Abstract: A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body, aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

Abstract: An annulus filler for mounting to a rotor disc in a gas turbine engine includes a body portion having a top wall arranged to bridge the gap between two adjacent blades extending from the rotor disc and to define an air flow surface for air passing between the blades; and a separately formed rear interface portion, fixed to the body portion adjacent to a down-flow end of the top wall. The rear interface portion forms a lip projecting below the top wall.

Abstract: A method for low-speed balancing of a rotor having at least one compressor stage blades assembly includes a row of blades circumferentially arranged with circumferential clearance. Two or more blades are located blades, each having an angular position in the assembly, at which the located blades are maintained. The located blades define sectors. Each sector includes movable blades and sectoral circumferential clearances. The movable blades, for each sector, are circumferentially adjusted such that the sectoral circumferential clearance of the sector moves circumferentially downstream relative to the movable blades with respect to a rotational direction when the assembly is rotated. Relative position of the sectoral circumferential clearances and the movable blades within each sector is maintained by inserts. A measure of unbalance is determined for the rotor in low-speed balancing conditions.

Abstract: The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disk.

Abstract: A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100° F. higher than that of the second material. A gas turbine engine is also disclosed.

Abstract: The invention relates to a rotor (30) of an electric motor having a shaft (33) and a magnet (32) disposed on said shaft (33), wherein the magnet (32) is attached to the shaft (33) using an injection molded plastic material and the plastic material forms a cooling vane (31) which generates a cooling air flow when the rotor (30) is in operation.

Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a plurality of platforms. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending attachment feature that is received in the disk. The platforms each have an axially extending attachment feature that is received in the disk.

Abstract: A bucket assembly for replacing an old bucket is provided with a turbine and a method for replacing the same. The bucket to be replaced is removed and then the bucket assembly configured of a blade part, first and second dovetail members, and a coupling member is simply assembled in a male dovetail, without sequentially disassembling the already installed buckets though a notch opening upon replacing the damaged bucket among the already installed buckets in a tangential entry type dovetail, thereby shortening replacement time and replacement costs of the bucket assembly and preventing a secondary damage occurring to the rotor or the rotor wheel during the disassembling process.

Abstract: A wind turbine blade is reinforced while suppressing possible stress concentration resulting from a load imposed on a blade root portion of the wind turbine blade in a flap direction. The wind turbine blade includes a blade main body extending from the blade root portion toward a blade tip portion and an FRP reinforcing layer formed so as to cover at least a part of the outer surface of the blade root portion of the blade main body. The FRP reinforcing layer includes a plurality of laminated fiber layers and a resin with which the plurality of fiber layers is impregnated. The FRP reinforcing layer is formed such that, in a cross section along a longitudinal direction of the blade main body, both ends of the plurality of laminated fiber layers in the longitudinal direction are tapered.

Abstract: A vacuum-pump rotor, in particular a vacuum-pump rotor for a turbomolecular pump, having a hub element for connecting to a rotor shaft or for forming a rotor shaft. A plurality of rotor blades are connected to the hub element. In order to form a vacuum-pump rotor by means of which a high tip speed can be achieved, the hub element and/or the rotor blades are produced of a plurality of material layers.

Abstract: A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100F higher than that of the second material. A gas turbine engine is also disclosed.

Abstract: In accordance with one aspect of the disclosure, a rotor is disclosed. The rotor may include a disk having a central axis, an airfoil radially extending from the disk, a bayonet tab extending radially from the disk, and a lock. The lock may further include a short tab and a long tab, both extending radially from the disk and in an axial direction with respect to the central axis. The long tab may have a greater axial length than the short tab.

Abstract: A method of making a root end joint for a wind turbine. A plurality of root segments (10) are formed of a composite material. Each has an arcuate end face (11) which subtends an angle of 90° or less and has a plurality of connection holes (12). The segments are joined together side-by-side to build up the circular profile of the root end. The segments include a proportion of uni-axial to multiaxial fiber which decreases from the arcuate end face towards the opposite end.

Abstract: The present invention relates to a rotor assembly for a rotary machine such as a gas turbine. The present solution provides a sealing wire located inside a groove engraved in the rotor body. The sealing wire is responsive to radial centrifugal forces acting during normal operation of the machine, and moves radially in the groove until a sealing configuration is achieved such to prevent damaging hot leakage towards machine components.

Abstract: An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features. The improved system also includes a method to axially retain segmented cover plates in relation to a turbine disc using a segmented retainer ring.

Abstract: A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc includes at least one longitudinal cavity configured to form, with the foil, when the foil is covering the bulb of the disc, a secondary passage through which a secondary cooling air flow can pass.

Abstract: A blade for a wind turbine comprising a blade root portion for attachment to a mounting flange of the wind turbine, the blade root comprising a plurality of first holes provided with an internal bushing wherein the bushings comprise a first end at or near a mounting surface of the blade root and an opposite second end embedded in their corresponding first holes, and wherein one or more internal bushing being guiding bushings, the guiding bushings comprising a first end that is adapted to guide the blade root with respect to a mounting flange.

Abstract: Embodiments of the present disclosure include a gas turbine engine system. The system may include a rotor wheel having a number of blades mounted about a periphery of the rotor wheel. Further, the system may include a retention device. The retention device may include a number of projections extending from a radial surface of the rotor wheel to form a number of circumferential slots about the rotor wheel. The retention device may also include a number of elongated members positioned within the circumferential slots to impede axial movement of the blades.

Abstract: Embodiments of the present disclosure include a system having a turbine blade segment having a blade and a mounting segment coupled to the blade, wherein the mounting segment has a multi-piece assembly configured to mount in a radial direction into a slot of a turbomachine rotor.

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 retention assembly for a propeller blade includes an inner ring that is conformally shaped to a bore of an annular loop, the annular loop being associated with a root portion of the propeller blade; a base that is configured to be immediately adjacent the annular loop; an annular outer ring including a bearing race interface that is conical in shape and includes a radially inner surface that conforms to a radially outer surface of the annular loop; and an adhesive that adhesively connects complementary surfaces of the outer ring and the annular loop. Also, a propeller blade assembly includes a propeller blade having a blade portion and a root portion; and the retention assembly that is configured to attach to the propeller blade.

Abstract: A blade retention disk includes, on its external surface, a peripheral annular groove configured to receive a plurality of blade roots of the hammer attachment type, the peripheral annular groove including a loading orifice intended for the introduction of blade roots inside the peripheral annular groove. The retention disk also includes: a crown covering the peripheral annular groove; a crown centering device to center the crown, the crown centering device and the crown forming an air supply enclosure from the bottom of the peripheral annular groove; at least one orifice opening in the air supply enclosure, the orifice being configured to introduce cooling air into the air supply enclosure. The blade retention disk finds a direct application in the field of low pressure turbines for aircraft turbine engines.

Abstract: A sealing system for a gas turbine engine includes an arcuate first ladder seal segment having a central portion, an upstream flange adjoining the central portion, a downstream flange adjoining the central portion opposite the upstream flange, and a plurality of openings. The upstream flange is arranged at an angle ?U greater than 0° and less than 90° relative to a given tangential plane, and the downstream flange is arranged at an angle ?D greater than 0° and less than 90° relative to the given tangential plane.

Abstract: A turbomachine rotor wheel including blades made of composite material; an annular mounting plate; a plurality of composite material blades mounted on the mounting plate, each blade also including a top platform at its tip carrying radial labyrinth teeth; an orientation disk fastened coaxially around the mounting plate and including at its outer periphery a plurality of axial slots that are open at one end, each slot presenting a cross-section that matches the cross-section of a blade root so as to hold it angularly in position by co-operation of shapes; and a variable-diameter spring ring housed in part in an axial notch formed in each blade root and projecting axially relative thereto, the spring ring to come into radial abutment against an inside surface of the orientation disk during radial outward movement of the blades relative to the mounting plate.

Abstract: A rotor assembly for a gas turbine engine includes a plurality of blades including a root portion and an airfoil portion. The rotor includes a plurality of slots that receive the root portion of a corresponding blade. The rotor includes an annular groove for a first and second retaining ring. The retaining rings are received within a common annular groove for holding each of the plurality of blades within the slots of the rotor.

Abstract: Methods and devices are described for reducing the torque and the level of vibration on a helicopter rotor blade by maintaining a constant lift and constant (low) drag on each section of the blade throughout the entire revolution. A rotor system includes a trackway defining a continuous travel circuit, truck members operatively coupled with the trackway wherein the truck members are selectively translatable along the travel circuit, prime movers operatively coupled with the truck member for selectively moving the truck members along the travel circuit, elongate rotor blades having proximal ends operatively coupled with the truck members and opposite free distal ends wherein the rotor blades are carried with the truck members along the travel circuit thereby generating an upward force for lifting associated load-carrying vehicles. The methods and apparatus allow the rotor blades and the transmission to be significantly lighter and easier to manufacture.

Abstract: A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot.

Abstract: According to one aspect of the invention, a turbine assembly is provided, wherein the turbine assembly includes a drum rotor comprising a slot and a closure bucket configured to be placed in the slot, the closure bucket including a lock pin disposed in a base member of the closure bucket. In addition, a portion of the lock pin is configured to rotatably extend into a cavity in the slot thereby securing the closure bucket within the slot.

Abstract: An arrangement and a method for mounting articulated turbine buckets in axial entry slots of rotor wheels. A curvature on a vertical plane may be incorporated on an axial male dovetail projection of the bucket root and the associated axial female dovetail slot of the rotor wheel. The curvature facilitates loading of buckets otherwise precluded by interferences, such as interlocking tip shrouds on adjacent buckets. Such loading may be provided by locating the shroud tip shroud in proximity to an adjacent tip shroud and pivoting the root end of the bucket around the location of the tip shroud such that the arc formed by the bucket allows the curvature of the axial male dovetail projection to swing into the axial female dovetail slot of the rotor wheel.

Abstract: A stator blade and a stator blade arrangement for a turbomachine which is exposable to axial throughflow is provided. Each stator blade is retained via a fixed clamping in a circumferential groove. For the fixed clamping, provision is made on one side of the blade root for a shaped piece with a threaded hole into which a tensioning screw, which is supported on the bottom of the circumferential groove, may be screwed.

Abstract: A compressor disk for a turbine engine includes a plurality of blades mounted about the circumference. To assemble the blades onto the disk a lock assembly is inserted within a blade slot on the disk. A blade is assembled into the blade slot and slider seals are inserted between the blade and the disk to limit air from entering the blade slot. Additional blades are assembled until the end of the slider seals are reached. The process is repeated until all the blades have been assembled onto the disk. After the last blade has been assembled a spacer seal is placed at each lock assembly to take up the slack. Once all the blades and spacer seals are assembled the lock assemblies can be moved to a locked position.

Abstract: A rotor assembly for use with a turbine engine. The rotor assembly includes at least one rotor disk that includes an inner surface that defines a dovetail groove. At least one turbine bucket is coupled to the rotor disk. The turbine bucket includes an airfoil that extends outwardly from a dovetail. The dovetail is inserted at least partially within the dovetail groove. A tang assembly extends from one of the inner surface of the rotor disk and the dovetail. the tang assembly minimizes a rotation of the turbine bucket with respect to the rotor disk.

Abstract: A platform for a bladed wheel of a turbomachine including a drum and blades of hammer-head attachment type, the foot of which is retained in a circumferential groove of the drum, having bearing and/or retaining faces cooperating with the drum is disclosed. The platform includes at least two openings spaced apart circumferentially and each able to receive the foot of a blade, whereby it constitutes a multiple-blade platform in the form of a piece separate from the blades.

Abstract: A device for axially retaining blades mounted on a turbomachine rotor disk is disclosed. The device includes a rotor disk having a plurality of slots and a flange extending radially outwards, cooperating with a bearing face of the disk to define a groove that is open radially outwards. The device also includes a plurality of blades, each having a root mounted in a slot of the disk, each blade root having a respective radial bearing face that corresponds to the bearing face of the disk and that has at least one nib extending radially inwards thereover to define a notch that is open radially inwards, and a retaining ring that is mounted against the bearing faces of the disk and of the blade roots. The retaining ring is housed in the groove of the disk, is held outwardly in the notches of the blade roots, and is constituted by a plurality of angular segments placed end to end.

Abstract: A turbomachine rotor wheel having composite material blades is disclosed. The wheel includes a slideway disk having a circumferential groove at its outer periphery, the groove having an opening that is narrower than its bottom, with a plurality of composite material blades each having a blade root engaged in the groove of the slideway disk and presenting a longitudinal section adapted to the longitudinal section of the slideway disk in order to be held radially therein by co-operating shapes, and an orientation disk fastened coaxially around the slideway disk and including, in its outer periphery, a plurality of axial slots each of which is open at one end. Each slot presents a cross-section that is adapted to the cross-section of a corresponding blade root so as to hold it angularly by co-operating shapes.

Abstract: In one embodiment, a catenary seal structure may be mechanically supported only by two adjacent rotor wheels to isolate a volume between the two adjacent rotor wheels. The catenary seal structure may be annularly disposed about the rotational axis of the adjacent rotor wheels.

Abstract: An airfoil structure, shim, and retention member combination includes an airfoil structure, a retention member and a shim. The airfoil structure may define a first recess. The retention member may define a second recess. The first and second recesses may define a cavity. The shim may include a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity.

Abstract: An array of blades for use in an engine includes a disk having a slot, a pair of rails adjacent the slot and extending above an upper surface of the slot, and a pair of shoulders located outside the rails. A plurality of radially loaded blades are inserted into the slot. A plurality of snaps overhang the rails and rest on the shoulders. Each of the blades is positioned between a pair of snap seals and overlaps a side edge of each one of the pair of snap seals.

Abstract: A closing assembly is provided. The closing assembly closes the gap remaining between the first blade and the last blade of a blade ring that is inserted in a peripheral groove of a turbo machinery, the assembly consisting of at least two lateral parts, at least one of which may be hooked onto a projection that forms an undercut in the peripheral groove and at least one securing element, which secures the parts from coming detached from the peripheral groove. To provide a particularly reliable closing assembly, the securing element is configured as a pin, joining the parts of the closing assembly in a non-positive fit.

Abstract: A closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into a peripheral groove of turbomachinery is provided. The assembly includes at least two parts each of which can be hooked onto projections that form an undercut in the peripheral groove and includes a securing element, which secures the parts from becoming detached from the peripheral groove. For closing the remaining gap, the securing element is mounted to rotate about its longitudinal axis between the two parts and has a key head and a web. The web can be positioned by rotation is such a way that to fit the parts in the peripheral groove. The parts can be displaced in relation to one another and to secure the parts from being detached from the groove. The web can be placed against at least one lateral face of one of the parts.

Abstract: A small twin spool gas turbine engine with a forward end of the engine supported by bearings that are cooled by passing a cooling fluid such as cooling air bled off from the compressor with a liquid lubricant sprayed into the cooling air that is then passed through the bearing to prevent overheating. The cooling fluid is then discharged from the bearing cooling circuit out the front end of the engine through a number of discharge holes formed within the threaded nut that secures the fan blade assembly to the low speed rotor shaft. The threaded nut includes a plurality of slanted holes that slant outward from the rotational axis in the direction of fluid discharge.

Abstract: A fully bladed closure design for a turbine wheel with tangential entry. A set of the final three buckets including a bladed closure bucket are disposed about a wheel margin with two buckets adjacent to the bladed closure bucket secured to the wheel margin by the dovetails. The closure bucket is secured to adjacent buckets by a combination of one or more retaining keys and to the margin by one or more retaining pins. The bladed closure bucket and the adjoining faces of the adjacent buckets have flat skirts providing suppport from the retaining keys across the full axial width of the bladed closure bucket and the adjacent buckets.

Abstract: A blade lock structure for blading an axial flow turbine having a rotor and blades. The blades are inserted into an undercut blade groove of the rotor providing a positive lock between the blades and the rotor. The lock structure includes an entry slot located in the blade groove for receiving the blades for insertion to the undercut blade groove, and an insert space axially extending from the entry slot. The insert space defines a radially extending longitudinal axis. An insert piece is located in positive-locking relationship with the insert space, and a lock screw threadably engages between the insert piece and a closing blade inserted to the entry slot.

Abstract: A rotating body includes a rotor disk 10 that has a moving blade fitting groove 11 that is annularly provided along the outer circumference and a moving blade lead-in hole 12 that is provided in the outer circumference and is in communication with the moving blade fitting groove 11; a plurality of moving blades 20 that are consecutively provided in the outer circumference and that each have a blade root 21 that is fitted in the moving blade fitting groove 11 and a wing body 23 that projects to the outer side of the rotor disk 10; two special moving blades 20A and 20B that each have a blade root 21 of which a portion is fitted in the moving blade fitting groove 11 and a wing body 23 that projects to the outer side of the rotor disk 10, and that by mutually adjoining block the moving blade lead-in hole 12; and a tensioning key 13 that is inserted between the moving blades 20, in which the tensioning key 13 is provided with an insertion portion whose thickness dimension in the circumferential direction gradually

Abstract: A fiber reinforced metal compressor disc includes a hub, a rim and a diaphragm extending radially between the hub and the rim. The fiber reinforced metal compressor disc comprises a first ring of ceramic fibers and a second ring of ceramic fibers. The first ring of fibers is arranged in the hub and the second ring of fibers is arranged in the rim of the disc. The rim of the disc carries a plurality of blades. This arrangement of the rings of fibers minimizes the weight of the disc, especially for large radius discs suitable for carrying large blades and operating at high rotational speeds.

Abstract: A rotor disc and rotor blade assembly in which the rotor blades include curved shear pins to secure the blade to the rotor disc. The blade includes an airfoil portion with an airfoil outline shape at the junction of the airfoil with the platform, and the root extends below the platform and has the general shape of the airfoil at the junction. An opening in the rotor disc also has the shape of the airfoil outline such that the root will fit snuggly within the opening in the rotor disc. Curved slots in both the opening and the root wall are formed on both sides of the opening and the blade root. Shear pins having a rectangular cross sectional shape fit within the slots to secure the blade to the disc. Because the root curvature follows the airfoil shape, the shear pins are located below the airfoil walls and absorb the shear stress caused by bending forces acting on the airfoil from the fluid reaction.

Abstract: An airfoil structure, shim and retention member combination is provided. The combination comprises an airfoil structure, a retention member and a shim. The airfoil structure may comprise a first recess. The retention member may comprising a second recess. The first and second recesses may define a cavity. The shim may comprise a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity.

Abstract: An inner diameter shroud for receiving an inner diameter base portion of a rotatable vane in a gas turbine engine has a single piece channel and a core. The channel has a leading edge wall, an inner diameter wall, a trailing edge wall, a radial outer surface, and at least two axial projections. The axial projections prevent radial movement of the core. The core has an outer radial surface that generally aligns with the radial outer surface of the channel. The core is movable in the channel in a circumferential direction and is configured to rotatably retain the inner diameter base portion of the rotatable vane.

Abstract: A rotor disk for a turbomachine, the disk carrying blades whose roots are retained in a peripheral groove of the disk, the groove including a window for inserting blade roots and a locking member that is a single elastically deformable piece and dimensioned to be received and retained in a notch of the groove while in its free state, and to be capable of being displaced to slide inside the groove while in a stressed and elastically deformed state.

Abstract: Rhombic shrouded tangential entry buckets are circumferentially applied to the rotor wheel rim of a turbine. A fixture is releasably secured to a lug on each bucket and includes a chamfered surface for engaging a complementary surface on the lug. Upon applying a tangential assembly force, the shroud and airfoil of adjacent buckets are pre-twisted in a rotational direction about a generally radial axis enabling dovetail faces to contact one another notwithstanding interference fit shroud contacting surfaces. The removal of the fixture from the lug enables the bias of the airfoil to rotate the shroud in an opposite direction into final assembly with the shroud edges of adjacent buckets in contact with one another and the dovetail faces thereof in contact with one another.