Abstract: A turbine assembly having a hollow aerofoil, an impingement tube, and an impingement tube sleeve. The sleeve has as least one impingement tube sleeve segment, the aerofoil having at its interior surface longitudinal ribs extending from a leading edge towards a trailing edge. A first impingement tube sleeve segment provides a slotted flow blocker at a surface of the first impingement tube sleeve segment, the first impingement tube sleeve segment inserted into the hollow aerofoil such that the ribs of the hollow aerofoil engage with corresponding slots of the slotted flow blocker and such that the surface of the first impingement tube sleeve segment rests on the ribs. The impingement tube is inserted into the hollow aerofoil such that the at least one impingement tube sleeve segment is arranged between the interior surface of the hollow aerofoil and an exterior surface of the impingement tube.

Abstract: Coating system (1) for coating a surface (3) of a substrate (5), the coating system (1) comprising; a coating (7), and an adhesive layer (9), that is disposed between the substrate (5) and the coating (7), wherein the adhesive layer (9) comprises a first adhesive layer portion (13) adjacent the substrate (5) and a second adhesive layer portion (15) adjacent the coating (7) and a carrier (11) placed between said first and second adhesive layer portions (13, 5), wherein the first adhesive layer portion (13) is composed of a first adhesive layer material, wherein the second adhesive layer portion (15) is composed of a second adhesive layer material, wherein the first adhesive layer material and the second adhesive layer material is having an adhesive or bond strength to the surface (3) of the substrate (5) and to the coating (7) respectively that exceeds their respective cohesive or tensile strength, wherein the first and second adhesive layer materials and carrier (11) combination is configured for having an ad

Abstract: A configuration and manufacturing method for a trailing edge of an aircraft airfoil, such as a control surface or a lifting surface is described. The trailing edge is formed and configured by upper and lower composite covers, which are stitched to each other with a metallic wire, such as the metallic wire is electrically in contact with upper and lower metallic meshes to provide electrical continuity between meshes. According to a method, upper and lower covers configuring the trailing edge, are stitched with the metallic wire before curing the covers, so that the metallic wire gets embedded within the composite material. A trailing edge for an aircraft airfoil, which is easy to manufacture and that at the same time fulfills aerodynamic, mechanical and electrical conductivity requirements is described.

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: Provided is a turbine blade of a gas turbine including a turbine blade part having an airfoil shape including an internal cavity therein, a cast tip disposed at an upper portion of the turbine blade part, and a braze joint to attach the turbine blade part and the cast tip to each other. The turbine blade part and the cast tip has substantially the same cross-sectional shape in a top plan view. In addition, the turbine blade part further includes a protrusion disposed at a surface where the turbine blade part is attached to the cast tip. In a similar manner, the cast tip may have a concave portion at a surface where the cast tip is attached to the turbine blade part to allow the concave portion to be coupled to the protrusion of the turbine blade part.

Abstract: Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position of one or more propeller blade treatments of a propeller blade of an aerial vehicle during operation of the aerial vehicle. For example, the propeller blade may have one or more propeller blade treatments that may be adjusted between two or more positions. Based on the position of the propeller blade treatments, the airflow over the propeller is altered, thereby altering the sound generated by the propeller when rotating. By altering the propeller blade treatments on multiple propeller blades of the aerial vehicle, the different sounds generated by the different propeller blades may effectively cancel, reduce, and/or otherwise alter the total sound generated by the aerial vehicle.

Abstract: A fixture assembly includes a first fixture portion, a second fixture portion that interfaces with the first fixture portion, and a sub-fixture movably mounted to the first fixture portion. A multiple of actuators selectively move the sub-fixture toward the second fixture portion. A method of manufacturing a fan blade includes deploying the sub-fixture from the first fixture portion to effectuate a peripheral diffusion bond to join the blade body and the cover of the fan blade.

Abstract: A composite blade is formed by laying up composite material layers in which reinforcement fibers are impregnated with resin in a thickness direction of the blade. The composite blade includes a blade root on a base end side, an airfoil on a tip side, a first lay-up in which some composite material layers are laid up in the blade root so as to space parts of the composite material layers to form spacing parts and to extend from the distal toward the base end side in the thickness direction, and second lay-ups in which some composite material layers are laid up in the spacing parts so as to be lined up in the thickness direction. Among the second lay-ups, a second lay-up closer to a center side than to an outer side in the thickness direction is a larger distance from a proximal position to a top position.

Abstract: A rotor blade component for a wind turbine includes a first structural component, such as a spar cap, formed from a plurality of stacked pultruded members. A second structural component, such as a shear web, is fixed to the first structural component at a joint interface. One or more webs form the joint interface, wherein each of the webs has a first section bonded between at least two of the pultruded members in the first structural component and a second section extending across the joint interface and bonded onto or into the second structural component.

Abstract: A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.

Abstract: A jointed wind turbine rotor blade includes a first blade segment and a second blade segment extending in opposite directions from a chord-wise joint. A beam structure extends span-wise from the first blade segment into a receiving section formed in the second blade segment. The receiving section includes opposite spar caps and opposite interconnecting webs. The spar caps have a constant thickness along the receiving section where the spar caps overlap with the beam structure and are formed of a material or combination of materials along the receiving section to produce a desired stiffness of the spar caps along the receiving section. The webs have a reduced amount of conductive material adjacent to a chord-wise joint between the blade segments.

Abstract: An airfoil assembly includes an airfoil body extending from a root to a tip defining a longitudinal axis therebetween. The airfoil body includes a leading edge between the root and the tip. A sheath is direct deposited on the airfoil body. The sheath includes at least one metallic material layer conforming to a surface of the airfoil body. In accordance with another aspect, a method for assembling an airfoil assembly includes directly depositing a plurality of material layers on an airfoil body to form a sheath. In accordance with some embodiments, the method includes partially curing the airfoil body.

Abstract: A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip made of materials with different elasticity and mounted to the core leading edge.

Abstract: A fan blade includes a blade body, a composite segment and a cover. The blade body extends from a blade root to an opposed blade tip along a longitudinal axis. The blade body defines a leading edge and a trailing edge. A first airfoil surface extends from the leading edge to the trailing edge. A pocket is defined between the leading edge, the trailing edge, the blade root and the blade tip. The pocket has a bottom surface that opposes the first airfoil surface across the blade body. The composite segment is disposed in the pocket. The cover is mounted to the composite segment and to the blade body to form a second airfoil surface opposed to the first airfoil surface.

Abstract: A ram air turbine (RAT) is provided and includes a turbine assembly including blades and a hub to which the blades are connected, a generator or a pump and a drivetrain mechanically interposed between the turbine assembly and the generator or the pump. Each blade includes an exterior, airfoil-shaped structure defining an interior and support structures disposed within the interior which connect with an inner surface of the exterior, airfoil-shaped structure and which define hollow regions within the interior.

Abstract: An airfoil includes an airfoil section that extends in a radial direction from a platform to a tip, and extends in a thickness direction between a pressure side and a suction side that meet together at both a leading edge and a trailing edge. A purge partition radially divides the airfoil section. A perimeter of the purge partition follows along external walls of the airfoil section. The tip defines a tip pocket that extends radially inwardly from the tip to a floor. The airfoil section includes at least one internal cooling circuit and a purge cavity opposed to the at least one internal cooling circuit along the purge partition, with the purge partition bounded by the floor. The purge partition defines a first set of apertures that fluidly couple the at least one internal cooling circuit and the purge partition. A method of cooling a gas turbine engine component is also disclosed.

Abstract: A method of manufacturing a protective edge for a blade, wherein a protective edge (30) made of an anodizable metal is provided, and that protective edge (30) undergoes a micro-arc oxidation electrolytic treatment. Protective edge (30) manufactured using said method.

Abstract: A propeller component, for example a propeller blade airfoil, includes an external surface exposed in use to an oncoming airstream (A), and a protective polymeric film applied over substantially the entire exposed external surface of the component.

Abstract: A blade for a gas turbine engine includes composite layers including neck plies and tooth plies that are flared relative to the neck plies. The neck plies and tooth plies respectively provide a neck and a root. The root includes a tooth. A Wedge is provided by wedge plies adhered over the root and the tooth.

Abstract: A rotor blade assembly for a wind turbine may include a first blade segment having a first joint end and a second blade segment having a second joint end, with the blade segments being coupled together such that the first and second joint ends are located at or adjacent to a joint interface between the blade segments. The blade assembly may also include a pre-loaded beam extending outwardly from the second blade segment across the joint interface such that the pre-loaded beam is received within the first blade segment. The pre-loaded beam may be compressed between the opposed internal structural components of the first blade segment such that a first engagement interface is defined between a first side of the pre-loaded beam and the first internal structural component and a second engagement interface is defined between an opposed second side of the pre-loaded beam and the second internal structural component.

Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.

Abstract: A sheath, for protecting the leading edge of airfoils used in gas turbine engines, may have a solid member, a pressure side flank and a suction side flank. The solid member may form an outer edge, which may include a main portion and a projecting portion. The projecting portion may have a variable dimension. The pressure side flank and suction side flank may project from the solid member opposite the outer edge. The pressure side flank and suction side flank may form a receiving cavity for receiving an airfoil.

Abstract: A fan blade for a fan of a gas turbine engine is described which includes an airfoil having an inner core and an outer shell composed of different metals, and a galvanic separator therebetween. The galvanic separator including an adhesive layer covering said at least a portion of the inner core, and a non-conductive fabric covering the adhesive layer. A plurality of solid metal particles may be disposed on an outer surface of the non-conductive fabric layer, between the non-conductive fabric layer and the outer shell.

Abstract: A gas turbine engine having a combustor, turbine and transition duct to channel hot gas from combustor to turbine. The transition duct has an internal surface on which the hot gas impinges causing a varying temperature profile. A thermal barrier coating is located on the internal surface having a first and second thermal barrier coating patch. The first patch having a first thickness located on the internal surface and within a first area subject to a higher temperature than an uncoated part and bounded by a first isotherm of a first temperature. The second patch having a second thickness located on the internal surface and within a second area subject to a higher temperature than the uncoated part and bounded by a second isotherm of a second temperature. The second temperature is higher than the first temperature and the second thickness is thicker than the first thickness.

Abstract: A method of assembling an airfoil includes depositing a bonding material on a first end of the tip portion and shaping the bonding material to form a first plurality of features. The first plurality of features correspond to a second plurality of features on a second end of the body portion. The method also includes positioning the first end relative to the second end such that the first plurality of features and the second plurality of features interlock. The method further includes coupling the first end of the tip portion to the second end of the body portion.

Abstract: A method for manufacturing a rotor blade of a wind power plant which has an area close to the blade root in which the rotor blade has an obtuse rear edge. The method includes manufacturing a half-shell on the pressure side and a half-shell on the suction side, introducing and adhesively bonding filler bodies into at least one section of the area of the obtuse rear edge of the pressure-side half-shell and the suction-side half-shell, wherein the sections with the filler bodies lie opposite one another in the assembled rotor blade, assembling and positioning the half-shells relative to one another, wherein an adhesive gap which is delimited by the first adhesive surfaces of the filler bodies remains between the filler bodies, and introducing an adhesive medium into the adhesive gap. Also a rotor blade manufactured according to the method, and a wind power plant including such a rotor blade.

Abstract: A method of making a fan blade may include the steps of forming a core comprising fibrous material, and placing a first layer of dry fiber tows over the core using a robot. The first layer of dry fiber tows may be substantially un-crimped and may have a thermoplastic coating. A second layer of dry fiber tows may be placed over the first layer of dry fiber tows using the robot. The second layer may be un-crimped and coated similar to the first layer. The core, the first layer, and the second layer may be molded using resin transfer molding. The first layer may be placed over the core in a curved configuration. The core may include a three-dimensionally woven core formed on a loom and/or a plurality of layers of dry fiber tows placed by the robot.

Abstract: A turbine airfoil includes a turbine component that includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a near wall source cavity disposed within the turbine component, and the near wall source cavity receives cooling air, and a second near wall cooling cavity disposed within the turbine component. The turbine airfoil further includes a first circuit completion plate disposed on a first end of the turbine component, and the first circuit completion plate fluidly couples the near wall source cavity to the second near wall cooling cavity.

Abstract: An airfoil includes an airfoil section defining an airfoil profile, the airfoil section including a core structure and a plurality of rods disposed adjacent the core structure.

Abstract: A fan blade includes a metallic body, a first composite cover, and a second composite cover. The metallic body may have a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, in accordance with various embodiments. The first and second retention slots may extend from the first side to the second side of the metallic body. The first composite cover may be coupled to the first side of the metallic body and may include a plurality of first fingers that extend through the first retention slots and are coupled to the second side of the metallic body. The second composite cover may be coupled to the second side of the metallic body and may include a plurality of second fingers that extend through the second retention slots and are coupled to the first side of the metallic body.

Abstract: A joint assembly for joining rotor blade segments of a wind turbine rotor blade includes a female structural member secured within a first rotor blade segment. The female structural member includes first bore holes on opposing sides thereof that are aligned in a chord-wise direction. Further, the joint assembly includes a male structural member extending longitudinally from an end face of a second rotor blade segment. As such, the male structural member is received within the female structural member of the first rotor blade segment such that the first and second rotor blade segments are aligned and connected. The male structural member includes second bore holes on opposing sides thereof. Further, the second bore holes are aligned with the first bore holes. Moreover, the joint assembly includes at least one chord-wise extending pin extending through the first and second bore holes so as to join the first and second rotor blade segments.

Abstract: The application describes methods of making composite bodies including fibre-reinforced composite material with carbon fibre reinforcement and also a metal-containing portion (4). The metal-containing portion (4) is formed by laying up metal reinforcement elements, such as tapes of titanium alloy, among the carbon fibre reinforcement tapes which make up the composite body. The proportion of metal reinforcement may increase progressively towards the surface and/or towards an edge (14) of the composite body. In an example, metal leading and trailing edges (14,15) of a fan blade (1) are integrally formed in this way.

Abstract: A fan blade having a damping system is provided. The fan blade comprising: a fan blade body having one or more compartments within the fan blade body; a damping material located within at least one of the one or more compartments; one or more partial ribs originating at the fan blade body and extending into at least one of the one or more compartments, wherein each of the one or more partial ribs terminate at a distal end; and one or more damping plates, wherein each of the one or more damping plates are attached to a distal end of a partial rib, wherein the damping material is located between the damping plate and the fan blade body.

Abstract: A method for balancing segmented rotor blades for a wind turbine may include determining a weight for each of a plurality of blade segments, wherein each blade segment extends between a first end and a second and is configured to form a common spanwise section of a segmented rotor blade between the first and second ends. The method may also include determining an initial static moment for each blade segment based on the weight of the blade segment, wherein the initial static moment of at least one of the blade segments differing from the initial static moments of the remainder of the blade segments. Additionally, the method may include adding mass to each of the blade segments to increase the initial static moment for each blade segment to a predetermined static moment, wherein the predetermined static moment is greater than each of the initial static moments of the blade segments.

Abstract: A set of stationary blades for a steam turbine is provided. At least one of the stationary blades includes a suction side and an opposite pressure side, and a plurality of ejection channels defined in the at least one stationary blade. Each of the plurality of ejection channels extends through an outer surface of the pressure side, and each of the plurality of ejection channels is coupled in flow communication to a blade inlet aperture.

Abstract: An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.

Abstract: The invention relates to a blade made of composite material, provided with a reinforcement (17) made of a stronger material with regard to a leading edge (5) likely to be struck by solid objects, which comprises, under the aerodynamic portion of the blade, extensions (18, 19) attached to the blade root. According to the invention, the extensions (18, 19) are dissymmetric, the extension (18) located on the suction side being generally further back from the leading edge (5) than the extension (19) on the pressure side.

Abstract: The present invention provides a stator component of a vacuum pump, which is suitable for reducing the fracture energy (energy of fracture that occurs when a rotor of the pump is damaged during its rotation) and the size of the pump, and also provides a vacuum pump having this stator component. In the vacuum pump, a spacer or of a thread groove pump stator, which is a stator component forms a gap satisfying the following <<condition>> between an outer circumferential surface of each of housed in a pump case of the vacuum pump, and an inner circumferential surface of the pump case, with the stator component being housed in the pump case. <<Condition>> 2d/D??max, where D is the outer diameter of the stator component (spacer or thread groove pump stator), d is the width of the gap, and ?max is the breaking elongation of the stator component.

Abstract: A method for manufacturing a component having a defined geometry includes: a) defining a pre-component geometry including interim shape elements and additional, sacrificial elements for supporting interim elements; b) on a base plate, depositing multiple layers of a powder including a material from which the pre-component will be manufactured; c) sintering the powder to form the pre-component to the defined geometry; d) removing at least some of the sacrificial elements from the pre-component; e) subjecting the remaining pre-component from step d) to a HIP step; and f) removing remaining sacrificial elements from the pre-component product of step e) to provide a component to the defined component geometry. In the definition of the pre-component geometry, the interim elements differ from the corresponding final shape elements in the defined component geometry such that during the HIP step, the interim shape elements adjust to form final shape elements in the defined component geometry.

Abstract: Turn caps for airfoils of gas turbine engines including cavity sidewalls, a first turn cap divider extending between the cavity sidewalls and defining a turning cavity between the first turn cap divider and the cavity sidewalls, and a second turn cap divider disposed radially inward within the turning cavity. A first turning path is defined between the first turn cap divider and the second turn cap divider and a second turning path is defined radially inward of the second turn cap divider and a merging chamber is formed in the turn cap wherein fluid flows through the first turning path and the second turning path are merged, the merging chamber, the first turning path, and the second turning path forming the turning cavity.

Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A plurality of separate spacers (320; 380; 400) are between the sheath and the substrate and have a plurality of gaps between the spacers.

Abstract: An airfoil for a turbine engine includes an airfoil body with a cover mounting support, a first cover, and a second cover. The airfoil body includes a solid perimeter portion surrounding a recess formed into at least one of a suction side and a pressure side of the airfoil body, while the cover mounting support extends through the recess. The first cover can be engaged with a first edge of the recess and joined to a first portion of the cover mounting support by a first stir weld. The second cover can be engaged with a second edge of the recess, and joined to a second portion of the cover mounting support by a second stir weld.

Abstract: An airfoil with dual wall cooling for a gas turbine engine comprises a spar having pressure and suction side walls that meet at leading and trailing edges of the airfoil, with a tip extending therebetween. An interior of the spar includes a coolant cavity, and each of the pressure and suction side walls includes an arrangement of pedestals on an outer surface thereof and a plurality of cooling holes in fluid communication with the coolant cavity. A pressure side coversheet overlies the pressure side wall and terminates in a radial direction short of the tip of the spar to form a shelf extending along a chordal direction. Flow channels between the pressure side wall and coversheet are configured to direct coolant from the cooling holes to radial flow outlets adjacent to the shelf. A suction side coversheet overlies the suction side wall, and a coolant circuit between the suction side wall and coversheet does not include radial coolant outlets.

Abstract: A lightweight fan blade for use in turbofan gas turbine engines is disclosed. The fan blade includes a metallic body having a pressure side and a suction side. The suction side of the body includes one or more cavities. A cover is then attached to the suction side of the body to cover or enclose the one or more cavities. The cover includes one or more transverse weakened areas, such as a transverse slit so that the cover separates into one or more smaller segments in the event of a foreign object damage (FOD) or fan blade out (FBO) event occurs. The smaller segments of the cover are less likely to do damage to downstream components such as the low and high-pressure compressors. A single smaller segment of the cover may allow for continued operation of the engine because the imbalance created by the event may be tolerated by the engine.

Abstract: A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening and at least one cavity for purposes of reducing the weight of the fan blade. The cover overlays the opening and includes a peripheral edge that is received in a slot defined by the body. The cavities are filled with a sacrificial material.

Abstract: A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side. The body also includes a leading edge, a trailing edge, a distal tip and a base that is coupled to a hub. The suction side of the body includes at least one cavity for purposes of reducing the weight of the fan blade. The at least one body is surrounded by a slot that extends outwardly away from the cavity. A lip that extends inwardly towards the body further defines the slot. A cover is provided that overlays the cavity and includes a peripheral edge that is received in the slot and that is at least partially covered by the lip for a robust connection between the fan blade body and the cavity cover.

Abstract: The present disclosure is directed to a method for manufacturing a thermoset component having a weldable thermoplastic interface. The method includes forming a polymerized thermoplastic component having a removable protective layer on a portion thereof. Another step includes placing a plurality of dry plies and the thermoplastic component into a mold of the thermoset component with the removable protective layer facing an outer surface of the thermoset component mold. Thus, the method further includes co-infusing the dry plies and thermoplastic component with a resin material so as to form the thermoset component having a weldable thermoplastic interface.

Abstract: The disclosure describes techniques for joining a first part including a ceramic or a CMC and a second part including a ceramic or a CMC using brazing. A technique may include positioning a filler material in a joint region between the first and second parts and a metal or alloy on a bulk surface of the filler material. The metal or alloy may be locally heated to melt the metal or alloy, which may infiltrate the filler material. A constituent of the molten metal or alloy may react with a constituent of the filler material to join the first and second parts. Another technique may include depositing a powder that includes the filler material and the metal or alloy in the joint region. Substantially simultaneously with depositing the powder, the powder may be locally heated. A constituent of the molten metal or alloy may react with a constituent of the filler material to join the first and second parts.

Abstract: A device for protecting an airfoil element made of a complex comprising a polymer film, a metal strip deposited on a part of the polymer film and an adhesive element to attach the polymer film on the airfoil element. The polymer film forms a protection against sand abrasion. The metal strip forms a protection against water abrasion of the airfoil element on which the complex is attached.

Abstract: A composite aerofoil, the aerofoil having a leading edge, a trailing edge a pressure side and a suction side and comprising an outer erosion protection layer along one or both of the pressure side or suction side, a structural core having a plurality of resin impregnated plies of unidirectional fibers, and between the outer erosion protection layer and the structural core a woven composite impregnated with a resin having a modulus of elasticity greater lower than that of the resin impregnating the plies in the structural core.