Abstract: A rotating blade assembly for a turbine engine having a drive shaft, the rotating blade assembly comprising a disc, at least one blade assembly, and a retainer. The disc being operably coupled to the drive shaft and including a seat having at least a portion of a first through hole. The at least one blade assembly having an upper platform, a lower platform, a dovetail extending from the lower platform, and a blade extending between the upper platform and the lower platform. The retainer assembly securing the disc to the at least one blade assembly and comprising a hollow tubular element, a pin, and a fastener.

Abstract: A turbine, and particularly a low pressure turbine is disclosed, which comprises a plurality of rotor members and spacers for arranged between rotor members, to avoid that an ingested gas flow from the hot gas flow path channel reaches the wheel space. The rotor members each include a deflector. The deflector is placed in correspondence with each spacer and deflects the ingested gas flow over the upper surface of the spacer, thus preventing it to heat up the roots of the blades.

Abstract: A fan blade platform assembly includes a pressure side platform half that includes a first attachment wall, a first gas path wall, and a first connecting wall attached to both the first attachment wall and the first gas path wall. A suction side platform half includes a second attachment wall, a second gas path wall, and a second connecting wall attached to both the second attachment wall and the second gas path wall. A seal engages the pressure side platform half and the suction side platform half.

Abstract: Turbomachine components and compressors are provided. The turbomachine component includes a platform and a mounting portion that extends from the platform. The mounting portion includes a dovetail received by a slot defined in the turbomachine. The slot includes a floor and a ceiling. The dovetail includes an inner surface and an outer surface. A hole is defined in the dovetail from an inlet at the inner surface to an end wall. The hole has a cylindrical portion and a tapered portion. A mechanical spring is disposed within the hole and in contact with the floor and the end wall such that the outer surface of the dovetail is forced into contact with the ceiling of the slot.

Abstract: Unmanned aircraft have aligned forward and aft propulsion systems possessing different performance and/or noise characteristics. According to some embodiments, unmanned aircraft have a forward engine and a forward tractor propeller and an aft engine and an aft pusher propeller. Selected ones of forward and aft propulsion systems will thus be provided to have greater and lesser operational flight performance characteristics and greater and lesser noise signature characteristics, respectively, as compared to the other. For example, the forward propulsion system may be provided with the greater operational flight performance and higher signature characteristics as compared to the aft propulsion system, while conversely the aft propulsion system may be provided with a lesser flight performance and lower noise signature characteristics as compared to the forward propulsion system.

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

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The disk mounts connect the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount. The first disk mount is integral with the first rotor disk. The first disk mount projects axially through the second rotor disk.

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis, the rotor disk comprising a slot within a rim of the disk and a spacer within the slot, the spacer having a clearance feature sized to permit rotation of a rotor blade from an insertion position to an installed position.

Abstract: A rotor assembly for a gas turbine engine includes a shaft and first and second annular drum segments coupled to the shaft. Furthermore, the rotor assembly includes an annular flange positioned between the first and second annular drum segments along the axial centerline, with the annular flange coupled to the first and second annular outer drum segments. Additionally, the rotor assembly includes a blade having a shank section and an airfoil section. The shank section is, in turn, coupled to the annular flange such the airfoil section extends inward along the radial direction toward the axial centerline and into a hot gas path of the gas turbine engine.

Abstract: A vane includes a ceramic vane piece that defines first and second vane platforms and a hollow airfoil section that joins the first and second vane platforms. A structural platform adjacent the first platform defines a radial seal slot. A seal has a radial leg and an axial leg. The radial leg extends in the radial seal slot and the axial leg extends in an interface between the structural platform and the first vane platform.

Abstract: A fan platform for electrically grounding an airfoil of a gas turbine engine includes a flow path surface extending between a first and second side. An inner surface radially opposing the flow path surface also extends between the first and second side, and includes a body portion extending radially inwardly therefrom. At least a first conductive path for grounding travels from the first side via the body portion.

Abstract: The present invention relates to a lightweight composite propeller for an outboard motor, wherein the propeller has a separate hub and blades which are easily repaired when damaged, improves fuel efficiency because a lightweight composite material is used therefor, and is easily manufactured in large quantities.

Abstract: Radial turbomachine includes fixed case; one rotor disc installed in case and having rotor blades mounted on front face thereof; plurality of elements projecting from case and terminating proximity to rotor disc, wherein projecting elements include seal elements acting against rotor disc are operatively active on rear face of rotor disc or stator blades radially interposed between rotor blades of rotor disc; and one support plate bearing projecting elements and installed in case. Support plate is radially extended across from rotor disc and includes plurality of first circular portions concentric with rotation axis of rotor disc and plurality of second circular portions radially interposed between first circular portions.

Abstract: A shutter is provided for repairing a turbine engine having a damaged or absent fixed rectifier blade (38, 39), this damaged or absent fixed blade (38, 39) leaving free an opening (34) of a ferrule (31) intended to receive an end of this fixed blade (38, 39). The shutter (48) arranged to close the free opening (34) by being rigidly attached to this free opening (34).

Abstract: A particle separator adapted for use with a gas turbine engine includes an inner wall, an outer wall, and a splitter. The splitter cooperates with the inner wall and the outer wall to separate particles suspended in an inlet flow moving through the particle separator to provide a clean flow of air to the gas turbine engine.

Abstract: A gas turbine rotor includes: a first rotor in a shaft shape extending by a predetermined length in an axial direction, and provided with an insertion hole at an end of the first rotor; a second rotor in a shaft shape extending by a predetermined length in the axial direction, and provided with an insertion part extending by a predetermined length at an end of the second rotor and corresponding to the insertion hole such that the insertion part is inserted into the insertion hole; and a connecting member mounted between the insertion hole and the insertion part to connect the first rotor and the second rotor together, and made of a material having a thermal expansion coefficient different from a thermal expansion coefficient of both the first rotor and the second rotor.

Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

Abstract: In a featured embodiment, a fan rotor includes a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.

Abstract: The present invention relates to a bladed rotor for a gas turbine, with a body and a plurality of rotating blades where contact regions of a cylindrical surface of the body and front faces of the rotating blades are joined together cohesively. At least one of these contact regions and/or at least one of these front faces has at least one blind hole, in which at least one impulse body is arranged with play of movement and which is sealed and rotating blades are joined with the cylindrical surface. Alternatively, the body and rotating blades are manufactured integrally with one another by machining, and at least one blind hole extends from an inner surface of the body facing away from the blade out to one of the rotating blades, at least one impulse body being disposed with play of movement in this hole, and this hole is sealed.

Abstract: The invention relates to a turbomachine including: a guide baffle, whose sv guide blades are situated on c guide blade carriers; and an adjacent moving baffle including sb moving blades; the guide baffle nv including impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nb including impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient ? i = 1 n v ? ? m i s v - c of sum ? i = 1 n v ? ? m i of the masses of all impulse bodies of the guide baffle divided by the difference (sv?c) of the number sv of all guide blades minus the number c of all guide blade carriers amounts to at least 1.

Abstract: A hollow blade of a gas turbine engine has a sacrificial elongated damper disposed slideably in a chamber for minimizing modes of vibration during operation. The chamber is defined between two opposing surfaces generally spanning radially outward from an axis of the engine and a face facing radially inward. The damper is constructed and arranged to make loaded contact with the face via a centrifugal force created by rotation of the engine.

Abstract: A laser shock peening method and device for a bottom surface of a tenon groove of an aircraft blade. During the laser shock peening process, according to geometric characteristics of the bottom surface of a tenon groove, a circular facula of a laser beam is changed into a strip-shaped facula, at the same time as a flow-guiding injection device and a water pumping device are respectively arranged at two end surfaces of the bottom surface of the tenon groove to ensure the stability of a water confinement layer.

Abstract: Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein.

Abstract: A cover plate assembly according to an exemplary aspect of the present disclosure includes, among other things, a first cover plate and a second cover plate in contact with a portion of the first cover plate to at least axially retain the first cover plate.

Abstract: A fixture for restraining a wheel of a turbomachine is provided. The fixture includes a dovetail section adapted for insertion into a dovetail slot of the wheel, and a mounting section located adjacent to, or formed integrally with, the dovetail section. At least one coupling ring is attached to a top of the mounting section. The at least one coupling ring is adapted to be secured to a stationary anchoring point via a restraint.

Abstract: Various embodiments include a rotor key member, along with a related assembly and steam turbine. Particular embodiments include a rotor key member for retaining a circumferential seal in a steam turbine, the rotor key member including: a main body; a first arm extending from the main body; a second arm extending from the main body, wherein the first, arm, the second arm and the main body define a space spanning axially between the first arm and the second arm; and a hook extending from the second arm in a direction axially away from the space, the hook sized to contact a radially inner surface of the circumferential seal.

Abstract: A rotor of a turbomachine. The rotor includes at least one blade (4, 6, 8) that has a blade leaf (20) and a blade root (54, 55, 58), and a rotor base body (2), in particular a disk (2), that has an outwardly open, circumferential groove (12) for receiving the blade root (54, 55, 58). The circumferential groove (12) and the blade root (54, 55, 58) are shaped in a way that allows the blade root (54, 55, 58) to be secured in the circumferential groove (12) by the rotation of the blade (4, 6, 8) about an axis (Ar, AT).

Abstract: Various embodiments include a rotor key member having: a body with a primary axis extending in a direction substantially perpendicular to an axial direction in a steam turbine, the body including: a first pair of opposing sides; a second pair of opposing sides extending between the first pair of opposing sides; a top surface and a bottom surface extending between the second pair of opposing sides; and a fillet, bevel or chamfer edge extending between a first one of the first pair of opposing sides and the bottom surface and extending an entire length of the body along the primary axis; and a slot within the body, the slot extending a portion of a length of the body along the primary axis between the second pair of opposing sides and forming an opening in a second one of the first pair of opposing sides.

Abstract: Various embodiments include a rotor key member, along with a related assembly and steam turbine. Particular embodiments include a rotor key member for circumferentially retaining a circumferential seal in a steam turbine rotor body, the rotor key member having: a main body sized to contact an axial face of the circumferential seal; and a locking member extending from the main body in a direction axially toward the circumferential seal, the locking member having at least one circumferential edge sized to substantially complement a corresponding slot in the circumferential seal to restrict movement of the circumferential seal relative to the steam turbine rotor body.

Abstract: A fixture for restraining a wheel of a turbomachine has a dovetail section adapted for insertion into a dovetail slot of the wheel. A mounting section is located adjacent to, or formed integrally with, the dovetail section. At least one coupling ring is attached to the mounting section, and the coupling ring is adapted to be secured to a stationary anchoring point via a restraint. The stationary anchoring point includes at least one counterbore assembly having a coupling ring attached thereto. The counterbore assembly is adapted to be secured to a stationary structure. The stationary structure may be a shell, a flange or a casing of the turbomachine.

Abstract: A fast-dismounted cymbal-locking nut being screwed through an outer thread of a mounting bolt of a cymbal to press the cymbal tightly and adjust the position of the cymbal, comprises a seat, a first wing, a second wing, and a resilience element. The first and second wings are pivotally coupled to the seat; each of them has a locking position and a fast-dismount position. The first and second wings respectively include first and second semi-spherical threaded grooves, which jointly form an inner thread corresponding to the outer thread at their locking positions. At the fast-dismount positions, the shortest distance between the first and second semi-spherical threaded grooves is larger than the outer diameter of the outer thread. The user can directly mount the nut to the outer thread without screwing the nut through the outer thread. The nut enables the user to fast mount or dismount a cymbal.

Abstract: An example turbomachine rotor provides a groove that is annular and is configured to receive a root of an airfoil, the groove having a radial cross-sectional area. A ratio of the radial cross-sectional area of the groove to a radial cross-sectional area of the root received within the annular groove is from 2 to 5.

Abstract: A wind turbine rotor blade is for mounting on a rotor hub covered by a spinner having a rotor blade opening and includes a wind turbine rotor blade body having a fastening section and a longitudinal section. The fastening section is configured for fastening the rotor blade body on the rotor hub. The longitudinal section is arranged inside the rotor blade opening when the wind turbine rotor blade is mounted on the rotor hub. The longitudinal section and the rotor blade opening conjointly define an annular gap therebetween when the wind turbine rotor blade is mounted on the rotor hub. A cover profile is fastened on the wind turbine rotor blade and covers the annular gap. The cover profile has a circular ring-shaped outer edge and a circular ring-shaped inner edge. The inner edge is disposed at a radial distance from the wind turbine rotor blade. An annular-shaped cover element is fastened on the wind turbine rotor blade and bridges the radial distance.

Abstract: A system includes a turbomachine that includes at least one rotor disk or stage having a peripheral portion disposed about a rotational axis of the rotor disk or stage. The peripheral portion includes a groove that extends circumferentially about the peripheral portion. The groove has a first groove surface and a second surface disposed opposite the first groove surface. The turbomachine also includes a closure bucket disposed adjacent at least one bucket within the groove. The closure bucket has a first surface that interfaces with the first groove surface and a second groove surface disposed opposite the first surface. The closure bucket blocks circumferential movement of the at least one bucket within the groove relative to the rotor disk or stage. The turbomachine further includes a single wedge disposed between and contacting the second surface of the closure bucket and the second groove surface to secure the closure bucket within the groove.

Abstract: A method for balancing a compressor rotor assembly including a forward weldment (211) and an aft weldment (212) includes pre-balancing the aft weldment (212) of the compressor rotor assembly (210) with compressor disks (220) prior to populating the compressor disks (220) with circumferentially installed compressor rotor blades (230). Pre-balancing the aft weldment (212) includes measuring a rotational balance of the aft weldment (212). Pre-balancing the aft weldment (212) also includes determining a number of underplatform weights (260) needed and a location for each underplatform weight (260) within a circumferential slot (236) of one the compressor disks (220). Pre-balancing the aft weldment (212) further includes mounting each underplatform weight (260) in the determined location.

Abstract: A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge. A load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentially to have the mounted structure radially inwardly of the ledge. A lock slot is positioned on one circumferential side of the load slot. The lock slot is formed to receive a lock, and the lock is partially received within a portion of at least one of the blades, to lock the blades within the rotor, and a shield slot on a second circumferential side of the load slot. The shield slot is sized to be different from the lock slot such that a lock cannot be inadvertently positioned within the shield slot.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

Abstract: A balanced rotor of a turbine engine, having a rotor disc with a circumferential slot and a row of rotor blades mounted in the slot and a balance weight having a land which extends beneath the root of a blade and having a mass-adjustment protrusion extending from the land in a radial direction relative to the axis of the rotor component and which lies wholly between the blade root and an adjacent blade root.

Abstract: An assembly includes a fixture, first and second vanes, and an insert. The first vane and the second vane are retained within the fixture and are spaced at a distance from one another. The insert is disposed between the first vane and the second vane and the insert includes a spring that exerts a force that is applied to both the first vane and the second vane.

Abstract: A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining the first sidewall, and a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis.

Abstract: A gas turbine engine system includes a disk and an airfoil. The disk includes a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail. The airfoil is engaged with the retention slot, and includes a platform with an upstream angled portion, a downstream angled portion, and a notch defined in the platform. The ridge of the disk extends at least partially into the notch of the platform.

Abstract: According to one aspect of the invention, a turbine assembly includes a rotor wheel and a circumferential slot formed in the rotor wheel, the circumferential slot including a uniform cross-section shape for a circumference of the rotor wheel. The assembly also includes a first ring member positioned in the circumferential slot, the first ring member being configured to prevent radial movement of a dovetail attachment when positioned in the circumferential slot, wherein the dovetail attachment is part of a turbine blade.

Abstract: A turbine bucket including an integral rotation controlling feature is disclosed. In one embodiment, a turbine bucket includes: a blade section having an inner radial end and an outer radial end; an integral cover section connected to the outer radial end of the blade section; and a base section for engaging a rotor body, the base section connected to the inner radial end, wherein the base section includes: a central body; a set of tangs extending axially from the central body; a set of flanges radially inboard of the set of tangs and extending axially from the central body; and an integral rotation controlling feature extending from the central body, wherein the rotation controlling feature engages a radial opening in the rotor body. The integral rotation controlling feature is sized to limit rotation of the base section, when the turbine bucket is engaged with a rotor body.

Abstract: Aerodynamic root adapters for rotor blades include an interior support section having a first end that connects to a root end of the rotor blade and a second end that connects to a rotor hub of the wind turbine, and, an aerodynamic exterior section supported by the interior support section. The aerodynamic exterior section thereby extends an aerodynamic profile of the rotor blade beyond the root end of the rotor blade to at least partially between the root end of the rotor blade and the rotor hub when the aerodynamic root adapter is connected thereto.

Abstract: A propeller is provided including a hub and a first blade group and a second blade group. The first blade group includes at least one first propeller blade and the second blade group includes at least one second propeller blade. The at least one first propeller blade and the at least one second propeller blade are mounted to and equidistantly spaced about the hub. The at least one first propeller blade of the first blade group has at least one geometric characteristic different from the at least one propeller blade of the second blade group. The different blade groups will generate different noise signatures over a wider range of frequencies allowing for the design of low noise propeller systems.

Abstract: Disclosed is a blade-disk assembly of a turbomachine, the blade-disk assembly having a plurality of adjacent rotor blades and a closure blade which are tilted into an anchoring groove, and at least one circumferential retention element which interlockingly cooperates with at least one blade, as well as a plurality of tilt-out prevention elements which are disposed between the groove base and the root portions and which, in the rest state, space the blades from the groove base when in the upper position. The blade-disk assembly further has a locking element, a portion of which is located between the groove base and the root portions and which, in the rest state, spaces the closure blade from the groove base when in the upper position. Also disclosed are a method for assembling such a blade-disk assembly, as well as a turbomachine.

Abstract: A wind turbine is described which comprises a tower, a nacelle mounted to the top of the tower, and a rotor mounted to the nacelle. The rotor comprises two or more blades mounted to a central hub. The hub supports two or more annular pitch bearings associated respectively with the two or more blades. Each pitch bearing defines a bearing plane inclined at a first angle with respect to a horizontal plane when the respective blade is oriented in a downwardly direction in alignment with the tower. Each pitch bearing is spanned by a hub plate; and a work platform integral with or mounted to the hub plate lies generally in a plane at a second angle to the horizontal plane when the respective blade is oriented in a downwardly direction in alignment with the tower, which second angle is less than the first angle. The work platform provides a substantially horizontal platform for use by maintenance personnel when installing or servicing components in and around the hub.

Abstract: A blade arrangement on a wall of a fluid flow path of a turbomachine includes a locating channel disposed in the wall and having undercut flanks. A plurality of blades each having a blade-side root section corresponding to the undercut flanks. A plurality of intermediate filling pieces correspond to the undercut flanks and separate each of the blade-side root sections. The plurality of blade-side root sections and intermediate filling pieces are seated in a form-fitting manner and fixed in a force-locking manner in the locating channel. The plurality of intermediate filling pieces fill out the locating channel so as to form a gas flow-side surface essentially free of a disturbing contour between the blade-side root sections. Each of the plurality of intermediate filling pieces includes a threaded hole disposed essentially perpendicular to a base of the channel. A screw is disposed in the threaded hole.

Abstract: A process of repairing a component, a repair tool for a component, and a component are disclosed. The process includes removing material from a region of the component. The removing forms a through-cut in the component, forms a partial-frustoconical geometry in the component, forms a substantially partial-frustoconical geometry in the component, forms a partial-spherical geometry in the component, forms a substantially partial-spherical geometry in the component, forms a partial-elliptical geometry in the component, forms a substantially partial-elliptical geometry in the component, forms a partial-cylindrical geometry in the component, forms a substantially partial-cylindrical geometry in the component, is in a direction substantially perpendicular to a surface of the component, is in a direction substantially inclined with respect to the surface of the component, or a combination thereof. The repair tool includes a securing mechanism and a cutting portion for removing a region.

Abstract: A gas turbine blade in an associated receiving recess of a rotor base body includes a slot in the blade root and has the shape of a straight cylinder. A blade retaining plate has a first securing region and a second securing region interconnected by a shaft region; the shaft region having the shape of a straight cylinder configured to conform to the slot of the blade root. The shaft region comes to rest on a bottom of the receiving recess of the rotor base body; the first securing region being reshaped to form a first limit stop for a first end wall of the blade root; and the second securing region being reshaped to allow the blade root to be inserted along the insertion direction into the receiving recess. The second securing region of the blade retaining plate is subsequently reshaped to allow the second securing region to form a second limit stop for a second end wall of the blade root facing opposite the first end wall, and the blade root to be secured in position in the receiving recess.