BLADE OF A TURBOMACHINE, INCLUDING A COOLING CHANNEL AND A DISPLACEMENT BODY SITUATED THEREIN, AS WELL AS A METHOD FOR MANUFACTURING

Abstract

A blade of a turbomachine is provided, including at least one cooling channel in the interior of the blade for cooling the blade with the aid of a fluid flowing through the cooling channel, the cooling channel having at least one inlet and at least one outlet, between which the cooling channel extends along its longitudinal axis, and the cooling channel being radially delimited by at least one wall, at least one displacement body being situated in the cooling channel, so that an annular or tubular gap between the displacement body and the wall of the cooling channel results in the area of the displacement body/bodies, which is available for the through-flow of the fluid, or at least two or multiple subchannels being formed in the area of the displacement body/bodies. The invention also relates to a method for manufacturing a corresponding blade.

Claims

1. A blade of a turbomachine, the blade comprising: at least one cooling channel in an interior of the blade for cooling the blade with the aid of a fluid flowing through the cooling channel, the cooling channel having at least one inlet and at least one outlet, the cooling channel extend between the at least one inlet and the at least one outlet along a longitudinal axis, and the cooling channel being radially delimited by at least one wall; and at least one displacement body situated in the cooling channel, so that an annular or tubular gap between the displacement body and the at least one wall of the cooling channel results in an area of the displacement body, the annular or tubular gap being available for through-flow of the fluid, or so that at least two subchannels are formed in the area of the displacement body.

2. The blade as recited in claim 1 wherein the at least one displacement body is situated at an axial or radial center of the cooling channel along a center axis of the cooling channel, or the at least one displacement body is situated entirely inside the cooling channel.

3. The blade as recited in claim 2 wherein the at least one displacement body is situated coaxially to the cooling channel.

4. The blade as recited in claim 1 wherein the at least one displacement body is situated entirely inside the cooling channel and not touching the wall of the cooling channel or is held via at least one web.

5. The blade as recited in claim 1 wherein a gap width of the gap between the displacement body and the wall of the cooling channel, or a maximum diameter of one or each of the subchannels, is varied along the longitudinal axis of the cooling channel or is uniform at least in subareas.

6. The blade as recited in claim 5 wherein the gap width or the maximum diameter is uniform over at least 90% of the length of the displacement body.

7. The blade as recited in claim 6 wherein the gap width or the maximum diameter is uniform over an entirety of the length of the displacement body.

8. The blade as recited in claim 1 wherein a gap width of the gap between the displacement body and the wall of the cooling channel is varied along a circumference of the cooling channel or the displacement body reduces a flow cross section of the cooling channel.

9. The blade as recited in claim 1 wherein a gap width of the gap between the displacement body and the wall of the cooling channel remains the same along a circumference of the cooling channel or the displacement body reduces a flow cross section of the cooling channel.

10. The blade as recited in claim 1 wherein the displacement body is unremovably enclosed or trapped within the blade.

11. The blade as recited in claim 1 wherein the displacement body includes at least one displacement body channel for conducting cooling air and connected to the cooling channel.

12. The blade as recited in claim 11 wherein the at least one displacement body channel has at least one overflow opening.

13. The blade as recited in claim 1 wherein the displacement body has a honeycomb, matrix or lattice structure, or the displacement body is provided with a closed shell defining an inner volume.

14. The blade as recited in claim 13 wherein the closed shell or the inner volume are situated entirely inside the cooling channel or the inner volume includes a cavity or has a lesser density compared to the blade material.

15. The blade as recited in claim 1 wherein a cross-sectional shape of a circumference of the cooling channel or the subchannel or the displacement body is selected from the group consisting of round, circular, oval, angular, quadrangular, hexagonal shape and arbitrary free shapes.

16. The blade as recited in claim 1 wherein at least two of the subchannels open into a shared cooling channel or have a shared cooling channel inlet.

17. The blade as recited in claim 1 wherein the displacement body is situated in the cooling channel in such a way that the subchannels are formed with a large portion of their surface on a side of the cooling channel situated closer to a surface of the blade than an other side without or having a smaller surface portion of the subchannels.

18. The blade as recited in claim 1 wherein a longitudinal extension of the cooling channel or the subchannels is greater than a maximum diameter of the cooling channel or of one or each of the sub channels.

19. The blade as recited in claim 1 wherein the cooling channel extends in a meandering manner through the blade, or the displacement body is bent according to a bent course of the channel.

20. A method for manufacturing a blade of a turbomachine as recited in claim 1, the blade being manufactured using a generative method.

21. The method as recited in claim 20 wherein the generative method is selective electron beam melting or laser beam melting.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The attached drawings show the following in a purely schematic way:

[0032] FIG. 1 shows a perspective representation of a turbine blade according to the present invention;

[0033] FIG. 2 shows a longitudinal section of the turbine blade from FIG. 1, with a sectional view according to Arrows A;

[0034] FIG. 3 shows a cross section of the turbine blade from FIG. 1, with a sectional view according to Arrows B;

[0035] FIG. 4 shows another specific embodiment of a turbine blade according to the representation in FIG. 3; and

[0036] FIG. 5 shows another specific embodiment of a turbine blade according to the representation in FIG. 3.

DETAILED DESCRIPTION

[0037] Additional advantages, characteristics and features of the present invention are apparent from the following detailed description of the exemplary embodiments. However, the present invention is not limited to these exemplary embodiments.

[0038] FIG. 1 shows a perspective representation of a turbine blade 1, in which the present invention is implemented. Turbine blade 1, which may be used, for example, in the high-pressure turbine area of a turbomachine, includes a vane 2 as well as a blade root 3, a shroud 4 being formed between vane 2 and blade root 3.

[0039] As is apparent from the sectional view in FIG. 2, a cooling channel 5 is formed in the interior of turbine blade 1, which has a cooling channel inlet 6 in the area of blade root 3 and two cooling channel outlets 7 in the area of the blade tip of vane 2.

[0040] Cooling channel 5 initially runs in a meandering manner from cooling channel inlet 6 in the area of blade root 3 to the upper end of vane 2 and, after a 180 deflection, it runs from the upper end of vane 2 back to blade root 3, where, after another 180 deflection, cooling channel 5 again runs in the direction of the upper end of vane 2. In the area of the upper end of vane 2, at the blade tip, cooling channel 5 has multiple cooling channel outlets 7, through which a fluid, which is used to cool turbine blade 1, for example cooling air, may exit cooling channel 5.

[0041] To achieve the fact that the cooling fluid or the cooling air preferably passes along the wall of cooling channel 5 radially delimiting cooling channel 5, for the purpose of facilitating a corresponding heat transfer there with the aid of the material of vane 2 heated during operation, a displacement body 8 is provided in cooling channel 5, which, in the illustrated exemplary embodiment in FIGS. 2 and 3, extends in the middle along the longitudinal axis of cooling channel 5.

[0042] As is apparent in FIG. 2, in the illustrated exemplary embodiment, displacement body 8 is not provided over the entire length of cooling channel 5 but only in a subsection of cooling channel 5, in the subsection, in which cooling channel 5 runs from blade root 3 to upper end of vane 2 at the blade tip and back again to blade root 3. However, it is, of course, also possible to provide displacement body 8 over other areas along the longitudinal axis of cooling channel 5 or to situate multiple displacement bodies 8 one after the other along cooling channel 5.

[0043] In the example in FIG. 2, displacement body 8 is bent according to a course of cooling channel 5, is situated entirely within cooling channel 5 and is not nondestructibly removable therefrom.

[0044] Displacement body 8, which, in the illustrated exemplary embodiment, has a cylindrical basic shape with an oval cross section (see FIG. 3) and also has a U shape according to the 180 deflection of cooling channel 5 in the area of the blade tip and is situated via holding webs 9 in the middle of cooling channel 5 at a distance from the radial delimiting wall of cooling channel 5. Holding webs 9 may be situated spaced apart from each other along the circumference of displacement body 8 as well as spaced apart from each other along the longitudinal direction of displacement body 8.

[0045] Displacement body 8 is thus situated spaced apart from the wall of cooling channel 5 in such a way that an annular gap 10 results, which surrounds displacement body 8 and is formed between displacement body 8 and the wall of cooling channel 5. Annular gap 10 extends in a tubular manner along the longitudinal direction of displacement body 8 and cooling channel 5. The cooling fluid flowing through the cooling channel may flow through cooling channel 5 only in the area of annular gap 10, due to displacement body 8, so that a large portion of the through-flowing cooling fluid flows in the direct vicinity of the wall of cooling channel 5, where it is able to effectuate a corresponding heat transfer.

[0046] FIG. 3 shows a cross-sectional view of the arrangement of displacement body 8, which has an oval cross-sectional shape, in the first two subsections of cooling channel 5, which extend from blade root 3 to the blade tip of vane 2 and back again. It is apparent in the illustration in FIG. 3 that cooling channel 5 also has an oval cross-sectional shape. However, it is, of course, possible that both cooling channel 5 and displacement body 8 have other cross-sectional shapes, for example a circular cross-sectional shape, angular, in particular quadrangular, rectangular, square, polygonal or arbitrarily shaped cross-sectional shapes. The cross-sectional shape of displacement body 8 may correspond to the cross-sectional shape of cooling channel 5, or the cross-sectional shapes of cooling channel 5 and displacement body 8 may be different.

[0047] In the illustrated exemplary embodiment in FIG. 3, annular gap 10 is uniformly designed to have a constant annular gap width S circumferentially around displacement body 8. However, displacement body 8 and cooling channel 5 may also be shaped in such a way, and/or displacement body 8 may be situated in cooling channel 5 in such a way that annular gap width S is variable circumferentially around displacement body 8. For example, displacement body 8 may not be situated with its central longitudinal axis coaxial to the central longitudinal axis of cooling channel 5, as in the illustrated exemplary embodiment in FIG. 3, but rather situated eccentrically to the center axis of cooling channel 5.

[0048] Moreover, it is also possible that gap width S of gap 10 between displacement body 8 and the wall of cooling channel 5 varies along the longitudinal axis of cooling channel 5. FIG. 2 shows that gap width S is held constant in the subsections extending in a straight line from blade root 3 to the blade tip. In the area of the 180 deflection of cooling channel 5 in the upper area of vane 2, at the blade tip, gap width S is, however, partially different than gap width S in the straight subsections of cooling channel 5.

[0049] In a cross-sectional view comparable to the cross-sectional view in FIG. 3, FIG. 4 shows another specific embodiment of a turbine blade 1 according to the present invention, in which cooling channel 5 has a rectangular cross-sectional shape. In the specific embodiment in FIG. 4, a displacement body 8 is used in cooling channel 5, which is designed with a polygonal shape in cross section having multiple triangular indentations along the longitudinal sides of a rectangular basic shape. In the arrangement of displacement body 8 in cooling channel 5, due to the triangular indentations, multiple subchannels 11 are formed on the longitudinal sides of the rectangular cross-sectional shape of cooling channel 5, which make it possible for the cooling fluid flowing through cooling channel 5 to pass essentially along the surfaces of the wall of cooling channel 5 which are situated adjacent to the outsides of vane 2, i.e. along the longitudinal sides of cross-sectionally rectangular cooling channel 5 in the illustrated exemplary embodiment. As a result, the cooling fluid flowing through the cooling channel is concentrated on the wall areas of cooling channel 5 which are adjacent to the temperature-loaded outsides of vane 2, i.e. the longitudinal sides of the rectangular cooling channel This permits a particularly efficient use of the cooling fluid.

[0050] In a cross-sectional view comparable to the cross-sectional view in FIG. 3, FIG. 5 shows another specific embodiment of a blade according to the present invention, in which a cooling channel 5 is formed centrally over a wide area of the cross section in the manner of a hollow blade, in which a displacement body 8 is again situated, so that an annular gap 10 results circumferentially around the displacement body Channels 12 (displacement body channels) are again situated in displacement body 8 itself, which are connected to annular gap 10 and cooling channel 5 via overflow openings 13. The displacement body channels are formed essentially axially along the cooling channel longitudinal axis and radially with respect to a turbomachine, while the overflow openings run transversely thereto in the radial direction with respect to the cooling channel axis. Accordingly, a variety of structures are formed through which cooling channels pass and which facilitate an efficient cooling of the structures.

[0051] Although the present invention was described in detail on the basis of exemplary embodiments, it is as a matter of course to those skilled in the art that the present invention is not limited to these exemplary embodiments, but instead modifications are possible in such a way that individual features may be omitted or different combinations of features may be implemented, without departing from the scope of protection of the attached claims. In particular, the above description includes all combinations of the individual features shown in the different exemplary embodiments, so that individual features described only in connection with one exemplary embodiment may also be used in other exemplary embodiments or in combinations of individual features not explicitly illustrated.

LIST OF REFERENCE NUMERALS

[0052] 1 turbine blade [0053] 2 vane [0054] 3 blade root [0055] 4 shroud [0056] 5 cooling channel [0057] 6 cooling channel inlet [0058] 7 cooling channel outlet [0059] 8 displacement body [0060] 9 holding web [0061] 10 gap [0062] 11 subchannel [0063] 12 displacement body channels [0064] 13 overflow openings [0065] S gap width