EP2808558A1 - Structure assembly for a turbomachine - Google Patents

Abstract

The invention relates to a structural assembly for a turbomachine, comprising: a main flow path boundary (4), which borders a main flow path of a turbomachine, wherein in the main flow path at least one row of blades (3) each having a blade end is arranged, wherein a gap (5) between the blade ends of the at least one row of blades (3) and the main flow path boundary (4), and wherein the blades (3) of a blade row and the Hauptströmungspfadberandung (4) perform a rotating relative movement to each other; and at least one secondary flow channel (1) each having an opening (111, 112) formed at the downstream ends formed in the main flow path boundary (4) so that the secondary flow channel (1) is opened by means of the two openings (111, 112). is connected to the main flow path. It is provided that the structural assembly comprises at least one support member (21) and at least one replaceable plug (6) connected directly or indirectly to the support member (21), and that the replaceable plug (6) comprises a portion of a secondary flow duct (1), wherein the subsection complements at least one further subsection of the secondary flow channel (1) extending outside the plug (6) in the structural assembly into a secondary flow channel (1) continuous between its openings (111, 112).

Description

The invention relates to a structural assembly for a turbomachine according to the preamble of patent claim 1.

The aerodynamic load capacity and the efficiency of turbomachines, in particular of fluid flow machines such as fans, compressors, pumps and fans, is limited by the growth and separation of boundary layers in the rotor and stator tip region near the housing or hub wall. In the case of blade rows with a running gap, this leads to high secondary losses and possibly to the occurrence of operational instabilities at higher loads.

As a countermeasure, it is known to use so-called casing treatments. The simplest form of casing treatments are circumferential grooves with a rectangular or parallelogram-shaped cross-section, as used, for example, in US Pat EP 0 754 864 A1 are disclosed. Other solutions provide for rows of slots or openings in the housing, the individual slots / openings being oriented substantially in the flow direction and having a slender shape with a small extension viewed in the circumferential direction of the machine. Such solutions are for example in the DE 101 35 003 C1 disclosed.

Further casing treatments are provided as a ring on the entire circumference in the region of a rotor in the housing, with guide vanes often being provided to reduce the flow swirl within the casing treatment; such as in the publications EP 0 497 574 A1 . US 2005-0226717 A1 . US Pat. No. 6,585,479 B2 . US 2005-0226717 A1 and DE 103 30 084 A1 ,

Existing concepts of casing treatments in the form of slots and / or chambers in the annular channel wall increase the stability of the fluid flow machine. However, this is achieved due to the unfavorably chosen arrangement or shaping only at loss of efficiency. Known solutions also take up a large space at the periphery of the annular channel of the fluid flow machine, they are due to their shape (eg simple parallelogram Umfangsgehäusenuten) only partially effective and they are always provided in the housing in the range of a rotor blade row. Casing treatments according to the prior art are designed so that they can be easily inserted from an accessible side into the housing with the aid of mostly machining.

As a further countermeasure against secondary losses and the occurrence of operational instabilities, it is known to use injector systems. So it is from the US 8 152 445 B2 known to direct fluid from a fluid supply chamber into the flow channel by means of a nozzle system. The FIG. 1 shows the in the US 8 152 445 B2 described solution. The disadvantage of this solution, a complex secondary flow channel system for the injection of fluid in the region of the housing or the hub must be provided by special design and manufacturing measures.

From the DE 10 2008 037 154 A1 a fluid flow machine is known, which forms at least one secondary flow channel in the area of the blade leading edge in a main flow path boundary, which connects two openings arranged on the main flow path boundary. Each secondary flow channel in each case connects a removal opening with a supply opening provided further upstream. By providing such secondary flow channels, boundary layer influencing in the blade tip region can be effected effectively and an increase in the stability of a fluid flow machine can be achieved without requiring an elaborate casing treatment on the entire circumference of the casing in the region of a rotor. However, complex secondary flow channels in the region of the housing or the hub can be realized only by special design and manufacturing measures.

Starting from the DE 10 2008 037 154 A1 The present invention is based on the object to provide a structural assembly, which efficiently secondary flow channels, including those of complex shape, in the field of Main flow path boundary of a turbomachine (ie in the region of the housing or the hub) can provide.

This object is achieved by a structural assembly having the features of claim 1 and a turbomachine with the features of claim 15. Embodiments of the invention are specified in the subclaims.

Thereafter, the invention provides that the structural assembly has at least one support member and at least one directly or indirectly connected to the support member, replaceable plug. For example, the neck is directly connected to the support member, e.g. arranged on the circumference of the support member, or the connecting piece is connected to a component connected to the support member and thus indirectly to the support member. It is further provided according to the invention that the replaceable plug comprises a subsection of a secondary flow channel, the subsection completing at least one further subsection of the secondary flow channel extending outside of the plug in the structural assembly to a secondary flow passage continuous between its openings.

The solution according to the invention has the advantage that the secondary flow channel can be interrupted or varied by replacing the plug. Also, in the event of wear, a portion of the secondary flow channel formed in the plug can be replaced in a simple manner. In the plug simultaneously spatially compact and robust three-dimensional structures of a secondary flow channel can be provided.

The invention thus contemplates a portion of the main flowpath of a turbomachine, in the region of a free end and a nip row of blades, in which a series of circumferentially distributed secondary flow channels are provided. The course of the secondary flow channels can each be spatially complex. According to the invention, a structural assembly is provided for structurally implementing said secondary flow channels.

In one embodiment of the invention, it is provided that the replaceable plug penetrates at least one structural component which overhangs the main flow path and which is the support component or a further component.

In a further embodiment of the invention, it is provided that the support component forms at least part of the main flow path boundary with at least part of its surfaces. It can also be provided that the replaceable plug extends in a substantially radial direction relative to the main flow path and forms an end face which forms part of the main flow path boundary. According to one embodiment, at least one of the openings of the secondary flow channel is formed in the end face of the replaceable plug.

According to one embodiment of the invention, at least one subsection of a secondary flow channel is realized in the support component, so that at least the support component and the plug accommodate subsections of the secondary flow channel. Further sections can be provided by further components.

According to one embodiment of the invention, the support member is formed as an annular housing or as a half-shell housing a turbomachine, or the support member is formed like a ring or half-ring on the hub of a turbomachine.

In an advantageous embodiment, the support member is structurally such that for the purpose of assembly and disassembly of the interchangeable plug from the main flow path side facing a direct access to the interchangeable plug is given, so that the interchangeable plug from the main flow path side facing away from the support member without disassembling others Structural components is replaceable.

In a further embodiment, the structural assembly according to the invention further comprises at least one insert member, wherein in the support member is provided a circumferentially extending recess which receives along the circumference at least one insert member, and wherein each insert member forms part of the surfaces of a part of the Hauptströmungspfaderbandung and at least forms a portion of a secondary flow channel.

It can be provided that the insert member is completely penetrated at the periphery of at least one replaceable plug, such that the end face of the replaceable plug forms part of the Hauptströmungspfadberandung. It can also be provided that the replaceable plug penetrates only the insert component and there has a defined seat, wherein the support member is a local Has recess through which the replaceable plug in the insert component is mounted and dismounted. Alternatively, the replaceable plug penetrates both the support member and the insert member.

According to one embodiment of the invention, the structural assembly according to the invention further comprises at least one connecting member, wherein the connecting member substantially on the side facing away from the main flow path side of the support member to the support member, and wherein the connecting member forms at least a portion of a secondary flow channel.

It can be provided that the support member is completely penetrated at the periphery of at least one replaceable plug such that the end face of the replaceable plug forms part of the main flow path boundary, wherein portions of a secondary flow channel are formed in the support member, in the connection member and in the replaceable plug and complement each other to a continuous secondary flow channel.

A further variant of the invention provides that the connecting component is installed in recesses in the support component in the area of at least one end of the secondary flow channel and in this way directly adjoins the main flow path. In this embodiment variant, the connecting component thus also forms an opening-near region of the secondary flow channel.

For receiving and fastening the replaceable plug, at least one connecting piece may be formed on the side of the support component facing away from the main flow path on the circumference of the support component. Also, on the side facing away from the main flow path side of the support member is at least one, at least along a portion of the circumference continuously extending web for receiving at least one interchangeable plug is formed.

Another variant of the invention provides that the replaceable plug is designed as a multi-part element. For this purpose, an embodiment variant provides that the replaceable plug is subdivided into partial plugs along at least partial sections of the secondary flow channel. For this purpose, a further embodiment provides that the replaceable plug is formed in two parts and provided a fixing top plug and a example with a defined seat Understop comprises, with upper and lower plugs together form the interchangeable plug.

According to one embodiment, the fixation of the interchangeable plug is realized by a fit, a press fit, a plug, a clamp or a screw.

The interchangeable plug with implemented portion of a secondary flow channel may be replaced by a blind plug with no channel implemented for the purpose of inhibiting flow through the secondary flow channel.

The present invention relates generally to structural assemblies for turbomachines, such as turbines, and to particular fluid flow machines, such as fans, compressors, pumps, and fans, in both axial, semi-axial, and radial designs. The working medium or fluid may be gaseous or liquid. The turbomachine may include one or more stages each having a rotor and a stator. In some cases, the stage is formed only by a rotor.

The rotor of a turbomachine, in which a structural assembly according to the invention is used, consists of a number of blades, which are connected to the rotating shaft of the turbomachine and deliver energy to the working fluid in the case of the fluid flow machine. The rotor can be designed with or without shroud on the outer blade end.

The stator of a turbomachine, in which a structural assembly according to the invention is used, consists of a number of stationary blades, which can be designed on the hub side as the housing side with a fixed or free blade end.

The rotor drum and the blading are usually surrounded by a housing. In other cases, z. As in propellers or propellers, no housing exists.

A turbomachine, in which a structural assembly according to the invention is used, can also have a stator in front of the first rotor, a so-called leading wheel. At least one stator or Vorleitrad - may be rotatably mounted - deviating from an immovable fixation - to change the angle of attack can. A Adjustment takes place for example by a spindle accessible from outside the annular channel.

In one embodiment, a turbomachine, in which a structural assembly according to the invention is used, have at least one row of adjustable rotors.

In one embodiment, a turbomachine in which a structural assembly according to the invention is used in multi-stage have two opposing waves, so that the rotor blade rows change the direction of rotation from stage to stage. There are no stators between successive rotors.

In one embodiment, a turbomachine in which a structural assembly according to the invention is used, have a bypass configuration such that a single-flow annular channel behind a certain row of blades divides into two concentric annular channels, which in turn accommodate at least one more row of blades.

In the turbomachine in which a structural assembly according to the invention is used, it is, for example, a jet engine, in particular a turbofan engine. The structural assembly is formed, for example, in the region of a compressor of a jet engine or turbofan engine.

The invention further relates to a fluid flow machine with a structural assembly according to the invention.

Fig. 1

ein Rotorgehäuse mit einer integrierten Düse zur Injektion von Fluid in einen Laufspalt gemäß dem Stand der Technik;

Fig. 2A

ein Ausführungsbeispiel eines Rotorgehäuses einer Strömungsmaschine mit einem Sekundärströmungskanal in einem Meridianschnitt;

Fig. 2B

ein Ausführungsbeispiel eines Rotorgehäuses einer Strömungsmaschine mit einem Sekundärströmungskanal in räumlicher Ansicht;

Fig. 3A

ein erstes Ausführungsbeispiel einer Strukturbaugruppe für eine Strömungsmaschine, die einen Sekundärströmungskanal ausbildet;

Fig. 3B

ein zweites Ausführungsbeispiel einer Strukturbaugruppe für eine Strömungsmaschine, die einen Sekundärströmungskanal ausbildet;

Fig. 3C

ein drittes Ausführungsbeispiel einer Strukturbaugruppe für eine Strömungsmaschine, die einen Sekundärströmungskanal ausbildet.

Fig. 3D

ein viertes Ausführungsbeispiel einer Strukturbaugruppe für eine Strömungsmaschine, die einen Sekundärströmungskanal ausbildet; und

Fig. 3E

ein fünftes Ausführungsbeispiel einer Strukturbaugruppe für eine Strömungsmaschine, die einen Sekundärströmungskanal ausbildet.

The invention will be explained in more detail with reference to the figures of the drawing with reference to several embodiments. Show it:

Fig. 1

a rotor housing with an integrated nozzle for the injection of fluid into a running gap according to the prior art;

Fig. 2A

an embodiment of a rotor housing of a turbomachine with a secondary flow channel in a meridian section;

Fig. 2B

an embodiment of a rotor housing of a turbomachine with a secondary flow channel in a three-dimensional view;

Fig. 3A

a first embodiment of a structural assembly for a turbomachine, which forms a secondary flow channel;

Fig. 3B

a second embodiment of a structural assembly for a turbomachine, which forms a secondary flow channel;

Fig. 3C

A third embodiment of a structural assembly for a turbomachine, which forms a secondary flow channel.

Fig. 3D

A fourth embodiment of a structural assembly for a turbomachine, which forms a secondary flow channel; and

Fig. 3E

A fifth embodiment of a structural assembly for a turbomachine, which forms a secondary flow channel.

The teaching of the prior art, by means of a nozzle system to inject fluid from a fluid supply chamber in a flow channel, was initially based on the FIG. 1 been described.

The Fig. 2A shows an arrangement of a blade row 3 with free end and running gap 5 in the meridian plane formed by the axial direction x and the radial direction r. The nip 5 separates the blade tip from a component 2 belonging to the main flow path at the hub or housing of the fluid flow machine. In this case, the component 2 forms a main flow path boundary 4 toward the main flow path.

There is a rotating relative movement between the blade tip and the component 2 belonging to the main flow path. The illustration thus applies equally to the following arrangements: 1.) rotating blade on stationary housing; 2.) stationary blade on rotating hub; 3.) stationary blade on rotating housing; and 4.) rotating blade on standing hub.

The main flow direction in the main flow path is indicated by an arrow A. Upstream and / or downstream of the row of blades 3 with running gap, further rows of blades may be located. Within the main flow path belonging to the component 2 is in the region of the running gap 5 a number of the circumference distributed secondary flow channels 1 are provided, which each form an opening at their ends (feed opening and removal opening).

The openings of the secondary flow channels are located at the main flow path boundary 4. Die Fig. 2A shows the outline or the projection of a single secondary flow channel 1 in the meridian plane (xr). In spatial terms, each channel 1 has a three-dimensional spatially twisted course, which in the Fig. 2B is shown by way of example.

It should be noted that the cross-sectional shape of the secondary flow channels 1 in the Fig. 2B merely exemplified as rectangular. For example, the cross section of the secondary flow channels 1 may be formed in other embodiments without corners, in particular circular or elliptical.

The FIG. 3A shows a structural assembly according to the invention in the region of a row of blades with running gap in the meridian view (xr). The main flow direction is indicated by an arrow A. The blade row is no longer shown in favor of a simpler representation.

In the structural assembly at least one secondary flow channel 1 is formed, which has two openings 111, 112 in the main flow path boundary 4 and is connected via this to the main flow path. It should be noted that in the embodiment of FIG. 3A the secondary flow channel 11 is designed as a single-path path with an opening through which fluid flows from the main flow channel into the secondary flow channel 1 and a second opening, through which the fluid leaves the secondary flow channel 1. Through which of the openings 111, 112 flows fluid and through which the openings 111, 112 fluid flows, depends on the exact positioning of the openings 111, 112 with respect to the blades of the blade row 3 (see. Fig. 2B ).

In alternative embodiments, it can be provided that at least one of the secondary flow channels is formed by an arrangement in which a single channel is divided along its course into at least two subchannels, thereby forming a kind of "trouser configuration". In this case, an inflow port and a plurality of outflow ports are included, which belong to the secondary flow passage. According to a further alternative embodiment it can be provided that at least one of the secondary flow channels is formed by an arrangement in which at least two Channels are merged into a channel, in which case a plurality of inflow and a discharge port to the secondary flow passage.

According to the FIG. 3A the secondary flow channel 1 is realized in a structural assembly comprising a support member 21, an insert member 22 and a replaceable plug 6.

• Bestandteil eines ein- oder mehrschaligen Gehäuses von Schaufelreihen oder Stufen mit fester Schaufelgeometrie;
• Bestandteil eines ein- oder mehrschaligen Gehäuses von Schaufelreihen oder Stufen mit verstellbarer Schaufelgeometrie;
• Bestandteil von Rotortrommeln, Rotorscheiben oder Blisk-Modulen;
• Bestandteil von Innendeckbandbaugruppen im Nabenbereich von Leitradschaufeln.

The support member 21 is used for structural realization in the region of the inner or outer Hauptströmungspfadberandung and may belong to the outer housing or the inner hub of the turbomachine. It can be provided that it forms part of its surfaces with a part of the main flow path boundary 4. In the illustrated embodiment, the support member 21 is a part of the outer casing of the turbomachine. Basically, the support member 21 may be in particular part of the flow machine design in the following areas:

• Component of a single or multi-shell housing of blade rows or steps with fixed blade geometry;
• Component of a single or multi-shell housing of blade rows or stages with adjustable blade geometry;
• Component of rotor drums, rotor disks or blisk modules;
• Component of inner shroud assemblies in the hub area of stator vanes.

In the embodiment of FIG. 3A the support member 21 is formed as an annular housing of a turbomachine or as a half shell housing a turbomachine. With a corresponding arrangement in the hub region, it is, for example, annularly formed on the hub of a turbomachine or semi-annular on the hub of a turbomachine.

In the support member 21, a recess extending in the circumferential direction is provided, in which at least one insert member 22 is inserted along the circumference. The insert component 21 forms part of its surfaces with a part of the main flow path boundary 4.

The replaceable plug 6 extends in a substantially radial direction with respect to the main flow path, penetrating both the support member 21 and the insert member 22. The plug 6 has an end face 60 which forms part of the main flow path boundary 4.

The secondary flow channel 1 comprises two subsections 11, 12, wherein one subsection 11 is formed in the insert component 22 and the other subsection 12 is formed in the interchangeable plug 6. The one of the two openings 111, 112 of the secondary flow channel 1 is in the insert member 22 and the other of the openings 111, 112 of the secondary flow channel 1 is in Plug 6 is formed.

It should be noted that in the embodiment of FIG. 3A the insert member 22 is inserted in the axial direction in the corresponding recess in the support member 21. A fixation of the components 21, 22 to each other in the axial direction can be effected by a further component 7.

It should also be noted that the portion 12 of the secondary flow channel 1 is provided by means of internal surfaces of the plug 6, that is not by means of structures formed on the outside of the plug 6.

The formation of a portion 12 of the secondary flow channel 1 in a replaceable plug 6 is associated with the advantage that it is possible by replacing the plug 6 by a blind plug without integrated channel section, to prevent the flow through the secondary flow channel 1. Thus, by means of the replaceable plug 6, a flow through a secondary flow channel can be switched on and off. It is also possible to have available various plugs 6 in which the partial section 12 realized in the stopper 6 is embodied in different ways, in each case complementing the partial section 11 formed in the insert component 22. In this way, the formation of the secondary flow channel 1 and the flow occurring therein can be varied in a simple manner.

The FIG. 3B shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr). The embodiment of FIG. 3B differs from the embodiment of FIG. 3A in that the replaceable plug 6 is designed as a multipart element. Thus, the plug 6 is divided into two sub-plugs 61, 62, wherein in principle more than two sub-plugs are possible. According to the FIG. 3B For example, the plug 6 comprises a fixing top plug 62 and a properly fitted bottom plug 61 Part region 12 of the secondary flow channel 1 in the lower plug 61 is formed. The top plug 62 is fixed by screwing or the like in a corresponding opening of the support member 21, for example.

FIG. 3C shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr). In this embodiment is different from the embodiments of FIGS. 3A and 3B provided that the replaceable plug 6 penetrates only the insert member 22 and is fitted in this. A structural member penetrating the plug 6 is thus provided solely by the insert member 22.

In this case, the support member 21 has a local recess 215, for example in the form of a mounting opening through which the replaceable plug 6 in the insert member 22 can be mounted and dismounted. It can be provided, for example, that the plug 6 has a round cross section and is fixed by means of a thread 63 in its upper part in the insert member 22. However, the shape and fixation modes of the replaceable plug 6 may be formed in other ways.

The Figure 3D shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr). In this embodiment, the replaceable plug 6 penetrates again alone the insert member 22, wherein above the plug 6 in the support member 21, a mounting opening 215 is formed. Unlike in the embodiment of FIG. 3C the plug 6 is designed as a multi-part element with two partial plugs 64, 65, whereby more than two partial plugs can be provided. The subdivision of the plug 6 into two sub-plugs 64, 65 takes place along two sections of the secondary flow channel 1, that is, each of the two sub-plugs 64, 65 accommodates a lower portion 12a, 12b of the portion 12 realized in the plug 6. This is associated with the advantage in that the secondary flow channel 1 can be made more easily accessible, for example, to a production tool.

Due to the possibly existing complexity of the secondary flow channels with regard to their three-dimensional shape, it may be provided to produce the exchangeable plug 6 by means of a casting, sintering or print production method. This applies to all described embodiments.

The FIG. 3E shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr). In this embodiment, the secondary flow channel 1 comprises three subsections 11, 12, 13, wherein a subsection is formed in a support member 21, a subsection in a replaceable plug 6, and a subsection in a connection component 23.

The support member 21 forms with part of its surfaces a part of the main flow path boundary 4. At the side facing away from the main flow path, it forms a structure 212 for receiving the replaceable plug 6, which is formed in the illustrated embodiment by a cylindrical wall or a nozzle 212. In the wall 212 of the plug 6 is inserted, wherein the end face 60 of the plug 6 is a part of the Hauptströmungspfadberandung 4. In the plug 6, a portion 12 of the secondary flow channel and one of the openings 111 of the secondary flow channel are integrated.

The support member 21 further includes on its side facing away from the main flow path side a web 211, in which a first portion 13 of the secondary flow channel is formed. Between the web 211 and the neck or the wall 212 extends the connecting member 22 which extends on the side facing away from the main flow path side of the support member 21 between these portions 211, 212 of the support member 21 and is arranged, for example as a line freely in space.

A fixation of the replaceable plug 6 can be realized for example by a fit, a press fit, a plug, a clamp or a screw. The connecting member 11 is attached to the web 211 and the nozzle 212, for example, by a fit, a plug, a clamp, a screw, a weld or a solder.

According to an alternative embodiment, the connecting member 23 is formed such that it is inserted in recesses in the support member 21 in the region of at least one end of the secondary flow channel and in this way has surfaces which form part of the Hauptströmungspfadberandung 4. For example, in a modification of FIG. 3E the connecting piece 211 is formed as part of the connecting component 23.

In further embodiments of the invention, the constructive solutions, with regard to FIGS. 3A to 3E are described, combined with each other. For example, a multipart plug 6 in the embodiment of the FIG. 3E be realized.

The invention is not limited in its embodiment to the embodiments shown above, which are to be understood only as examples. For example, the shape and configuration of the secondary flow channels and of the components providing them (supporting component, connecting component, insert component and plug) can be realized in a different way than illustrated.

Claims (15)

Structural assembly for a turbomachine, comprising: a main flow path boundary (4) which borders a main flow path of a turbomachine, wherein in the main flow path at least one row of blades (3) each having a blade end is arranged, wherein a gap (5) between the blade ends of the at least one row of blades (3 ) and the main flow path boundary (4), and wherein the blades (3) of a blade row and the main flow path boundary (4) perform a rotating relative movement to each other; and at least one secondary flow channel (1) each having an opening (111, 112) at flow-spaced ends formed in the main flow path boundary (4) such that the secondary flow channel (1) is opened by means of the two openings (111, 112) connected to the main flow path, characterized in that - The structural assembly at least one support member (21) and at least one directly or indirectly connected to the support member (21) exchangeable plug (6), and the replaceable plug (6) comprises a subsection of a secondary flow channel (1), the subsection comprising at least one further subsection of the secondary flow channel (1) extending outside the plug (6) in the structural assembly, to one between its openings (111, 112) continuous secondary flow channel (1) added. An assembly according to claim 1, characterized in that the replaceable plug (6) penetrates at least one main flow path overlying the structural component, which is the support member (21) or another component (22). An assembly according to claim 1 or 2, characterized in that the support member (22) forms at least part of the main flow path boundary (4) with at least part of its surfaces. Assembly according to one of the preceding claims, characterized in that the replaceable plug (6) extends in a substantially radial direction with respect to the main flow path . Assembly according to one of the preceding claims, characterized in that the replaceable plug (6) forms an end face (60) which forms part of the main flow path boundary (4). An assembly according to claim 5, characterized in that in the end face of the replaceable plug (6) at least one of the openings (111, 112) of the secondary flow channel (1) is formed. Assembly according to one of the preceding claims, characterized in that at least one subsection of a secondary flow channel (1) in the support member (21) is realized. Assembly according to one of the preceding claims, characterized in that the support member (21) is designed as an annular housing or as a half-shell housing a turbomachine or ring-like or semi-annular manner on the hub of a turbomachine. Assembly according to one of the preceding claims, characterized in that it further comprises at least one insert member (22), wherein in the support member (21) is provided a circumferentially extending recess which receives along the circumference at least one insert member (22), and wherein each insert member (22) forms with part of its surfaces a portion of the main flow path boundary and forms at least a portion of a secondary flow channel SSK. An assembly according to claim 9, characterized in that the replaceable plug (6) penetrates only the insert member (22) and has a defined seat there, wherein the support member (21) has a local recess (215) through which the interchangeable plug (6 ) in the insert component (22) can be mounted and removed. Assembly according to one of the preceding claims, characterized in that it further comprises at least one connecting member (23), wherein the connecting member (23) substantially on the side facing away from the main flow path side of the support member (21) connects to the support member (21), and wherein the connecting member (23) forms at least a portion (11) of a secondary flow passage (1). An assembly according to claim 11, characterized in that the support member (21) is completely penetrated at the circumference of at least one interchangeable plug (6), such that the end face (60) of the replaceable plug (6) forms part of the main flow path boundary (4) wherein the subsections (13, 11, 12) of a secondary flow channel are formed in the support member (21), the connection member (23) and the replaceable plug (6) and complement each other to form a continuous secondary flow passage (1). Assembly according to one of the preceding claims, characterized in that on the side facing away from the main flow path side of the support member (21) locally on the circumference at least one nozzle (212) for receiving a replaceable plug (6) is provided. Assembly according to one of the preceding claims, characterized in that the replaceable plug (6) is designed as a multi-part element. Turbomachine with a structural assembly according to one of the preceding claims.

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