EP2725202A1 - Inner ring seal support arrangement for an adjustable stator blade assembly of a turbomachine - Google Patents

Abstract

The assembly (1) has a sealing substrate (4) that is pushed towards a circumferential direction or an axial direction of an inner ring (2) for storing a radially inner blade. An upper separation plane (8) having separate annular portions (10a,10b), and a lower separation plane (20) having separate support portions (22a,22b) are provided in the inner ring for sealing a radial gap to a rotor. The separation planes are twisted in a mounted state in a circumferential direction of a stator vane cascade relative to one another.

Description

The invention relates to an inner ring seal carrier assembly according to the preamble of patent claim 1 and a turbomachine.

Inner ring seal carrier assemblies for variable nozzle vanes of a turbomachine such as an aircraft engine or stationary gas turbine each have an inner ring to the radially inner guide blade bearing, which often has two joinable in a machine housing parting ring ring halves, and a pushed onto the inner ring or its ring halves seal carrier for sealing a radial gap to Rotor with two carrier halves which can be joined in the same parting plane. Such inner ring seal carrier assembly is for example in the DE 10 2006 024 085 A1 and WO 2010/081468 A1 , In order to prevent relative movement of the ring halves in the region of the parting plane and thus in the region of butt joints of the ring halves, the two ring halves are conventionally pinned together in the circumferential direction. In each case, at least one pin protrudes from one half of the ring beyond the dividing plane and enters a pin receptacle of the other half of the ring. However, the formation of the pin connections is relatively expensive. In particular, the pins formed as loose items can be lost before and during assembly.

The object of the invention is to provide an inner ring seal carrier assembly of an adjustable vane grille of a turbomachine, which eliminates the aforementioned disadvantages and prevents relative movement of ring members and support members in the assembled state. Furthermore, it is an object of the invention to provide a turbomachine with improved efficiency.

This object is achieved by an inner ring seal carrier arrangement with the features of patent claim 1 and by a turbomachine having the features of patent claim 8.

An inner ring seal carrier arrangement according to the invention of an adjustable guide vane grille of a turbomachine has an inner ring for the radially inner guide vane bearing, which has two ring parts separated at least in a first parting plane. Furthermore, the inner ring seal carrier assembly has a pushed onto the inner ring seal carrier for sealing a radial gap to the rotor of the two separate at least in a second parting plane support members. According to the dividing planes are rotated in the mounted state in the circumferential direction of the guide vane against each other or offset.

By the rotation of the parting planes against each other, the butt joints of the inner ring and the seal carrier are offset from each other, whereby an end overlap of the ring parts with the carrier parts or vice versa takes place. As a result, the ring parts and support parts fix each other in the region of their butt joints, whereby relative movements of the ring parts and the support parts to each other and to each other are prevented. A separate pinning of the ring parts and / or the carrier parts is not necessary. By fixing the two ring parts and the support members or by eliminating those relative mobility in the assembled state can also be a radial gap or a running gap between rotor seal tips to opposite, on the support parts on the inner peripheral side arranged static sealing elements or to a corresponding on the support parts inside circumference applied Precise adjustment of coating system. Furthermore, the seal carrier closes by the staggered assembly, the usual separation gaps between the opposing ring parts, whereby leakage currents are at least greatly reduced or completely prevented by the inner ring seal carrier assembly in the butt joints.

In one embodiment, the ring members and the support members each enclose an angle of 180 °, wherein the support members and the ring members are twisted to each other. As a result, the inner ring and the seal carrier each have two identical or symmetrical ring parts and two identical or symmetrical support parts, which allows a comfortable production and a particularly simple assembly.

In another embodiment, the two ring parts each enclose an angle of 180 °, wherein the carrier parts span different angles to form the offset parting planes. In this case, the one carrier parts has an angle which is reduced by a certain angle change, and the other carrier parts has an angle which is increased by this change in angle. The ring parts are thus symmetrical in this embodiment, allowing a comfortable production of these parts. The carrier parts are however asymmetrical.

In an alternative embodiment, the carrier parts are symmetrical and the ring parts each span different angles. In particular, the two support parts each enclose an angle of 180 ° and the one ring parts has an angle which is reduced by a certain angle change, and the other ring parts has an angle which is increased by this angle change. Thus, in this embodiment, the carrier parts can be produced conventionally.

In one embodiment, the two ring parts and the two support parts are each formed asymmetrically. In each case, the one ring parts and the one support parts enclose an angle which is reduced by a certain angle change, and the other ring parts and the other support parts each span an angle which is increased by this change in angle.

In a variant of this embodiment, the angular changes of the ring parts and the carrier parts are identical. This allows for easy production and easy twisted positioning of the parts to each other.

In an alternative variant of this embodiment, the angular changes of the ring parts and the support parts are different. Hereby a greatest possible flexibility with regard to the ring and support part angles is created.

A turbomachine according to the invention has an adjustable vane grille having an inner ring seal carrier assembly according to the invention. Due to the twisted arrangement of the parting planes of the inner ring and the seal carrier leakage currents are through Butt joints of the inner ring at least greatly reduced. In addition, the ring parts of the inner ring are fixed, whereby a precise running gap can be set to rotor tip points. This leads to reduced leakage flows through the running gap. Such a turbomachine thus has a higher efficiency and in particular a higher compressor efficiency compared to a turbomachine with a conventional guide vane grille.

Other advantageous embodiments of the invention are the subject of further subclaims.

Figur 1

eine Vorderansicht auf ein erstes Ausführungsbeispiel einer erfindungsgemäßen Innenring-Dichtungsträgeranordnung,

Figur 2

eine Detaildarstellung der Innenring-Dichtungsträgeranordnung im Bereich einer Stoßfuge,

Figur 3

eine schematische Vorderansicht auf ein zweites Ausführungsbeispiel der erfindungsgemäße Innenring-Dichtungsträgeranordnung,

Figur 4

eine schematische Vorderansicht auf ein drittes Ausführungsbeispiel der erfindungsgemäße Innenring-Dichtungsträgeranordnung, und

Figur 5

eine schematische Vorderansicht auf ein viertes Ausführungsbeispiel der erfindungsgemäße Innenring-Dichtungsträgeranordnung.

In the following, a preferred embodiment of the invention is explained in more detail with reference to schematic representations. Show it:

FIG. 1

a front view of a first embodiment of an inner ring seal carrier assembly according to the invention,

FIG. 2

a detailed representation of the inner ring seal carrier assembly in the region of a butt joint,

FIG. 3

a schematic front view of a second embodiment of the inner ring seal carrier assembly according to the invention,

FIG. 4

a schematic front view of a third embodiment of the inner ring seal carrier assembly according to the invention, and

FIG. 5

a schematic front view of a fourth embodiment of the inner ring seal carrier assembly according to the invention.

In FIG. 1 is a view of an embodiment of an inventive inner ring seal carrier assembly 1 shown in the flow direction of a hot gas stream. The inner ring seal carrier assembly 1 is part of an adjustable vane grille of a turbomachine such as an aircraft engine or a stationary gas turbine. The vane grille is arranged on the stator side in the compressor of the turbomachine and surrounds a rotor drum of a rotor which rotates about a rotor axis m. It has a multitude of uniformly distributed over its circumference and in FIG. 1 not illustrated vanes, which are each adjustable about their radially to the rotor axis m extending vertical axis.

The inner ring seal carrier assembly 1 has an inner ring 2 and a seal carrier 4, which is pushed onto the inner ring 2 in the circumferential direction or axial direction of the arrangement 1 and thus the guide vane grille and is arranged radially inwardly thereto.

The inner ring 2 serves for the radially inner bearing of the guide vanes. He has for this purpose a plurality of bearing bores 6, which are distributed uniformly over its circumference and in which the guide vanes are guided by means of a respective bearing bush, not shown. It consists of two in a first circumferential parting plane 8 separate ring parts 10a, 10b, which are mounted via an elastic deformation via guide blade pins. Of course, the ring parts 10a, 10b can additionally be subdivided along an axial dividing plane into ring quarters. In the embodiment shown, the ring parts 10a, 10b each enclose an angle α = 180 ° and are thus formed symmetrically. In the mounted state, the ring parts 10a, 10b lie flat against each other with their respective opposite side surfaces 12a, 12b.

As in FIG. 2 As shown, the ring members 10a, 10b for receiving the seal carrier 4 in the flow direction of the hot gas flow have front and rear guide members 14, 16 formed as a front guide groove 14 and a rear guide projection 16 in the embodiment shown here.

The seal carrier 4 is used to seal a radial gap to the rotor and in particular for sealing a running gap to opposite circumferential rotor seal tips. As in FIG. 1 For this purpose, the seal carrier 4 has an inner peripheral surface 18 for receiving corresponding sealing elements, not shown, such as honeycomb sheets or for applying a coating system. The seal carrier 4 consists of two separate in a second parting plane 20 support members 22a, 22b. In the exemplary embodiment shown, the carrier parts 22a, 22b each span an angle β = 180 ° and are thus formed symmetrically. In the assembled state, they lie with their side surfaces 24a, 24b flat against each other.

For sliding on the ring parts 10a, 10b, the carrier parts 22a, 22b with the guide elements 14, 16 corresponding counter-elements 26, 28. In the illustrated embodiment, the front mating member 26 is formed as a hook-like projection for engaging the guide groove 14 and the rear mating member 28 as a rear circumferential groove for receiving the rear guide projection 16.

In the in FIG. 1 In the embodiment shown, the ring parts 10a, 10b and the carrier parts 22a, 22b are oriented relative to one another such that the ring separating plane 8 is arranged offset in the circumferential direction to the carrier separating plane 20. As a result, the two abutting areas 30, 32 of the inner ring seal carrier arrangement 1 are designed as overlap joints, in which, as in FIG FIG. 2 shown, in each case an end-side support portion portion 34, an end-side ring portion portion 36 overlaps in the circumferential direction. The respective butt joints of the ring parts 10a, 10b and the carrier parts 22a, 22b are thus steppedly offset from each other, whereby the butt joints of the ring parts 10a, 10b are closed by the carrier parts 22a, 22b. As a result, leakage currents between the side surfaces 12a, 12b of the ring parts 10a, 10b are prevented or at least greatly reduced. At the same time, the overlap on the one hand fixes the inner ring 2 and, on the other hand, the seal carrier 4, so that relative movements of the ring parts 10a, 10b and the carrier parts 22a, 22b are prevented. By this fixation, the running gaps are precisely adjustable to the rotor tip.

As already mentioned above, are in the embodiment shown according to FIG. 1 the two ring parts 10a, 10b symmetrically and the two support parts 22a, 22b formed symmetrically. To form the twisted arrangement of the parting planes 8, 20, the ring parts 10a, 10 terminate flush with a housing parting plane 38 of the turbomachine, whereas the support parts 22a, 22b respectively protrude beyond the housing parting plane 38 with their support part section 34. The ring separation plane 8 is thus in this embodiment in the housing separation plane 38 and the carrier separation plane 20 is also rotated to the housing separation plane 38 in the circumferential direction. Of course, however, the carrier separation plane 20 positioned in the housing separation plane 38 and the ring separation plane 8 to the housing separation plane 36 staggered. Of course, both the inner ring 8 and the seal carrier 4 can be rotated with its parting plane 8, 20 to the housing separation plane 34.

In FIG. 3 an alternative embodiment of the inner ring seal carrier assembly 1 is shown. In this embodiment, the ring parts 10a, 10b are symmetrical and the support parts 22a, 22b are asymmetrical. The ring parts 10a, 10b each span an angle α = 180 °. The one support part 22a, however, spans an angle β '<180 ° and the other support part 22b an angle β "> 180 ° .An angular change Δ with respect to 180 ° is constant, so that the seal carrier 4 is closed over 360 ° in the installed state. In particular: β '= 180 ° - Δ and β "= 180 ° + Δ. The carrier parts 22a, 22b are thus formed by separating the seal carrier 4 along two parting planes 20 ', 20 "which are set apart by the angle change Δ. In the assembled state, for example, one carrier parting plane 20' lies in the housing parting plane 38, whereas the other carrier parting plane 20" is made by the angle change Δ to the housing separation plane 38. In addition, for example, the ring parts 10a, 10b are arranged such that the ring separation plane 8 is offset to the housing separation plane 38.

In FIG. 4 another embodiment of the inner ring seal carrier assembly 1 is shown. In this embodiment, the support parts 22a, 22b are symmetrical and the ring parts 10a, 10b are asymmetrical. The carrier parts 22a, 22b each span an angle β = 180 °. The one ring part 10a, however, spans an angle α '<180 ° and the other ring part 10b an angle α "> 180 ° .An angular change Δ with respect to 180 ° is constant, so that the inner support 2 is closed over 360 ° in the mounted state. In particular: α '= 180 ° -Δ and α "= 180 ° + Δ. The ring parts 10a, 10b are thus formed by separating the inner support 2 along two parting planes 8 ', 8 "set apart by the angle change Δ. In the assembled state, for example, one ring separation plane 8' lies in the housing separation plane 38, whereas the other ring separation plane 8" is made by the angle change Δ to the housing separation plane 38. In addition, for example, the carrier parts 22a, 22b arranged such that the carrier separation plane 20 is offset to the housing separation plane 38.

In FIG. 5 another embodiment of the inner ring seal carrier assembly 1 is shown. In this embodiment, the ring parts 10a, 10b are asymmetrical and the support parts 22a, 22b are asymmetrical. Both the inner ring 2 and the seal carrier 4 is divided along two mutually employed parting lines 8 ', 8 ", 20', 20" in two ring parts 10a, 10b and in two support parts 22a, 22b, each spanning an angle not equal to 180 ° , In the exemplary embodiment shown, an angle change Δr of the ring parts 10a, 10b is equal to an angle change Δt of the carrier parts 22a, 22b. However, the ring parts 10a, 10b and the carrier parts 22a, 22b may also have different angle changes Δr, Δt. The orientation of the ring parts 10a, 10b and the support parts 22a, 22b is in the embodiment shown such that in each case one of the ring separation planes 8 'and one of the support separation planes 20' lie in a housing separation plane 38 and the other ring separation plane 8 "and the other carrier separation plane 20 "offset to housing separation plane 38 are located. Of course, both parting planes 8 ', 8 ", 20', 20" of the inner ring 2 and the seal carrier 4 may be offset to the housing separation plane 38.

Disclosed is an inner ring seal carrier assembly of an adjustable guide vane grille of a turbomachine whose divided into two ring parts inner ring and its divided into two carrier parts seal carrier in the circumferential direction of the arrangement are arranged rotated to each other, and a turbomachine.

LIST OF REFERENCE NUMBERS

1

Inner-ring seal carrier assembly

2

inner ring

4

seal carrier

6

bearing bore

8, 8 ', 8 "

Parting plane / ring parting plane

10a, 10b

ring parts

12a, 12b

side surface

14

guide element

16

guide element

18

Inner circumferential surface

20, 20 ', 20 "

Parting plane / carrier separating plane

22a, 22b

support parts

24a, 24b

side surface

26

counter-element

28

counter-element

30

joint area

32

joint area

34

Support members section

36

Ring parts section

38

Housing separation plane

α, α ', α "

angle

β, β 'β "

angle

Δ, Δr, Δt

angle change

m

rotor axis

Claims (8)

Inner ring seal carrier assembly (1) of an adjustable stator blade of a turbomachine, having an inner ring (2) for radially inner guide blade bearing, the two in at least a first parting plane (8, 8 ', 8 ") separated ring parts (10a, 10b), and a Having on the inner ring (2) pushed-seal carrier (4) for sealing a radial gap to the rotor with two at least in a second parting plane (20, 20 ', 20 ") separate carrier parts (22a, 22b), characterized in that the parting planes (8 , 8 ', 8 ", 20, 20', 20") in the mounted state in the circumferential direction of the vane grille are rotated against each other. Inner ring according to claim 1, wherein the ring parts (10a, 10b) and the carrier parts (22a, 22b) each enclose an angle (α, β) of 180 ° and rotate the carrier parts (22a, 22b) to the ring parts (10a, 10b) are. Inner ring according to claim 1, wherein the two ring parts (10a, 10b) each enclose an angle (α) of 180 ° and the one support part (22a) has an angle (β ') which is reduced by a certain angle change (Δ). and the other support part (22b, 16) has an angle (β ") which is increased by the angle change (Δ). Inner ring according to claim 1, wherein the two support parts (22a, 22b) each enclose an angle (β) of 180 ° and the one ring part (10a, 13b) has an angle (α ') which is reduced by a certain angle change (Δ) , and the other ring part (10b) has an angle (α ") which is increased by the angle change (Δ). An inner ring according to claim 1, wherein said one ring member (10b) and said one support member (22b) have angles reduced by a certain angular change (Δr, Δt) and said other ring member (10a) and said other support member (22a), respectively have an angle which is increased by the angle change (Δr, Δt). Inner ring according to claim 5, wherein the angular changes (Δr, Δt) of the ring parts (10a, 10b) and the carrier parts (22a, 22b) are the same. An inner ring according to claim 5, wherein the angular changes (Δr, Δt) of the ring members (10a, 10b) and the support members (22a, 22b) are different. Turbomachine with an adjustable vane grille having an inner ring seal carrier assembly (1) according to any one of the preceding claims.

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