Method for adapting a turbine device, liner, kit comprising a plurality of liner plates, use, and diffuser

Abstract

The invention relates to a method for adapting a turbine device designed for a first operating parameter range, in particular a load range, to a second operating parameter range, in particular a load range, wherein a turbine device having a diffuser (1) is provided, wherein the diffuser (1) comprises an outer boundary wall (2) and an inner boundary wall (3), between which an annular flow channel (4) is formed, and the diffuser comprises a plurality of struts (5) which connect the outer boundary wall (2) and the inner boundary wall (3) to each other, and wherein a lining (12) is preferably releasably fastened to at least one of the struts (5) in order to obtain at least one adapted strut (13), wherein the lining (12) is designed and arranged in such a way that the at least one adapted strut (3) protrudes at least partially by an outer geometry that is modified compared to at least one original strut (5). The invention further relates to a lining (12) for a support (5) of a diffuser (1) for a turbine system, a set comprising two or more such linings (12) of different configurations, such a lining (12) or the use of such a set of linings (12), and a diffuser (1) for a turbine system.

Description

Technical Field

[0001] The present invention relates to a method for adapting a turbine installation, in particular a gas turbine installation, designed for a first operating parameter range, in particular a load range, to a second operating parameter range, in particular a load range. Furthermore, the present invention relates to a lining plate for a support of a diffuser of a turbine installation, a kit having two or more such lining plates of different designs, the use of such a lining plate or such a kit of lining plates, and a diffuser for a turbine installation. Background Art

[0002] Many power plants with turbine installations are designed, in other words, configured, for a specific operating parameter range. For example, they may be designed for a range extending from operation at high load to operation at full load, for example (optimized) for a range above 75% of the turbine output mass flow, which would be expected at full power under standard environmental conditions (ISO).

[0003] Many power plants with turbine systems are designed with the expectation that they will always operate within the full load range. However, in practice, they deviate from this and operate at partial load. This can be due to various reasons. Changes in the connected power grid, such as those caused by renewable energy, the online or offline operation of other power plants, changes in priorities, etc., are mentioned purely by way of example.

[0004] Power plants, which are distinguished by a design optimized for full-load operation, are particularly designed to achieve particularly good or optimal efficiency at full load, whereas they are often distinguished by poorer performance at part-load operation. In particular, if part-load operation subsequently becomes the dominant operating mode, improving the efficiency for the part-load range can be economically attractive, even if this involves trade-offs, resulting in a reduction in the original full-load efficiency or full-load rated power.

[0005] Of particular interest is a possibility that achieves good performance both within the originally set operating parameter range and also within operating parameter ranges that are subsequently added. Summary of the Invention

[0006] Starting from this, the object of the present invention is to provide a possibility of achieving good efficiency at reasonable cost with a turbine power plant which is designed for a first operating parameter range and which is also intended or required to be used in a second operating parameter range.

[0007] This object is achieved by a method for adapting a turbine arrangement designed for a first operating parameter range, in particular a load range, to a second operating parameter range, in particular a load range, wherein

[0008] - providing a turbine arrangement having a diffuser, wherein the diffuser comprises an outer boundary wall and an inner boundary wall, an annular flow channel being formed between the boundary walls, and the diffuser comprises a plurality of struts connecting the outer boundary wall and the inner boundary wall to one another, and

[0009] - A lining is preferably releasably fastened to at least one of the struts in order to obtain at least one adapted strut, wherein the lining is designed and arranged in such a way that the at least one adapted strut protrudes at least partially in sections by an outer geometry that is modified compared to at least one original strut.

[0010] Furthermore, the object is achieved by a lining plate for a support of a diffuser of a turbine system, in particular a gas turbine system, for carrying out the method according to the invention, and a kit comprising two or more such differently designed lining plates.

[0011] Furthermore, the present invention relates to a diffuser for a turbine device, in particular a gas turbine device, comprising an outer boundary wall and an inner boundary wall, between which an annular flow channel is formed; and a plurality of brackets connecting the outer boundary wall and the inner boundary wall to one another; and a lining plate for carrying out the method according to the invention, which is particularly releasably fastened to one of the brackets, preferably a plurality of lining plates for carrying out the method according to the invention, each of which lining plates is particularly releasably fastened to one of the brackets.

[0012] The invention also relates to the use of a lining plate according to the invention or a set of lining plates according to the invention when carrying out the method according to the invention.

[0013] In other words, the basic idea of ​​the present invention is to adapt a turbopower plant to other operating conditions, for example when changing from operation in the full-load range to operation in the partial-load range, by adapting the outer geometry of at least one strut, preferably a plurality of struts, particularly preferably all struts of a diffuser of such a turbopower plant.

[0014] The diffuser of a turbine arrangement can be arranged, for example, in a sufficiently known manner downstream of a turbine stage of the arrangement, for example the last turbine stage, and serve to set desired pressure and temperature conditions of the working medium.

[0015] The external geometry of the diffuser strut influences the flow in or through the diffuser's annular flow channel and can therefore also be referred to as the strut's flow geometry or flow cross section. It has been shown that geometrical changes in the diffuser strut represent a particularly suitable and advantageous measure for responding to changing operating conditions (e.g., a switch from full-load to part-load operation), thereby ensuring improved performance under these changing conditions.

[0016] According to the invention, the external geometry of one or more diffuser struts is adapted by providing at least one, in particular a plurality, and particularly preferably all of the originally existing struts with a lining. It has been shown that the lining allows the flow-influencing external geometry of one or more diffuser struts to be adapted to other operating conditions in a particularly simple manner, even temporarily, as needed.

[0017] The first operating parameter range preferably includes a full-load range or is formed by the full-load range, and the second operating parameter range preferably includes a part-load range or is formed by the part-load range.

[0018] "Full-load operation" can refer to operation at the maximum possible mass flow, particularly at the turbine outlet and / or under standard environmental conditions (ISO). For example, operation from a high mass flow below one or the maximum possible mass flow, particularly at the turbine outlet and / or under standard environmental conditions (ISO), to the maximum possible mass flow, particularly at the turbine outlet and / or under standard environmental conditions (ISO), can also be considered full-load operation. The full-load range can, for example, be a range extending from 75% to 100%, or from 85% to 100%, or from 95% to 100%, of the maximum possible mass flow, particularly at the turbine outlet and / or under standard environmental conditions (ISO). The partial-load range, in particular, does not include the range of full-load operation. For example, the partial-load range can be a range extending from 30% to 60%, or from 65% to 75%, or from 65% to 85%, of the maximum possible mass flow, particularly at the turbine outlet and / or under standard environmental conditions (ISO).

[0019] The first operating parameter range, in particular load range, is different from the second operating parameter range, in particular load range. However, a partial overlap of the two ranges is not excluded.

[0020] The turbine arrangement is designed for a first operating parameter range, in particular a load range, which in particular means or includes that the diffuser is designed for this first operating parameter range, in particular a load range. A diffuser designed for this operating parameter range preferably has a support frame whose outer geometry is adapted to this operating parameter range.

[0021] The or multiple corresponding lining plates provided according to the present invention are preferably designed and arranged in a suitable manner on the or the corresponding original support frame so as to achieve an external geometry adapted to the second operating parameter range. "External geometry adapted to the second operating parameter range" preferably refers to an external geometry that achieves better performance, such as higher power and / or higher efficiency, within the second parameter range than with the original support frame external geometry, i.e., without one or more lining plates. It is possible, but not absolutely necessary, to design the geometric adaptation achieved with the (corresponding) lining plates so as to ensure optimal performance, such as the best possible power and / or the best possible efficiency, within the second operating parameter range. However, an improvement of, for example, a few percent or even less than one percent may be sufficient, and this may depend on the individual application and how much should be achieved or how much should be selected.

[0022] The or, in the case of a plurality of corresponding linings, the lining is preferably designed and preferably arranged on the or the corresponding original strut in such a way that an external geometry is obtained which is better adapted to the turbine output flow in a second operating parameter range, for example, a partial load range, than the external geometry of the or the corresponding original strut. The turbine output flow is in particular the flow emerging from the last turbine stage arranged upstream of the diffuser in the flow direction.

[0023] It can also be provided that the one or more corresponding linings are designed and arranged on the or the corresponding original support in such a way that an external geometry is obtained, which has the following curvature at least in sections, which provides improved tolerances compared to the external geometry of the or the corresponding original support with respect to changing inflow angles and the development of flow separation.

[0024] The approach according to the present invention makes it possible to adapt the flow geometry of the diffuser struts to changing operating conditions with surprisingly simple means, thereby achieving improved performance under changed conditions. For example, a diffuser that exhibits good or optimal performance in full-load operation due to the original flow geometry of its struts can be easily and with little effort adapted to other operating parameter ranges, such as partial-load operation, or optimized for these other operating parameter ranges, for example, within the originally intended operating intervals, by lining one or more, preferably all, of its struts according to the present invention.

[0025] The present invention is also based on the recognition that there is no external support geometry that achieves a uniform performance improvement, such as an increase in efficiency and / or power, across all operating points, or that does not lead to a deterioration at any operating point (compared to another geometry). The present invention overcomes this problem by providing a possibility to vary the geometry with little effort, so that in each operating range, operation can be carried out in a targeted manner using a geometry that exhibits better performance under the corresponding specific conditions.

[0026] For example, if full-load operation is required for several months of the year and partial-load operation is required for several months of the year, operation can be performed without linings, i.e., with the original diffuser-brackets, during the full-load period, and with linings, i.e., with diffuser-brackets adapted according to the present invention, during the partial-load period. This results in good, if possible, optimal performance over the entire time period and within both parameter ranges. An example of this is a power plant in the Middle East that operates at partial load for six months and at full load in the summer. For example, during a brief downtime in the fall, at least one, and preferably all, diffuser-brackets can then be lined according to the present invention to improve partial-load efficiency during the partial-load period. During a brief plant downtime in the spring, one or more linings can be removed to return to the optimal design for full-load operation.

[0027] Another advantage of the solution according to the invention is that it can be handled without moving parts. The production and installation of the lining involves relatively little time and cost expenditure, and the lining, when viewed as a whole, requires little maintenance. It is also economically attractive because no extensive cutting or welding is required. No changes to the structural integrity of the original diffuser are necessary.

[0028] In a particularly preferred embodiment, the lining plate is releasably fastened to at least one original support. The geometric adaptation according to the invention can then be undone in a particularly simple manner in order to return to the original flow geometry of the support and thus to a design for the original operating parameter range, or to switch to a different lining plate for yet another parameter range. This makes it possible, in particular, to operate with high performance in both the first and second operating parameter ranges (and, if necessary, other operating parameter ranges) with particular flexibility.

[0029] The or the corresponding original brace preferably remains intact and functional beneath the or the corresponding lining plate and undergoes only minor modifications, in particular to enable a preferably releasable fastening of the lining plate. With regard to minor modifications of one or more original braces, the provision of anchor points and / or threaded holes and / or inserts provided with an internal thread is mentioned purely as an example.

[0030] The or corresponding lining plate can be constructed not only in one piece but also in multiple pieces, in other words, comprise two or more parts. In the case of a multiple-piece lining plate, it can be provided that the multiple parts of the lining plate are successively, preferably releasably, fastened to the or corresponding original support frame.

[0031] Multi-piece linings have proven successful, for example, in situations where the flow channel defined by the diffuser is characterized by an increasing diameter in the downstream direction. Looking downstream into the diffuser, the brackets, or corresponding brackets, also extend into the overlapping region, into which the lining cannot be positioned by simply moving in the axial direction. For example, a three-piece lining can be used, where the first component is then pushed axially onto the bracket and then moved radially until it now abuts the outer wall of the diffuser. The second lining component can then be correspondingly installed, but in the opposite radial direction until it abuts the inner wall of the diffuser. Finally, the free space remaining between the first and second components can be filled by a third lining component that can be inserted in a form-fitting manner into place.

[0032] If a geometrical change is desired or required not only in the region of the leading edge but also in the region of the trailing edge, a multi-part lining plate can be used, for example, while the region between the lining plates can or should remain unlined. For example, at least one part of the lining plate can then be arranged in the region of the leading edge of the original strut and preferably releasably fastened, and at least one part can be arranged in the region of the trailing edge of the original strut.

[0033] In order to preferably releasably fasten the or the corresponding lining plate, in principle, any means known from the prior art can be used. The or the corresponding lining plate can, for example, be preferably releasably fastened to the (corresponding) bracket by means of bolts and / or screws and / or clips and / or pins and / or latching elements. As explained above, the or the corresponding original bracket can, for example, be provided with inserts or bores into which, for example, threaded bolts can be inserted.

[0034] The or the corresponding covering plate can, for example, have holes through which fastening elements, such as screws and / or bolts, extend in the assembled state.

[0035] Furthermore, it is possible for the or corresponding lining plate to have a varying wall thickness at least in sections. For example, the lining plate can have a wall thickness that decreases toward the end in one or more end regions (where the lining plate rests, or with one or more end regions, such as one or more end regions facing away from the leading edge, against the or corresponding original support 5). This allows for a particularly smooth transition from the lining plate to the original support without edges. It is also possible to provide means for securing the (corresponding) lining plate to the (corresponding) original support in such end regions with reduced wall thickness.

[0036] Using one or more linings provided according to the present invention, it is possible, for example, to vary the angle of the diffuser support or its leading edge, in particular relative to the working medium flowing through the flow channel during operation, in order to better coordinate the turbine output flow in other operating parameter ranges, such as partial load operation. For example, an angular adaptation of 20° or more is possible.

[0037] It is of course also possible to achieve adaptation to more than one changed operating parameter range by the processing according to the invention, for example not only to the second operating parameter range, but also to the third operating parameter range and, if necessary, further operating parameter ranges, for which purpose a plurality of differently constructed linings can then be taken into account in a suitable manner for the or the corresponding original support.

[0038] For example, different degrees of angular adaptation can be achieved. Thus, for example, the (corresponding) first lining plate can be designed and arranged on the (corresponding) original support frame so as to achieve a first angular adaptation of, for example, 20°, in order to achieve good / optimal performance in the second operating parameter range. If the operating parameter range changes again, and more precisely, does not return to the first range (for which the original external geometry is particularly suitable), but returns to the third range, the (corresponding) second lining plate can be designed and arranged on the (corresponding) original support frame so as to achieve another angular adaptation of, for example, 10°.

[0039] Here, at least one kit according to the invention can then be provided or used of a plurality of different lining plates. For example, at least one kit can have three differently designed lining plates designed for the second, third, and fourth operating parameter ranges. Such a kit is expediently provided or used for each diffuser support so that all supports can be equipped with lining plates of the same design.

[0040] Another embodiment is characterized in that the covering plate is designed and arranged on at least one original strut in such a way that it at least partially overlaps the front edge of at least one original strut and at least partially forms the front edge of at least one adapted strut.

[0041] The leading edge formed by the or corresponding lining plate, i.e. the leading edge of the or corresponding adapted strut, is preferably wider than the trailing leading edge of the or corresponding original strut. In particular, the leading edge can have a larger diameter than the trailing leading edge of the (corresponding) original strut.

[0042] If the lining plate does not overlap the leading edge over its entire extent, but only in sections, it can accordingly apply that the leading edge section formed by the lining plate is wider than the trailing leading edge section of the at least one original strut.

[0043] Furthermore, it is preferably applicable that the new front edge of the at least one adapted strut, which is present after the or the corresponding covering plate has been provided, is located in a different position than the front edge of the at least one original strut.

[0044] The at least one original strut can be distinguished by its aerodynamic outer geometry. The lining is suitably designed and arranged on the at least one original strut so that the at least one resulting strut also is distinguished by its aerodynamic outer geometry.

[0045] The or the corresponding original strut can, like the or the corresponding adapted strut, have a pressure side wall and an intake side wall which extend in the axial direction from a leading edge of the or the corresponding original strut to a downstream trailing edge.

[0046] In another advantageous embodiment, it can then be provided that the lining plate is designed and arranged on at least one original strut in such a way that it extends at least within the region of a section of the pressure side wall of the at least one original strut and forms at least one section of the pressure side wall of the at least one adapted strut.

[0047] As an alternative or in addition, the lining plate can be designed and arranged on at least one original strut such that it extends at least within the range of a section of the air intake side wall of the at least one original strut and forms at least one section of the air intake side wall of the at least one adapted strut.

[0048] Furthermore, it has proven particularly expedient if the lining plate is designed and arranged on at least one original strut in such a way that the lining plate or at least one part of the lining plate extends in the axial direction over a larger section of the inlet side wall of the at least one original strut than in the axial direction over the pressure side wall of the at least one original strut. In other words, it has proven particularly advantageous to modify the external geometry on the inlet side wall by means of the lining plate or its part over a larger area than on the pressure side.

[0049] For example, the lining or at least one part of the lining can extend in the axial direction on the intake wall side over a range of at least 30%, in particular at least 40%, preferably at least 50% of the total extension of the bracket in the axial direction, and / or extend in the axial direction on the pressure wall side over a range of at most 20%, in particular at most 10%, preferably at most 5% of the total extension of the bracket in the axial direction.

[0050] Furthermore, it can be provided that the projection of the lining plate, viewed in cross section, is at least partially J-shaped. For example, in the case of a multi-part lining plate, it can also be provided that at least one component of the lining plate, viewed in cross section, is J-shaped. With a lining plate or a component of a lining plate that is J-shaped in cross section, it is particularly easy to achieve a situation in which the lining plate or lining plate component extends to a greater extent on one side of the associated original strut than on the other side.

[0051] The lining plate or at least one component of the lining plate can be produced, for example, from at least one bent sheet, in particular a metal sheet. Conventional methods can be used or have already been used for forming. It is also possible to use a lining plate or at least one lining plate component produced using a generative manufacturing method, such as 3D printing. Combinations of different manufacturing methods for different components or sections of the lining plate are also conceivable.

[0052] Furthermore, it has proven particularly suitable if the lining plate is designed and arranged on at least one original strut such that the lining plate or at least one part of the lining plate extends the intake side wall and / or the pressure side wall forward beyond the leading edge of at least one original strut.

[0053] Alternatively or additionally, it can be provided that the lining plate is designed and arranged on at least one original strut such that the lining plate or at least one part of the lining plate extends the intake side wall and / or the pressure side wall rearwards beyond the trailing edge of at least one original strut.

[0054] Furthermore, it is preferably applicable that the lining plate is designed and arranged on at least one strut such that it extends at least in sections at least substantially parallel to sections of the intake side wall and / or pressure side wall of at least one original strut.

[0055] According to another particularly advantageous embodiment, the lining plate is designed and arranged on at least one original strut such that the angle enclosed between the pressure side wall of at least one adapted strut and the inlet side wall of at least one adapted strut is smaller than the angle enclosed between the pressure side wall of at least one original strut and the inlet side wall of at least one original strut. In other words, in this embodiment, the placement of the or corresponding lining plate results in a flow geometry that is characterized by the pressure side wall and the inlet side wall, which, compared to the geometry of the original strut, are characterized by their parallel orientation.

[0056] In an improved embodiment, the at least one original strut is characterized by an air intake side wall that is curved at least in sections, and the lining is designed and arranged on the at least one original strut in such a way that the at least one adapted strut is characterized by an air intake side wall that is curved at least in sections, wherein the curvature of the air intake side wall of the at least one adapted strut preferably differs at least in sections from the curvature of the air intake side wall of the at least one original strut.

[0057] As an alternative or in addition, it can be provided that the at least one original strut features a pressure side wall that is curved at least in sections, and that the lining is designed and arranged on the at least one original strut in such a way that the at least one adapted strut features a pressure side wall that is curved at least in sections, wherein the curvature of the pressure side wall of the at least one adapted strut preferably differs at least in sections from the curvature of the pressure side wall of the at least one original strut.

[0058] Another advantageous embodiment is characterized by the fact that the lining plate is designed and arranged on at least one original support so that at least one cavity is enclosed between the lining plate and the at least one original support. The flow characteristics depend on the outer contour and not on whether there is solid material or one or more cavities underneath. In the latter case, material can be saved. It should be mentioned purely by way of example that the lining plate comprises one, particularly curved plate or, in the case of a multi-piece design, two or more, particularly curved plates, which only partially rest on the or the corresponding original support, for example with their end regions, and are preferably releasably connected thereto, and thus extend for the most part spaced apart from the or the corresponding original support.

[0059] For the sake of completeness, it should be noted that the originally provided support frame does not necessarily represent a completely material-filled element, but can be hollow at least in sections. The one or more original support frames can, for example, comprise a supporting structure, each of which is provided with a lining to create a closed surface facing the flow channel. In this case, the originally provided lining according to the invention is then preferably releasably fastened to the already existing original lining of the originally provided support frame, in particular for adapting the external geometry. The two linings are then arranged one above the other, at least in sections.

[0060] Alternatively or additionally, it can be provided that the at least one original strut features a cross-section that remains constant in the radial direction, and that the insert is designed and arranged on the at least one original strut such that the at least one adapted strut features a cross-section that varies in the radial direction. Purely by way of example, it should be mentioned that the original strut features a leading edge whose width / diameter remains constant in the radial direction, and that the insert is designed and arranged such that the resulting adapted strut features a leading edge whose width or diameter varies at least partially in sections in the radial direction. For example, an adapted strut can be obtained in which the width or diameter of the leading edge and / or trailing edge increases or also decreases in the radial direction from the outer boundary wall toward the inner boundary wall of the diffuser, at least in sections.

[0061] “The cross section varies in the radial direction” is intended to mean, in particular, that the cross section is not constant over the entire extent in the radial direction, but rather that it varies at least over a section in this direction.

[0062] It is also possible that the at least one original strut features a cross-section that varies in the radial direction, and that the insert is designed and arranged on the at least one original strut such that the resulting at least one adapted strut features a cross-section that remains constant in the radial direction. For example, the original strut can then have a leading edge and / or a trailing edge whose width or diameter increases or also decreases in the radial direction from the outer boundary wall toward the inner boundary wall of the diffuser, at least in sections, and that the constant width of the leading edge and / or trailing edge in the radial direction is achieved by means of the insert.

[0063] The appropriate design and arrangement of the or corresponding lining plates, or in the case of a set of multiple lining plates, lining plates of different designs for different parameter ranges, can be determined, for example, using computer-aided simulations. CFD simulations can be used, for example, to determine the efficiency of a specific or multiple different strut outer geometries. The abbreviation CFD stands for Computational Fluid Dynamics (CFD), which translates to "digital fluid dynamics" in German.

[0064] For example, it is also possible to use a digital twin of the turbine system to be modified or a power plant having such a turbine system. The diffuser struts of this digital twin can then be equipped with linings according to the present invention in a simulation, for example, and the operating characteristics or performance can be checked. In particular, simulations can also be performed for different linings and the results compared.

[0065] In another advantageous embodiment, before the lining is fastened to at least one original support, a suitable time for fastening the lining is determined using a computer-aided simulation, preferably using a digital twin of the turbine system to be adapted. The lining is then preferably placed on the at least one original support at the determined time. This allows for targeted planning of when one or more adaptations according to the invention will be performed.

[0066] In the case of using two or more different liners, in particular at least one set with a plurality of liners (in order to improve the performance within the second, third and, if necessary, further operating parameter ranges), a plan can be created using computer-aided simulations, such as digital twins, as to when which liners are to be placed on or removed from the (corresponding) original support.

[0067] To determine at least one time for lining installation or lining replacement or removal of such a lining, for example, a digital twin of the turbine system to be adapted and historical operating parameters can be provided and the digital twin can be calibrated with the historical operating data.

[0068] The calibrated digital twin can then be adapted so that in its diffuser at least one strut is an adapted strut provided with a lining, preferably all struts are adapted struts. Assumed operating data can be simulated using the correspondingly adapted digital twin.

[0069] An operating point can be found at which better performance, in particular better power and / or efficiency, is achieved with the diffuser having the original strut without a lining, and an operating point can be found at which better performance, in particular better power and / or efficiency is achieved with the diffuser having at least one adapted strut.

[0070] It can be specified how long the downtime required for installing and / or replacing and / or removing one or more linings is, and / or whether there are other downtimes, and / or how long the total downtime permissible per year is. These specifications can be provided as input to the simulation.

[0071] Furthermore, a plurality of case scenarios can be simulated, which are characterized by different times of placement and / or replacement and / or removal of one or more liners, and / or different combinations of one or more different liners, and / or different times of placement and / or replacement and / or removal of one or more liners.

[0072] From the different case scenarios, for example, the case scenario can then be identified in which the best overall performance of the turbine system is achieved, in particular over the entire time period over which the historical operating data extend.

[0073] The placement and / or replacement and / or removal of one or more liners on the diffuser support of the actual turbine installation can then be handled according to the case identified by the simulation. Thus, the simulation can be used to determine the appropriate number and timing, in other words, the planning of downtimes for liner placement, liner replacement, or liner removal, and then to carry out the procedures accordingly. BRIEF DESCRIPTION OF THE DRAWINGS

[0074] With regard to further advantageous embodiments of the invention, reference is made to the dependent claims and to the following description of exemplary embodiments with reference to the drawings.

[0075] In the attached figure:

[0076] Figure 1 A perspective view showing a diffuser of a turbine arrangement,

[0077] Figure 2 Shown Figure 1A cross-sectional view of one of the diffuser supports, wherein the support is provided with a two-piece liner,

[0078] Figure 3 Shown in accordance with Figure 1 A view of a diffuser in which one of the supports is provided with a lining plate,

[0079] Figure 4 Shown Figure 3 A side view of a support frame with a lining plate,

[0080] Figure 5 shows a first section through a support, to which a lining plate having a cross section that varies in the radial direction is fastened,

[0081] Figure 6 Shown Figure 5 The second section of the support and lining,

[0082] Figure 7 shows a first section through a support having a cross section that varies in the radial direction, to which a lining plate is fastened, the cross section of which does not vary in the radial direction,

[0083] Figure 8 Shown Figure 7 The second section of the support and lining,

[0084] Figure 9 shows a side view of a support frame to which a one-piece lining plate is fixed,

[0085] Figure 10 shows a side view of a bracket to which a two-piece liner is secured, with one liner part overlapping the leading edge of the bracket and the other liner part overlapping the trailing edge of the bracket,

[0086] Figure 11 shows a graph with simulation data showing the efficiency improvements associated with the present invention, and

[0087] Figure 12 A purely schematic block diagram is shown with exemplary steps for obtaining a plan for placing and / or replacing and / or removing one or more lining panels on a diffuser support.

[0088] In the figures, identical components are provided with the same reference numerals. DETAILED DESCRIPTION

[0089] Figure 1The diffuser 1 of a turbine arrangement (not shown in detail) of a gas turbine of a gas turbine power plant is shown. The diffuser can be arranged, for example, downstream after the last turbine stage and serves to set desired pressure and temperature conditions of the working medium.

[0090] The diffuser 1 comprises an external and internal dividing wall 2, 3 and a plurality of struts 5, between which an annular flow channel 4 is formed, and the struts connect the external dividing wall 2 and the internal dividing wall 3 to each other. In the embodiment shown, there are a total of five struts 5, which are arranged equidistantly from each other in the circumferential direction. As can be seen, the diffuser 1 comprises an external annular element 6 and an internal annular element 7, which are connected to each other by the struts 5, and the inner wall of the external annular element 6 forms the external dividing wall 2 that defines the annular channel 4 on the outer side, and the outer wall of the internal annular element 7 forms the internal dividing wall 3 that defines the flow channel 4 on the inner side. The internal annular element 7 is cylindrical here and is distinguished by a constant diameter in the axial direction. The external annular element 6 is conical. Specifically, the diameter of the external annular element decreases in the downstream axial direction (in the axial direction). Figure 1 The annular channel 4 also widens in the downstream axial direction accordingly.

[0091] The flow channel 4 defined by the diffuser 1 forms a section of the entire flow channel of the turbine assembly (not shown in detail). To this end, when the diffuser 1 is installed in the turbine assembly, the upstream and downstream components or other elements of the stage are connected in a sufficiently known manner with respect to its two end faces, thereby creating an overall channel.

[0092] The struts 5 each have a pressure side wall 8 and an intake side wall 9 , which extend in the axial direction from a leading edge 10 of the respective strut 5 to a downstream trailing edge 11 .

[0093] The sides 8, 9 and edges 10, 11 of the bracket 5 can also be Figure 2 It is known that the Figure 2 Shown Figure 1 FIG. 5 is a cross-sectional view of a support frame 5 of a diffuser 1. In the example shown, all five supports 5 are identical in structure, so that Figure 2 A cross section of all the struts is shown as an example.

[0094] If it can be Figure 1As is known, the struts 5 are hollow. Furthermore, they are distinguished by their aerodynamic outer geometry. Both the pressure side wall 8 and the intake side wall 9 of the respective struts 5 are not flat but curved. The shape of the struts 5 is designed, in other words, arranged or intended, for a first operating parameter range. This first operating parameter range is defined by the full load range, here the range above 75% of the turbine output mass flow, which would be expected at full power under standard environmental conditions (ISO). This is to be understood purely as an example.

[0095] Many power plants with turbine systems are designed with the expectation that they will always operate in the full load range. However, in practice, they often deviate from this and operate at partial load. This can be due to various reasons. Changes in the connected power grid, such as those caused by renewable energy, the online or offline operation of other power plants, and changes in priorities are mentioned only as examples.

[0096] Power plants, which are distinguished by a design optimized for full-load operation, are typically designed so as to achieve particularly good or optimal performance, such as power and / or efficiency, at full load, whereas they often exhibit poorer performance at part-load operation. Improving efficiency in the part-load range can be economically attractive, especially if part-load operation subsequently becomes the dominant operating mode.

[0097] This is possible by carrying out the exemplary embodiment of the method according to the invention described below for adapting a turbine arrangement designed for a first operating parameter range to a second operating parameter range.

[0098] In the embodiments described herein, a Figure 1 , and in this case, a respective lining plate 12 is detachably fastened to all five struts 5 of the diffuser 1 in order to obtain an adapted strut 13, wherein the lining plates 12 are each designed and arranged on the respective strut 5 in such a way that the respectively produced adapted strut 13 stands out, at least in sections, by a modified outer geometry compared to at least one original strut 5.

[0099] In the embodiment shown, the lining plates 12 used are each constructed in multiple pieces. Each lining plate specifically comprises two lining plate parts 12a, 12b, which are each produced by bending a plate. The two parts 12a, 12b have a J-shaped cross section. This can be achieved in accordance with Figure 2 It should be noted that the support frame 5 is shown from both sides together with the lining plate 12 arranged thereon. Figure 4As can be known, Figure 2 The section shown passes through the upper region of the adapted strut 13 including the lining plate 12 . Figure 2 The upper lining plate component 12a is shown in cross section accordingly. The lower component 12b has the same cross-sectional shape.

[0100] In perspective Figure 3 , the lining plate 12 is also shown, wherein the lining plate is schematically outlined with dashed lines in order to also illustrate the region of the lining plate that is covered by the outer ring element 6. Figure 3 In FIG, a lining 12 is shown as an example for all struts 5 on one of the struts 5. A diffuser with the illustrated lining 12 arranged on the original strut 5 is an embodiment of a diffuser according to the invention.

[0101] The multi-part, here two-part, construction of the lining 12 takes into account the fact that the flow channel 4 widens in the flow direction. In this case, only one component, specifically Figure 4 The upper middle part 12a (whose width increases with increasing distance from the leading edge 14) can be pushed onto the corresponding original bracket in the axial direction in the flow direction at a position spaced apart from the outer boundary wall 2 and then pushed in the radial direction toward the outer boundary wall 2 in order to contact it. Subsequently, the second part 12b (whose width does not change in the axial direction because the inner boundary wall 3 is cylindrical) can be placed by pushing it onto the bracket 5 in the axial direction. Figure 4 In FIG, the flow direction is outlined by arrows.

[0102] Furthermore, the lining plates 12 are each designed and arranged on the respective original struts 5 in such a way that the following applies.

[0103] The respective lining plate 12 overlaps the front edge 10 of the respective original strut 5 over its entire length (see Figure 4 ) and forms the leading edge 14 of the corresponding adapted strut 13. As can be seen, the leading edge 14 formed by the lining plate 12 is wider than the leading edge 10 of the corresponding original strut 5 located behind it.

[0104] The respective lining plate 12 extends the pressure side wall 8 of the respective original strut 5 forwardly beyond the leading edge 10 of the respective original strut 5 . The same applies to the pressure side wall 9 .

[0105] Furthermore, the respective lining plate 12, specifically both its component 12a and its component 12b, extends within the region of the section of the pressure side wall 8 of the respective original strut 5 and forms a section of the pressure side wall 15 of the respective adapted strut 13. In a similar manner, the lining plate extends within the region of the section of the intake side wall 9 of the respective original strut 5 and forms a section of the intake side wall 16 of the respective adapted strut 13, which also applies to the two components 12a, 12b.

[0106] Here, as in Figure 2 and Figure 4 As can be clearly seen in FIG, the respective lining plate 12 (having two parts 12a, 12b) extends in the axial direction over a larger section of the intake-side wall 9 of the respective original strut 5 than in the axial direction over the pressure-side wall 8 of the respective original strut 5. In other words, the lining plate changes the outer geometry over a larger section on the pressure side than on the intake side.

[0107] The adapted bracket 13 including the corresponding lining plate 12 is distinguished by an at least partially curved intake side wall 16, just like the corresponding original bracket 5. The curvature of the intake side wall 16 of the corresponding adapted bracket 13 differs in this case in sections from the curvature of the intake side wall 9 of the corresponding original bracket 5, specifically in Figure 2 In the left half of the embodiment, the lining plate 12 is located in front of the inlet side wall. This also applies to the pressure sides 8, 15 of the original strut 5 and the adapted strut 13, but to a significantly smaller section, as already explained above, so that the lining plate 12 only extends within the area of ​​a significantly smaller section of the pressure side 8. With the help of the corresponding lining plate 12, approximately half of the strut 5, specifically Figure 2 The outer geometry is changed within the first half of the section, whereas this applies only to a relatively small area on the pressure side.

[0108] The angle enclosed between the pressure side wall 15 of the respective adapted strut 13 and the intake side wall 16 of the respective adapted strut 13 is smaller than the angle enclosed between the pressure side wall 8 of the respective original strut 5 and the intake side wall 9 of the respective original strut 5. In other words, the placement of the respective lining plate 12 results in a flow geometry that is characterized by a more parallel orientation of the pressure and intake side walls compared to the geometry of the original strut 5.

[0109] In the example shown, the position of the leading edge and its angle, in particular the leading edge relative to the front side ( Figure 1The angle of the working medium entering the diffuser 1 (on the left in the figure) is also changed by the corresponding lining 12. The curvature on the inlet side of the convex shape is also changed by the corresponding lining 12, and a straight line is achieved from the leading edge 14 of the adapted support 13 to the rear of the original support 5. Figure 2 Smooth transition in the middle right half.

[0110] The respective lining plate 12 is combined with the respective original strut 5 in such a way that an aerodynamic profile is obtained which, viewed from the perspective of the turbine outflow, deviates from the original outer geometry on the inlet side in the front half (in the flow direction) of the respective strut 13 and conforms to it in the rear half.

[0111] Due to the reduced leading edge angle and reduced curvature, the modified profile of the adapted strut 13 is better oriented for the turbine output flow from the last turbine stage during partial load operation. In contrast, the original geometry of the original strut 5 is better adapted to the turbine output flow during full load operation.

[0112] As can be seen, the lining plates 12 extend everywhere outside the original struts 5 , in other words rest only on or against these struts, and the original outer geometry of the original struts 5 remains beneath the respective lining plates 12 .

[0113] If the same Figure 2 As can be clearly seen in FIG, a cavity 17 is enclosed between the respective lining plate 12 and the respective original strut 5, so that the change in the outer geometry can be achieved in a particularly material-saving manner.

[0114] In the end region of the respective lining plate 12, in which or with which it rests on the respective strut 5, here with the end region facing away from the leading edge 14, the wall thickness of the lining plate 12 decreases in order to achieve a particularly smooth, edgeless transition. Means are also provided here for releasably fastening the respective lining plate 12 to the respective original strut 5.

[0115] In the embodiment shown, the lining plates are each detachably fastened to the original struts 5, which has proven to be particularly advantageous. These lining plates can therefore also be easily removed again in order to return to the original outer geometry without lining plates 12 or to replace it with a differently designed lining plate 12. The lining plates 12 are fastened to the original struts 5 by means of screws 18 (see Figure 2), the screws are screwed through openings 19 provided for this purpose in the corresponding lining plates 12 into threaded holes which are made in the original bracket 5 in order to enable detachable fastening of the lining plates 12. It should be noted that the threaded holes made are the only necessary modifications to the original bracket 5, which otherwise remains in its original state.

[0116] In the example shown, each of the lining plates 12 is releasably fastened to the corresponding support 5 by means of twelve screws 18. Figure 4 Twelve holes 19 can be seen in FIG. As can be seen, six holes are provided in each of the two lining plates 12 a, 12 b in their end region facing away from the leading edge 14 .

[0117] In accordance with Figures 2 to 4 In the example of , the original support frame 5 and the lining plate 12 are distinguished by maintaining the same cross section in the radial direction. This is a different option.

[0118] Therefore, as an alternative, it can also be provided that, although the original struts 5 are characterized by a constant cross section in the radial direction, the lining plates are designed and arranged on the respective original struts in such a way that the respective adapted struts 13 are characterized by a cross section that varies in the radial direction. This is purely exemplary. Figure 5 and Figure 6 As shown in Figure 5 and Figure 6 Two cross-sections are shown at different radial positions through such an adapted bracket 13 including a lining plate 12. As can be seen, in the example of FIG, which shows a cross-section closer to the inner boundary wall 3, Figure 6 In the embodiment, the width of the leading edge 14 formed by the liner 12 is greater than that of the leading edge 14 formed by the liner 12. Figure 5 The radial position of the boundary wall 2 closer to the outside is smaller. The width can, for example, increase continuously (or can also decrease) from the inner boundary wall 3 to the outer boundary wall 2. Other geometric shapes are also possible.

[0119] Of course, it is also possible that the original strut 5 is characterized by a cross section that varies in the radial direction. Figure 7 and Figure 8 As shown in Figure 7 and Figure 8 and Figure 5 and Figure 6 Similarly, two sections of the original support frame with the lining plate 12 fixed thereon are shown at different radial positions. Here, the leading edge 10 of the original support frame 5 is at a radial position closer to the outer boundary wall 2 ( Figure 7 ) than in accordance with Figure 8 The radial position of the boundary wall 3 closer to the inside is wider. For example, the width can increase continuously (also can decrease) from the outer boundary wall 2 to the inner boundary wall. Other geometric shapes are also possible.

[0120] If the (respective) original strut 5 has a cross section that varies in the radial direction, it is also possible that the (respective) lining plate is designed and arranged on the (respective) original strut 5 in such a way that the (respective) adapted strut 13 is characterized by a constant cross section in the radial direction, e.g. Figure 7 and Figure 8 Shown exemplarily.

[0121] In addition, as Figure 2 and Figure 4 As an alternative to the two-piece lining shown in FIG, a one-piece lining 12 can also be used for flow channels with variable width or variable diameter. An example of such a lining is shown in FIG. Figure 9 As shown in Figure 9 and Figure 4 Similarly, a view of the pressure side wall 8 is shown on the left, and a view of the intake side wall 9 is shown on the right. If the width or diameter of the flow channel 4 is constant, the inner and outer boundary walls run parallel, and the one-piece lining plate 12 can be pushed in the axial direction onto the (corresponding) original bracket 5.

[0122] If a geometrical change is desired or required not only in the region of the leading edge 10 of the (corresponding) strut 5 but also in the region of the trailing edge 11, a multi-part lining plate 12 can be used as an alternative or in addition. For example, at least one part 12a of the lining plate 12 can then be arranged in the region of the leading edge 10 of the original strut 5, and at least one part 12b can be arranged in the region of the trailing edge 11 of the original strut 5. An example of such an arrangement is shown in FIG. Figure 10 As shown in Figure 10 And with Figure 4 Similarly, a view of the pressure side wall 8 is shown on the left and a view of the intake side wall 9 is shown on the right. Here, the lining part 12a overlaps the leading edge 10 of the original strut 5 and forms the leading edge 14 of the adapted strut 13. The lining 12b overlaps the trailing edge 11 of the original strut 5 and forms the trailing edge 20 of the adapted strut 5. Figure 2 and Figure 4 The difference from the embodiment is that the lining parts 12a and 12b are not against each other, but are arranged on the corresponding support frame 5 at a distance from each other. Figure 10Alternatively to the example shown in , it is of course also possible that the two elements 12a and 12b on the leading and trailing edges themselves are multi-part, for example two-part, as in Figure 2 and Figure 4 Then the lining plate 12 will comprise four parts, for example.

[0123] In particular, in order to cover three or more different operating parameter ranges, one or more sets of differently designed lining plates 12 can be used. If all struts 5 are provided with lining plates, then a number of sets corresponding to the number of struts 5 are expediently provided, each of which has two or more different lining plates 12. Each set of lining plates 12 can, for example, include one as in Figure 2 and Figure 4 and a further lining plate 12 with which an adapted brace 13 can be obtained which only slightly widens the front edge. The second lining plate 12 can protrude, for example, Figure 6 The shape shown is such that, for example, this is the case over the entire extent in the radial direction.

[0124] For all previously described embodiments of the lining 12 according to the invention and sets of such linings, it is true that the flow geometry of the diffuser support 5 can be adapted to the changing operating conditions using surprisingly simple means and thus improved performance can be achieved under the changed conditions.

[0125] Figure 11 By way of example, a diagram is shown with simulation data which demonstrates the efficiency improvement achieved by the process according to the invention. The simulation data were calculated with the aid of CFD (Computational Fluid Dynamics).

[0126] Specifically, in Figure 11 The change in diffuser efficiency compared to the original support 5, that is to say the original external geometry, is plotted on the Y-axis, and the percentage share of the turbine outlet flow at full load (at an ambient temperature of 30° C.) is plotted on the X-axis. Two different curves are shown in the diagram, which include values ​​for two different shapes B1, B2 of the upstream turbine blades. The shape B2 is distinguished by a slightly wider leading edge. It can be seen that for both shapes B1, B2, an efficiency increase of more than 0.5% can be achieved in partial load operation with a full load of specifically 60% of the turbine outlet flow. This advantage decreases approximately linearly up to approximately 80% of the full load of the turbine outlet flow to approximately zero. The curves relate to the flow rate according to Figure 2The geometrical adaptation of the embodiment should however be understood purely as an example. Similar efficiency gains can also be achieved with other original and adapted strut geometries. Figure 11 As can be seen in Figure 2 , the efficiency variation for both blade shapes diverges above 100% of the full-load turbine output flow. The efficiency variation for blade shape B1 remains at approximately -0.05%, while for shape B2 it drops to -0.6% up to 120% of the full-load turbine output flow. This behavior has no impact on the approach according to the present invention, because here the original external geometry is restored for operation above 80% of the full-load turbine output flow, meaning the lining is removed for this operating range.

[0127] It is also possible, in particular using computer-aided simulations, to plan when to place and / or remove and / or replace one or more linings on the diffuser support. Figure 12 The purely exemplary block diagram is used for explanation.

[0128] For example, historical operating parameters of the turbine plant to be adapted can be collected and provided as input values ​​(S1), and the digital twin of the turbine plant to be adapted can be calibrated with the historical operating data (S2). Figure 12 Input values ​​are outlined purely schematically by block elements on the left under the heading “I”, output values ​​are outlined on the right under the heading “O”, and the calculations based on the algorithm are outlined in the middle under the heading “AC”.

[0129] The calibrated digital twin can then be adapted so that in its diffuser 1 at least one strut 5 is an adapted strut 13 provided with a lining 12, preferably all struts are adapted struts 13. Assumed operating data can be simulated with the correspondingly adapted digital twin (S3).

[0130] An operating point can be found at which better performance, in particular better power and / or efficiency, is achieved with the diffuser 1 having the original struts 5 without the lining 12, and an operating point can be found at which better performance, in particular better power and / or efficiency, is achieved with the diffuser 1 having at least one adapted strut 13, preferably all adapted struts 13 (S4).

[0131] It can be specified how long the downtime required for installing and / or replacing and / or removing the one or more linings is, and / or whether there are other downtimes, and / or how long the total permissible downtime is per year (S5). These specifications can be forwarded as input information. It should be noted that this can of course also be done in advance, for example, before calibrating the digital twin (S2).

[0132] Furthermore, a plurality of case scenarios can be simulated, which are characterized by different times of placement and / or replacement and / or removal of one or more liners, and / or different combinations of one or more different liners, and / or different times of placement and / or replacement and / or removal of one or more liners. From the various case scenarios, the case scenario can then be identified in which the best overall performance of the turbine installation is achieved, particularly over the entire time period over which the historical operating data extends (S6).

[0133] As output information from the simulation, a best-case scenario or the associated number and associated timing for placing and / or replacing and / or removing the one or more lining plates ( S7 ), in other words a plan, can be obtained.

[0134] The placement and / or replacement and / or removal of one or more lining panels 12 on the diffuser support 5 of the actual turbine installation can then be carried out according to the case situation determined by the simulation or the plan.

[0135] Although the present invention has been illustrated and described in detail by means of preferred embodiments, the invention is not restricted to the disclosed examples and other variants can be derived therefrom by a person skilled in the art without departing from the scope of protection of the invention.

Claims

1. A method for adapting a turbine arrangement designed for a first operating parameter range to a second operating parameter range, wherein - a turbine arrangement having a diffuser (1) is provided, wherein the diffuser (1) comprises an outer boundary wall (2) and an inner boundary wall (3), between which an annular flow channel (4) is formed, and the diffuser comprises a plurality of struts (5) connecting the outer boundary wall (2) and the inner boundary wall (3) to each other, and - fixing a lining plate (12) to at least one of the struts (5) in order to obtain at least one adapted strut (13), wherein the lining plate (12) is designed and arranged in such a way that the at least one adapted strut (13) protrudes at least partially by a modified outer geometry compared to at least one original strut (5), and - the at least one original strut (5) has a pressure side wall (8) and an intake side wall (9), which extend in the axial direction from a leading edge (10) of the at least one original strut (5) to a downstream trailing edge (11), characterized in that The at least one original strut (5) is characterized by a cross section that remains constant in the radial direction, and the lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that the at least one adapted strut (13) is characterized by a cross section that varies in the radial direction, or The at least one original strut (5) is characterized by a cross section that varies in the radial direction, and the lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that the at least one adapted strut (13) is characterized by a cross section that remains constant in the radial direction.

2. The method according to claim 1, characterized in that The first operating parameter range is a load range.

3. The method according to claim 1, characterized in that The second operating parameter range is a load range.

4. The method according to claim 1, wherein The lining plate (12) is releasably fixed to at least one of the supports (5).

5. The method according to any one of claims 1 to 4, It is characterized by: The lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that the lining plate (12) at least partially overlaps the front edge (10) of the at least one original strut (5) and at least partially forms the front edge (14) of the at least one adapted strut (13).

6. The method according to claim 5, characterized in that The leading edge (14) formed by the lining plate (12) is wider than the leading edge (10) of the at least one original strut (5) located behind it, or the leading edge section formed by the lining plate (12) is wider than the leading edge section of the at least one original strut (5) located behind it.

7. The method according to any one of claims 1 to 4, It is characterized by: The lining plate (12) is constructed and arranged on the at least one original strut (5) in such a way that the lining plate (12) or at least a portion of the lining plate extends the intake side wall (9) and / or the pressure side wall (8) forward beyond the leading edge (10) of the at least one original strut (5), and / or the lining plate (12) is constructed and arranged on the at least one original strut (5) in such a way that the lining plate (12) or at least a portion of the lining plate extends the intake side wall (9) and / or the pressure side wall (8) rearward beyond the trailing edge (11) of the at least one original strut (5).

8. The method according to any one of claims 1 to 4, It is characterized by: The lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that it extends at least within the region of a section of the pressure side wall (8) of the at least one original strut (5) and forms at least one section of the pressure side wall (15) of the at least one adapted strut (13), and / or The lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that it extends at least within the range of a section of the air intake side wall (9) of the at least one original strut (5) and forms at least a section of the air intake side wall (16) of the at least one adapted strut (13).

9. The method according to claim 8, It is characterized by: The lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that the lining plate (12) or at least a part of the lining plate extends in the axial direction within the range of a larger section of the intake side wall (9) of the at least one original strut (5) than in the axial direction within the range of the pressure side wall (8) of the at least one original strut (5).

10. The method according to claim 8, It is characterized by: The lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that the angle enclosed between the pressure side wall (15) of the at least one adapted strut (13) and the intake side wall (16) of the at least one adapted strut (13) is smaller than the angle enclosed between the pressure side wall (8) of the at least one original strut (5) and the intake side wall (9) of the at least one original strut (5).

11. The method according to claim 8, It is characterized by: The at least one original strut (5) projects from the at least partially curved intake side wall (9), and the lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that the at least one adapted strut (13) projects from the at least partially curved intake side wall (16), and / or the at least one original strut (5) projects from the at least partially curved pressure side wall (8), and the lining plate (12) is designed and arranged on the at least one original strut (5) in such a way that the at least one adapted strut (13) projects from the at least partially curved pressure side wall (15).

12. The method according to claim 11, characterized in that The curvature of the air intake side wall (16) of the at least one adapted strut (13) differs at least in sections from the curvature of the air intake side wall (9) of the at least one original strut (5).

13. The method according to claim 11 or 12, characterized in that The curvature of the pressure side wall (15) of the at least one adapted strut (13) differs at least in sections from the curvature of the pressure side wall (8) of the at least one original strut (5).

14. The method according to any one of claims 1 to 4, It is characterized by: The lining plate (12) is designed and arranged on the at least one original brace (5) in such a way that at least one cavity (17) is enclosed between the lining plate (12) and the at least one original brace (5).

15. The method according to any one of claims 1 to 4, It is characterized by: The lining plate (12) is fastened to the at least one original bracket by means of bolts and / or screws (18) and / or clips and / or pins and / or latching elements, and / or the lining plate (12) is designed in multiple parts.

16. The method according to claim 15, characterized in that The plurality of parts (12a, 12b) of the lining plate (12) are fixed successively to the at least one original support frame (5).

17. The method according to claim 16, characterized in that The plurality of parts (12a, 12b) of the lining plate (12) are releasably fastened one after the other to the at least one original support frame (5).

18. The method according to any one of claims 1 to 4, It is characterized by: Before the lining plate (12) is fastened to the at least one original support (5), a suitable time for fastening the lining plate (12) is determined using computer-aided simulation and the lining plate is positioned at this time.

19. The method according to any one of claims 1 to 4, characterized in that Before the lining plate (12) is fastened to the at least one original bracket (5), a suitable time for fastening the lining plate (12) is determined using a digital twin of the turbine system to be adapted and the lining plate is positioned at this time.

20. A lining (12) for a support frame (5) of a diffuser (1) of a turbine installation for carrying out the method according to any one of claims 1 to 19.

21. The lining plate according to claim 20, wherein: The turbine arrangement is a gas turbine arrangement.

22. A set comprising two or more differently configured lining plates (12) according to claim 20 or 21.

23. Use of a lining plate (12) according to claim 20 or 21 or a set of lining plates (12) according to claim 22 when carrying out a method according to any one of claims 1 to 19.

24. A diffuser (1) for a turbine device, said diffuser comprising an outer boundary wall (2) and an inner boundary wall (3) forming an annular flow channel (4) between them; and A plurality of struts (5) connecting the outer boundary wall (2) and the inner boundary wall (3) to one another, and a lining plate (12) for carrying out the method according to any one of claims 1 to 19, the lining plate being fastened to one of the struts (5).

25. The diffuser according to claim 24, characterized in that The turbine arrangement is a gas turbine arrangement.

26. The diffuser according to claim 24 or 25, characterized in that The lining plate (12) is releasably fixed to one of the supports (5).

27. The diffuser according to claim 24 or 25, characterized in that The diffuser (1) comprises a plurality of lining plates (12) for carrying out the method according to any one of claims 1 to 19, wherein each lining plate is fastened to one of the brackets (5).

28. The diffuser according to claim 27, characterized in that One of the lining plates (12) is releasably fastened to one of the struts (5).

Images