Gas turbine component

Abstract

A gas turbine component, in particular a stator vane cluster (10), having at least one radial flange (12, 13) with a radial slot (20) for spoke-type centering of a gas turbine element, in particular an inner ring (100), the radial slot (20) having a first slot flank (21), a slot base (23) adjoining the same, and a second slot flank (22) adjoining the same, the slot base (23) being asymmetric with respect to a mid-plane (M) which extends radially and perpendicularly to the circumferential direction and centrally between the two slot flanks (21, 22).

Claims

1. A gas turbine component comprising: at least one radial flange with a radial slot for spoke centering of a gas turbine element, the radial slot having a first slot flank, a slot base adjoining the first slot flank, and a second slot flank adjoining the slot base, the slot base being asymmetric with respect to a mid-plane extending radially and perpendicularly to a circumferential direction and centrally between the first and second slot flanks.

2. The gas turbine component as recited in claim 1 wherein the radial slot is offset in the circumferential direction from a middle of the gas turbine component by at least one slot width defined by a distance between the first and second flanks.

3. The gas turbine component as recited in claim 1 wherein the second slot flank is spaced in the circumferential direction further away from a middle of the gas turbine component than the first slot flank.

4. The gas turbine component as recited in claim 1 wherein a first minimum radius of curvature of a first transition region from the first slot flank into the slot base is greater than a second minimum radius of curvature of a second transition region from the slot base into the second slot flank.

5. The gas turbine component as recited in claim 4 wherein the first minimum radius of curvature is greater that the second minimum radius of curvature by at least 5%.

6. The gas turbine component as recited in claim 1 wherein a first transition region from the first slot flank into the slot base or a second transition region from the slot base into the second slot flank has a varying curvature.

7. The gas turbine component as recited in claim 1 wherein at least one tangent at a point of the slot base forms an angle less than 90° and greater than 0° with the mid-plane.

8. The gas turbine component as recited in claim 7 wherein the point is at an intersection of the slot base with the mid-plane.

9. The gas turbine component as recited in claim 1 wherein the radial flange has a first outer flank adjacent to the first slot flank in the circumferential direction and a second outer flank adjacent to the second slot flank in the circumferential direction, each of the first and second outer flanks merging into a circumferential surface of the gas turbine component.

10. The gas turbine component as recited in claim 9 wherein a first minimum radius of curvature of a first transition region from the circumferential surface into the first outer flank is different than a second minimum radius of curvature of a second transition region from the second outer flank into the circumferential surface.

11. The gas turbine component as recited in claim 10 wherein the minimum radius of curvature is greater than the second minimum radius of curvature.

12. The gas turbine component as recited in claim 9 wherein a first transition region from the circumferential surface into the first outer flank or a second transition region from the second outer flank into the circumferential surface has a varying curvature.

13. The gas turbine component as recited in claim 12 wherein the gas turbine element is an inner ring.

14. A stator vane cluster comprising the gas turbine component as recited in claim 1.

15. The stator vane cluster as recited in claim 13 wherein the gas turbine element is an inner ring.

16. A gas turbine subassembly having a gas turbine component as recited in claim 1 and the gas turbine element.

17. The gas turbine component as recited in claim 16 wherein the gas turbine element is an inner ring with a pin for spoke centering at the radial slot of the gas turbine component.

18. A gas turbine comprising the gas turbine component as recited in claim 1.

19. An aircraft engine gas turbine comprising the gas turbine as recited in claim 18.

20. The gas turbine component as recited in claim 2 wherein the gas turbine component includes five circumferentially spaced vanes and the middle of the gas turbine component at a middle vane of the five vanes and the radial slot is radially inner of a further of the five vanes adjacent to the middle vane.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Further advantageous refinements of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. To this end, in partially schematic form, the only FIG. 1 shows a gas turbine subassembly having a gas turbine component according to an embodiment of the present invention.

DETAILED DESCRIPTION

(2) FIG. 1 depicts a gas turbine subassembly having a gas turbine component according to an embodiment of the present invention in the form of a stator vane cluster 10 including a plurality of stator vanes 11 and a radial flange projecting radially inwardly (downwardly in FIG. 1) and having a radial slot 20 which is formed by two projections 12, 13 (projecting radially inwardly or downwardly in FIG. 1) and has a first slot flank 21, a slot base 23 adjoining the same, and a second slot flank 22 adjoining the same for spoke-type centering (of a pin 110) of a gas turbine element which is in the form of an inner ring 100 and which is shown in FIG. 1 in a position removed or spaced apart radially inwardly or downwardly for the purpose of illustration. In the assembled state, pin 110 engages in radial slot 20 for purposes of spoke-type centering.

(3) In FIG. 1, axial direction (A), radial direction (R), and circumferential direction (U) are indicated by A, R, and U, respectively.

(4) In FIG. 1, a mid-plane M is plotted as a dash-dot line. Mid-plane M extends radially (vertically in FIG. 1) and perpendicularly to the circumferential direction; i.e. vertically in and perpendicularly to the plane of the drawing of FIG. 1, and has the same distance “a” from the two slot flanks 21, 22 in the lower portion in FIG. 1, and thus extends centrally therebetween.

(5) Radial slot 20 is offset in the circumferential direction from the middle of stator vane cluster 10 by more than one slot width 2.Math.a, the second slot flank 22 being spaced in the circumferential direction further away from the middle of the stator vane cluster than the first slot flank 21.

(6) A minimum radius of curvature R1 of a transition region from first slot flank 21 into slot base 23 has a varying curvature, in the exemplary embodiment a free-form contour, and is greater than a minimum radius of curvature R2 of a transition region from slot base 23 into second slot flank 22, this transition region from slot base 23 into second slot flank 22 also having a varying curvature, in the exemplary embodiment a free-form contour.

(7) Similarly, a minimum radius of curvature R11 of a transition region from a radially inner circumferential surface 14 of the stator vane cluster into the a or the (first) outer flank 12A of first projection 12 has a varying curvature, in the exemplary embodiment a free-form contour, and is greater than a minimum radius of curvature R12 of a transition region from a or the (second) outer flank 13A of second projection 13 into circumferential surface 14, this transition region from second outer flank 13A into circumferential surface 14 also having a varying curvature, in the exemplary embodiment a free-form contour.

(8) The tangent T, plotted in FIG. 1, at a point of intersection S of slot base 23 with mid-plane M forms an angle α less than 90° and greater than 0° with the mid-plane.

(9) Accordingly, slot base 23 is asymmetric (configured asymmetrically) with respect to mid-plane M.

(10) Although the above is a description of exemplary embodiments, it should be noted that many modifications are possible. It should also be appreciated that the exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing at least one exemplary embodiment, it being understood that various changes may be made in the function and arrangement of elements described without departing from the scope of protection as set forth in the appended claims or derived from combinations of features equivalent thereto.

LIST OF REFERENCE CHARACTERS

(11) 10 stator vane cluster (gas turbine component) 11 stator vane 12 (first) projection 12A first outer flank 13 (second) projection 13A second outer flank 14 circumferential surface 20 radial slot 21 first slot flank 22 second slot flank 23 slot base 100 inner ring (gas turbine element) 110 pin M mid-plane R1 minimum radius of curvature of the transition region from the first slot flank into the slot base R2 minimum radius of curvature of the transition region from the slot base into the second slot flank R11 minimum radius of curvature of the transition region from the circumferential surface into the first outer flank R12 minimum radius of curvature of the transition region from the second outer flank into the circumferential surface S point of intersection T tangent α angle