Turbomachine rotor assembly and method

Abstract

A turbomachine assembly is shown, including a rotor and a ring of blades mounted on the rotor. Each blade includes an airfoil portion and a root portion inserted in a circumferential blade-retaining groove of the rotor. The blade-retaining groove includes an enlarged groove portion. The blades in the enlarged groove portion are rotatable around a respective, generally radial axis, to take a position of minimum tangential dimension. At least one removable insert is arranged along the enlarged groove portion, between the root portions of the blades located in the enlarged groove portion and a side wall of the blade-retaining groove, to force and lock the blades in a final assembled arrangement.

Claims

1. A turbomachine assembly comprising: a rotor and a ring of blades mounted on said rotor, each blade comprising an airfoil portion and a root portion inserted in a circumferential blade-retaining groove of the rotor; wherein said blade-retaining groove comprises a second groove portion, the blades in the second groove portion being rotatable around a respective, generally radial axis, to take a position of minimum tangential dimension; and wherein at least one removable insert is arranged along said second groove portion, between the root portions of the blades located in the second groove portion and a side wall of the blade-retaining groove, to force and lock the blades in a final assembled arrangement; and wherein said blades are divided into a first set of blades and a second set of blades, said second set of blades being arranged along the second groove portion and the first set of blades being arranged along the remaining of said blade-retaining groove; and wherein one ledge of the blades of the second set of blades has a smaller axial extension than ledges of the first set of blades, and a slanted surface co-acting with said at least one insert.

2. The turbomachine assembly according to claim 1, wherein said at least one removable insert is housed in a tangentially extending seat formed between the root portions of the blades and the side wall of the second groove portion, said seat and said at least one insert having a cross section configured to radially retain the insert in the seat.

3. The turbomachine of claim 1, comprising a plurality of said inserts, arranged tangentially along the second groove portion.

4. The turbomachine assembly according to claim 1, wherein said blade-retaining groove has an inlet slot and a bottom portion forming a blade-retaining undercut; and wherein along the second groove portion said inlet slot has an axial dimension larger than in the remaining part of said blade-retaining groove.

5. The turbomachine assembly according to claim 4, wherein along said second groove portion the inlet slot forms an undercut, which radially retains said least one insert.

6. The turbomachine assembly according to claim 1, wherein each blade comprises a blade platform between the respective airfoil portion and the root portion; and wherein said at least one removable insert is forcedly engaged between a side wall of the groove and the platform of the respective blades along the second groove portion.

7. The turbomachine assembly according to claim 1, wherein the second groove portion and the root portions of the blades arranged there along form opposite undercuts, radially retaining said at least one insert therebetween.

8. The turbomachine assembly according to claim 1, wherein said at least one inset is provided with sloped, radially outwardly converging lateral surfaces, co-acting with the blade root portions and the second groove portion for radially retaining the insert in said second groove portion.

9. The turbomachine assembly according to claim 1, wherein said second groove portion has an inlet end, through which said at least one insert is introduced into or removed from the second groove portion.

10. The turbomachine assembly according to claim 1, wherein said at least one insert is tangentially constrained to the rotor, preventing tangential displacement thereof with respect to the rotor.

11. The turbomachine assembly according to claim 1, comprising a number of removable inserts corresponding to the number of blades in the second groove portion.

12. A turbomachine assembly comprising: a rotor and a ring of blades mounted on said rotor, each blade comprising an airfoil portion and a root portion inserted in a circumferential blade-retaining groove of the rotor; wherein said blade-retaining groove comprises a second groove portion, the blades in the second groove portion being rotatable around a respective, generally radial axis, to take a position of minimum tangential dimension; and wherein at least one removable insert is arranged along said second groove portion, between the root portions of the blades located in the second groove portion and a side wall of the blade-retaining groove, to force and lock the blades in a final assembled arrangement; wherein said second groove portion has an inlet end, through which said at least one insert is introduced into or removed from the second groove portion; and wherein the inlet end has a flared guiding surface for introducing said at least one insert in the second groove portion and for removing the insert from the second groove portion.

13. The turbomachine assembly according to claim 12, wherein each root portion of said blades comprises opposite axially extending ledges co-acting with opposed tangentially extending side walls of the groove, to retain each blade in a fixed angular position with respect to a radially extending axis of the blade; and wherein along said second groove portion said at least one insert is arranged between one of said axially extending ledges of the blades arranged along the second groove portion and an opposing tangentially extending side wall of the groove, said insert forcedly engaging between the axially extending projection and the side wall of the groove, thus retaining the blades in the final angular position.

14. The turbomachine assembly of claim 13, wherein: the axially extending ledges of said blades contacting said at least one insert form an undercut and the side wall of the second groove portion facing said axially extending ledges form an opposite undercut; said undercuts radially retaining said at least one insert in the second groove portion.

15. The turbomachine assembly according to claim 12, wherein said inlet end has a bottom surface and a side surface forming a flared inlet aperture, extending tangentially and radially from an outer surface of the rotor in the second groove portion.

16. The turbomachine of claim 12, comprising a plurality of said inserts, arranged tangentially along the second groove portion.

17. The turbomachine assembly according to claim 12, wherein each blade comprises a blade platform between the respective airfoil portion and the root portion; and wherein said at least one removable insert is forcedly engaged between a side wall of the groove and the platform of the respective blades along the second groove portion.

18. The turbomachine assembly according to claim 12, wherein the second groove portion and the root portions of the blades arranged there along form opposite undercuts, radially retaining said at least one insert therebetween.

19. The turbomachine assembly according to claim 12, wherein said at least one inset is provided with sloped, radially outwardly converging lateral surfaces, co-acting with the blade root portions and the second groove portion for radially retaining the insert in said second groove portion.

20. The turbomachine assembly according to claim 12, wherein said at least one insert is tangentially constrained to the rotor, preventing tangential displacement thereof with respect to the rotor.

21. The turbomachine assembly according to claim 12, comprising a number of removable inserts corresponding to the number of blades in the second groove portion.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) A more complete appreciation of the disclosed embodiments of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings, wherein:

(2) FIG. 1 illustrates a side view of one of the blades of a first set of blades according to the present disclosure;

(3) FIGS. 2 and 3 illustrate views of the blade of FIG. 1 according to lines II-II and III-III respectively;

(4) FIG. 4 illustrates a view, similar to FIG. 1, of one of the blades of a second set of blades according to the present disclosure;

(5) FIGS. 5 and 6 illustrate views of the blade of FIG. 4 according to lines IV-IV and V-V respectively;

(6) FIG. 7 illustrates a portion of a rotor drum;

(7) FIG. 8 illustrates a detail of a peripheral portion of the rotor drum of FIG. 7;

(8) FIG. 9 illustrates a different view of a detail of a peripheral portion of the rotor drum of FIG. 8;

(9) FIGS. 10 and 11 illustrate two sections according to lines X-X and XI-XI of FIG. 7 of the blade-retaining groove of the rotor drum;

(10) FIGS. 12 and 13 illustrate two steps of the mounting process of a blade of the first set of blades;

(11) FIG. 14 illustrates a perspective view of a rotor drum portion with a partially assembled blade ring;

(12) FIGS. 15 and 16 illustrate perspective views of the rotor drum with all but the last blade mounted around the rotor drum;

(13) FIG. 17 illustrates the final step of insertion of the last blade;

(14) FIG. 18 illustrates a perspective view of the rotor drum with all the blades and part of the inserts mounted thereon;

(15) FIG. 18A illustrates an enlargement of a detail of FIG. 18;

(16) FIGS. 19 and 20 illustrate perspective views of the rotor with the blade ring in the final assembled position;

(17) FIG. 20A illustrates an enlargement of a detail of FIG. 20;

(18) FIG. 21 illustrates a section according to a radial plane of one of the blades of the second set in the assembled and locked condition;

(19) FIG. 22 illustrates a perspective view of one of the inserts used to lock the blades in their final angular position; and

(20) FIG. 23 illustrates a system for mounting blades on a rotor according to the current art.

DETAILED DESCRIPTION

(21) The following detailed description of the exemplary embodiments refers to the accompanying drawings. The same reference numbers in different drawings identify the same or similar elements. Additionally, the drawings are not necessarily drawn to scale. Also, the following detailed description does not limit the invention. Instead, the scope of the invention is defined by the appended claims.

(22) Reference throughout the specification to one embodiment or an embodiment or some embodiments means that the particular feature, structure or characteristic described in connection with an embodiment is included in at least one embodiment of the subject matter disclosed. Thus, the appearance of the phrase in one embodiment or in an embodiment or in some embodiments in various places throughout the specification is not necessarily referring to the same embodiment(s). Further, the particular features, structures or characteristics may be combined in any suitable manner in one or more embodiments.

(23) In the following description and enclosed drawings reference will be made to a single disk of a turbine rotor, around which a ring of blades is mounted. It shall be understood that a plurality of such disks or a drum with a plurality of rings of blades can be provided, depending upon the number of stages of the turbomachine. In general, a turbomachine will as a matter of fact include a plurality of stages, each stage comprising a ring of rotating blades mounted on the rotor and a ring of stationary blades mounted on a stationary portion of the machine. The blades of some or all the stages can be mounted on the rotor as described here below.

(24) Moreover, reference will be specifically made to a turbine and in particular to a steam turbine, by way of example. It shall however be understood that the same mounting technique can be used for assembling the blades in different kinds of turbomachines, e.g. in axial compressors or gas turbines.

(25) In the drawings a rotor 1 is comprised of a central drum 3 around which a plurality of blades 7A, 7B are arranged in a ring configuration. In the drawings only a slice of the rotor 1 is shown, which corresponds to one of the turbine stages. It shall be understood that in actual fact the rotor has an axial extension depending to the number of stages and that for each stage a ring of blades is mounted on the rotor drum along a corresponding blade-retaining groove.

(26) FIGS. 1-3 and 4-6 illustrate in detail the shape of the blades 7A and 7B respectively. The structure of the blades will be described in greater detail later on.

(27) The rotor 1 has a rotation axis X-X and for each stage of the turbomachine an undercut blade-retaining groove 5 developing circumferentially around the rotor 1. The blade-retaining groove 5 is shaped such as to retain the blades 7A, 7B mounted thereon by means of a dovetail or T-shaped cross section of the blade retaining groove 5 and a correspondingly shaped root portion of the blades 7A, 7B. Generally speaking the cross sectional shape of the blade-retaining groove 5 and the corresponding shape of the blade root portions are such that the blades can be constrained to the rotor by engaging the root portions of the blades in an undercut formed by the blade-retention groove 5.

(28) In some embodiments (see FIGS. 7-11) the blade-retaining groove 5 comprises an inlet slot or platform slot 5A, an intermediate neck portion 5B and a bottom portion 5C. The inlet slot 5A has a dimension D1 in the axial direction, i.e. in the direction parallel to the rotation axis X-X of the rotor 1. The intermediate portion 5B of the blade-retaining groove 5 has a width D2, smaller than D1, and the inner or bottom portion 5C has a width D3. The width D3 can be identical to D1, as shown in FIG. 10, or different, e.g. larger than D1. The cross section of the blade-retaining groove 5 thus forms an undercut 5D for radial retention of the blades 7A, 7B. The inlet slot 5A is bounded by two annular, more particularly planar side walls or surfaces 5E, 5F. In some embodiments, the side walls 5E, 5F are generally parallel to one another and can be orthogonal to the rotor axis X-X. In other embodiments, the side walls 5E, 5F can be non-parallel.

(29) The cross-section of the blade-retaining groove 5 shown in FIG. 10 is constant along the entire circumferential extension of the blade-retaining groove 5 corresponding to an angle ? (see e.g. FIGS. 7, 13). Along the remaining portion of the circumferential extension thereof, the blade-retaining groove 5 has a slightly different cross sectional shape, as shown in FIG. 11. Along the remaining portion, corresponding to an angle ? (see FIGS. 7, 13, for instance), and extending from a first end 5X to a second end 5Y, the blade-retaining groove 5 has an enlarged cross-section. In an embodiment, angle ? can range between e.g. about 20? and 100?, particularly between about 25? and 80?, and more particularly between about 30 and 60?, for example. This portion of the blade-retaining groove 5 will be referred to herein as the enlarged groove portion.

(30) The cross section of the enlarged groove portion substantially corresponds to the cross section of the blade-retaining groove 5 along the portion corresponding to angle ?, except for a different shape of the inlet slot or platform slot 5A. Along the enlarged groove portion the inlet slot 5A is formed between side wall 5E and an opposing, slanted side wall 5F. This latter wall is inclined and radially outwardly converging towards the opposing side wall 5E. In some embodiments the slanted side wall 5F can be substantially conical, the axis of the conical surface thereof being coincident with the rotation axis X-X of the rotor 1. The side wall 5F can also have a shape different than the one shown in the drawings. In general, the side wall 5F is shaped so as to form an undercut for the purposes which will become apparent from the following description.

(31) The width of the inlet slot 5A along the enlarged groove portion is thus variable from a minimum dimension D5 to a maximum dimension D4. D5 is larger than D1. In other embodiments the width of the inlet slot 5A along the enlarged groove portion can vary stepwise, increasing in a radially inwardly direction, so as to form an undercut.

(32) For the reasons which will become apparent from the following description, each ring of blades mounted in one of the blade-retaining grooves 5 of the rotor 1 is comprised of two types of blades, forming a first set of blades 7A and a second set of blades 7B, which slightly differ from one another. FIGS. 1 to 3 illustrate one blade 7A in isolation. Each blade 7A comprises an intermediate airfoil portion 7F, an optional radially outer shroud portion 7S and a radially inner root portion 7R. Between the root portion 7R and the airfoil portion 7F the blade 7A is provided with a platform 11. The root portion 7R has two generally planar surfaces 13 which, when the blade 7A is mounted on the rotor 1, extend radially and generally inclined e.g. up to about 30? or 40? to the rotor axis X-X. The root portion 7R of each blade 7A further comprises two side indentations 15, which define a lower T-shaped section or undercut section of the root portion 7R of the blade. The T-shaped section, labeled 17, can be engaged in the undercut section 5C of the blade-retaining groove 5, each blade 7A being locked in the blade-retaining groove 5 as will be described later on.

(33) The platform 11 extends sideways above the indentations 15 forming two opposing ledges 19. When the blade 7A is in its final assembled position on the rotor 1 the ledges 19 coact with the side walls 5E, 5F defining the inlet slot 5A of the blade-retaining groove 5.

(34) FIGS. 4 to 6 illustrate one blade 7B of the second set of blades, in isolation. The same reference numbers designate the same or corresponding parts as already described in connection with blade 7A. The main difference between the blades 7A of the first set or type and the blades 7B of the second set or type is the shape of one of the two ledges 19. As can best be appreciated by comparing FIGS. 1 and 4, one of the ledges 19 (the right-hand one in the drawings) of blade 7B has a slanted surface 19X. The total width of the blade 7B at the level of the ledges 19 is thus smaller than the width of the blade 7A. In some embodiments, both ledges 19 of the blades 7B can be chamfered at one end, as shown at 19C (FIGS. 5, 6).

(35) Each ring of blades of a turbomachine stage is formed by a larger number of blades 7A and a smaller number of blades 7B. The blades 7A are arranged around the major portion of the blade retaining-groove 5, along angle ?, while the blades 7B of the second set of blades are located in the enlarged groove portion extending from point 5X to point 5Y along angle ? of the rotor.

(36) The procedure for mounting each blade 7A of the first plurality or set of blades in the blade-retaining groove 5 will now be described reference being made to FIGS. 7, 12, 13 and 14. The distance between the two surfaces 13 delimiting the root portion 7R of the blade 7 is slightly smaller than the axial dimension D2 of the intermediate section 5B of the blade-retaining groove 5, so that each blade 7 can be introduced in the blade-retaining groove 5, by orienting the root portion 7R with the two planar surfaces 13 approximately orthogonal to the rotation axis X-X of the rotor. In FIG. 7 a first blade 7A is shown in the starting position. The root 7R of the blade 7A is introduced in the blade-retaining groove 5. Once the blade root 7R has been introduced in the blade-retaining groove 5, the blade 7A is twisted or rotated around a radial axis Y-Y thereof. In the final twisted position the surfaces 15X of the indentations are substantially orthogonal to the rotation axis X-X of the rotor 1. By twisting the blade 7A, the T-shaped section 17 of the root portion 7R of the blade 7A engages the bottom portion 5C of the enlarged blade-retaining groove 5, so that the blade 7A is radially engaged in the enlarged blade-retaining groove 5. In the final twisted position one of the ledges 19 of the platform 11 abuts against the side surface 5E of the inlet slot 5A of the enlarged blade-retaining groove 5. The blade 7A is then displaced tangentially in the non-enlarged blade retaining groove to reach its final position in the blade row and with both ledges 19 engaging surfaces 5E and 5F.

(37) This procedure is repeated for a number of blades 7A sufficient to fill the entire blade-retaining groove 5 except the enlarged groove portion, i.e. until a partial blade ring extending along an angle ? is formed, as shown in FIG. 14. The blades 7A thus mounted are locked in their angular position and do not rotate around their respective radial axes Y-Y as the ledges 19 abut against side surfaces 5E, 5F of the blade-retaining groove 5.

(38) The blade root 7R can be suitably chamfered or rounded in a manner known to those skilled in the art, to reduce the dimension D2 of the blade-retaining groove 5 and to increase the number of blades 7A forming each blade ring, i.e. to increase the angle ?.

(39) Once a number of blades 7A sufficient to fill the blade-retaining groove 5 along the angle ? have been mounted on the rotor 1, the blades 7B of the second set of blades are mounted along the remaining enlarged groove portion in quite the same manner.

(40) As mentioned above, the inlet slot 5A of the blade-retaining groove 5 along the enlarged groove portion is wider that the inlet slot 5A of the remaining major portions of the blade-retaining groove 5, so that the blades 7B of the second set of blades can be over-twisted once introduced with their root portion 7R in the blade-retaining groove 5, as shown in FIGS. 15 and 16. Over-twisted means that once the root portion 7R of a blade 7B has been introduced in the enlarged groove portion, the blade 7B is rotated about its radial axis Y-Y by an angle greater than the angle required to achieve the final position of the blade. Over-twisting is made possible by the enlarged axial dimension D4, D5 of the inlet slot 5A along the enlarged groove portion and by the reduced dimension of one of the ledges 19 of the blades 7B of the second set of blades 7B. The chamfer 19C of the ledges 19 of blades 7B (FIGS. 4-6) increases the entity of the over-twisting movement.

(41) In the over-twisted position (FIGS. 15, 16, 17) each blade 7B takes a tangential dimension, i.e. a dimension in the direction fT, which is smaller than the tangential dimension of the blades 7 in the final angular position (FIGS. 19, 20). This means that the blades 7B take a position of minimum pitch, smaller than the pitch between the blades of the first set of blades 7A mounted along the blade-retaining groove portion corresponding to angle ?. Thus, as shown in FIGS. 15, 16 and 17, once a certain number of blades 7B have been introduced in the enlarged groove portion and over-twisted they leave a free gap G between the first blade 7A (labeled 7A1 in FIGS. 15, 16 17) of the first set of blades 7A and last blade of the second set of blades 7B, labeled 7B1.

(42) In the free gap G which is thus formed a last blade 7BX can be introduced and twisted so as to engage the root portion 7R thereof in the blade-retaining groove 5. See FIG. 17. The tangential dimension of gap G is larger than the width of the T-shaped section of the root portion 7R, so that the last blade 7BX can be introduced in the gap with the surfaces 15A of the indentations 15, parallel to the rotation axis X-X of the rotor 1 and subsequently twisted around its own radial axis Y-Y to take the final position, with the surfaces 15A orthogonal to the rotation axis X-X.

(43) In order to close the tangential gap G and eliminate any clearance between the blades 7A, 7B and lock the blades thus mounted in the enlarged groove portion in their final correct angular position, each blade 7B arranged along the enlarged groove portion, i.e. along the groove portion corresponding to angle ?, may be twisted back from the over-twisted angular position (FIGS. 15-17) to the final angular position (FIGS. 18-20).

(44) To move each over-twisted blade 7B, 7B1, 7BX back to the final angular position, tangential inserts 21 are introduced in a seat 20 formed along the enlarged groove portion between the side wall or side surface 5F and the slanted surface 19X of the ledge 19 facing the side wall 5F. FIG. 21 show a cross-section of the enlarged groove portion with a blade root portion 7R and an insert 21 inserted between the blade root 7R and the surface 5F.

(45) In the embodiment illustrated in the drawings, a number of inserts 21 identical to the number of blades 7B, 7B1, 7BX arranged along the enlarged groove portion are introduced in the seat 20. This, however, is not mandatory. A different number of inserts 21 can be used. In some embodiments, more inserts 21 than blades 7B along angle ? can be used. Vice-versa, a number of inserts 21 smaller than the number of the blades 7B of the second set can be provided in the seat 20. In some embodiments a single insert 21 can be introduced in the tangential seat formed between blades 7B and the side surface 5F of the blade-retaining groove 5.

(46) The cross sectional shape and dimension of each insert 21 and of the seat 20 are such that the inserts 21 engage in the seat 20 pushing the respective blades 7B in the final angular position rotating them around their radial axes Y-Y. Each insert 21 can be provided with opposing slanted side surfaces 21A and 21B as shown in FIG. 22. The surfaces 21A and 21B converge radially outwardly, so that each insert 21 has a generally wedge-shaped cross section. The inclination of the slanted side surfaces 21A and 21B can be identical or similar to the inclination of the side wall 5F and of the surface 19X of the ledges 19 of blades 7B located along the enlarged groove portion of the blade-retaining groove 5. By sequentially introducing inserts 21 in the seat 20 the blades 7B along the enlarged groove portion are rotated or twisted about their respective radial axis Y-Y in the final position and locked in the position by the interference between the inserts 21 and the side walls 5F, 19X of the seat 20. Such interference increases as long as more inserts are introduced and more blades 7B are forced in their final angular position. In FIG. 18 the first three inserts 21 have been introduced in the tangential seat 20. In FIGS. 19, 20 the total number of inserts 21 have been introduced in the seat 20 and all blades 7B are locked in their final angular position about the respective radial axes.

(47) The wedge-shaped cross section of the inserts 21 and the corresponding slanted shape of the surfaces or walls 19X and 5F generate a radial retention effect, preventing the inserts 21 from moving away from the seat 20 under the effect of the centrifugal force during operation of the turbomachine. As noted above, the wall 5F can be shaped differently, provided it forms an undercut to radially retain the inserts 21.

(48) In some embodiments, at one end (5Y in the example) of the enlarged groove portion flared guide surfaces can be provided, to facilitate the tangential insertion of the inserts 21 between the slanted side surface or wall 5F and the slanted surfaces 19X of the ledges 19. FIGS. 8 and 9 schematically show a possible shape of the flared guide surfaces provided at the inlet end 5Y of the enlarged groove portion, where the inserts 21 are introduced. In some embodiments a bottom guide surface 27 and a side flared surface 29 can be provided, defining a sliding and guide surface for the inserts 21.

(49) In some embodiments the last introduced insert 21, located at the inlet end of the enlarged groove portion (position 5Y) can be constrained to the rotor 1. For example the last insert 21 (labeled 21X in FIGS. 19 and 20) can be soldered, welded, screwed, glued or constrained in any other suitable way to the rotor drum 3. Constraining of the last insert 21X to the rotor drum 3 is particularly simple, since during operation of the turbomachine the inserts 21 are subject to strong centrifugal forces acting in the radial direction and counter-acted by the wedge-shaped cross section of the inserts 21 and of the seat 20 where the latter are introduced, while substantially no forces or only negligible forces are applied in the tangential direction. The constraining means provided for constraining the last inserts 21 tangentially to the rotor 1 are therefore provided just for the sake of additional safety.

(50) In the embodiment disclosed so far the inserts 21 are introduced in the seat 20 with a substantially tangential movement, with the aid of the flared guide and slide surfaces 27, 29. In some embodiments, not shown, insertion can be through a radial slot machined in the rotor drum 3 and reaching a depth substantially corresponding to the bottom of the seat 20. Once an insert 21 has been introduced radially in the slot, it can be shifted with a tangential movement into seat 20.

(51) Rotation of the blades 7B arranged along the enlarged groove portion between point 5X and point 5Y, in the final angular position (FIGS. 19, 20), increases the tangential dimension of each such blade. The number of blades and the shape thereof are chosen such that in the final assembled position a complete ring of blades will be formed, where each blade is forced in the tangential direction against the neighboring blades removing any clearance between the blades. The platforms 11 of the sequentially arranged blades 7A, 7B will contact each other forming a continuous annular collar surrounding the blade-retention groove 5. The shroud portions 7S of the blades, if provided, will contact each other along respective side edges. Some degree of interference between the mutually abutting shroud portions 7S can be generated, which can torsionally bias the airfoil portion 7F, if so required.

(52) The inserts 21 thus lock the entire ring of blades 7A, 7B in the final position. The back twisting of the blades 7A, 7B along the enlarged groove portion (angle ?) from the over-twisted position to the final assembled position, caused by the introduction of the inserts 21, removes the clearance between blades.

(53) Disassembling of the blades, for example for maintenance or repairing purposes, is obtained by a reversed sequence of operations. Firstly, the last introduced insert 21X is removed. If a constraining member, such as a screw, is provided, which locks tangentially the insert 21 to the rotor drum 3, the constraining member is removed. Afterwards the inserts 21X, 21 are sequentially removed from the seat 20 by tangentially sliding them out of the seat 20 along the blade-retaining groove 5. The blades 7BX, 7B1, 7B arranged along the enlarged groove portion between point 5X and point 5Y are over-twisted in their position of minimum tangential dimension, thus creating a free gap G, where the blade 7BX can be twisted about the radial axis Y-Y thereof by approximately 90? until the surfaces 13 of the blade root 7R are positioned approximately orthogonal to the rotation axis X-X of the rotor 1. Once this angular position has been achieved, the T-shaped part of the root portion 7R of blade 7BX can be disengaged from the undercut 5D formed in the bottom portion 5C of the blade-retaining groove 5. The blade 7BX can thus be radially removed. The remaining blades 7B, 7A can now be individually rotated about approx. 90? and radially extracted from the blade-retaining groove 5 by disengaging the respective T-shaped section of each blade from the undercut 5D.

(54) Removal of the inserts 21 can be facilitated by providing a notch or the like on each inert 21X, 21. In FIG. 22 a notch 21N is provided at one end of the insert 21. A tool, such as a screwdriver, can engage the notch 21N to push the insert 21 out of the seat 20.

(55) While the disclosed embodiments of the subject matter described herein have been shown in the drawings and fully described above with particularity and detail in connection with several exemplary embodiments, it will be apparent to those of ordinary skill in the art that many modifications, changes, and omissions are possible without materially departing from the novel teachings, the principles and concepts set forth herein, and advantages of the subject matter recited in the appended claims. Hence, the proper scope of the disclosed innovations should be determined only by the broadest interpretation of the appended claims so as to encompass all such modifications, changes, and omissions. In addition, the order or sequence of any process or method steps may be varied or re-sequenced according to alternative embodiments.