EP2722485A1 - Inner ring for a stator assembly with adjustable vanes - Google Patents

Abstract

The ring (9) has adjustable guide vanes (2) provided with a groove (9.3) and arranged on an outer surface of the ring. Two guide vane retainers are arranged between the guide vanes away from the outer surface of the ring. A high-heat conducting material is filled in the guide vanes through the groove, where cross-section of the groove is in U-shape or V-shape. Independent claims are also included for the following: (1) a guide vane collar (2) a method for manufacturing an inner ring.

Description

The present invention relates to an inner ring for a vane ring with adjustable guide vanes of a turbomachine, in particular a gas turbine, preferably a gas turbine engine, a vane ring and such a turbomachine with such an inner ring and a method for producing such an inner ring.

For example, from the WO 2007/134585 A1 the applicant and the US 7,722,318 B2 Leitschaufelkränze with adjustable vanes and a radially inner inner ring are known which has Leitschaufelaufnahmen in which the vanes are rotatably mounted.

Such inner rings can, in particular in transient operation, be exposed to partially changing and / or high temperature gradients, in particular by the working vane flowing through the vane ring and / or a sliding seal between the vane ring and the rotor rotating relative thereto. As a result of these temperature gradients, temperature distributions can be formed in a cross-section, in particular a meridian section, of the guide vane ring, which influence its diameter and / or shape, in particular roundness - the inner ring can, so to speak, move thermally.

As a result, a seal between the vane ring and the rotor is adversely affected, in particular a gap between the vane ring and the rotor can be increased and / or an inlet can be increased.

An object of the present invention is to improve the performance of a turbomachine.

This object is achieved by an inner ring for a vane ring with adjustable guide vanes of a turbomachine having the features of claim 1. Claim 10 illustrates a vane ring with an inner ring according to the invention, claim 11 a turbomachine with such a vane ring and claim 12 a method for producing an inner ring according to the invention under protection. The subclaims relate to advantageous developments.

A turbomachine according to one aspect of the present invention includes one or more compressor stages and / or one or more turbine stages. One or more of these compressor and / or turbine stages each have a rotor and a guide grid, wherein one or more of these guide grilles comprise a stator vane ring with adjustable vanes according to one aspect of the present invention. With particular advantage, the invention is used in gas turbines, in particular in gas turbine engines, preferably in a low-pressure and / or high-pressure compressor. Accordingly, one aspect of the present invention relates to a low or high pressure compressor having an inner ring according to one aspect of the present invention.

A vane ring according to one aspect of the present invention comprises a plurality of guide vanes, which are adjustably, in particular rotatably, mounted on an inner ring according to an aspect of the present invention. For this purpose, the guide vanes can be supported radially on the inner ring. Additionally or alternatively, the guide vanes may be partially arranged, in particular rotatably supported, in continuous or blind-hole-like recesses on a lateral surface of the inner ring facing the guide vanes, in which case separate bearing elements are arranged in the recesses could be. As a guide blade receptacles according to the present invention, in particular continuous or blind hole-like recesses are referred to, in which guide vanes are rotatably mounted and / or radially supported. In particular, for the arrangement of the adjustable guide vanes on the inner ring is fully content to the introductory mentioned WO 2007/134585 A1 the applicant and the US 7,722,318 B2 Reference is made, the content of which is expressly incorporated herein by reference.

An inner ring according to one aspect of the present invention has one or more grooves which are arranged on a lateral surface of the inner ring facing away from the guide vanes. A groove in the sense of the present invention is understood in particular to mean a local, preferably channel-like, radial recess in the lateral surface.

Such grooves reduce the cross-sectional area of the inner ring locally. As a result, in one embodiment, a better temperature distribution, preferably an approximately or at least substantially constant temperature, can advantageously be represented in the remaining cross section. Additionally or alternatively, through such grooves in one embodiment, a heat conduction in the circumferential direction of the inner ring can be influenced, in particular limited and / or reduced. In one embodiment of the present invention can be influenced by the groove or grooves a thermal movement of the inner ring, in particular during operation, in particular reduced, and so a change in its diameter and / or its shape, in particular roundness, influenced, in particular reduced. As a result, in one embodiment, a seal between the vane ring and the rotor can advantageously be improved, in particular a gap between the vane ring and the rotor and / or an inlet can be reduced and thus the operating behavior, in particular an efficiency, of a turbomachine can be improved.

In one embodiment of the present invention are seen in the circumferential direction between at least two adjacent vanes or Leitschaufelaufnahmen on the side facing away from the vanes Outer surface of the inner ring arranged one or more grooves. In one embodiment, an arrangement between guide blade receptacles can advantageously reduce the cross section at this point, at which point it would initially have a greater wall thickness compared to recesses for receiving the guide blades.

In one embodiment of the present invention, one or more grooves arranged on the lateral surface of the inner ring remote from the guide vanes extend, at least substantially, in the axial direction. The grooves may be inclined in the circumferential and / or radial direction against the axial direction. In a further development, the grooves are straight or have a straight center line. As a result, with minimal material thinning a maximum meridian cross-section reduction of the inner ring can be represented.

In one embodiment of the present invention, one or more grooves arranged on the lateral surface facing away from the guide vanes of the inner ring are open on one or both end faces or in the axial direction. Such unilaterally or bilaterally open grooves can be advantageously produced easily. In another embodiment of the present invention, one or more arranged on the side facing away from the vanes lateral surface of the inner ring grooves are closed on one or both end faces or in the axial direction. As a result, a leakage of working fluid through the groove can advantageously be prevented or reduced.

In addition or in particular, alternatively to grooves closed on one or both sides in the axial direction, a leakage of working fluid through the groove (s) can be prevented or reduced by, in one embodiment of the present invention, a seal carrier the groove (s), in particular on the front side or in the axial direction seen, covering. The seal carrier may rest against the inner ring, in particular at least in the edge region of open grooves on one or both end faces of the inner ring, in a development of the seal carrier, in particular the front side and / or radially from the inside, engage in the groove (s).

In one embodiment of the present invention, the grooves in a cross section perpendicular to the axial direction on, at least substantially, U-shaped or V-shaped cross-section. This can be constant in the axial direction, at least substantially. This is manufacturing and strength engineering advantageous.

A groove in one embodiment of the present invention is, at least substantially, free of material to reduce the cross-section and thus improve the temperature distribution in the inner ring. In particular, in order nevertheless to represent a better strength with improved temperature distribution, the grooves can also be completely or partially filled with a highly heat-conductive material. A material having a thermal conductivity of at least 40 W / (Km), for example steel, in particular is considered to be a high-thermal conductivity material in the sense of the present invention at least 200 W / (Km), for example aluminum, preferably at least 300 W / (Km), for example copper.

In one embodiment of the present invention, two or more grooves arranged on the lateral surface of the inner ring facing away from the guide vanes are distributed over the circumference of the inner ring, in particular at least substantially equidistantly. As a result, an advantageous temperature distribution can be represented. In particular, it has been found that an arrangement of one or more grooves between each two adjacent vane seats, i. one or more grooves seen in the circumferential direction after all vane receptacles or vanes, thermodynamically may be advantageous. Furthermore, it has been found that an arrangement of one or more grooves between each two adjacent vane receiving pairs or vane receiving nipples, i. one or more grooves seen in the circumferential direction after each second or third vane receiving or guide vane, can represent an optimal combination of thermodynamic and structural aspects.

In one embodiment of the present invention, the inner ring is formed in one piece. In another embodiment, it has two or more segments. In one development, an abutting edge between circumferentially adjacent segments of the inner ring may be groove-free, in particular in order not to impress any cross-sectional weakening there. Likewise, a groove may be arranged on an abutting edge between circumferentially adjacent segments of the inner ring on the lateral surface facing away from the guide vanes, in particular in order to facilitate their manufacture.

The grooves can be formed according to an embodiment of the present invention on the side facing away from the vanes lateral surface of the inner ring in particular by machining. Likewise, they may be uroformed with the inner ring, for example cast, or thermally or optically removed, in particular eroded or formed by means of a laser.

Fig. 1:

einen Meridianschnitt eines Teils eines Gasturbinentriebwerkverdichters mit einem Leitschaufelkranz mit einem Innenring nach einer Ausführung der vorliegenden Erfindung;

Fig. 2:

einen in Umfangsrichtung um eine halbe Schaufelteilung versetzten Meridianschnitt durch eine Nut des Innenrings der Fig. 1; und

Fig. 3:

eine perspektivische Ansicht eines Leitschaufelkranzes mit einem Innenring nach einer weiteren Ausführung der vorliegenden Erfindung.

Further advantages and features emerge from the subclaims and the exemplary embodiments. This shows, partially schematized:

Fig. 1:

a meridian section of a portion of a gas turbine engine compressor with a vane ring with an inner ring according to an embodiment of the present invention;

Fig. 2:

a circumferentially offset by half a blade pitch meridian section through a groove of the inner ring of Fig. 1 ; and

3:

a perspective view of a vane ring with an inner ring according to another embodiment of the present invention.

Fig. 1 1 shows a meridian section of a part of a gas turbine engine compressor with a vane ring with an inner ring 9 according to an embodiment of the present invention, which is shown in FIG Fig. 2 is shown enlarged in a circumferentially offset by half a blade pitch meridian section.

The gas turbine engine compressor has in known manner a rotor 1 with blades 1.1, which in the axial direction (from left to right in Fig. 1 ) are arranged alternately with vanes 2. The guide vanes 2 are mounted on the inner ring 9 in a manner known per se on the lateral surface 9.1 facing the guide vanes, which defines the annular space contour. For example, the guide vanes 2 can have axle journals which are rotatably mounted in recesses in the inner ring 9, as shown in FIG Fig. 3 is indicated. As can be seen there, the guide vanes 2 can have radially outer outer pins 8, with which they can be mounted radially on the outside of the guide vane ring or housing and by means of which they can be adjusted. In addition, the introductory mentioned WO 2007/134585 A1 the applicant and the US 7,722,318 B2 Referenced.

Between each two adjacent pairs of guide vanes, ie in the circumferential direction after every second vane or guide vane and thus equidistantly distributed over the circumference of the inner ring is on the side facing away from the vanes 2 lateral surface 9.2 of the inner ring 9, which faces the vanes facing lateral surface 9.1 (see. Fig. 2 ), a groove 9.3 arranged, which, in particular in the meridian section of Fig. 2 recognizable, essentially in the axial direction (from left to right in Fig. 2 ).

Through these grooves 9.3, the meridian cross section of the inner ring is reduced at these points, so that adjusts an advantageous temperature distribution in the remaining reduced residual cross section 9.4, which reduces thermal movement of the inner ring 9 and thus a change in the sealing gap or inlet between the vane ring and rotor 1.

The grooves 9.3 have in a cross section perpendicular to the axial direction or plane of the drawing Fig. 2 one, at least substantially, U-shaped or V-shaped cross section and are free of material.

The grooves 9.3 are, as in Fig. 2 recognizable, on both front sides (left, right in Fig. 2 ) open.

However, in order to reduce a leakage of working fluid through the grooves 9.3, the guide vane ring on a seal carrier 13, which covers the arranged on the side facing away from the vanes shell surface 9.2 of the inner ring 9 9.3 on both end faces, as in Fig. 1 shown.

Fig. 3 shows a perspective view of a vane ring with an inner ring according to another embodiment of the present invention. With the above with reference to Fig. 1, 2 explained features identical features are denoted by identical reference numerals, so that reference is made to the above explanations.

As in the execution of Fig. 1, 2 is the inner ring 9 of the execution of Fig. 3 formed in several parts by being composed of two or more segments 10 which abut one another in the circumferential direction. Likewise in the execution of the Fig. 1, 2 is arranged in the circumferential direction between each two adjacent Leitschaufelpaaren or Leitschaufelaufnahmepaaren on the side facing away from the vanes 2 lateral surface of the inner ring 9, a groove 9.3. Likewise in the execution of the Fig. 1, 2 These grooves 9.3 are covered by a seal carrier 13, which is also divided into segments 14 which abut one another in the circumferential direction and radially inwardly have an inlet lining 15.

LIST OF REFERENCE NUMBERS

1

rotor

1.1

blades

2

vanes

8th

radially outer outer pin

9

inner ring

9.1

the stator blades facing lateral surface

9.2

the side walls facing away from the vanes

9.3

groove

9.4

Residual cross-section

10

Inner ring segment

13

seal carrier

14

Seal carrier segment

15

inlet lining

Claims (12)

Inner ring (9) for a vane ring with adjustable guide vanes (2) of a turbomachine,
marked by
at least one groove (9.3), which is arranged on a side facing away from the vanes lateral surface (9.2) of the inner ring. Inner ring according to claim 1, characterized in that at least one groove is arranged between two guide blade receptacles on the lateral surface of the inner ring facing away from the guide vanes. Inner ring according to one of the preceding claims, characterized in that at least one arranged on the side facing away from the vanes lateral surface of the inner ring groove extends, at least substantially, in the axial direction. Inner ring according to one of the preceding claims, characterized in that at least one arranged on the side facing away from the vanes lateral surface of the inner ring groove is open or closed on one or both end faces. Inner ring according to one of the preceding claims, characterized in that at least one arranged on the side facing away from the vanes lateral surface of the inner ring groove in a cross section perpendicular to the axial direction has a, at least substantially, U-shaped or V-shaped cross-section. Inner ring according to one of the preceding claims, characterized in that at least one arranged on the side facing away from the vanes lateral surface of the inner ring groove is filled material-free or at least partially filled with a highly heat-conductive material. Inner ring according to one of the preceding claims, characterized in that a plurality of arranged on the side facing away from the vanes lateral surface of the inner ring grooves, in particular at least substantially equidistantly, are arranged distributed over the circumference of the inner ring. Inner ring according to the preceding claim, characterized in that at least one groove is arranged between each two adjacent guide blade receptacles, guide blade receiving pairs or Leitschaufelaufnahetrippeln, on the side facing away from the vanes lateral surface of the inner ring. Inner ring according to one of the preceding claims, characterized in that the inner ring is formed in one or more parts. Guide vane ring with adjustable guide vanes for a turbomachine, comprising an inner ring according to one of the preceding claims, characterized by a seal carrier (13), which covers at least one on the side facing away from the vanes lateral surface of the inner ring groove, in particular the front side. Turbomachine, in particular gas turbine, in particular gas turbine engine, with at least one vane ring according to the preceding claim or an inner ring according to claim 1 or a claim relating thereto. A method for producing an inner ring according to claim 1 or a claim based thereon, wherein on the side facing away from the vanes lateral surface of the inner ring at least one groove, in particular machined, is formed.

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