Abstract: A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.

Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.

Abstract: A spinner is described that can provide aerodynamic advantages for vertical takeoff and landing (VTOL) aircraft. The spinner can be shaped with multiple faces divided by chines. The chines can run down the edge of the spinner to fairings that can cover rotor blades and/or couplings between rotor blades and the rotor hubs of the aircraft. During forward flight the rotor blades can be folded down into recesses on the spinner. The spinner and fairings can provide aerodynamic advantages in addition to protection for sensitive components within the rotor and blades apparatus. This improves efficiency and allows the aircraft to fly faster.

Abstract: Disclosed is a wind turbine blade assembly and a method for its manufacture. The wind turbine blade assembly comprises a leading edge, a trailing edge, a blade shell with a trailing portion, and a flatback profile component. The trailing portion has an outwardly curving arc shape and the flatback profile is positioned so as to cover the trailing portion of the blade shell.

Abstract: An apparatus for mitigating vortex-shedding vibrations or stall-induced vibrations on one or more rotor blades of a wind turbine during standstill includes at least one positioning element located between a blade tip section and a blade root section thereof. The positioning element is adapted for wrapping around at least a portion of the rotor blade. The apparatus also includes at least one airflow modifying element coupled to the positioning element and defining a height relative to a surface of the rotor blade. Additionally, the apparatus includes at least one securing element operably coupled to the positioning element for temporarily securing the airflow modifying element to the rotor blade.

Abstract: An airfoil assembly comprising a central spar extending along the radial direction; a blade skin positioned around the central spar to define an airfoil that has a pressure side and a suction side extending in the axial direction between a leading edge and a trailing edge, wherein at least one cavity is defined between the blade skin and the central spar; and a support structure positioned at least partially within the at least one cavity. The support structure comprises: a foam; and a foam reinforcement structure embedded within the foam.

Abstract: Provided is a composite material for a wind turbine blade, the composite material including a plurality of rigid elements and plurality of flexible elements, wherein each flexible element is arranged between two rigid elements and is connected thereto such that the rigid elements are flexibly connected to each other by the flexible elements. The flexibility of the composite material can be achieved by using the interspaces between the rigid elements. Therefore, when the composite material is placed on a curved surface, hollow spaces between the rigid elements may be reduced or avoided.

Abstract: A root assembly of a wind turbine blade for a wind turbine is provided. Also provided is a wind turbine blade including the root assembly and a wind turbine including the wind turbine blade.

Abstract: Apparatuses and systems are provided herein for unducted propulsion systems. The system includes a forward housing for high efficiency for high subsonic sustained flight. A plurality of blades are affixed to the forward housing, wherein the forward housing defines a flowpath curve extending from the forward-most end of the forward housing through the axial extent of a forward blade root. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes a first point having a first radius where the radius reaches a maximum forward of the forward blade root and a second point aft of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.029.

Abstract: A turbine blade includes: a platform; an airfoil portion extending from the platform in a blade height direction and having a pressure surface and a suction surface extending between a leading edge and a trailing edge; a blade root portion positioned opposite to the airfoil portion across the platform in the blade height direction and having a bearing surface; and a shank positioned between the platform and the blade root portion. The shank has a cross-section which is perpendicular to the blade height direction of the airfoil portion, and in which a line segment connecting a widthwise center position of a leading-edge-side end portion of the shank and a widthwise center position of a trailing-edge-side end portion of the shank is sloped to a center line between a pressure-surface-side contour of the blade root portion and a suction-surface-side contour of the blade root portion.

Abstract: A rotor blade for a wind energy installation includes a blade root, a blade tip, and at least one rotor blade shell extending in a longitudinal direction from the blade root to the blade tip, and having an inner shell region and an outer shell region. The inner shell region includes a first fiber composite with at least two first fiber layers, and the outer shell region includes a second fiber composite with at least two second fiber layers. The first and second fiber layers extend substantially in the longitudinal direction. At least a first fiber layer of the first fiber composite terminates in the region of at least one end position in the longitudinal direction, whereas the remaining first fiber layers extend beyond the end position. At least a second fiber layer of the second fiber composite terminates in the region of the end position in the longitudinal direction, whereas the remaining second fiber layers extend beyond the end position.

Abstract: A blade for a propulsion apparatus that includes a body formed of a first material having opposed pressure and suction sides, and extending in span between a root and a boundary, and extending in chord between a leading edge and a trailing edge. A tip region that is formed of a second material and that is positioned such that it extends from the body and defines a tip. The tip region joins the body at the boundary. The tip region is configured to fail when a predetermined force is applied to the tip such that the tip separates from the blade and defines a fused tip.

Abstract: The present invention relates to a blade or vane for a turbomachine, particularly for an aircraft engine, with a blade element for interacting with the flow medium, wherein the blade has different diffusion protective coatings in various regions on its surface for protection against corrosion and/or oxidation, wherein the diffusion protective coatings are produced by chromizing and/or aluminizing, wherein the blade element is divided into two regions along the longitudinal axis of the blade element, wherein the first region extends over 80 to 95% of the length of the blade element, and the second region extends over the remainder of the length of the blade element, and wherein in both regions, an AlCr diffusion protective coating is applied, and wherein in one of the regions, the AlCr diffusion protective coating has a higher Cr content.

Abstract: The present disclosure is directed to a blade sleeve for a blade tip of a rotor blade of a wind turbine. The blade sleeve includes a rapid-prototyped body having a pressure side, a suction side, a first open span-wise end, a closed leading edge, and a trailing edge. Further, the body is slidable onto the blade tip of the rotor blade. In addition, the blade sleeve includes at least one additional rapid-prototyped feature integral with the body.

Abstract: A proprotor assembly for a tiltrotor aircraft having a forward flight mode. The proprotor assembly includes a spinner subjected to freestream airflow during forward flight. The spinner is elongated to form a tapered leading portion and a substantially cylindrical aft portion. The spinner forms a plurality of rotor blade cutouts exposing an inner chamber. The proprotor assembly includes a plurality of proprotor blade assemblies protruding radially from the spinner through the rotor blade cutouts. The rotor blade cutouts are formed at the substantially cylindrical aft portion of the spinner to reduce the freestream airflow into the inner chamber via the rotor blade cutouts during forward flight, thereby reducing drag experienced by the tiltrotor aircraft.

Abstract: A blade, configured to be mounted on a hub of a turbomachine propeller so that an empty space is defined between a base of the blade and a face of the hub facing the base. The blade includes a retractable blanking mechanism configured to reversibly occupy at least one of following two positions: a deployed position in which the retractable blanking mechanism at least partially closes off the empty space; and an extreme retracted position in which the retractable mechanism is kept out of the empty space.

Abstract: According to one aspect of the invention, a turbine assembly includes an airfoil extending from a blade and a dovetail located on a lower portion of the blade, wherein the dovetail has a dovetail contact surface. The turbine assembly also includes a member with a slot configured to couple to the airfoil via the dovetail, the slot having a slot contact surface to contact the dovetail contact surface, wherein the dovetail contact surface is reduced by a relief to alter a fundamental frequency of an assembly of the blade and member.

Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.

Abstract: A blade of a gas turbine engine is provided having an airfoil, a platform, a shank, a dovetail, and a skirt. The airfoil may extend distally from the platform, and the shank may extend proximally from the platform. The dovetail may also be provided to extend proximally from the shank. The skirt may be disposed on an aft side of the shank and may extend from the shank in a direction at least partially axially aft from the shank.

Abstract: A turbomachinery blade includes: an airfoil; and a shank extending from a root of the airfoil, the shank being constructed from a composite material including reinforcing fibers embedded in a matrix The shank includes a pair of spaced-apart side faces that cooperatively define: a dovetail disposed at a radially inboard end of the shank, comprising spaced-apart, diverging faces; a first neck portion having a concave curvature disposed radially outboard of the dovetail, and defining a primary minimum neck at which a thickness of the shank is at a local minimum; and a second neck portion disposed radially outboard of the first minimum neck, the second neck portion having a concave curvature and defining a secondary minimum neck at which the thickness of the shank is at a local minimum.

Abstract: A rotor blade for a flow machine, in particular a steam turbine, includes an insertion root with a first finger and two second fingers which are arranged on either side of the first finger in axial direction. The first finger and the second fingers have a shoulder in axial direction on axial sides facing one another such that the fingers have a radially outer first portion and a radially inner second portion whose axial extension is shorter than that of the outer, first portion. In relation to a total axial width between axial sides of the two second fingers which face away from one another, the radial height of the first, radially outer portion is in the range of 0.39 to 0.45, particularly 0.40 to 0.44, and the radial height of the second, radially inner portion is between 0.40 and 0.46, particularly between 0.41 and 0.45.

Abstract: A rotor blade assembly for a wind turbine, and a method for installing a rotor blade assembly on a wind turbine, are disclosed. The rotor blade assembly includes a rotor blade having exterior surfaces defining an aerodynamic profile including a pressure side and a suction side extending between a leading edge and a trailing edge. The rotor blade further extends in a generally span-wise direction between a root and a tip. The rotor blade assembly further includes a blade extension extending in the generally span-wise direction from the root towards the tip, and a plurality of connection devices connecting the blade extension to the rotor blade. Each of the plurality of connection devices includes a mechanical fastener extending through the root in the generally span-wise direction for connecting the rotor blade to a hub of the wind turbine.

Abstract: A wind turbine blade includes a root region. A first extension (LEX) is attached to the leading edge side of the root region while a trailing edge strake (TES) is attached to the trailing edge side of the root region. The LEX and TES each include an outer profile that becomes more pronounced relative to their respective locations in the root region as the root region of the wind turbine blade morphs from a substantially cylindrical shape to a substantially airfoil shape. The LEX provides both optimal angle of attack and lift generation in the root region, while the TES mitigates airflow separation and enhances airfoil lift in the root region.

Abstract: A rotor blade (1), in particular of a main rotor of a rotary-wing aircraft, made of fiber-reinforced plastic includes a blade section (10) and a connecting section (12) for fastening the rotor blade (1) to a drive device (18) which includes a sleeve-shaped connecting device (14), is further developed in that the connecting device (14) includes flat fiber layers (S1 to S18) running substantially in the plane of extension of the connecting section (12).

Abstract: A wheel dovetail groove with a wheel hook retains blade hooks of mounted blades. Opposed arcuate cut-outs in upper recessed areas of the groove may form an assembly gate. Blade hooks may be inserted into the groove in a first orientation, rotated to a second orientation at the assembly gate, and slid into a predetermined position. Blades may be secured with shims between adjacent bucket dovetails. Blade tip cover blocks may be included to form a cover. All blades may be substantially identical and not need special mounting arrangements at the assembly gate.

Abstract: Certain embodiments of the invention may include systems methods, and apparatus for sealing a bucket dovetail in a turbine. According to an example embodiment of the invention, a method is provided for sealing a gap between a bucket dovetail and a rotor wheel slot. The method can include providing a bucket tab associated with a bucket dovetail, wherein the bucket tab is configured to accept a seal tab; configuring the bucket tab and the seal tab to engage at least one dimension upon insertion of the seal tab into the bucket tab; and sealing a gap between the bucket dovetail and a rotor wheel slot with the seal tab; wherein at least a portion of the seal tab changes as a function of temperature for further sealing gap between the bucket dovetail and the rotor wheel slot.

Abstract: Rotor blade or rotor blade segment for a wind turbine, having at least one cable for fixing the rotor blade or rotor blade segment to a rotor hub or to a further rotor blade segment, wherein the at least one cable is redirected in a U-shaped manner within the rotor blade or rotor blade segment.

Abstract: A component for a gas turbine, especially a blisk or a bling, whereby the component includes a rotor base (12) made of a high temperature-resistant nickel alloy and a plurality of turbine blades (14) joined to the rotor base, whereby each turbine blade includes a rotor blade (16) made of a titanium alloy and a blade root. The blade root is configured as an adapter element (18) that is made of a material that can be welded to the titanium alloy as well as to the high temperature-resistant nickel alloy and that is integrally joined to the rotor base (12) and to the rotor blade (16) fusion. A method for the production of the component is also described.

Abstract: The present invention relates to a rotor stage of a compressor drum (2) for an axial turbomachine comprising a row of rotor vanes (9) each provided with a platform (12), and a wall (3) that is generally symmetrical in revolution relative to the rotation axis of the turbomachine and forming a hollow body, said wall (3) comprising a partition wall and a support zone (5) that is raised relative to the partition wall in a direction oriented towards the outside of the hollow body, said support zone (5) having a central portion (8) and side walls (7) connecting the central portion (8) to the partition wall of the drum, said platform (12) of each of said vanes (9) being assembled to said central portion (8) by means of one or more fastening elements.

Abstract: A rotor wing in a fiber-reinforced composite design including fiber layers, in particular for a tail rotor of a rotary wing aircraft, with a rotor blade (1) that includes a blade skin (40, 50) and a blade body (41-57) that includes an aerodynamically effective profile, with a tension-torque-transmission element (3) connected to it, which is designed in one piece with the rotor blade (1), and with fiber layers (42-47) that extend through the tension-torque-transmission element (3) and are scarf-join in the rotor blade (1), is improved in that the fiber layers (42-47) extend right through from the tension-torque-transmission element (3) to the blade body (41-57). Furthermore, a method for producing the rotor wing is described.

Abstract: A tension-torque-transmission element (3; 3?; 4) for a rotor blade of a rotary wing aircraft (helicopter), in particular for a fenestron blade of a tail rotor, with a connecting section on the blade side and a connecting section (30; 30?; 40) on the axis side, with a connecting eye (32) on each connecting section, and with a torque-transmission section (34; 34?; 44) that connects the connecting sections (30; 30?; 40), is improved in that the tension-torque-transmission element (3; 3?; 4) is designed in a fiber-reinforced composite design including several layers (A to G) of a textile fabric. A method for producing such a tension-torque-transmission element (3; 3?; 4) is also described.

Abstract: A turbomachinery blade for a gas turbine engine is provided and includes an airfoil extending between a leading edge and a trailing edge. In one embodiment the turbomachinery blade is a compressor blade. The blade can include a platform attached to the airfoil on one side, the other side being attached to a stalk having a lower attachment portion useful for being received in a compressor disk. The blade includes an undercut beneath a portion of the airfoil, preferably beneath the leading edge and/or trailing edge of the airfoil. In one form the undercut is located in a corner of the platform and extends partially along two sides of the platform.

Abstract: A blade for a rotor of a wind turbine having a substantially horizontal rotor shaft, the rotor comprising a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade comprises a main blade part having a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge. The profiled contour generates a lift when being impacted by an incident airflow. The profiled contour is divided in the radial direction into a root region with a substantially circular or elliptical profile closest to the hub, the substantially circular or elliptical profile having a diameter, an airfoil region with a lift generating profile furthest away from the hub, and a transition region between the root region and the airfoil region.

Abstract: A system including: a first turbine segment comprising a first blade coupled to a first shank. The system also includes a second turbine segment including a second blade coupled to a second shank, as well as an elongated flexible seal disposed in a gap between the first and second shanks. The elongated flexible seal includes an opening configured to channel a fluid flow into a hollow region of the elongated flexible seal to induce expansion of the elongated flexible seal in the gap.

Abstract: An integrally bladed rotor disk (20) for a turbine, including rotor blades (40), which are joined in a substance-to-substance bond to a disk element (30), and a sealing device (60) for preventing or reducing the extent to which cooling air is able to flow from a high-pressure side (12) of the rotor disk (20) through openings (24) on the rotor disk (20) to a low-pressure side (14) of the rotor disk (20).

Abstract: An airfoil (26, 62, 64) is mounted on a chordwise stall fence (28) of a wind turbine blade (22). The airfoil may be an aerodynamic slat (26) positioned over a forward portion of the suction side (38) of the blade or a flap (63) disposed near a trailing edge (34) of the blade. The stall fence may be at least as high as the thickness of the boundary layer (39) of air passing over the blade. The slat or flap may be twisted between an inboard end (26A) and an outboard end (26B) to compensate for the radially varying angle of the relative air inflow (46A, 46B).

Abstract: The invention relates to a process for manufacturing a blade connection of a rotor blade for a wind energy system which comprises fastening elements for fastening the blade connection to a hub, which fastening elements are provided on a circular arc, preferably equidistant from each other. Furthermore, the invention relates to a blade connection and a fastening element for a blade connection. The invention is based on the problem of improving the fastening of a rotor blade on the hub of a wind energy system as well as improving the manufacture and/or making a suitable blade connection available. The invention solves this problem as regards the process in that fastening elements formed in pieces are arranged on the circular arc and spaced from each other with spacer elements.

Abstract: The present invention discloses a hub fin device for improving the efficiency of a propeller. The hub fin device can include a propeller having a hub and a plurality of propeller blades that extend radially outward from the hub. Each of the plurality of propeller blades has a trailing edge region. A fin can also be included and located in the trailing edge region of at least one of the plurality of propeller blades. The fin extends radially outward from the hub and reduces or eliminates a hub vortex that is normally present during operation of the propeller.

Abstract: A root attachment for a wind turbine rotor blade having a blade root is disclosed. The root attachment may include a wall panel configured to be coupled to the rotor blade at or adjacent to the blade root. The wall panel may define at least a portion of an airfoil shape and may include an inner side and an outer side. In addition, the wall panel may define a non-uniform cross-section between the inner and outer sides.

Abstract: A turbine blade is disclosed. The turbine blade includes a platform, an airfoil extending from one side of the platform, a root extending radially from another side of the platform, and a pocket located beneath the platform. The pocket is defined by a plurality of walls, and a pad is disposed in a corner of the pocket. The pad includes three pad corners and three sides connecting the three pad corners, wherein each side extends along a different one of the plurality of walls.

Abstract: A wind turbine rotor blade with a suction side and a pressure side is provided. The blade includes a cylindrical root portion, an airfoil portion defining the suction side and the pressure side, and a transition portion which is located between the airfoil portion and the root portion. The transition portion has a transition profile changing from the airfoil of the airfoil portion to the cylindrical profile of the root portion. The leading section of the transition profile is cylindrical and the trailing section of the transition profile is elongated. In the rotor blade, the maximum chord length of the airfoil portion is at least the maximum chord length of the transition portion. In addition, the transition profile includes a section with a concave curvature on the pressure side of the rotor blade.

Abstract: An airfoil includes a body that has a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from another side of the platform. A member is connected in an articulated joint to the body.

Abstract: A system and method of extending the useable life of a gas turbine blade is disclosed in which the gas turbine blade includes an undercut configuration designed to relieve mechanical and thermal stress imparted into the pedestal region of the airfoil trailing edge. The embodiments of the present invention include turbine blade configurations having different trailing edge undercut configurations as well as additional cooling supplied to the internal passages of the trailing edge region of the turbine blade.

Abstract: A rotor blade assembly is disclosed herein. The rotor blade assembly includes a composite blade portion extending a length from a root to a tip. A leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root. The rotor blade assembly also includes a base portion fixed to the composite blade portion proximate to the root. The rotor blade assembly also includes a sheath extending around the composite blade portion. The sheath is positioned along the length adjacent to the base portion and between the root and the end point of the leading edge.

Abstract: An airfoil having an inboard blade section (106) and an outboard blade section (108). The inboard blade section (106) has a mid-blade end (114), and the inboard blade section (106) includes a biplane wing (116). The multiplane wing (116) has a first blade (118) and a second blade (120). The first blade (118) has a first airfoil cross-section (122), and the second blade (120) has a second airfoil cross-section (132). The first blade (118) is generally parallel to the second blade (120). The outboard blade section (108) has a mid-blade end (148), and the outboard blade section (108) includes a monoplane wing (156) with a third airfoil cross-section (158). The mid-blade end (148) of the outboard blade section (108) is joined to the mid-blade end (114) of the inboard blade section (106).

Abstract: A blade for a gas turbine, is provided and includes a blade airfoil which extends in a blade longitudinal direction and at the lower end merges into a shank which terminates in a blade root for fastening the blade on a blade carrier, particularly on a rotor disk. Devices for cooling the blade, which are supplied with a cooling medium, especially cooling air, via a feed hole arranged on the shank at the side, are arranged inside the blade airfoil. In the region of the feed hole provision is made for a planar stiffening element which reaches beyond the immediate region of the feed hole for reducing peaks of mechanical stress.

Abstract: A turbomachinery blade includes: an airfoil; and a shank extending from a root of the airfoil, the shank being constructed from a composite material including reinforcing fibers embedded in a matrix The shank includes a pair of spaced-apart side faces that cooperatively define: a dovetail disposed at a radially inboard end of the shank, comprising spaced-apart, diverging faces; a first neck portion having a concave curvature disposed radially outboard of the dovetail, and defining a primary minimum neck at which a thickness of the shank is at a local minimum; and a second neck portion disposed radially outboard of the first minimum neck, the second neck portion having a concave curvature and defining a secondary minimum neck at which the thickness of the shank is at a local minimum.

Abstract: The disclosed propeller/turbine blade enhancement will be used in the moving fluid kinetic energy conversion field. This turbine blade skirt enhancement to a propeller/turbine bladed assembly will increase the kinetic energy conversion of the assembly on which the enhancement has been made a part of. The disclosed turbine blade skirt will contact and redirect a portion of the moving fluid the propeller/turbine bladed assembly is converting into mechanical rotational energy. The contacting and redirecting the fluid from the least efficient conversion areas of the assembly to the more efficient conversion areas of the assembly increases the amount of mechanical rotational energy obtained from the assembly.

Abstract: A turbine blade includes a platform, an airfoil located on one side of the platform, and a base located on an opposite side of the platform. The base includes an attachment portion that is receivable in a blade retention slot of a turbine disk and a shelf located outside the turbine disk. The shelf includes a mistake proof feature that projects from an outer surface of the shelf.

Abstract: A turbine bucket includes a radially inner mounting portion, a shank radially outward of the mounting portion, a radially outer airfoil and a substantially planar platform radially between the shank, and the airfoil. At least one axially-extending angel wing seal flange is formed on a leading end of the shank forming a circumferentially extending trench cavity along the leading edge of the shank, radially between an underside of the platform leading edge and the angel wing seal flange. A plurality of substantially radially-extending purge air holes are formed in the angel wing seal flange, adapted to fluidly connect a turbine rotor wheel space cavity with the trench cavity and thereby supply purge air to the outer surface of the angel wing seal flange.