LEVER FOR ADJUSTING AN ADJUSTABLE VANE

Abstract

The present invention relates to a lever for adjusting an adjustable vane of a turbomachine, wherein the lever has a fulcrum for the rotatable mounting of the lever about an axis of rotation, a first load arm with a first adjusting connection point for at least indirect connection to an adjustable vane and a first force arm with a first actuating connection point for connection to an adjusting device, wherein the lever further has a first strut, which connects the first adjusting connection point and the first actuating connection point to each other and thereby extends in an arc-shaped manner about the axis of rotation.

Claims

1. A lever for adjusting an adjustable vane of a turbomachine, comprising: a lever having a fulcrum for the rotatable mounting of the lever around an axis of rotation, a first load arm with a first adjusting connection point for at least indirect connection to the adjustable vane, and a first force arm with a first actuating connection point for connection to an adjusting device, wherein the lever further has a first strut, which connects the first adjusting connection point and the first actuating connection point to each other and thereby extends in an arc-shaped manner around the axis of rotation.

2. The lever according to claim 1, wherein the first arc-shaped strut, as viewed in the axial direction with respect to the axis of rotation, extends tangentially into the first adjusting connection point.

3. The lever according to claim 1, wherein the first arc-shaped strut, as viewed in the axial direction with respect to the axis of rotation, extends tangentially into the first actuating connection point.

4. The lever according to claim 1, further comprising a first cross strut, which connects the fulcrum and the first arc-shaped strut to each other.

5. The lever according to claim 4, wherein, with respect to the axis of rotation, the first cross strut extends radially into the first arc-shaped strut.

6. The lever according to claim 4, wherein the first cross strut lies between the first adjusting connection point and the first actuating connection point on a central position of rotation with respect to the axis of rotation.

7. The lever according to claim 1, wherein the first load arm and the first force arm lie in a first plane.

8. The lever according to claim 1, further comprising: a second load arm with a second adjusting connection point for at least indirect connection to the adjustable vane, a second force arm with a second actuating connection point for connection to the adjusting device, and a second strut, which extends in an arc-shaped manner around the axis of rotation and connects the second adjusting connection point and the second actuating connection point to each other.

9. The lever according to claim 8, wherein the second load arm and the second force arm lie in a second plane, which is axially offset with respect to the axis of rotation and lies parallel to the first plane.

10. The lever according to claim 8, further comprising a first connecting strut, which connects the first and second arc-shaped struts to each other.

11. The lever according to claim 10, further comprising a second connecting strut, which connects the first and second arc-shaped struts to each other and crosses the first connecting strut.

12. An adjustment assembly for adjusting an adjustable vane of a turbomachine, comprising: a lever according to claim 1, a push rod, which is mounted at the first adjusting connection point, and a coupling rod, which is mounted at the first actuating connection point, wherein a displacement of the coupling rod by way of the lever is converted to a displacement of the push rod, and the displacement of the push rod is converted to an adjustment of the adjustable vane.

13. The adjustment assembly according to claim 12, wherein the first arc-shaped strut is exclusively subject to normal force.

14. A compressor or turbine module having an adjustment assembly according to claim 12 and an adjustable vane.

15. Use of a lever according to claim 1 for a jet engine.

16. The lever according to claim 5, wherein the first cross strut lies between the first adjusting connection point and the first actuating connection point on a central position of rotation with respect to the axis of rotation.

17. The lever according to claim 9, further comprising a first connecting strut, which connects the first and second arc-shaped struts to each other.

18. The lever according to claim 17, further comprising a second connecting strut, which connects the first and second arc-shaped struts to each other and crosses the first connecting strut.

19. A compressor or turbine module having an adjustment assembly according to claim 13 and an adjustable vane.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The invention is explained below in detail on the basis of an exemplary embodiment, whereby, in the scope of the dependent claims, the individual features also can be essential to the invention in other combinations and also, furthermore, no distinction is made in detail between the different claim categories.

[0026] Taken individually:

[0027] FIG. 1 shows a turbomachine in an axial section;

[0028] FIG. 2 shows an adjustment assembly for adjusting adjustable vanes in an overview depiction;

[0029] FIG. 3 shows a lever according to the invention for the adjustment assembly in accordance with FIG. 2 in a plan view;

[0030] FIG. 4 shows the lever in accordance with FIG. 3 in an oblique view; and

[0031] FIG. 5 shows the lever in accordance with FIGS. 3 and 4 in a side view.

DESCRIPTION OF THE INVENTION

[0032] FIG. 1 shows a turbomachine 1, specifically a turbofan engine, in a longitudinal section. Functionally, the turbomachine 1 is divided into a compressor 1a, a combustion chamber 1b, and a turbine 1c. Both the compressor 1a and the turbine 1c are each constructed from a plurality of stages. Each of the stages is composed of a guide vane ring 5 and a rotating blade ring 6. The reference number 7 refers to the gas duct, that is, the compressor gas duct in the case of the compressor 1a or the hot gas duct in the case of the turbine 1c. In the compressor gas duct, the air intake is compressed and then undergoes combustion with admixed kerosene in the combustion chamber 1b. The resulting hot gas flows through the hot gas duct and thereby drives the rotating blade rings 6 of the turbine 1c.

[0033] In the present example, a plurality of guide vane rings 5 of the compressor 1a are equipped with adjustable vanes 10, which can be adjusted in order to adapt the angle of attack.

[0034] FIG. 2 shows an adjustment assembly 20, which is provided for this purpose and which, among other things, has a lever 21. A load arm 22 of the lever 21 is coupled in an adjusting connection point 32 to the adjustable vanes of the respective stage, namely, by way of a push rod 25, which converts a displacement of the lever 21 to a rotational displacement of an adjustment ring 26. The adjustment ring 26 extends circumferentially around the longitudinal axis of the turbomachine 2 (not depicted in detail here) and then transmits the displacement onto each individual adjustable vane of the respective ring.

[0035] The displacement is transmitted onto the lever 21 by use of a coupling rod 27, which is part of an adjusting device 28 with an actuator 29. The coupling rod 27 couples to a force arm 23 of the lever 21 and is mounted there on an actuating connection point 33. At a fulcrum 34, the lever 21 is mounted rotatably around an axis of rotation 35.

[0036] FIG. 3 shows a lever according to the invention 21 in a plan view, namely, as viewed axially with respect to the axis of rotation 35. To be seen, furthermore, is a first force arm 23.1 with a first actuating connection point 33.1 as well as a first load arm 22.1 with a first adjusting connection point 32.1. The push rod is mounted at the latter, but is not depicted for reasons of clarity. In addition, in this case, the connection points 32.1, 33.1 are connected to each other by way of a first strut 41, which extends in an arc-shaped manner around the axis of rotation 35 and extends tangentially into the connection points 32.1, 33.1. The arc-shaped first strut 41 reduces the torque; essentially only normal forces are introduced or further transmitted. Overall, this is of advantage in regard to the level of mechanical stress, for which reason the lever 21 can be designed in a weight-reduced manner — compare the introductory description for details.

[0037] In the plan view, furthermore, a first cross strut 51 is to be seen, which connects the fulcrum 34 to the first arc-shaped strut 41 and hereby is situated radially. The first cross strut 51 supports the first arc-shaped strut 41 more or less, whereby it is likewise subject essentially only to normal forces.

[0038] FIG. 4 shows the lever 21 in an oblique view, with the components described on the basis of FIG. 3 lying in a first plane 61 (plane shown in FIG. 5). Axially offset with respect to said plane is a second plane 62 (compare likewise FIG. 5), in which a second load arm 22.2 with a second adjusting connection point 32.2 and a second force arm 23.2 with a second actuating connection point 33.2 are arranged. Furthermore, there is a second arc-shaped strut 42, which connects the second connection points 32.2, 33.2 to each other. The second arc-shaped strut 42 is connected here to the fulcrum 34 by way of a second cross strut 52.

[0039] FIG. 5 shows the lever 21 in a side view, as viewed radially with respect to the axis of rotation 35. To be seen are the first and second arc-shaped struts 41, 42, as well as the respective planes 61, 62. To be seen, furthermore, are first and second connecting struts 71, 72 (not shown in FIG. 4 for reason of clarity), each of which connects the first and second arc-shaped struts 41, 42 to each other. The connecting struts 71, 72 cross axially and also centrally with respect to a position of rotation.