GUIDE VANE RING FOR A TURBOMACHINE, TURBOMACHINE AND METHOD FOR MOUNTING A GUIDE VANE RING

Abstract

The invention relates to a guide vane ring for a turbomachine comprising at least one guide vane, at least one bearing body, and at least two inner ring segments. The guide vane has a bearing journal that is arranged in a in form-fitting manner in a bearing bush of the at least one bearing body. The at least two inner ring segments have on their respective outer radial faces a guide channel running along a circumferential direction of the guide vane ring for receiving the bearing body, into which project at least two opposite-lying guide projections of the inner ring segments, said projections running along the circumferential direction of the guide vane ring. The bearing bodyis arranged in the guide channel of the inner ring segments, and the at least two guide projections of the inner ring segments engage in at least two guide grooves of the bearing body.

Claims

1. A guide vane ring for a turbomachine comprising at least one guide vane , at least one bearing body, and at least two inner ring segments, wherein the guide vane has a bearing journal that is arranged in a form-fitting manner in a bearing bush of the at least one bearing body; the at least two inner ring segments have on their respective outer radial faces a guide channel running along a circumferential direction of the guide vane ring for receiving the bearing body , into which project at least two opposite-lying guide projections of the inner ring segments, said projections running along the circumferential direction of the guide vane ring; the bearing body is arranged in the guide channel of the inner ring segments, and the at least two guide projections of the inner ring segments engage in at least two guide grooves of the bearing body or engage through these, wherein the bearing journal of the guide vane has at least one journal groove, into which at least one of the guide projections of the inner ring segment engages.

2. The guide vane ring according to claim 1, wherein the journal groove runs around a lengthwise axis of the bearing journal.

3. The guide vane ring according to claim 2, wherein a journal groove radius of the bearing journal in the lengthwise region of the respective journal groove is at most half as large as a journal radius outside the journal groove .

4. The guide vane ring according to claim 1, wherein the bearing journal has an inner guide vane plate and an outer guide vane plate , which are separated by the journal groove.

5. The guide vane ring according to claim 2, wherein, on one axial end of the bearing journal, the bearing journal has a bore running parallel to the lengthwise axis of the bearing journal, said bore receiving a pin of the bearing body.

6. The guide vane ring according to claim 1, wherein the inner ring segments have a central point angle of 30 degrees, 45 degrees, 60 degrees, 90 degrees or 180 degrees.

7. The guide vane ring according to claim 1, wherein the bearing body is composed, at least partially, of metal and/or a carbon.

8. The guide vane ring according to claim 1, wherein sealing bodies are arranged on the inner radii of the inner ring segments.

9. A turbomachine comprising at least one guide vane ring according to claim 1.

10. A method for mounting a guide vane ring for a turbomachine according to claim 1, comprising the following steps: arranging in a form-fitting manner a bearing journal of a guide vane in a bearing bush of a bearing body; threading of the bearing body in a guide channel running along a circumferential direction of the guide vane ring on an outer radial face of an inner ring segment, wherein at least two opposite-lying guide projections of the inner ring segment running along the circumferential direction of the guide vane ring and projecting into the guide channel are guided into at least two guide grooves of the bearing body; guiding the at least two guide projections of the inner ring segment into a journal groove of the bearing journal of the guide vane; and arranging the inner ring segments together to form an inner ring.

Description

BRIEF DESCRIPTION OF THE DRAWING FIGURES

[0029] Additional features of the invention result from the claims and the exemplary embodiments. The features and combinations of features named above in the description, as well as the features and combinations of features named below in the exemplary embodiments, and/or the features and combination of features shown alone can be used not only in the respectively indicated combination, but also in other combinations or alone, without departing from the scope of the invention. Thus, embodiments that are not explicitly shown and explained in the embodiment examples, but proceed from the explained embodiments and can be produced by separate combinations of features, are also to be viewed as comprised and disclosed by the invention. Embodiments and combination of features that thus do not have all features of an originally formulated independent claim are also to be viewed as disclosed. Herein:

[0030] FIG. 1 shows a schematic cross section through a guide vane ring;

[0031] FIG. 2 shows another illustration of the guide vane ring of FIG. 1;

[0032] FIG. 3 shows a schematic three-dimensional view, which represents an arrangement of the bearing body in the inner ring segment;

[0033] FIG. 4 shows the position of the guide projections of the inner ring segments in the journal groove;

[0034] FIG. 5 shows how the guide projections of the inner ring segment engage in the guide groove of the guide vane and the guide grooves of the bearing body; and

[0035] FIG. 6 shows a flow chart of a method for mounting a guide vane ring for a turbomachine.

DESCRIPTION OF THE INVENTION

[0036] FIG. 1 shows a schematic cross section through a guide vane ring. The schematically shown guide vane ring 2 can involve the guide vane ring 2 of a turbomachine 1, wherein the turbomachine 1 can involve, in particular, a turbine of an aircraft. The guide vane ring 2 can be provided for the purpose of influencing the course of a flow of air, so that it strikes rotating blades of a rotating blade ring of the turbomachine 1 at a predetermined angle. The guide vane ring 2 can have at least one guide vane 3, which can be arranged in a bearing body 4. The bearing body 4 can be provided for the purpose of making possible a bearing of the guide vane 3 in an inner ring segment 6 of an inner ring 5 of the guide vane ring 2. The inner ring 5 of the guide vane ring 2 can be provided for the purpose of mechanically stabilizing the guide vanes 3 of the guide vane ring 2 in an inner region of the turbomachine 1. In order to minimize any efficiency loss due to leakage flow, it can be provided that a space 7 between the inner ring 5 and a rotor component 8 is sealed by an inner ring sealing means 9 and a sealing body 10 of the inner ring 5. In order, on the one hand, to prevent a reduction of the leakage flow in the space 7 as well as friction losses, which may occur due to the rubbing of the inner ring sealing means 9 against the sealing body 10, it is necessary that the space 7 remains constant during the operation of turbomachine 1. Based on so-called cording, a change in the curvature of the inner ring 5 during the operation can lead to the circumstance that the space 7 increases during the operation and thus a loss in efficiency occurs due to the greater leakage flow between the inner ring 5 and the rotor component 8. In the case when the space 7 between the inner ring 5 and the rotor component 8 decreases, losses in efficiency can also occur due to rubbing between the inner ring sealing means 9 and the sealing body 10. So-called cording can be produced, for example, by a reduction in an inner angle of the inner ring segment 6 of the inner ring 5. It is thereby possible that an inner ring can be composed of more than two inner ring segments 6. For this, however, it is necessary to make possible a more stable arrangement of the inner ring segments 6 on the guide vanes 3. The invention provides this mechanical stabilization by making possible a direct connection of the inner ring segments 6 to the guide vanes 3.

[0037] For this purpose, it can be provided that a bearing journal 11 of the guide vane 3 has a journal groove 12, which can run around the bearing journal 11. In this case, the bearing journal 11 can be configured in such a way that a journal radius 13 of the bearing journal 11 in an axial region outside the journal groove 12 is twice as large as a journal groove radius 14 within an axial region of the journal groove 12. The bearing journal 11 can be arranged in a bearing bush 20 of the bearing body 4. In order to make possible an optimal arrangement of the bearing journal 11 in the bearing body 4, the bearing body 4 can have a guide pin 16 that can engage in a bore 17 of the bearing journal 11. The bore 17 can run parallel to the axis of the bearing journal. In order to make possible an arrangement of the bearing body 4 in the inner ring segment 6, the inner ring segment 6 can have a guide channel 18, which can run along a circumferential direction around the inner ring 5 of the guide vane ring 2. Two opposite-lying guide projections 19 of the inner ring segment 6 can project into the guide channel 18. In an assembled state, the bearing body 4 with the bearing journal 11 can be arranged in the guide channel 18 in such a way that the two guide projections 19 of the inner ring segment 6 engage in both the guide grooves 15 of the bearing body 4 and in the journal groove 12 of the bearing journal 11 of the guide vane 3. In this way, a direct mechanical connection exists between the guide vane 3 and the inner ring segment 6, so that a mechanically more stable bearing of the inner ring segments 6 of the guide vanes 3 is made possible. It is possible in this way to reduce the size of the inner ring segments 6, so that the latter enclose a central point angle, for example, of 30 degrees, 45 degrees, 60 degrees, 90 degrees, or 180 degrees. By way of the journal groove 12 of the bearing journal 11, the bearing journal 11 can have two plates 21, 22, whereby these can involve an inner plate 22 and an outer plate 21. In this case, in the axial direction, the inner plate 22 can be arranged closer to the inner ring 5, whereas the outer plate 21, also in the axial direction, can be arranged closer to the guide vane 3. The plates 21, 22 can be round in order to make possible a rotation of the guide vane 3 in the bearing body 4. The bearing body 4 may contain carbon and/or metal.

[0038] FIG. 2 shows another illustration of the guide vane ring of FIG. 1.

[0039] FIG. 3 shows a schematic three-dimensional view, which represents an arrangement of the bearing body in the inner ring segment;

[0040] FIG. 4 shows the position of the guide projections 19 of the inner ring segments 6 in the journal groove 12, in order to make possible a bearing of the guide vane 3 in the inner ring segment 6. In FIG. 4 it can be recognized how the guide projections 19 of the inner ring segment 6 engage in the bearing body 4 at the guide grooves 15, in order to stabilize these projections in the guide channel 18. The bearing bush 20 of the bearing body 4 with a round opening can also be recognized, as seen in FIG. 5, and this makes possible a rotation of the guide vane 3.

[0041] FIG. 5 shows how the guide projections 19 of the inner ring segment 6 engage in the guide groove 12 of the bearing journal 11 of the guide vane 3 and in the guide grooves 15 of the bearing body 4, in order to fasten the guide vane 3 and the bearing body 4 in the guide channel 18.

[0042] FIG. 6 shows a flow chart of a method for mounting a guide vane ring for a turbomachine. It is provided that in a first step P1 of the method, the bearing journal 11 of the guide vane 3 is arranged in a form-fitting manner in the bearing bush 20 of a bearing body 4.

[0043] In a second step P2, the bearing body 4 can be threaded in the guide channel 18 running along the circumferential direction of the guide vane ring 2 on an outer radial face of an inner ring segment 6. In this way, the at least two opposite-lying guide projections 19 of the inner ring segment 6 running along the circumferential direction of the guide vane ring 2 and projecting into the guide channel 18 can be guided into the at least two guide grooves 15 of the bearing body 4. The at least two guide projections 19 of the inner ring segment 6 can be guided at the same time into the journal groove 12 of the bearing journal 11 of the guide vane 3.

[0044] In a third step P3, the inner ring segments 6 can be arranged together to form an inner ring 5.

[0045] In the prior art, in fact, the reduction of the guide vane plate leakage as well as the possible miniaturizing of the geometry for future small compressor sizes has been achieved, but not the problem of cording, the de-curving or the overcurving of the inner ring/half ring. The cording can lead to strong gap fluctuations in the region of the separating planes of the inner ring 5. These gap fluctuations lead to a drop in efficiency when the gap is opened up due to increased leakages, or due to an overload of the shrinkability of the inner ring sealing means 9 with increased closing of the gap.

[0046] In the concept described here, the inner ring segment 6 used as a seal carrier not only joins together the bearing bodies 4 by way of the guide grooves 15, but simultaneously joins the plates 21, 22 of the guide vanes 3. This means that when the seal carrier is threaded on the bearing body 4, the guide projections 19 or hooks of the seal carrier also penetrate the journal groove 12, which was made in the plate or the bearing journal 11 of the guide vane 3. The seal carrier is thus joined radially with the bearing journal 11 of the guide vane 3 and is guided and controlled in its radial position over the guide vane 3 by the outer housing (usually by a split case). The seal carrier thus no longer absolutely needs to be a half ring, but can also be divided into smaller segments that have less cording.