Abstract: A stator vane formed of CMC has a radially outer platform and a radially inner platform attached to an airfoil. There are a pair of flanges on a side of each of the radially inner platform and radially outer platform which is remote from the airfoil. A first of the pair of flanges is associated with the suction side of the airfoil and a second of the pair of flanges is associated with the pressure side of the airfoil. The flanges extend in a generally axial direction. The first of the pair of flanges extend over at least a majority of the suction side measured between the leading and trailing edge of the airfoil and the second of the pair of flanges extend over at least a majority of the pressure side measured between the leading and trailing edges of the airfoil.

Abstract: A rotor assembly includes: a rotor disc; a plurality of rotor blades fixed to the rotor disc and extending radially outward in a radial direction of the rotor disc; and at least one rolling element configured to roll on a curved surface facing inward in the radial direction of the rotor disc.

Abstract: A vane configured to be disposed in a gas path defined in part by an inner surface of a case of a gas turbine engine is provided. The vane comprises a vane body configured to extend through an aperture in the case and a vane head disposed at an end of the vane body. The vane head has an abutting surface configured to contact an outer surface of the case when the vane body extends through the aperture, and a groove configured to receive a sealing member. The groove opens to the abutting surface and is outwardly open relative to an inner region surrounded by the groove. The groove has an inner seating surface that hinders movement of the sealing member toward the abutting surface and can facilitate installation of the vane in the engine.

Abstract: The invention relates to a retaining device for disassembling a bladed wheel of a turbine engine. The invention is characterized in that the retaining device (100) includes: an inter-blade ring sector (101), a plurality of retaining clips (105), each retaining clip (105) cooperating with one of the damping elements (40), the retaining clips (105) extending radially while being attached circumferentially to the ring sector (101).

Abstract: Provided herein is a shear web support for wind turbine blade. Particularly, the present disclosure provides a frangible shear web support element that is designed to fail under certain specific conditions. The frangible support(s) enhance the structural rigidity of the shear web, allow for one-step mold closures, and rupture or disconnect once a predetermined condition (e.g. load threshold, load orientation/vector) is applied to the support element.

Abstract: A vane arc segment includes an airfoil piece that defines a first platform and an airfoil section that extends from the first platform. The first platform defines a radial flange that extends along at least a portion of a circumferential mate face of the first platform. The airfoil piece is formed of a fiber-reinforced composite that has fibers that are continuous between the airfoil section and the first platform. The airfoil section carries a second platform radially opposite the first platform. The second platform includes a through-hole, and the airfoil section extends through the through-hole.

Abstract: A lifting device for a wind turbine component includes a yoke for connecting the wind turbine component to a crane, the yoke including at least one sensor for measuring the position and/or the speed and/or the acceleration of the wind turbine component at least during a lifting operation of the component is provided. The yoke further includes a pitching device for rotating the wind turbine component around a pitching axis when the wind turbine component is connected to the yoke. The lifting device further includes a controller for controlling the rotation of the pitching device around the pitching axis as a function of the measurement of the at least one sensor.

Abstract: A method and a lifting arrangement for mounting a blade on a wind turbine rotor carried by a wind turbine structure. The method comprises providing a control line guide at the wind turbine structure, the control line guide forming a control line point configured to restrain the control line attaching the control line to the control line point; lifting the blade with an external blade lifting crane while a root end of the blade is guided towards the rotor by use of said control line restrained at said control line point, and connecting said blade to said rotor.

Abstract: A panel for attenuating noise is disclosed comprising a face skin having a first inner surface, a base skin having a second inner surface, a cellular core connected to and forming a plurality of cells between the face skin and the base skin, wherein the cellular core is defined by a cell structure having a plurality of cell walls extending between the face skin and the base skin defining each of the plurality of cells and a septum disposed within each of the plurality of cells, the septum defining an upper chamber proximate the face skin and a lower chamber proximate the base skin, wherein the face skin comprises a plurality of perforations fully through the face skin and in fluid communication with the upper chamber.

Abstract: A steam turbine diaphragm including a diaphragm inner ring, a diaphragm outer ring, and a blade section that are formed integrally includes: a collector ring that retains a seal fin having a radial spill strip structure; and an adapter ring interposed between the diaphragm outer ring and the collector ring. The collector ring and the adapter ring have external radii that are larger than an external radius of the diaphragm outer ring. The diaphragm outer ring and the adapter ring are mutually coupled by a plurality of first bolts. Facing surfaces of the diaphragm outer ring and the adapter ring are kept together tightly and sealed. The collector ring and the adapter ring are mutually coupled by a plurality of second bolts that are inserted at positions on an outer circumference side of the seal fin.

Abstract: A fan section for a gas turbine engine is disclosed herein. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.

Abstract: There is disclosed a shroud for a compressor stator, including: shroud segments extending circumferentially around an axis along portions of a circumference of the shroud. At least one of the shroud segments extending from a first lateral edge to a second lateral edge. The shroud segment has an inner face oriented toward the axis and an opposed outer face oriented away from the axis. At least one opening extends from the inner face to the outer face for receiving a vane of the compressor. A tab protrudes circumferentially from the second lateral edge and away from the first lateral edge. A slot extends circumferentially from the first lateral edge toward the second lateral edge. The tab is matingly received within a slot of an adjacent one of the shroud segments.

Abstract: A shroud for a turbine blade includes a shroud body having an outer side and opposite first and second Z-shaped side edges; a first sealing fin and a second sealing fin extending outwardly from the outer side and spaced apart from each other in a streamwise direction, the first and second sealing fins extending between the first and second side edges of the shroud body; a first ridge extending radially outwardly from the outer side, the first ridge extending from and connecting the first and second sealing fins along the first side edge and having a radial height which varies; and a second ridge extending radially outwardly from the outer side, the second ridge extending from and connecting the first and second sealing fins along the second side edge and having a radial height which varies.

Abstract: A fan section for a gas turbine engine is disclosed herein. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.

Abstract: A blade for a gas turbine engine includes a fiber reinforced ceramic matrix composite structure that provides an airfoil with an exposed exterior airfoil surface and a refractory structure that provides at least an outer portion of a root secured relative to the airfoil.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a vane support and a vane heat shield comprising ceramic matrix composite materials to insulate the metallic materials of the vane support. The turbine vane assembly further includes an aero-load transfer rib located outside of a primary gas path and configured to carry loads applied to the vane heat shield to the vane support.

Abstract: A wind turbine blade and method of manufacture, the blade extending between root and tip ends on a longitudinal axis and having root, transition, and airfoil regions. The blade has a profiled contour with a chord extending between the leading and trailing edges; a blade shell with a first blade shell part with a pressure side and a second blade shell part with a suction side, the blade shell parts extending between root and tip ends and are joined on a primary glue joint; first and second main spar caps integrated in the first and the second blade shell parts, respectively, and have one or more shear webs there between. A third blade shell part may be present and joined to the first blade shell part along a first secondary glue joint and to the second blade shell part along a second secondary glue joint.

Abstract: A root extending from a platform of an airfoil is disclosed. The root may include a first portion having a generally cylindrical shape, and a second portion extending from the first portion to the platform. The second portion may have a circumference larger than a circumference of the first portion.

Abstract: A gaspath component includes a body having at least one internal cooling passage and a metering feature integral to the internal cooling passage. The metering feature and the body are a unitary structure.

Abstract: A rotor assembly includes a plurality of rotor disks that each have a rim portion. The plurality of rotor disks includes a first rotor disk and at least one first bleed air passage that extends through a forward rim portion of the first rotor disk. At least one second bleed air passage that extends through an aft rim portion of the first rotor disk.

Abstract: An airfoil array for a turbomachine, in particular a turbine or compressor stage of a gas turbine.

Abstract: A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

Abstract: A removal device includes a base, a push rod, a rod-moving mechanism and a rod guide. The base is restrained immovably in a first direction. The push rod can protrude from a front surface of the base toward a front side. The rod-moving mechanism is installed on the base. The rod-moving mechanism moves the push rod toward the front side. The rod guide is attached to the base. The rod guide guides movement of the push rod by the rod-moving mechanism in a second direction that forms an acute angle with respect to the first direction.

Abstract: Various embodiments include a system for machining a hole in a turbine blade. The system can include: a mount for engaging a first side of a turbine rotor, the mount including: a drill plate for coupling with the first side of the turbine rotor, the drill plate having: a body; a feed opening on a first side of the body; a passage extending from the feed opening through the body; and a second opening on a second side of the body, the second opening coupled with the passage and positioned to align with the pre-formed hole in the turbine rotor; an alignment bushing for engaging the pre-formed hole in the rotor at a second side of the rotor; and a cutting device for extending through the body and alignment bushing, the cutting device for machining the hole in the blade, the cutting device aligned along a chamfer axis relative to a primary axis of the turbine rotor.

Abstract: A free-tipped axial fan assembly features a shroud barrel comprising an inlet, the radius of said inlet at its upstream end being greater than the radius of said inlet at its downstream end. An angle, in a plane including the fan axis, between the surface of said inlet and the direction of the fan axis varies non-monotonically with respect to a surface coordinate which increases with distance along the surface of the inlet.

Abstract: A turbine blade assembly adapted for use in a gas turbine engine is disclosed in this paper. A primary member of the turbine blade assembly shaped to form an airfoil and comprises ceramic matrix composite materials. A independent platform of the turbine blade assembly is coupled to the primary member of the turbine blade assembly such that the primary member need not be shaped to provide the platform.

Abstract: A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine. The turbine vane is made from ceramic matrix composite materials with three-dimensionally woven or braided reinforcing tows and includes an inner band, an outer band, and an airfoil that extends between the inner band and the outer band.

Abstract: A turbine engine including: rotor blades circumferentially arrayed about a rotor wheel; a connection assembly by which each of the rotor blades connects to the rotor wheel, the connection assembly including: an axially oriented slot formed through a perimeter face of the rotor wheel; a root of the rotor blade installed within the slot, the root being shaped in relation to the slot such that the installation therein forms an axially extending shim cavity between opposing exterior surfaces of the root and the slot; and a shim installed within the shim cavity for restraining movement of the rotor blade relative to the rotor wheel in a radial direction.

Abstract: A shroud (22) comprises shroud bodies (22) fixed to blade tips of blades (18) mounted to a rotor body to extend in a radial direction, the shroud bodies (22) being disposed adjacent to one another in a circumferential direction, wherein each of the shroud bodies (22) includes a circumferential end surface (27, 28) that includes an abutting end surface where adjacent shroud bodies (22) abut, and an opposing surface (34) where adjacent shroud bodies (22) face one another with a clearance (32) therebetween, the opposing surface (34) being contiguous with the abutting end surface; and an outer surface (24) that includes a radially outward protruding protrusion (40) formed to extend along the opposing surface (34).

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 1.13-1.23 inch (28.7-31.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.64-0.74 inch (16.3-18.8 mm). The airfoil element includes at least two of a first mode with a frequency of 1634±10% Hz, a second mode with a frequency of 5611±10% Hz, a third mode with a frequency of 19027±10% Hz, a fourth mode with a frequency of 29268±10% Hz, a fifth mode with a frequency of 33103±10% Hz, a sixth mode with a frequency of 34908±10% Hz and a seventh mode with a frequency of 41277±10% Hz.

Abstract: A system for coating a component is provided. The system includes a feedstock supply, a carrier fluid supply, and a thermal spray gun coupled in flow communication with the feedstock supply and the carrier fluid supply. The feedstock supply contains a substantially homogeneous powder mixture of a first powder and a second powder. The second powder is softer than the first powder and has a percentage by mass of the powder mixture of between about 0.1% and about 3.0%.

Abstract: A turbine stator vane or turbine rotor vane has a body, a channel being adapted for leading a cooling fluid through the body, and a flow adaption feature protruding from the body to the channel in such a manner as to reduce a cross-sectional area of the channel.

Abstract: A vane ring for a gas turbine engine includes an outer end wall and a plurality of spars coupled to the outer end wall. The vane ring further includes an inner end wall positioned radially inward of the outer end wall and coupled to the spars. The outer and inner end walls cooperate to form a flowpath.

Abstract: An airfoil cluster includes an inner diameter platform and an outer diameter platform. A plurality of airfoils extend radially from the inner diameter platform to the outer diameter platform. Each airfoil has a leading edge and a trailing edge, and pressure and suction sides between the leading and trailing edges. At least one of the airfoils includes a recessed portion on the pressure side adjacent to the trailing edge.

Abstract: The present disclosure provides a rotary friction welding process including: providing an outer axisymmetric workpiece having a front first annular weld surface at a radially inward extent and a rear first annular weld surface at a radially inward extent; providing a front inner axisymmetric workpiece, the front inner workpiece having a front second annular weld surface at a radially outward extent of the front inner workpiece; providing a rear inner axisymmetric workpiece, the rear inner workpiece having a rear second annular weld surface at a radially outward extent of the rear inner workpiece; and rotary welding the workpieces together.

Abstract: One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

Abstract: The invention relates to a ventilator wheel which is produced in the form of a radial or a diagonal ventilator wheel, and comprises a bottom disc and a plurality of ventilator blades arranged, on said bottom disc, so as to be distributed about an axial rotational axis, said bottom disc comprising a circumferential radial outer edge section that, when viewed in cross-section, extends in a curved shape in at least some sections and thus forms an elliptical transition of said bottom disc from a radial extension into an axial extension.

Abstract: A method of manufacturing a composite material vane with a covering element, the vane including a platform and a profile extending perpendicularly to the platform, comprises the following steps: providing a covering element and a preform of the vane, the preform comprising a platform portion and a profile portion extending substantially perpendicularly to the platform portion; positioning the covering element against the platform portion so as to obtain an assembly; placing said assembly in a mold; injecting a first resin into the mold so that said resin impregnates and covers the preform and covers at least a portion of the covering element; and carrying out a heat treatment so as to harden the first resin.

Abstract: A structure includes a first body section that has a wall that spans in a vertical direction. The wall has a relatively thin thickness with respect to a length and a width of the wall. A second body section is arranged next to, but spaced apart from, the first body section. A gusset connects the first body section and the second body section. The gusset extends obliquely from the wall of the first body section with respect to the vertical direction such that the gusset is self-supporting. The first body section has a geometry that corresponds to an end-use component exclusive of the gusset.

Abstract: A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.

Abstract: A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.

Abstract: An article includes a ceramic wall that defines at least a side of a passage. The ceramic wall includes a flow turbulator that projects into the passage. The flow turbulator is formed of ceramic matrix composite. A gas turbine engine is also disclosed. The gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. At least one of the turbine section or the compressor section including the article.

Abstract: An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.

Abstract: A workpiece for use with a flash producing welding process comprises a revolute body, a plurality of first attachment portions, a plurality of second attachment portions. The revolute body has an axis of rotation. Each of the first attachment portions has a first radially outer weld joint surface, and each of the second attachment portions has a second radially outer weld joint surface. The revolute body comprises a plurality of first and second stub portions, with each of the first stub portions having a first radially inner weld joint surface, and each of the second stub portions having a second radially inner weld joint surface.

Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.

Abstract: A locking element for a row of blades of a turbomachine includes a number of blades that are inserted by their roots in an anchoring groove on the rotor side and are thereby held in the radial direction in form-fitting manner in the anchoring groove. The locking element has a basic body that has a front bearing surface and a back bearing surface for form-fitting with opposite-lying groove surfaces, a front lock projection and a back lock projection for engaging in opposite-lying recesses of the anchoring groove, and a threaded region for interacting with a tightening element. Access to the threaded region for the tightening element is blocked on one side.

Abstract: A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.

Abstract: A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.

Abstract: A turbomachine assembly is shown, including a rotor and a ring of blades mounted on the rotor. Each blade includes an airfoil portion and a root portion inserted in a circumferential blade-retaining groove of the rotor. The blade-retaining groove includes an enlarged groove portion. The blades in the enlarged groove portion are rotatable around a respective, generally radial axis, to take a position of minimum tangential dimension. At least one removable insert is arranged along the enlarged groove portion, between the root portions of the blades located in the enlarged groove portion and a side wall of the blade-retaining groove, to force and lock the blades in a final assembled arrangement.

Abstract: A stator blades of an axial turbomachine intended to be fitted on a ferrule in an annular row of identical blades. Each blade includes a platform with opposed lateral edges and a screw to the ferrule. The contour of the platform has, at each of the lateral edges, an angular profile designed to mate with the contiguous edge of the platform of an adjacent blade. This feature enables the angular position or pitch of the blade to be set. In a blade row fixed on a stator, mechanical clearances J1, J2, J3 and the fixation screws cause an average angular orientation error. The blades are made with a compensatory angle to offset the angular orientation error.