EP4180635A1 - Pivotable guide vane assembly of a flow machine and method for assembling a pivotable guide vane assembly - Google Patents

Abstract

The invention relates to a guide vane arrangement (10) and a method for assembling a guide vane arrangement (10) of a turbomachine, having a plurality of adjustable guide vanes (11) whose guide vane platform (12) has a guide vane journal mounted in a receiving opening (14) of a housing (15) of the turbomachine (13), wherein a guide vane head (16) of the guide vane (11) has a bearing journal which is mounted on an inner ring (19) arranged on a rotor (119) of the turbomachine. Between the housing (15) and the vane platform (12), an assembly space (20) is formed, in which a support device (30) is arranged, which supports the vane (11) against the housing (15). Guide vane journals (13) arranged on a guide vane platform (12) of a guide vane (11) are guided into a receiving opening (14) of a housing (15) arranged radially with respect to a rotor axis of the turbomachine, and an inner ring (19) is provided on a rotor (119) of the turbomachine, the guide vane platform (12) forming an assembly space (20) with the housing. A support (30) is placed in the mounting space (20) so that the vane (11) is supported against the casing (15), and the support (30) is locked.

Description

The invention relates to a guide vane arrangement of a turbomachine, having a plurality of adjustable guide vanes, the guide vane platform of which has a guide vane journal which is mounted in a receiving opening of a housing of the turbomachine, and a method for assembling a guide vane arrangement.

A turbomachine includes a compressor, a combustor, and a turbine arranged in series in the direction of flow. Air enters the turbomachine and is pressurized in the compressor. The compressed air is then mixed with fuel in the combustion chamber. Hot combustion gases are generated when the mixture of compressed air and fuel is subsequently burned in the combustion chamber. The hot combustion gases flow downstream to the turbine, which extracts energy from the combustion gases to drive the compressor.

Both the compressor and turbine of a turbomachine typically include multiple stages, with each stage having a row of stationary vanes and a row of rotating blades. The stationary vanes steer the gas flow in such a way that it flows against the rotating rotor blades at a specified angle. To adapt the angle of attack, the guide vanes can be designed to be adjustable around their longitudinal axis. Such vanes are typically journalled at their radially inner end to a stationary inner ring, providing spoke centering of the assembly. This creates a degree of freedom for the inner ring relative to the rotor of the turbomachine, as a result of which there is a necessary play between these components of the turbomachine. The radially outer ends of the adjustable guide vanes are usually mounted on the housing of the turbomachine so that they can rotate about their longitudinal axis, which is in particular radially aligned. Since several components are typically installed in a tight installation space on the inner ring, complex inner ring constructions are sometimes required, which impair the stability or inherent rigidity of the inner ring and thus also the continuity of a sealing gap of the turbomachine.

Proceeding from this, it is an object of the present invention to provide an improved guide vane arrangement of a turbomachine and an improved turbomachine. Furthermore, an improved method for assembling a guide vane arrangement and for assembling a flow arrangement of a turbomachine is to be made available. According to the invention, this is achieved by the teaching of the independent claims. Advantageous embodiments of the invention are the subject matter of the dependent claims.

To solve the problem, a guide vane arrangement of a turbomachine with a plurality of adjustable guide vanes is proposed. The guide vane platform of a guide vane has a guide vane journal, which is mounted in a receiving opening, in particular arranged radially with respect to a rotor axis of the turbomachine, in a housing of the turbomachine. A vane head of the vane has a bearing journal which is mounted on an inner ring which is arranged on a rotor of the turbomachine. A support device is arranged in a mounting space formed between the housing and the vane platform, which supports the vane against the housing.

The support device reduces, in particular prevents, a movement of the guide vanes relative to the housing, in particular in a longitudinal direction of the guide vane, and in particular of a plurality of guide vanes relative to one another. A load on the inner ring caused by a relative movement of the guide vane(s) can thus be reduced, which on the one hand enables a simplified construction of the inner ring and on the other hand the assembly of the guide vane arrangement is facilitated by a simplified construction of the inner ring.

A turbomachine has a housing (stator) through which flow can flow axially, on which a plurality of guide vanes, in particular a multiplicity of guide vanes arranged adjacent in the circumferential direction, are arranged radially to an axis of rotation of the turbomachine, in particular spoke-centered. In one embodiment of the invention, the housing can also be made in one piece, in particular circumferentially, as a result of which a more uniform thermal expansion of the housing and thus an improved gap behavior between rotor and stator is made possible.

Each vane can be rotatably mounted in the receiving opening of the housing via a bearing bush. For the purpose of adjustment, the guide vane can be connected to an adjusting mechanism and in particular to an adjusting lever, in particular at an end of the guide vane journal which is arranged on the outside of the housing. The guide vane can be rotatable about its adjustment axis by means of the adjustment mechanism, in particular at a predetermined angle.

The guide vane, which extends in particular radially to an axis of rotation of the turbomachine, has the guide vane head, which is mounted on the inner ring, on its side facing the rotor of the turbomachine. For this purpose, the guide vane head has a bearing journal, which is received by a bearing seat arranged in particular on the peripheral side of the inner ring and is rotatably held therein. The inner ring is configured to coaxially surround the rotor and configured to interconnect the vanes of the vane assembly to stabilize the vane assembly and provide proper vibratory behavior of the vane assembly. A sealing device is arranged on the inner ring and serves to seal a sealing gap formed between the inner ring and the peripheral surfaces arranged opposite on the rotor. The inner ring can have, for example, a radially outer part of a labyrinth seal on its radial inner surface facing the rotor, which forms a labyrinth seal with a second radially inner part arranged on the opposite radial outer surface of the rotor.

The proposed solution is based, among other things, on the idea of supporting a guide vane at its housing-side end in such a way that the guide vane arrangement can have greater stability in order to make the structure of the inner ring simpler. To this end, it is proposed to use an assembly space, which is formed in particular during the assembly of the guide vane, to support the guide vane.

This assembly space is in particular formed essentially in the housing of the turbomachine and can be at least partially open or delimited by the guide vane platform. In this case, the guide vane platform can in particular be arranged essentially completely within the assembly space, or at least partially protrude out of it. The assembly space can have at least one, in particular along the radial inside of the Housing running and / or having a segmented projection or wall, which is used for arranging the guide vanes and / or for arranging or fastening the support device. The support device can be designed to essentially completely fill the assembly space, in particular radially to the turbomachine, at least in regions or sections, in order to enable the guide vane to be supported. In particular, the support device is set up to at least partially encompass the guide vane journal, in particular axially, in order to also support the guide vane in particular in the axial direction of the guide vane journal. In this way, the guide vane is supported in particular essentially without play in relation to the housing. The support device is in particular also set up to rest at least partially on the housing radially with respect to the guide vane journal in order to enable force to be introduced in the radial direction of the guide vane journal via the support device into the housing.

In some embodiments, a bearing bushing is arranged between the receiving opening formed in the housing and the guide vane journal, which supports the guide vane journal in particular so that it can rotate about an axis of the guide vane journal and thus enables the guide vane to be adjustable. In addition, a slide bushing acting in the axial direction can also be arranged between the guide vane platform and the support device, which is set up to enable a rotary movement of the guide vane, in particular the guide vane platform, relative to the support device.

The proposed guide vane arrangement makes it possible to use a degree of freedom created by the installation space on the housing when mounting the guide vanes on the inner ring, as a result of which the provision and accessibility of components, in particular of the guide vane arrangement, is improved. As a result, the inner ring can also be constructed and assembled in a simplified manner. In addition, the proposed guide vane arrangement and its simplified assembly allows the housing and/or the inner ring of the turbomachine to be designed as undivided components. The additional omission of connecting components for the housing or the inner ring also enables a weight reduction and a fundamentally more cost-effective design of the turbomachine. In addition, the proposed structure, which provides a support device in the assembly space or between the vane and the housing, which in particular one of the Guide vane platform facing the end of a guide vane journal is arranged, the vibration resistance of the guide vane (s) and thus also the guide vane arrangement can be improved.

In one embodiment of the guide vane arrangement, the inner ring is designed in one piece or in one piece or in segments. A one-piece or one-part inner ring within the meaning of the disclosure is designed as a ring that completely surrounds the rotor and can be pushed or pushed axially around the rotor of the turbomachine. In particular, on the peripheral side, the inner ring has at least one bearing seat, which is aligned in particular radially with respect to the turbomachine and is set up to accommodate a bearing journal of a guide vane.

In one embodiment of the guide vane arrangement, the inner ring can also be designed as a half ring. A half ring within the meaning of the disclosure describes a semicircular arc and is in particular designed as a circular arc with an inner diameter and an outer diameter arranged coaxially thereto, having a central angle of 180° over the inner and/or outer diameter. In particular, the inner ring of the guide vane arrangement is formed from two half-rings which complement one another to form a circumferential ring which is designed to completely enclose the rotor coaxially. Such an embodiment of the inner ring can increase the stability of the inner ring and/or the guide vane arrangement, as a result of which sealing of a circumferential sealing gap of the turbomachine can also be stabilized and thus improved.

In one embodiment of the guide vane arrangement, the housing is designed in one piece, in particular circumferentially. As a result, the airtightness of the housing and thus of the turbomachine can be improved. Furthermore, the additional material of the flange surfaces results in unequal thermal behavior over the circumference of the housing, which has an unfavorable effect on the radial gaps between the rotor and stator. In addition, a one-piece housing has a simpler construction, so that it can also be produced more cost-effectively, in particular since fastening elements such as nuts and screws required for connecting a plurality of housing parts can be omitted.

In one embodiment of the guide vane arrangement, the support device can be designed to center an adjustment axis of the guide vane in the receiving opening. For this purpose, the support device can be set up to provide the guide vane in addition to a support in the radial direction, also axially and/or in the circumferential direction of the turbomachine, in particular with respect to its housing. Centering the guide vanes can also reduce wear on a bearing bushing in the receiving opening.

In one embodiment of the guide vane arrangement, the support device has at least one first support element and at least one second support element. The support elements can be designed and/or arranged in the assembly space in such a way that they form a support device or support the guide vane against the housing. For example, the first support element and the second support element can be designed or interact in such a way that they, in particular together, radially at least partially, in particular completely, enclose the guide vane journal. The first support element and the second support element can rest against one another. In particular, both support elements are designed to rest against the housing in the axial and/or circumferential direction, in particular within the assembly space on the housing, in order to support the guide vane. In particular, the support elements can be introduced individually and independently of one another into the assembly space or can be moved therein, as a result of which assembly of the guide vane arrangement is further simplified.

In one embodiment of the guide vane arrangement, the first support element is locked by means of the second support element. In particular, the first support element is locked or fixed by means of the second support element in such a way that it is firmly arranged in the assembly space, in particular during operation. For example, a first support element can rest against a suitably aligned projection or wall of the housing and be held in position by a second support element. The assembly space can be delimited adjacent to the guide vane trunnion by the housing or a projection or wall of the housing and be open in another area adjacent to the guide vane trunnion, in particular opposite, in order to be able to arrange one or more support elements during assembly.

The support elements can be designed to correspond to one another or be analogous to one another in order to form a form-fitting connection. In particular, the support elements can each have mutually facing contact surfaces which are designed to create a form fit between the two support elements. In one embodiment, an additional fixation, in particular of a first support element, can also be omitted, which simplifies assembly of the guide vane arrangement.

In one embodiment of the guide vane arrangement, the second support element can be locked by means of a fastening element arranged in particular on the housing. The fastening element can be designed and/or arranged in the housing in such a way that there is a positive connection between the second support element and the fastening element. In particular, the fastening element can be formed by a liner element arranged on an inner circumference of the housing. In this case, the second support element is locked or fastened by means of the liner element, it being possible for the liner element to be pushed into a receiving device of the housing which is set up for this purpose. In this way, a space-saving attachment of the second support element and thus in particular of the first support element or the support device is also possible.

In one embodiment of the guide vane arrangement, the first support element can be designed as a hollow cylinder segment. In particular, the first support element can be designed as a hollow cylinder half or as a hollow cylinder segment having a central angle of 180° over the outer and/or inner diameter of the hollow cylinder segment. An inner diameter of the hollow cylinder essentially corresponds in particular to a diameter of the guide vane journal, so that the first support element partially, in particular half, radially surrounds the guide vane journal and thus enables a firm seat or form-fitting support of the guide vane. The support element can be placed in the assembly space, for example, by rotating around the guide vane journal.

In one embodiment of the guide vane arrangement, the second support element can be set up with at least two first support elements, each of which is assigned to a guide vane, a support device, in particular for the respective guide vane(s), to train. The second support element can be set up to contact at least two, in particular several, first support elements that are adjacent in the circumferential direction or to bear against them and/or to lock them in order to form a support device. In particular, the mounting space of this embodiment can be formed along a radial inner circumference of the housing of the turbomachine. For example, an area of the mounting space that is set up to arrange the second support element therein can also be formed along a radial inner circumference of the housing of the turbomachine. In this way, a plurality or also a large number of first support elements can also be locked by means of a second support element, as a result of which the stability of the support device(s) and thus of the guide vane arrangement can be improved.

In one embodiment of the guide vane arrangement, the second support element can be designed as a ring segment which has at least two adapter sections, and each adapter section is designed to cooperate with a first support element to form a support device. In particular, the second support element can be embodied as a half ring, so that two second support elements together form an essentially complete circular ring in order to be or can be arranged in an assembly space embodied circumferentially, in particular along a radial inner side of the housing, or in an area of the assembly space embodied circumferentially.

An adapter section is arranged in particular on an end face of the ring segment and has a radially aligned recess in particular. The adapter section of the second support element is configured to cooperate with a first support element to form a support device. This recess, which is arranged in the adapter section of the second support element, can be of essentially cylindrical design in order to at least partially accommodate or encompass the guide vane pivot. In addition, a contact surface for the first support element can be provided on both sides of the recess, which is in particular set up to form a form fit with the first support element.

In one embodiment of the guide vane arrangement, the support device has at least one third support element. In such an embodiment acts at least a third Support element in particular with at least one first and / or at least one second support element together to form a support device for at least one vane. For example, the first and the second support element can be constructed identically, in particular in a mirror-symmetrical manner, and in particular can be set up to encompass the guide vane journal. For example, the first support element and the second support element can be essentially cuboid and have a recess which is set up to accommodate a guide vane journal. The first and the second support element can also be set up to hold the third support element in the mounting space. For this purpose, the third support element can, for example, form a particularly positive connection with at least one first support element and/or at least one second support element.

In one embodiment of the guide vane arrangement, the third support element is configured to be arranged between two guide vane platforms in order to support them. In this case, the third support element is set up, for example, to form a form-fitting connection with at least one guide vane platform. For example, the guide vane platform has an essentially cylindrical outer contour transverse to an adjustment axis of the guide vane, which allows rotation about the adjustment axis. In such an embodiment, the third support element can be set up to interact in a form-fitting manner with the guide vane platforms of two adjacent guide vanes in order to support them against one another and space them apart.

For example, the third support element can be designed to be arranged in or at least essentially in the assembly space in such a way that it supports at least one guide vane platform against the housing. In particular, it can be arranged between two guide vane platforms in or at least essentially in the assembly space so that it supports two guide vane platforms, in particular adjacent ones, against one another and/or against the housing. The third support element can have at least one fixing device, in particular a first fixing device. This engages, for example, in a form-fitting manner in a fixing bearing. Such a fixing bearing can in particular be designed as a groove which is designed, for example, in at least one first support element, in particular in two first support elements. The third supporting element can also have a second fixing device, which also engages in particular in a form-fitting manner in a fixing bearing, which is formed, for example, on at least one second support element, or in particular on two second support elements.

In one embodiment of the guide vane arrangement, the first support element and the second support element are each locked by means of a fastening element. In this case, a fastening element can be designed, for example, as a screw or bolt that can be fixed in some other way. In one embodiment, the support elements can each be locked or fixed by means of a fastening element designed as a bolt. A bolt can be inserted in particular transversely to the guide vane journal in an opening arranged in the housing and fix a support element on the guide vane journal, in particular tensioned against the guide vane journal in order to support the guide vane against the housing. It can be provided here that the support elements can each be displaced by a fastening element from an assembly position into a holding position in which the guide vane is supported by the support elements in the housing. In particular, it can be provided that an area is formed in the housing or in the assembly space, in which the support elements can be arranged or maintained and can be moved towards one another by means of fastening elements, in particular in the direction of the guide vane journal, in order to form a support device.

In one embodiment of the guide vane arrangement, a large number of guide vanes can be arranged radially, in particular circumferentially, on the housing and each guide vane can be supported against the housing by means of a support device.

In one embodiment, the support device is designed as a circular arc segment and has at least two receiving recesses which are each set up to at least partially receive a guide vane journal.

The support device or the receiving recess(es) is/are set up to axially, in particular at least partially, encompass the respective guide vane journal in order to support the respective guide vane relative to the housing and thus to stiffen the guide vane arrangement. The support device can be set up, in particular radially to the Guide vane trunnions to be inserted and placed (in an assembly) in the assembly space and there at least partially abut the casing to provide support. In this way, a plurality of guide vane journals can be supported by means of the support device, as a result of which the stability of the support device and thus of the guide vane arrangement can be improved.

In one embodiment of the guide vane arrangement, the support device can be designed as a half ring, so that two support devices can enable the guide vanes to be supported, in particular circumferentially, with one another. A half ring within the meaning of the disclosure describes an arc of a semicircle and is designed in particular as an arc of a circle with an inner diameter and an outer diameter, having a central angle of 180° over the inner and/or outer diameter. In this way, two supporting devices can form a circumferential ring in order to be or to be arranged in a particularly circumferential assembly space. In this way, the number of components for the guide vane arrangement can be reduced and thus the assembly time can be reduced. Here, the assembly space can be delimited in an area radially to the vane journal by the housing or the projection of the housing and be open in a further area radially to the vane journal in order to be able to insert the support device or support devices during assembly.

In one embodiment, the receiving recess is essentially U-shaped and/or is open in particular in the axial direction. The support device can thus be pushed around or between the guide vane journals during assembly, in particular in an axial direction. Installation of the support device in the installation space can be simplified by such an embodiment, since the support device can be placed in the installation space in an axial movement around the guide vane journal.

An end region of the receiving recess supporting the guide vane journal can be designed in the form of a hollow cylinder in order to radially encompass the guide vane journal, in particular halfway. A width or an inner diameter of the U-shaped receiving recess can essentially correspond to the diameter of the guide vane pivot, so that the support device or its exceptional recess(es) can hold the respective guide vane pivot can encompass radially and thus allows a tight fit or a form-fitting support of the guide vanes.

In some embodiments, the receiving recess may not be designed axially, i.e., for example, at an angle to a flank of the support device, or curved, so that during an assembly movement, an additional direction to the axial pushing-on can occur in order to prevent the support device from becoming detached, in particular in the axial direction make more difficult.

In one embodiment, the support device has at least one spacer element, which is set up to be arranged around the guide vane pivot and/or around the guide vane platform. In this case, the spacer element can be set up to at least partially, in particular completely, encompass the guide vane platform and to support it with respect to the housing and/or the support device. The guide vane platform has an essentially circular outer contour perpendicular to an adjustment axis of the guide vane in order to enable rotation about the adjustment axis. Due to the fact that the spacer element encompasses the respective guide vane platform and at the same time can be positioned or supported in relation to the housing and/or the support device, forces can be absorbed by the guide vanes.

In one embodiment, the spacer element is set up to at least partially accommodate a sliding bush or thrust washer, in particular to fix it against the guide vane platform and/or to enable the guide vane to be adjusted about the adjustment axis or the guide vane pivot. The fastening of the thrust washer made possible in this way can reduce wear.

In one embodiment, the spacer element has a substantially rectangular cross section. In particular, two adjacent spacer elements are set up to support one another, in particular in the circumferential direction of the turbomachine, in order to support and/or space two adjacent guide vane platforms against one another. In this case, the spacer element can have a substantially rectangular or square cross-section in order to be able to be arranged between the support device, housing and guide vane platform in the assembly space, and a mutual one To support two spacer elements, in particular in the circumferential direction of the turbomachine, to support and in particular to cover or limit the assembly space. For example, the spacer element can rest against a projection of the housing, which is arranged in particular radially to the guide vane journal, and can be held in position by the support device and/or a fixing section of the support device and/or the guide vane platform.

In one embodiment of the guide vane arrangement, a large number of guide vanes can be arranged radially, in particular circumferentially, on the housing and each guide vane can be supported by means of at least one support device. In this case, each guide vane can be assigned a receiving recess and in particular a support element in order to support the plurality of guide vanes. With this embodiment, a guide vane arrangement that can be assembled in a simplified manner can be created, which at the same time enables a stable configuration of a sealing gap of the turbomachine.

• Führen eines an einer Leitschaufelplattform einer Leitschaufel angeordneten Leitschaufelzapfens in eine radial zu einer Rotorachse der Strömungsmaschine angeordnete Aufnahmeöffnung eines Gehäuses;
• Bereitstellen eines Innenrings an einem Rotor der Strömungsmaschine;
• Führen des Leitschaufelzapfens aus der Aufnahmeöffnung bis ein an einem Leitschaufelkopf der Leitschaufel angeordneter Lagerzapfen in einen am Innenring angeordneten Lagersitz eingreift, wobei die Leitschaufelplattform mit dem Gehäuse einen Montageraum ausbildet;
• Anordnen einer Abstützeinrichtung in dem Montageraum, so dass die Leitschaufel gegen das Gehäuse abgestützt wird; und
• Arretieren der Abstützeinrichtung.

According to a further aspect of the invention, a method for assembling a guide vane arrangement of a turbomachine is specified, comprising the following steps:

• guiding a guide vane journal arranged on a guide vane platform of a guide vane into a receiving opening of a housing arranged radially with respect to a rotor axis of the turbomachine;
• providing an inner ring on a rotor of the turbomachine;
• guiding the guide vane journal out of the receiving opening until a bearing journal arranged on a guide vane head of the guide vane engages in a bearing seat arranged on the inner ring, the guide vane platform forming an assembly space with the housing;
• arranging a support device in the mounting space so that the vane is supported against the casing; and
• Locking the support device.

The radial guidance of the guide vane in the receiving opening simplifies the assembly of the guide vane arrangement, since the installation space in the turbomachine can be better used and the construction of the inner ring can be simplified. Moreover, it is through that proposed method also possible to arrange the vane assembly in a one-piece housing, whereby the turbomachine can be made lighter and cheaper.

Since the guide vane arrangement is arranged rotationally symmetrically to the axis of rotation of the rotor, the guide vanes can be mounted on the inner ring radially around the rotor. Furthermore, the inner ring can be designed more simply due to the use of a housing-side mounting space for supporting the guide vanes. In a guide vane arrangement according to the invention, this can be designed, for example, as a closed ring, in particular a one-piece ring, or can be composed of two half rings, as a result of which the number of components to be assembled can be reduced. In particular, the proposed method allows a reduction in the complexity of the design of the inner ring and thus also a more cost-effective manufacture and assembly of the inner ring and other components of the turbomachine.

In this case, the support device can be locked, for example, by means of a fastening element arranged in particular on the housing, so that the support device is arranged firmly in the assembly space, in particular during operation.

In one embodiment, when arranging the support device, a first support element and then a second support element can be arranged in the mounting space to form a support device. A first support element can be introduced into the assembly space and then locked by means of a second support element, particularly after the guide vane has been guided out of the receiving opening and arranged on the inner ring (bearing journal engages in the bearing seat).

In particular, each guide vane can be assigned a first support element and arranged in the assembly space and subsequently locked by means of a second support element, the second support element being configured to interact with a plurality of first support elements and to form a support device for a plurality of guide vanes. Here, the second support element as a ring segment or as a half ring be formed, which is set up to be received substantially in the assembly space.

In one embodiment, the second support element can be fastened by means of a fastening element, in particular by means of a liner element of the turbomachine, which in particular also locks the first support element.

In another embodiment, before the guide vane is inserted, a first and a second support element is arranged in the assembly space and after the guide vane has been guided out of the receiving opening (bearing journal engages in the bearing seat), a third support element is arranged in the assembly space. In this way, the first support element and the second support element can be kept available in at least one area of the assembly space in order to be brought into an end position in a further step, in which they support the guide vane against the housing.

Here, the housing can have an opening in the assembly space, in particular in front of the receiving opening, for inserting the guide vane or the guide vane platform, which adjoins an area for holding the first support element and an area for holding the second support element. These areas are limited in particular by the housing. A support element can be arranged in each of these areas of the assembly space in such a way that the support elements can be moved in a further step towards one another and thereby towards the guide vane trunnion arranged between them, in order in particular to at least partially encompass it in the end position or to support it in a form-fitting manner against the housing.

After the guide vane is in its intended position, in particular if the bearing journal is arranged in the bearing seat on the inner ring, a third support element can be arranged in the assembly space between the guide vane platform and the housing. For this purpose, the third support element can be set up, for example, to create a form fit with at least one guide vane platform. In particular, the third support element is designed to be arranged in an opening of the assembly space arranged between the housing and a guide vane platform. Here is the third support element in particular designed to close the assembly space together with the vane platform in a direction facing the rotor. The mounting space or one or more area(s) of the mounting space can be formed along a radial inner side of the housing.

The third support element can be set up to be arranged between two adjacent guide vane platforms. In this case, the third support element can be set up to form a form fit with two adjacent guide vane platforms and to space them apart from one another and/or to support them against the housing.

Furthermore, the third support element can have a fixing device which is set up to be arranged on at least one first support element and/or on at least one second support element and with at least one first support element, in particular two adjacent first support elements, and/or at least one second support element, in particular two adjacent second support elements to be positively connected. For example, the third support element can have at least one, in particular T-shaped, fixing device which is set up to be arranged on at least one or between two first and/or second support element(s). The first support element and/or the second support element can have at least one groove which is set up to accommodate a partial area of an in particular T-shaped fixing device.

In one embodiment, the method includes a further step of arranging a spacer element around the vane pivot or vane platform of the vane. A sliding bushing or pressure washer can first be inserted into the spacer element or arranged around the guide vane journal before the spacer element is arranged on the guide vane journal or the guide vane platform and the guide vane journal is inserted into the receiving opening of the housing. In this way, the spacer element can be kept available, in particular in a region of the assembly space, in order to be brought into an end position in a further step in order to support the guide vane(s) against one another or against the housing. In this case, the spacer element is designed in particular to close off the assembly space together with the guide vane platform in a direction facing the rotor. The opening of the housing, which in particular is an opening of the Assembly space forms, and / or the assembly space can be formed circumferentially or continuously on the housing and in particular circumferentially or continuously be completed by means of the vane platforms and spacer elements.

In one embodiment, the guide vane journal is guided into and out of a receiving opening along an adjustment axis of the guide vane arranged radially with respect to a rotor axis of the turbomachine. In this case, the guide vane is introduced into the installation space of the turbomachine and the adjustment axis of the guide vane is aligned with the receiving opening formed in the housing. The vane journal is then guided into the receiving opening, in particular until the surface of the vane platform facing the vane journal strikes the housing. In this case, the guide vane is arranged in a radially outer position, so that there is sufficient installation space radially inside the guide vane in order to provide an inner ring on the rotor. For example, the guide vane can be rotated through an angle, in particular by about 90°, when being guided into or out of the receiving opening, in order to be able to move a blade of the guide vane, in particular temporarily, into the assembly space, thereby increasing the installation space for providing the inner ring can.

As soon as the inner ring is provided on the rotor and in particular arranged in the intended position, the guide vane can be guided out of the receiving opening along the adjustment axis until the bearing journal of the guide vane engages in a bearing seat arranged on the circumference of the inner ring and can be fastened to it. The adjustment axis is in particular a central axis of the guide vane pivot and thus also the axis of rotation of the guide vane, about which this guide vane or the guide vane blade can be rotated in order to bring about a desired inflow through the air flow.

In one embodiment, the method includes a further step of connecting the vane pivot to an adjustment device. In particular, the adjustment device is set up to adjust the guide vane at a predetermined angle about its adjustment axis in order to guide a gas flow in such a way that it flows at a preferred angle of an arrangement of rotating rotor blades. The adjustment device can be connected to the guide vane journal by means of an adjustment lever. In particular, the Adjusting device designed so that it interacts with a variety of other adjusting devices, which are connected to a plurality of guide vanes or vane journals of a guide vane arrangement.

• Bereitstellen eines Gehäuses;
• Anordnen einer ersten Laufschaufelanordnung in dem Gehäuse;
• Montieren einer ersten Leitschaufelanordnung gemäß einem oder mehrerer Aspekte des vorausgehend beschriebenen Verfahrens in dem Gehäuse; und
• Anordnen einer zweiten Laufschaufelanordnung in dem Gehäuse.

According to a further aspect of the invention, a method for assembling a flow arrangement of a turbomachine is specified, comprising the following steps:

• providing a housing;
• placing a first blade assembly within the casing;
• assembling a first vane assembly according to one or more aspects of the method described above in the casing; and
• locating a second blade assembly within the casing.

A flow arrangement of a turbomachine forms in particular a compressor or a turbine device and usually has a number of stages. Each stage includes a stationary vane assembly and a rotating blade assembly extending from a rotor hub. In particular, in the proposed method, a housing that is configured in particular in one or more parts to be rotationally symmetrical about an axis of rotation of the turbomachine can be provided, in which housing a first rotor blade arrangement is arranged. In this case, for example, first a large number of guide vanes are arranged in and in particular also on the housing in such a way that one guide vane journal is guided into a receiving opening of the housing arranged in particular radially to the rotor axis of the turbomachine. An inner ring is then provided, in particular on the rotor, and the guide vane journal of the respective guide vane is guided out of the receiving opening in the direction of the axis of rotation of the turbomachine until a bearing journal arranged on a guide vane head of the respective guide vane engages in a bearing seat arranged on the inner ring. The guide vane platform now forms an assembly space with the housing, in which in the next step a support device is arranged in such a way that it supports the guide vane(s) against the housing. In the next step, the support device can then be locked. In a further step, the guide vane pin of the respective guide vane can be connected to an adjustment device.

In a further step of the proposed method for assembling a flow arrangement, a second rotor blade arrangement of the turbomachine, rotating in particular with the rotor, is arranged in the housing. In optional further steps, further guide vane arrangements and rotor blade arrangements, in particular as described above, can be arranged alternately in order to provide a flow arrangement with a predetermined number of stages.

The method described for assembling a flow arrangement enables simplified assembly compared to known methods, because space in the housing can be used in an improved manner by the particular radial insertion and removal of the vane(s) into the receiving opening(s) and at the same time a simplified construction of a Inner ring of the respective vane arrangement and - in particular depending on other structures of the turbomachine - a one-piece design of the housing is made possible.

According to a further aspect, a turbomachine is specified which has at least one guide vane arrangement described herein or which has a guide vane arrangement or flow arrangement assembled according to a method described herein. Such a turbomachine has the advantage that it can be designed and assembled in a simplified manner and at the same time can be produced more cost-effectively.

In general, the disclosure of the described guide vane arrangement also applies to a corresponding method for assembling a guide vane arrangement, flow arrangement or a corresponding flow machine, which comprises one or more guide vane arrangements, and vice versa. The features of the various exemplary aspects and embodiments described above or below can be combined unless explicitly stated otherwise.

Fig. 1

eine schematische Darstellung eines ersten Ausführungsbeispiels einer erfindungsgemäßen Leitschaufelanordnung einer Strömungsmaschine;

Fig. 2

eine schematische Darstellung der Abstützeinrichtung des ersten Ausführungsbeispiels der Leitschaufelanordnung aus Fig. 1;

Fig. 3

eine schematische Darstellung eines zweiten Ausführungsbeispiels einer erfindungsgemäßen Leitschaufelanordnung einer Strömungsmaschine;

Fig. 4

eine schematische Darstellung der Abstützeinrichtung des zweiten beispielhaften Ausführungsbeispiels der Leitschaufelanordnung aus Fig. 3 in einem Schritt eines beispielhaften Montageverfahrens;

Fig. 5

eine schematische Darstellung eines dritten Ausführungsbeispiels einer erfindungsgemäßen Leitschaufelanordnung einer Strömungsmaschine;

Fig. 6

eine schematische Darstellung der Abstützeinrichtung des dritten erfindungsgemäßen Ausführungsbeispiels der Leitschaufelanordnung aus Fig. 5;

Fig. 7

eine schematische Darstellung der beispielhaften Abstützeinrichtung des dritten erfindungsgemäßen Ausführungsbeispiels der Leitschaufelanordnung aus Fig. 5;

Fig. 8

eine schematische Darstellung eines Ablaufdiagramms eines ersten Ausführungsbeispiels eines erfindungsgemäßen Verfahrens zur Montage einer Leitschaufelanordnung einer Strömungsmaschine;

Fig. 9

eine schematische Darstellung eines Ablaufdiagramms eines zweiten Ausführungsbeispiels eines erfindungsgemäßen Verfahrens zur Montage einer Leitschaufelanordnung einer Strömungsmaschine; und

Fig 10a bis Fig. 10f

eine schematische Darstellung eines Ausführungsbeispiels eines erfindungsgemäßen Verfahrens zur Montage einer Strömungsanordnung einer Strömungsmaschine.

Further features, advantages and possible applications of the invention result from the following description in connection with the figures. It shows

1

a schematic representation of a first exemplary embodiment of a guide vane arrangement according to the invention of a turbomachine;

2

a schematic representation of the support device of the first exemplary embodiment of the guide vane arrangement 1 ;

3

a schematic representation of a second exemplary embodiment of a guide vane arrangement according to the invention of a turbomachine;

4

1 shows a schematic representation of the support device of the second exemplary embodiment of the guide vane arrangement 3 in a step of an exemplary assembly method;

figure 5

a schematic representation of a third exemplary embodiment of a guide vane arrangement according to the invention of a turbomachine;

6

a schematic representation of the support device of the third exemplary embodiment of the guide vane arrangement according to the invention figure 5 ;

7

a schematic representation of the exemplary support device of the third exemplary embodiment of the guide vane arrangement according to the invention figure 5 ;

8

a schematic representation of a flow chart of a first exemplary embodiment of a method according to the invention for assembling a guide vane arrangement of a turbomachine;

9

a schematic representation of a flowchart of a second exemplary embodiment of a method according to the invention for assembling a guide vane arrangement of a turbomachine; and

Figures 10a to 10f

a schematic representation of an embodiment of a method according to the invention for assembling a flow arrangement of a turbomachine.

1 shows a guide vane arrangement 10 for a turbomachine, having a plurality of adjustable guide vanes 11, the guide vane platform 12 of which has a guide vane journal 13, which is mounted in a receiving opening 14 of a housing 15 of the turbomachine arranged radially to a rotor axis RA of the turbomachine. An adjusting device 40 is connected to the guide vane journal 13 by means of an adjusting lever 41 in order to rotate the guide vane 11 about its adjustment axis A.

A vane head 16 of the vane 11 has a bearing journal 17 which is mounted in a bearing seat 18 of an inner ring 19 . In the embodiment shown as an example, this inner ring 19 is undivided and extends in a plane perpendicular to the plane of illustration around the rotor 119. The inner ring 19 has a radially outer part 50 of a sealing device 52 on its radially inner surface facing the rotor 119 of the turbomachine , which forms a sealing device 52 with a second radially inner part 51 arranged on the radial peripheral surface on the rotor 119 .

Between the guide vane platform 12 and the housing 15 there is an assembly space 20 in which a first support element 21 and a second support element 22 are arranged and form a support device 30 by means of which the guide vane 11 is supported against the housing 15 . Here, the support elements 21, 22 are set up to center the vane 11 about its adjustment axis A in a bearing bushing 23 of the receiving opening 14. A slide bushing 32 is arranged between the guide vane platform 12 and the support device 30 in order to enable the guide vane 11 to be adjusted.

The mounting space 20 of the exemplary embodiment is delimited in the axial direction of the guide vane journal 13 by the housing 15 and radially to the guide vane journal 13 by a shoulder or projection 151 of the housing 15 extending radially inward along a radial inner side of the housing 15 . The first support element 21 is designed as a hollow cylinder segment, which is arranged radially around the guide vane pivot 13 . The second support element 22 is formed in the embodiment as a half ring, which extends in a plane perpendicular to the plane of the rotor axis RA. A recess 26 (cf. 2 ) formed, which is set up to enclose the vane pin 13 at least partially. Adjacent to the recess 26 , the second support element 22 has a design that is designed to rest against the first support element 21 in order to at least partially enclose the guide vane journal 13 together with the latter or to form a support device 30 .

A fastening element 24, which is designed as a liner element in the exemplary embodiment, is arranged on the housing 15 or pushed into it. The second support element 22 is held in the assembly space 20 with the fastening element 24 in such a way that it locks the first support element 21 in the assembly space 20 . As in 1 is further shown, the second support element 22 has a mounting edge 221 which is intended to interact with the fastening element 24 in order to fix the support device 30 in the mounting space.

2 FIG. 12 shows a section of an exemplary support device 30 of guide vane arrangement 10 of a turbomachine Fig.1 . The first support element 21 of the exemplary embodiment is a hollow cylinder half, the inner diameter of the hollow cylinder being designed to at least partially encompass the (not shown) guide vane journal 13 of a guide vane 11 , in the exemplary embodiment approximately half. The second support element 22 is designed as a half ring, which is set up to be arranged on the circumference of the housing 15 or in the mounting space 20 . A recess 26 is formed in an adapter section 25 on an end face of the second support element 22 and is set up to engage around the guide vane pivot 13 together with the first support element 21 in order to support it.

On both sides of the recess 26, the second support element 22 is set up, in particular in the adapter section 25, to interact with the first support element 21 in order to arrest or support it. The second support element 22 is set up to form a support device 30 with one or more first support elements 21 , in particular adjacent in the circumferential direction, which are each assigned to a guide vane 11 .

This configuration of support elements 21, 22 enables simplified assembly of the guide vane arrangement 10, since the support elements 21, 22 can be easily introduced into the assembly space 20 and positioned there.

3 shows a guide vane arrangement 10 of a turbomachine, having a plurality of adjustable guide vanes 11, the guide vane platform 12 of which has a guide vane journal 13 which is mounted in a receiving opening 14 of a housing 15 of the turbomachine arranged radially to a rotor axis of the turbomachine. A vane head 16 of the vane 11 has a bearing journal 17 which is mounted in a bearing seat 18 of an inner ring 19 . This inner ring 19 is formed in this exemplary embodiment of two half rings, which are arranged coaxially to the axis of rotation of the turbomachine and in the 3 extend in a plane perpendicular to the plane of the drawing. On its radial inner surface facing the rotor 119 of the turbomachine, the inner ring 19 has a radially inner part 50 of a sealing device, which forms a sealing device 52 with a second part 51 arranged radially on the outside of the rotor 119 .

An assembly space 20 is arranged between the guide vane platform 12 and the housing 15, in which a first support element 21, a second support element 22 and a third support element 200 are arranged. The mounting space 20 is delimited axially and radially with respect to the guide vane journal 13 by the housing 15 . in a 4 In the storage situation shown, the support elements 21, 22 can each be arranged in one of two areas 20a, 20b of the assembly space 20 and stored in order to be able to introduce the guide vane platform 12 between them into the assembly space 20. In this embodiment, the areas 20a, 20b are part of the assembly space 20.

The support elements 21, 22 are set up to engage around the guide vane pin 13 and to center the guide vane 11 about its adjustment axis A in a bushing 23 of the receiving opening 14. In the present exemplary embodiment, support elements 21, 22 are each fixed in the housing 15 by means of a bolt 224a, 224b, the bolts 224a, 224b being secured in the exemplary embodiment by means of a respective securing element 225a, 225b.

Together with the third support element 200 (cf. 4 ), the first support element 21 and the second support element 22 form a support device 30, by means of which the guide vane 11 is supported against the housing 15. A slide bushing 32 is arranged between the guide vane platform 12 and the support device 30 in order to enable the guide vane 11 to be adjusted.

figure 4 . FIG. 12 shows a partial schematic representation of an exemplary support device 30 of the exemplary embodiment of the guide vane arrangement 10 3 during an assembly step of a method described herein for assembling a guide vane arrangement 10. A first support element 21 is provided in an area 20a of the assembly space 20 and a second support element 22 in an area 20b of the assembly space 20, in order to be used in a further step of a method described in more detail below to be displaced in the direction of the guide vane pivot 13 in order to support the guide vane 11 against the casing 15. For this purpose, bolts 224a, 224b can be provided, for example, by means of which the support elements 21, 22 can be displaced and locked in particular through fastening openings 226 in the housing 15.

In 4 a section of a guide vane arrangement 10 is shown in one step of a method described in more detail below. A guide vane head 16, not shown, is already arranged on an inner ring 19, also not shown. Two guide vane platforms 12 are shown, which are arranged in an opening 20c of the assembly space 20 formed by the housing 15 .

A third support element 200 is shown below the casing 15 and is adapted to be arranged in the mounting space 20 or in the opening 20c formed by the casing 15 between two adjacent vane platforms 12 (the airfoil of the vanes 11 is not shown). The mounting space 20 can be closed off by a third support element 200 and the guide vane platforms 12 can be supported against one another and against the housing 15 at the same time.

In the exemplary embodiment shown, the third support element 200 has two opposing flanks 203a, 203b, which are set up on the housing 15, especially in the opening 20c. Between the flanks 203a, 203b, the third support element 200 has opposite receiving areas 201a, 201b, which are set up to support one guide vane platform 12 of two adjacent guide vanes 11 in such a way that these can be rotated about their adjustment axis A.

On an upper side, which in an assembled state faces at least one first support element 21 and at least one second support element 22, the third support element 200 has two fixing devices 202a, 202b, which are set up with at least one first support element 21 and at least one second support element 22 cooperate to lock the third support member 200 in the mounting space 20 . In the exemplary embodiment shown, the fixing devices 202a, 202b are designed in such a way that they can be arranged between two first supporting elements 21 and two second supporting elements 22 in each case. The supporting elements 21 and 22 have lateral grooves which are set up to form a positive connection with the respective T-shaped fixing device 202a, 202b. For this purpose, the third support element 200 is arranged in the assembly space 20 such that the grooves of the support elements 21, 22 engage in the fixing device 202a, 202b when the support elements 21, 22 move towards one another in the direction of the guide vane journal 13. In this way, a support device 30 is formed, which supports the guide vane(s) 11 against the housing 15 .

A vane assembly 10 according to the present disclosure may include a variety of, for example, in 1 or 3 shown guide vanes 11, which are arranged in radial alignment on the housing 15, each guide vane 11 being supported by means of a support device 30.

figure 5 shows a third exemplary embodiment of a guide vane arrangement 10 for a turbomachine in a sectional illustration. The design of the guide vane arrangement 10 essentially corresponds to the exemplary embodiments illustrated above 1 and 3 , with the differences shown below.

Between the guide vane platform 12 and the housing 15 there is a mounting space 20 which extends axially to the guide vane trunnion 13 from the housing 15 and radially to the guide vane trunnion 13 is delimited by a projection 151 of the housing 15. A support device 30 designed as a circular arc segment is shown in this mounting space 20 embodied all around, by means of which the guide vanes 11 are supported against the housing 15 . This support device has at least two receiving recesses 31 which are designed to at least partially encompass a guide vane pin 13 in each case in order to support the guide vane 11 against the housing 15 . The support device 30 embodied here as a half ring extends in the circumferential direction in a plane perpendicular to the plane of representation. The U-shaped receiving recess(es) 31 is/are formed on an axis-side flank of the support device 30 and set up to at least partially encompass the guide vane journal(s) 13 . Only one of the receiving recesses 31 of the support device 30 is shown in the illustration; the statements relating to the receiving recess 31 apply correspondingly to the at least one further receiving recess 31 of the support device 30.

The support device 30 or its receiving recess 31 and 13 and a spacer element 33 arranged around the guide vane journal 13 and the guide vane platform 12 are set up to receive the guide vane 11 and to center it about its adjustment axis A in a bushing 23 of the receiving opening 14 . A slide bushing 32 is arranged between guide vane platform 12 and spacer element 33 . In this case, the spacer element 33 is set up to accommodate the guide vane platform 12 and the sliding bush 32 in order to fix them in relation to one another and to enable the guide vane 11 to be adjusted. In the exemplary embodiment shown, the spacer element 33 has a rectangular cross section and an anti-twist device 34 in the form of a chamfer on one edge, so that assembly can be simplified and accidental incorrect assembly can be avoided.

A fastening element 24, here a liner element, is arranged on the housing 15 or pushed into it, by means of which the support device 30 is arrested or fixed in the axial direction.

figure 6 . shows a detail of the vane arrangement 10 of a turbomachine Fig.5 without housing 15 in a partially exploded view. Designed as a circular arc segment support device 30 has a plurality of receiving recesses 31 which in an axial Direction can be arranged around the guide vane journal 13 and into the mounting space 20 or can be inserted between the guide vane journals 13 in order to stabilize the guide vanes 11 .

Spacer elements 33 are arranged around the guide vane journals 13 of the guide vanes 11, having a recess 36 that receives the guide vane journal 13, in particular is arranged centrally, and has a square cross section. The spacer elements 33 are each set up to receive a sliding bush 32 and to position this relative to the guide vane platform 12 and at the same time to support the guide vane platform 12 in such a way that it can be rotated in order to enable the guide vane 11 to be adjusted about the adjustment axis A. Due to the square cross section, the spacer elements 33 can be arranged in the assembly space 20 and delimit it, the spacer elements 33 being fixed, for example, by means of a fixing section 35 arranged on the support device 30, in particular in the axial direction of the turbomachine. Thus, the spacer elements 33 can, on the one hand, support the guide vane 11 relative to the housing 15 and, on the other hand, reduce a relative movement of the guide vanes 11 .

7 12 shows an illustration of an exemplary support device 30 of the guide vane arrangement 10 from FIG figure 5 or. 6 . The support device 30 is designed as a semicircular segment or half ring and has a large number of U-shaped receiving recesses 31 which are each assigned to a guide vane journal 13 and are set up to receive this and thus to support it against the housing 15 .

Due to the design as a half-ring, a mounting space 20 formed all around can be filled all the way around by means of two such half-annular support devices 30 in order to support the guide vanes 11 . Because only two support devices 30 are provided in such an exemplary embodiment, the number of components to be assembled and thus the assembly time for the guide vanes 11 and the inner ring 19 can be reduced.

A width B of the receiving recess 31 can essentially match a diameter of the guide vane journal 13 and/or a radius R of a hole in the receiving recess 31 The hollow (semi)cylinder formed on the inside can essentially correspond to a radius of the guide vane journal 13 in order to be able to accommodate, store and support it. A depth T of the receiving recess 31 is in particular greater than a diameter of the vane journal 13, so that the support device 30 can protrude radially beyond the vane journal 13 in order to improve a stabilizing effect. On an axle-side flank of the support device 30, the receiving recess 31 is designed to be open so that it can be pushed onto the guide vane pivot 13 and thus support it.

8 FIG. 1 shows a flowchart of a first exemplary method 100 for assembling a guide vane arrangement 10 of a turbomachine.

In a first step 101, a guide vane journal 13 arranged on a guide vane platform 12 of a guide vane 11 is inserted into a receiving opening 14 of a housing 15 arranged radially to a rotor axis of the turbomachine, in particular until the guide vane platform 12 strikes the housing 15. In a further step 102, an inner ring 19 is provided on a rotor 119 of the turbomachine. In a further step 103, the guide vane journal 13 is guided out of the receiving opening 14 in the radial direction to a rotor axis of the turbomachine until a bearing journal 17 arranged on a guide vane head 16 of the guide vane 11 engages in a bearing seat 18 arranged on the inner ring 19. The guide vane platform 12 forms an assembly space 20 with the housing 15 .

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

In a further step 106, the guide vane pivot 13 is connected to an adjusting device 40, in particular by means of an adjusting lever 41, in order to be able to adjust the guide vane 11 about its adjustment axis A.

9 FIG. 1 shows a flowchart of a second exemplary method 100 for assembling a guide vane arrangement 10 of a turbomachine.

In a first step 101, a guide vane journal 13 arranged on a guide vane platform 12 of a guide vane 11 is inserted into a receiving opening 14 of a housing 15 arranged radially to a rotor axis of the turbomachine, in particular until the guide vane platform 12 abuts the housing 15. In an optional step 107, a support element 32 can be arranged around the guide vane journal 13 or the guide vane platform 12 or provided there beforehand.

In a step 102 an inner ring 19 is provided on a rotor 119 of the turbomachine and in a further step 103 the guide vane journal 13 is guided out of the receiving opening 14 radially to a rotor axis of the turbomachine until a bearing journal 17 arranged on a guide vane head 16 of the guide vane 11 in engages a bearing seat 18 arranged on the inner ring 19 , the guide vane platform 12 forming an assembly space 20 with the housing 15 .

In a step 104 , a support device 30 is arranged in the assembly space 20 in order to support the guide vane 11 with respect to the housing 15 . In a further step e, the guide vane pivot 13 is connected to an adjusting device 40, in particular by means of an adjusting lever 41, in order to be able to adjust the guide vane 11 about its adjustment axis A. In a further step 105, the support device 30 is fixed or locked, in particular by means of a fastening element 24.

Figures 10a to 10f 12 show a schematic representation of steps of an exemplary embodiment of a method 300 for assembling a flow arrangement 310 of a turbomachine. Figure 10a shows a step of providing a housing 15. Figure 10b shows the placement of a first rotor blade arrangement 311, having a first rotor section 312 in the casing 15. Figure 10c shows the mounting of a first vane assembly 10 according to a method 100 described here in the housing 15. Here, a divided or undivided inner ring 19 is introduced into the available space of the turbomachine, whereupon the guide vanes 11 of the Guide vane assembly 10 can be arranged on this. Compared to known methods, the proposed method can dispense with the assembly of several inner ring components, which simplifies the assembly of the flow arrangement 310.

Figure 10d Figure 12 shows the placement of a second blade assembly 313 having a second rotor portion 314 in casing 15 and Figure 10e shows the mounting of a second guide vane arrangement 10 according to the proposed method 100 in the housing 15. Fig. 10f shows the arrangement of a third rotor blade arrangement 315, which has a second rotor section 316, in the housing 15.

REFERENCE LIST

10

guide vane arrangement

11

vane

12

vane platform

13

vane pivot

14

intake opening

15

Housing

16

vane head

17

bearing journal

18

bearing seat

19

inner ring

20

assembly room

20a, 20b

area of the assembly room

20c

Opening of the assembly room

21

first support element

22

second support element

23

Rifle

24

fastener

25

adapter section

26

recess

30

support device

31

recording recess

32

sliding bush

33

spacer element

34

anti-rotation device

35

fixing section

36

recess

40

adjusting device

41

adjustment lever

50, 51

Part of a sealing device

52

sealing device

100

Proceedings

101 - 107

process steps

119

rotor

151

head Start

200

third support element

201a, 201b

recording area

202a, 202b

fixing device

203a, 203b

flank

221

edge

224a, 224b

fastener

225a, 225b

fuse element

300

Proceedings

310

flow arrangement

311

first blade assembly

312

first rotor section

313

second blade assembly

314

second rotor section

315

third blade assembly

316

third rotor section

A

adjustment axis

RA

rotor axis

B

Width of the recording recess

R

Radius of the recording recess

T

Depth of the recording recess

Claims (15)

Guide vane arrangement (10) of a turbomachine, having a plurality of adjustable guide vanes (11), the guide vane platform (12) of which has a guide vane journal (13) mounted in a receiving opening (14) of a housing (15) of the turbomachine, with a guide vane head (16) of the guide vane ( 11) has a bearing journal (17) which is mounted on an inner ring (19) arranged on a rotor (119) of the turbomachine and wherein an assembly space (20) is formed between the housing (15) and the guide vane platform (12), in which a support device (30) is arranged, which supports the vane (11) against the housing (15). Guide vane arrangement (10) according to one of the preceding claims, wherein the support device (30) is designed to center an adjustment axis (A) of the guide vane (11) in the receiving opening (14). Guide vane arrangement (10) according to one of the preceding claims, wherein the support device (30) has at least one first support element (21) and at least one second support element (22). Guide vane arrangement (10) according to one of the preceding claims, in which the second support element (22) is fastened by means of a fastening element (24) arranged on the housing (15). Guide vane arrangement (10) according to one of the preceding claims, wherein the first support element (21) is locked by means of the second support element (22). Guide vane arrangement (10) according to one of the preceding claims, wherein the first support element (21) and the second support element (22) are each locked by means of a fastening element (224a, 224b). Guide vane arrangement (10) according to one of claims 1 or 2, wherein the support device (30) is designed as a circular arc segment and has at least two receiving recesses (31), which are each set up to at least partially receive a guide vane journal (13). Guide vane arrangement (10) according to Claim 7, in which the support device (30) is designed as a half ring. Guide vane arrangement (10) according to claim 7 or 8, wherein the receiving recess (31) is formed substantially U-shaped. Guide vane arrangement (10) according to one of the preceding claims, wherein the support device (30) has at least one spacer element (33), in particular designed with a substantially rectangular cross section, which is set up to be arranged around the guide vane journal (31). Guide vane arrangement (10) according to claim 10, wherein the spacer element (33) is set up to at least partially accommodate a sliding bush (32). Method (100) for assembling a guide vane arrangement (10) of a turbomachine, comprising the following steps: - guiding (101) of a guide vane journal (13) arranged on a guide vane platform (12) of a guide vane (11) into a receiving opening (14) of a housing (15) arranged radially with respect to a rotor axis of the turbomachine; - Providing (102) an inner ring (19) on a rotor (119) of the turbomachine; - Guide (103) the guide vane journal (13) out of the receiving opening (14) until a bearing journal (17) arranged on a guide vane head (16) of the guide vane (11) engages in a bearing seat (18) arranged on the inner ring (19), the guide vane platform (12) forms an assembly space (20) with the housing; - arranging (104) a support device (30) in the mounting space (20) so that the vane (11) against the housing (15) is supported; and - Locking (105) of the support device (30). Method (100) according to claim 12, wherein when arranging the support device (30), a first support element (21) and a second support element (22) are arranged in the assembly space (20). Method (100) according to one of Claims 19 to 20, a first support element (21) and a second support element (22) being arranged in the assembly space (20) before the guide vane journal (13) is guided into the receiving opening (14) and after guiding the vane out of the receiving opening (14), a third support element (200) is arranged in the assembly space (20). Method for assembling a flow arrangement (310) of a turbomachine, comprising the following steps: - Providing a housing (15); - arranging a first blade assembly (311) in the casing (15); - mounting a first guide vane arrangement (10) according to a method according to at least one of claims 12 to 14 in the housing (15); and - arranging a second blade assembly (313) in the casing (15).

Images