Abstract: A water-cooled compressor housing assembly for a turbocharger includes a compressor housing that defines an open-ended cavity extending axially downstream into the compressor housing, and a separately formed cover that is affixed to the compressor housing so as to close the open end of the cavity and thereby define a coolant passage for a liquid coolant to be circulated through. A coolant inlet and a coolant outlet are provided for supplying coolant into and exhausting coolant from the coolant passage. The compressor housing has a simplified geometry that is manufacturable by sand casting without needed a sand core for the coolant passage, or by die casting.

Abstract: A turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending concentrically around the axial direction. The turbomachine includes a nozzle having an inner platform, an outer platform, and an airfoil. The airfoil includes a leading edge, a trailing edge downstream of the leading edge, a pressure side surface, and a suction side surface opposite the pressure side surface. The trailing edge defines a circular arc between the inner platform and the outer platform.

Abstract: A blade and gas turbine include a stationary blade main body provided internally with cavities, and an inner shroud linked to an end portion, in the longitudinal direction, of the stationary blade main body, and which is internally provided with an inner shroud cooling passage with which a first cavity is in fluid communication. The inner shroud is provided, in front edge corner portions, with a first chamfered portion intersecting a front surface, a side surface, and an upper surface, and first cooling holes in fluid communication with the inner shroud cooling passage are provided in the first chamfered portion.

Abstract: A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

Abstract: A rotor assembly includes a rotor having a dovetail slot. The dovetail slot includes a plurality of recesses and a first radially innermost surface. A rotor blade includes an airfoil that extends radially outward from a platform and a dovetail that extends radially inward from the platform. The dovetail includes a plurality of projections extending in opposite directions that are received by the plurality of recesses of the dovetail slot. The dovetail further includes a leading edge surface, a trailing edge surface, and a second radially innermost surface. The second radially innermost surface defines a groove from the leading edge surface to the trailing edge surface. The shim is positioned within the groove and between the first radially innermost surface of the dovetail slot and the second radially innermost surface of the dovetail.

Abstract: Provided is a stepped conductivity arrangement between a carbon-based element and a down conductor of a wind turbine rotor blade, which stepped conductivity arrangement includes a transition interface arranged to electrically connect a first electrically conductive part and a second electrically conductive part, wherein the first electrically conductive part extends from the down conductor, the second electrically conductive part extends from the carbon-based element, and wherein the electrical conductivity of the transition interface decreases in the direction of the second electrically conductive part. The embodiments further describe a wind turbine rotor blade comprising such a stepped conductivity arrangement and a method of providing such a stepped conductivity arrangement.

Abstract: An example embodiment of a turbine engine assembly includes a low spool including a low spool accessory drive gear driven by a low rotor shaft, a high spool including a high spool accessory drive gear driven by a high rotor shaft concentric around a portion of the low rotor shaft, and a differential gear assembly adapted to offtake power from rotation of one or both of the low spool and the high spool to drive one or more accessory loads. The differential gear assembly includes a differential bullgear and one or more idler gears each including a plurality of teeth meshed with the low spool accessory drive gear and the high spool accessory drive gear, and a bearing surface. The differential bull gear includes a plurality of teeth and a corresponding at least one bearing surface engaging with the bearing surface of each of the one or more idler gears. The plurality of teeth are adapted to mesh with an accessory drive system to transfer the power offtake and drive the one or more accessory loads.

Abstract: A negative hinge offset rotor head for a coaxial helicopter, the rotor head having two or more flapping rotor blades having outer and inner tips, the inner tips rotatably attached to a hinge attachment rotated by a driveshaft where the driveshaft is positioned between the rotor blades and the rotor blades' respective hinge attachment.

Abstract: A non-contact seal assembly for sealing a gap between relatively rotatable components in a gas turbine engine is presented. The non-contact seal assembly includes a primary seal having a radially movable seal shoe, a mid-plate, an aft secondary seal radially movable along with the seal shoe, a forward secondary seal and a U-shaped seal carrier for holding the components together using pins. The seal shoe includes a plurality of seal shoe segments. The aft secondary seal includes a plurality of aft secondary seal segments. Each aft secondary seal segment is attached to each seal shoe segment. Each aft secondary seal segment includes at least a notch at outer radial side to receive the pin for accommodating radial movement of the seal shoe segment.

Abstract: A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface, are circumferentially spaced around the circular disk, and extending along the longitudinal axis from a first end portion to a second end portion. At least part of the first end portion and/or of the second end portion comprises a material having higher magnetic permeability than that of a remainder of the position markers.

Abstract: A method of controlling a wind turbine for the avoidance of edgewise vibrations. The method comprises the steps of determining a whirling mode frequency of a rotor blade of the wind turbine; determining a rotational frequency of the rotor blade corresponding to the speed of the rotor blade; determining a threshold value for the whirling mode frequency based on the rotational frequency; and, reducing the speed of the rotor blade if the whirling mode frequency substantially equals or is less than the threshold value.

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 gas turbine engine rotor having an axis, comprising: a body about the axis having an inner surface, a seat having an outer seat edge at a first radial location surrounded by the inner surface at a second radial location, a lip along the inner surface having an inner lip edge spaced axially away from the seat to define a gap, the lip at a rated axial location between the inner lip edge and the seat facing toward the seat at a normal angle; a damper in the gap having first and second damper surfaces, the first damper surface adjacent the seat; and a split ring in the gap adjacent the second damper surface, having an outer ring edge spaced from the inner surface, engaging the lip at the rated axial location and resiliently expandable against the lip deflects the split ring to load the damper against the seat.

Abstract: Disclosed is wind turbine blade and a spar beam for structurally connecting a first blade section and a second blade section of a wind turbine blade. The spar beam comprises a first fibre reinforced element extending parallel to a spar beam axis. The spar beam comprising a conductive beam sheath circumscribing at least a beam sheath angular distance of the spar beam about the spar beam axis and longitudinally extending from a fourth beam axis position to a fifth beam axis position. The first fibre reinforced element is positioned between the conductive beam sheath and the spar beam axis.

Abstract: A fan frame body structure includes a first frame body. The first frame body has a first upper end, a first lower end, a first frame wall and a first main flow way. The first main flow way passes through the first frame body and is formed with a first main inlet and a first main outlet respectively at the first upper end and the first lower end. A first subsidiary flow way is disposed in the first frame wall. The first subsidiary flow way is in parallel the first main flow way. The first subsidiary outlet is positioned at the first upper end of the first frame body in flush with and in adjacency to the first main inlet.

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: 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 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: The present invention relates to a wind turbine blade (10) comprising a shell body with at least one pressure side shell member (36) and at least one suction side shell member (38), and a plurality of shear webs (70) arranged within the shell body. The plurality of shear webs (70) is successively arranged spanwise within the shell body such that adjacent shear webs overlap along part of their spanwise extent (L), wherein a gap (88) in the chordwise direction is provided between adjacent shear webs (70).

Abstract: A turbine engine having an engine core, a first seal structure, a plurality of circumferentially arranged vanes, a plurality of struts, and a second seal structure. The engine core can define a rotor and a stator having a casing. The first seal structure can include a finger seal projecting from the rotor. The plurality of circumferentially arranged vanes can include an uppers band mounted to the casing, and a lower band located radially above the finger seal. At least some of the struts of the plurality of struts can extend through the plurality of circumferentially arranged vanes. The second seal structure can form a seat with the lower band.