EP3613952A1 - Adjustable guide blade assembly, guide blade, seal carrier, and turbomachine - Google Patents

Abstract

The invention relates to a guide vane arrangement (100) for a turbomachine with an axis of rotation, in particular for a compressor or turbine stage of a gas turbine, a guide vane (10) and a seal carrier (20) for such a guide vane arrangement (100) and a turbomachine with such a guide vane arrangement (100), the guide vane arrangement (100) having a plurality of adjustable guide vanes (10) rotatably mounted about an adjustment axis (V), at least one inner ring segment (30) formed separately from the guide vanes (10) and one separately from the at least one inner ring segment ( 30) formed seal carrier (20), wherein the at least one inner ring segment (30) is attached to one or more guide vanes (10), and wherein the seal carrier (20) is centered on the at least one inner ring segment (30), so that the Seal carrier (20) opposite the at least one inner ring segment (30) in the direction we at least one adjustment axis (V) of at least one guide vane (10) and / or in the radial direction, based on the axis of rotation of the turbomachine in a functional state of use of the guide vane arrangement (100) in a turbomachine, is movably mounted.

Description

The present invention relates to a guide vane arrangement for a turbomachine with an axis of rotation, in particular for a compressor or turbine stage of a gas turbine, the guide vane arrangement comprising a plurality of adjustable guide vanes which are rotatably mounted about an adjustment axis, at least one inner ring segment which is formed separately from the guide vanes and one separately from the latter comprises at least one inner ring segment formed seal carrier.

Furthermore, the present invention relates to a guide vane, in particular an adjustable guide vane, for a aforementioned guide vane arrangement and a seal carrier for such a guide vane arrangement.

Furthermore, the present invention relates to a turbomachine, in particular a gas turbine, with at least one compressor or turbine stage with at least one guide vane arrangement.

When operating turbomachines with generic guide vane arrangements, the guide vane arrangements are exposed, among other things, to thermal stresses, in particular partially changing and / or high temperature gradients, in particular due to the working fluid flowing through the guide vane arrangement and thus at least partially flowing and / or flowing around the inner ring segments and / or through, in particular grinding , Seals which are arranged in the radial direction between the guide vanes and a rotor rotating relative to the latter. As a result of the thermal load, undesirable, thermally induced deformations of parts of the guide vane arrangement can occur, in particular to a change in the length of the guide vanes and to an expansion in the circumferential direction of the inner ring segments or of an inner ring formed from these and the seal carrier.

As a result, gaps can in particular widen between the individual components, in particular between the guide vanes and the inner ring or the corresponding inner ring segments, as well as between a sealing structure held by the seal carrier and the rotor, and consequently to undesirable leaks, which adversely affect the efficiency can affect the turbomachine.

The achievable sealing effect depends largely on the gap widths of the respective sealing gaps that arise during operation. The larger the sealing gaps that result, the larger the leaks that occur and, as a result, the resulting losses in efficiency.

The overall achievable sealing effect depends in particular on how the guide vanes are each connected with their radially inner end to the inner ring or corresponding inner ring segments, and how the seal carrier, on which a sealing structure for sealing an annular gap around the rotor is generally applied is attached around, designed and stored.

Various concepts of guide vane arrangements are known from the prior art, whereby basically between concepts for guide vane arrangements with fixed, i.e. A distinction must be made between non-adjustable guide vanes and concepts for guide vane arrangements with adjustable guide vanes, with different concepts for the connection or connection between the guide vanes and the inner ring or corresponding inner ring segments as well as with respect to both for guide vane arrangements with fixed guide vanes and for guide vane arrangements Connection and storage of the seal carrier are known.

From the EP 2 722 485 A1 For example, a guide vane arrangement with adjustable guide vanes is known in which the inner ring has at least one groove which extends in the axial direction and into which the seal carrier engages with a guide rail for attachment to the inner ring.

Guide vane arrangements with adjustable guide vanes are also known from internal operational practice, in which the seal carrier is formed integrally with the inner ring or corresponding inner ring segments.

In addition, guide vane arrangements with fixed guide vanes are known in which the seal carrier is mounted on the inner ring in a spoke-centered manner, for example from EP 2 696 039 A1 ,

An object of an embodiment of the present invention is to provide an alternative guide vane arrangement, in particular an improved guide vane arrangement, in which in particular the gap widths of the individual sealing gaps change less during operation and which consequently enables in particular larger tolerance ranges and in particular also simpler determination of the for a desired operating behavior maximum permissible tolerances. Another object of the invention is to provide an alternative, in particular improved, guide vane and an alternative, in particular improved, seal carrier for a guide vane arrangement, and an alternative, in particular improved, turbomachine.

This object is achieved by a guide vane arrangement having the features of claim 1, by a guide vane according to claim 11, by a seal carrier according to claim 14 and by a turbomachine according to claim 15. Advantageous embodiments of the invention are the subject of the dependent claims.

According to an embodiment of the present invention, a guide vane arrangement according to the invention for a turbomachine with an axis of rotation, in particular for a compressor or turbine stage of a gas turbine, comprises a plurality of adjustable guide vanes, in particular in each case rotatably mounted about an adjustment axis, at least one inner ring segment formed separately from the guide vanes and one seal carrier formed separately from the at least one inner ring segment, the at least one inner ring segment being fastened to one or more guide vanes, in particular to at most four guide vanes.

According to the invention, the seal carrier is mounted in a spoke-centered manner with respect to the at least one inner ring segment, so that the seal carrier with respect to the at least one inner ring segment in the direction of at least one adjustment axis of at least one guide vane and / or in the radial direction, based on the axis of rotation of the turbomachine, in a functional state of use of the guide vane arrangement in one Turbo machine that is movably mounted.

In the context of the present invention, an "adjustable guide vane" is understood to mean a guide vane which is designed for this purpose and in particular is mounted in the guide vane arrangement in such a way that it can be adjusted by rotation about an adjustment axis, in particular its flow angle, the adjustment axis with its Longitudinal axis can coincide, or can also be different from this, the adjustment axis extending in particular essentially in the longitudinal direction of the guide vane.

A "seal carrier" in the sense of the present invention is understood to mean a support structure which is designed to be a seal structure, in particular a seal structure which is fundamentally known from the prior art, such as a brush seal structure and / or a fundamentally also known and known from the prior art to hold so-called "honeycomb" structure used in turbomachinery.

For the purposes of the present invention, a "spoke-centered bearing" is understood to mean a bearing which is designed in such a way that the respective component mounted in this way, in the present case in particular the seal carrier, is always about an axis, in particular about a Axis that runs parallel to the axis of rotation of a turbomachine or is centered about the axis of rotation itself, and which also enables compensation in the radial direction, based on the axis of rotation of a turbomachine. That is, in other words, a spoke-centered bearing in the sense of the present invention is understood to mean in particular a bearing which in particular has a degree of freedom in the radial direction and which is self-centering with respect to an axis, in particular one parallel to the axis of rotation of a turbomachine extending axis or to the axis of rotation itself acts, similar to a bicycle wheel, in which the hub is supported by spokes in the rim.

Unless explicitly stated otherwise, in particular a different axis, the "axial" direction refers to a direction parallel to a main rotation or (main) machine axis of the turbomachine, the direction information "circumferential direction" in the present case in the usual manner "Correspondingly, unless explicitly stated otherwise, in particular a different axis, to a direction of rotation about this axis of rotation or (main) machine, the direction" radial ", unless explicitly stated otherwise, in particular another axis a direction perpendicular to the axial and circumferential directions. Unless explicitly stated otherwise, the direction "tangential" refers in particular to another axis, corresponding to a direction which is perpendicular to the axial direction according to the aforementioned definition and the radial direction according to the aforementioned definition, in particular all the direction information provided is not explicitly stated otherwise, in each case related to a functional installation state of the corresponding component in a turbomachine.

The spoke-centered mounting of the seal carrier according to the invention enables the seal in the region of the radially inner ends of the guide vanes to be decoupled between the guide vanes and the at least one inner ring segment from the seal with respect to a rotor.

In particular, by means of the spoke-centered mounting of the seal carrier according to the invention, in particular due to the degree of freedom in the radial direction, a decoupling of the mounting of the seal carrier in the radial direction can be achieved from the at least one inner ring segment. As a result, at least one sealing gap between the guide vane and the at least one inner ring segment can be designed and set independently of the seal carrier and thus also independently of a ring of a rotor. In other words, a change in the length of the guide vanes, which is in particular thermally induced, no longer necessarily leads to a change in the gap width of the sealing gap between the seal carrier or a sealing structure attached to it and the rotor and a, in particular thermally dependent,

Changing the length of the seal carrier in the circumferential direction or its diameter no longer necessarily leads to a change in a gap width between an inner ring segment and at least one guide vane.

A guide vane arrangement according to the invention also has the advantage that the gap between a sealing structure attached to the seal carrier and the rotor can be designed and adjusted almost independently of the at least one inner ring segment and its attachment to the respective guide vanes. As a result, the resulting sealing gaps between the at least one inner ring segment and the guide vanes to which the inner ring segment is fastened can be designed separately and independently of the sealing gap between the seal carrier or a sealing structure fastened thereon and the rotor, thereby shortening the tolerance chains to be taken into account, in particular divide, and consequently simplify and, furthermore, less tight tolerances are to be observed overall.

In one embodiment of the present invention, a guide vane arrangement according to the invention has, in particular, a plurality of adjustable guide vanes which are arranged distributed in the circumferential direction, in particular uniformly distributed in the circumferential direction, and are each rotatably mounted about an adjustment axis.

In an embodiment of a guide vane arrangement according to the present invention, at least one guide vane is arranged in such a way that, in a functional state of use of the guide vane arrangement in a turbomachine, its adjustment axis by more than 1 °, preferably by more than 2 °, in particular by more than 3 °, at most however, is inclined in the upstream direction by 5 °, in particular at most 4 °, preferably by at most 3 °, from a radial plane extending perpendicular to the axis of rotation of a turbomachine. This allows a particularly advantageous kinematics and a particularly advantageous flow behavior to be achieved, but still maintain sufficient play in the radial direction for advantageous, spoke-centered mounting of the seal carrier according to the invention.

In one embodiment of a guide vane arrangement according to the present invention, a separate inner ring segment is in particular assigned to each guide vane.

In an alternative embodiment of a guide vane arrangement according to the present invention, a plurality of guide vanes, in particular two or three guide vanes, but in particular, however, at most four guide vanes, are assigned to a common inner ring segment. That is, In an alternative embodiment of the present invention, an inner ring segment is fastened to a plurality of guide vanes, but in particular to a maximum of four guide vanes. Attachment to more than four guide vanes is possible. However, if the inner ring segment is attached to too many guide vanes, thermal stresses can occur, which can only be countered by larger gap dimensions between the inner ring segment and guide vanes, which in most cases will deteriorate the sealing effect, which can be a disadvantage of efficiency and therefore should be avoided.

In an embodiment of a guide vane arrangement according to the present invention, the guide vane arrangement comprises a plurality of inner ring segments which are arranged adjacent to one another in particular in the circumferential direction and in particular form an inner ring.

The individual inner ring segments are in particular designed in such a way that they have a type of shroud for delimiting a flow channel, in particular radially inward, which surrounds the guide vanes in the region of their flow profiles, the individual inner ring segments being in particular designed such that an inner shroud that is almost closed in the circumferential direction formed. In order to avoid thermally induced distortions, particularly in the circumferential direction, the individual inner ring segments are, however, in particular arranged at a sufficient distance from one another in the circumferential direction.

In one embodiment of a guide vane arrangement according to the present invention, the seal carrier has at least one sealing structure, in particular at least one, in particular at its radially inner end, based on a functional state of use of the guide vane arrangement in a turbomachine Brush sealing structure and / or at least one honeycomb sealing structure for sealing against a rotor rotatably mounted about an axis of rotation.

In a further development of a guide vane arrangement according to the present invention, at least one sealing structure is integral, i. H. in one piece, formed with the seal carrier.

In a further embodiment of a guide vane arrangement according to the present invention, the seal carrier is in particular spoke center-mounted on the guide vanes and / or the at least one inner ring segment, in particular over at least three bearing points distributed in the circumferential direction, in particular evenly distributed.

In a particularly advantageous embodiment of a guide vane arrangement according to the present invention, the seal carrier is mounted in a spoke-centered manner only on the guide vanes.

In this way, complete decoupling from the at least one inner ring segment, in particular from all inner ring segments, can be achieved and thus a decoupling of the seals of the guide vane (s) - inner ring segment and seal carrier / sealing structure - rotor.

In a further advantageous embodiment of a guide vane arrangement according to the present invention, at least one guide vane has at its radially inner end a fastening element, in particular a fastening pin, which extends along the adjustment axis, and the at least one inner ring segment which is fastened to this at least one guide vane, at least one associated, appropriately designed fastening opening, the fastening element of the guide vane, in particular in the direction of the adjustment axis, in particular extending through the at least one associated fastening opening of the inner ring segment.

This enables a particularly advantageous, spoke-centered mounting of the seal carrier on the guide vanes. In particular, this allows achieve a particularly advantageous embodiment of a guide vane arrangement, since in this way it is particularly easy to achieve attachment of the at least one inner ring segment to one or more guide vanes and, at the same time, spoke-centered mounting of the seal carrier on the guide vanes, namely on the radially inner ends of the guide vanes, which reach through the mounting holes.

Due to the spoke-centered, radially movable mounting of the seal carrier on the guide vanes, and thus in particular decoupled from the at least one inner ring segment, a thermally induced change in length of the guide vanes can be compensated for without a noticeable increase in the sealing gap between the seal structure attached to the seal carrier and the rotor. Since the at least one inner ring segment is fastened to the guide blades according to the invention, it follows the change in length of the guide blades, so that, in addition, an enlargement of the sealing gap between the guide blades and the inner ring segment can be avoided.

Alternatively or additionally, the seal carrier can also be mounted on the inner ring segments, in particular on at least three inner ring segments, in a spoke-centered manner, for example as is known from the prior art for a guide vane arrangement with fixed guide vanes and as for example in the EP 2 696 039 A1 described, the corresponding radial grooves being arranged in particular in the circumferential direction between the fastening elements of the guide vanes.

In one embodiment of a guide vane arrangement according to the present invention, at least one inner ring segment is fastened to the fastening element of the guide vane by means of an axial securing means and is secured on the fastening element in the direction of the adjustment axis, in particular with a defined play in the direction of the adjustment axis, in particular by means of a retaining ring or a locking washer.

In a further embodiment of a guide vane arrangement according to the present invention, the at least one inner ring segment is in this case with a defined one Game in the direction of the adjustment axis attached to one or more guide vanes, that the inner ring segment can be displaced outward in the direction of the adjustment axis within the scope of this play, in particular in such a way that the inner ring segment is in a radial direction Direction can be brought to bear on the associated guide vanes, so that a seal can be formed in the radial direction between the associated guide vanes and the inner ring segment, in particular with a sealing gap with a gap width of zero in the radial direction.

In order to achieve a particularly good sealing effect between the inner ring segment and the associated guide vanes, in particular when the inner ring segment is in contact with the associated guide vanes in the radial direction or in the direction of the adjustment axis, the associated guide vanes and the inner ring segment in particular have one or more appropriately designed, in particular radial shoulders and functional surfaces extending to the adjustment axis, in particular sealing surfaces.

In a further embodiment of a guide vane arrangement according to the present invention, the at least one inner ring segment is also attached to the respective guide vanes with a defined play in the axial direction and / or in the circumferential direction. In this way, tension, in particular thermally induced tension, can be avoided.

In a guide vane arrangement according to the invention, the guide vane is guided in the axial direction and / or in the circumferential direction in particular via the fastening elements of the guide vanes received by the seal carrier, with a clearance between the guide vanes and the at least one inner ring segment being greater in the axial direction and / or in the circumferential direction than between the guide vanes and the seal carrier in these directions.

In an embodiment of a guide vane arrangement according to the present invention, the seal carrier has at least one guide vane receptacle, into which the Fastening element, in particular a fastening pin, engages at least one guide vane in such a way that the fastening element of the guide vane is mounted movably with respect to the seal carrier in the guide vane receptacle of the seal carrier along the adjustment axis and / or in the radial direction, based on the state of use of the guide vane arrangement according to the invention in a turbomachine , wherein the guide vane receptacle is formed and arranged in the seal carrier in particular concentrically with at least one fastening opening of at least one inner ring segment.

As a result, the fastening element of at least one guide vane can be mounted so that it can move in the direction of the adjustment axis of the guide vane or in the radial direction, but at the same time, in particular in the axial direction and in the circumferential direction, relative to the axis of rotation of a turbomachine. This enables a particularly advantageous, spoke-centered mounting of the seal carrier to be formed. The spoke centering with the aid of fastening pins enables this, in particular in comparison to a slot-guided spoke centering, as for example from the EP 2 696 039 A1 is known, a more precise guidance and thus an improved, in particular more accurate centering. As a result, the gap widths can be set more precisely as a result.

In a preferred embodiment of a guide vane arrangement according to the present invention, the at least one guide vane receptacle is designed as a cylindrical or cup-shaped or cylinder-like or cup-like recess. Alternatively, at least one guide vane receptacle can also be designed as a frustoconical or conical recess, the fastening element provided for storage in the vane receptacle, in particular the respective fastening pin, in particular correspondingly corresponding, in particular correspondingly complementary, for the design of the vane receptacle.

In an embodiment of a guide vane arrangement according to the present invention, the fastening element of the guide vane engages, in particular in the direction of the adjustment axis, in particular with a defined play in the axial direction and / or in the circumferential direction, into the guide vane receptacle of the seal carrier, the play in the direction of the adjustment axis being dimensioned in particular at least so large that a thermally induced length increase of the guide vane is possible without tension during operation. It goes without saying that the play should be selected at most so large that the seal carrier is always securely mounted on the guide blades during operation and in particular that the fastening elements cannot slip out of the guide blade receptacles in the seal carrier.

In an alternative, but also conceivable, configuration of a guide vane arrangement according to the present invention, the fastening element, in particular in the form of a fastening pin, can also be assigned to the seal carrier and one or more guide vanes can each have a corresponding receptacle for the fastening element, in this case a "seal carrier receptacle" exhibit.

The seal carrier of a guide vane arrangement according to the invention can be formed in one part or in several parts and in particular in the circumferential direction and / or in the axial direction or in a direction perpendicular to the adjustment axis of at least one guide vane, in particular all guide vanes, can be axially divided, the individual parts being preferred in the case of a divided seal carrier are connected to one another by means of releasable connecting means, in particular by means of screws or the like.

In one embodiment of a guide vane arrangement according to the present invention, the seal carrier is a circumferentially formed seal carrier ring, wherein the seal carrier ring is formed in one piece in the circumferential direction or has several seal carrier segments that only extend over a part in the circumferential direction, the seal carrier in particular consisting of several, each only is assembled over a part extending in the circumferential direction of the seal carrier segments.

The division of the seal carrier in the circumferential direction enables a particularly simple assembly of a guide vane arrangement according to the invention, the individual seal carrier segments being arranged to overlap in particular in the circumferential direction, i.e. preferably by means of an overlap joint and not with a butt joint, the overlap surfaces in particular each being designed as wedge surfaces. In this way, a particularly good seal in the axial direction can be achieved on the seal carrier. Furthermore, an advantageous flow of force in the seal carrier can be achieved in this way.

In a development of a guide vane arrangement according to the present invention, at least one seal carrier segment or seal carrier part is produced by an additive manufacturing process, in which case the seal carrier segment in particular does not extend over more than a circumferential angle of 60 °. The production by an additive manufacturing process enables a particularly flexible configuration of the seal carrier, since this type of production enables a particularly high degree of geometric freedom with good mechanical and thermal properties at the same time.

In one embodiment of a guide vane arrangement according to the present invention, the seal carrier, in particular in the seal carrier ring or at least one seal carrier segment, is divided into at least one upstream seal carrier part and at least one downstream seal carrier part, the seal carrier in particular at least partially along a division plane running parallel to the adjusting axis of the guide vanes and / or is divided into an upstream seal carrier part and a downstream seal carrier part along a radial plane extending perpendicular to the axis of rotation.

This enables the guide vane receptacles to be inserted particularly easily into the seal carrier, and particularly simple assembly.

In a particularly advantageous embodiment of a guide vane arrangement according to the present invention, the seal carrier is divided both in the circumferential direction into seal carrier segments and also in an upstream and one downstream seal carrier part, wherein at least one seal carrier part or seal carrier segments is produced by an additive manufacturing process and / or extends in particular in the circumferential direction at most over a range of a circumferential angle of 60 °.

In a development of a guide vane arrangement according to the present invention, the at least one upstream seal carrier part and at least one downstream seal carrier part are connected to one another, in particular detachably, in particular by means of at least one, by means of at least one connecting means, in particular by means of at least one screw or by means of a rivet or the like Connecting means extending in a direction perpendicular to the parting plane of the seal carrier, wherein the at least one connecting means, based on a state of use of the guide vane arrangement according to the invention in a turbomachine, is arranged offset in the circumferential direction to the fastening elements of the guide vanes and in the radial direction, based on the axis of rotation of the turbomachine , in particular at the level of at least one fastening element of at least one guide vanes.

In particular with screws, the individual seal carrier parts can be assembled quickly, in particular releasably.

If the connecting means are each arranged in the radial direction at the level of the fastening elements, in particular at the level of the fastening pins, a guide vane arrangement which is particularly compact in the radial direction and saves space can be realized.

In a further embodiment of a guide vane arrangement according to the present invention, at least one inner ring segment and the seal carrier overlap, in particular downstream, in relation to a functional installation state in a turbomachine, in the direction of the adjustment axis or in the radial direction, at least partially and in particular form one in relation to one another the axis of rotation of a turbomachine in a functional state of use of the guide vane arrangement, sealing gap acting in the axial direction , wherein the sealing gap itself extends in particular parallel to the adjustment axis of at least one guide vane, in particular parallel to the adjustment axis of the closest guide vane, or in the radial direction.

As a result, a seal acting in the axial direction can be implemented in a particularly simple manner, in particular additionally, downstream of the guide vane receptacles, which in particular also enables a length compensation of the guide vane or a radial movement of the inner ring segment with respect to the seal carrier without the sealing effect in the axial direction Direction significantly negatively impact. Leakage effects can be reduced even further by the additional sealing, which generally has an advantageous effect on the efficiency of a turbomachine.

To form the axial seal, the at least one inner ring segment and the seal carrier, in particular a downstream part of the seal carrier, and in particular in each case downstream of the respective guide vane receptacle, each have a sealing flange which extends in the radial direction with respect to the axis of rotation of a turbomachine, wherein the sealing flange of the inner ring segment extends in particular radially inward, and the sealing flange of the seal carrier in particular radially outward.

A particularly good seal in the axial direction can be achieved if the at least one inner ring segment is fastened to the respective guide vane with a defined play in the axial direction, and the play is dimensioned in such a way that there is sufficient space available radially within the inner ring segment Operating pressure, the inner ring segment can be brought into contact with its sealing flange against the sealing flange of the seal carrier in the axial direction within the scope of this play, in particular such that a seal can be formed in the axial direction of the inner ring segment and the seal carrier, in particular with a sealing gap with a gap width of Zero in the axial direction.

In a further embodiment of a guide vane arrangement according to the present invention, the guide vane arrangement has at least two inner ring segments which are formed separately from the guide vanes, the at least two inner ring segments being arranged adjacent to one another in the circumferential direction and with a compensating gap in the circumferential direction therebetween, the compensating gap being based on the axis of rotation a turbomachine, in particular in the radial direction, in particular at least one sealing element being arranged between two inner ring segments arranged adjacent in the circumferential direction in the region of the compensating gap, in particular at least for at least partially sealing the compensating gap in the radial direction.

The compensating gaps can be used to reduce tensions in the circumferential direction, in particular thermally-induced tensions due to thermally induced expansions of the inner ring segments, or even to avoid them altogether if the compensating gaps are appropriately large.

By means of the at least one sealing element arranged in the compensating gap, leakages in this area can be reduced and in particular the sealing towards the radially inward can be improved, which has an advantageous effect on the efficiency.

At least one sealing element extends in particular in the circumferential direction and at least partially in the axial direction, at least one sealing element being in particular a sealing strip, in particular a sheet metal strip or the like, in particular made of spring steel, which in particular is accommodated in a correspondingly formed groove in each case by two adjacent inner ring segments is, in particular such that a labyrinth gap is formed between the sealing element and the respective inner ring segment.

In a guide vane according to the invention for a turbomachine, which is, in particular, an adjustable guide vane, in particular for a compressor or turbine stage of a gas turbine, in particular for a guide vane arrangement according to the invention, the guide vane relating to a functional installation state of the guide vane in a turbomachine and with respect to an axis of rotation of the turbomachine, has a radially outer end and a radially inner end, wherein in the region of the radially inner end of the guide vane an inner ring segment can be fastened to the guide vane and the guide vane along its radially inner end has an adjustment axis extending fastening pin, which is designed to cooperate with a fastening recess, in particular a fastening opening, of an inner ring segment which can be fastened to the guide vane, in particular to reach through a fastening opening, according to the invention, in the fastening pin, in each case with respect to the adjustment axis, in particular circumferential, radial Groove for receiving an axial securing means, in particular a locking ring or a locking washer, introduced.

This enables an inner ring segment to be attached to the guide vane in a very simple and robust manner.

In an embodiment of a guide vane according to the present invention, the fastening pin of the guide vane, with respect to the axis of rotation of a turbomachine, borders with its radially outer end to a shoulder with a larger outside diameter, the circumferential radial groove, with respect to the adjustment axis, for Recording the axial securing means with a defined distance in the direction of the radially inner end of the fastening pin from this shoulder of the guide vane is introduced into the fastening pin.

In this way, the fastening of an inner ring segment to the guide vane can be realized in a particularly simple manner, in particular with a defined play in the direction of the adjustment axis or with a defined play in the radial direction, based on an axis of rotation of a turbomachine.

In a further embodiment of a guide vane according to the present invention, the shoulder has an end face facing the radially inner end of the guide vane and extending in a radial plane perpendicular to the adjustment axis on, wherein the end face is at least partially, preferably completely, formed as a sealing surface.

In this way, a good seal between the guide vane and the at least one inner ring segment in the radial direction, based on an axis of rotation or in the direction of the adjustment axis, can be achieved in a particularly simple manner, as a result of which leakages can be reduced, which has an advantageous effect on the efficiency ,

In an advantageous embodiment of a guide vane according to the present invention, a peripheral surface of the fastening pin is at least partially, preferably completely, as a functional surface on a side of the groove facing away from the shoulder and facing the radially further inward end of the fastening pin or the radially inner end of the guide vane formed, in particular as a guide surface, in particular as a sliding bearing surface. The functional surface is designed in particular for guiding the fastening pin in a guide vane receptacle of a seal carrier, in particular for guiding the fastening pin in a seal carrier according to the invention, it being possible for the guide surface to have a functional coating, in particular a friction-reducing coating and / or a coating for increasing a surface hardness, in particular to prevent and / or reduce or even avoid fretting.

As a result, good guidance of the guide vane in the direction of the adjustment axis or in the radial direction, based on the axis of rotation of a turbomachine, can be achieved in a seal carrier in a particularly simple manner.

Furthermore, a guide vane equipped in this way enables a separation of the seal in the radial direction (via the end face of the shoulder) and a guide by means of different functional surfaces (end face of the shoulder for sealing in the radial direction relative to an inner ring segment, peripheral face of the fastening pin for guiding in the axial direction and circumferential direction) in the direction of the adjustment axis (over the circumferential surface of the fastening pin) and the seal towards the rotor. In this way, a particularly good seal between the guide vanes and an associated inner ring segment attached to the guide vanes can be achieved, with in particular a sealing gap in the direction of the adjustment axis and / or in the radial direction, based on the axis of rotation of a turbomachine, almost independently of the current length of the guide vane, ie not significantly changed due to a change in length of the guide vane under temperature, in particular not significantly increased. On the other hand, a sealing gap between a sealing structure held by the seal carrier and the rotor can also be set almost independently of a current guide vane length and thus independently of thermally induced changes in length of the guide vane occurring during operation.

A seal carrier according to the invention for a guide vane arrangement, in particular for a guide vane arrangement with adjustable guide vanes, in particular a compressor or turbine stage of a gas turbine, in particular for a guide vane arrangement according to the invention, is designed for spoke-centered storage in a guide vane arrangement and, according to the invention, has at least one guide vane receptacle for receiving a fastening element, in particular a fastening pin, an adjustable guide vane, into which the fastening element, in particular a fastening pin, of a guide vane can engage in such a way that the fastening element of the guide vane can move along an adjustment axis or longitudinal axis of the guide vane and / or in the radial direction, based on an axis of rotation of a turbomachine in a functional state of use of the seal carrier in a turbomachine, relative to the seal carrier in the guide blade receptacle of the seal carrier is storable and in particular also rotatable about the adjustment axis. In this way, a spoke-centered mounting of the seal carrier, in particular on the guide vanes, can be implemented in a particularly simple manner.

A turbomachine according to the invention, in particular a gas turbine, with at least one compressor or turbine stage with a guide vane arrangement with guide vanes has, according to the invention, a guide vane arrangement and / or at least one guide vane according to the invention and / or at least one seal carrier according to the invention.

Fig. 1

eine Prinzipdarstellung eines Ausschnitts eines Ausführungsbeispiels einer erfindungsgemäßen Leitschaufelanordnung mit einer erfindungsgemäßen Leitschaufel und einem erfindungsgemäßen Dichtungsträger mit Blick in Umfangsrichtung und

Fig. 2

die Leitschaufelanordnung aus Fig. 1 in abgewickelten Darstellung mit Blick in axialer Richtung, jedoch ohne den Dichtungsträger.

Further advantageous developments of the present invention result from the subclaims and the following description of preferred embodiments. This shows in a highly schematic way:

Fig. 1

a schematic representation of a section of an embodiment of a guide vane arrangement according to the invention with a guide vane according to the invention and a seal carrier according to the invention with a view in the circumferential direction and

Fig. 2

the vane assembly Fig. 1 in a developed view with a view in the axial direction, but without the seal carrier.

Fig. 1 shows a highly schematic basic illustration of a section of an exemplary embodiment of a guide vane arrangement 100 according to the invention with a view in the circumferential direction U of the guide vane arrangement 100, the guide vane arrangement 100 having an adjustable guide vane 10 according to the invention with a fastening pin 11 formed at its radially inner end, one on the guide vane 10 fastened inner ring segment 30 and a seal carrier 20 according to the invention, which is movably mounted on the fastening pin 11 in the radial direction R.

The guide vane 10 is rotatable about an adjustment axis V, which in this case runs in the radial direction R, but could also be inclined to it, in particular by a few degrees, and is rotatably mounted with respect to the inner ring segment 30 and rotatably received by the seal carrier 20.

At the radially inner end of the seal carrier 20 there is a sealing structure 21 in the form of a honeycomb sealing structure designed in a manner known from the prior art for sealing against a rotor (not shown here) 21 arranged, which in this embodiment is, in particular, integrally formed with the downstream seal carrier part 20B.

In order to fix the inner ring segment 30 to the guide vane 10, a circumferential groove 15 is introduced into the fastening pin 11, in which an axial securing means 40 in the form of a securing ring 40 engages, the inner ring segment 30 being fastened to the guide vane 10 with a defined play in the direction of the adjustment axis V. is.

The fastening pin 11 borders with its radially outer end on a shoulder 12 with a larger outer diameter, the, with respect to the adjustment axis, circumferential radial groove 15 for receiving the axial securing means 40 with a defined distance in the direction of the radially inner end of the fastening pin 11 of this shoulder 12 of the guide vane 10 is introduced into the fastening pin 11.

The play in the direction of the adjustment axis V between the guide vane 10 and the inner ring segment 30 in the radial direction, in particular in the region of a radially sealing sealing gap 13, is in particular dimensioned in such a way, in particular in connection with the geometric configuration of the inner ring segment 30, that by applying a Operating pressure p1 in a region radially within the inner ring segment 30, the inner ring segment 30 can be pressed outward in the direction of the adjustment axis V and can be brought into contact with the guide vane 10 in the region of the radially sealing sealing gap 13, as a result of which a particularly good radial seal Direction R can be achieved in the area of the sealing gap 13.

For a particularly good seal, the shoulder 12 of the guide vane has an end face facing the radially inner end of the guide vane 10 and extending in a radial plane perpendicular to the adjustment axis V, the end face being at least partially, preferably completely, designed as a sealing surface and one of the two Forms sealing surfaces of the radially sealing sealing gap 13. For fastening to the guide vane 10, the inner ring segment 30 has a fastening opening, which is not described here in greater detail, through which the radially inner end of the guide vane 10, in particular the fastening pin 11, extends, the guide vane 10 as a stop in the radial direction radially outward corresponding paragraph 12 and the inner ring segment 30 has a corresponding flange, not shown here.

The fastening pin 11, which extends through the fastening opening in the inner ring segment 30, is received in a guide vane receptacle 24 corresponding to the fastening pin 11, the vane receptacle 24 being a cylindrical recess in this exemplary embodiment and the fastening pin 11 being a cylindrical fastening pin 11.

The fastening pin 11 is guided with a defined play, symbolized by the guide gap 23, in the axial direction A and in the circumferential direction U in the seal carrier 20, with both a circumferential surface 27 of the fastening pin 11 and an inner circumferential surface of the guide vane receptacle 24 each having a coefficient of friction reduction Coated and also have a hardened surface to reduce the risk of fretting (fretting).

According to the invention, the seal carrier 20 is spoke-centered in the direction of the adjustment axis V, which in this case coincides with the radial direction R, and is movably mounted on the guide vane 10 in the direction of the adjustment axis V.

In this embodiment, the seal carrier 20 is divided on the one hand in the axial direction A and has an upstream seal carrier part 20A and a downstream seal carrier part 20B, which are each connected to one another by means of a plurality of connecting means 22 arranged in the circumferential direction in the form of screws 22, the connecting means 22 each are arranged at the level of the fastening pins 11 in the radial direction R in order to enable a particularly compact and space-saving design of the guide vane arrangement 100 in the radial direction R (see Fig. 2 ).

In addition to the axial division of the seal carrier 20, the latter is further divided in the circumferential direction U into a plurality of seal carrier segments, not shown, wherein the individual seal carrier segments each extend over no more than a circumferential angle range of 55 °. The individual seal carrier parts or segments are each produced by an additive manufacturing process.

The seal carrier segments adjacent to each other in the circumferential direction are arranged to overlap each other both in the axial direction A and in the circumferential direction U, the seal carrier segments in each case being wedge-shaped in the overlap regions, as a result of which a particularly good sealing effect can be achieved in the overlap region, in particular in the axial direction A. and in the circumferential direction U.

In this exemplary embodiment, the connecting means 22 in each case connect two adjacent, upstream seal carrier parts 20A to one another and also the two associated downstream seal carrier parts 20B, and these also to the two upstream seal carrier parts 20A. That is, With a connecting means 22, in particular a screw 22, a total of four individual parts of a seal carrier 20 are connected to one another in this exemplary embodiment of a guide vane arrangement 100 according to the invention.

For an even further improved sealing, the downstream seal carrier part 20B and the inner ring segment 30 each have on their downstream side a sealing flange 25 or 35 which extends in the radial direction and which overlap in the radial direction R and in the circumferential direction U and between them an axially acting one Form sealing gap 26.

For a particularly good sealing effect, the guide vane 10 is also connected in the area of its shoulder 12 in the axial direction A with a defined play to the inner support segment 30, in particular with a defined axial play 14, by applying a corresponding operating pressure p1 in connection with the geometric dimensions of the inner ring segment 30, the inner ring segment 30 can be displaced in the axial direction A in the direction of the sealing flange 25 of the seal carrier 20, in particular can be brought into abutment against the seal carrier 20, so that an axially acting sealing gap 26 with a gap width of zero is established and thus a seal of a Flow channel, which is designed to be flowed through by a hot gas flow with flow direction HS, is further improved radially inward compared to a region radially inside the seal carrier 20. Because should hot gas emerge through the radially sealing sealing gap 13, this can still be prevented by the downstream, axially acting sealing gap 26 from further escaping radially inwards.

As with Fig. 1 is clearly recognizable, in a guide vane arrangement 100 according to the invention, the seal carrier 20 is mounted so as to be movable in the direction of the adjustment axis V or in this case also in the radial direction R, relative to the guide vane 10 and the inner ring segment 30 fastened thereon. If a thermally induced length change of the guide vane 10 now occurs in operation in a turbomachine, the fastening pin 11 can move freely in the guide vane receptacle 24 in the direction of the adjustment axis V or in the radial direction R without this having a negative effect on a position of the Sealing structure 21 and thus on a sealing gap formed with a rotor, not shown here, in the radial direction.

Likewise, changing the length of the guide vane 10 does not change the gap width of the axially acting sealing gap 26 between the downstream seal carrier part 20B and the inner ring segment 30.

Since the inner ring segment 30 is fixed on the guide vane 10, it follows the change in length of the guide vane 10, so that there is also no change in the gap width of the radially sealing sealing gap 13.

A guide vane arrangement 100 according to the invention thus enables advantageous gap widths over a wide operating range and thus high efficiencies over a wide operating range.

Furthermore, the spoke-centered mounting of the seal carrier 20 according to the invention, decoupled from the inner ring segment 30, causes a separation of the tolerance chain and thus a significantly simplified determination of the maximum permissible tolerances in order to determine the respectively desired maximum gap widths or the maximum permissible for the desired, maximum gap widths tolerances.

Fig. 2 shows the guide vane arrangement 100 Fig. 1 with a view in the axial direction A in the direction of flow HS in a developed state, it being particularly easy to see in this illustration how two inner ring segments 30 are arranged in the circumferential direction U with a defined compensating gap 50 between them, in order to avoid tension in the circumferential direction, wherein a sealing element 60 is arranged in the area of the compensating gap 50, in particular in the form of a sealing strip 60 made of spring steel, which is respectively introduced into a groove in the two adjacent inner ring segments and extends in the axial direction A, in particular over the length of the inner ring segments 30 and over extends a certain distance in the circumferential direction U in order to effect a seal in the radial direction R between the inner ring segments 30. The sealing element 60 each forms a labyrinth gap with the associated inner ring segment 30.

Also clearly visible in this illustration is the position of the individual connecting elements 22 in each case between two guide vanes 10 and offset to these and in particular at the level of the fastening pins 11 in the radial direction R for a particularly space-saving and compact configuration of a guide vane arrangement 100 according to the invention in the radial direction.

It should be pointed out that the exemplary embodiments are only examples that are not intended to restrict the scope of protection, the applications and the structure in any way. Rather, the person skilled in the art is given a guide for the implementation of at least one exemplary embodiment by the preceding description, it being possible for various changes, in particular with regard to the function and arrangement of the described components, to be carried out without leaving the scope of protection as it is the claims and these equivalent combinations of features.

LIST OF REFERENCE NUMBERS

100

Guide vane arrangement according to the invention

10

vane

11

fastening pins

12

paragraph

13

radial sealing gap

14

end play

15

groove

20

seal carrier

20A

upstream seal carrier part

20B

downstream seal carrier part

21

sealing structure

22

Lanyard (screw)

23

guide gap

24

Leitschaufelaufnahme

25

Sealing flange of the seal carrier

26

axially sealing sealing gap

27

Circumferential surface of the fastening pin (functional surface)

30

Inner ring segment

35

Sealing flange of the inner ring segment

40

circlip

50

compensation gap

60

sealing element

A

axial direction

R

radial direction

U

circumferentially

HS

flow direction

p1

operating pressure

V

adjustment axis

Claims (15)

Guide vane arrangement (100) for a turbomachine with an axis of rotation, in particular for a compressor or turbine stage of a gas turbine, comprising: - Several, adjustable guide vanes (10) rotatably mounted about an adjustment axis (V), - At least one inner ring segment (30) formed separately from the guide vanes (10) a seal carrier (20) formed separately from the at least one inner ring segment (30), the at least one inner ring segment (30) being fastened to one or more guide vanes (10),
characterized in that the seal carrier (20) is mounted in a spoke center with respect to the at least one inner ring segment (30), so that the seal carrier (20) with respect to the at least one inner ring segment (30) in the direction of at least one adjustment axis (V), at least one guide vane (10 ) and / or in the radial direction (R), relative to the axis of rotation of the turbomachine in a functional state of use of the guide vane arrangement (100) in a turbomachine, is movably mounted. Guide vane arrangement (100) according to Claim 1, characterized in that the seal carrier (20) is mounted on the guide vanes (10) in a spoke-centered manner, in particular via at least three bearing points arranged distributed in the circumferential direction (U). Guide vane arrangement (100) according to Claim 1 or 2, characterized in that at least one guide vane (10) has at its radially inner end a fastening element (11), in particular a fastening pin (11), which extends along the adjustment axis (V), and at least an inner ring segment (30), which is fastened to this at least one guide vane (10), at least one associated, appropriately designed fastening opening, the fastening element (11) of the guide vane (10) through the at least one an associated fastening opening of the inner ring segment (30) passes through. Guide vane arrangement (100) according to Claim 3, characterized in that the at least one inner ring segment (30) is fastened to the fastening element (11) by means of an axial securing means (40) and is secured on the fastening element (11) in the direction of the adjustment axis (V), in particular by means of a locking ring (40) or a locking washer. Guide vane arrangement (100) according to claim 3 or 4, characterized in that the seal carrier (20) has at least one guide vane receptacle (24) into which the fastening element (11), in particular a fastening pin (11), engages at least one guide vane (10) in this way that the fastening element (11) of the guide vane is mounted so that it can move along the adjustment axis (V) and / or in the radial direction (R) relative to the seal carrier (20) in the guide vane receptacle (24) of the seal carrier (20). Guide vane arrangement (100) according to one of the preceding claims, characterized in that the seal carrier (20) is a circumferentially formed seal carrier ring, the seal carrier ring in the circumferential direction (U) being at least partially formed in one piece, or several, each only over a part in the circumferential direction (U) extending seal carrier segments, the seal carrier (20) being composed in particular of a plurality of seal carrier segments which only extend over a part in the circumferential direction (U). Guide vane arrangement (100) according to one of the preceding claims, characterized in that the seal carrier (20) is divided into at least one upstream seal carrier part (20A) and at least one downstream seal carrier part (20B), the seal carrier (20) in particular at least partially along a parallel to the adjustment axis (V) of the guide vanes (10) extending division plane and / or along a radial plane extending perpendicular to the axis of rotation in an upstream Seal support member (20A) and a downstream seal support member (20B) is divided. Guide vane arrangement (100) according to claim 7 or 8, characterized in that the upstream seal carrier part (20A) and the downstream seal carrier part (20B) are connected to one another by means of at least one connecting means (22), in particular by means of at least one in a direction perpendicular to the parting plane of the Connecting means (22) extending seal carrier (20), the at least one connecting means (22), in relation to a functional state of use of the guide vane arrangement (100) in a turbomachine, offset in the circumferential direction (U) from the fastening elements (11) of the guide vanes (10) is arranged and is located in the radial direction (R), in particular at the level of at least one fastening element (11) of at least one guide vane (10). Guide vane arrangement (100) according to one of the preceding claims, characterized in that at least one inner ring segment (30) and the seal carrier (20) overlap at least partially downstream in relation to a functional installation state in a turbomachine and in the direction of the adjustment axis (V) In the axial direction (A), form a sealing gap (26). Guide vane arrangement (100) according to one of the preceding claims, characterized in that the guide vane arrangement (100) has at least two inner ring segments (30) formed separately from the guide vanes (10), the at least two inner ring segments (30) being adjacent to one another in the circumferential direction (U) and with a compensating gap (50) in the circumferential direction (U) between them, in particular at least one sealing element (60) being arranged between two inner ring segments (30) arranged adjacent in the circumferential direction (U) in the region of the compensating gap (50) Sealing of the compensating gap (50) in the radial direction. Guide vane (10) for a turbomachine, in particular adjustable guide vane, in particular for a compressor or turbine stage of a gas turbine, in particular for a guide vane arrangement (100) according to one of claims 1 to 10, wherein the guide vane (10), based on a functional installation state of the Guide vane (10) in a turbomachine and in relation to an axis of rotation of the turbomachine, has a radially outer end and a radially inner end, an inner ring segment (30) being attachable to the guide vane (10) in the region of the radially inner end of the guide vane and the guide vane (10) has at its radially inner end a fastening pin (11) which extends along an adjustment axis (V) and which is designed to have a fastening recess, in particular a fastening opening, of an inner ring segment which can be fastened to the guide vane (11). 30) to cooperate, in particular through a fastening opening rch reach, characterized in that in the fastening pin (11), in relation to the adjustment axis (V), in particular circumferential, radial groove (15) for receiving an axial securing means (40), in particular a locking ring (40) or a locking washer, is introduced , Guide vane (10) according to claim 11, characterized in that the fastening pin (11), with respect to the axis of rotation of a turbomachine, is adjacent with its radially outer end to a shoulder (12) with a larger outer diameter, the circumferential radial groove ( 15) for receiving the axial securing means (40) at a defined distance in the direction of the radially inner end of the fastening pin (11) from this shoulder (12) of the guide vane (12) into the fastening pin (11). Guide vane (11) according to claim 12, characterized in that the shoulder (12) has an end face facing the radially inner end of the guide vane (10) and extending in a radial plane perpendicular to the adjustment axis (V), the end face at least partially, preferably completely, is designed as a sealing surface. Seal carrier (20) for a guide vane arrangement (100), in particular for a guide vane arrangement (100) with adjustable guide vanes (10), in particular a compressor or turbine stage of a gas turbine, in particular for a guide vane arrangement (100) according to one of claims 1 to 10, wherein the seal carrier (20) is designed for spoke-centered storage in a guide vane arrangement (100), characterized in that the seal carrier (20) is designed for spoke-centered storage on guide vanes (10) and at least one guide vane receptacle (24) for receiving a fastening element (11) , in particular a fastening pin (11), has an adjustable guide vane (10) into which the fastening element (11), in particular a fastening pin (11), of a guide vane (10) can engage in such a way that the fastening element (11) of the guide vane (10 ) movable along an adjustment axis (V) or longitudinal axis of the guide vane (10 ) and / or in the radial direction (R), based on an axis of rotation of a turbomachine in a functional use state of the seal carrier (20) in a turbomachine, relative to which the seal carrier (20) can be stored in the guide vane receptacle (24) of the seal carrier (20), and in particular also rotatable about the adjustment axis (V) of the guide vane (10). Turbo machine, in particular gas turbine, with at least one compressor or turbine stage with a guide vane arrangement (100) with guide vanes (10), characterized in that
the guide vane arrangement (100) is designed according to one of claims 1 to 10,
and or - At least one guide vane (10) according to one of claims 11 to 13 and / or - The seal carrier (20) according to claim 14.

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