Abstract: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades, or rotor blade segments, or an integrally bladed, circumferentially closed rotor blade ring. The rotor blades, or rotor blade segments, or rotor blade ring are/is anchored in the groove extending in the circumferential direction of the rotor base body by a blade base or ring base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments, or ring base of the rotor blade ring, being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.

Abstract: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades or rotor blade segments. The rotor blades or rotor blade segments are each anchored in the groove extending in the circumferential direction of the rotor base body by a blade base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.

Abstract: System for connecting and locking blades which are fixed circumferentially to a rotor disc (1) of an axial compressor, comprising a plurality of blades (10, 10?) positioned in an array along the circumference of rotor disc (1), each blade (10, 10?) being provided with a shaped root (13) for connection to the rotor disc (1), and a dowel for positioning and locking the blades (10, 10?) in a predetermined position in a circumferential seat (3) which has a shaped profile and which is formed along the circumference of the rotor disc (1). At least one insertion slot (4) intersects the circumferential seat (3) to permit the insertion of the roots (13) of the blades (10, 10?) and the dowel.

Abstract: A steam turbine includes a rotor supporting a plurality of turbine buckets. The rotor has shaped grooves for receiving a complementary-shaped bucket hook formed on an end of each of the turbine buckets. A rope seal is disposed in each interface between the bucket hooks and the shaped grooves, respectively. The rope seal serves to seal a leakage path that may exist over the bucket hooks between the buckets and respective rotor grooves.

Abstract: Airfoils and grooves on the rotor or carrier for the airfoils have generally complementary dovetail shapes. The airfoils are installed in the grooves by sliding the bases of the airfoils along the circumferential grooves into final circumferential positions. At each circumferential position, a pin is driven between the base of the airfoil and the bottom of the groove to displace the airfoil radially into a final radially secured position taking up the clearance necessary to enable sliding movement of the airfoils about the groove. A first tool is used to drive each pin in a generally tangential direction by hammering on the end of the tool, transmitting an axial force to the pin. When the circumferential clearance of the last installed airfoil is insufficient to permit further use of a tangentially oriented tool to install additional airfoils, a second tool having an angled head is disposed into the groove to engage the pin.

Abstract: A method of assembling a turbine comprises coupling at least one bucket to a rotor wheel. The bucket includes an upstream side, a downstream side, an airfoil extending therebetween and a dovetail extending radially inwardly from the airfoil to the rotor wheel. The method further comprises fixedly securing the bucket to the rotor wheel with a locking pin that extends from the bucket upstream side through the bucket dovetail to the bucket downstream side.

Abstract: A steam turbine includes a rotor supporting a plurality of turbine buckets. The rotor has shaped grooves for receiving a complementary-shaped bucket hook formed on an end of each of the turbine buckets. A rope seal is disposed in each interface between the bucket hooks and the shaped grooves, respectively. The rope seal serves to seal a leakage path that may exist over the bucket hooks between the buckets and respective rotor grooves.

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 composite blade assembly comprises a root portion and blade portion that is connected to the root portion. The root portion comprises inner and outer rings and the blade portion comprises at least one layer of composite material that is folded to form a loop. The inner ring is disposed in the loop and the outer ring is disposed outside the loop such that a portion of the loop is positioned between the inner and outer rings. In this manner, the loop portion is held in compression between the inner and outer rings at least when the composite blade assembly is subject to centrifugal force to thereby prevent separation of the root portion and blade portion.

Abstract: The rotor blades of a turbomachine are fastened to the rotor (3) of the machine by means of blade roots (1) by the blade roots (1) being anchored in peripheral grooves (2). According to the invention, the blade roots (1) have at least one recess or opening (4), which extends in the peripheral direction and in each of which a connecting piece (5) is arranged. This connecting piece (5) connects at least two blade roots (1) to form a blade pack. By means of the connection, the blade roots (1) are secured against twisting and falling out of the peripheral groove (2). The connecting piece (5) consists of a shaped piece, which is laid with little clearance into the recess or opening (4), a displacement of a blade root (1) and of the connecting piece (5) relative to one another still being possible. The blade root of the last blade of a blade row which is assembled in a peripheral groove is locked to the adjacent blade roots by a final connecting piece.

Abstract: A rotor blade includes an airfoil, an integral platform, and a dovetail integrally joined to the platform. The dovetail includes a neck extending between a pair of dovetail lobes configured to engage a complementary slot in a rotor disk. The dovetail includes an undercut extending between an outer face of the dovetail lobes and the neck for introducing a stress concentration thereat. The stress concentration relieves stress at the outer face at the expense of the neck for increasing the high cycle fatigue life of the blade.

Abstract: A lightweight gas turbine rotor having a pair of high specific strength support ring members positioned fore and aft a center hub member. The unitary center hub member for carrying a plurality of airfoils that extend radially outward therefrom. The pair of high specific strength support ring members are connected to the blade carrying member at a location to compressively transmit the centrifugal force generated by the rotating rotor to a radially inward location on the support ring members. The support ring members being utilized to resist a majority of the centrifugal force generated by the components of the rotor. The center hub member and the pair of support ring members are made of different materials. More particularly the pair of support ring members are made of a metal matrix composite, and the center hub member when utilized in a compressor is formed of a high temperature titanium alloy, and the center hub member when utilized in a turbine is formed of a nickel alloy.

Abstract: A turbocompressor disk having on its periphery a circular groove able to receive blade roots having a substantially hammer shape, said circular groove comprising an upstream lip and a downstream lip against which bear the blade roots. The upstream lip has a curvature of gradient inclined by an angle .alpha. with respect to the plane perpendicular to the rotation axis and the downstream lip has a curvature of gradient inclined by an angle .beta. with respect to the plane perpendicular to the rotation axis, .alpha. being strictly different from .beta..

Abstract: To manufacture a turbine wheel having blades made of a ceramic or composite material and inserted into a metal hub, firstly blades (16) are manufactured that are right cylindrical, each blade having a base (18) through which a hole is formed; a cylindrical ring (20) is formed, the ring being provided with orifices through which the bases (18) of the respective blades (16) are inserted; the blade bases (18) are successively threaded onto an open annular rigid metal wire (30); the resulting assembly (16, 20, 30) is disposed inside a sealed housing (161); hot isostatic compaction is performed so as to compact a metal alloy in powder form (41) inside the sealed housing (161) so as to make the hub of the turbine wheel (100) while embedding the blade bases (18) and the metal wire (30) by using the powder metallurgy technique; and the outside portion of the sealed housing (161) delimiting the hub of the turbine wheel (101) is machined. Application, in particular, to the field of aeronautical or space engineering.

Abstract: This disclosure relates to a fan for an electric machine, the fan comprising a hub having a centrally located bore sized to receive the shaft of the machine, the bore having an axis which coincides with the shaft axis. The fan further comprises a plurality of angularly spaced fan blades which extend radially outwardly from the hub. The blades are formed separately from the hub and are secured to the hub by an improved interlocking joint arrangement. A series of hubs which are substantially identical except for the shaft bore diameter are provided, and a series of blades which are substantially identical except for the radial length are provided. Thus, a hub matching a specified shaft diameter, and a blade length matching a specified housing size, may be selected and assembled to match a machine.

Abstract: A retainer ring is arranged to mount turbine blades to a turbine disk so that aerodynamic forces produced by a gas turbine engine are transferred from the turbine blades to the turbine disk to cause the turbine blades and turbine disk to rotate, but so that centrifugal forces of the turbine blades resulting from the rotation of the turbine blades and turbine disk are not transferred from the turbine blades to the turbine disk.

Abstract: A gas turbine engine impeller having a plurality of blades attached to a rotor disk and an integral, annular collar defining openings through which the blades extend which acts as a platform extending between the adjacent blades. The annular collar is formed as an integral, annular structure and may be formed from a composite material, or other material which is resistant to high temperatures and high centrifugal forces. The annular collar defines a plurality of openings to accommodate the blade portion of the plurality of blades and to enable the blades to extend radially outwardly from the collar. The openings may be formed in the annular collar when the collar itself is formed, or may be machined therein after the collar has been fabricated.

Abstract: A platform spacer is joinable to a rotor disk between adjacent rotor blades having dovetails retained in a circumferential dovetail groove therein. The spacer includes a platform having a flat upper surface sized for abutting adjacent blade platforms to form an inner flowpath, and first and second hooks extending downwardly from the platform lower surface. The first and second hooks are configured for insertion radially inwardly through first and second loading recesses in the rotor disk for retention thereto.

Abstract: A gas turbine engine having an outer annular turbine rotor, which is counterrotatable relative to an inner annular turbine rotor, includes attachment structure for attaching turbine blades in circumferential rows to the inner rotor. The attachment structure includes first and second male members of hook-like configurations spaced axially along and circumferentially extending about the rotor, and first and second grooves defined by flanges attached to the rotor and axially spaced along and circumferentially extending about the rotor. The grooves open in a common axial direction for receiving in mated relation respectively and concurrently the hook-like configured first and second male members. The attachment structure also includes several different locking arrangements for locking the male members in mated relation with the grooves to thereby restrain the turbine blade against radial and axial movements relative to the rotor.

Abstract: A gas turbine engine having an outer annular turbine rotor, which is counterrotatable relative to an inner annular turbine rotor, includes attachment structure for attaching turbine blades in circumferential rows to the outer rotor. The attachment structure includes first and second male members spaced axially along and circumferentially extending about the rotor, and first and second grooves spaced axially along and extending circumferentially about the rotor being defined by flanges attached to the rotor. Each male member has a first portion attached to an end of a turbine blade and extending therefrom in a radial direction. The first male member has a second portion attached to its first portion and extending therefrom in an axial direction to define the first male member with an overall hook-like cross-sectional configuration. The first groove is cross-sectionally shaped for receiving in mated relation the second portion of the first male member.

Abstract: The invention comprises an internal blade retention system for rotary engines and particularly for gas turbine engines. The system comprises a rotary disk 12 positioned for rotation within the turbine engine, the disk having a multitude of dovetail blade slots 16 and a groove 12E centrally positioned on its circumferential edge and cutting across the blade slots. A preloaded circular snap ring 10 is positioned in the centrally located groove 12E on the disk edge and in its relaxed position the snap ring extends radially outward from the groove. Multiple blades 14 are installed onto the blade seats in the disk, each of the blades having a base with a centrally located goove 14E that engages the snap ring 10 in order to axially lock the blade in its seat.

Abstract: An anti-rupture ring is slit axially at least at one location and is provided thereat with clamping devices which permit a rapid tightening and loosening of the anti-rupture ring. In one embodiment, the clamping of the anti-rupture ring can be varied hydraulically so as to minimize clearance losses in operation. The invention can be used in all types of turbo engines endangered by breakage of rotor blades, particularly in aircraft gas turbine construction, and it permits simple, damage-free mounting and a well-defined clamping of the anti-rupture ring.

Abstract: In a compressor rotor assembly of an axial flow gas turbine engine, wherein the rotor disk has a circumferential blade retaining slot for receiving the root of each blade of a row of blades, a ladder seal is provided between the slot and the blade platforms to limit the leakage of working medium gases from the flow path and through the slot. During engine operation, the seal moves radially outwardly into sealing relation with the underside surface of each platform. At the same time, radially inwardly extending flanges of the seal move radially outwardly into sealing relation with the sidewalls of the disk slot.

Abstract: In an axial guide blade assembly for a compressor stator, the root end of each guide blade is attached in a ring gap of a preferably axially split, i.e. split along a normal plane, compressor housing made of a fiber reinforced synthetic material. The root of each blade is received in the ring gap or circumferential groove formed between two adjacent housing sections joined together along the axial separating plane. The guide blades hang on fiber rings with which the blade roots are clamped into the circumferential groove.

Abstract: The pre-load device for a turbomachine rotor according to the invention has a shank formed of a superplastic material which is axially insertable in a shank bore formed between confronting notches formed on a rotor disk and a blade root portion. In one embodiment, the notches extend generally parallel to the longitudinal axis of rotation of the rotor disk. The shank defines an interior chamber in which is located a low-melting point material. An electrical resistance heating element is located in the low-melting point material and has means to be connected to an electrical source. The device also includes headed portions attached to each end of the shank, each of the headed portions bearing against axially facing surfaces of the rotor disk and the blade root so that, when the head means are attached, relative axial movement between the elements is prevented.

Abstract: A carrier ring for a large diameter propeller system fabricated from a composite material having metallic blade mounting insert members in which are fastened roots of the propeller blades. The carrier ring has an annular ring member formed of a composite material which defines a plurality of radially extending openings, in which openings metallic blade mounting insert members are attached. The blade mounting insert members are retained in assembled relationship with the composite annular ring member by one or more fastening belts which extend around the circumference of the annular ring member in one or more grooves defined by the blade mounting inserts. The fastening belts may be formed by a plurality of turns of a fibrous filament, such as carbon filaments, so as to provide the necessary strength to retain the metallic blade mounting inserts in the composite annular ring member.

Abstract: A strong, lightweight blade provided for use on wind turbines utilizes an interior reinforcing strut which extends part-way out the blade and consists of telescoped steel pipes welded to one another and mounted at their root ends to a steel cuff. A carbon graphite spar slips over the telescoped tubes and inside the cuff and extends radially outwardly substantially to the end of the blade. A rigid skin which is airfoil-shaped in all of its cross-sections attaches to the spar and spans from the root of the spar to the distal tip of the blade, defining the wind-driven surfaces of the blade.

Abstract: A method for assembling a plurality of bucket assemblies having tangential entry dovetails onto a wheel of a turbomachine such that a predetermined circumferential force is obtainable on the bucket assemblies when assembled, includes reducing the distance between lateral faces on the base portion of at least a first bucket assembly and preferably all bucket assemblies, such as by cooling, and increasing the distance between the lateral faces after assembly, so that the predetermined circumferential force is obtained. Alternatively, the wheel circumference may be increased as by heating before the bucket assemblies are assembled. A combination of appropriate heating and cooling may be used. A closure piece having a predetermined circumferential expanse may be inserted in the bucket row of the wheel to obtain the desired circumferential force.

Abstract: The blade rotor structure of an axial flow elastic fluid utilizing machine such as a turbine is divided into groups by a lashing wire structure. The lashing wires of adjacent groups are flexibly connected to each other by sleeves that are held in place without heating so that the sleeves can be used with electroplated blades without the problems associated with brazing.

Abstract: A turbine wheel for a hot gas turbine engine operable at relatively high peratures, e.g. above 2,000.degree. F., and high velocities, e.g. above 30,000 r.p.m. The blades are formed of temperature-resistant ceramic material. A special annular band of high tensile strength material is affixed to tip areas of the blades for translating centrifugal forces into compressive loadings on the blades. To compensate for differential thermal expansion of the band relative to the blades a localized cooling system is provided for selectively cooling the annular band without cooling the blades.

Abstract: Device for the containment of fragments of a fan ring in the event of burng of the ring.The fan ring comprises two cylindrical surfaces spaced axially and located radially inside of two containment rings of high tensile strength in the circumferential direction, engaged respectively in grooves of two parts of the rotor, located on either side of the fan ring.

Abstract: A circumferentially extending structure 30 for containing particles having an axial component and a radial component of velocity is disclosed. The apparatus is comprised of a support structure 46 and a fabric 44 wrapped under tension about the support structure such that the installed length of the fabric is greater than the free length of the fabric. In one particular embodiment the fabric is coated with a layer of epoxy resin such that the resin penetrates only the top layer of the fabric to form a shield 95 which protects the containment fabric from injury. A method for forming the circumferentially extending structure is disclosed which includes the steps of forming a support structure and wrapping a fabric about the support structure under a preload to cause an elongation of the fabric and tension in the fabric in the installed condition.

Abstract: A circumferentially extending structure 30 for containing particles having an axial component of velocity and a radial component of velocity is disclosed. The structure includes an inner casing, such as the first casing 48, and an outer casing, such as the second casing 50. The outer casing is flexible. The outer casing is formed of a plurality of layers of fabric and a means for applying a load to the fabric such as a plurality of bars 80, 82 and turnbuckles 74. A method of forming the structure is disclosed. The method includes the step of wrapping a fabric having a first length about the inner casing and the step of stretching the fabric to a second length to affect the operative response of the fabric to the impact of a particle.

Abstract: The Assembly has a submerged root, turbine-wheel-blading configuration, and utilizes circumferentially oriented, buried, friction damping wires, and continuous, overlapping, tip shrouds to minimize vibratory response. The wires, in the presence of blade vibration, simultaneously rub on both the blades and surfaces of a recess in the wheel in which the blade roots are fixed. The continuous tip shrouding provides additional damping through shroud-to-shroud interface rubbing. The assembly has a stack of identical blades, obviating any need for relatively weak locking blades or pieces. The method defines the steps of forming a peripheral recess in a wheel, in which to secure root ends of blades, and setting the damping wires (or wire) therein prior to installing the blade root ends, and uniformly spacing-apart the blades after securing the same to the wheel.

Abstract: The assembly has a submerged root, turbine-wheel-blading configuration, and utilizes circumferentially oriented, buried, friction damping wires, and continuous, overlapping, tip shrouds to minimize vibratory response. The wires, in the presence of blade vibration, simultaneously rub on both the blades and surfaces of a recess in the wheel in which the blade roots are fixed. The continuous tip shrouding provides additional damping through shroud-to-shroud interface rubbing. The assembly has a stack of identical blades, obviating any need for relatively weak locking blades or pieces. The method defines the steps of forming a peripheral recess in a wheel, in which to secure root ends of blades, and setting the damping wires (or wire) therein prior to installing the blade root ends, and uniformly spacing-apart the blades after securing the same to the wheel.

Abstract: A circumferentially extending apparatus 46 for containing particles having an axial component and a radial component of velocity is disclosed. The apparatus is comprised of a support structure 48 and a flexible casing 50 formed of a fabric 78. The external surface of the support structure has a first diameter and a second diameter not equal to the first diameter at a location spaced axially from the location of the first diameter. The fabric is preloaded to increase the length of the fabric and is wrapped under tension about the surface of the support structure such that the installed length of the fabric is greater than the free length of the fabric. A method for forming the circumferentially extending structure is disclosed which includes the steps of forming a support structure and wrapping a preloaded fabric about the support structure to cause an elongation of the fabric and tension in the fabric in the installed condition, which varies depending on the diameter of the support structure.

Abstract: A dovetail type circumferential slot fixing for retaining blades of a bladed rotor assembly of a turbomachine which requires no additional loading slot. The shape and dimensions of the dovetail roots of the blades and the dovetail blade-retaining slot are such as to allow the blades to be loaded by introducing a flank of each root dovetail into the slot and rolling the blades in an axial direction. The blades are held outwards against radially inward facing faces of the blade-retaining slot by a support means which may be a detachable plate, flange member or nose bullet that engages the blade platforms.

Abstract: A rotor stage assembly 20 of the type adapted for use in an axial flow gas turbine engine is disclosed. The assembly includes a rotor disk 36 having blade attachment slots 42 configured to receive a plurality of rotor blades 40. Each rotor blade is insertable into the disk in a generally axial direction. Each rotor blade is retained against fore and aft movement by a lock pin 52. The disk is adapted by a groove 44 and the blade is adapted by a groove 48 to receive the lock pin. During assembly the lock pin is slidable in the grooves 44,48 to bring the lock pin into engagement with the corresponding groove in a rotor blade in a corresponding groove in the disk.

Abstract: A compressor rotor for a turbine comprises individual segments radially stressed by a bandage of fibre-reinforced material which is under prestress when the rotor is stationary. The bandage cross-section has regions of different stiffness and different tensile strength, constituted by retaining rings arranged one inside another or side-by-side.

Abstract: A rotor for axial-flow turbomachines with a locking pin connection for the blade roots. The blade roots are suspended in fiber-reinforced retaining rings and evidence cylindrical circumferential surfaces at their lower side. These cylindrical surfaces contact a correspondingly conformed circumferential surface on the metallic rotor disc.

Abstract: A rotor wheel, particularly for compressors, including a rotor disc and a plurality of radially-projecting metal blades arranged along the periphery of the disc. A plurality of locating rings, formed predominantly of directionalized fibers, are provided, each locating ring being adjacent to all the blade roots and serving to resist centrifugal loads on the blades. An attachment ring formed predominantly of undirectionalized fibers surrounds the periphery of the rotor disc, and all the blade roots and locating rings are embedded in the attachment ring. The attachment ring serves to attach the blades to the rotor disc. Each blade root may have a T-shape and each locating ring engages over the cross bar of the T of each root. Alternatively, each blade root may have a hole accommodating a pin, and each locating ring engages over the pin of each blade root. Each blade root may have a plurality of sections, a single pin passing through holes in all of the sections of each root.

Abstract: An apparatus for attaching blades to a compressor rotor for a turbojet including a rotor drum in which holes are provided which extend radially and into which the blades are inserted. The blades include successive platform portions by means of which such draw support from the wall portion of the holes, such blades being locked radially to the drum by means of a cotter pin engaged between foot portions of two adjacent blades and pressing against the interior surface of the drum.

Abstract: An object of the invention is to prevent the leakage of working medium gases across a rotor stage beneath the platforms of the rotor blades.A rotor assembly structure in which the concepts of the present invention are employable is disclosed. Techniques for blocking the leakage of working medium gases around a rotor stage beneath the platforms of the blades are discussed.

Abstract: Hollow filament wound spar structure is provided adapted for rotational hub mounting under centrifugal and bending loads. The structure comprises an integrally wound, filament and resin composite spar of a predetermined wall thickness, a fitting integrally wound therein, the fitting defining rotational hub fastening means and comprising a plug having a mechanical engagement groove circumferentially of its longitudinal axis into which the opposing spar wall portion is deflected responsive to winding fabrication of the spar wall on the fitting. Belt means additionally are provided opposite the groove locally peripherally confining the deflected spar wall portion in mechanical engagement reinforcing relation, against relative dislodgement of the spar wall portion from the plug groove in the mounted condition of the spar structure, under centrifugal and bending loads.

Abstract: A rotor assembly including a spool and a plurality of radially extending rotor blades mounted in a groove provided circumferentially of the spool is described. The groove includes a pair of inwardly extending flanges which define a throat area narrower than the groove. A stacking hole extends radially and communicates with the groove to allow the rotor blade members to be individually mounted to the spool. The locking device for retaining the rotor blades in the spool includes a C-shaped spring adapted to urge against the roots of each rotor blade in the groove and a locking protrusion adapted to engage in the stacking hole and in an opening formed in the platforms of two adjacent blades straddling the stacking hole whereby the locking device abuts against the ends of the flanges in the stacking hole and retains the rotor blades against circumferential movement. A pair of anchor members can also be provided near the ends of the C-shaped spring member for engagement in the root of pairs of blades.

Abstract: A fan for use as a front fan or in the lift fan system with aircraft jet engines having blades supported by a segmented hub platform and a segmented tip platform which are supported by hub support hoops and tip support hoops. The blades are secured to the hub platform segments and tip platform segments by composite pre-preg pin stock which is inserted in holes in the tip platform, the hub platform and fan blades. The pins are placed under axial compression to expand the pin diameter to provide a precise fit. Channel members are provided between the tip hoops and the blades. Some of the channels have extensions which form seals.

Abstract: A rotor driven for an axial flow gas turbine engine compressor is formed as a composite structure of inner and outer skins with a core therebetween and a set of tensile reinforcing rings each located in a respective groove of a corrugated outer surface of the drum. In the completed drum the drum body is preferably under compressive prestress while the reinforcing rings are under tensile prestress.

Abstract: A rotor blade system which is adaptd for long term reliable operation in a gas turbine engine is disclosed. Techniques incorporating composite materials into the rotor system are developed. One rotor structure shown utilizes a paired blade assembly having a core of continuous fibers running from the tip of one blade to the tip of the adjacent blade. Each of said paired blade assemblies is mchanically detachable from the engine rotor.

Abstract: A fan rotor has a hub having a peripheral rim, a plurality of segments assembled together in the rim to form a ring, at least some of the segments having a base portion which forms a segment of the ring and a blade integral with the base and extending outwardly therefrom, slots in the segments and a U-shaped clamping member having its legs in slots of adjacent segments which hold the segments together.

Abstract: Rotor parts, such as blades, are locked in axially extending slots in a rotor by locking members positioned in circumferentially extending slots extending between and intersecting the axially extending slots. The locking members are slidably positionable into the circumferentially extending slots and displaceable between a release position and a locking position where they hold the rotor parts within the axially extending slots. A retaining element is in operative association with the locking member for securing it in the locking position. The locking members have ridges which seat against corresponding ridges formed in the circumferentially extending slots for retaining the locking members within the slots. In the locking position, the locking elements form a closure for the opening through the rotor surface into the circumferentially extending slots so that a completely smooth surface is presented on the surface of the rotor.