EP2816198B1 - Guide vane assembly, guide vane and method for mounting a guide vane - Google Patents

Description

The invention relates to a vane assembly according to the preamble of claim 1, a vane for such a vane assembly, and a method of mounting such a vane.

From the prior art, a plurality of differently shaped turbomachines is already known. The turbomachines have an axially flow-through housing, to which at least one stator is attached, which has a plurality of adjacently arranged in the circumferential direction vanes. The vanes have at their radially inner end an end portion which may be releasably connected to a seal carrier. The seal carrier serves to seal a gap between the vane, in particular the end portion, and a rotor of the turbomachinery.

Guide vanes, which can be adjusted about their longitudinal axis are movably connected at its radial end with an inner ring segment as the end portion. According to in-house practice, a radially inner end of the vane, such as a spigot provided on the airfoil, is received in a bushing which is fixed by the inner ring segment. The inner ring segment is in turn releasably connected to a seal carrier segment. The fixation of the guide vane in the radial direction in the inner ring segment must be such that it is ensured that the vane can be adjusted about its own longitudinal axis.

From the DE 10 2009 038 623 A1 a vane is known which has at its radially inner end a transverse bearing element in the form of a spherical disk. To store the guide vane on the inner ring segment, the spherical disc is introduced into a bearing receptacle provided in the inner ring segment.

A disadvantage of the aforementioned connection is in particular that the components that are required for the movable mounting of the guide vane on the inner ring segment, require a lot of space.

From the EP 0 204 615 A1 For example, a turbomachine stator blade having an ankle bolt carrying a bushing rotatable in an inner ring is known, the ankle bolt being in the form of a pin laterally delimited by two parallel sides.

It is an object of one embodiment of the present invention to provide an improved turbomachine having at least one vane assembly. A task

It is an object of one embodiment of the present invention to provide an improved turbomachine having at least one vane assembly. An object of an embodiment of the present invention is in particular to provide a guide blade, which requires less space for the fixation or storage on the inner ring segment. Additionally or alternatively, an object of an embodiment of the present invention may be to provide a method by which the vane can be easily connected to the inner ring segment.

According to the invention, a vane arrangement with one or more vanes is provided. At least one vane has a radially inner pin which engages a bore of a bushing disposed in a bore of an inner ring segment. The spigot may extend radially inward from a radially inner end of a vane blade of the vane. Between the pin and the bush, a rotationally fixed connection is provided between the bushing and the bore of the inner ring segment a sliding bearing in the direction of rotation about the bore or adjustment axis. In one embodiment, the inner ring segment in the circumferential direction on a plurality of holes, at least in two, in particular in the two outer circumferential or frontal, bores bushings are slidably mounted, engage in the bores pins of vanes, which are rotatably connected to this socket. The pins of one or more, in particular all, further vanes of the inner ring segment may be rotatably connected in the same manner with bushings which are slidably mounted in bores of the inner ring segment. In another embodiment, the pins of one or more, in particular all, further, in particular in the circumferential direction inner vanes of the inner ring segment are rotatable or slidably mounted in their sockets, which in turn may be slidably mounted in bores of the inner ring segment.

As a rotationally fixed connection between a pin and a socket, in particular a connection is understood, in which the pin and the sleeve relative to each other, at least substantially or macroscopically, can not rotate. The sliding bearing between a bushing and a bore of the inner ring segment may be formed in one embodiment by a clearance fit.

Such a vane arrangement may have the advantage that by the use of the rotationally fixed connection between one or more pin and the respective bushing and by the sliding bearing between this bushing or these bushes and the respective bore of the inner ring segment of the assembly of the vane assembly, in particular the installation of the guide vane in the inner ring segment is simplified. In addition, in one embodiment, a fixing of the guide vane in the radial direction can be achieved. Additionally or alternatively, the guide vane assembly, in particular the vane of the inner ring segment, can be dismantled in a simpler manner. The space required for the components required for fixing is low in one embodiment, so that advantageously also a plurality of guide vanes can be coupled to the same inner ring segment.

Another advantage of the aforementioned vane arrangement may be that rotate due to the rotationally fixed connection between at least one vane and its socket in an adjustment of the vane about its longitudinal axis both the vane and the socket. Rotation of the bushing has the advantage that wear occurs primarily on the bushing and not on the journal of the blade, as is known in the art. Thus, when servicing the turbomachine, only the bushing and not the entire stator blade needs to be replaced. Furthermore, due to the rotationally fixed connection between the pin of the guide vane and the bush advantageously increases the span of the storage.

In a preferred embodiment, the pin may have an external thread and the socket have a screwed or screwed internal thread. Alternatively or additionally, a threaded sleeve may be arranged between the pin and the bush, which may be rotatably connected to the pin and / or the socket. The pin can be connected to the threaded sleeve by a screw connection. Alternatively or additionally, the bush can be connected to the threaded sleeve by a screw connection. Alternatively or additionally, the pin may have an external thread which is screwed or screwed to an internal thread of a nut. The nut can be supported against the bush, in particular in a state bolted to the journal. Furthermore, the nut may be arranged on the side facing away from the blade of the vane side of the bushing.

An advantage of the aforementioned connection possibilities may be that the guide vane can be connected in a simple manner to the inner ring segment, in particular the bushing, in a rotationally fixed manner.

A screw lock can be provided to secure the screw. The screw lock prevents loosening of the screw connection between the guide vane and the inner ring segment. Thus, a secure connection between the vane and the inner ring segment is ensured by the screw lock. In one embodiment, the screw lock can have a splint lock and / or a pin lock and / or a snap ring lock and / or a safety wire.

The inner ring segment can be releasably connected to a seal carrier segment, in particular by a positive connection. Furthermore, the inner ring segment may be coupled to at least one vane. The seal carrier segment may include a sealant extending from the seal carrier segment in a direction away from the inner ring segment. The seal carrier segment, in particular the sealing means, serves to seal a gap between the guide vane, in particular the inner carrier segment, and a rotor of the turbomachine.

According to another aspect of the invention, a vane is provided which has a pin with an external thread. The pin may protrude from the radially inner end of the airfoil. In particular, the pin can be stirred into the bore of the bush, which is arranged in the bore of the inner ring segment.

The vane assembly or vane described above may be used in a gas turbine, particularly an aircraft engine, having at least one compressor and / or turbine stage. However, the use of the vane assembly or vane is not limited to the gas turbine and aircraft engine, but may be used in other turbomachinery.

The mounting of at least one vane into an inner ring segment can be carried out as follows: The vane of the vane is inserted into the bore of the bush, which in one embodiment is already located in the bore of the inner ring segment. In another embodiment, first, the pin of the vane in the bore introduced the sleeve, which is then arranged in the bore of the inner ring segment wind. Similarly, the insertion of the pin into the bushing and the bushing in the inner ring segment can also be performed together, at least substantially.

The pin is fixed in rotation with the socket. The rotation can be done in particular by a screw or screwing. The bush is slidably mounted with the inner ring segment. The sliding bearing of the sleeve with the inner ring segment, as stated above, before or at the same time or after the rotation of the pin with the bushing. As a result of the sliding bearing a relative movement, in particular relative rotation, between the sleeve and the inner ring segment is possible. Dismantling can be done in an embodiment in reverse order.

By the method described above, an assembly and / or disassembly of the vane in a simple and fast way possible.

Fig. 1:

eine perspektivische Ansicht eines Ausschnitts der Verbindung einer Leitschaufel mit einem Innenringsegment einer Turbomaschine gemäß einer Ausführung der vorliegenden Erfindung,

Fig. 2:

eine Seitenschnittansicht einer Mehrzahl von in Umfangsrichtung benachbarten Leitschaufeln der Turbomaschine der Fig. 1,

Fig. 3

eine Seitenschnittansicht der Verbindung der Leitschaufel mit dem Innenringsegment der Turbomaschine der Fig. 1 mit einer Schraubensicherung gemäß einer Ausführung der vorliegenden Erfindung,

Fig. 4:

eine Seitenschnittansicht der Verbindung der Leitschaufel mit dem Innenringsegment der Turbomaschine der Fig. 1 mit einer Schraubensicherung gemäß einer weiteren Ausführung der vorliegenden Erfindung, und

Fig. 5:

eine Seitenschnittansicht der Verbindung der Leitschaufel mit dem Innenringsegment der Turbomaschine der Fig. 1 mit einer Schraubensicherung gemäß einer weiteren Ausführung der vorliegenden Erfindung.

Further features and advantages emerge from the subclaims and the exemplary embodiment. Show:

Fig. 1:

3 is a perspective view of a section of the connection of a guide vane to an inner ring segment of a turbomachine according to an embodiment of the present invention,

Fig. 2:

a side sectional view of a plurality of circumferentially adjacent vanes of the turbomachine of Fig. 1 .

Fig. 3

a side sectional view of the connection of the vane with the inner ring segment of the turbomachine of Fig. 1 with a screw lock according to an embodiment of the present invention,

4:

a side sectional view of the connection of the vane with the inner ring segment of the turbomachine of Fig. 1 with a screw lock according to another embodiment of the present invention, and

Fig. 5:

a side sectional view of the connection of the vane with the inner ring segment of the turbomachine of Fig. 1 with a screw lock according to another embodiment of the present invention.

An otherwise not shown turbomachine has a plurality of offset in the axial direction of the turbomachine to each other arranged impellers and guide wheels. The guide wheels are each arranged between two wheels along the axial direction of the turbomachine and have a plurality of guide vanes 110 in the circumferential direction.

At the in FIG. 1, 2 illustrated guide vanes 110 are those which are adjustable about its longitudinal axis. The vanes 110 are connected at their radially inner end with an inner ring segment 2. At the radially inner end of the inner ring segment 2, a flange 30 of the bushing 3 protrudes in the radial direction from the inner ring segment 2. The illustrated inner ring segment 2 is part of an inner ring, which is composed of a plurality of circumferentially adjacent inner ring segments 2.

Fig. 2 11 shows a side sectional view of a plurality of circumferentially adjacent vanes 110. Each vane 110 includes an airfoil having a peg 111 at the radially inner end. The pin 111 protrudes from the blade in the radial direction and engages in a bore of a bushing 3 a. The bushes 3 are arranged in bores of the inner ring segment 2.

The pins 111 of the circumferentially outer vanes (left, right in Fig. 2 ) each have an external thread, which is in engagement with an internal thread of the respective bushing 3. The bushes 3 are slidably mounted in bores of the inner ring segment 2. This means that the bushes 3 can rotate relative to the inner ring segment 2. At the same time it is ensured that no relative movement between the circumferentially outer bushes 3 and the outer circumferential guide vanes 110, in particular their pin 111, is possible.

The pins 111 of the other or circumferentially inner vanes (second to seventh vane in Fig. 2 ) have no external thread, but are slidably mounted in the bores of the respective sleeve 3. These bushes 3 are in turn slidably mounted in holes of the inner ring segment 2 or rotationally fixed. Likewise, these pins 111 may be rotationally fixed in the bores of the respective bushing 3, which in turn are slidably mounted in bores of the inner ring segment 2.

The inner ring segment 2 is connected to a seal carrier segment 4. The seal carrier segment 4 is part of a seal carrier, which has a plurality of circumferentially adjacent seal carrier segments 4.

Furthermore, (alternatively or in combination), only the two outer pins 111 of an inner ring segment can be screwed to the bushings 3. The screw can be secured by splint 33 against untwisting.

In FIG. 3 an enlarged view of a compound of a circumferentially outer stator blade 110 with the inner ring segment 2 is shown. The seal carrier segment 4 has a bottom, from which a sealing means 40 extends in a direction remote from the inner ring segment 2 direction. Further, extending from the seal carrier segment 4, two flanks, which are detachably connected at their respective end remote from the bottom of the seal carrier segment 4 via a positive connection with the inner ring segment 2.

The flange 30 of the bushing 3 protrudes from the inner ring segment 2 and projects transversely to a longitudinal axis of the bushing 3. At the end of the bushing remote from the flange 30, a sliding ring 5 is provided, which is arranged between the bushing 3 and the blade of the guide blade 110 is.

A screw lock is provided to prevent unscrewing the screw connection between the pin 111 and the socket 3. Thus, the screw lock serves to prevent relative movement between the pin 111 and the socket 3. The in FIG. 3 illustrated screw lock according to a first embodiment corresponds to a splint lock. To realize the splint lock, a recess is provided in the bushing 3, the pin 111 and a part of the inner ring segment 2, into or through which a split pin 33 can be inserted in order to realize the aforementioned securing.

In FIG. 4 a screw lock according to a second embodiment is shown. The screw lock has a locking pin 7, which is inserted into a gap between the pin 111 and the socket 3.

In FIG. 5 a screw lock according to a third embodiment is shown. In this, the screw lock on a fuse wire 8. The fuse wire 8 is arranged in receptacles in the socket 3 and coupled to the pin 111.

LIST OF REFERENCE NUMBERS

1

turbomachinery

2

Inner ring segment

3

Rifle

4

Seal carrier segment

5

sliding ring

7

safety pin

8th

fuse wire

10

impellers

11

Idlers

110

vanes

111

spigot

30

flange

33

cotter

40

sealant

Claims (11)

1. A guide vane assembly having at least one guide vane (110) with a radial inner journal (111), which engages in a borehole of a bushing (3), which is disposed in a borehole of an inner ring segment (2), with a rotation-resistant connection being present between the journal (111) and the bushing (3) and a slide mounting being present between the bushing (3) and the borehole of the inner ring segment (2), characterized in that the journal (111) has an outer thread and the bushing (3) has an inner thread screwed thereto.
2. The guide vane assembly as set forth in the preceding claim, characterized in that a threaded sleeve is disposed between the journal (111) and the bushing (3), and that the journal (111) and the bushing (3) are connected to the threaded sleeve.
3. The guide vane assembly as set forth in any one of the preceding claims, characterized in that the journal (111) has an outer thread that is screwed with an inner thread of a nut.
4. The guide vane assembly as set forth in any one of the preceding claims, characterized by a screw locking device for securing the screw connection between the inner thread of the bushing and an outer thread screwed thereto and/or the screw connection between an outer thread of the journal and an inner thread screwed thereto.
5. The guide vane assembly as set forth in the preceding claim, characterized in that the screw locking device has a split-pin locking device (33) and/or locking pin (7) and/or snap-ring locking device and/or a locking wire (8).
6. The guide vane assembly as set forth in the preceding claim, characterized in that the inner ring segment (2) is detachably connected to a seal support segment (4).
7. The guide vane assembly as set forth in any one of the preceding claims, characterized by at least one additional guide vane (110) that is distanced in the peripheral direction, particularly on the outside in the peripheral direction, and has an additional radially inner journal (111) that engages in an additional borehole of a bushing (3), which is disposed in an additional borehole of an inner ring segment (2), with the additional journal (111) and the additional bushing (3) being connected in a rotation-resistant manner, and with the additional bushing (3) being slide-mounted in the additional borehole of the inner ring segment (2).
8. The guide vane assembly as set forth in any one of the preceding claims, characterized by at least one additional, adjacent guide vane (110), particularly on the inside in the peripheral direction, having an additional radially inner journal (111) that engages in an additional borehole of a bushing (3), which is disposed in an additional borehole of an inner ring segment (2), with the additional journal (111) being slide-mounted in the additional bushing (3) and/or with the additional bushing (3) being slide-mounted in the additional borehole of the inner ring segment (2).
9. A guide vane (110) with a journal (111) having an outer thread for a guide vane assembly as set forth in any one of preceding claims 1 to 6.
10. A gas turbine, particularly aircraft engine, having at least one compressor and/or turbine stage with a guide vane assembly as set forth in any one of preceding claims 1 to 8 and/or a guide vane (110) as set forth in claim 9.
11. A method for fastening a guide vane (110) as set forth in claim 9 to an inner ring segment (2), characterized by the following steps:

    - introduction of a journal (111) of the guide vane (110) into a borehole of a bushing (3),

    - previous, simultaneous, or subsequent disposal of the bushing in a borehole of the inner ring segment (2), and

    - precious, simultaneous, or subsequent rotational fixation of the journal (111) to the bushing (3).

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