Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend from a first surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.

Abstract: A wind turbine blade includes: a metal receptor including a blade tip of the wind turbine blade; and a blade body portion connected to the metal receptor so as to be positioned on a blade-root side of the metal receptor, the blade body portion having a hollow structure and forming an airfoil shape in a blade tip region of the wind turbine blade with the metal receptor in a joint region to the metal receptor. As seen in a blade-thickness direction of the wind turbine blade, a tangent to a joint line between the metal receptor and the blade body portion at an intersection between the joint line and a leading edge of the wind turbine blade is inclined from a chordwise direction of the wind turbine blade.

Abstract: An impingement insert for an airfoil of a turbomachine component is provided. The insert includes first and second body parts, each having inner and outer surfaces; and first and second contact parts provided on the outer surfaces of the first and the second body parts. The insert includes a flexible mechanical seal part between the body parts. A flow channel for cooling air is defined by the seal part and the inner surfaces of the body parts. One or both of the body parts include impingement holes. The insert has an elastic part connected to the body parts. When the elastic part is subjected to deformation, the elastic part is configured to apply a force, on the first and/or the second body parts, in a direction of increasing a separation between the first contact part and the second contact part.

Abstract: A humidification and air cleaning apparatus is provided, in which a first sweep angle and a second sweep angle are formed at diffuser blades, and an included angle is formed between the first sweep angle and the second sweep angle, such that a phase difference is formed in air passing through the diffuser blades, and thus, air flow noise may be reduced.

Abstract: A rotor and a turbo machine including the same are provided. The rotor includes a disk including a disk slot, a blade including a root member inserted into the disk slot and an airfoil disposed outside the root member in a radial direction of the disk, a locking sheet disposed inside the root member in the radial direction, and a fixing portion disposed inside the root member in the radial direction and configured to fix the locking sheet to the root member.

Abstract: Counter-rotating turbine (C) of a turbomachine (10) extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum on which an inner movable blading (22) is fixed, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum (50) on which an outer movable blading (20) is fixed, the outer movable blading (20) comprising at least one fixing rod (212) extending through an orifice (51) of the outer drum (50), the outer movable blading (20) being fixed to the outer drum (50) via a clamping means (100) fixed to the fixing rod (212) from an outer face of the outer drum (50), a set ring (80) being disposed around the fixing rod (50) in the orifice (51) of the outer drum (50).

Abstract: The disclosure provides a removable support interface for an annular turbomachine casing, the removable interface having a coupling part configured for being mounted on the casing, and at least one attachment element for suspending the casing, orifices arranged in the coupling part the interface having means for locking the coupling part to the casing.

Abstract: A turbine wheel that retains a fixation wire to inhibit the movement of turbine rotor blades along mating grooves includes: multiple tab sections that form housing sections that house part of the fixation wire; and a wire retention pin to retain the fixation wire in the housing sections. The tab section has a pin slot extending from the radially inner end toward the radially outward side. The wire retention pin has a first pin section having a width smaller than the pin slot and a second pin section having a width larger than the pin slot. The first pin section has multiple divided pieces. The wire retention pin is arranged such that the first pin section is positioned in the pin slot and the second pin section is positioned in the housing section, and is fixed to the tab section with the divided pieces bent outward.

Abstract: A turbine guide apparatus, having multiple guide blades. Each guide blade has a first shroud and a second shroud formed on radial ends of a blade leaf having a first carrier for the guide blades. Each guide blade is fastened to the first carrier via a first shroud projection having a second carrier for the guide blades and is fastened on the second carrier via a second shroud projection. The first shroud projection is inserted into a groove of the first carrier in the radial direction and fastened in this groove via a bolt extending in the axial direction through the projection of the first shroud with radial mobility in this groove. The second shroud projection of the guide blade is fastened in the circumferential and radial direction via a pin extending in the axial direction into the projection of the second shroud and the second carrier.

Abstract: A wind turbine having a support structure and a method for operating a wind turbine. The support structure includes a structural component and a reinforcing element. The structural component has fastening holes provided for fastening an operating means. The wind turbine can be operated in at least two states. In an operating state, the reinforcing element is screwed to the fastening portion of the structural component by screw connections which are preloaded in a defined manner using the fastening holes. In a maintenance state, the screw connections are released and the reinforcing element is removed from the structural component of the support structure. A maintenance device can be connected to the fastening portion of the structural component using the fastening holes provided for fastening a maintenance device.

Abstract: A vertical wind turbine that includes a plurality of vertical vanes which can be rotated independently of one another about a respective vane rotational axis by a motor and which are mounted on a common circular path in a rotatable manner about a vertical rotor rotational axis. A method for operating a vertical wind turbine. Angular positions are specified for vertical wind turbine vanes which are mounted in a rotatable manner about a respective vertical rotor rotational axis and which can be rotated about a respective vane rotational axis by a motor. The vertical wind turbine is operated in a particularly efficient and material-preserving manner in that the angular positions of the vanes are specified by at least one respective pitch motor which at least partly supports the respective vane.

Abstract: Embodiments are directed to a blade lock comprising a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position. The blade lock further comprises a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position. A spring-loaded link pivotally connects both the fold lock and the pitch lock and is adapted to provide passive, overcenter locking in the fold-lock position. An actuator is coupled to the pitch lock and is adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions.

Abstract: A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or a downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a compressor including a rotor defining a circumferential direction, wherein the rotor includes a slot, the slot including a first neck portion, a first blade and a second blade disposed circumferentially apart in the slot, and a block disposed in the slot circumferentially between the first blade and the second blade, the block including second neck portion, the first neck portion to at least partially interface the second neck portion.

Abstract: The invention relates to a turbomachine assembly (1) comprising a fan (2) and a booster drum-type part (3), the fan (2) comprising:—blades (20) comprising an airfoil (23) and an extension (30) mounted on and attached to the trailing edge (25) of the airfoil (23),—a fan (2) disc (10) and—a series of inter-blade platforms (16), the extension (30) of each blade (20) extending beyond the downstream face (14) of the fan (2) disc (10) in the direction of the upstream edge (4) of the part (3) and covering, at least partially, the cavity (6) between the fan (2) and the part (3).

Abstract: An airfoil fairing includes an airfoil section that is formed of a fiber-reinforced composite wall. The airfoil section has first and second radial ends, pressure and suction sides, leading and trailing ends that join the pressure and suction sides, an internal cavity, and a rib that extends radially in the internal cavity. The rib has a radial rib end at the first radial end of the airfoil section and extends across the internal cavity from a first rib side at the pressure side to a second rib side at the suction side. The rib defines at the radial end first and second shoulders. The first and second shoulders define a radial notch there between.

Abstract: An edge guard apparatus for an airfoil includes: a body having a nose section with spaced-apart first and second sidewalls extending therefrom, the body defining a cavity between the first and second sidewalls; and internal bracing disposed in the cavity, the internal bracing including at least one cross-member extending between the first and second sidewalls.

Abstract: Provided are fluid exchange apparatuses and methods of exchanging fluids between streams. Exemplary fluid exchange apparatus includes a first interleaved pathway with a plurality of first passages, and a second interleaved pathway with a plurality of second passages, in which the plurality of first passages and the plurality of second passages interleave with one another. Exemplary methods include directing a first fluid through a first interleaved pathway of a fluid exchange apparatus and directing a second fluid through a second interleaved pathway of a fluid exchange apparatus. The first fluid may flow from an upstream portion of a first duct into the first interleaved pathway and may discharge into a downstream portion of the second duct. The second fluid may flow from an upstream portion of the second duct into the second interleaved pathway and may discharge into a downstream portion of the first duct.

Abstract: A computer implemented method for detecting a damage to a gas turbine engine. The gas turbine engine includes a fan and a plurality of turbine stages including a low pressure turbine stage. The fan is drivably coupled to the low pressure turbine stage. The method includes receiving a first signal indicative of a speed of rotation of the fan. The method further includes receiving a second signal indicative of a speed of rotation of the low pressure turbine stage. The method further includes determining a difference metric representative of a difference between the speed of rotation of the fan and the speed of rotation of the low pressure turbine stage. The method further includes determining whether a damage event has occurred based on whether the difference metric passes a threshold.