one of the recesses (50) and an engaged position wherein the pin is located at least partially in one of the recesses (50) for locking the rotor hub (22) against rotation.

Abstract: Examples of the present disclosure generally relate to wind turbine blades configured to minimize or eliminate buildup of ice on the blades. In order to maintain an ice free surface on a wind turbine blade, one or more ETH panels are embedded in the wind turbine blade to heat the wind turbine blade. One or more busbars are electrically connected to each of the one or more ETH panels for conducting electrical power to the ETH panels. The busbars may be disposed in an overlapping configuration to provide uniform heating of the wind turbine blade.

Abstract: A component for a gas turbine engine, comprising: a first wall defining an exterior surface of the component; a second wall, arranged such that a coolant channel is defined by the space between the first and second walls; and a plurality of apertures provided through the first wall to connect the coolant channel to the exterior surface of the component; wherein adjacent at least one aperture the coolant channel comprises a flow modifier, configured to locally change the pressure of the coolant flowing in the coolant channel in the region of the aperture relative to a region of the coolant channel adjacent another aperture.

Abstract: A two-stage, high speed fluid compressor including a case having a fluid inlet and a compressed fluid outlet and containing a shaft rotatably mounted about a longitudinal axis, a first compression wheel and a second compression wheel mounted back-to-back on the shaft, the first compression wheel forming a first compression stage and the second compression wheel forming a second compression stage, and a motor positioned between the first compression wheel and the second compression wheel and arranged to rotate the shaft. The case includes an inner through housing inside which is arranged at least the motor, the inner housing having an inner wall arranged to form, with the motor, channels between at least the inner wall and the motor, the channels extending to cool the motor in contact with the fluid flowing in the channels.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction, and the airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core, and the core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. The first and second ligaments define respective sets of bores, and the respective sets of bores are aligned to receive a common set of retention pins.

Abstract: A gas turbine engine including a compressor section, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a plurality of gas path components exposed to a primary fluid flowpath through the compressor section, the combustor section and the turbine section. At least one of the gas path components includes an exterior facing surface, a lattice structure extending outward from the exterior facing surface, the lattice structure being integral to the exterior facing surface, and a thermal barrier coating adhered to at least a portion of the exterior facing surface and the lattice structure.