Guide vane assembly of a turbomachine, method for assembling a guide vane assembly of a turbomachine, and turbomachine

Abstract

The invention relates to a guide vane assembly (10) of a turbomachine, a method for assembling a guide vane assembly (10) of a turbomachine, and a turbomachine. The guide vane assembly (10) has several 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. A guide vane head (16) of the guide vane (11) has a bearing journal that is mounted on an inner ring (19) arranged on a rotor (119) of the turbomachine. In the method, a guide vane journal (13) arranged on a guide vane platform (12) of a guide vane (11) is guided into a receiving opening (14) of a housing (15) arranged radially to a rotor axis of the turbomachine, and an inner ring (19) is provided on a rotor (119) of the turbomachine.

Description

[0001] The invention relates to a guide vane arrangement of a turbomachine, comprising several adjustable guide vanes, the guide vane platform of which has a guide vane pin which is mounted in a receiving opening of a housing of the turbomachine, and a method for mounting a guide vane arrangement.

[0002] A turbomachine comprises a compressor, a combustion chamber, and a turbine, arranged in series in the direction of airflow. 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 produced 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.

[0003] Both the compressor and the turbine of a turbomachine typically comprise several stages, each stage having a series of stationary guide vanes and a series of rotating rotor blades. The stationary guide vanes direct the gas flow so that it approaches the rotating rotor blades at a predetermined angle. To adjust the angle of approach, the guide vanes can be adjustable about their longitudinal axis. Such guide vanes are typically mounted at their radially inner end on a stationary inner ring, thus creating spoke-centering of the assembly. This provides one degree of freedom for the inner ring relative to the turbomachine rotor, resulting in a necessary clearance between these components of the turbomachine. The radially outer ends of the adjustable guide vanes are usually rotatably mounted on the turbomachine casing about their radially oriented longitudinal axis.Since several components are typically installed in a confined space on the inner ring, sometimes complex inner ring designs are required, which impair the stability or inherent stiffness of the inner ring and thus also the continuity of a sealing gap in the turbomachine.

[0004] Starting from this, it is an object of the present invention to provide an improved guide vane arrangement for a turbomachine and an improved turbomachine itself. Furthermore, an improved method for assembling a guide vane arrangement and for assembling a flow arrangement for a turbomachine is to be provided. This is achieved according to the invention by the teachings of the independent claims. Advantageous embodiments of the invention are the subject of the dependent claims.

[0005] To solve the problem, a guide vane arrangement for a turbomachine with several adjustable guide vanes is proposed. The guide vane platform of each guide vane has a guide vane journal which is supported in a receiving opening of the turbomachine housing, arranged, in particular, radially to a rotor axis of the turbomachine. A guide vane head of the guide vane has a bearing journal which is supported on an inner ring arranged on a rotor of the turbomachine. Each guide vane is supported against the housing by means of a support device arranged in the receiving opening. The support device has at least one first support element and at least one second support element, wherein the first support element is supported on the housing radially to a rotor axis of the turbomachine within the receiving opening by means of the second support element.

[0006] The support device reduces, and in particular prevents, relative movement of the guide vanes to the housing, especially in a longitudinal direction of the guide vane, and especially of several guide vanes relative to each other. This reduces the load on the inner ring caused by relative movement of the guide vane(s), thereby enabling a simplified design of the inner ring and facilitating assembly of the guide vane assembly.

[0007] The support elements can be designed and / or arranged in the receiving opening 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, each radially enclose the guide vane journal at least partially, and in particular completely.

[0008] The first and second support elements can abut each other. In particular, both support elements are designed to abut the housing or the inner circumference of the receiving opening in the axial and / or circumferential direction to support the guide vane or guide vane journal and / or the guide vane platform. The support elements can be inserted into the receiving opening individually and / or independently of each other, further simplifying the assembly of the guide vane assembly.

[0009] A turbomachine has an axially flowable housing (stator) on which several guide vanes, in particular a plurality of circumferentially adjacent guide vanes, are arranged radially to an axis of rotation of the turbomachine, particularly spoke-centered. In one embodiment of the invention, the housing can also be made in one piece, particularly around its circumference, which allows for more uniform thermal expansion of the housing and thus improved clearance behavior between the rotor and stator.

[0010] The guide vane, which extends radially to an axis of rotation of the turbomachine, has a guide vane head on its side facing the turbomachine's rotor. This head is mounted on the inner ring. The guide vane head has a bearing journal that is received by a bearing seat, arranged circumferentially on the inner ring, and rotatably held within it. The inner ring is designed to coaxially surround the rotor and connect the guide vanes of the guide vane assembly to one another, thereby stabilizing the assembly and ensuring suitable vibration characteristics. A sealing device is arranged on the inner ring to seal a gap formed between the inner ring and the opposing circumferential surfaces on the rotor.In this case, the inner ring can, for example, have 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.

[0011] For adjustment, the guide vane can be connected, in particular at an end of the guide vane journal located on the outside of the housing, to an adjustment mechanism and, in particular, an adjustment lever. By means of the adjustment mechanism, the guide vane can be rotated about its adjustment axis, in particular at a predetermined angle.

[0012] 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: Arranging a first support element around a guide vane journal located on a guide vane platform; guiding the guide vane journal into a receiving opening in a housing arranged radially 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 located on a guide vane head engages in a bearing seat located on the inner ring; arranging a second support element in the receiving opening so that the guide vane is supported against the housing in the radial direction of the turbomachine.

[0013] By guiding the guide vane radially within the receiving opening, the assembly of the guide vane assembly is simplified, allowing for better utilization of the installation space in the turbomachine and a simplified design of the inner ring. Furthermore, the proposed method also makes it possible to arrange the guide vane assembly in a one-piece housing, resulting in a lighter and more cost-effective turbomachine.

[0014] Since the guide vane assembly is arranged rotationally symmetrically to the rotor's axis of rotation, the guide vanes can be mounted radially around the rotor on the inner ring. 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 assembly according to the invention, this inner ring can, for example, be designed as a closed, particularly one-piece, ring or, for example, be composed of two half-rings, thereby reducing the number of components to be mounted. In particular, the proposed method enables a reduction in the complexity of the inner ring's design and thus also more cost-effective manufacturing and assembly of the inner ring as well as other components of the turbomachine.

[0015] 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 assembly can exhibit sufficient stability to simplify the construction of the inner ring. It is proposed to use each receiving opening to individually support its respective guide vane within it.

[0016] The receiving opening extends continuously from an inner circumference of the housing to an outer circumference of the turbomachine housing. Each receiving opening can be rotationally symmetrical about a radial of the turbomachine and bounded by the turbomachine housing. The support device can be designed to essentially completely fill the receiving opening, or a space between the guide vane journal and the receiving opening, at least partially or in sections, in order to support the guide vane. In particular, the support device is configured to at least partially encompass the guide vane journal, especially axially, in order to support the guide vane, particularly in the axial direction of the guide vane journal. In this way, the guide vane is supported with virtually no play relative to the housing.The support device is specifically designed to at least partially rest against the housing radially to the guide vane journal, in order to enable force to be transmitted in the radial direction of the guide vane journal into the housing via the support device.

[0017] The proposed guide vane arrangement, or rather the proposed method for mounting a guide vane arrangement, allows for the utilization of a degree of freedom created by the receiving opening in the housing when mounting the guide vanes to the inner ring. This improves the provision and accessibility of components, particularly the guide vane arrangement. This also simplifies the design and assembly of the inner ring. Furthermore, the proposed guide vane arrangement and its simplified assembly enable the housing and / or inner ring of the turbomachine to be designed as single, undivided components. The additional elimination of connecting components for the housing and / or inner ring also results in a weight reduction and a generally more cost-effective design of the turbomachine.

[0018] In one embodiment of the guide vane arrangement, the inner ring is formed in one piece or segmented. A one-piece inner ring as defined in the disclosure is designed as a ring that completely surrounds the rotor and can be slid axially around the rotor of the turbomachine. In particular, the inner ring has a number of bearing seats, especially radially oriented to the turbomachine, on its circumferential side, which are each configured to receive a bearing journal of a guide vane.

[0019] In one embodiment of the guide vane assembly, the inner ring can also be designed as a semi-ring. A semi-ring, as defined in 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° about the inner and / or outer diameter. In particular, the inner ring of the guide vane assembly is formed from two semi-rings that complement each other to form a circumferential ring, which is designed to completely enclose the rotor coaxially. Such a design of the inner ring can increase the stability of the inner ring and / or the guide vane assembly, thereby also stabilizing and thus improving the sealing of a circumferential sealing gap of the turbomachine.

[0020] In one embodiment of the guide vane assembly, the housing is formed as a single, continuous piece. This improves the airtightness of the housing and thus of the turbomachine. Furthermore, the additional material of the flange surfaces results in uneven thermal behavior around the circumference of the housing, which can adversely affect the radial gaps between the rotor and stator. In addition, a one-piece housing has a simpler design, making it more cost-effective to manufacture, especially since fasteners such as nuts and bolts required to join multiple housing parts are no longer necessary. In other embodiments, the housing can be assembled from two semi-circular housing parts.

[0021] 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 configured to provide the guide vane with axial and / or circumferential support for the turbomachine, in addition to radial support, particularly relative to its housing. Centering the guide vanes can also reduce wear on the guide vane journal.

[0022] In one embodiment of the guide vane assembly, the receiving opening is circular at its radially inner end region and has a diameter that essentially corresponds to the diameter of the guide vane platform. The guide vane platform has a substantially circular outer contour, particularly perpendicular to an adjustment axis of the guide vane, to allow rotation about the adjustment axis. This allows the guide vane platform to be rotatably received and held in the housing or receiving opening, while simultaneously providing radial support for the guide vane platform. Furthermore, the proposed design, which includes a support device in the receiving opening or receiving opening, allows for...between the guide vane journal and the housing, which is arranged in particular around an end of a guide vane journal facing the guide vane platform, improves the vibration resistance of the guide vane(s) and thus also of the guide vane assembly.

[0023] In some embodiments, the receiving opening can have at least two different diameters in its radial direction relative to the turbomachine, with a radially outer diameter being smaller than a radially inner diameter. These different diameters can form a stop for the guide vane journal, the guide vane platform, and / or a support element attached thereto, thus blocking the guide vane's radial outward movement during assembly.

[0024] In one embodiment of the guide vane arrangement, at least two adjacent receiving openings are connected to each other at their radially inner region by means of a connecting opening such that the guide vane can be received section by section, particularly temporarily, in the connecting opening. This allows the guide vane to be shifted further towards the housing during assembly, in order to increase the available installation space for arranging the inner ring. When inserted into the receiving opening, the respective guide vane can be rotated or positioned such that its blade is aligned in a circumferential direction of the turbomachine in order to be received in the connecting opening.

[0025] In one embodiment of the guide vane assembly, the support device is configured to mount at least one pivot bearing bushing for the guide vane or guide vane journal. A pivot bearing bushing can be, for example, a radial bearing, a transverse bearing, a radial sliding bearing, a sliding bushing, and / or a flanged bushing, which in particular restricts two degrees of freedom in the radial direction of its circular cross-section. In some embodiments, a bearing bushing is arranged between the receiving opening formed in the housing and the guide vane journal, which rotatably mounts the guide vane journal, in particular about an axis of the guide vane journal, thus enabling adjustment of the guide vane.Furthermore, an axially acting sliding bushing can be arranged between the guide vane platform and the support device, which is designed to allow a rotational movement of the guide vane, in particular the guide vane platform, relative to the support device. The rotary bearing bushing can form or be a component of the support device, in particular the first and / or second support element.

[0026] In one embodiment of the guide vane assembly, the support device is locked to the receiving opening of the housing by means of a locking element. In some embodiments, the receiving opening can have a receiving groove for the locking element, particularly in its region facing away from the guide vane platform in the longitudinal direction. The locking element can, for example, form the second support element and / or be part of the support device. In particular, the first support element and / or the support device is locked or fixed by means of the locking element in such a way that it is firmly arranged in the receiving opening in the radial direction of the turbomachine, especially during operation. For example, a locking element designed as a retaining ring can be arranged on or in a suitably designed groove or a wall of the receiving opening, thus securing the first support element or the first support element.Hold the support device in position. The locking element and the receiving opening or its groove can, for example, be designed to correspond to each other, so that a positive-locking connection between the locking element and the receiving opening can be formed. This eliminates the need for additional fixing, especially of a first support element or the support device, thus simplifying the assembly of the guide vane assembly.

[0027] In one embodiment of the guide vane assembly, the guide vane journal has a mounting groove on its side facing away from the guide vane platform. This mounting groove can be configured to provide a point of engagement for a tool, allowing the guide vane journal or guide vane to be moved within the receiving opening by means of the tool. This can, for example, simplify the disassembly of the guide vane assembly.

[0028] In one embodiment of the guide vane assembly, the second support element is a sliding bushing for the guide vane journal. The sliding bushing can be configured to allow the guide vane journal to rotate about an axis of the journal relative to the receiving opening formed in the housing, thus enabling adjustment of the guide vane. The sliding bushing can be arranged in the receiving opening and, in particular, secured to or within the receiving opening of the housing by means of a locking element, such that it supports the first support element in a radial direction. The sliding bushing can extend at least partially or section by section into a region of the receiving opening with an enlarged diameter.

[0029] In one embodiment, the first support element comprises at least one spacer element configured to support at least one flanged bushing for the guide vane platform or to support the flanged bushing on the guide vane platform. The spacer element can be configured to be arranged around the guide vane journal and / or around the guide vane platform. The spacer element can be configured to at least partially, and in particular completely, encompass the guide vane journal and, in particular, to support it against an enlarged diameter of the receiving opening.

[0030] In one embodiment, the spacer element is designed to at least partially accommodate a sliding bushing or pressure plate, in particular to fix it against the guide vane platform and / or to allow adjustment of the guide vane around the adjustment axis or the guide vane journal. This fastening of the pressure plate reduces wear.

[0031] In one embodiment of the guide vane assembly, the first support element is a sleeve element configured to at least partially encompass the guide vane journal. The sleeve element can be configured to rotatably support the guide vane journal relative to the receiving opening formed in the housing, particularly by means of at least one rotary bearing bushing or sliding bushing arranged in the sleeve element, about an axis of the guide vane journal. The sleeve element can be arranged in the receiving opening and, in particular, locked to or in the receiving opening of the housing by means of a locking element. The sleeve element can support the guide vane platform and / or a flanged bushing arranged thereon in a direction radial to the turbomachine. This also enables a space-saving and thus weight-saving mounting of the guide vane(s).

[0032] In one embodiment of the guide vane assembly, the sleeve element is configured to support two rotary bearing bushings opposite the guide vane. The sleeve element can have a cross-sectional constriction that spatially separates the two rotary bearing bushings. In particular, such a sleeve element can be configured to support a sliding bushing in the area of ​​the guide vane journal or relative to the guide vane journal, and a flanged bushing in the area of ​​the guide vane platform or relative to the guide vane platform, thus enabling the guide vane to rotate within the receiving opening. In this way, multiple rotary bearings can also be positioned, thereby improving the stability of the guide vane and, consequently, the guide vane assembly.

[0033] In one embodiment of the guide vane arrangement, a plurality of guide vanes can be arranged radially, in particular circumferentially, on the housing, wherein each guide vane can be supported against the housing by means of a support device.

[0034] In one embodiment, the guide vane journal can be extracted from the receiving opening using a tool from a radially outer region of the receiving opening. This allows the guide vane journal or guide vane to be moved by the tool, particularly over a predetermined distance, to make assembly more precise and / or faster.

[0035] In one embodiment, the second support element and / or the safety element can be positioned from a radially outer area of ​​the receiving opening. In particular, after the guide vane has been led out of the receiving opening and positioned on the inner ring (bearing journal engages in the bearing seat), a first support element can be inserted into the assembly space and then locked in place by means of a second support element.

[0036] In one embodiment, the method comprises a further step of arranging a locking element to secure the first and / or second support element and / or the support device. The locking element can be inserted into the receiving opening from a radially outer region to be fixed or locked there. The locking element is specifically designed and / or arranged such that the first and / or second support element or the support device is / are fixed in a direction radial to the rotor axis of the turbomachine. The first support element, the second support element, and / or the support device can thus be fixed in position, in particular releasably, to support the guide vane against the housing.

[0037] 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 to a rotor axis of the turbomachine. Here, the guide vane is inserted 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 guide vane journal is then guided into the receiving opening, in particular until the surface of the guide vane platform facing the guide vane journal abuts the housing. The guide vane is arranged in a radially outer position, so that sufficient installation space is available radially within the guide vane to provide an inner ring on the rotor. For example, when guiding the guide vane into or out of the receiving opening, the adjustment axis of the guide vane can be adjusted to the rotor's position.from the receiving opening by an angle, in particular by about 90°, in order to be able to move in particular a blade of the guide vane, in particular temporarily, into the assembly space, thereby increasing the installation space for providing the inner ring.

[0038] Once the inner ring is positioned 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 guide vane's bearing journal engages in a bearing seat located on the circumference of the inner ring and can be secured to it. The adjustment axis is, in particular, a central axis of the guide vane journal and thus also the axis of rotation of the guide vane, about which this guide vane or guide vane blade can be rotated to achieve the desired airflow.

[0039] In one embodiment, the method comprises a further step of connecting the guide vane journal to an adjustment device. The adjustment device is specifically configured to adjust the guide vane about its adjustment axis at a predetermined angle in order to direct a gas flow such that it flows at a preferred angle to an arrangement of rotating impeller blades. The adjustment device can be connected to the guide vane journal by means of an adjustment lever. In particular, the adjustment device is designed to interact with a plurality of further adjustment devices, which are connected to a plurality of guide vanes or guide vane journals of a guide vane arrangement.

[0040] 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; arranging a first impeller blade assembly in the housing; mounting a first guide vane assembly in the housing according to one or more aspects of the procedure described above; and arranging a second impeller blade assembly in the housing.

[0041] A flow arrangement of a turbomachine, in particular a compressor or turbine assembly, typically comprises several stages. Each stage includes a stationary guide vane arrangement and a rotating impeller blade arrangement extending from a rotor hub. In particular, the proposed method provides a housing, especially one- or multi-part, rotationally symmetrical about an axis of rotation of the turbomachine, in which a first impeller blade arrangement is arranged. For example, a plurality of guide vanes are first arranged in and, in particular, on the housing such that each guide vane journal is guided into a receiving opening in the housing, which is arranged, in particular, radially to the rotor axis of the turbomachine.Then, an inner ring is provided, particularly on the rotor, and the guide vane journal of the respective guide vane is guided from the receiving opening towards the axis of rotation of the turbomachine until a bearing journal located on the guide vane head engages in a bearing seat located 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 to support the guide vane(s) against the housing. The support device can then be locked in place. In a further step, the guide vane journal of the respective guide vane can be connected to an adjustment device.

[0042] In a further step of the proposed method for assembling a flow arrangement, a second impeller blade assembly of the turbomachine, in particular one rotating with the rotor, is arranged in the housing. In optional further steps, additional guide vane assemblies and impeller blade assemblies, in particular as described above, can be arranged alternately to provide a flow arrangement with a predetermined number of stages.

[0043] The described method for assembling a flow arrangement enables a simplified assembly compared to known methods, because the installation space in the housing can be better utilized by the radial insertion and removal of the guide vane(s) into the receiving opening(s), and at the same time a simplified construction of an inner ring of the respective guide vane arrangement as well as - particularly depending on other structures of the turbomachine - a one-piece design of the housing is enabled.

[0044] 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 more simply and is also more cost-effective to manufacture.

[0045] 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 corresponding turbomachine comprising 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 expressly stated otherwise.

[0046] The present disclosure further comprises a guide vane arrangement of a turbomachine with multiple guide vanes. The guide vane platform of a guide vane has a guide vane journal which is supported in a receiving opening of a turbomachine housing, arranged in particular radially to a rotor axis of the turbomachine. A guide vane head of the guide vane has a bearing journal which is supported 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 guide vane platform, which supports the guide vane against the housing. The support device has at least one first support element which is designed at least substantially as a ring segment, in particular as a half-ring.

[0047] The mounting space is formed in particular as a continuous, circumferential support element within the housing, allowing the at least one first support element to be inserted into the mounting space in a circumferential direction of the housing or the turbomachine. Specifically, the support device comprises two first support elements, one of which is arranged axially adjacent to the respective guide vane journal of the turbomachine. This provides stable support and bearing of the guide vane journal, and thus of the guide vane, on both sides.

[0048] The support device can include at least one spacer element configured to be arranged around the guide vane journal and / or the guide vane platform. This spacer element can be configured to at least partially, and in particular completely, encompass the guide vane platform and support it against the housing and / or the support device. The guide vane platform has a substantially circular outer contour perpendicular to an adjustment axis of the guide vane to allow rotation about the adjustment axis. Because the spacer element encompasses the respective guide vane platform and can simultaneously be positioned or supported against the housing and / or the support device, forces can be absorbed by the guide vanes.

[0049] The spacer element can be designed to at least partially accommodate a sliding bushing or pressure plate, in particular to fix it against the guide vane platform and / or to allow adjustment of the guide vane around the adjustment axis or guide vane journal. This securing of the pressure plate reduces wear.

[0050] The spacer element can have a substantially rectangular cross-section. In particular, two adjacent spacer elements are arranged to support each other, especially in the circumferential direction of the turbomachine, in order to support and / or space two adjacent guide vane platforms from each other. The spacer element can have a substantially rectangular or square cross-section to allow it to be positioned between the support device, housing, and guide vane platform in the assembly space, and to support the mutual support of two spacer elements, especially in the circumferential direction of the turbomachine, and in particular to cover or delimit the assembly space.For example, the spacer element can rest against a projection of the housing, which is arranged particularly radially to the guide vane journal, and be held in position by the support device and / or a fixing section of the support device and / or the guide vane platform.

[0051] Furthermore, a method for assembling such a guide vane arrangement of a turbomachine is specified, comprising the following steps: Guiding a guide vane shaft arranged on a guide vane platform into a receiving opening of a housing arranged radially 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 a bearing arranged on the inner ring, wherein the guide vane platform and the housing form a mounting space; arranging a support device in the mounting space so that the guide vane is supported against the housing, wherein at least a first support element of the support device is inserted into the mounting space in a circumferential direction of the turbomachine or the housing; and locking the support device.

[0052] In this case, the housing is designed in at least two parts, so that the housing can be assembled after the insertion of the first support device(s), which are designed in particular as a semi-ring. This simplifies the assembly of the guide vane assembly, while also allowing for better use of the installation space in the turbomachine and a simplified design of the inner ring.

[0053] Further features, advantages and possible applications of the invention will become apparent from the following description in conjunction with the figures. It shows Fig. 1 a schematic representation of a first embodiment of a guide vane arrangement of a turbomachine according to the invention; Fig. 2 a schematic representation of two further embodiments of a guide vane arrangement of a turbomachine according to the invention; Fig. 3 a schematic representation of a guide vane arrangement of a turbomachine; Fig. 4 a schematic representation of a flow diagram of a first embodiment of a method according to the invention for assembling a guide vane arrangement of a turbomachine; Figs. 5a to 5g schematic representations of a sequence of the first embodiment of a method according to the invention for assembling a guide vane arrangement of a turbomachine. Fig. 4 Fig. 6 shows a schematic representation of a flowchart of an embodiment of a method for assembling a guide vane arrangement of a turbomachine. Fig. 3 ; Figs. 7a to 7b schematic representations of a sequence of the procedure for assembling a guide vane arrangement of a turbomachine made of Fig. 6 ; Fig. 8a to Fig. 8 fine schematic representation of an embodiment of a method according to the invention for assembling a flow arrangement of a turbomachine.

[0054] Fig. 1 Figure 1 shows a first embodiment of a guide vane arrangement 10 for a turbomachine, comprising several 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 adjustment device 60 is connected to the guide vane journal 13 by means of an adjustment lever 61 in order to rotate the guide vane 11 about its adjustment axis A.

[0055] A guide vane head 16 of the guide vane 11 has a bearing journal 17, which is supported in a bearing seat 18 of an inner ring 19. In the exemplary embodiment shown, this inner ring 19 is formed as a single unit and extends around the rotor 119 in a plane perpendicular to the plane of representation. The inner ring 19 has, on its radially inner surface facing the rotor 119 of the turbomachine, a radially outer part 50 of a sealing device 52, which forms a sealing device 52 with a second radially inner part 51 arranged on the radial circumferential surface of the rotor 119.

[0056] Between the guide vane platform 12 and the housing 15, a first support element 21 and a second support element 22 are arranged in the receiving opening 14, forming a support device 20 by means of which the guide vane 11 is supported against the housing 15. The support elements 21, 22 and the support device 20 are configured to center the guide vane 11 about its adjustment axis A in the receiving opening 14.

[0057] The receiving opening 14 has a diameter at its radially inner end region that essentially corresponds to the diameter of the guide vane platform 12, this enlarged section of the receiving opening 14 being bounded by a shoulder 114. The first support element 21 is arranged in this enlarged section of the receiving opening 14 and is supported in the radial direction of the turbomachine by means of the second support element 22.

[0058] The first support element 21 has a spacer element 24, which is designed as a hollow cylinder arranged radially around the guide vane journal 13 and supports a flanged bushing 41 against the guide vane platform 12. The second support element 22 is designed as a sliding bushing arranged in the receiving opening 14 to allow adjustment of the guide vane 11. The second support element 22, and thus also the first support element 21, is secured radially against the receiving opening by means of a locking element 23, designed here as a retaining ring. For this purpose, the receiving opening 14 has a recess 124 in which the locking element 23 is engaged.

[0059] Fig. 2 Figure 1 shows two further embodiments of guide vane arrangements 10 for a turbomachine, with a second embodiment shown on the left and a third embodiment of a guide vane arrangement 10 described herein shown on the right. Both guide vane arrangements 10 essentially correspond to the one described in Figure 1. Fig. 1 The illustrated guide vane arrangement 10, the differences of which will be discussed below. First, the second embodiment shown on the left will be described:

[0060] In the embodiment shown on the left, the first support element 21 is designed as a sleeve element, which is configured to at least partially encompass the guide vane journal 13. The sleeve element 21 is arranged in the receiving opening 14 between the housing 15 and the guide vane journal 13 and is configured to support two rotary bearing bushings 41, 42 relative to the guide vane 11. The sleeve element 21 has an enlarged receiving cross-section at its radially outer end, in which a sliding bushing 42 is arranged to allow rotation of the guide vane 11 about the adjustment axis A. At its radially inner end, the sleeve element 21 has an enlarged receiving cross-section to receive a flanged bushing 41 and position it relative to the guide vane platform 12.The sleeve element 21 has an enlarged outer diameter at its radially inner end, which essentially corresponds to a diameter of the guide vane platform 12, so that the stop 114 formed in the receiving opening 14 can serve to prevent the guide vane 11 from being positioned too far radially outwards during assembly.

[0061] In the illustrated embodiment, the second support element 22 is designed as a ring element, which is locked in the receiving opening 114 by means of a locking element 23. This allows the guide vane 11 to be fixed in the radial direction and simultaneously supported in the receiving opening.

[0062] In the right hand in Fig. 2 In the third embodiment shown, the first support element 21 is also designed as a sleeve element and configured to support two rotary bearing bushings 41, 42 opposite the guide vane 11 or the guide vane journal 13 and the guide vane platform 12. In contrast to the second embodiment described above, the receiving opening 14 does not have a shoulder 114, but rather has a constant diameter along its longitudinal extent.

[0063] Fig. 3 Figure 1 shows an example of a guide vane arrangement 10 for a turbomachine. In the illustrated example, a mounting space 30 is arranged between the guide vane platform 12 and the housing 15. A first support element 21 is arranged in this space to form a support device 20 with the second support element 22, by means of which the guide vane 11 is supported against the housing 15. The second support element 22 is designed as a sliding bushing and is arranged in the receiving opening 14 between the guide vane journal 13 and the housing 15, in order to allow the guide vane 11 to be adjusted about its adjustment axis A by means of an adjustment device 60.

[0064] The first support element 21 is designed as a semi-ring and can be inserted in a circumferential direction into the assembly space 30 formed between the shoulder 114 and the guide vane platform 12 in a circumferential direction of the housing 15 or the turbomachine.

[0065] Fig. 4 shows a flowchart of a first exemplary procedure 100 for the assembly of a guide vane arrangement 10 of a turbomachine.

[0066] In a first step 101, a first support element 21 is arranged around a guide vane journal 13 located on a guide vane platform 12 of a guide vane 11. The first support element 21 can be a hollow cylindrical element configured to position a flanged bushing on the guide vane platform 12. This flanged bushing 41 can be arranged around the guide vane journal 13 in a previous step. In another embodiment, the first support element 21 can be designed as a sleeve element in which a flanged bushing 41 and a sliding bushing 42 are arranged in an optional previous step.

[0067] In a second step 102, 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 a further step 103, an inner ring 19 is provided on a rotor 119 of the turbomachine. In a further step 104, the guide vane journal 13 is guided out of the receiving opening 14 in a radial direction to the rotor axis of the turbomachine until a bearing journal 17, arranged on a guide vane tip 16 of the guide vane 11, engages in a bearing seat 18 arranged on the inner ring 19. The guide vane journal 13 can be guided out of the receiving opening 14 by means of a tool from a radially outer region of the receiving opening 14.The guide vane journal 13 is guided into and out of the receiving opening 14 along an adjustment axis A of the guide vane 11 arranged radially to a rotor axis of the turbomachine.

[0068] In a further step 105, a second support element 22 is arranged or placed in the receiving opening 14 such that the guide vane 11 is supported against the housing 15 in the radial direction of the turbomachine. The arrangement of the second support element 22 can be carried out from a radially outer region of the receiving opening.

[0069] In a further optional step, in some embodiments of the proposed method 100, a locking element 23 can be arranged to lock the first and / or second support element 21, 22. In a further step 106, the guide vane journal 13 is connected to an adjusting device 60, in particular by means of an adjusting lever 61, in order to be able to adjust the guide vane 11 about its adjustment axis A.

[0070] Fig. 5a bis 5h The illustrated steps of a procedure 100 for assembling a guide vane arrangement 10 of a turbomachine are shown as examples.

[0071] In a first optional in Fig. 5a In the step shown, a housing 15 for a guide vane assembly 10 of a turbomachine is provided. The housing 15 has several receiving openings 14 that extend radially to an axis of rotation of the turbomachine. Each pair of receiving openings 14 is connected to each other at their radially inner region by means of a connecting opening 115. Fig. 5b shows a representation of step 101 from Fig. 4 , in which a first support element 21 is arranged around a guide vane pin 13 of a guide vane 11. Fig. 5c Figure 1 shows a guide vane 11 in an inserted position, in which the first support element 21 rests against a shoulder 114 formed in the receiving opening 14. A tool 70 can be arranged in the space formed between the guide vane journal 13 and the housing 15 in order to extend the guide vane 11 from the receiving opening 14 by a predetermined distance and to position it on the inner ring.

[0072] Fig. 5d Figure 1 shows another illustration of the guide vane 11 in its fully inserted state. It can be seen that the blades of the guide vanes 11 are oriented in a circumferential direction of the housing 15, so that they can be accommodated in the connecting openings 115, thus providing more space for the arrangement of the inner ring 19 and facilitating assembly.

[0073] Fig. 5e Figure 104 shows the guide vane 11 after it has been formed from the receiving opening 14 by means of the tool 70 in step 104. Here, the first support element 21 is arranged at a distance from the shoulder 114 of the receiving opening 14, and the guide vane platform 12 is flush with a radially inner edge of the housing 15.

[0074] In Fig. 5f Step 105 is shown, wherein a second support element 22 in the form of a sliding bushing is arranged in the receiving opening 14 from a radially outer area. Fig. 5g Figure 1 shows a support device 20 formed by the first and second support elements 21, 22, which is locked by means of a locking element 23 arranged in the receiving opening 14 in order to support the second support element 22 and thus also the first support element 21 in the radial direction of the turbomachine against the housing 15 or to hold it in position. Furthermore, a mounting groove 33 is arranged on the area of ​​the guide vane journal 13 facing away from the guide vane platform 12, which can serve as a point of application for mounting and / or dismounting the guide vane assembly in order to facilitate movement of the guide vane 11 in the receiving opening 14.

[0075] Fig. 6 shows a flowchart of an exemplary procedure 200 for assembling one in the Fig. 7a und 7b Guide vane arrangement 10 of a turbomachine shown.

[0076] In a first step 201, 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 207, a support element 32 and / or a rotary bearing bushing 41, 42 can be arranged around or provided there for the guide vane journal 13 or the guide vane platform 12.

[0077] In step 202, an inner ring 19 is provided on a rotor 119 of the turbomachine, and in a further step 203, the guide vane journal 13 is extended radially from the receiving opening 14 to a rotor axis RA 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, wherein the guide vane platform 12 forms a mounting space 30 with the housing 15, which is formed continuously around or in the circumferential direction in the housing 15.

[0078] In step 204, a first support element 21 is arranged in the assembly space 30 to support the guide vane 11 against the housing 15. The first support element 21 is inserted into the assembly space 30 in a circumferential direction of the housing 15 or the turbomachine. In a further step 205, the guide vane journal 13 is connected to an adjustment device 60, in particular by means of an adjustment lever 61, to allow the guide vane 11 to be adjusted about its adjustment axis A. In a further step 205, the support device 20 is fixed or locked, in particular by means of a fastening element 24.

[0079] The method can include a further step of arranging a spacer element 24 around the guide vane journal 13 or the guide vane platform 12 of the guide vane 11. In this step, a flanged bushing 41 or pressure washer can first be inserted into the spacer element 24 or arranged around the guide vane journal 13 before the spacer element 24 is positioned on the guide vane journal 13 or the guide vane platform 12 and the guide vane journal 13 is inserted into the receiving opening 14 of the housing 15. In this way, the spacer element 24 can be held in place to be brought into a final position in a further step in order to support the guide vane(s) 11 against each other or against the housing 15. In this case, the spacer element 24 is specifically designed to close the receiving opening 14 together with the guide vane platform 12 in a direction facing the rotor 119.The opening of the housing 15, which in particular forms an opening of the mounting space 30, and / or the mounting space 30 can be formed around the entire housing 15 and in particular be closed off around the entire housing 15 by means of the guide vane platforms 12 and spacer elements 24.

[0080] Fig. 7a und 7b show steps of the preceding to Fig. 6 described method 200 for the assembly of a guide vane arrangement 10 of a turbomachine in schematic illustrations.

[0081] In Fig. 7a Figure 203 shows how the assembly space 30 is formed between the guide vane platform 12 or the spacer element 24 surrounding the guide vane platform 12 and the housing 15, wherein this space is formed continuously in the housing 15 in the circumferential direction.

[0082] Fig. 7b Figure 204 illustrates step 204, in which two first support elements 21 are inserted into the assembly space 30 in the circumferential direction of the housing 15. The illustration shows that the two first support elements 21 are arranged on both sides of the turbomachine in the axial direction adjacent to the guide vane journal(s) 13 in order to support the guide vane(s).

[0083] Fig 8a bis Fig. 8f show a schematic representation of steps of an embodiment of a method 300 for assembling a flow arrangement 310 of a turbomachine. Fig. 8a shows one step in the provisioning of a housing 15. Fig. 8b Figure 1 shows the arrangement of a first rotor blade assembly 311, comprising a first rotor section 312 in the housing 15. Fig. 8c Figure 1 shows the assembly of a first guide vane assembly 10 in the housing 15 according to a method 100 described herein. A split or undivided inner ring 19 is inserted into the available installation space of the turbomachine, after which the guide vanes 11 of the guide vane assembly 10 can be arranged on it. Since the proposed method eliminates the need to assemble multiple inner ring components compared to known methods, the assembly of the flow arrangement 310 is simplified.

[0084] Fig. 8d shows the arrangement of a second rotor blade assembly 313, which has a second rotor section 314, in the housing 15 and Fig. 8e Figure 1 shows the mounting of a second guide vane assembly 10 in the housing 15 according to the proposed method 100. Fig. 8f shows the arrangement of a third rotor blade assembly 315, which has a second rotor section 316, in the housing 15. REFERENCE MARK LIST

[0085] 10 Guide vane assembly 11 Guide vane 12 Guide vane platform 13 Guide vane journal 14 Mounting opening 15 Housing 16 Guide vane head 17 Bearing journal 18 Bearing seat 19 Inner ring 20 Support device 21 First support element 22 Second support element 23 Locking element 24 Spacer element 30 Mounting space 33 Mounting groove 41 Flanged bushing 42 Sliding bushing 50, 51 Part of a sealing device 52 Sealing device 60 Adjustment device 61 Adjustment lever 100 Method 101 - 106 Method steps 114 Recess in mounting opening 115 Connecting opening 119 Rotor 124 Recess 200 Method 201 - 207 Method steps 300 Method 310 Flow arrangement 311 First Rotor blade arrangement 312first rotor section 313second rotor blade arrangement 314second rotor section 315third rotor blade arrangement 316third rotor section Aadjustment axis RARotor axis

Claims

1. A guide vane arrangement (10) of a turbomachine, comprising 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, wherein 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 each guide vane is supported against the housing (15) by means of a respective support device (20) arranged in the receiving opening (14), and wherein the support device (20) has at least one first support element (21) and at least one second support element (22), and the first support element (21) is fixed to the housing by means of the second support element (22) within the receiving opening (14) radially to a rotor axis (RA) of the turbomachine (15) is supported.

2. Guide vane arrangement (10) according to claim 1, wherein the inner ring (19) is formed in one piece or segmented, in particular as a half ring.

3. Guide vane arrangement (10) according to at least one of the preceding claims, wherein the support device (20) is designed to center an adjustment axis (A) of the guide vane (11) in the receiving opening (14).

4. Guide vane arrangement (10) according to at least one of the preceding claims, wherein the receiving opening (14) is circular at its radially inner end region (114) and has a diameter which substantially corresponds to a diameter of the guide vane platform (12).

5. Guide vane arrangement (10) according to at least one of the preceding claims, wherein at least two adjacent receiving openings (14) are connected to one another at their radially inner region by means of a connecting opening (115) such that the guide vane (11) can be received in sections in the connecting opening (115).

6. Guide vane arrangement (10) according to at least one of the preceding claims, wherein the support device (20) is designed to support at least one pivot bearing bush (41, 42) for the guide vane (11).

7. Guide vane arrangement (10) according to at least one of the preceding claims, wherein the support device (20) is locked to the receiving opening (14) of the housing (15) by means of a securing element (23).

8. Guide vane arrangement (10) according to at least one of the preceding claims, wherein the guide vane pin (13) has a mounting groove (33) in its region facing away from the guide vane platform (12).

9. Guide vane arrangement (10) according to at least one of the preceding claims, wherein the second support element (22) is a sliding bushing (42) for the guide vane pin (13).

10. Guide vane arrangement (10) according to at least one of the preceding claims, wherein the first support element (21) has at least one spacer element (24) which is designed to support at least one flange bushing (41) for the guide vane platform (12).

11. Guide vane arrangement (10) according to at least one of claims 1 to 10, wherein the first support element (21) is a sleeve element which is designed to at least partially encompass the guide vane pin (13).

12. Guide vane arrangement (10) according to claim 11, wherein the sleeve element (21) is arranged to support two pivot bearing bushes (41, 42) opposite the guide vane (11) 13. Guide vane arrangement (10) according to claim 11 or 12, wherein the second support element (22) is the securing element (23) according to claim 7.

14. A method (100) for assembling a guide vane arrangement (10) of a turbomachine, comprising the following steps: - arranging (101) a first support element (21) around a guide vane pin (13) arranged on a guide vane platform (12) of a guide vane (11); - guiding (102) the guide vane pin (13) into a receiving opening (14) of a housing (15) arranged radially to a rotor axis of the turbomachine; - providing (103) an inner ring (19) on a rotor (119) of the turbomachine; - guiding (104) the guide vane pin (13) out of the receiving opening (14) until a bearing pin (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); - arranging (105) a second support element (22) in the receiving opening (14) so ​​that the guide vane (11) is supported against the housing (15) in the radial direction of the turbomachine.

15. Turbomachine, comprising at least one guide vane arrangement (10) according to one of claims 1 to 13 and / or at least one guide vane arrangement (10) assembled according to a method (100) of claims 14 to 19 and / or a flow arrangement (310) assembled according to a method (100) according to claim 20 or 21.

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