EP1917419B1 - Guide vane arrangement of a turbo-machine - Google Patents

Abstract

A guide vane arrangement of a turbomachine includes a casing, at least one guide vane carrier connected to the casing and having a first carrying portion and a second carrying portion spaced apart axially from the first carrying portion, a plurality of guide vanes connected to the guide vane carrier and arranged next to each other in a circumferential direction, and at least one securing element connected to the guide vane carrier and configured to provide an axial fixing of at least one of the guide vanes. Each guide vane has a platform including a first locking portion and a second locking portion spaced apart axially from the first locking portion, wherein each of the first and second locking portions and the respective first and second carrying portion are adapted to provide an axially pluggable and a radially positive fastening between the guide vane carrier and the respective guide vane.

Description

Technical area

The present invention relates to a vane arrangement of a turbomachine, in particular a gas turbine, with the features of the preamble of claim 1. Furthermore, the invention relates to a turbomachine with such a Leitschaufelanordnung_.

State of the art

A typical vane assembly includes at least one vane support attached to a housing of a turbomachine. Such a vane assembly also includes a plurality of vanes mounted on the vane support and circumferentially juxtaposed. Typically, each vane has a platform having at least two latch portions circumferentially spaced from one another. Each latch portion has a tongue which projects circumferentially from the platform and extends in the axial direction. The vane support has at least two support portions which are circumferentially spaced from each other. Each support portion has a groove which is open in the circumferential direction and extends in the axial direction. The tongues of the latch sections and the grooves of the support sections are configured to provide an axially pluggable and radially positive fit attachment between the vane support and the respective vane. A vane arrangement of this type gives the possibility to assemble and disassemble individual vanes without disassembly of the entire vane support.

From the EP 0 943 785 A is a vane arrangement for one. Turbomachine known to one at a. Housing the turbomachine fixed guide vane and a plurality of fixed to the vane carrier and circumferentially juxtaposed vanes has. In this case, each vane on a platform having a first latch portion and axially spaced therefrom has a second latch portion. The vane support is provided with a first support portion and axially spaced therefrom with a second support portion. The latch sections and the support sections are configured to provide an axially pluggable and radially positive fit attachment between the vane support and the vanes. Furthermore, at least one securing element is fastened to the guide blade carrier and configured such that it allows axial fixing of at least one of the guide vanes.

Further Leitschaufel arrangements for turbomachines are from the US 2,982,519 A , from the US 2,910,269 A and from the US 2005/111969 A1 known.

Presentation of the invention.

It is an object of the present invention to provide an improved vane assembly that retains the ability to easily assemble and disassemble individual vanes, and is particularly characterized by improved cooling. This problem is solved by the independent claims. Preferred embodiments are shown in the dependent claims.

The invention is based on the general idea to arrange the Riegefabschnitte and the complementary support sections with axial offset. The assembly and disassembly of the vanes is simplified because the axial movement of the vanes, which must be performed in order to establish the positive locking, is significantly reduced. Problems such as distortion, jamming and jamming along the axial contact are reduced. Since the cooperating support sections and latch sections extend in the circumferential direction, the guide vane arrangement according to the invention allows stiffening of the guide vanes in the circumferential direction.

According to the invention, the platform has a cavity which is bounded radially inwardly by a base and is bounded axially and circumferentially by walls projecting outwardly from the base. The vane carrier has a common collection channel,
which extends in the circumferential direction. The housing has at least one cooling gas supply channel, which is fluidically connected to the common collection channel. The vane carrier has a plurality of connection openings, each fluidically connecting the common collection channel with one of the cavities. Due to this feature, the vane support comprises an important part of a cooling gas supply path. Said common common rail significantly simplifies the cooling gas supply through the casing of the turbomachine, since the cooling gas supply passage of the casing can be disposed in a suitable portion of the casing and because the arrangement of the cooling gas supply passage is independent of the arrangement of the vanes.

In another embodiment of the invention, the vane arrangement allows circumferentially adjacent vanes to be provided with a gap seal arrangement. Said gap seal arrangement is designed to seal a gap extending axially between each two circumferentially adjacent vanes. By means of such a gap sealing arrangement, the leakage of cooling gas through said gap can be significantly reduced. A decrease in the leakage of cooling gas results in an increase in the efficiency of the turbomachine.

Other objects and many of the attendant advantages of the present invention will be more readily appreciated and become better understood by reference to the following detailed description when considered in conjunction with the accompanying drawings.

Brief description of the drawings

Fig. 1

zeigt einen vereinfachten, schematischen Axialschnitt einer. Leitschaufelanordnung entsprechend einer Ausführungsform der Erfindung,

Fig. 2

zeigt eine Detailansicht gemäß Pfeil II in Fig. 1,

Fig. 3

zeigt einen Umfangsschnitt entsprechend Schnittlinien III in Fig. 1,

Fig. 4

zeigt eine Explosionsdarstellung der Leitschaufelanordnung gemäß Fig. 1.

Preferred embodiments of the invention are illustrated in the drawings and will be explained in more detail in the following description. For features that are substantially or functionally the same or similar reference is made to the same reference numeral.

Fig. 1

shows a simplified, schematic axial section of a. Vane arrangement according to an embodiment of the invention,

Fig. 2

shows a detailed view according to arrow II in Fig. 1 .

Fig. 3

shows a circumferential section corresponding to section lines III in Fig. 1 .

Fig. 4

shows an exploded view of the vane assembly according to Fig. 1 ,

Detailed description of the drawings

Corresponding Fig. 1 For example, a vane assembly 1 according to an embodiment of the invention has at least one vane carrier 2 and a plurality of stator vanes 3. The vane arrangement 1 is part of a turbomachine 4. Said turbomachine 4 is in particular a gas turbine. In principle, the turbomachine can also be a steam turbine or a compressor. The vane arrangement 1 has the guide vanes 3 of a row of guide vanes of the turbomachine 4. Usually, the turbomachine 4 is equipped with a plurality of vane rows.

In principle, each of these vane rows may comprise the vane arrangement 1 according to the invention.

The guide blade carrier 2 is attached to a housing 5 of the turbomachine 4. The vanes 3 are attached to the vane carrier 2. In order to form the guide blade row, the guide vanes 3 are arranged next to one another in the circumferential direction.

Each vane 3 has a platform 6 and a flow profile 7, which projects radially and inwardly from the Platlform 6. The platform 6 has a first latch portion 8 located on the left side of FIG Fig. 1 and a second latch portion 9 on the right side of FIG Fig. 1 , is shown. The locking portions 8, 9 are arranged at an axial distance from each other. For example, the first locking portion 8 is arranged in the region of a downstream side 10 of the profile 7, while the second locking portion 9 is arranged in the region of an inflow side 11 of the profile 7.

Complementary to the locking sections 8, 9, the guide blade carrier 2 has a first support section 12 and a second support section 13. The two support portions 12, 13 are also axially spaced apart from each other. Each latch section 8, 9 and the associated support section 12, 13 are designed such that they provide an axially pluggable and radially positive fastening between the guide blade carrier 2 and the respective vane 3. In other words, the cooperating latch sections 8, 9 and support sections 12, 13 open an axial push-in movement for mounting and an axial pull-out or pull-down movement to disassemble the respective guide blade 3. In the assembled state, the cooperating latch sections 8 , 9 and support sections 12, 13 a Radial fixation with a positive connection between the vane support 2 and the respective vane. 3

In addition, the vane arrangement 1 has at least one securing element 14 which is fastened to the guide vane carrier 2. Said securing element 14 is designed such that it provides an axial fixation of at least one of the guide vanes 3. The vane 3 is axially fixed or secured in its assembled state by means of said securing element 14.

Preferably, the support portions 12, 13 and the locking portions 8, 9 extend in the circumferential direction. During assembly, in principle, each vane 3 is adjustable in the circumferential direction. Such an adjustment may be advantageous for eliminating or reducing backlash between adjacent soldering vanes 3. According to the preferred embodiment, the first latch portion 8 and the second latch portion 9 are arranged at a radial distance from each other. This feature results in an axially compact structure of the vane assembly 1. This feature also reduces manufacturing costs. Of course, the first support portion 12 and the second support portion 13 may be radially spaced from each other.

The first support portion 12 has an inner collar 15 which projects radially inwardly from the Leitschaüfelträger 2 and extends in the circumferential direction. Said inner collar 15 is provided with an inner tongue 16 which extends axially and circumferentially. Complementarily, the first locking portion 8 has an inner groove 17. Said inner groove 17 is axially open and extends circumferentially. Said inner tongue 16 and said inner groove 17 are configured to provide a first tongue-and-groove joint 18 between the vane support 2 and the respective vane 3. In the assembled State, the inner tongue 16 projects axially into the inner groove 17 and engages radially on the platform 6.

The second latch portion 9 has an outer collar 19 which projects radially outward from the platform 6 and extends in the circumferential direction. Said outer collar 19 is provided with an outer tongue 20 which extends in the axial direction and in the circumferential direction. Accordingly, the second support portion 13 is provided with an outer groove 21 which is axially open and extends circumferentially. Said outer tongue 20 and said outer groove 21 are configured to provide a second tongue-and-groove joint 22 between the vane support 2 and the respective vane 3. In the assembled state, the outer tongue 20 extends into the outer groove 21 and engages radially on the guide vane carrier 2.

As mentioned above, the vane 3 is circumferentially adjustable during assembly. To a set position between the vane support 2 and the respective. Guide blade 3 to fix circumferentially, a locking pin 23 is provided. Said locking pin 23 penetrates into a recess 24, which is recessed in the outer collar 19. Said locking pin 23 is screwed into a complementary threaded opening 25 which is provided in the guide blade carrier 2.

Corresponding Fig. 2 the vane 3 is preferably equipped with at least one pullout opening 26, which is a threaded opening, which is provided for cooperation with a pullout device, not shown. By means of such an extraction device, the pulling or removal of the guide vane 3 from the guide vane carrier 2 is simplified.

Corresponding Fig. 3 the platform 6 has a cavity 27 which is open towards the guide blade carrier 2. Said cavity 27 is bounded radially inwardly by a base 28 of the platform 6. The airfoil 7 projects radially inwardly from said base 28. The cavity 27 is axially and circumferentially bounded by walls 29. Said walls 29 are radially outwardly of the base 28. The cavity 27 forms a cooling gas distribution chamber. For example, the airfoil 7 includes a cooling gas path 30 that is fluidically connected by the base 28 to the cavity 27.

The vane carrier 2 is equipped with a common collection channel 31. Said common collecting channel 31 extends circumferentially and preferably extends along the entire guide blade carrier 2. The housing 5 is equipped with at least one cooling gas supply channel 32 which is fluidly connected to a not shown cooling gas supply device. Said cooling gas supply channel 32 is also fluidly connected to the common collection channel 31 and thus supplies the common collecting channel 31 with cooling gas. The cooling gas flow is symbolized by arrows 33. The vane support 2 is additionally equipped with a plurality of connection openings 34. Each connection opening 34 fluidly connects the common collection channel 31 with one of the cavities 27. Accordingly, the cavities 27 of the guide vanes 3 are supplied with cooling gas from the common collection channel 31 via the respective connection opening 34. In the cavity 27, a baffle plate 43 may be arranged.

The use of a common collecting channel 31 for supplying a plurality or all of the guide vanes 3 with cooling gas, which is preferably air or steam, has the advantage that the cooling gas supply of the respective vane 3 due to approximately the same Kühlgaspfadkonfigurationen between the common collecting channel 31 and the cavities 27 of the respective guide vanes 3 can be provided with the same pressure. In addition, the at least one cooling gas supply passage 32 can be disposed within the housing 5 regardless of the position of the respective guide blade 3. Also, the number of cooling gas supply passages 32 may be smaller than the number of guide vanes 3 to be supplied with cooling gas. The flexibility for designing the housing 5 is increased, thereby reducing the manufacturing cost of the housing 5.

One of the walls 29, which axially delimits the cavity 27 in the region of the outflow side 10 of the airfoil 7, is provided with the first latching section 8. The other wall 29, which axially delimits the cavity 27 in the region of the inflow side 11 of the airfoil 7, is equipped with the second latch portion 9. Accordingly, the cavity 27 extends axially from the downstream side 10 to the inflow side 11. In the circumferential direction, said cavity 27 extends over the entire circumferential extent of the base 28th

Corresponding Fig. 3 are circumferentially adjacent vanes 3 equipped with a gap seal assembly 35. Said gap sealing arrangement 35 is designed to seal a gap 36, which is formed in each case between two circumferentially adjacent guide vanes 3. Said gap 36 extends axially between the two adjacent vanes 3. In particular, the gap 36 extends between two walls 29 which define the cavities 27 of said vanes 3 circumferentially.

Said gap seal arrangement 35 has a radial sealing plate 37 which extends circumferentially and axially. Perpendicular to its extension, the radial sealing plate 37 has a relatively small thickness, since the radial sealing plate 37 as Plate is formed. The platforms 6 of the two adjacent guide vanes 3 are provided with two radial sealing slots 38. Said pair of radial sealing slots 38 are arranged circumferentially opposite one another and extend axially and circumferentially. The radial sealing plate 37 is inserted into the radial sealing slot 38 to achieve a radial sealing effect.

Corresponding Fig. 1 For example, the gap seal arrangement 35 can also have a first axial sealing plate 39, which is arranged in the region of the first locking portion 8. Said first axial sealing plate 39 extends circumferentially and radially. Perpendicular to its extension, the first axial sealing plate 39 has a relatively small thickness. The platforms 6 of the two adjacent guide vanes 3 are provided with two circumferentially opposite first axial sealing slots 40. Said first axial sealing slots 40 extend circumferentially and radially. The first axial sealing plate 39 is inserted into said pair of first axial sealing slots 40 to achieve an axial sealing effect.

In addition, the gap seal arrangement 35 also has a second axial sealing plate 41, which extends parallel to the first axial sealing plate 39. Said second axial sealing plate 41 is arranged in the region of the second locking portion 9. The platforms 6 of the two adjacent vanes 3 are also provided with two circumferentially opposite second axial sealing slots 42 into which the second axial sealing plate 41 is inserted to achieve an axial sealing effect.

Corresponding Fig. 4 For example, each individual vane 3 can be assembled and disassembled independently of other vanes 3. In particular, the guide blade carrier 2 does not have to be dismantled for the assembly and disassembly of the guide vanes 3.

For the assembly of the vane 3 on the vane support 2, the respective vane 3 is moved axially according to an arrow 44. In an end phase of this axial movement, the two tongue and groove connections 18, 22 are produced by axial insertion of the tongues 16, 20 into the respective grooves 17, 21. After this insertion process, the respective guide blade 3 is fastened radially to the guide blade carrier 2 by means of the positive connection provided by the tongue and groove connections 18, 22.

To circumferentially fix the vane 3 with respect to the vane support 2, the locking pin 23 is mounted After mounting the locking pin 23, the securing element 14 is mounted to the vane support 2. Preferably, the securing element 14 and the vane support 2 are two tongue and groove joints 45, which are similar to the tongue and groove joints 18, 22 between the vane 3 and the vane carrier 2. The securing element 14 is fixed to the vane carrier 2 by means of at least one locking bolt 46 in connection with at least one inlet segment 47. Said inlet segment 24 is provided with a External platform 48. The platform 6 is provided with an internal step 49, which is arranged with respect to the mounting direction 44 at the rear end of the platform 6. In the mounted state accordingly Fig. 1 is the outer stage 48 of the inlet segment 47 with the inner stage 49 of the vane 3 in engagement. As a result, the inlet segment 47 is carried by the vane 3. The inlet segment 47 can additionally be fastened to the guide blade carrier 2 by further fastening means (not shown).

The locking bolt 46 penetrates the securing element 14 within a passage opening 50 and projects into a blind hole 51 which is formed on the guide blade carrier 2. When assembled, said locking bolt 46 is supported radially inwardly by the inlet segment 47. Radial On the outside, the locking bolt 46 is supported by the guide blade carrier 2 by means of a compression spring 52. The locking bolt 46 secures the axial position of the securing element 14 and the support between the two stages 48 and 49.

LIST OF REFERENCE NUMBERS

1

Vane arrangement

2

guide vane

3

vane

4

flow machine

5

housing

6

platform

7

flow profile

8th

first latch section

9

second latch section

10

Downstream side of 7

11

Upstream side of 7

12

first support section

13

second support section

14

fuse element

15

inner collar

16

interior tongue

17

inner groove

18

first tongue and groove connection

19

outer collar

20

outer tongue

21

outer groove

22

second tongue and groove connection

23

locking pin

24

deepening

25

threaded opening

26

excerpt opening

27

cavity

28

Base

29

wall

30

Cooling gas path

31

common collection channel

32

Cooling gas supply channel

33

Cooling gas flow

34

connecting opening

35

Gap sealing arrangement

36

gap

37

radial sealing plate

38

radial sealing slot

39

first axial sealing plate

40

first axial sealing slot

41

second axial sealing plate

42

second axial Dichtschtitz

43

flapper

44

mounting direction

45

Tongue and groove

46

locking bolt

47

inlet section

48

outdoor stage

49

indoor stage

50

Through opening

51

blind

52

compression spring

Claims (9)

1. Guide vane arrangement of a turbomachine (4), in particular of a gas turbine, comprising:

   - at least one guide vane carrier (2) which is fastened to a casing (5) of a turbomachine (4),

   - a plurality of guide vanes (3) which are fastened to the guide vane carrier (2) and are arranged next to one another in the circumferential direction,

   - each guide vane (3) having a platform (6), comprising a first locking portion (8), and, spaced apart axially from this, a second locking portion (9),

   - the guide vane carrier (2) having a first carrying portion (12), and, spaced apart axially from this, a second carrying portion (13),

   - each locking portion (8, 9) and the respective carrying portion (12, 13) being designed such that they provide an axially pluggable and a radially positive fastening between the guide vane carrier (2) and the respective guide vane (3),

   - at least one securing element (14) being fastened to the guide vane carrier (2) and being designed such that it provides an axial fixing of at least one of the guide vanes (3),

   characterized

   - in that each platform (6) or at least one of the platforms (6) has a cavity (27) which is delimited radially inward by a base (28) and which is delimited axially and circumferentially by walls (29) which project radially outward from the base (28),

   - in that the guide vane carrier (2) has a common collecting duct (31) which extends circumferentially,

   - in that the casing (5) has at least one cooling-gas supply duct (32) which is connected fluidically to the common collecting duct (31),

   - in that the guide vane carrier (2) has a plurality of connecting orifices (34) which in each case connect the common collecting duct (31) fluidically to one of the cavities (27).
2. Guide vane arrangement according to Claim 1,

   - the carrying portions (12, 13), and the locking portions (8, 9) extending in the circumferential direction, and/or

   - the first locking portion (8) and the second locking portion (9) being arranged at a mutual radial spacing, and/or

   - the first carrying portion (12) and the second carrying portion (13) being arranged at a mutual radial spacing.
3. Guide vane arrangement according to Claim 1 or 2,

   - the first carrying portion (12) having an inner collar (15) which projects radially inward and which extends in the circumferential direction,

   - the inner collar (15) being provided with an inner tongue (16) which extends axially and circumferentially,

   - the first locking portion (8) having an inner groove (17) which is axially open and which extends circumferentially,

   - the inner tongue (16) and inner groove (17) being configured such that they provide a first tongue-and-groove connection (18) between the guide vane carrier (2) and the respective guide vane (3).
4. Guide vane arrangement according to Claim 1 or any one of the preceding claims,

   - the second locking portion (9) having an outer collar (19) which projects radially outward and which extends in the circumferential direction,

   - the outer collar (19) being provided with an outer tongue (20) which extends axially and circumferentially,

   - the second carrying portion (13) having an outer groove (21) which is axially open and which extends circumferentially,

   - the outer tongue (20) and outer groove (21) being configured such that they provide a second tongue-and-groove connection (22) between the guide vane carrier (2) and the respective guide vane (3).
5. Guide vane arrangement according to Claim 1 or any one of the preceding claims,

   - one of the walls (29), which axially delimits the cavity, being equipped with the first locking portion (8), and/or

   - the other wall (29), which axially delimits the cavity (27), being equipped with the second locking portion (9).
6. Guide vane arrangement according to Claim 1 or any one of the preceding claims,

   - each guide vane having a flow profile (7) which projects radially inward from the base (28),

   - each flow profile (7) containing a cooling-gas path (30) which is connected fluidically to the cavity (27) by means of the base (28).
7. Guide vane arrangement according to Claim 1 or any one of the preceding claims,

   - circumferentially adjacent guide vanes (3) being provided with a gap seal arrangement (35) which is designed for sealing a gap (36) which extends axially in each case between two circumferentially adjacent guide vanes (3).
8. Guide vane arrangement according to Claim 7, comprising at least one of the following features:

   - the gap seal arrangement (35) has a first axial sealing plate (39) which is arranged in the region of the first locking portion (8) and which extends circumferentially and radially;

   - the platforms (6) of the two adjacent guide vanes (3) are provided with two circumferentially opposite first axial sealing slits (40) into which the first axial sealing plate (39) is inserted;

   - the seal arrangement (35) has a second axial sealing plate (41) which is arranged in the region of the second locking portion (9) and which extends circumferentially and radially;

   - the platforms (6) of the two adjacent guide vanes (3) are provided with two circumferentially opposite second axial sealing slits (42), into which the second axial sealing plate (41) is inserted;

   - the gap seal arrangement (35) has a radial sealing plate (37) which extends circumferentially and axially;

   - the platforms (6) of the two adjacent guide vanes (3) are provided with two circumferentially opposite radial sealing slits (38) into which the radial sealing plate (37) is inserted.
9. Turbomachine, in particular a gas turbine, comprising at least one row of guide vanes (3), which is equipped with the guide vane arrangement (1) according to Claim 1 or any one of Claims 1 to 8.

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