Abstract: A rotor assembly includes a rotor having a dovetail slot. The dovetail slot includes a plurality of recesses and a first radially innermost surface. A rotor blade includes an airfoil that extends radially outward from a platform and a dovetail that extends radially inward from the platform. The dovetail includes a plurality of projections extending in opposite directions that are received by the plurality of recesses of the dovetail slot. The dovetail further includes a leading edge surface, a trailing edge surface, and a second radially innermost surface. The second radially innermost surface defines a groove from the leading edge surface to the trailing edge surface. The shim is positioned within the groove and between the first radially innermost surface of the dovetail slot and the second radially innermost surface of the dovetail.

Abstract: A turbine wheel that retains a fixation wire to inhibit the movement of turbine rotor blades along mating grooves includes: multiple tab sections that form housing sections that house part of the fixation wire; and a wire retention pin to retain the fixation wire in the housing sections. The tab section has a pin slot extending from the radially inner end toward the radially outward side. The wire retention pin has a first pin section having a width smaller than the pin slot and a second pin section having a width larger than the pin slot. The first pin section has multiple divided pieces. The wire retention pin is arranged such that the first pin section is positioned in the pin slot and the second pin section is positioned in the housing section, and is fixed to the tab section with the divided pieces bent outward.

Abstract: A method includes: an arrangement step of arranging a phased array probe including a plurality of oscillators each of which is capable of emitting ultrasonic waves on an end surface of the rotor disc, in a parallel state in which the plurality of oscillators are arranged along a circumferential direction of the rotor disc; a first transmission step of emitting ultrasonic waves from the plurality of oscillators in the parallel state, while a timing of emitting the ultrasonic waves from each of the oscillators is controlled in a first emission pattern, and receiving reflection waves of the ultrasonic waves; and a second transmission step of emitting ultrasonic waves from the plurality of oscillators in the parallel state, while the timing of emitting the ultrasonic waves from each of the oscillators is controlled in a second emission pattern different from the first emission pattern, and receiving reflection waves of the ultrasonic waves.

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle. The fan blades are provided with at least a first type having a first natural frequency, and a second type having a second natural frequency. The fan rotor has a first mount structure intended for the first type and a distinct second mount structure intended for the second type. The first type of fan blade fits into the first mount structure intended for the first type, but there is a first obstruction preventing the first type of fan blade from being placed into the second mount structure intended for the second type. The second type of fan blade fits into the second mount structure intended for the second type, but there is a second obstruction preventing the second type of fan blade from being placed into the first mount structure intended for the first type.

Abstract: A propulsive assembly for an aircraft includes a nacelle and a turbojet. The nacelle includes an upstream air inlet section. The turbojet includes a fan with removable blades. The air inlet section extends longitudinally. The fan includes a rotary disk including an annular peripheral wall and a plurality of curvilinear recesses positioned circumferentially in the wall. Each blade includes a blade body extending between a blade root and a blade head in a blade axis which is roughly radial relative to a fan rotation axis. Each blade root includes a curvilinear attachment housed in a respective recess of the rotary disk. Each attachment has a support surface forming an arc. The function of the support surface is to hold the attachment in the recess. The arc extends in or parallel to an attachment plane containing the blade axis or forming with the blade axis an angle of less than 15°.

Abstract: A rotor blade arrangement for a turbomachine having a blade carrier, on whose outer circumferential surface there is formed a circumferential T-shaped slot, having a blade ring which has a plurality of blades and spacers, that are inserted in alternation into the T-shaped slot, and having support elements that are braced between the blades and spacers on one hand and a base of the T-shaped slot on the other hand such that the blades and spacers are pressed radially outward, a separate support element being assigned to each spacer and being releasably held thereon, in particular secured in a clamping manner. A method includes assembling a rotor blade arrangement.

Abstract: A rotationally symmetrical part, such as a disk, for a turbine engine rotor. The part has a rotational axis (A) and includes, an annular row of teeth defining grooves therebetween for therein holding fir tree-shaped rotor blade roots. Each tooth includes a first side flank, having at least two projecting portions for holding a blade root and separated from each other by a hollow portion, and a second side flank including at least two projecting portions for holding an adjacent blade root and separated from each other by a hollow portion. Each tooth has, on substantially the entire longitudinal dimension thereof, a lack of symmetry in relation to a substantially radial median longitudinal plane. At least one of the circumferences of the projecting portions of the second flank is located between the circumferences of the projecting portions of the first flank and is radially shifted from the circumferences.

Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.

Abstract: The gas turbine engine rotor can have a body having a solid-of-revolution-shaped portion centered around a rotation axis, the body defining an annular cavity centered around the rotation axis, the annular cavity penetrating into the body from an annular opening, the annular cavity extending between two opposite annular wall portions each leading to a corresponding edge of the opening; and at least one structural plate mounted to and extending between the two opposite annular wall portions and forming an interference fit therewith.

Abstract: In one embodiment, a hub for a fan of a gas turbine engine is provided. The hub having: a plurality of attachment features located on an outer circumferential surface of the hub, wherein at least some of the plurality attachment features extend radially away from the outer circumferential surface and are axially aligned with each other and at least some of the plurality of attachment features extending radially away from the outer circumferential surface and are off set from each other, and wherein the plurality of attachment features have an opening configured to receive a portion of a pin; and wherein at least some of the plurality of attachment features are located on a forward leading edge of the hub.

Abstract: A method of forming a curved slot in a turbine disk includes the steps of forming a pre-slot in the turbine disk and finishing the pre-slot to form a slot that receives a portion of a turbine blade. The turbine disk including a first face, an opposing second face, and an outer perimeter surface extending between the first face and the opposing second face. The pre-slot includes a first curved wall and a second curved wall that each extend between the first face and the opposing second face. An intersection between the outer perimeter surface and each of the first curved wall and the second curved wall is defined by a curved line.

Abstract: The invention relates to a turbomachine rotor including a disk and at least one blade wherein the root comprises a bulb accommodated into a groove associated with the disk, wherein the bulb includes a slot that opens up radially inwards at its lower face, and in that the rotor includes a retaining part extending partly into the groove projecting radially outwards from the bottom face of the groove, of which a radially outer end of the retaining part fits into the slot of the bulb and bears radially inwards on the inner wall of the slot of the bulb.

Abstract: The subject application relates to blade root wedging lock in a circumferential groove in a rotor such as the drum of an axial turbomachine compressor. The body (32) of the lock includes a solid portion (38) designed to be housed in the groove and having two opposite bearing surfaces (40) and at least one circumferential wedging surface (42). The body (32) further includes an upper portion (36) in the shape of an elongated generally vertical chamber designed to be flush with the upper surfaces of the platforms of adjacent blades when the lock is correctly positioned. This chamber (36) is truncated (44) so as to reduce its length in a direction perpendicular to the circumference, corresponding to the axis of rotation of the rotor. The lock can thus be accommodated in a narrow groove without decreasing the diameter of the clamping screw passing through the hole (34). The subject application also relates to a rotor and a turbomachine equipped with the lock.

Abstract: A turbomachine rotor blade has a firtree shaped root, to be secured in a rotor disc rotatable around a rotor axis. In a plane perpendicular to the rotor axis, the root has a first, second, and third root lobe with a first, second, and third root contact face. Each of the first, second, and third root contact face is angled relative to a radial root bottom axis with a first, second, and third root angle, respectively. The first root angle is smaller than the second and the second root angle is substantially equal to the third. A turbomachine rotor disc has a firtree shaped slot having a first, second, and third slot angle, the first slot angle being smaller than the second and the second slot angle being substantially equal to the third. A gas turbine engine has the turbomachine rotor herein.

Abstract: A compressor disc for a compressor of a gas turbine engine includes a circumferentially extending groove for receiving blade roots of a plurality of compressor blades. The circumferentially extending groove includes a planar surface offset into the groove.

Abstract: The present application provides a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor and a locking blade positioned about the rotor. The locking blade may include a base, a first side hook, and a second side hook. The locking blade may include a first side pilot hole defined between the base and the first side hook and a second side pilot hole defined between the base and the second side hook.

Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define an angled first inner surface of the first end piece. The root portion defines a first projection adapted to project into a recess portion of the attachment slot. A second end piece fits between the first inner surface and a sidewall portion of the attachment slot and includes a platform portion and a root portion that define a second projection adapted to project into a recess portion of the attachment slot. The platform portion and the root portion define an angled second inner surface and that is configured to mate with the first inner surface. A borehole extends through the platform portion of the first end piece and the root portion of the second end piece and a fastener extends through the borehole.

Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define a first inner surface of the first end piece. The root portion defines a first projection and an opposing second projection of the first end piece. The first projection has an outer profile adapted to project into a first lateral recess of the attachment slot. The second projection has an outer profile adapted to project into a second lateral recess of the attachment slot. A second end piece fits between the first inner surface of the first end piece and a sidewall portion of the attachment slot and includes a platform portion and a root portion. A borehole extends continuously through the first end piece and the second end piece. A fastener configured to engage with a sidewall portion of the attachment slot extends through the borehole.

Abstract: The present application provides a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor, and a locking blade positioned about the rotor. The locking blade may include a multi-piece configuration.

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

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

Abstract: A blade assembly for a groove of a wheel of rotating machinery is described. The blade assembly includes, a blade root having two longitudinal sides, a base, and a roof, wherein the profile of the longitudinal sides includes a rounded surface, a blade connected to the roof of the blade root, and one or more keys juxtaposed along each longitudinal side of the blade root, each key having an inboard side and an outboard side, wherein the profile of the inboard side of each key is configured to mate with the profile of the blade root. The blade assembly allows replacement of a compressor blade without the need for unstacking the rotor to gain access to the damaged blade.

Abstract: A process of preparing a turbine rotor wheel, a repair tool for machining a turbine rotor wheel, and a turbine rotor wheel are disclosed. The process includes providing the turbine rotor wheel, the turbine rotor wheel having a dovetail slot, a cooling slot, and a dovetail acute corner formed by the dovetail slot and the cooling slot and removing a stress region from the dovetail acute corner. The repair tool permits removal of strained material while also reducing the operating stress of the feature. The turbine rotor wheel includes a machined portion resulting in lower stress for the turbine rotor wheel.

Abstract: A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction.

Abstract: A gas-turbine blade root 1 has at least two essentially rectangularly adjoining surfaces 4, 5 for locating the gas-turbine blade root 1 and a transition area of the surfaces 4, 5 includes a bevelled, plane edge 6.

Abstract: A disk for a turbine engine is disclosed herein. The disk includes a rotatable body extending along a longitudinal axis between a forward side and an aft side. The disk also includes a plurality of slots disposed about a periphery of the body. Each of the slots extends between the forward and aft sides along a respective slot axis. The sides of each of the slots are asymmetrical relative to one another in a cross-section normal to the slot axis.

Abstract: Disclosed is a rotor assembly for a turbomachine includes a disk having a first axial face and a second axial face. The disk includes at least one circumferential dovetail extending around an outer surface of the disk and a plurality of axial dovetails extending from the first axial face to the second axial face. Each blade of a plurality of blades is installed into an axial dovetail of the plurality of axial dovetails and each platform of a plurality of platforms is installed adjacent to a blade of the plurality of blades via the at least one circumferential dovetail. Further disclosed is a method of assembly of a rotor for a turbomachine.

Abstract: A rotor for a turbine engine has a pair of spaced rails that extend around a cylindrical surface space. The rails define a space for receiving blades and locks. A plurality of slots are formed in one of the rails, with an opposed surface on an opposed rail not being formed with a slot. The slots are utilized to move at least one of the locks and the blades into the space.

Abstract: Disclosed is a rotor assembly for a turbomachine includes a disk having a first axial face and a second axial face. The disk includes at least one circumferential dovetail extending around an outer surface of the disk and a plurality of axial dovetails extending from the first axial face to the second axial face. Each blade of a plurality of blades is installed into an axial dovetail of the plurality of axial dovetails and each platform of a plurality of platforms is installed adjacent to a blade of the plurality of blades via the at least one circumferential dovetail. Further disclosed is a method of assembly of a rotor for a turbomachine.

Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has an end portion extending between a reference section and a radially outer end of the blade with respect to a rotation axis of the blade; the rotation axis is outside the blade and crosswise with respect to the longitudinal axis; the length of the chord at the end portion decreases from the reference section to the radially outer end; and the leading and trailing edges are joined at the radially outer end.

Abstract: A cylindrical casing for a turbomachine that is suitable for receiving a rotor fitted with at least one bladed wheel is disclosed. The casing includes a device for preventing instability during contact between the casing and the bladed wheel. The device includes a succession of elements disposed around the circumference of the casing, and presenting different stiffnesses between two adjacent elements. The number of elements having the same stiffness not being equal to a multiple of the wave number of the vibratory mode of the bladed wheel that is to be inhibited. The invention is applicable to a compressor, a turbine, or a fan.

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 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 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 method of manufacturing a turbine disk involves machining to an initial form a slot in a turbine disk using a firm cutting tool. An intermediate form is then machined using a second cutting tool different from the first cutting tool. A final form using a third cutting tool different from the first cutting tool and the second cutting tool is then machined.

Abstract: A turbine engine and a rotor for a turbine engine are provided. Several adjacent turbine blades are positioned in the circumferential direction of the rotor, each turbine blade having a blade root, each turbine being fixed in a retainer groove, running in the circumferential direction of the rotor, by means of the blade root. Each turbine blade may be introduced, by the blade roots thereof, into the retaining groove, by means of a filling groove, whereby the width of the filling groove is matched is matched to the width of the blade roots. The width of the blade roots (13, 14) and the width of the, or each filling groove (17) in the circumferential direction is greater than half the width of a desired nominal blade pitch (18), whereby in the region of the, or each filling groove (17), a first number of turbine blades (11) with desired nominal blade pitch (18), is exchanged for a second number of turbine blades (12), with increased blade pitch (19), the first number being greater than the second number.

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: The invention relates to a bladed disk for a turbomachine, the disk including blades which extend into a conical stream and which are held in a peripheral groove of said disk by hammerhead type fasteners, each of said blades further including a platform whose radially-outer face defines the boundary of the gas flow stream and whose radially-inner face presents an upstream rib and a downstream rib disposed in planes that are perpendicular to the axis of rotation of said disk and that are radially adjacent respectively to an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove in order to provide leaktightness in these zones, wherein the thickness of the downstream rib in the axial direction is greater than the thickness of the upstream ring.

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 turbomachine, in particular a gas turbine, includes a rotor which extends along an axis of rotation. The rotor includes a circumferential face, which is defined by the outer radial boundary surface of the rotor, and a receiving structure. Additionally, it includes a first rotor blade and a second rotor blade, which each have a blade root and a blade platform. The blade platform of the first rotor blade and the blade platform of the second rotor blade adjoin one another, and a space is formed between the blade platforms and the circumferential face. A sealing system is provided on the circumferential face in the space, the sealing system including a labyrinth sealing system.

Abstract: A locking device (36) for use in retaining an assembly of rotor blades against movement around a rotor disc on which they are mounted comprises a body member having first and second portions interconnected by a weakened region (66) whereby a force applied to turn the first portion (38) relative to the second portion (40) can cause them to shear apart at said weakened region (66) thereby facilitating release of seized devices to enable blade removal.

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: The blades (10) of a turbine or a compressor are here fixed to the disk (1) by three roots (7, 8 and 9) inserted in the same number of circular grooves (4, 5 and 6). This assembly makes it possible to provide a good distribution of stresses during functioning.

Abstract: A fan for a ducted fan gas turbine engine comprises a hub carrying an array of generally radially extending fan blades. The hub is hollow and tapered in an axial direction. The radially outer hub surface is provided with a plurality of generally axially extending slots. The slots receive corresponding stepped teeth provided on the radially inner ends of the fan blades. A nose cone engages the upstream end of the roots of the fan blades to ensure that the teeth are retained in the slots.

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: To attach blades (5) on a rotor wheel for turbines or compressors, the wheel (1) has threads (2) running to the inside in a spiral shape on both sides of the outer edge. The blades (5) have segments on their feet (7) of counter-threads shaped accordingly. The threads are designed to have one turn, and their beginnings are staggered 180.degree. to one another on both sides of the wheel to offset inbalances. The threads on the wheel and on the blade feet there are self-locking and prestressed.

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.