GUIDE VANE ASSEMBLY OF A TURBOMACHINE AND METHOD FOR MOUNTING A GUIDE VANE ASSEMBLY

Abstract

The invention relates to a guide vane assembly as well as to a method for mounting a guide vane assembly of a turbomachine, including a number of adjustable guide vanes, the guide vane platform of which has a guide vane journal that is mounted in a receiving opening of a housing of the turbomachine, wherein a guide vane head of the guide vane has a bearing pin, which is mounted on an inner ring arranged on a rotor of the turbomachine. In the method, a guide vane journal, which is arranged on a guide vane platform of a guide vane, is brought into a receiving opening of a housing, which is arranged radially with respect to a rotor axis of the turbomachine, and an inner ring is provided on a rotor of the turbomachine.

Claims

1. A guide vane assembly of a turbomachine, comprising: a plurality of adjustable guide vanes, the guide vane platform of which has a guide vane journal mounted in a receiving opening of a housing of the turbomachine, wherein a guide vane head of the guide vane has a bearing pin, which is mounted on an inner ring arranged on a rotor of the turbomachine, and wherein a mounting space is arranged between the housing and the guide vane platform, in which a support device is arranged, which supports the guide vane against the housing.

2. The guide vane assembly according to claim 1, wherein the inner ring is one-piece or segmented in design, and is configured as a half-ring.

3. The guide vane assembly according to claim 1, wherein the support device is configured and arranged to center an adjustment axis of the guide vane in the receiving opening.

4. The guide vane assembly according to claim 1, wherein the support device has at least one first support element and at least one second support element.

5. The guide vane assembly according to claim 4, wherein the at least one second support element is fastened by a fastening element arranged on the housing.

6. The guide vane assembly according to claim 4, wherein the at least one first support element is locked in position by the at least one second support element.

7. The guide vane assembly according to claim 4, wherein the at least one first support element is a hollow cylinder segment.

8. The guide vane assembly according to claim 4, wherein the at least one second support element is configured and arranged to form, together with at least two first support elements, which are each assigned to a guide vane, a support device.

9. The guide vane assembly according to claim 4, wherein the at least one second support element is configured and arranged as a ring segment, which has at least two adapter sections, and each adapter section is configured and arranged to interact with a first support element to form a support device.

10. The guide vane assembly according to claim 1, wherein the support device has at least one third support element.

11. The guide vane assembly according to claim 10, wherein the at least one third support element is configured and arranged between two guide vane platforms to support them.

12. The guide vane assembly according to claim 4, wherein the at least one first support element and the at least one second support element are each locked in position by a fastening element.

13. The guide vane assembly according to claim 1, wherein the support device is configured and arranged as a circular arc segment and has at least two receiving recesses, which are each configured and arranged to accommodate a guide vane journal, at least in part.

14. The guide vane assembly according to claim 13, wherein the support device is configured and arranged as a half-ring.

15. The guide vane assembly according to claim 13, wherein the receiving recess is substantially U-shaped in configuration.

16. The guide vane assembly according to claim 1, wherein the support device has at least one spacer element, which is arranged all around the guide vane journal.

17. The guide vane assembly according to claim 16, wherein the at least one spacer element is configured and arranged to accommodate a sliding bush bearing, at least in part.

18. The guide vane assembly according to claim 16, wherein the at least one spacer element is substantially rectangular in cross-section.

19. A method for mounting a guide vane assembly of a turbomachine, comprising the steps of: bringing a guide vane journal, which is arranged on a guide vane platform of a guide vane, into a receiving opening of a housing, which is arranged radially with respect to a rotor axis of the turbomachine; providing an inner ring on a rotor of the turbomachine; bringing the guide vane journal out of the receiving opening until a bearing pin arranged on a guide vane head of the guide vane engages in a bearing seat arranged on the inner ring, wherein the guide vane platform, together with the housing, creates a mounting space; arranging a support device in the mounting space, so that the guide vane is supported against the housing; and locking in position the support device.

20. The method according to claim 19, wherein, during the arrangement of the support device, a first support element and a second support element are arranged in the mounting space.

21. The method according to claim 19, wherein, prior to bringing the guide vane journal into the receiving opening, a first support element and a second support element are arranged in the mounting space, and, after bringing the guide vane out of the receiving opening, a third support element is arranged in the mounting space.

22. The method according to claim 19, further comprising the step of: arranging a spacer element around the guide vane platform.

23. The method according to claim 19, wherein bringing the guide vane journal into and out of receiving opening occurs along an adjustment axis of the guide vane that is arranged radially with respect to a rotor axis of the turbomachine.

24. The method according to claim 19, further comprising the step of: connecting the guide vane journal to an adjusting device.

25. A method for mounting a flow arrangement of a turbomachine, comprising the steps of: providing a housing; arranging a first rotating blade assembly in the housing; mounting a first guide vane assembly in accordance with a method according to claim 19 in the housing; and arranging a second rotating blade assembly in the housing.

26. A method for mounting a flow arrangement of a turbomachine in accordance with claim 25, wherein the first guide vane assembly comprises: a plurality of adjustable guide vanes, the guide vane platform of which has a guide vane journal mounted in a receiving opening of a housing of the turbomachine, wherein a guide vane head of the guide vane has a bearing pin, which is mounted on an inner ring arranged on a rotor of the turbomachine, and wherein a mounting space is arranged between the housing and the guide vane platform, in which a support device is arranged, which supports the guide vane against the housing.

27. A turbomachine, comprising: at least one guide vane assembly including: a plurality of adjustable guide vanes, the guide vane platform of which has a guide vane journal mounted in a receiving opening of a housing of the turbomachine, wherein a guide vane head of the guide vane has a bearing pin, which is mounted on an inner ring arranged on a rotor of the turbomachine, and wherein a mounting space is arranged between the housing and the guide vane platform, in which a support device is arranged, which supports the guide vane against the housing; and/or at least one guide vane assembly that is mounted in accordance with the steps of: bringing a guide vane journal, which is arranged on a guide vane platform of a guide vane, into a receiving opening of a housing, which is arranged radially with respect to a rotor axis of the turbomachine; providing an inner ring on a rotor of the turbomachine; bringing the guide vane journal out of the receiving opening until a bearing pin arranged on a guide vane head of the guide vane engages in a bearing seat arranged on the inner ring, wherein the guide vane platform, together with the housing, creates a mounting space; arranging a support device in the mounting space, so that the guide vane is supported against the housing; and locking in position the support device; and/or a flow arrangement that is mounted in accordance with the steps of: providing a housing; arranging a first rotating blade assembly in the housing; mounting a first guide vane assembly in the housing in accordance with the steps of mounting at least one guide vane assembly; and arranging a second rotating blade assembly in the housing.

Description

BRIEF DESCRIPTION OF THE DRAWING FIGURES

[0072] Further features, advantages and possible applications of the invention ensue from the following description in association with the figures. Shown are:

[0073] FIG. 1 is a schematic illustration of a first exemplary embodiment of a guide vane assembly of a turbomachine in accordance with the invention;

[0074] FIG. 2 is a schematic illustration of the support device of the first exemplary embodiment of the guide vane assembly from FIG. 1;

[0075] FIG. 3 is a schematic illustration of a second exemplary embodiment of a guide vane assembly of a turbomachine in accordance with the invention;

[0076] FIG. 4 is a schematic illustration of the support device of the second exemplary embodiment of the guide vane assembly from FIG. 3 in a step of an exemplary mounting method;

[0077] FIG. 5 is a schematic illustration of a third exemplary embodiment of a guide vane assembly of a turbomachine in accordance with the invention;

[0078] FIG. 6 is a schematic illustration of the support device of the third exemplary embodiment of the guide vane assembly from FIG. 5;

[0079] FIG. 7 is a schematic illustration of the exemplary support device of the third exemplary embodiment of the guide vane assembly from FIG. 5;

[0080] FIG. 8 is a schematic illustration of a flow chart of a first exemplary embodiment of a method according to the invention for mounting a guide vane assembly of a turbomachine;

[0081] FIG. 9 is a schematic illustration of a flow chart of a second exemplary embodiment of a method according to the invention for mounting a guide vane assembly of a turbomachine; and

[0082] FIG. 10a to FIG. 10f are schematic illustrations of an exemplary embodiment of a method according to the invention for mounting a flow arrangement of a turbomachine.

DESCRIPTION OF THE INVENTION

[0083] FIG. 1 shows a guide vane assembly 10 for a turbomachine having a plurality of adjustable guide vanes 11, the guide vane platform 12 of which has a guide vane journal 13, which is mounted in a receiving opening 14, which is arranged radially with respect to a rotor axis RA of the turbomachine, of a housing 15 of the turbomachine. An adjusting device 40 is connected by an adjusting lever 41 to the guide vane journal 13 in order to pivot the guide vane 11 around its adjustment axis A.

[0084] A guide vane head 16 of the guide vane 11 has a bearing pin 17, which is borne in a bearing seat 18 of an inner ring 19. In the exemplary embodiment illustrated, this inner ring 19 is designed to be undivided and extends in a plane perpendicular to the plane of the illustration around the rotor 119. On its radially inner surface facing the rotor 119 of the turbomachine, the inner ring 19 has a radially outer part 50 of a sealing device 52, which, together with a second radially inner part 51 arranged on the radial peripheral surface on the rotor 119, forms a sealing device 52.

[0085] Arranged between the guide vane platform 12 and the housing 15 is a mounting space 20, in which a first support element 21 and a second support element 22 are arranged and form a support device 30, by which the guide vane 11 is supported against the housing 15. The support elements 21, 22 are hereby set up to center the guide vane 11 around its adjustment axis A in a bush bearing 23 of the receiving opening 14. Arranged between the guide vane platform 12 and the support device 30 is a sliding bush bearing 32 in order to make possible an adjustment of the guide vane 11.

[0086] The mounting space 20 of the exemplary embodiment is delimited in the axial direction of the guide vane journal 13 by the housing 15 and radially with respect to the guide vane journal 13 by an inward-extending shoulder or projection 151 of the housing 15 that extends radially along a radial inner side of the housing 15. The first support element 21 is designed as as hollow cylinder segment, which is arranged radially around the guide vane journal 13. In the exemplary embodiment, the second support element 22 is designed as a half-ring, which extends in a plane perpendicular to the plane of the illustration around the rotor axis RA. A recess 26 (compare FIG. 2) is hereby designed on the front side of the support element 22 and is set up to surround the guide vane journal 13 at least in part. Adjacent to the recess 26, the second support element 22 has a shape that is designed to rest against the first support element 21 so as, together with it, thereby to surround the guide vane journal 13 at least in part or to form a support device 30.

[0087] Arranged on the housing 15 or pushed into it is a fastening element 24, which, in the exemplary embodiment, is designed as a liner element. By way of this fastening element 24, the second support element 22 is held in the mounting space 20 in such a way that it locks in position the first support element 21 in the mounting space 20. As further shown in FIG. 1, the second support element 22 has a mounting edge 221, which is provided to interact with the fastening element 24 in order to fix in place the support device 30 in the mounting space.

[0088] FIG. 2 shows a cutout of an exemplary support device 30 of the guide vane assembly 10 of a turbomachine from FIG. 1. The first support element 21 of the exemplary embodiment is a hollow cylinder half, for which the inner diameter of the hollow cylinder is designed to engage around the (not depicted) guide vane journal 13 of a guide vane 11 at least in part and, in the exemplary embodiment, to an extent of about one-half. The second support element 22 is designed as a half-ring, which is set up to be arranged circumferentially on the housing 15 or in the mounting space 20. Designed on the front side of the second support element 22 in an adapter section 25 is a recess 26, which is set up so as to engage, together with the first support element 21, around the guide vane journal 13 in order to support it.

[0089] On both sides of the recess 26, the second support element 22 is set up, in particular in the adapter section 25, to interact with the first support element 21 in order to lock it in position or support it. The second support element 22 is hereby set up with one adjacent first support element 21 or a plurality of first support elements 21, in particular in the peripheral direction, which each are assigned to a guide vane 11, in order to form a support device 30. Owing to this configuration of support elements 21, 22, a simplified mounting of the guide vane assembly 10 is made possible, because the support elements 21, 22 can be brought into the mounting space 20 in a simple manner and positioned there.

[0090] FIG. 3 shows a guide vane assembly 10 of a turbomachine having a plurality of adjustable guide vanes 11, the guide vane platform 12 of which has a guide vane journal 13, which is borne in a receiving opening 14, which is arranged radially with respect to a rotor axis of the turbomachine, of a housing 15 of the turbomachine. A guide vane head 16 of the guide vane 11 has a bearing pin 17, which is borne in a bearing seat 18 of an inner ring 19. In the exemplary embodiment, this inner ring 19 is formed from two half-rings, which are arranged coaxially with respect to the axis of rotation of the turbomachine and, in FIG. 3, extend in a plane perpendicular to the plane of the illustration. The inner ring 19 has, at its radial inner surface facing the rotor 119 of the turbomachine, a radially inner part 50 of a sealing device, which, together with a radially outer second part 51 arranged on the rotor 119, forms a sealing device 52.

[0091] Arranged between the guide vane platform 12 and the housing 15 is a mounting space 20, in which a first support element 21, a second support element 22, and a third support element 200 are arranged. The mounting space 20 is delimited axially and radially with respect to the guide vane journal 13 by the housing 15. In a situation in which they are held ready, as illustrated in FIG. 4, the support elements 21, 22 are each arranged in second regions 20a, 20b of the mounting space 20 and are held ready in order to introduce the guide vane platform 12 between them in the mounting space 20. In this embodiment, the regions 20a, 20b are part of the mounting space 20.

[0092] The support elements 21, 22 are set up to engage around the guide vane journal 13 and to center the guide vane 11 around its adjustment axis A in a bush bearing 23 of the receiving opening 14. In the present exemplary embodiment, the support elements 21, 22 are each fixed in place in the housing 15 by a bolt 224a, 224b, whereby the bolts 224a, 224b are secured in the exemplary embodiment by a securing element 225a, 225b in each case.

[0093] Together with the third support element 200 (compare FIG. 4), the first support element 21 and the second support element 22 form a support device 30, by which the guide vane 11 is supported against the housing 15. Arranged between the guide vane platform 12 and the support device 30 is a sliding bush bearing 32 in order to make possible an adjustment of the guide vane 11.

[0094] FIG. 4 shows a cutout schematic illustration of an exemplary support device 30 of the exemplary embodiment of the guide vane assembly 10 from FIG. 3 during a mounting step of a method described herein for mounting a guide vane assembly 10. A first support element 21 is kept in a region 20a of the mounting space 20 and a second support element 22 is kept in a region 20b of the mounting space 20 so as, in a further step of a method described below in detail, to be pushed in the direction of the guide vane journal 13 in order to support the guide vane 11 against the housing 15. For this purpose, for example, the bolts 224a, 224b can be provided, by which the support elements 21, 22 can be pushed, in particular, through the fastening opening 226 in the housing 15 and locked in position.

[0095] Illustrated in FIG. 4 is a cutout of a guide vane assembly 10 in a step of a method described below in detail. A non-depicted guide vane head 16 is already arranged on a likewise non-depicted inner ring 19. Illustrated are two guide vane platforms 12, which are arranged in an opening 20c of the mounting space 20 that is formed by the housing 15.

[0096] A third support element 200 is illustrated below the housing 15 and is set up to be arranged in the mounting space 20 or in the opening 20c formed by the housing 15 between two adjacent guide vane platforms 12 (the airfoil of the guide vane 11 is not depicted). The mounting space 20 can be closed off by a third support element 200 and, at the same time, the guide vane platforms 12 can be supported against each other and against the housing 15.

[0097] In the illustrated exemplary embodiment, the third support element 200 has two oppositely lying flanks 203a, 203b, which are set up to rest against the housing 15, in particular in the opening 20c. Between the flanks 203a, 203b, the third support element 200 has oppositely lying receiving regions 201a, 201b, which are each set up to mount a guide vane platform 12 of two adjacent guide vanes 11 in such a way that they can pivot around the adjustment axis A thereof.

[0098] On a top side, which, in a mounting state, faces at least one first support element 21 and at least one second support element 22, the third support element 200 has two fixing devices 202a, 202b, which are set up to interact with at least one first support element 21 and at least one second support element 22 in order to lock in position the third support element 200 in the mounting space 20. In the illustrated exemplary embodiment, the fixing devices 202a, 202b are designed in such a way that they can each be arranged between two first support elements 21 and two second support elements 22. The support elements 21 and 22 hereby have lateral grooves, which are set up to create a form-fitting connection to the respective T-shaped fixing device 202a, 202b. For this purpose, the third support element 200 is arranged in the mounting space 20 in such a way that, when the support elements 21, 22 move toward each other in the direction of the guide vane journal 13, the grooves of the support elements 21, 22 engage in the fixing device 202a, 202b. In this way, a support device 30 that supports the guide vane(s) 11 against the housing 15 is formed.

[0099] A guide vane assembly 10 in accordance with the present disclosure can have a plurality of guide vanes 11, such as illustrated, for example, in FIG. 1 or FIG. 3, which are arranged in radial alignment on the housing 15, whereby each guide vane 11 is supported by a support device 30.

[0100] FIG. 5 shows a third exemplary embodiment of a guide vane assembly 10 for a turbomachine in a sectional illustration. The guide vane assembly 10 corresponds in terms of its structure essentially to the exemplary embodiments of FIG. 1 and FIG. 3 illustrated above, with the differences being presented below.

[0101] Arranged between the guide vane platform 12 and the housing 15 is a mounting space 20, which is delimited axially with respect to the guide vane journal 13 by the housing 15 and radially with respect to the guide vane journal 13 by a projection 151 of the housing 15. Illustrated in this circumferentially formed mounting space 20 is a support device 31, designed as a circular arc segment, by which the guide vanes 11 are supported against the housing 15. This support device has at least two receiving recesses 31, which are each set up to engage around a guide vane journal 13 at least in part in order to support the guide vane 11 against the housing 15. The support device 30, designed here as a half-ring, hereby extends in the peripheral direction in a plane perpendicular to the plane of the illustration. The receiving recess(es) 31, which are U-shaped in design, is/are formed on an axis-side flank of the support device 30 and are set up to engage around the guide vane journal(s) 13 at least in part. In the illustration, only one of the receiving recesses 31 of the support device 30 is depicted; the embodiments relating to the receiving recess 31 apply correspondingly to the at least one further receiving recess 31 of the support device 30.

[0102] The support device 30 or the receiving recess 31 as well as the guide vane journal 13 thereof and a spacer element 12 arranged around the guide vane journal 13 and the guide vane platform 12 are set up to accommodate the guide vane 11 and to center it around its adjustment axis A in a bush bearing 23 of the receiving opening 14. Arranged between the guide vane platform 12 and the spacer element 33 is a sliding bush bearing 32. In this case, the spacer element 33 is set up to accommodate the guide vane platform 12 and the sliding bush bearing 32 so as to fix them in place against each other and to make possible an adjustment of the guide vane 11. In the illustrated exemplary embodiment, the spacer element 33 has a rectangular cross-section and, on an edge, has an anti-pivot element 34 in the form of a chamfer, so that the mounting can be simplified and any accidental incorrect mounting can be prevented.

[0103] Arranged on the housing 15 or else inserted into it is a fastening element 24, in this case, a liner element, by which the support device 30 can be locked in position or fixed in place in the axial direction.

[0104] FIG. 6 shows a cutout of the guide vane assembly 10 of a turbomachine from FIG. 5 without the housing 15 in a partially exploded illustration. The support device 30, which is designed as a circular arc segment, has a plurality of receiving recesses 31, which can be arranged in an axial direction around the guide vane journal 13 and in the mounting space 20 or can be introduced between the guide vane journals 13 in order to stabilize the guide vane 11.

[0105] Arranged around the guide vane journal 13 of the guide vane 11 are spacer elements 33, which have a recess 36 and a square cross-section and which accommodate the guide vane journal 13 and, in particular, are centrally arranged. The spacer elements 33 are hereby each set up to accommodate a sliding bush bearing 32 and to position it with respect to the guide vane platform 12 and, at the same time, to mount the guide vane platform 12 in such a way that it can pivot in order to make possible an adjustment of the guide vane 11 around the adjustment axis A. Owing to the square cross-section, the spacer elements 33 can be arranged in the mounting space 20 and delimit it, whereby the spacer elements 33 are fixed in place, for example, by a fixing section 35 arranged on the support device 30, in particular in the axial direction of the turbomachine. Accordingly, the spacer elements 33 can, on the one hand, assist a support of the guide vane 11 against the housing 15 and, on the other hand, decrease any relative movement of the guide vane 11.

[0106] FIG. 7 shows an illustration of an exemplary support device 30 of the guide vane assembly 10 from FIG. 5 or FIG. 6. The support device 30 is designed as a semicircular segment or half-ring and has a plurality of U-shaped receiving recesses 31, which each are assigned to a guide vane journal 13 and are set up to accommodate it and accordingly to support it against the housing 15.

[0107] Owing to the embodiment as a half-ring, it is possible for a circumferentially formed mounting space 20 to be filled by two such half-ring-shaped support devices 30 in order to support the guide vanes 11. Owing to the fact that, in such an exemplary embodiment, only two support devices 30 are provided, it is possible to reduce the number of components that are to be mounted and, accordingly, to decrease a mounting time for the guide vane 11 or the inner ring 19.

[0108] A width B of the receiving recess 31 can essentially correspond to a diameter of the guide vane journal 13 and/or a radius R of an inner-lying hollow (half) cylinder formed in the receiving recess 31 can essentially correspond to a radius of the guide vane journal 13 in order to accommodate it, keep it ready, and support it. A depth T of the receiving recess 31 is, in particular, greater than a diameter of the guide vane journal 13, so that the support device 30 can protrude radially over the guide vane journal 13 in order to thereby improve a stabilization effect. The receiving recess 31 is formed openly at an axis-side flank of the support device 30 in order to be able to push it onto the guide vane journal 13 and thereby to support it.

[0109] FIG. 8 shows a flow chart of a first exemplary method 100 for mounting a guide vane assembly 10 of a turbomachine.

[0110] In a first step 101, a guide pin 13 arranged on a guide vane platform 12 of a guide vane 11 is introduced in a receiving opening 14 of a housing 15 radially with respect to a rotor axis of the turbomachine, in particular until the guide vane platform 12 abuts against the housing 15. In a further step 102, an inner ring 19 is provided on a rotor 119 of the turbomachine. In a further step 103, the guide vane journal 13 is brought out of the receiving opening 14 in the radial direction with respect to a rotor axis of the turbomachine until a bearing pin 17 arranged on a guide vane head 16 of the guide vane 11 engages in a bearing seat 18 arranged on the inner ring 19. The guide vane platform 12 thereby creates, together with the housing 15, a mounting space 20.

[0111] In a further step 104, a first support element 21 and a second support element 22 are arranged in the mounting space 20 in such a way that they form a support device 30. In a further step 105, the second support element 22 is fixed in place, in particular by a fastening element 24, as a result of which, in particular, the first support element 21 is also locked in position.

[0112] In a further step 106, the guide vane journal 13 is connected to an adjusting device 40, in particular by an adjusting lever 41, in order to be able to adjust the guide vane 11 around its adjustment axis.

[0113] FIG. 9 shows a flow chart of a second exemplary method 100 for mounting a guide vane assembly 10 of a turbomachine.

[0114] In a first step 101, a guide vane journal 13 arranged on a guide vane platform 12 of a guide vane 11 is introduced in a receiving opening 14 of a housing 15 arranged radially with respect to a rotor axis of the turbomachine, in particular until the guide vane platform 12 is in abutment with the housing 15. In an optional step 107, it is possible beforehand to arrange or provide a support element 32 around the guide vane journal 13 or the guide vane platform 12.

[0115] In a step 102, an inner ring 19 is provided on a rotor 119 of the turbomachine and, in a further step 103, the guide vane journal 13 is brought out of the receiving opening 14 radially with respect to a rotor axis of the turbomachine until a bearing pin 17 arranged on a guide vane head 16 of the guide vane 11 engages in a bearing seat 18 arranged on the inner ring 19, whereby the guide vane platform 12, together with the housing 15, creates a mounting space 20.

[0116] In a step 104, a support device 30 is arranged in the mounting space 20 in order to support the guide vane 11 against the housing 15. In a further step, the guide vane journal 13 is connected to an adjusting device 40, in particular by an adjusting lever 41, in order to be able to adjust the guide vane 11 around its adjustment axis A. In a further step 105, the support device 30 is fixed in place or locked in position, in particular by a fastening element 24.

[0117] FIG. 10a to FIG. 10f show a schematic illustration of steps of an exemplary embodiment of a method 300 for mounting a flow arrangement 310 of a turbomachine. FIG. 10a shows a step of providing a housing 15. FIG. 10b shows the arrangement of a first rotating blade assembly 311, which has a first rotor section 312, in the housing 15. FIG. 10c shows the mounting of a first guide vane assembly 10 in the housing 15 in accordance with the method 100 described herein. A divided or undivided inner ring 19 is hereby introduced into the structural space that is available in the turbomachine, after which the guide vane 11 of the guide vane assembly 10 can be arranged on it. Because, in the proposed method in comparison to known methods, a mounting of a plurality of inner-ring components can be dispensed with, the mounting of the flow arrangement 310 is simplified

[0118] FIG. 10d shows the arrangement of a second rotating blade assembly 313, which has a second rotor section 314, in the housing 15 and FIG. 10e shows the mounting of a second guide vane assembly 10 in the housing 15 in accordance with the proposed method 100. FIG. 10f shows the arrangement of a third rotating blade assembly 315, which has a second rotor section 316, in the housing 15.