GUIDE VANE ASSEMBLY FOR A TURBOMACHINE, COMPRESSOR MODULE, TURBOMACHINE, AND METHOD FOR PRODUCING A GUIDE VANE ASSEMBLY

Abstract

The invention relates to a guide vane assembly for a turbomachine, comprising a guide vane, which has a guide vane airfoil; and a guide vane holder. The guide vane is mounted in the guide vane holder such that the guide vane can be moved about an axis of rotation. For this purpose, the guide vane has at least one axle element, which is inserted into the guide vane holder in such a way that an outer lateral surface of the axle element faces an inner lateral surface of the guide vane holder. A protective coating is applied to at least parts of the guide vane airfoil. A protective coating is applied to at least one of the lateral surfaces. The invention also relates to a compressor module, a turbomachine, and a method for producing a guide vane assembly.

Claims

1. A guide vane assembly for a turbomachine, comprising a guide vane having a guide vane airfoil, and a guide vane holder, in which the guide vane is mounted adjustably about an axis of rotation, for which reason, the guide vane has at least one axle element that is inserted in the guide vane holder in such a way that an outer lateral surface of the axial element is facing an inner lateral surface of the guide vane holder, wherein a protective coating is applied onto the guide vane airfoil, at least in regions, and wherein a protective coating is applied onto at least one of the lateral surfaces.

2. The guide vane assembly according to claim 1, wherein the protective coatings of the guide vane airfoil and the at least one lateral surface are identical.

3. The guide vane assembly according to claim 1, wherein the protective coating of the at least one lateral surface is applied onto the inner and the outer lateral surfaces.

4. The guide vane assembly according to claim 1, wherein the protective coating of the at least one lateral surface is applied exclusively onto the inner lateral surface.

5. The guide vane assembly according to claim 2, wherein the protective coating of the at least one lateral surface is applied onto the inner and the outer lateral surfaces and in which the entire guide vane is provided with a protective coating.

6. The guide vane assembly according to claim 1, wherein the protective coating of the at least one lateral surface is applied exclusively onto the outer lateral surface.

7. The guide vane assembly according to claim 1, wherein at least one of the protective coatings has a galvanic or chemical layer, or in which at least one of the protective coatings has a layer deposited from the vapor phase.

8. The guide vane assembly according to claim 1, wherein at least one of the protective coatings has a thermally sprayed layer.

9. The guide vane assembly according to claim 1, wherein the guide vane holder is a recess in a housing segment and the axle element is bushless and being configured and arranged to be mounted in direct contact in the guide vane holder.

10. The guide vane assembly according to claim 1, wherein the axle element is a journal, which lies radially inside when referred to a longitudinal axis of the turbomachine.

11. The guide vane assembly according to claim 1, wherein the axle element is a shaft, which lies radially outside when referred to a longitudinal axis of the turbomachine.

12. A compressor module having at least one housing segment, wherein at least one guide vane holder is formed, as well as a guide vane assembly according to claim 1.

13. A turbomachine, having a compressor module according to claim 12.

14. A method for producing a guide vane assembly according to claim 1, wherein the protective coating is applied, at least in regions, onto the guide vane airfoil, and wherein the protective coating is applied onto at least one of the lateral surfaces.

15. The method according to claim 14, wherein the protective coating is applied onto the outer lateral surface, and is done simultaneously with the application of the protective coating onto the guide vane airfoil.

16. The guide vane assembly according to claim 2, wherein the protective coating of the at least one lateral surface is applied exclusively onto the inner lateral surface and the entire guide vane is provided with a protective coating.

17. The turbomachine according to claim 13, wherein the turbomachine is an aircraft engine.

18. A method for producing a guide vane assembly according to a compressor module according to claim 12, wherein the protective coating is applied, at least in regions, onto the guide vane airfoil, and wherein the protective coating is applied onto at least one of the lateral surfaces.

19. A method for producing a guide vane assembly according a turbomachine according to claim 13, wherein the protective coating is applied, at least in regions, onto the guide vane airfoil, and wherein the protective coating is applied onto at least one of the lateral surfaces.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The invention will be explained in more detail in the following on the basis of an example of embodiment, wherein the individual features in the scope of the independent claims can also be essential to the invention in other combinations, and wherein also no distinction is made individually between the different claim categories.

[0022] Taken individually,

[0023] FIG. 1 shows a schematic view of a turbofan engine in a longitudinal section;

[0024] FIG. 2 shows a guide vane assembly according to the invention;

[0025] FIG. 3 shows a view of a detail of FIG. 2.

DESCRIPTION OF THE INVENTION

[0026] FIG. 1 shows a turbomachine 1 in section, specifically a jet engine (turbofan engine). The turbomachine 1 is functionally 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 several modules; the compressor 1a is presently composed of a low-pressure compressor module 1aa and a high-pressure compressor module lab. Each compressor module 1aa, lab is in turn constructed from a plurality of stages; each stage is usually composed of a rotating blade ring and a guide vane ring following thereon. During operation, with reference to a longitudinal axis 2, the compressor gas 3, air in the present case, flows through the compressor 1a axially, and does so in a compressor gas channel 4. In this way, the compressor gas 3 is compressed, then kerosene is mixed with it in the combustion chamber 1b, and this mixture is combusted.

[0027] FIG. 2 shows a guide vane assembly 20 having a guide vane 21 and guide vane holders 22. The guide vane 21 comprises a guide vane airfoil 31, the latter having a leading edge 31.1 and a trailing edge 31.2, as well as two lateral surfaces 31.3, 31.4 that join together the leading edge 31.1 and the trailing edge 31.2. Further, the guide vane 21 has two axle elements 25, namely a radially inner journal 26 and a radially outer shaft 27. In this mounting arrangement, the guide vane 21 is rotatable about an axis 28, so that an inflow angle 29 of the guide vane airfoil 31 can be changed (perpendicular to the plane of the drawing).

[0028] For example, the radially inner guide vane holder 22 can be formed in a mounting ring 35; in this example, radially outwardly, the shaft 27 is guided in two mounting rings 36. As can be seen from FIG. 2 and discussed in detail based on FIG. 3, the mounting arrangement of the axle element 25 both radially inside as well as radially outside is configured in a bushless manner; the axle elements 25 are each inserted directly into the respective holder 22. This is achieved by protective coatings 37 in the appropriate regions.

[0029] FIG. 3 shows such a protective coating 37 in detail. A section is shown wherein the sectional plane lies parallel to the axis of rotation 28 of the guide vane airfoil 21. The axle element 25 can be the journal 26 or the shaft 27. An outer lateral surface 25.1 of the axial element 25 is facing an inner lateral surface 22.1 of the holder 22. In the example shown, the holder 22 is designed without a bush, i.e., the holder does not have a slide mounting bush, but is formed directly by a recess/drill hole in a housing part. In a section lying horizontally and perpendicular to the plane of the drawing, the two lateral surfaces 25.1, 22.1 are each of circular shape.

[0030] The figure illustrates the protective coating 37; a protective layer 40 is introduced presently on the outer lateral surface 25.1, and a protective layer 40 is also introduced onto the inner lateral surface 22.1. During operation, the components rub against one another via these protective layers 40 (for the sake of clarity in the present case, a gap is depicted therebetween), the protective layers thus preventing wear. Alternatively, the inner lateral surface 22.1 may also be provided exclusively with the protective layer 40 or the outer lateral surface 25.1 may also be provided exclusively with the protective layer 40.

[0031] As can be seen from FIG. 2, the guide vane airfoil 21 is also provided with a protective coating 47. For reasons of clarity, this coating is only shown in regions, but in the present example, it extends over the entire guide vane airfoil 21. The protective coating 47, like the protective coating 37, can be composed of a galvanic layer 50, a layer 51 deposited from the vapor phase, and/or a thermally sprayed layer 52, for example. In one variant, the guide vane airfoil 21 and the axle elements 25 have an identical protective coating; in particular, the entire guide vane 21 can possess the same protective coating.