A tandem stator vane component for a stator stage and a method of manufacturing a tandem stator vane component

Abstract

The disclosure relates to a tandem guide vane component (204) for a stator stage (201) of a turbomachine compressor (27), comprising a front guide vane (210), a rear guide vane (211), a platform (212), and a mounting structure (213). According to the disclosure, the front guide vane (210) is assigned to a first tandem guide vane pair (205.1), and the rear guide vane (211) is assigned to a second, circumferentially adjacent tandem guide vane pair (205.2), and the front guide vane (210) and rear guide vane (211) are offset from each other circumferentially (RU) such that they do not overlap in the circumferential direction (RU).

Description

[0001] The disclosure relates to a tandem guide vane component for a stator, in particular of a gas turbine engine.

[0002] A tandem guide vane component of the type mentioned above is disclosed, for example, in US 2015 / 027131 A1.

[0003] US 11 338 400 B2, US 2020 / 0392967 A1, US 2024 / 0183279 A1 and DE 102016113568 A1 each describe tandem guide vane components and their manufacturing.

[0004] To achieve a favorable aerodynamic efficiency, parameters such as gap width and blade overlap of the tandem guide vanes are optimized for the respective concept. These parameters can limit the space available for manufacturing and thus also restrict the technically available and feasible manufacturing methods.

[0005] In a first aspect, a tandem guide vane component for a stator stage of a turbomachine compressor is proposed, comprising a front guide vane, a rear guide vane, a platform, and a mounting structure. The front and rear guide vanes are circumferentially offset from each other such that they do not overlap circumferentially. Specifically, the tandem guide vane component comprises exactly one front guide vane and exactly one rear guide vane. In particular, the two guide vanes do not belong to a common tandem guide vane pair. The front guide vane of the tandem guide vane component is associated with a first tandem guide vane pair. The rear guide vane of the tandem guide vane component is circumferentially offset tangentially to the front guide vane such that it is associated with a second, circumferentially adjacent, tandem guide vane pair.

[0006] The disclosure includes the knowledge that this tangential offset of the front and rear guide vanes enables advantageous manufacturing. This is primarily due to the improved accessibility of the surfaces of the front and rear guide vanes, allowing the surfaces to be better accessed by machining tools.

[0007] Tandem guide vane components are subjected to high mechanical and thermal stresses and are therefore advantageously manufactured from durable materials. However, high dimensional accuracy and geometric precision are required, which makes post-processing particularly challenging with the durable materials used.

[0008] The disclosure has recognized, particularly in this context, that it is not necessary for a matching tandem guide vane pair—that is, two guide vanes arranged essentially axially one behind the other and / or two guide vanes considered as an aerodynamically cooperating unit—to be arranged on a common platform. Rather, the proposed tangentially offset arrangement can also achieve an improvement with regard to the mechanical stress during operation of the tandem guide vane component. The zone of increased stress is now advantageously located on the platform within the component and no longer at a transition zone or joint between two tangentially adjacent guide vane pairs.

[0009] In this case, the aerodynamically interacting unit is understood to be the gap formed between the tandem guide vane pair. Due to its nozzle shape, this gap accelerates the flow and thus stabilizes the boundary layer on the trailing guide vane of the tandem guide vane pair, thereby increasing the deflection and deceleration of the flow compared to conventional stators. The gap between a tandem guide vane pair is preferably kept small to achieve the most advantageous aerodynamic properties. In particular, the gap between the two guide vanes of a tandem guide vane pair is smaller than the gap between two circumferentially adjacent tandem guide vane pairs.

[0010] The gap formed between two guide vanes of the tandem guide vane component is preferably larger than the gap between the tandem guide vane pair. In other words, the front guide vane and the rear guide vane of a tandem guide vane component preferably form a gap that is larger than a gap formed between the front guide vane and a rear guide vane of a tandem guide vane pair. The gap between the front guide vane and the rear guide vane of a tandem guide vane pair is preferably defined by the smallest distance between a trailing edge of the front guide vane and a suction side of the rear guide vane. The term "gap" in relation to the tandem guide vane component specifically refers to a circumferential distance between the trailing edge of the front guide vane and a leading edge of the rear guide vane of the tandem guide vane component.

[0011] In a further development, it is provided that the platform forms a boundary contour with a circumferentially adjacent tandem guide vane component. In other words, the platform can have a boundary contour that can be brought into contact with a complementary boundary contour of a platform of a circumferentially adjacent tandem guide vane component. Advantageously, the boundary contour can have a profile that extends at least partially in the circumferential direction. By separating a tandem guide vane pair between two platforms using a boundary contour, improved accuracy in the alignment of the circumferentially adjacent platforms can be achieved. This is advantageous because the alignment of the tandem guide vane pair influences the aerodynamic properties of the stator stage.A first boundary contour of a first tandem guide vane component can be designed such that it can engage with a second boundary contour of a second tandem guide vane component in a positive fit. This positive fit can be effective in the axial and / or circumferential direction. The first boundary contour can include a first positive-fit feature, and the second boundary contour can include a second, complementary positive-fit feature that can engage with the first positive-fit feature. For example, the positive-fit feature can include a contact surface that is arranged and designed to engage with a complementary contact surface of an adjacent boundary contour, thereby preventing relative movement between the adjacent boundary contours, particularly in the axial direction.The boundary contour advantageously enables the tandem guide vane components to be aligned to each other with high accuracy in both the axial and circumferential directions with relatively little effort. For example, the boundary contour can be Z-shaped or toothed, but other designs are also possible.

[0012] In a second aspect, a tandem guide vane segment is proposed, comprising: a plurality of tandem guide vane components according to the first aspect, wherein the front guide vanes form an axially upstream offset front stator vane row and the rear guide vanes form an axially downstream offset rear stator vane row, wherein two adjacent tandem guide vane components form a tandem guide vane pair, wherein a rear guide vane of a first tandem guide vane component with a front guide vane of a second, adjacent tandem guide vane component forms a tandem guide vane pair.

[0013] Such a tandem guide vane segment has the advantage that, by combining, and especially pre-assembling, tandem guide vane components into tandem guide vane segments, a controlled distance between the individual tandem guide vane components of a tandem guide vane segment is achieved. Furthermore, the probability of twisting is advantageously reduced due to the larger circumferential length compared to individual tandem guide vane components.

[0014] In a third aspect, a stator stage for a turbomachine compressor is proposed, comprising: a plurality of tandem guide vane segments according to the second aspect, or a plurality of tandem guide vane components according to the first aspect, wherein the leading guide vanes form an axially upstream offset leading stator vane row, and the trailing guide vanes form an axially downstream trailing stator vane row, wherein each trailing guide vane of a first tandem guide vane component forms a tandem guide vane pair with a leading guide vane of a second, adjacent tandem guide vane component. This means that each pair of adjacent tandem guide vane components forms a tandem guide vane pair.

[0015] To achieve the required tolerances and / or configuration, it may be advantageous to combine tandem guide vane segments of different segment lengths into one stator stage.

[0016] In a fourth aspect, a turbomachine compressor is proposed, comprising a plurality of stator stages according to the third aspect.

[0017] In a fifth aspect, a gas turbine engine is proposed, with a turbomachine compressor according to the fourth aspect.

[0018] In a sixth aspect, a method for manufacturing a tandem guide vane component is proposed, characterized by: manufacturing an upstream front guide vane in a first tangential section; manufacturing a downstream rear guide vane in a second tangential section, wherein the upstream front guide vane and downstream rear guide vane do not overlap in the circumferential direction.

[0019] It is intended that the front and rear guide vanes of a connected tandem guide vane pair are not located on a single platform of a tandem guide vane component, but rather that one front and one rear guide vane from each of two adjacent tandem guide vane pairs are located on the same platform. While an aerodynamically advantageous small distance can be achieved between two guide vanes of a tandem guide vane pair, a larger distance, particularly a wider gap, is achieved between the guide vanes of a tandem guide vane component – ​​which is advantageous from a manufacturing perspective. In other words, the larger distance between the guide vanes of a tandem guide vane component allows for better accessibility for necessary machining operations.

[0020] In a further development of the manufacturing process according to the sixth aspect, it is provided that the upstream front guide vane and the downstream rear guide vane are manufactured using a separating, preferably machining, manufacturing process. This produces the desired shape and surface finish of the front and rear guide vanes. In a further development, additional parts of the tandem guide vane component, or the complete tandem guide vane component, are manufactured using the separating, preferably machining, manufacturing process.

[0021] In a further development of the manufacturing process according to the sixth aspect, it is provided that the upstream front guide vane and the downstream rear guide vane are manufactured using a forming process. The forming process can be a casting process, preferably an injection molding process, such as a metal powder injection molding process. In a further development, additional parts of the tandem guide vane component, or the complete tandem guide vane component, are manufactured using the forming process.

[0022] Complex components can be produced using such injection molding processes. In particular, tandem guide vane components with larger gap widths can be demolded more easily using injection molding. Further development allows for the additional or alternative use of additive manufacturing processes for the partial or complete production of the tandem guide vane component, especially the upstream front guide vane and the downstream rear guide vane.

[0023] Components manufactured using injection molding processes generally employ materials that are also suitable for the necessary processing steps for the production of tandem guide vane components, particularly those preceding or following the injection molding process. Such processing steps include, for example, surface treatments and joining processes.

[0024] In a further development of the manufacturing process according to the sixth aspect, the creation of a tangential boundary contour is provided. The formation of the boundary contour is achieved, for example, by a separating manufacturing process, particularly a machining process, such as milling. The creation of the tangential boundary contour can include the creation of a positive locking feature. With two circumferentially adjacent tandem guide vane components, two engaging positive locking features, which are directed towards each other, particularly in the circumferential direction, can form a positive locking connection. The boundary contour, and in particular the positive locking feature, makes it possible to align the tandem guide vane components with each other with improved accuracy in the axial direction and / or in the circumferential direction with relatively little effort.For example, the boundary contour can be Z-shaped or toothed, but other forms are also possible.

[0025] In a further development of the manufacturing process according to the sixth aspect, the production of a fastening structure is provided for. The formation of the fastening structure is carried out, for example, by a separating, in particular machining, manufacturing process such as milling.

[0026] In a further development step according to the sixth aspect, the mounting structure of the tandem guide vane component is not manufactured. In this case, the tandem guide vane component is referred to as an interim tandem guide vane component.

[0027] In a seventh aspect, a method for manufacturing a tandem guide vane segment is proposed, characterized by: joining several tandem guide vane components according to the sixth aspect by means of a joining method, preferably by welding or brazing, wherein the rear guide vane of a first tandem guide vane component forms a tandem guide vane pair with a front guide vane of a second, adjacent guide vane component.

[0028] The individual tandem guide vane components are arranged side by side in the circumferential direction and assembled into tandem guide vane segments, particularly pre-assembled. In addition to the advantages already mentioned for tandem guide vane segments, pre-assembled tandem guide vane segments can advantageously shorten downstream manufacturing steps, especially assembly steps.

[0029] In a further development step according to the seventh aspect, individual interim tandem guide vane components are assembled into an interim tandem guide vane segment, particularly pre-assembled. A subsequent manufacturing step involves producing a segment mounting structure. This segment mounting structure is formed, for example, by a separating, particularly machining, manufacturing process such as milling. Manufacturing the mounting structure in a later step, after the interim tandem guide vane components have been assembled into an interim tandem guide vane segment, allows for a significant reduction in tolerances, particularly misalignment along the mounting structure, compared to manufacturing the mounting structure during the production of the tandem guide vane component itself.

[0030] In a further development according to the seventh aspect, the first and last circumferential components of the tandem guide vane segment are designed as segment end components. The last circumferential component, the segment end component, comprises a segment boundary contour and a leading guide vane. The first circumferential component, the segment end component, comprises a trailing guide vane and a segment boundary contour. These segment end components allow for the advantageous compensation of circumferential tolerances.

[0031] An eighth aspect proposes a method for manufacturing a stator stage, characterized by: assembling several tandem guide vane segments according to the seventh aspect. The tandem guide vane segments can be arranged side by side in the circumferential direction and fixed in the housing with the mounting structure. The tandem guide vane segments can form a stator stage of an axial compressor, comprising a front and a rear guide vane row formed by tandem guide vane pairs.

[0032] In a further development according to the eighth aspect, the individual tandem guide vane segments are joined together to form a solid ring using a joining process, preferably by welding or brazing. The solid ring can form a stator stage of an axial compressor, which comprises a front and a rear guide vane row formed by tandem guide vane pairs.

[0033] In a further development step according to aspect eight, the individual tandem guide vane components are assembled circumferentially and fixed in the housing with the mounting structure. The tandem guide vane components can form a stator stage of a compressor, in particular an axial compressor, which comprises a front and a rear guide vane row formed by tandem guide vane pairs.

[0034] In In a further development according to the eighth aspect, the individual tandem guide vane components are joined to form a solid ring using a joining process, preferably by welding or brazing. The solid ring can form a stator stage of a compressor, in particular an axial compressor, which comprises a front and a rear row of guide vanes formed by tandem guide vane pairs.

[0035] It should be understood that the tandem guide vane component according to the first aspect, the tandem guide vane segment according to the second aspect, the stator stage according to the third aspect, the axial compressor according to the fourth aspect, the gas turbine engine according to the fifth aspect, the method for manufacturing the tandem guide vane component according to the sixth aspect, the method for manufacturing the tandem guide vane segment according to the seventh aspect, and the method for manufacturing the stator stage according to the eighth aspect, have the same and similar sub-aspects, as set forth in particular in the dependent claims. In this respect, for the further development of one aspect, reference is also made to the further developments of the other aspects of the disclosure.

[0036] The disclosure is explained in more detail below with reference to exemplary embodiments and the drawings. The drawings show: Fig. 1 A simplified schematic sectional view of a gas turbine engine. Fig. 2 Top view of a tandem guide vane component, according to the present disclosure. Fig. 2a Arrangement of a plurality of tandem guide vane components according to Fig. 2 Fig. 3 Side view of a tandem guide vane component, according to the present disclosure. Fig. 4 Two tandem guide vane segments arranged in a row, which were assembled from a plurality of tandem guide vane components. Fig. 5 a simplified schematic representation of a stator stage in which tandem guide vane components are arranged according to the present disclosure. Fig. 6 Simplified flowchart of the manufacturing steps for producing a tandem guide vane segment, according to the present disclosure. Fig. 7 Simplified flowchart of the assembly steps for manufacturing a stator stage, according to the present disclosure.

[0037] Fig. 1 Figure 1 schematically and in a sectional view shows a gas turbine engine 1000. Engine components are arranged sequentially along a longitudinal axis A of the gas turbine engine 1000. Air is drawn in at the inlet 12 by means of a fan 13 along an inlet direction E. This fan 13 is arranged in a fan housing 14 and is driven by a turbine 23 via a rotor shaft 22. The turbine 23 is connected to a compressor, also called a turbomachine compressor 27, which has a low-pressure compressor 15 and a high-pressure compressor 16, and optionally a medium-pressure compressor. To generate thrust, the fan 13 supplies the low-pressure compressor 15 and the high-pressure compressor 16, as well as the bypass channel 17, with air. This creates a main flow SH, which passes through the core of the gas turbine 1000, and a bypass flow SN, which passes through the bypass channel 17.The air compressed in the compressor 15, 16 is mixed with fuel and combusted in the combustion chamber 18. The resulting hot gas drives the turbine 23, which may comprise a high-pressure turbine 19, optionally a medium-pressure turbine 20, and a low-pressure turbine 21. The energy released during combustion is used by the turbine 23 to drive a rotor shaft 22 and thus the fan 13, which then generates the required thrust via the air conveyed into the bypass channel 17. Both the bypass flow from the bypass channel 17 and the main flow exit through an outlet 26. The outlet 26 typically features a thrust nozzle with a centrally located outlet cone 25. To reduce noise, a mixer is located in the outlet area as part of a mixer group 24.The mixer's unique contour deflects and mixes the main flow from the core flow and the bypass flow from bypass channel 17 of the 1000 gas turbine in such a way that the resulting turbulence reduces the audible noise level. The proposed solution can also be applied to gas turbines with different designs, for example, any type of gas turbine engine such as an open-rotor, a turboprop, or a geared fan.

[0038] Fig. 2 Figure 1 schematically shows a top view of a tandem guide vane component 204 according to the disclosure. A leading guide vane 210 and a trailing guide vane 211 are formed on a platform 212, the terms "leading" and "trailing" referring to an axial direction RA parallel to the longitudinal axis A of the engine. The leading guide vane 210 comprises a leading edge 206 and a trailing edge 208. The trailing guide vane 211 comprises a leading edge 207 and a trailing edge 209. To achieve advantageous aerodynamic properties, the guide vanes are manufactured with high dimensional accuracy and geometric precision. This applies particularly to the edges and corners, such as the leading edges 206, 207 and trailing edges 208, 209 of the guide vanes. The front guide vane 210 is arranged in a first tangential section T1 and the rear guide vane 211 is arranged in a second tangential section T2.A gap with a gap width dX in a circumferential direction RU is formed between the front guide vane 210 and the rear guide vane 211. In the embodiment shown, according to the disclosure, the gap width dX is advantageously large to facilitate access for tools and necessary machining steps.

[0039] The platform 212 is formed with boundary contours 214, namely a first boundary contour 214.1 and a second boundary contour 214.2 opposite the circumferential direction RU, which form a contact surface with the tandem guide vane components 204 adjacent to each other in the circumferential direction RU, or rather with their boundary contours 214. The boundary contour 214 of the platform 212 is advantageous for the arrangement and orientation of individual tandem guide vane components 204 relative to each other. With two tandem guide vane components 204 adjacent in the circumferential direction RU, the boundary contour 214 facing each other in the circumferential direction RU forms a positive fit. The circumferential direction RU corresponds to the tangential direction. The boundary contour 214 thus makes it possible to align the tandem guide vane components 204 to each other with high accuracy in the axial direction RA and in the circumferential direction RU with relatively little effort.The boundary contour can be Z-shaped or toothed, for example, but other configurations are also possible. A mounting structure 213 is also provided on the platform 212. This mounting structure 213 is advantageous for securing the tandem guide vane components 204 in the stator housing. The boundary contour 214 can have one or more positive locking features 216 to form a positive locking connection. In this case, the first boundary contour 214.1 has a first positive locking feature 216A and a second positive locking feature 216B, and the second boundary contour 214.2 has a third positive locking feature 216C and a fourth positive locking feature 216D. The first positive locking feature 216A and the third positive locking feature 216C are corresponding to each other, i.e. complementary, such that the first positive locking feature 216A forms a first boundary contour 214.1. Upon contact with the third positive locking feature 216C of a second boundary contour 214.2 of a tandem guide vane component 204 adjacent in the circumferential direction RU, relative movement towards each other in at least one direction, e.g., as in the present case, the axial direction RA, is prevented. By designing the first positive locking feature 216A as a convex and the third positive locking feature 216C as a concave bend point, a defined stop for assembly is advantageously formed, which defines a fixed relative reference between two adjacent tandem guide vane components 204. The same applies analogously to the second positive locking feature 216B and the fourth positive locking feature 216D. However, other positive locking features 216 can be selected which are designed to prevent relative movement of two adjacent boundary contours 214, in particular in the axial direction RA.Alternatively or additionally to the kinks described here, the positive locking feature 216, as shown here at the first boundary contour 214.1, can comprise a contact surface 216E which can be brought into contact with a complementary contact surface 216F of a positive locking feature of an adjacent boundary contour 214 (e.g., the boundary contour 214.2) in order to prevent relative movement in the axial direction RA and thus, in particular, to provide a reference surface for precise and accurate assembly. Fig. 2a Figure 204 schematically illustrates the arrangement of a plurality of tandem guide vane components. Fig. 2 in circumferential direction RU. Fig. 3 schematically shows the side view of the tandem guide vane component 204.

[0040] Fig. 4 Figure 1 schematically shows two assembled tandem guide vane segments 215. A single tandem guide vane segment 215 is assembled from a plurality of tandem guide vane components 204. By way of example, a first tandem guide vane component 204.1 and a second tandem guide vane component 204.2 are shown, arranged adjacent in the circumferential direction RU, forming a first tandem guide vane pair 205.1. Generally, any two tandem guide vane components 204 adjacent in the circumferential direction RU form a tandem guide vane pair 205. The first tandem guide vane pair 205.1 consists of a first, front guide vane 210.1 of the second tandem guide vane component 204.2 and a first, rear guide vane 211.1 of the first, adjacent tandem guide vane component 204.1.The front guide vanes 210 of all tandem guide vane components 204 form a front guide vane row 202, and the rear guide vanes 211 of all tandem guide vane components form a rear guide vane row 203. The front guide vane 210 and rear guide vane 211 of the tandem guide vane pair 205 can overlap, particularly in the axial direction RA and / or in the circumferential direction RU. The front guide vane 210 and rear guide vane 211 of the tandem guide vane component 204 do not overlap in the circumferential direction RU in order to provide adequate clearance for tools used, for example, in machining operations during manufacturing. A gap with a gap width dG is formed between the trailing edge 208 of the front guide vane 210 and a suction side 211S of the rear guide vane 211 of the tandem guide vane pair 205.In particular, the gap width dG can be considered as the smallest distance between the leading guide vane 210 and the trailing guide vane 211. The gap width dG between a leading guide vane 210 and a trailing guide vane 211 of a tandem guide vane pair 205 is preferably small in order to achieve the most advantageous aerodynamic properties. A segment mounting structure 217 is formed at the leading and trailing edges in the axial direction RA of the tandem guide vane segment 215. The first and last components of the tandem guide vane segment 215 in the circumferential direction RU are designed as segment end components 218 and 219, respectively. The last component in the circumferential direction, the segment end component 218, comprises a segment boundary contour 220 and a front guide vane 210. The first component in the circumferential direction, the segment end component 219, comprises a rear guide vane 211 and a segment boundary contour 220.

[0041] Fig. 5 Figure 1 schematically shows a stator stage 201. According to one embodiment of the disclosure, the stator stage 201 is constructed from tandem guide vane segments 215, of which a first tandem guide vane segment 215.1 and a second tandem guide vane segment 215.2 are labeled here as examples. The individual tandem guide vane segments 215 are constructed from a plurality of tandem guide vane components 204. The number of tandem guide vane components 204 that form a tandem guide vane segment 215 can vary depending on the requirements.

[0042] Fig. 6 Figure 1 shows a flowchart for the production of a tandem guide vane segment 215. The tandem guide vane component 204 is manufactured in a first manufacturing step by primary forming or by a separating process. In primary forming, the upstream front guide vane 210 and the downstream rear guide vane 211 are produced, preferably by a casting process, and particularly preferably by an injection molding process such as metal powder injection molding. Depending on the surface quality and dimensional accuracy of the geometries, the desired shape and surface finish of the upstream front guide vane 210 and the downstream rear guide vane 211 are achieved in a further manufacturing step by means of a separating, preferably machining, manufacturing process. If the desired quality and surface finish are already achieved after primary forming, no further manufacturing step is required.The tandem guide vane component can also be manufactured without primary forming, but by means of a separating process. The blank produced by primary forming or by a separating process can be further processed into a finished tandem guide vane component 204 by producing the mounting structure 213 and the boundary contour 216 using a separating, preferably machining, manufacturing process. Alternatively, the blank is further processed into an interim tandem guide vane component 221. In this case, the boundary contour 216 is produced, but not the mounting structure 213. A plurality of tandem guide vane components 204 are joined together by means of an joining process, preferably by welding or brazing, and form a tandem guide vane segment 215. A tandem guide vane pair 205 is formed by joining two adjacent tandem guide vane components 204.The individual tandem guide vane components 204 are arranged side by side in the circumferential direction RU and joined together to form tandem guide vane segments 215. Joining them by means of an joining process creates a controlled distance between the individual tandem guide vane components 204. Tandem guide vane segments 215 offer the advantage that twisting is prevented due to their greater circumferential length compared to the tandem guide vane component 204. Alternatively, a plurality of interim tandem guide vane components 221 are joined together by means of an joining process, preferably by welding or brazing, to form an interim tandem guide vane segment 222. In a further manufacturing step, the interim tandem guide vane segment 222 is further processed into a tandem guide vane segment 215, in which the segment mounting structure 217 is produced by means of a separating, preferably machining, manufacturing process.

[0043] Fig. 7 Figure 1 shows a flowchart for the assembly of a stator stage 201. The stator stage can be manufactured either by assembling a plurality of tandem guide vane components 204, or by assembling a plurality of tandem guide vane segments 215, or by joining a plurality of tandem guide vane segments 215 to form a solid ring. In a further embodiment, the tandem guide vane segments 215 are arranged side by side in the circumferential direction RU and fixed in the housing by the mounting structure 213, wherein the tandem guide vane segments 215 form a stator stage 201 of an axial compressor, which comprises a front guide vane row 202 and a rear guide vane row 203, formed by tandem guide vane pairs 205. In a further development, the full ring is assembled from a plurality of tandem guide vane segments 215 by means of a joining process, preferably by welding or brazing.The full ring forms a stator stage 201 of an axial compressor, comprising a front guide vane row 202 and a rear guide vane row 203, which are formed by tandem guide vane pairs 205. Bezugszeichenliste

[0044] 1000 Gas turbine engine 12 Inlet 13 Fan 14 Fan housing 15 Low-pressure compressor 16 High-pressure compressor 17 Bypass channel 18 Combustion chamber 19 High-pressure turbine 20 Intermediate-pressure turbine 21 Low-pressure turbine 22 Rotor shaft 23 Turbine 24 Mixer group 25 Outlet cone 26 Outlet 27 Turbomachine compressor / Compressor 201 Stator stage 202 Front stator blade row 203 Rear stator blade row 204, 204.1, 204.2 Tandem guide vane component 205, 205.1, 205.2 Tandem guide vane pair 206, 207 Leading edge 208, 209 Trailing edge 210, 210.1, 210.2 Front guide vane 210D, 211D Print side 210S, 211S Suction side 211, 211.1, 211.2 Rear guide vane 212 Platform 213 Mounting structure 214, 214.1, 214.2 Boundary contour 215, 215.1, 215.2 Tandem guide vane segment 216 Positive locking feature 216A, 216B, 216C, 216D Positive locking feature, kink point 216E, 216F Positive locking feature, contact surface 217 Segment mounting structure 218 Segment end component with front guide vane 219 Segment end component with rear guide vane 220 Segment boundary contour 221 Interim tandem guide vane component 222 Interim tandem guide vane segment A Engine longitudinal axis dG Gap between trailing edge of front guide vane and suction side of rear guide vane of a tandem guide vane pair dX Circumferential distance between two guide vanes of a tandem guide vane component E Inlet direction RAA Axial direction RRR Radial direction RTT Tangential direction RU Circumferential direction SH Main flow SN Bypass flow T1, T2 Tangential section.

Claims

1. A tandem guide vane component (204) for a stator stage (201) of a turbomachine compressor (27), comprising a front guide vane (210), a rear guide vane (211), a platform (212) and a mounting structure (213) characterized by the fact that - the front guide vane (210) is assigned to a first tandem guide vane pair (205.1) and the rear guide vane (211) to a second tandem guide vane pair (205.2) adjacent in the circumferential direction (RU), - the front guide vane (210) and rear guide vane (211) are offset from each other in the circumferential direction (RU) such that they do not overlap in the circumferential direction (RU).

2. A tandem guide vane component (204) according to claim 1, characterized by the fact that - the platform (212) forms a boundary contour (214) to a tandem guide vane component (204) adjacent in the circumferential direction (RU).

3. A tandem guide vane component (204) according to claim 1 or 2, characterized by the fact that- the front guide vane (210, 210.1) and the rear guide vane (211, 211.2) form a gap (dX) that is larger than a gap (dG) formed between the front guide vane (210, 210.1) and a rear guide vane (211, 211.1) of a tandem guide vane pair (205).

4. A tandem guide vane segment (215) comprising: - a plurality of tandem guide vane components (204, 204.1, 204.2) according to any one of the preceding claims, wherein - the front guide vanes (210, 210.1, 210.2) form an axially upstream offset front stator blade row (202) and the rear guide vanes (211, 211.1, 211.2) form an axially downstream offset rear stator blade row (203), wherein - two adjacent tandem guide vane components (204, 204.1, 204.2) form a tandem guide vane pair (205), wherein - a rear guide vane (211, 211.1) of a first tandem guide vane component (204, 204.1) is connected to a front guide vane (211, 211.1) of a first tandem guide vane component (204, 204.1). The guide vane (210, 210.1) of a second, adjacent tandem guide vane component (204, 204.2) forms a tandem guide vane pair (205).

5. A stator stage (201) for a turbomachine compressor (15, 16) comprising: - a plurality of tandem guide vane segments (215, 215.1, 215.2) according to claim 4 or a plurality of tandem guide vane components (204, 204.1, 204.2) according to any one of claims 1 to 3, wherein: - the front guide vanes (210, 210.1, 210.2) form an axially upstream offset front stator vane row (202) and the rear guide vanes (211, 211.1, 211.2) form an axially downstream offset rear stator vane row (203), wherein: - each rear guide vane (211, 211.1) of a first tandem guide vane component (204, 204.1) is connected with a front guide vane (210, 210.1) and a second, adjacent tandem guide vane component (204, 204.2) form a tandem guide vane pair (205).

6. A turbomachine compressor (27) comprising a plurality of stator stages (201) according to claim 5.

7. A gas turbine engine (1000) with a turbomachine compressor (27) according to claim 6.

8. Method for manufacturing a tandem guide vane component (204), characterized by : - Production of an upstream front guide vane (210) in a first tangential section; - Production of a downstream rear guide vane (211) in a second tangential section, wherein - the upstream front guide vane (210) and downstream rear guide vane (211) do not overlap in the circumferential direction.

9. Method according to claim 8, characterized by , - the production of the upstream front guide vane (210) and downstream rear guide vane (211) by means of a separating, preferably machining, manufacturing process.

10. Method according to claim 8 or 9, characterized by, - the manufacture of the upstream front guide vane (210) and downstream rear guide vane (211) by means of a primary forming process, preferably by a casting process, particularly preferably by an injection molding process such as metal powder injection molding.

11. Method according to any one of claims 8 to 10, characterized by - Creating a tangential boundary contour (214).

12. Method for manufacturing a tandem guide vane segment (215), characterized by- Joining several tandem guide vane components (204, 204.1, 204.2) according to one of claims 1 to 3 and / or manufactured according to one of claims 8 to 11 by means of a joining method, preferably by welding or brazing, wherein - the rear guide vane (211, 211.1) of a first tandem guide vane component (204, 204.1) with a front guide vane (210, 210.1) of a second, adjacent guide vane component (204, 204.2) forms a tandem guide vane pair (205).

13. Method for manufacturing a stator stage (201), characterized by- Assembling several tandem guide vane segments (215, 215.1, 215.2) according to claim 4 and / or manufactured according to claim 12, or - Assembling several tandem guide vane components (204, 204.1, 204.2) according to any one of claims 1 to 3 and / or manufactured according to claim 8, or - Joining several tandem guide vane segments (215, 215.1, 215.2) according to claim 4 and / or manufactured according to claim 12 by means of a joining process, preferably by welding or brazing, or - Joining several tandem guide vane components (204, 204.1, 204.2) according to any one of claims 1 to 3 and / or manufactured according to claim 8 by means of a joining process, preferably by welding or brazing.

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