Abstract: A shim for a turbomachine blade is disclosed. The shim includes two branches which wrap around flanks of a blade root, and two tabs. Each of the tabs extend from one end of a respective one of the two branches. The tabs are folded towards each other and are interconnected in such a manner as to prevent them from unfolding. Advantageously, the shim includes a connection part which interconnects the tabs in such a manner as to prevent them from unfolding. The connection part is assembled to the tabs in such a manner as to allow the branches of the shim to spread apart. For example, the connection part can be suitable for stretching in the direction for spreading the branches apart.

Abstract: A turbomachine rotor includes a plurality of turbomachine rotor blades. The turbomachine rotor has a plurality of firtree shaped slots in its radially outer periphery to form a plurality of rotor posts. The turbomachine rotor blades have correspondingly shaped firtree roots to fit in the firtree shaped slots in the turbomachine rotor. The firtree roots of the turbomachine rotor blades comprise a plurality of radially spaced lobes on each of it flanks. The rotor posts of the turbomachine rotor comprise a plurality of radially spaced lobes on each of its flanks. A radially inner lobe of at least one of the turbomachine rotor blades has reduced stiffness such that the load on the radially inner lobe of the at least one turbomachine rotor blade is shared with the other lobes of the at least one turbomachine rotor blade.

Abstract: A blade closing key system includes a first key piece and a second key piece. The first key piece includes a first finger and an elongated alignment plate. The second key piece includes a second finger and a key slot. The key pieces are installed in a cavity collectively formed by a notch in a blade root and a slot in a rotor disc. The first and second fingers are bent toward each other and engage each other at their ends. Simultaneously, at least a portion of the alignment plate is received in the key slot. During engine operation, the engagement between the alignment plate and the key slot keeps the first and second key pieces aligned. Thus, regardless of the width of either of the two key pieces or the width of the cavity, the fingers remain constantly engaged during engine operation, minimizing the potential for blade liberation.

Abstract: The rotor disk carries an axial retention plate facing slots having blade roots received therein, the disk and the plate are shaped so as to define outer circumferential interlock and inner circumferential interlock.

Abstract: The blade retention system comprises an annular sealing plate and a plurality of spaced-apart blade retention tabs having opposite first and second ends and a radially-orientated corrugated profile. The first ends of the tabs are connected to a first side face of the annular sealing plate. Each tab is configured and disposed to be inserted through a bottom portion of a respective one of the blade retention slots when the first side face of the sealing plate is positioned against one of the side faces of the rotor disc and covers an end side of the blade retention slots. The second end of each tab extends beyond the other of the side faces of the rotor disc and is bent to secure the annular sealing plate with reference to the rotor disc.

Abstract: A shim for a turbomachine blade is disclosed. The shim includes two branches which wrap around flanks of a blade root, and two tabs. Each of the tabs extend from one end of a respective one of the two branches. The tabs are folded towards each other and are interconnected in such a manner as to prevent them from unfolding. Advantageously, the shim includes a connection part which interconnects the tabs in such a manner as to prevent them from unfolding. The connection part is assembled to the tabs in such a manner as to allow the branches of the shim to spread apart. For example, the connection part can be suitable for stretching in the direction for spreading the branches apart.

Abstract: A compressor blade for a gas turbine engine that includes a composite leading edge insert attached to a titanium blade by a row of fastener pins along an aft edge of the insert to prevent unzipping. Each insert is also secured by an electrochemically disbondable composition for easy removable of a damaged insert from an integrally bladed disk. One or more of the fastener pins provides for an electrical conductive path that bypasses the disbondable composition during a lightening strike so that the insert does not release. Each replaceable insert includes a root portion that fits within a slot of the rotor disk, with each insert being secured against radial displacement by two shear pins secured within two shear pin slots formed in both the insert root portion and the rotor disk slot. The shear pin slots are curved and follow the curvature of the airfoil at the junction to the rotor disk.

Abstract: A removable fan blade of a turbofan engine includes a blade root at one end thereof. A rotor disk has a retention slot having dimensions corresponding for receiving the root of the fan blade in the slot. An elongated resilient member extends within the retention slot in a lengthwise direction between the root of the fan blade and the bottom of the retention slot and an elongated member extends lengthwise between the root of the fan blade and the elastomeric member to compress the resilient member and provide a radial preload to the fan blade.

Abstract: A fan rotor is provided. Each blade of the fan rotor is held by a bolt. Each blade includes a blade root engaged in a groove of the rim and held by a bolt. The bolt includes a concave plate with its curve directed upstream.

Abstract: A turbo machine airfoil, such as a blade or a vane in a compressor, in which the airfoil root portion includes screw threads having a dove tail cross sectional shape, and the rotor disk includes holes having similar screw threads such that a blade or vane can be easily replaced by unscrewing the old blade or vane and screwing in a new blade or vane. A locking pin biased by a spring is located in the root of the airfoil to lock the airfoil in the threaded hole to prevent the airfoil from loosening due to vibrations and to lock the airfoil in place at a desired angle of attack for maximum efficiency of the turbo machine. The removable cover plate is located on the casing and over the rotor disk such that the blade can be removed through the opening without the need to disassemble the turbo machine.

Abstract: A fan type compressor includes a rotor disk with a plurality of root insertion openings to receive a blade. Each insertion opening includes two shear pin slots on the sides, and the blade includes a root portion with shear pin slots formed on the pressure side and the suction side of the root. The blade is inserted into the insertion opening such that the slots are aligned, and a shear pin is inserted into both slots to secure the blade within the rotor disk. The shear pin slots are formed below the airfoil curvature and follow the airfoil curvature at the root portion. The shear pins are flexible enough to bend during insertion into the slots, and are strong enough to prevent from shearing off during rotor disk operation. The blade attachment structure provides for reduction of the dead weight from the attachment structure in order to simulate an IBR while providing for easy removal and replacement of a damaged blade.

Abstract: The invention relates to a rotor for a non-positive-displacement machine, particularly a rotor for a compressor of a gas turbine, on which at least one shaft collar with an outer periphery and with two radially extending faces are placed. The rotor also comprises a multitude of retaining grooves for moving blades, said retaining grooves being provided on the outer periphery and extending transversal to the peripheral direction and each retaining groove has a groove bottom. In order to provide a rotor for a non-positive-displacement machine that makes it possible to reduce flow losses while having a simple geometrical design of the attachment of moving blades, the invention provides that an annual groove, which extends in an axial direction and which is coaxial to the rotation axis of the rotor, is provided at least on one face of the shaft collar.

Abstract: A fan assembly of a gas turbine engine, the fan assembly includes an array of radially extending blades defining gaps therebetween and an annulus filler located within at least one gap. The annulus filler includes at least two individual bodies arranged circumferentially adjacent one another with at least one adjacent a blade, one of the bodies includes a flexible wall arranged to centrifuge outwardly against the other body thereby urging both bodies against the blades and securing them during engine operation.

Abstract: A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear.

Abstract: A seal plate assembly is provided in a rotor disc for a turbine engine. The seal plate assembly includes a radially extending flange on the disc and an annular groove defined between a radial surface on the flange and a face of the disc. An annular outer surface extends axially in facing relationship to an annular inner surface of the groove. A plate structure is supported between the inner and outer surfaces, and a lock structure is provided for holding the plate structure in place. The lock structure includes an axial leg that is adapted to be located between an inner edge of the plate structure and the inner surface of the groove, and the lock structure further includes a radial leg that is adapted to be located between the radial surface on the flange and an outwardly facing surface of the plate structure.

Abstract: A device for rotationally blocking a retaining ring on a rotor disk three successive blocking hooks of the disk (10), two cleats of the retaining ring, arranged on either side of a split in the retaining ring. The position of the cleats on the retaining ring is such that, when the retaining ring is in place in a groove situated in the rotor disk, the two cleats are in respective abutment against the first and third blocking hooks, and the split is covered by the second blocking hook.

Abstract: A seal plate system (24) for a rotor in a turbine engine. The rotor includes a rotor disc (10) for supporting a plurality of blades (16), and an annular groove (32) provided in the disc (10) adjacent at least one end (30) of the disc (10). A plurality of plate structures (60) are provided supported between the annular groove (32) of the disc (10) and a groove (56) formed in a platform (26) of the blade (16) adjacent an end (30) of the disc (10). The plate structure (60) includes a plate (64) and an elongated resilient locking pointer (66) extending from the plate (64) for engaging in a lock notch (98) formed in an outer wall (38) of the annular groove (32). The locking pointer (66) forms a self-locking feature that is biased into the lock notch (98) as the plate structure (60) is moved into position on the disc (10).

Abstract: Compressor impellers, compressor sections, and methods of manufacturing compressor impellers and cooling the compressor impellers are provided. In an embodiment, and by way of example only, a compressor impeller includes a bore section and a rim section. The bore section comprises a first nickel-based alloy and includes an inner disk portion and a first plurality of blade portions extending therefrom. The rim section comprises a second nickel-based alloy and includes an outer disk portion and a second plurality of blade portions.

Abstract: A blade retaining clip and a blade assembly for axially securing a root portion of a blade component within an axially extending slot of a rotating disk. The blade retaining clip includes a shank portion, a first end portion and a second end portion. The shank portion includes an axial downwardly curved profile. The first end portion and the second end portion are integrally formed at opposed ends of the shank portion. The first end portion and the second end portion are configured to secure the root portion of the blade component within the axially extending slot of the rotating disk. The axial downward curvature of the shank portion minimized operating stresses at the first end portion and the second end portion and subsequent failure of the blade retaining clip.

Abstract: A blade for a rotor assembly including a root portion, a platform with an overhang, an airfoil portion and a sealing plate. The sealing plate protrudes from the blade along a circumferential direction.

Abstract: A turbine airfoil support system for supporting a turbine blade to prevent wear during turning gear operation when a rotor assembly supporting the turbine blade rotates at about two revolutions per minute (RPM) to keep the turbine ready for quick startup requirements. The turbine airfoil support system may be formed from a radial biasing spring positioned between a radially outermost point of a disk steeple extending from a rotor assembly and a radially inner surface of the platform. The radial biasing spring may be formed from a first flat member with a disk steeple engaging surface, a second flat member with a blade platform engaging surface, a bent biasing section extending from the first flat member to the second flat member and biasing the first and second flat members away from each other, and a stress reducing member extending from the second flat member toward the first flat member.

Abstract: A turbine blade locking device axially retains a turbine blade (1) inserted in an axial, profiled slot (10) of a turbine disk (6). The turbine disk (6) is provided with a locking groove (8) passing through the slot (10) and extending radially in the plane of the turbine disk (6). A locking pin (4) is inserted in the locking groove (8) and the blade root (3) is provided at its bottom side with a notch (9) aligning with the locking groove (8). A portion of an elastic element (5) is arranged radially below the locking pin (4) to pre-load the locking pin (4) in a radially outward direction and into the notch (9).

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: A device for axially retaining blades on a rotor disk of a turbomachine, includes an annulus which is mounted via a radially inner edge in an annular groove of the disk and which presses against the roots of the blades mounted in grooves in the periphery of the disk, and an annular lock received in the annular groove of the disk to prevent the annulus from turning, the annular lock being turnable in the annular groove between an annulus-locking position and a position for mounting and dismounting in the annular groove.

Abstract: A rotor end piece (1) for a rotor (6) of a thermal turbomachine, having at least one circumferential slot (3) in which moving blades and intermediate pieces are provided, includes a residual gap (15) formed between an end blade (2) and an end part (11), in which residual gap (15) two end piece halves (4, 4) are arranged which have securing tabs (8, 8) which are in each case connected to the latter in one piece and are in engagement with the end blade (2) and with the end part (11), respectively.

Abstract: A device for the positioning of a blade in a slot of a rotor disk includes a spring spacer that consists of a single elastic piece of profiled shape with a top wall and a bottom wall connected together by two side walls. The two side walls include at least one machined feature.

Abstract: A rotor for a turbo engine is disclosed including a rotor base body and a plurality of rotor blades distributed over the circumference of the rotor base body. The rotor base body is formed by at least one ring-shaped element made of a metal matrix composite material. The rotor blades are attached by footing to the rotor base body in such a way that the footing is positioned in a fiber-free area of the rotor base body.

Abstract: In an axial turbine wheel including a rotor disk and a plurality of turbine blades each having a base end retained by the rotor disk via a joint and extending radially from the rotor disk, a seal plate is received in outer and annular slots formed in the base ends of the turbine blades and rotor disk, respectively, and an annular shoulder is formed in the wall defining the inner annular slot on a side remote from the rotor disk, the annular shoulder thereby defining an inner narrow section and an outer wide section in the inner annular slot. Thus, the seal plate can be easily placed in position by first fitting the inner peripheral edge thereof in the inner narrow section of the inner annular slot, fitting the outer peripheral edge thereof in the outer annular slot until the inner peripheral edge clears the annular shoulder. Thereby, the outer and inner peripheral edges of the seal plate are received in the outer annular slot and outer wide section of the inner annular slot.

Abstract: A blade retention arrangement axially fixes blades (1) to a disk (2). A profiled blade root (3) extending from the airfoil is inserted into a conformal axial slot (5) in the disk (2) and is axially secured by means of a split retaining ring (4), with the retaining ring (4) at least partly engaging a groove (6) on the blade root (3). The disk (2) is provided with a circumferential annular groove (7) which has a radially inward seating face for the retaining ring (4) and the retaining ring (4) is elastically deformable at least in the axial direction.

Abstract: A rotor stage (13, 14, 15, 17, 18, 19) of a gas turbine engine (10) comprises an annular retaining plate (38) capable of preventing axial movement of blades (30). The retaining plate (38) is secured to the disc (32) via a bayonet arrangement (49). A locking assembly (48) is provided to prevent relative rotation between the disc (32) and the retaining plate (38). The locking assembly (48) comprises a locking plug (50) configured in a generally Y-shaped cross section having a channel portion defined by arms (56), which engage upstream and downstream of the retaining plate (38) and a leg part (58) configured to span between bayonet parts (40 and 42), thereby preventing relative rotation between the disc (32) and the retaining plate (38). The assembly (48) further comprises a securing plate (52) configured to span between circumferentially adjacent castellations (40) thereby preventing the locking plug (50) disengaging the disc (32) and retaining plate (38).

Abstract: A device for holding an annular end plate against a radial face of a rotor disc, the disc having in the radial face an annular recess behind a collar extending radially outwards, and the end plate having, in its radially inner part, an annular base bearing against the radially outer wall of the recess and a foot extending radially inwards in the recess from the base, the device including a split annular retaining ring disposed in the recess. The ring is constituted by a snap ring interposed axially between the foot of the end plate and the collar and the peripheral surface of which butts against the base, the peripheral surface and the collar comprising, when joined, notches, which open radially outwards and are intended to receive compression tools for the snap ring, which tools retract into the contour of the collar during the assembly or disassembly of the end plate.

Abstract: A gas turbine engine fan blade (22) and disk assembly (30) is provided with levers (36) with which to apply a force to the radially inner end of respective blades (22) so as to move the roots (26) of the blades (22) into abutting engagement with the side walls of the inverted “V” shaped grooves (32) in the disk rim (34), and thereby prevent relative wearing movement therebetween. The levers (36) are appropriately moved by rotation of respective screws (52) that pass through exposed ends thereof in screw threaded engagement, and abut a fixed land (46) so as to apply a pivoting force on each lever (36).

Abstract: A restraining device for a fan blade root, in which a packing member is constituted by a metal structure having hollowed out portions filed in by overmolding with a semi-rigid elastomer material, in particular on a lateral edge concave side between an upstream end zone and a downstream end zone, which end zones are entirely of metal structure, on a lateral edge convex side between the end zones and a central zone that is essentially of metal structure, and on two top portions of the packing member that extend between the elastomer lateral edges on either side of the metal central zone. The metal structure also includes a bottom recess extending over its entire surface between the upstream end zone and the downstream end zone. Hence, the metal structure behaves like a spring blade when the blade turns following a violent impact.

Abstract: A fastening device for fastening moving blades to a disk of a turbomachine rotor includes moving-blade roots which have a mirror-symmetrical cross section with projections, axial disk slots holding the moving-blade roots in a positive-locking manner, and one riveted joint per moving blade for axially fixing the latter. Each blade root and the disk, in the region of each moving-blade root, have axial extensions. The extensions of moving blade and disk are opposite one another in pairs, in each case a hole lying in a radial plane relative to the disk axis is formed half in the extension of the moving blade and half in the extension of the disk. A rivet is inserted into each hole and fixed by plastic deformation.

Abstract: A connecting assembly of a ceiling fan for fixing blades includes a connecting device mounted to a motor of the ceiling fan and a seat having multiple grooves radially defined in a bottom of the seat. The grooves extend to an outer periphery of the seat. A channel is laterally defined in one side of each of the multiple grooves and laterally communicates with the groove. A buckle is movably received in a corresponding one of the channels. A bracket has a first end inserted into a corresponding one of the multiple grooves and a second end adapted to connected to a blade of the ceiling fan. Each bracket has an indentation laterally defined for selectively partially receiving the buckle to hold the bracket in place when the first end of the bracket is inserted into the corresponding one of the multiple grooves in the seat.

Abstract: A fan rotor includes a disk having a rim with a plurality of substantially axial grooves that are spaced apart angularly. Removable blades extend radially outwards from the periphery of the disk. Each blade has a blade root in a respective groove. A downstream flange plate can be secured to the disk with the downstream faces of the blade roots being in abutment against the downstream flange plate. An upstream flange plate is secured to the disk so as to retain the blade roots in the grooves. In the rotor, the upstream flange plate is fitted on its downstream face with a resilient device configured to exert sufficient force on the upstream faces of the blade roots, after assembly, to prevent an axial displacement of the blades during normal operation (apart from exceptional events of the type in which foreign bodies are ingested or blades are lost).

Abstract: A fan blade assembly (24) comprises a fan rotor (28) and a plurality of radially extending fan blades (30). The periphery (38) of the fan rotor (28) has a plurality of axially extending slots (40). Each of the fan blades (30) has a root portion (42), which locates in one of the slots (40) in the fan rotor (28). Each slot (40) has a slider member (50), which is locatable between the fan blade (30) root portion (42) and the bottom (31) of the slot (40). Each slot (40) has a spring (52), which is locatable between the fan blade (30) root portion (42) and the slider member (50). Each slot (40) has a wedge (54), which is locatable between the slider member (50) and the spring (52).

Abstract: A blade retention assembly is provided that comprises: a disk, a plurality of blades, each having a dovetail disposed in one of an array of slots formed in the outer periphery of the disk, an annular inner retainer attached to the disk, and a plurality of arcuate blade retainers, the blade retainers being secured to the inner retainer by a hooked rabbet joint. A blade retainer is also provided, comprising an arcuate body having a planar inner face having an arcuate depression formed therein defining a sealing lip, and an aft face disposed opposite the inner face which has an arcuate rim formed therein.

Abstract: Rotor blades 40 for a bladed rotor feature a chamfered attachment 44 that improves the energy absorption capability of a snap ring 60 used as one component of a blade axial retention system. The chamfered attachment plastically deforms the snap ring rather than shearing through it in response to abnormally high forces exerted on the blade.

Abstract: The invention provides for a simple and inexpensive fabrication to provide radial position retention to minimize the problems associated with single lobe attachment radial slop.

Abstract: A loading spring segment for radially loading a turbine bucket within a turbine rotor groove includes a substantially circular metal sheet with a gap between opposed edges of the sheet, the sheet defining an arcuate segment in an arcuate length direction of the spring segment; and a plurality of radial slots in the sheet, spaced along the arcuate length direction to thereby create a plurality of individual springs within the arcuate segment.

Abstract: A loading spring segment for radially loading a turbine bucket within a turbine rotor groove includes a substantially circular metal sheet with a gap between opposed edges of the sheet, the sheet defining an arcuate segment in an arcuate length direction of the spring segment; and a plurality of radial slots in the sheet, spaced along the arcuate length direction to thereby create a plurality of individual springs within the arcuate segment.

Abstract: A ceiling fan blade with quick assembly comprises a connector disposed below a disc of the ceiling fan, and a blade holder coupled to the connector, in which the connector has an embedded hole at the end of its insert rod; a blocking groove on the vertical surface of the connector; a spring and a convex insert member are placed in advance, and a blade holder forming an accommodating groove at an end proximate to the connector for receiving the insert rod, and the accommodating groove has a blocking member corresponsive to the embedding hole of the insert rod. By means of pushing the insert rod of the connector into the accommodating groove of the blade holder, the protruded member of connector is exactly blocked by the transversal isolating plate and compresses the spring inward.

Abstract: The invention provides for a simple and inexpensive fabrication to provide radial position retention to minimize the problems associated with single lobe attachment radial slop.

Abstract: A blade retention system, for use with a rotor hub disk with peripheral circumferential array of spaced apart blade retention slots extending between the forward and rearward hub faces, each slot having a radially inward floor and side walls adapted for sliding engagement with a blade root of a rotor blade. The blade root has a bottom surface which when engaged in the slot, is radially spaced from and adjacent the slot floor thus defining a gap extending between the forward and rearward hub faces at said selected broach angle. The blade root retention tab has an elongated web with a thickness less than said gap and including a preformed transverse flange extending from a first end of the web and a second end that extends from the slot and is bent on installation into an installation flange.

Abstract: An attachment mechanism for mounting fan blades to a ceiling fan, characterized in that a ring is attached to the bottom of the motor housing, the ring having a plurality of dovetailed recesses spaced equally apart. A tongue is located on an end of each fan blade, the tongue having a corresponding dovetail shape such that the tongue can be inserted into a recess. A biasing member is located between the recess and tongue to provide a bias that prevents undue vibration.

Abstract: A lockable quick-release blade assembly for ceiling fans is disclosed. The lockable blade assembly comprises a fan blade having one end for inserting into a blade receiving slot in a fan rotor. The blade inserting end is provided with a notch on the longitudinal side for lockably engaging with a blade locking member. A housing defining the blade receiving slot and comprises a blade locking member and a blade releasing member. The blade locking member has a spring biased locking bolt for locking into the notch of the inserted fan blade. The blade releasing member has a spring biased slide slice located atop the housing and abutting the spring biased locking bolt at a 45° angle so that upon a user pressing the releasing member the locked fan blade is released from the locking member.

Abstract: The present invention provides for an easily installed ceiling fan. The fan includes a quick-connect device for physically mounting the fan blades to a ceiling fan hub. The fan blades may be re-positioned from an operating position to an assembly position. In the operating position, the fan blades are locked into position and retained relative to the fan hub by a locking means. In the assembly position the fan blades may be to hung from the drive hub in a collapsed, vertical orientation and then quickly snapped into the extended position during operation. The articulating fan blade assembly of the present invention includes a fan blade hub, a fan blade, and a locking mechanism. The hub includes at least one receiving slot. The fan blade includes a mounting portion extending from its end and includes a tab configured for being received in the receiving slot. The locking means retains the fan blade shaft within the receiving slot upon insertion of the shaft into the receiving slot.

Abstract: A lockable quick-release blade assembly for ceiling fans is disclosed. The lockable blade assembly comprises a fan blade having one end for inserting into a blade receiving slot in a fan rotor. The blade inserting end is provided with a notch on the longitudinal side for lockably engaging with a blade locking member. A housing defining the blade receiving slot and comprises a blade locking member and a blade releasing member. The blade locking member has a spring biased locking bolt for locking into the notch of the inserted fan blade. The blade releasing member has a spring biased slide slice located atop the housing and abutting the spring biased locking bolt at a 45° angle so that upon a user pressing the releasing member the locked fan blade is released from the locking member.

Abstract: A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to a forward extension of the disk at a location between a tip and an axially aft spinner end of the spinner. Non-integral platforms circumferentially disposed between the fan blades. A booster spool is connected to the rotor disk by a mounting plate therebetween and the platforms are radially retained to the disk and mounting plates by pins through holes in mounting lugs depending radially inwardly from the platforms.