EP3885536B1 - Gas turbine component - Google Patents

Description

The present invention relates to a gas turbine component, in particular a guide vane cluster, with at least one radial flange with a radial groove for spoke centering of a gas turbine element, in particular an inner ring, as well as a gas turbine assembly and a gas turbine with the gas turbine component.

Spoke centerings of inner rings on guide vane clusters of gas turbines are known from in-house practice, with webs of the inner rings engaging in radial grooves of radial flanges of the guide vane clusters. The present invention is particularly suitable for such spoke centerings, but is not limited to this, but can also be used to advantage in other spoke centerings of gas turbine components and elements.

A guide vane cluster with a radial groove is, for example, from the EP2696039A1 known.

From the WO0212680A1 A suspension with a sliding guide with a linear direction of movement that is at an angle to the radial direction is known.

The object of the present invention is to improve spoke centering of gas turbine components.

This object is achieved by a gas turbine component with the features of claim 1. Claims 9, 10 protect a gas turbine assembly with at least one gas turbine component described here and a gas turbine with at least one gas turbine component described here, in particular with at least one gas turbine assembly described here. Advantageous embodiments of the invention are the subject of the subclaims.

According to the present invention, a gas turbine component has at least one radial flange with a radial groove, which is provided, in particular designed, or used for spoke centering of a gas turbine element. Accordingly, a web of the gas turbine element engages in the radial groove, in one embodiment in a form-fitting and/or axial manner, or the web extends through the radial groove, in particular axially.

In one embodiment, "axial" refers to a direction parallel to a rotational or (main) machine axis of the gas turbine, a circumferential direction corresponding to a rotational or circumferential direction around this rotational or (main) machine axis of the gas turbine, and "radial" refers to a direction perpendicular to the axial and circumferential direction, in particular away from the rotational or (main) machine axis of the gas turbine or a coordinate (axis) direction that perpendicularly intersects the rotational or (main) machine axis of the gas turbine.

In one embodiment, the radial flange and the radial groove thus extend in the radial direction, wherein in one embodiment the radial flange extends or protrudes radially inward from the gas turbine component and/or the radial groove is (a) open radially inward.

In one embodiment, the gas turbine component is formed in one or more parts and/or a guide vane cluster with one or more guide vanes, in particular one after the other in the circumferential direction, and/or the gas turbine element is formed in one or more parts and/or an inner ring, in particular a sealing ring with a seal for sealing against a rotor of the gas turbine ("inner air seal").

According to the present invention, the radial groove has a first groove flank, a groove base adjoining it (in the circumferential direction) and a second groove flank adjoining it (in the circumferential direction). In one embodiment, the two groove flanks fix the web of the gas turbine element in the circumferential direction or serve to secure it in the circumferential direction or circumferentially or are provided for this purpose, in particular designed or are used for this purpose. Accordingly, the In one design, both groove flanks have stops in the circumferential direction and/or the groove base has a stop in the radial direction.

According to one embodiment of the present invention, the first and second groove flanks run parallel to one another (in sections, over at least 60% or at least 70% of their radial length or completely) and/or define parallel planes. This can be particularly advantageous for radial guidance and for spoke centering.

According to one embodiment of the present invention, a groove width or a groove depth, in particular a mean, maximum or minimum groove depth, is at least as large or at least 1.5 times as large as a distance, in particular a mean, maximum or minimum distance, in the circumferential direction between the first and the second groove flank. This can enable radial guidance on a specific radial section and can be particularly advantageous for spoke centering.

Additionally or alternatively, according to an embodiment of the present invention, a groove width or a groove depth, in particular an average, maximum or minimum groove depth, is at most three times as large or at most 2.5 times as large as a distance, in particular an average, maximum or minimum distance, in the circumferential direction between the first and the second groove flank.

According to the present invention, a center plane extends radially or in the radial direction and perpendicular to the circumferential direction, in one embodiment containing the rotary or (main) machine axis of the gas turbine, as well as centrally between these two groove flanks, in one embodiment such that the center plane has the same, in particular minimum, maximum and/or average, distance to the first and second groove flanks in the circumferential direction at at least one radial height, in one embodiment several radial heights, in particular over at least one radial section. In one embodiment, the first and/or second groove flanks have at least one flat section and the center plane has the same, in particular minimum, maximum and/or average, distance to the first and second groove flanks in the circumferential direction at at least one radial height of these flat sections. in particular minimum, maximum and/or average distance to the first and second groove flank.

According to the present invention, the groove base is asymmetrical to this center plane (formed, in particular contoured), in particular in the circumferential direction (seen) or in at least one meridian section.

In one embodiment, this advantageously makes it possible to bring about an asymmetrical stress distribution in the gas turbine component, in particular its radial flange, and thus, in one embodiment, peak stresses can be reduced and/or advantageously distributed.

In one embodiment, the radial groove is offset or arranged off-center in the circumferential direction, in one embodiment by at least one, in particular minimum, maximum or average, groove width, from a center of the gas turbine component in the circumferential direction.

In this way, in a design in combination with the asymmetrical groove base, a particularly advantageous stress distribution, in particular stress reduction, can be achieved.

In one embodiment, a minimum radius of curvature of a transition region from the first groove flank to the groove base is larger than a minimum radius of curvature of a transition region from the groove base to the second groove flank, in one embodiment by at least 5%, in particular by at least 10%, in one embodiment by at least 15% larger. In one embodiment, the second groove flank is spaced further in the circumferential direction from a center of the gas turbine component in the circumferential direction than the first groove flank.

Such an asymmetry can be used to achieve a particularly advantageous stress distribution, in particular stress reduction, in one embodiment.

Additionally or alternatively, in one embodiment, a transition region from the first groove flank to the groove base and/or a transition region from the groove base to the second groove flank (each) has a varying curvature, in particular a free-form contour.

In this way, a particularly advantageous stress distribution, in particular stress reduction, can be realized in one embodiment.

In one embodiment, at least one tangent (to the groove base), in particular in at least one meridian section, at a point on the groove base, in particular an intersection point of the groove base with the center plane, encloses an angle with the center plane which is less than 90° and greater than 0°, in one embodiment at most 88°, in particular at most 85°, in one embodiment at most 80°, and/or at least 60°, in particular at least 70°, in one embodiment at least 75°.

In this way, a particularly advantageous stress distribution, in particular stress reduction, can be realized in one embodiment.

In one embodiment, the radial flange has a first outer flank adjacent to the first groove flank in the circumferential direction and a second outer flank adjacent to the second groove flank, each of which merges into a lateral surface of the gas turbine component. Thus, in one embodiment, the radial flange has two radial projections that follow one another in the circumferential direction, in particular projections that project radially inward, which each have or form one of the two outer flanks and one of the two groove flanks, in particular a first radial projection with the first outer flank and the first groove flank and a second radial projection with the second outer flank and the second groove flank.

In one embodiment, a minimum radius of curvature of a transition region from the lateral surface to one, in one embodiment, first, outer flank is greater than a minimum radius of curvature of a transition region from the other or second outer flank into the lateral surface, in one embodiment by at least 5%, in particular by at least 10%, in one embodiment by at least 15% larger.

As a result, in an embodiment in combination with the asymmetrical groove base, a particularly advantageous stress distribution, in particular stress reduction, can be realized, particularly advantageously if both the first groove flank and the first outer flank adjacent to it or arranged on the same (first) projection have transition regions with larger minimum radii of curvature than the second groove flank and the second outer flank adjacent to it or arranged on the same (second) projection.

Additionally or alternatively, in one embodiment, a or the transition region from the lateral surface to the first outer flank and/or a or the transition region from the second outer flank to the lateral surface (each) has a varying curvature, in particular a free-form contour.

In this way, a particularly advantageous stress distribution, in particular stress reduction, can be realized in one embodiment.

Fig. 1

eine Gasturbinenbaugruppe mit einem Gasturbinenbauteil nach einer Ausführung der vorliegenden Erfindung.

Further advantageous developments of the present invention emerge from the subclaims and the following description of preferred embodiments. In this regard, the only one shows, partially schematically:

Fig.1

a gas turbine assembly with a gas turbine component according to an embodiment of the present invention.

Fig.1 shows a gas turbine assembly with a gas turbine component according to an embodiment of the present invention in the form of a guide vane cluster 10 with several guide vanes 11 and a radially inward (downward in Fig.1 ) projecting radial flange with a through two (radially inward or Fig.1 radial groove 20 formed by projections 12, 13 projecting downwards, with a first groove flank 21, an adjoining groove base 23 and an adjoining second groove flank 22 for spoke centering (of a web 110) of a gas turbine element in Form of an inner ring 100, which in Fig.1 For clarity, it is shown pulled out or spaced radially inwards or downwards, whereby in the assembled state the web 110 engages in the radial groove 20 for spoke centering.

With A, R and U are in Fig.1 the axial direction (A), radial direction (R) or circumferential direction (U) are indicated.

Dash-dotted lines are in Fig.1 a central plane M is drawn, which extends radially (vertically in Fig.1 ) and perpendicular to the circumferential direction, ie vertical and perpendicular to the plane of the Fig.1 , and from the two groove flanks 21, 22 in Fig.1 lower section has the same distance a and thus extends centrally between them.

The radial groove 20 is offset in the circumferential direction by more than a groove width 2·a from the center of the guide vane cluster 10, wherein the second groove flank 22 is spaced further in the circumferential direction from the center of the guide vane cluster than the first groove flank 21.

A minimum radius of curvature R1 of a transition region from the first groove flank 21 to the groove base 23 has a varying curvature, in the exemplary embodiment a free-form contour, and is larger than a minimum radius of curvature R2 of a transition region from the groove base 23 to the second groove flank 22, wherein this transition region from the groove base 23 to the second groove flank 22 also has a varying curvature, in the exemplary embodiment a free-form contour.

Likewise, a minimum radius of curvature R11 of a transition region from a radially inner lateral surface 14 of the guide vane cluster into a (first) outer flank 12A of the first projection 12 has a varying curvature, in the exemplary embodiment a free-form contour, and is larger than a minimum radius of curvature R12 of a transition region from a (second) outer flank 13A of the second projection 13 into the lateral surface 14, wherein this transition region from the second outer flank 13A into the lateral surface 13 also a varying curvature, in the embodiment a free-form contour.

In the Fig.1 The tangent T drawn at an intersection point S of the groove base 23 with the median plane M forms an angle α with the median plane which is less than 90° and greater than 0°.

Accordingly, the groove base 23 is asymmetrical to the center plane M (formed).

Although exemplary embodiments have been explained in the preceding description, it should be noted that a large number of modifications are possible. It should also be noted that the exemplary embodiments are merely examples that are not intended to limit the scope of protection, applications and structure in any way. Rather, the preceding description provides the person skilled in the art with a guide for implementing at least one exemplary embodiment, whereby various changes, in particular with regard to the function and arrangement of the described components, can be made without departing from the scope of protection as defined by the claims.

List of reference symbols

10

Guide vane cluster (gas turbine component)

11

vane

12

(first) lead

12A

first outer flank

13

(second) lead

13A

second outer flank

14

Shell surface

20

Radial groove

21

first groove flank

22

second groove flank

23

Groove base

100

Inner ring (gas turbine element)

110

web

M

Middle level

R1

Minimum curvature radius transition area first groove flank-groove base

R2

Minimum curvature radius transition area groove base-second groove flank

R11

Minimum radius of curvature transition area lateral surface-first outer flank

R12

minimum radius of curvature transition area second outer flank-surface

S

Intersection

T

tangent

α

angle

Claims (10)

1. Gas turbine component, in particular a guide vane cluster (10), comprising at least one radial flange (12, 13) having a radial groove (20) for spoke-centering of a gas turbine element, in particular an inner ring (100), in which spoke-centering a web (100) of the gas turbine element engages into the radial groove or engages through the radial groove, the radial groove (20) comprising a first groove flank (21), an adjoining groove base (23) and an adjoining second groove flank (22), characterized in that the groove base (23) is asymmetrical to a central plane (M) which extends radially and perpendicularly to the circumferential direction and centrally between the two groove flanks (21, 22).
2. Gas turbine component according to claim 1, characterized in that the radial groove is offset in the circumferential direction, in particular by at least one groove width (2·a), from a center of the gas turbine component in the circumferential direction.
3. Gas turbine component according to any of the preceding claims, characterized in that the second groove flank (22) is spaced further in the circumferential direction from a center of the gas turbine component in the circumferential direction than the first groove flank (21).
4. Gas turbine component according to any of the preceding claims, characterized in that a minimum radius of curvature (R1) of a transition region from the first groove flank (21) into the groove base (23) is greater, in particular by at least 5%, than a minimum radius of curvature (R2) of a transition region from the groove base (23) into the second groove flank (22).
5. Gas turbine component according to any of the preceding claims, characterized in that a transition region from the first groove flank (21) into the groove base (23) and/or a transition region from the groove base (23) into the second groove flank (22) has a varying curvature, in particular a free-form contour.
6. Gas turbine component according to any of the preceding claims, characterized in that at least one tangent (T) at a point of the groove base (23), in particular a point of intersection (S) of the groove base (23) with the central plane (M), forms an angle (α) with the central plane (M) which is less than 90° and greater than 0°.
7. Gas turbine component according to any of the preceding claims, characterized in that the radial flange (12, 13) comprises, in the circumferential direction, a first outer flank (12A) adjacent to the first groove flank (21) and a second outer flank (13A) adjacent to the second groove flank (22), which each transition into a lateral surface (14) of the gas turbine component.
8. Gas turbine component according to the preceding claim,
   characterized in that a minimum radius of curvature (R12) of a transition region from the lateral surface (14) into one, in particular the first, outer flank (12A) is greater, in particular by at least 5%, than a minimum radius of curvature (R12) of a transition region from the other, in particular the second, outer flank (13A) into the lateral surface (14), and/or a transition region from the lateral surface (14) into the first outer flank (12A) and/or a transition region from the second outer flank (13A) into the lateral surface (14) has a varying curvature, in particular a free-form contour.
9. Gas turbine assembly having a gas turbine component (10) according to any of the preceding claims and a gas turbine element, in particular an inner ring (100), having a web (110) for spoke-centering at the radial groove (20) of the gas turbine component.
10. Gas turbine, in particular an aircraft engine gas turbine, having at least one gas turbine component, in particular at least one gas turbine assembly, according to any of the preceding claims.

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