EP2808559A1 - Structure assembly for a turbomachine - Google Patents

Abstract

The invention relates to a structure assembly for a turbomachine, comprising: a main flow path boundary (4) which borders a main flow path of a fluid flow machine, 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 insert member (22), wherein in the support member (21) has a circumferentially extending recess (210, 211) is provided which receives at least one insert member (22) in that the support member (21) substantially surrounds the at least one insert member (22) at its side not facing the main flow path, and wherein the insert member (22) completely surrounds or forms at least one secondary flow passage (1).

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 of rectangular or parallelogram cross-section, such as in EP 0 754 864 A1 revealed and in the Fig. 1a outlined as an example. 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 revealed and in the Fig. 1b outlined as an example.

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 due to the unfavorable arrangement or shaping only at Loss of efficiency achieved. 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.

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 It is an object of the present invention to provide a structural assembly which can efficiently provide secondary flow channels, even those of complex shape, in the region of a main flow path boundary of a turbomachine (ie in the region of the housing or the hub). Here, a spatially compact and robust structural design is to be provided.

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 insert member, wherein in the support member is provided a circumferentially extending recess which receives at least one insert member such that the support member, the at least one insert component largely on its not facing the main flow path sides surrounds, and wherein the insert member completely surrounds or forms at least one secondary flow channel. In other words, the solution according to the invention implements the secondary flow channels in a separate component, the insert component, which is inserted into a recess or opening of the support component, which is for example part of the housing or the hub defining the main flow channel.

The invention contemplates a portion of the main flowpath of a turbomachine, in the region of a free end and nip row of blades, in which a series of circumferentially distributed secondary flow passages 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.

It can be provided that the insert component forms the main flow path boundary with at least part of its surfaces. It can further be provided that the insert component completely surrounds at least one secondary flow channel in such a way that all wetted surfaces of the secondary flow channel belong to the insert component undivided.

According to one embodiment of the invention, the support member is designed as an annular housing of a turbomachine and surrounds the support member, the at least one insert member from the outside.

According to a further embodiment of the invention, the support member is formed as a half shell housing a turbomachine and the support member surrounds the at least one insert member from the outside.

According to a further embodiment of the invention, the support member is annularly formed on the hub of a turbomachine and holds the support member, the at least one insert member from the inside.

According to a further embodiment of the invention, the support member is formed semi-annular manner on the hub of a turbomachine and holds the support member, the at least one insert member from the inside.

The insert member may be formed according to the invention as a whole ring or as a ring sector. The production of the insert component can be done for example by means of a casting, sintering or print manufacturing process.

An embodiment of the invention provides that the shape and the surfaces of the insert component are such that the insert member can be inserted into the support member in the axial direction of the turbomachine and an additional component in the axial direction adjacent to the support member and fixes the insert component. In this way, an otherwise required introduction of the insert component in the support member in the radial direction can be avoided.

An embodiment of the invention provides that on the insert component, which is designed as a ring sector or entire ring, on at least parts of its main flow path surface facing a Anstreifbelag is provided. For this purpose, it may also be provided that on the main flow path side facing the insert member adjacent to another whole or partial ring on which on at least parts of its main flow path surface facing a Anstreifbelag is provided.

The present invention relates generally to structural assemblies for turbomachinery such as turbines, and more particularly to 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 fixed blades, the hub side as the housing side can be designed 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. An adjustment is made 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. 1A

ein Casing Treatment eines Rotorgehäuses in Form von Ringnuten gemäß dem Stand der Technik in zwei Ansichten;

Fig. 1B

ein Casing Treatment eines Rotorgehäuses in Form von Schlitzen gemäß dem Stand der Technik in zwei Ansichten;

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; und

Fig. 3D

ein viertes 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. 1A

a casing treatment of a rotor housing in the form of annular grooves according to the prior art in two views;

Fig. 1B

a casing treatment of a rotor housing in the form of slots according to the prior art in two views;

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; and

Fig. 3D

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

Various casing treatments of a rotor housing according to the prior art were initially based on the Figures 1A and 1B 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) dormant 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 component 2 belonging to the main flow path, a number of secondary flow channels 1 distributed on the circumference are provided in the region of the running gap 5, each of which forms an opening at its 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 in the main flow path of the fluid flow machine in which the structural assembly is formed is indicated by the arrow A. The blade row itself is not shown in favor of a simpler view.

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 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 1 is designed as a single-path path with an opening through which fluid flows from the main flow channel into the secondary flow channel and a second opening, through which the fluid leaves the secondary flow channel. 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, provision can be made for at least one of the secondary flow channels to be formed by an arrangement in which at least two channels are combined to form a channel, in which case several inlet openings and one outlet opening belong to the secondary flow channel.

The structural assembly comprises a support member 21 and an insert member 22. Provided in the support member 21 is a circumferentially extending recess 210 which receives the insert member 22 along its circumference. The insert member 22 (or, if multiple insert members are provided, each of the insert members) forms part of its surface with a portion of the outer main flow path boundary. Alternatively, where the structural assembly is disposed in the hub region of a fluid power machine, the liner member correspondingly forms at least a portion of its surfaces a portion of the inner major flow path boundary of the main flowpath of the fluid flow machine.

According to the Fig. 3A It is further provided that in the insert member 22, and only in this, the secondary flow channel 1 is formed, that is, the insert member 22 completely surrounds the secondary flow channel 1, wherein all wetted surfaces of the secondary flow channel 1 and possibly further Sekundärströmungskanäle undividedly belong to the insert member 22 ,

• 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 may be associated with the outer casing or inner hub of the turbomachine and forms with a portion of its surfaces the main flow path boundary. 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 is designed as a ring 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.

The insert component 22 is formed in one embodiment as a complete ring, which is inserted in the corresponding, extending in the circumferential direction recess 210 of the structural component 21. Alternatively, for example, it is provided that the insert component 22 is designed as a ring sector. It can be provided that a plurality of secondary flow channels along the circumference of the main flow path boundary are realized, so that the insert member 22 in the circumferential direction forms a plurality of secondary flow channels 1.

Due to the possible complexity of the secondary flow channels 1 can be provided to produce the insert member 22 by means of a casting, sintering or print manufacturing process. It can be provided as explained, to produce the insert member 22 as a whole ring or as a ring sector with the said method.

The FIGS. 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). In this embodiment, a recess 211 is formed in the support member 21 such that it does not surround the insert member 22 on all outer surfaces that are not part of the main flow path boundary. Thus, a further additional component 23 is provided which is arranged in the axial direction (x) in front of the support component 21 and the insert component 22 and, for example, has a ring shape with a surface 230 facing the support component 21 and the insert component 22. This arrangement makes it possible to insert the insert component 22 in a simple manner into the support component 21 in the axial direction (instead of in the radial direction as in the exemplary embodiment of FIG FIG. 3A ) and then provide axial positioning by the accessory component 23. In this case, the additional component 23 also forms surfaces that are part of the main flow path boundary.

Also in the embodiment of FIG. 3B the secondary flow channel 1 is completely formed in the insert component 22.

The FIG. 3C shows a further variant of a structural assembly. The embodiment differs from the embodiment of FIG. 3B in that additionally an abradable coating 6 is provided, which is formed directly on or in the insert component 22, it being possible to provide that at least one of the openings 111, 112 of the secondary flow channel 1 is located in an area in which the abradable coating 6 is formed , It can be provided that the abradable coating 6 is formed as a ring sector or entire ring on the insert member 22 and thereby provides a main flow path facing surface. Such a squish coating serves to mesh with the blades 3 of a rotating blade row and to achieve that the running gap 5 can be minimized (see. Fig. 2A ).

The Figure 3D shows a further embodiment of a structural assembly. In contrast to the embodiment of FIG. 3C it is provided that the abradable coating 6 is formed in an intermediate ring 7, which is inserted into a corresponding recess 220 in the insert member 22. The additional ring 7 can be formed as a whole ring or as a partial ring. On this ring or partial ring 7, the abradable coating 6 is provided on its surface facing the main flow path.

In further embodiments of the invention, the constructive solutions, with regard to FIGS. 3A . 3B . 3C . 3D are described, combined with each other. For example, a further variant of the invention provides that an abradable coating 6 also in the embodiment of Fig. 3A is 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 the support member and the insert member may be realized in a different manner than shown.

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 has at least one support component (21) and at least one insert component (22), wherein in the support component (21) a circumferentially extending recess (210, 211) is provided which receives at least one insert component (22) in such a way that the support component (21) the at least one insert component (22) largely surrounds its side not facing the main flow path, and wherein the insert component (22) completely surrounds or forms at least one secondary flow channel (1). An assembly according to claim 1, characterized in that the insert member (22) forms the Hauptströmungspfadberandung with at least a portion of its surfaces. An assembly according to claim 1 or 2, characterized in that the insert member (22) so completely surrounds at least one secondary flow channel (1) that all wetted surfaces of the secondary flow channel (1) undividedly belong to the insert member (22). Assembly according to one of the preceding claims, characterized in that the support member (21) is designed as an annular housing of a turbomachine and the at least one insert member (22) coated from the outside, or the support member (21) is designed as a half shell housing a turbomachine and the at least one Insert member (22) encased from the outside. Assembly according to one of the preceding claims, characterized in that the support member (21) is annularly formed on the hub of a turbomachine and the at least one insert member (22) from the inside holds. Assembly according to one of the preceding claims, characterized in that the support member (21) is formed in a semi-annular manner on the hub of a turbomachine and the at least one insert member (22) from the inside holds. Assembly according to one of the preceding claims, characterized in that the insert member (22) is formed as a whole ring or as a ring sector. Assembly according to one of the preceding claims, characterized in that the secondary flow channel (1) is designed as a single-path channel, with a first opening (111, 112), through which fluid flows into the secondary flow channel (1), and with a second opening (112 , 111), through which fluid leaves the secondary flow channel (1). Assembly according to one of the preceding claims, characterized in that at least one secondary flow channel (1) is formed by an arrangement in which a single channel is divided along its course in at least two channels and forms a kind of "pants configuration", wherein an inflow opening and a plurality of outflow openings belong to a secondary flow channel (1). Assembly according to one of the preceding claims, characterized in that at least one secondary flow channel (1) is formed by an arrangement in which at least two channels are merged into one, wherein a plurality of inlet openings and an outflow opening to a secondary flow channel (1). Assembly according to one of the preceding claims, characterized in that the insert component (22) is produced by means of a casting, sintering or print manufacturing process. Assembly according to one of the preceding claims, characterized in that the shape and the surfaces of the insert component (22) are such that the insert member (22) in the axial direction of the turbomachine in the support member (21) can be inserted and an additional component ( 23) in the axial direction to the support member (21) and the insert member (22) fixed. Assembly according to one of the preceding claims, characterized in that on the insert member (22) formed as a ring sector or whole ring, on at least parts of its main flow path surface facing a Anstreifbelag (6) is provided. Assembly according to one of the preceding claims, characterized in that on the side facing the main flow path to the at least one insert member (22) adjacent another whole or partial ring (7) on which on at least parts of its main flow path surface facing a Anstreifbelag (6 ) is provided. Turbomachine with a structural assembly according to one of the preceding claims.

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