ARRANGEMENT FOR A TURBINE

Abstract

An arrangement for a turbine has a metallic support structure having at least one radial support strut and a multiplicity of plate-shaped, fiber-reinforced ceramic segments which are arranged one on top of the other on the support structure and together define the circumferential contour, the segments being provided with through-openings through which the at least one support strut extends, wherein the at least one support strut has outwardly-extending projections that extend perpendicular to the radial direction and engage in corresponding recesses formed in the segments.

Claims

1.-15. (canceled)

16. An arrangement for a turbine, comprising a metal support structure, which has at least one support strut which extends in a radial direction, and a multiplicity of segments which are arranged one on top of the other on the support structure, which are of plate-like design, and which are produced from a ceramic fiber composite material, wherein the segments together define at least one part of a circumferential contour of the arrangement, wherein the segments include through-openings, through which the at least one support strut extends, wherein the at least one support strut has at least one outwardly protruding projection extending transversely to the radial direction, which projection engages in at least one correspondingly designed recess on at least one of the segments.

17. The arrangement as claimed in claim 16, wherein the support structure has a plurality of support struts, especially three support struts.

18. The arrangement as claimed in claim 16, wherein the at least one support strut has a non-round cross section.

19. The arrangement as claimed in claim 16, wherein the at least one support strut is of hollow design.

20. The arrangement as claimed in claim 16, wherein the support structure has a platform which extends basically parallel to the segments, from which the at least one support strut projects radially outward, wherein the segments are stacked on the platform.

21. The arrangement as claimed in claim 16, wherein a defined annular gap is formed between the at least one support strut and those through-openings of the segments through which this extends.

22. The arrangement as claimed in claim 16, wherein the at least one recess extends from an upper side of the respective segment.

23. The arrangement as claimed in claim 22, wherein the at least one recess is designed in the form of chamfers.

24. The arrangement as claimed in claim 16, wherein the at least one projection is accommodated, or can be accommodated, in the corresponding recess in a basically form-fitting manner.

25. The arrangement as claimed in claim 16, wherein each segment is provided with at least one recess, in which an associated projection engages.

26. The arrangement as claimed in claim 16, wherein the outer surfaces of the at least one segment are provided with a coating.

27. The arrangement as claimed in claim 16, wherein the arrangement is an arrangement for a turbine blade, or is an arrangement for a part for the turbine which is exposed to impingement by hot gas.

28. A method for producing an arrangement as claimed in claim 16, the method comprising: producing using a generative method at least the support struts of the support structure.

29. The method as claimed in claim 28, wherein a stacking of the segments and a stepwise producing of the at least one support strut alternate with each other in such a way that, after an arranging of a segment which is provided with a recess, a section of the at least one support strut, including a projection which engages in the recess, is generated.

30. The method as claimed in claim 28, wherein the stacking of the segments is carried out using a robot.

31. The arrangement as claimed in claim 18, wherein the at least one support strut has a cross section which follows the circumferential contour of the arrangement.

32. The arrangement as claimed in claim 26, wherein the coating comprises a thermal barrier coating.

33. The arrangement as claimed in claim 27, wherein the arrangement is an arrangement for a blade airfoil, or is an arrangement for a ring segment for the turbine which is exposed to impingement by hot gas.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Further features and advantages of the present invention become clear based on the following description of an arrangement according to an embodiment of the present invention with reference to the attached drawing. In the drawing:

[0028] FIG. 1 shows a schematic perspective view of an arrangement according to an embodiment of the present invention;

[0029] FIG. 2 shows a schematic plan view of a segment of the arrangement shown in FIG. 1;

[0030] FIG. 3 shows a schematic plan view of a platform of a support strut of the arrangement shown in FIG. 1 and

[0031] FIGS. 4 to 7 show schematic sectioned views, on the basis of which is explained the production of the arrangement shown in FIG. 1 using a method according to an embodiment of the present invention.

DETAILED DESCRIPTION OF INVENTION

[0032] FIGS. 1 to 3 show an arrangement 1 according to an embodiment of the present invention or components thereof. The arrangement 1 is an arrangement for a turbine, especially a gas turbine, wherein the arrangement 1 can in principle be designed both as a rotor blade, as a stator blade and/or as a ring segment or another part in the gas path or steam path of a turbine, although this is not shown in more detail in the present case.

[0033] As main components, the arrangement 1 comprises a metal support structure, with a platform 2, and three support struts 3, 4 and 5, which extend from the platform 2 in a radial direction R, and a multiplicity of segments 6 which are arranged one on top of the other on the support structure and are of plate-like design, which segments together define the circumferential contour of the arrangement.

[0034] The support structure, which principally serves for absorbing and dissipating forces which act upon the arrangement 1 during the specified use of this, is produced from a metal material which for example consists of a nickel based alloy, to name just one example. The platform 2 has a basically convexly curved suction side 7 and a basically concavely curved pressure side 8, wherein in principle other geometries are possible. In the case of the platform 2, it can be a prefabricated component which has been produced for example by means of casting and subsequent mechanical machining. Alternatively, the platform 2 can also be produced using a generative production method, such as by means of an SLM method, wherein other generative production methods are naturally also possible. The support struts 3, 4 and 5 are produced using a generative production method and fixedly connected to the platform 2, as is explained in more detail below. The struts extend from the platform 2 basically parallel to each other, are of hollow design, and in the present case have a non-round cross section in each case which follows the circumferential contour of the arrangement in the present case. Level with the upper edge of each segment 6, the support struts 3, 4 and 5 are circumferentially provided in each case with outwardly protruding projections 9 which extend transversely to the radial direction.

[0035] The segments 6 are produced in each case from a ceramic fiber composite material. Used as the ceramic fiber composite material can be for example Al.sub.2O.sub.3, 2O.sub.3/Al.sub.2O.sub.3, C/SiC, Sic/SiC or the like, to name just a few examples. Similar to the platform 2, the segments 6 comprise a suction side 10 and a pressure side 11, wherein the outer contours of adjacently arranged segments 6 are advantageously designed in alignment with each other, just as the outer contour of the platform 2 aligns with the outer contour of the adjacent arranged segment 6 in the present case. The segments 6 are provided in each case with three through-openings 12 through which the respective support struts 3, 4 and 5 extend. Between the segments 6 and the support struts 3, 4 and 5, a defined annular gap, which is broken only by the projections 9, can be left. Such an annular gap can be advantageous during the specified use of the arrangement 1 to the effect that in case of thermal expansions of the support struts 3, 4 and 5 and/or of the segments 6 a measured expansion space is created, reducing or preventing the occurrence of thermal stresses. Starting from the upper side of each segment 6 provision is made for encompassing recesses 13 of chamfer-like design which extend along the edge regions of the respective through-openings 12. The projections 9, which protrude from the support struts 3, 4 and 5, engage in these recesses 13 in a form-fitting manner so that each segment 6 is fixedly connected to the support struts 3, 4 and 5. For producing the arrangement 1 shown in FIG. 1, in a first step, as is shown schematically in FIG. 4, the platform 2 of the support structure is arranged on the base. After that, a segment is positioned on the platform 2 in such a way that the outer contour of the segment 6 aligns with the outer contour of the platform 2. The positioning of the segment can in this case be carried out using a robot, although this not shown in the present.

[0036] In a further step, sections of the support struts 3, 4 and 5 are generated in layers along the circumference of the respective through-openings 12 on the platform 2 up to the upper edge of the segment 6 using a generative production method, wherein the recesses 13 are also filled with metal material, creating the projections 9, as is shown in FIG. 5. In this connection, FIG. 4 schematically shows a nozzle arrangement 14 by means of which powdered metal material is directed in the direction of the platform 2 and is melted using a laser. It should be obvious that in principle any generative LMD method (Laser-Metal Deposition) can be used.

[0037] In a subsequent step, as is shown in FIG. 6, a further segment 6 is positioned on the segment 6 which is already fastened on the platform 2, whereupon sections of the support struts 3, 4 and 5 are again generated in layerssee FIG. 7. The previously described steps are repeated until the arrangement 1 shown in FIG. 1 is completed. In other words, a stacking of the segments 6 and a layered production of the support struts 3, 4 and 5 alternate, wherein after an arranging of a segment 6 which is provided with a recess 13, a section of the support struts 3, 4 and 5, including a projection 9 which engages in the recess 13, is generated in each case.

[0038] After completion of the arrangement 1 shown in FIG. 1, an uppermost metal cover layer, which can be provided with cooling fluid discharge holes and produced for example by means of deposition welding, can be arranged for forming a blade tip. Alternatively, a prefabricated cover layer can also be fixed on the metal support structure by means of high temperature soldering or the like. The arrangement 1 shown in FIG. 1 can also be provided with a coating, for example with a thermal barrier coating, if this is desired.

[0039] An essential advantage of the method according to the invention consists in the fact that during the production of a hybrid arrangement 1 the individual segments 6 are connected in a fixed and secure manner to the support structure in all spatial directions without separate fastening means being required for it.

[0040] Although in the views of the figures each segment can be provided with a recess, it is sufficient for the inventive idea if this is this case only for at least one of, or a number of, the segments, for example two, three or four segments. Consequently, according to the present invention only at least one corresponding support strut or the stated multiplicity has to have a corresponding projection.

[0041] For example, the engaging connection by means of the projections and the recesses in the middle of the arrangement or in every third or fourth stacked segment of the arrangement can be sufficient in order to utilize the advantages according to the invention.

[0042] Although the invention has been fully illustrated and described in detail by means of the preferred exemplary embodiments, the invention is not limited by the disclosed examples and other variations can be derived therefrom by the person skilled in the art without departing from the extent of protection of the invention.