EP2789798B1 - Turbine blade for a flow engine with profiled trailing edge, blade and integrally bladed rotor - Google Patents

Description

The present invention relates to an airfoil for a turbomachine, in particular a gas turbine blade, with a suction side, a pressure side and a blade trailing edge according to claim 1. Furthermore, the present invention relates to a blade according to claim 11 and an integrally bladed rotor according to claim 12.

From practice, blades for turbomachinery or turbine blades with different blade trailing edge geometries are known, for example to achieve noise reduction and / or higher efficiency. An airfoil according to the preamble of claim 1 is for example from EP 1 112 928 A2 known. For the sake of completeness, let me also mention the pamphlets EP 0 273 851 B1 EP 0 375 296 A1 . US 2008/050243 A1 and US 2010/150731 A1 pointed.

An object of the present invention is to propose a further airfoil for turbomachinery with a blade trailing edge profiled at least in one section. It is another object of the present invention to provide a blade and an integrally bladed rotor.

The object of the invention can be achieved by an airfoil with the features of claim 1. It can also be achieved by a blade having the features of claim 11 and an integrally bladed rotor having the features of claim 12.

Thus, according to the invention, an airfoil is proposed which, in the area of the blade trailing edge, has at least sections a profile which extends over the suction side and the pressure side of the blade trailing edge. Such an airfoil can be used as a guide vane and / or as a moving blade in turbomachines and / or turbines and / or blisks (abbreviation for "blade integrated disk") and / or bling (abbreviation for "bladed ring") are used and designed accordingly.

In all the above and following embodiments, the use of the term "may be" or "may have" etc. is synonymous with "preferably" or "preferably has", etc., and is intended to explain embodiments of the invention.

Advantageous developments of the present invention are the subject of subclaims and embodiments.

Embodiments of the invention may include one or more of the features mentioned below.

As used herein, the term "profile" refers to a structure or geometric shape that extends over both portions of the suction side and portions of the pressure side in the area of the blade trailing edge. A "profile" thus extends according to the invention both on the suction side and on the pressure side. In this case, differently shaped profiled part regions can be provided on the suction side and on the pressure side. On the suction side, in certain embodiments according to the invention, the profile part region can have, for example, structured surface roughness or surface depressions, and on the pressure side, for example, edges, bulges or steps can be arranged, or vice versa.

A profile may have structures or shapes to produce certain functional features, such as to specifically influence a flow around the blade trailing edge. For example, a stall edge can be achieved by means of the profile.

In some embodiments according to the invention, at least one so-called dead water area spreads downstream of the flow separation edge, which may be locally limited. This Totwassergebiet forms due to the caused by the stall edge cross-sectional widening. The flow or its laminar or turbulent flow profile, for example, can not follow this discontinuous cross-sectional widening. Therefore, in addition to the continuing (laminar or turbulent) flow profile arises another flow area, which can be referred to as Totwassergebiet. In this dead water area, self-contained vortices can be formed or formed.

A dead water area downstream of a stall edge may be referred to as a "trail dwell".

In some embodiments according to the invention, a so-called "Kármán vortex street" is formed by means of the profile. "Kármán vortex street" is a phenomenon in fluid mechanics, in which behind a flowing body counter-rotating vortices form.

In certain embodiments of the invention, an already formed "Kármán vortex street" is selectively influenced by means of the profile according to the invention. For example, the frequency of vortex shedding in the "Kármán vortex street" can be changed.

If, in the following, longitudinal turbulences or wake vortices or other vortices are described downstream of the profile, this also means possible flow separations and / or subsequent dead water areas.

Profiles on the trailing edge of the blade can be produced by means of various production methods, for example by forming (for example casting), forming (for example forging, pressing, rolling, folding, deep-drawing) or separating (for example milling, drilling), etc.

In certain exemplary embodiments of the invention, after being fabricated using one of the described manufacturing processes, profiles are reworked, e.g. B. by grinding, polishing, smoothing, etc.

In some embodiments of the present invention, the profile of the airfoil is configured to shorten caster vortices that form in the flow direction at or behind the blade trailing edge. In practice, vortices, in particular longitudinal vortices, may form at the trailing edges of flow-around vane blades. A shortening of these longitudinal vortices in the flow direction by profiles according to the invention in the region of Bucket trailing edges can advantageously lead to a reduction in noise and / or a reduction in drag of the blade according to the invention.

In certain embodiments according to the invention, the blade trailing edge of the blade has at least in sections thereto a different height perpendicular to the flow direction and / or perpendicular to the longitudinal direction of the blade trailing edge. The flow direction in this embodiment is the resulting flow direction downstream of the blade trailing edge. This resulting flow is composed of the flows of the suction side, which is also referred to as the blade top, vacuum side or suction side, and the pressure side, which is also referred to as the blade underside.

Synonymous with the term "height", the terms "thickness", "material thickness" or "transverse extent" can also be used.

The blade trailing edge has a different height in some exemplary embodiments of the invention due to the inventive profile. For example, a profile region on the suction side and / or on the pressure side may have a groove, a cutout, a material application (eg a welded or glued web) or the like, resulting in this profile region and a smaller or greater height.

In certain exemplary embodiments of the invention, the blade trailing edge of the airfoil terminates with a straight longitudinal portion of the airfoil, or has a straight longitudinal portion. A "straight longitudinal section" denotes a longitudinal section which may vary in height but has no, preferably at least no significant, cuts against the direction of flow. The term "no substantial cuts" means that the longitudinal section, for example, has no structural cuts, but may have manufacturing irregularities, wear, surface changes, etc. Structural cuts would be, for example, jagged, spring-like, slit-shaped and similar cuts. These reduce the respective width of the airfoil in the region of the incision. A straight Continuous longitudinal section of the blade trailing edge can be further described by the following terms: continuous edge (with a variable height) or continuous structure, Similarly, a "straight longitudinal section" can be described by the distance between the blade leading edge (the trailing edge of the airfoil) Likewise or alternatively, a "straight longitudinal section" can be described by the fact that in the observed section of the blade trailing edge all points, for example 3 cm in front of (upstream) the trailing edge of the blade on the suction side lie on a straight line.

In the embodiments of the invention, the profile has recesses at the blade trailing edge of the airfoil. These recesses are not to be understood as incisions of the blade trailing edge counter to the flow direction, which narrows the width of the blade, but as depressions perpendicular to the surface of the blade trailing edge and thus in the thickness of the blade trailing edge. Recesses can be made by drilling, milling, deep drawing, laser cutting, casting, etc.

In some example embodiments of the invention, at least some of the depressions of the airfoil are wedge-shaped at least in sections thereof. The wedge-shaped depressions can be tapered counter to the flow direction.

In certain exemplary embodiments according to the invention, the wedge-shaped depressions have an at least sectionally continuous taper counter to the flow direction. A continuous rejuvenation is a rejuvenation whose lateral boundary is straight (see Fig. 5 ).

In certain embodiments according to the invention, the wedge-shaped recesses have an at least partially non-continuous taper opposite to the flow direction. A non-continuous taper is a taper whose boundary is curved but not straight. One embodiment of a non-continuous taper is shown in FIG Fig. 6 shown.

In some embodiments of the invention, the wedge-shaped depressions taper counter to the flow direction such that the limiting side surfaces of rejuvenation are not merged or, in other words, do not converge. Rather, an opening remains as flow passage in the wedge-shaped depression. Thus, a portion of the flow on the suction side and / or on the pressure side in the wedge-shaped depressions flow (see FIG. 7 as an exemplary embodiment).

In certain embodiments of the invention, the transition from the surface of the suction side and / or the pressure side into the wedge-shaped taper is continuous, that is without edges. The surfaces on the one hand from the suction side and / or the pressure side and on the other hand from the wedge-shaped depression (the base surface) go continuously into one another.

In some embodiments according to the invention, the depressions, which may have wedge-shaped, channel-shaped or some other shape, are arranged on the suction side offset from the depressions on the pressure side. The offsets are arranged perpendicular to the flow direction and / or parallel to the blade trailing edge, or along the blade trailing edge (see Fig. 4 ).

In some embodiments of the invention, the profile at least partially channel-shaped depressions against the flow direction. Channel-shaped recesses have - preferably continuously or at least in sections - a constant cross section (see Fig. 2 ).

In certain embodiments according to the invention, the profile has channel-shaped depressions at least in sections. The channel-shaped depressions are arranged such that the blade trailing edge to the channel longitudinal axis forms an angle between 0 and 90 °. At an angle of 90 °, the channel longitudinal axis runs exactly opposite to the flow direction or parallel to it. At an angle of 0 °, the channel longitudinal axis runs parallel to the blade trailing edge. The angle preferably has a value between 5 ° and 85 °, in particular between 10 ° and 30 °. Likewise, the various channel-shaped recesses may have different angles. This applies both to the suction side of the blade in the region of the blade trailing edge and on the corresponding pressure side. Furthermore, on the suction side, the angle may have a certain value, for example 90 °, on the pressure side another value, for example 20 °. Any other combination is also possible.

Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.

The blade according to the invention can advantageously be used within the guide vane grille of a low-pressure turbine. By shortening the longitudinal vortices downstream of the guide vane grille due to use of the vane blade according to the invention with the above-described profiles in the region of the vane trailing edges, downstream trailing vane grates, for example, can be influenced less or not at all. This is at least a reduced noise on the subsequent blades possible because the shortened longitudinal vortices no longer reach the subsequent blade lattice. Overall, this leads to an advantageous noise reduction in the flow through the turbine.

For structural mechanical reasons, the profiling according to the invention of the blade trailing edge of guide vanes is advantageously more favorable in comparison to rotor blades, since the guide vanes are not exposed to the high rotational speeds and thus no additional dynamic load. This reduced load on the static vanes leads to a lower susceptibility, a longer service life and ultimately to a more economical use when using the blade according to the invention over conventional airfoils.

By using the blade according to the invention, the axial minimum distance (in the flow direction) between the Leitschaufelgittem and / or the blade airfires can be advantageously reduced because the trailing vortices can be shortened.

This advantageously results in less excitation or influencing of the following or adjacent blades.

Furthermore, when using the blade according to the invention, a lower loss coefficient of the blade profile can advantageously be achieved and thus the axial length of the blade profile or the number of blades can be reduced.

Alternatively or additionally, when using the blade according to the invention with unchanged length (extension of the length in the flow direction) of the blade profile or with unchanged number of blades, the efficiency (for example, the hydraulic efficiency of the airfoil), measured on embodiments not according to the invention without the profile according to the invention.

An insert of the blade according to the invention can therefore advantageously lead to a reduction in the weight of the engine, a cost reduction, a shortening of the installation space of the turbine and / or to an increase in the efficiency due to the advantages mentioned.

Fig. 1

zeigt schematisch ein erfindungsgemäßes Schaufelblatt mit keilförmigen Vertiefungen einer ersten Ausführungsform;

Fig. 2

zeigt schematisch ein weiteres erfindungsgemäßes Schaufelblatt mit kanalförmigen Vertiefungen einer zweiten Ausführungsform;

Fig. 3

zeigt schematisch ein nicht erfindungsgemäßes Schaufelblatt mit einer Lochstruktur einer dritten Ausführungsform;

Fig. 4a

zeigt schematisch eine Anordnung von keilförmigen Vertiefungen an der Schaufelhinterkante der ersten nicht erfindungsgemäßen Ausführungsform mit in einem Querschnitt geraden seitlichen Begrenzungen;

Fig. 4b

zeigt eine nicht erfindungsgemäße Anordnung von keilförmigen Vertiefungen mit in einem Querschnitt schrägen seitlichen Begrenzungen;

Fig. 4c

zeigt eine erfindungsgemäße Anordnung von keilförmigen Vertiefungen mit in einem Querschnitt schrägen seitlichen Begrenzungen;

Fig. 4d

zeigt eine nicht erfindungsgemäße Anordnung von keilförmigen Vertiefungen, die sich sowohl in Strömungsrichtung als auch senkrecht zur Schaufeloberseite und zur Schaufelunterseite ausbreiten;

Fig. 5

zeigt schematisch die Form einer keilförmigen Vertiefung mit einer kontinuierlichen Verjüngung einer vierten Ausführungsform;

Fig. 6

zeigt schematisch die Form einer keilförmigen Vertiefung mit einer nichtkontinuierlichen Verjüngung einer fünften Ausführungsform; und

Fig. 7

zeigt schematisch keilförmige Vertiefungen an der Schaufelhinterkante mit Wirbelbildungen.

The present invention will be explained in the following with reference to the accompanying drawings, in which identical reference numerals designate the same or similar components, by way of example. In the partially simplified figures:

Fig. 1

schematically shows an inventive blade with wedge-shaped depressions of a first embodiment;

Fig. 2

shows schematically a further inventive blade with channel-shaped recesses of a second embodiment;

Fig. 3

shows schematically a non-inventive airfoil with a hole structure of a third embodiment;

Fig. 4a

shows schematically an arrangement of wedge-shaped depressions on the blade trailing edge of the first embodiment not according to the invention with straight lateral boundaries in a cross section;

Fig. 4b

shows a non-inventive arrangement of wedge-shaped depressions with oblique lateral boundaries in a cross section;

Fig. 4c

shows an inventive arrangement of wedge-shaped depressions with oblique lateral boundaries in a cross section;

Fig. 4d

shows a non-inventive arrangement of wedge-shaped depressions, which propagate both in the flow direction and perpendicular to the blade top and the blade underside;

Fig. 5

shows schematically the shape of a wedge-shaped recess with a continuous taper of a fourth embodiment;

Fig . 6

shows schematically the shape of a wedge-shaped recess with a non-continuous taper of a fifth embodiment; and

Fig. 7

schematically shows wedge-shaped depressions on the blade trailing edge with vortex formations.

Fig. 1 schematically shows an inventive blade 100 with a blade profile 3, a suction side 5 and a pressure side 7. The blade 100 has wedge-shaped recesses 1 in the region of a blade trailing edge 200 on.

In the region of the blade trailing edge 200, a profile 9 is shown, which wedge-shaped recesses 1 both on the suction side 5 (in Fig. 1 only indicated as dashes) and on the pressure side 7, in each case in the region of the blade trailing edge 200. The wedge-shaped depressions 1 taper counter to the flow direction 11.

Fig. 2 schematically shows a further inventive blade 100 with channel-shaped recesses 1b in the region of the blade trailing edge 200. The channel-shaped recesses 1b have a channel longitudinal axis 10 and terminate semicircular. Such channel shapes are machined, for example, by means of a milling cutter.

The depressions can be executed both in (or opposite to) the flow direction (depressions 1b), as well as perpendicular to the surface and perpendicular to the flow direction (in Fig. 2 not shown). The depressions perpendicular to the surface can be designed to have different depths both in (or opposite to) the flow direction and perpendicular to the flow direction. Accordingly, for example a machining three-dimensional in all three processing angles (x, y, z-axis) take place.

The channel-shaped recesses 1b extend over the pressure side 7 and the suction side 5 (in FIG Fig. 2 the recesses of the suction side 5 are indicated only as dashes on the blade trailing edge 200) and together form a profile 9 in the region of the blade trailing edge 200.

Fig. 3 schematically shows a non-inventive blade 100 with a hole structure 300 in the region of the blade trailing edge 200. The individual holes of this hole structure 300 are purely exemplary designed as through holes, but can also be wholly or partially as non-through holes (holes with to be determined in individual blind hole depths). These holes can be made different on the suction side 5 and 7 on the pressure side.

The hole structure 300 is in this embodiment not according to the invention in the flow direction 11 parallel rows of holes (here exemplarily 5 holes per row of holes) executed, any other arrangement is also possible and encompassed by the invention.

Fig. 4a schematically shows a not inventive arrangement of wedge-shaped recesses 1a on the blade trailing edge 200 in a front view of the blade trailing edge 200 against the flow direction 11 (not shown here) seen.

The wedge-shaped recesses 1a are - based on the representation of Fig. 4a - Located on the suction side 5 (top) and on the pressure side 7 (bottom) in the region of the blade trailing edge 200. Thus, they are located above and below the continuous blade trailing edge portion.

The position of the wedge-shaped depressions 1a is arranged on the suction side 5 offset from the pressure side 7 or vice versa on the pressure side 7 offset from the suction side 5. "Staggered" means that the wedge-shaped recesses 1a in the longitudinal direction of the blade trailing edge 200 not at the same position in Longitudinal direction (ie in Left-right direction of the Fig. 4 ) are arranged. This offset position of the wedge-shaped depressions 1a can be regular, z. B. a wedge-shaped depressions 1a on the suction side 5, then on the pressure side 7, then again on the suction side 5, etc., or irregular. It can be irregular or irregularly irregular on a regular basis.

The width 13 of the wedge-shaped recess 1a at the blade trailing edge 200 may be the same or different on the suction side 5. This also applies to the wedge-shaped recesses 1a on the pressure side. 7

The width 14 of the webs between the wedge-shaped recesses 1a may also be the same or different on the suction side 5. This also applies to the width 14 of the webs between the wedge-shaped depressions 1a on the pressure side. 7

The depth 15 of the wedge-shaped recess 1a at the blade trailing edge 200 may also be the same or different on the suction side 5. This also applies to the wedge-shaped recesses 1a on the pressure side 7. The depth 15 can in the course of the profile 9 (see Fig. 5 and 6 ) be the same or different, z. For example, the depth 15 may be greater directly at the blade trailing edge 200 and become smaller in the course on the suction side 5 and / or in the course on the pressure side 7 or vice versa, ie initially smaller at the blade trailing edge 200 and then becoming larger in the course.

The height 17 of the blade trailing edge 200 indicates the minimum transverse dimension or thickness of the trailing blade trailing edge 200. Ie. the reference dimension for the height 15 is the total height of the blade trailing edge 200 minus the depth 15 of the wedge-shaped recesses 1a on the suction side 5 and the pressure side 7. The height 17 can be an important measure of the mechanical and dynamic stability of the blade trailing edge 200 and / or the entire Scoop 100 be.

What applies at any point herein (ie, not only with respect to the figure described herein) to the depressions or ridges of one geometry (eg, wedge-shaped) also applies to all other possible pits, lands, or dimples of other geometries (e.g. B. Channel-shaped depressions).

Possible embodiments of the measures mentioned are purely exemplary: width 13 of the recesses 1a in a range between 0.5 and 2 mm, preferably between 0.8 and 1.2 mm, in particular 1 mm; Depth 15 in a range between one tenth and one quarter of the height 17 (eg in a range between 0.1 and 0.25 mm), in particular a sixth of the height 17 (eg 0.2 mm); Height 17 in a range between 0.5 and 2 mm, preferably between 0.8 and 1.2 mm, in particular 1 mm; Width 14 in a range between 0.5 and 2 mm, preferably between 0.8 and 1.2 mm, in particular 1 mm.

All dimensions may depend in particular on the blade size.

The lateral boundaries of the recesses 1a in the exemplary embodiment shown here are straight (alternatively: only one of them) straight. They thus extend in this example perpendicular to the surface of the airfoil 100 in its depth.

Other possible embodiments of the profile are in the Fig. 4b, 4c, 4d in which the lateral boundaries of the recesses 1a extend in the exemplary embodiments shown therein both (alternatively: only one of two) not straight in the cross section through the airfoil 100 shown in the figure. Thus, they do not extend in this example perpendicular to the surface of the airfoil 100 in its depth. They are, unlike the parallel embodiment of Fig. 4a , not parallel to each other.

Fig. 4b shows depressions 1a, which at the lateral boundaries, with respect to the plane of Fig. 4b , Bevels with the angles 16a, 16b have. By way of example only, possible embodiments of the angles 16a, 16b are between 30 and 60 degrees, preferably between 40 and 50 degrees, in particular 45 degrees.

The angles 16a and 16b may be the same or different.

Fig. 4c shows depressions 1a according to the invention with lateral bevels with the further angles 16c, 16d. By way of example only, possible embodiments of the angles 16c, 16d are between 120 and 150 degrees, preferably between 130 and 140 degrees, in particular 135 degrees.

The angles 16c and 16d may be the same or different.

In the Fig. 4c shown inventive shape of the recess 1a with the two boundary surfaces can also be referred to as a "dovetail shape" whose width is wider at the recess bottom than at the opening of the recess 1a. Structurally, this form is also referred to as an undercut, for example in the form of a trapezoid.

Fig. 4d shows a non-inventive arrangement of wedge-shaped recesses 1a, which propagate both in the flow direction (perpendicular to the plane) and perpendicular to the blade top 5 and the blade bottom 7.

The wedge-shaped depressions 1a have the angles 18a and 18b in the direction of propagation perpendicular to the upper side 5 of the blade and to the underside of the blade 7.

By way of example only, possible embodiments of the angles 18a, 18b are between 10 and 50 degrees, preferably between 20 and 40 degrees, in particular 30 degrees.

The angles 18a and 18b may be the same or different.

The embodiments of the Fig. 4a, 4b and 4c can be advantageous in terms of manufacturing technology, since the depth 15 of the wedge-shaped depressions can be predetermined, which also determines the height 17 of the blade trailing edge. In contrast, the height 15 varies in the embodiment of Fig. 4d with the angles 18a and 18b, in particular, the height 17 decreases at increasing angles 18a, 18b. In addition, the stability of the blade trailing edge 200 at a predetermined minimum height 17 in the embodiments of the Fig. 4a, 4b and 4c be beneficial.

Furthermore, the stability of the blade trailing edge 200 overall at fixed minimum heights 17 may be advantageous, in particular with dynamic and / or flow-related loads on the blade profile 3. In addition, a blade trailing edge profile 200 of the embodiments 4a to 4c with predetermined minimum heights 17 may be advantageous since, for example, a cutting production of Recesses 1a at low material thicknesses (low height 17) requires at least an additional effort when clamping the workpiece.

Fig. 5 schematically shows the shape of a wedge-shaped recess 1 a with a continuous taper 19 on the suction side 5 and / or on the pressure side 7 in the region of the blade trailing edge 200 in a plan view of the suction side 5 or on the pressure side. 7th

The length 21 indicates how far the wedge-shaped depression 1a, starting at the blade trailing edge 200, extends over the suction side 5 and / or the pressure side 7.

A purely exemplary possible embodiments of the length 21 is 1.2 mm, alternatively, it is in a range between 0.9 and 1.8 mm.

Fig. 6 schematically shows the shape of a wedge-shaped recess 1a with a non-continuous taper 23 on the suction side 5 and / or on the pressure side 7 in the region of the blade trailing edge 200 in a plan view from above (on the suction side 5) or below (on the pressure side 7) seen.

The description of length 21 applies analogously to Fig. 5 ,

Fig. 7 schematically shows wedge-shaped depressions 1a on the blade trailing edge 200 with vortex formations in a perspective view (top) and in a view from downstream to the blade trailing edge 200th

The wedge-shaped depression 1a is viewed by means of a non-continuous taper (counter to the flow direction 11; Fig. 6 ).

The flow direction 11 flows around both the suction side 5 and the pressure side 7. For example, part of the flow flows from the suction side 5 into the wedge-shaped depression 1a. The surface of the suction side passes continuously into the wedge-shaped depression 1a. In other words, the transition of the two surfaces is continuous and without an edge.

When the wedge-shaped depressions 1a flow through, vortices 25 form on the two side walls of the wedge-shaped depressions 1a. The formation of these vortices 25 may depend on the flow velocity and / or on the shape of the widening of the wedge-shaped depression 1a. A more bulging shape may favor vortex formation more than a weaker flared shape.

Due to the pairs of vortices 25 (each at the two side walls of the wedge-shaped tapers 1a) results in a strong mixing of the total flow of the suction and pressure side in the region of the wedge-shaped recesses 1a in the adjoining flow region downstream of the blade trailing edge 200. This mixing is by the additional vortex 27 shown downstream of the blade trailing edge 200. Due to this mixing, the wake rolls downstream of the blade trailing edge 200 are shortened. As has already been discussed in the description (above), the term trailing vortices include, inter alia, longitudinal vortices and in particular dead water areas.

The shortening of the trailing vortices and / or the dead water zones leads to the advantages according to the invention described above, such as, for example, reduced noise generation and / or increased efficiency and / or less vibration excitation of further downstream downstream blades. <B> LIST OF REFERENCES </ b> reference numeral description 100 Airfoil for a turbomachine, turbine blade 200 Blade trailing edge 300 hole structure 1a wedge-shaped depression 1b channel-shaped depression 3 blade profile 5 suction side; Blade top side 7 Pressure side; Blade underside 9 Profile in the area of the blade trailing edge 10 channel longitudinal axis 11 flow direction 13 Width of the wedge-shaped depression at the blade trailing edge 14 Width of the webs between the wedge-shaped depressions 1a 15 Depth of the wedge-shaped depression at the blade trailing edge 16a, 16b, 16c, 16d Angle at the lateral boundaries (chamfers) of the recesses 1a 17 Height of the blade trailing edge 18a, 18b Angle of the wedge-shaped recesses 1a 19 continuous taper of a wedge-shaped depression in the region of the blade trailing edge 21 Length of the wedge-shaped depression at the blade trailing edge 23 non-continuous taper of a wedge-shaped depression in the area of the blade trailing edge 25 Vortex / dead water area in the wedge-shaped depression 27 Vortex / dead water area downstream of the blade trailing edge

Claims (12)

1. A turbine blade (100) for a flow engine with a suction side (5), a pressure side (7) and a blade trailing edge (200), the turbine blade (100) having a profile (9) at least in sections that extends over the suction side (5) and the pressure side (7) of the blade trailing edge (200) in the area of the blade trailing edge (200), the profile (9) having recesses (1a, 1 b) each having two lateral margins which connect to a recess base, characterized in that the width at the recess base is wider than at the opening of the recess (1a, 1b).
2. The turbine blade (100) according to claim 1, wherein the profile (9) is formed to reduce wake vortices which form in the direction of flow (11).
3. The turbine blade (100) according to claim 1 or 2, wherein the blade trailing edge (200) has at least in sections thereof a different height perpendicularly to the direction of flow (11) and perpendicularly to the longitudinal direction of the blade trailing edge (200).
4. The turbine blade (100) according to one of the preceding claims, wherein the blade trailing edge (200) closes the turbine blade (100) with a longitudinal section extending linearly.
5. The turbine blade (100) according to one of the preceding claims, wherein the recesses (1a) are formed in a wedge shape and are tapered against the direction of flow (11).
6. The turbine blade (100) according to claim 5, wherein the wedge-shaped recesses (1a) have a continuous tapering (19) at least in sections against the direction of flow (11).
7. The turbine blade (100) according to claim 5, wherein the wedge-shaped recesses (1a) have a non-continuous tapering (23) at least in sections against the direction of flow (11).
8. The turbine blade (100) according to one of the claims 1 to 7, wherein the recesses (1a, 1 b) on the suction side (5) are arranged offset opposite the recesses (1a, 1 b) on the pressure side (7), wherein the offsets are arranged perpendicular to the direction of flow (11) and/or parallel to the blade trailing edge (200) or along it.
9. The turbine blade (100) according to one of the claims 1 to 4, wherein the profile (9) has channel-like recesses (1 b) against the direction of flow (11) at least in sections.
10. The turbine blade (100) according to one of the claims 1 to 4, wherein the profile (9) has channel-like recesses (1b) at least in sections and wherein the channel-like recesses (1 b) are arranged such that the blade trailing edge (200) forms an angle between 0 and 90° with the longitudinal channel axis (10).
11. A blade with a turbine blade (100) according to one of the claims 1 to 10.
12. An integrally bladed rotor with at least a turbine blade (100) according to one of the claims 1 to 10 or at least a blade according to claim 11.

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