EP3269941B1 - Adjustable cascade for turbomachine - Google Patents

Description

The present invention relates to an adjustable vane grille for a turbo machine, in particular a compressor or turbine stage of a gas turbine, a turbo machine, in particular a gas turbine, with the adjustable vane grille and a method for adjusting the vane grille.

From the DE 103 51 202 A1 a device for adjusting guide vanes of a gas turbine is known in which guide vanes are pivotably connected to an adjusting ring via adjusting levers, all guide vanes of the same guide vane ring being uniformly pivotable via the adjusting ring.

From the US 2015/0159551 A1 a guide vane ring with adjustable guide vanes is known, two guide vanes having a different distance in the circumferential direction than two other guide vanes ("cyclic spacing").

DE 197 41 992 A1 shows a radial water turbine with guide blades extending in the axial direction and pivotable in the axial direction.

CH 360 074 A shows a gas turbine with an adjustable guide grille that can be adjusted in segments. The blades of the segments are each equally spaced from one another. Each segment is rotated by its own adjustment device. Disadvantageously, the blades cannot be rotated by an adjusting device, but only the entire segments can be adjusted by an angle. DE 10 2008 058 014 A1 shows an adjustable guide stage with tandem adjustable guide vanes, two of which are arranged on a vane disk and can be arranged differently on the vane disk. The blades on the plates of the tandem blades can be pivoted about a common axis of rotation. The adjacent plates and tandem blades correspond to one another, the single blades of two adjacent tandem blades each having the same staggering angle.

RU 2 145 391 C1 and JP 2004 100553 A1 relate to known gas turbine nozzle stages with individually adjustable blades that are constantly spaced from one another.

One object of an embodiment of the present invention is to improve a turbomachine, in particular a gas turbine, and / or its operation.

This object is achieved by an adjustable blade grille with the features of claim 1. Claims 11, 12 protect a turbomachine, in particular a gas turbine, with at least one blade grid described here or a method for adjusting a blade grid described here. Advantageous embodiments of the invention are the subject of the dependent claims.

According to one embodiment of the present invention, an adjustable vane grille for a turbo machine, in particular for a compressor or turbine stage of a gas turbine, in particular at least one adjustable vane grille of a turbo machine, in particular at least one compressor and / or at least one turbine stage of a gas turbine, (each) at least a blade, referred to here without loss of generality as the first blade, in particular stator or housing-side and / or guide blade, which is separated from one or both of the adjacent, in particular further, blade (s), in particular (further) stator or housing-side and / or guide vane (s), in the circumferential direction (in each case) has a distance designated here without loss of generality as the first distance, and at least one blade designated here without loss of generality as a second blade, in particular on the stator or housing side and / or of the guide vane, the one or both of one or both of the adjacent, in particular other, vane (s) in the circumferential direction, in particular (other) stator or housing-side and / or guide vane (s), in the circumferential direction (in each case) one in the present case without loss of generality as the second Distance has designated distance on. The invention can be used with particular advantage in guide vane grids, in particular in compressor stages, in particular high pressure compressor stages, in gas turbines, without being restricted thereto.

According to one embodiment of the present invention, the second distance is smaller than the first distance, in particular by at least 1%, in particular at least 5%, and / or at most 75%, in particular at most 50%, of the first or second distance.

In this way, in one embodiment, undesired resonances between adjacent blades in particular can be reduced.

According to one embodiment of the present invention, the vane grille has an adjusting device by means of which the first vane, in particular reversibly, from a position referred to here without loss of generality as the first position (of the first vane, in particular the vane grille), in particular an angular position, in the at least an airfoil profile section of the first blade has a staggering angle called the first stagger angle (of the first blade) in the present case without loss of generality, in a position called the second position (of the first blade or the blade grid), in particular an angular position, in the present case without loss of generality as the second position (At least) this airfoil profile section (of the first blade) has a staggering angle referred to in the present case without loss of generality as the second stagger angle (of the first blade), and, together with the first blade, in particular rev ersible and / or in the same direction, the second blade from one or the position designated here without loss of generality as the first position (of the second blade or the blade lattice), in particular an angular position in which at least one blade profile section of the second blade is present without restriction of the Generally referred to as the first stagger angle (of the second blade), into a position, in particular the angular position, in the (at least) this blade profile section (the.), In the present without loss of generality as the second position (of the second blade or of the blade grid) second blade) has a staggering angle referred to in the present case without loss of generality as the second stagger angle (the second blade), is adjustable, in particular pivotable or rotatable, is or adjusted, in particular pivoted or rotated, is or is or is set up for this purpose . is used.

According to one embodiment of the present invention, the second stagger angle of the first blade is different from the, in particular the same-direction, second stagger angle of the second blade, in particular greater than the second stagger angle of the second blade, in particular by at least 1 °, in particular at least 5 °, and / or by at least 1%, in particular at least 5%, of the first or second stagger angle of the first or second blade and / or by at most 45 °, in particular at most 25 °, and / or by at most 50%, in particular at most 25%, of the first or second The stagger angle of the first or second blade.

As a result, advantageous flow conditions can be represented in one embodiment with different positions of the vane grid or the first and second blades and, in a further development, a performance and / or suction limit can be improved or, conversely, a deterioration in the flow conditions can be reduced by adjusting the blade grid. In one embodiment, advantageous outflows, in particular outflow angles, and / or, in the case of larger or more closed stagger angles, advantageous conditions, in particular free flow cross-sections between adjacent blades, can be represented in one embodiment.

As a stagger angle ("stagger angle") in one embodiment, the angle which the pressure-side tangent to the respective airfoil profile section or the (pressure-side) profile tangent or chord ("cord line") is referred to is present in one embodiment the axial direction includes. In one embodiment, the staggering angle β is, as is customary in the art, equal to half the sum of the inflow and outflow angles α ₁ , α _{2 of} the airfoil profile section (β = (α ₁ + α ₂ ) / 2). The (relevant or at least one) airfoil profile section of the first and second blades or their respective airfoil is, in one embodiment, an airfoil profile section at the same radial height, in particular an airfoil profile section at the airfoil root, at the airfoil tip or at half the radial airfoil height. Correspondingly, in one embodiment, the first and second blades or the blade grid have at least one in the first position Airfoil profile section of the first blade the first stagger angle of the first blade and an airfoil profile section of the second blade at the same radial height the first stagger angle of the second blade and in the second position of the first and second blades or the airfoil this airfoil profile section of the first blade the second stagger angle of the first Blade and this airfoil profile section of the second blade on the second stagger angle of the second blade.

In the present case, a direction parallel to a rotation or (main) machine axis of the turbo machine or gas turbine (n stage), in particular from a turbo machine or vane grille inlet or outlet to a turbo machine or vane grille outlet or outlet, is used as the axial direction in the present case, in particular in the usual way - occurs, referred to, as a radial direction corresponding to a direction perpendicular to the rotation or (main) machine axis away from this axis, as a circumferential direction corresponding to a direction of rotation or rotation about this axis or a rotor of the turbo machine or gas turbine ( n stage), in particular of the adjustable rotor blade grid or of a rotor blade grid axially adjacent to the adjustable guide blade grid.

In the present case, the distance or division between two adjacent blades in the circumferential direction in the circumferential direction is an angle between the adjustment, in particular pivot or rotation axes, of the two adjacent blades or a corresponding circumferential or segment length, in particular a circumference - or segment length between the pivot bearings of the two blades.

In one embodiment, the first stagger angle of the first blade is equal to the first stagger angle of the second blade, in particular the first stagger angle in the same direction. In other words, in one embodiment there is at least one or the first position of the first and second blades or of the blade grid in which the first and second blades or their blades have the same staggering angle at at least one radial height.

Likewise, in one embodiment, the first stagger angle of the first blade can be different from, in particular the same-directional, first stagger angle of the second blade, in particular larger or, preferably, smaller than the first stagger angle of the second blade, in particular by at least 1 °, in particular at least 5 °, and / or by at least 1%, in particular at least 5%, of the first or second stagger angle of the first or second blade and / or by at most 45 °, in particular at most 25 °, and / or by at most 50%, in particular at most 25% , the first or second stagger angle of the first or second blade.

In particular, in a preferred embodiment, the first blade or its at least one airfoil profile section can have a larger stagger angle in at least one (second) position and a smaller stagger angle in at least one (first) position than the second blade or its at least one airfoil profile section. In another embodiment, the staggering angle of the first blade or of its at least one airfoil profile section is always greater or smaller than the second staggering angle of the second blade or of its at least one airfoil profile section or over the entire adjustment range.

As a result, advantageous flow conditions can be represented in one embodiment with different positions of the vane grid or the first and second blades and, in a further development, a performance and / or suction limit can be improved or, conversely, a deterioration in the flow conditions can be reduced by adjusting the blade grid.

In one embodiment, the first and / or second position of the first and / or second blade limits their (respective) adjustment range on one or both sides. Likewise, in one embodiment, the first vane can move from the first position beyond the second position and / or from the second position beyond the first position and / or the second vane from the first position beyond the second position and / or from the second Position to be adjustable beyond the first position or to be adjusted or to be set up for this purpose.

As a result, advantageous flow conditions can be represented in one embodiment with different positions of the vane grid or the first and second blades and, in a further development, a performance and / or suction limit can be improved or, conversely, a deterioration in the flow conditions can be reduced by adjusting the blade grid.

In one embodiment, the first stagger angle of the first blade is greater or, preferably, smaller than the second stagger angle of the first blade, in particular by at least 1 °, in particular at least 5 °, and / or by at least 1%, in particular at least 5%, of the first or second stagger angle of the first blade and / or by at most 75 °, in particular at most 45 °, and / or by at most 50%, in particular at most 25%, of the first or second stagger angle of the first blade. Additionally or alternatively, in one embodiment the first stagger angle of the second blade is greater or, preferably, smaller than the second stagger angle of the second blade, in particular by at least 1 °, in particular at least 5 °, and / or by at least 1%, in particular at least 5% , the first or second stagger angle of the second blade and / or by at most 75 °, in particular at most 45 °, and / or by at most 50%, in particular at most 25%, of the first or second stagger angle of the second blade.

As a result, advantageous flow conditions can be represented in one embodiment with different positions of the vane grid or the first and second blades and, in a further development, a performance and / or suction limit can be improved or, conversely, a deterioration in the flow conditions can be reduced by adjusting the blade grid.

In one embodiment, the adjustment device has a one-part or multi-part adjustment means, in particular a (adjustment) ring, for common and / or reversible, in particular in the same direction, adjustment of the first and second blades from the first to the second position, with which the first blade via at least one coupling member referred to here without loss of generality as the first coupling member, in particular a (first) adjusting lever, and the second blade via at least one in the present case without loss of generality as the second coupling member designated coupling member, in particular a (second) adjusting lever, is coupled. In this regard, reference is made to the aforementioned DE 103 51 202 A1 Reference is made and their content is expressly made the subject of the present disclosure.

Such, in particular common, adjusting means can advantageously adjust the first and second blades in one embodiment and thus adapt the blade grid to different boundary, in particular operating and / or flow conditions, whereby in one embodiment the corresponding adjustment of the blade profile sections is advantageous at the same time and thus the setting of their (first or second) graduation angles takes place.

In a further development, the adjusting means is or is rotationally and / or, in particular simultaneously, in particular positively coupled, translationally adjusted or adjustable or set up for this purpose, in particular around the axial direction or the rotational or (main) machine axis of the turbomachine. or displaceable in this direction or parallel thereto. Additionally or alternatively, in one embodiment, the adjusting means with the first coupling member is provided by a, in particular in a joint, in the present case referred to as the first joint without loss of generality, and / or with the second coupling member by a, in particular in one, in the present case without restriction of generality as second joint called joint connected. In a further development, the first coupling member is non-rotatably connected to a pivot axis of the first vane and / or the second coupling member is non-rotatably connected to a pivot axis of the second vane. In this regard, as mentioned, the aforementioned is in particular supplementary DE 103 51 202 A1 Referenced.

As a result, in one embodiment, the first and second blades can advantageously be adjusted and the blade grid can thus be adapted to different marginal, in particular operating and / or flow conditions, whereby in one embodiment the corresponding adjustment of the blade profile sections and thus the setting of their ( first or second) graduation angles.

In one embodiment, the first joint is a rotary and / or sliding joint and / or has at least one rotational or rotational degree of freedom, in particular in or around the radial direction, and / or at least one translational or sliding degree of freedom, in particular in the axial direction , on. Additionally or alternatively, in one embodiment, the second joint is a rotary and / or sliding joint and / or has at least one rotational or rotational degree of freedom, in particular in or around the radial direction, and / or at least one translational or sliding degree of freedom, especially in the axial direction.

As a result, advantageous adjustment kinematics can be represented in one embodiment, in particular different lever arm lengths can be compensated for in a development.

In one embodiment, the first joint is spaced apart from the second joint in the axial direction, in particular away from the first and / or second blade or (downstream) downwards.

As a result, the various staggering angles or adjustments can advantageously be implemented in one embodiment.

In one embodiment, a lever arm length of the first coupling member is different from a lever arm length of the second coupling member, in particular greater or, preferably, smaller than the lever arm length of the second coupling member, in particular by at least 1%, in particular at least 5%, and / or at most 50%, in particular at most 25% of the lever arm length of the first or second coupling link. In the present case, the lever arm length is a (Cartesian) distance between a connection of the coupling element to the adjustment means and a connection of the coupling element to the corresponding blade, in particular its adjustment, in particular pivot or rotation axis, or a (further) coupling element coupled thereto , Roger that.

As a result, the various staggering angles or adjustments can advantageously be implemented in one embodiment.

In one embodiment, an adjustment, in particular pivot or rotation axis of the first blade and an adjustment, in particular pivot or rotation axis of the second blade are aligned with one another in the circumferential direction or are at least substantially in the same axial position.

As a result, advantageous flow characteristics and / or adjustment kinematics can be represented in one embodiment.

According to one embodiment of the present invention, in order to adjust a blade grid described here, the first and second blades, in particular jointly, in particular by rotation and / or translation of the adjusting means, from the first position to the second position and thus the at least one blade profile section of the first and the second blade adjusted from the respective first to the respective second stagger angle, in particular pivoted or rotated, and / or from the second position to the first position and thus the at least one airfoil profile section of the first and second blades from the respective second back into the respective adjusted first stagger angle, in particular pivoted or rotated.

In one embodiment, the blade grid has a plurality of the first blades and / or a plurality of the second blades and / or a plurality of third, in particular further or different blades, two or more first blades and / or two or more second blades in groups or in Circumferential direction (in pairs) can be adjacent.

As a result, in one embodiment, advantageous flow characteristics and / or adjustment kinematics can be represented and / or undesired resonances between adjacent blades can be reduced.

Fig. 1

einen Teil einer Abwicklung eines Schaufelgitters nach einer Ausführung der vorliegenden Erfindung in einer ersten Stellung; und

Fig. 2

das Schaufelgitter in Fig. 1 entsprechender Darstellung in einer zweiten Stellung.

Further advantageous developments of the present invention emerge from the subclaims and the following description of preferred embodiments. This shows, partly schematically:

Fig. 1

a portion of a development of a blade grate according to an embodiment of the present invention in a first position; and

Fig. 2

the shovel grille in Fig. 1 corresponding representation in a second position.

Fig. 1 shows a part of a development of an adjustable blade grille, in particular a guide grille, of a turbo machine, in particular a compressor or turbine stage of a gas turbine, according to an embodiment of the present invention in a first position.

The blade grille has several in the circumferential direction (horizontally in Fig. 1 ) adjacent blades, in particular guide blades, of which in Fig. 1 only six are shown as examples.

In the Fig. 1 second shovel from the left, from the one in the settlement of the Fig. 1 an airfoil profile section 11 is shown, has a first distance B in each case from its two further blades 30 adjacent in the circumferential direction in the circumferential direction and represents a first blade 10.

In the Fig. 1 second shovel from the right, from the one in the settlement of the Fig. 1 an airfoil profile section 21 is shown at the same radial height as the airfoil profile section 11, has a second distance A in each case from its two other blades 40 adjacent in the circumferential direction, which is smaller than the first distance B (A <B), and represents one second blade 10.

The distance A or B is measured in the circumferential direction between radial pivot axes or pivot bearings 12, 32 and 22, 42 of the corresponding blades 10, 30 and 20, 40 to or in which the blades 10, 20, 30 or 40 are rotatably mounted and the in Fig. 1 are indicated by crosses.

The blades 10, 20, 30 and 40 are common, reversible and in the same direction from a first, in Fig. 1 shown, position, in a second, in Fig. 2 The position shown can be adjusted or rotated about their respective pivot axes 12, 22, 32 and 42.

In the first position (cf. Fig. 1 ) at least the airfoil profile section 11 of the first blade 10 has a first staggering angle β _1B (of the first blade 10) between its pressure-side profile tangent or tendon indicated by dash-dotted lines and the axial direction indicated by dash-double-dotted lines (vertical from bottom to top in Fig. 1 ), at least the airfoil profile section 21 of the second blade 20 has a first staggering angle β _{1A of the} same size and in the same direction (of the second blade 20).

In the second position (cf. Fig. 2 ) at least the airfoil profile section 11 of the first blade 10 has a second stagger angle β _2B (of the first blade 10), at least the airfoil profile section 21 of the second blade 20 has a second stagger angle β _2A (of the second blade 20) in the same direction.

The comparison of the Fig. 1 , 2 shows on the one hand that the second stagger angle β _{2B of} the first blade 10 or its airfoil profile section 11 is greater than the second stagger angle β _{2A of} the second blade 20 or its airfoil profile section 21, and on the other hand that the first stagger angle β _{1B of} the first blade 10 or its airfoil profile section 11 smaller than the second stagger angle β _{2B of} the first blade 10 or its airfoil profile section 11 and the first stagger angle β _{1A of} the second blade 20 or its airfoil profile section 21 smaller than the second stagger angle β _{2A of} the second blade 20 or its airfoil section 21 is.

This means that with smaller or more open staggering angles (cf. Fig. 1 ) advantageous outflow angles and with larger or more closed stagger angles (cf. Fig. 2 ) advantageous free flow cross-sections are realized between adjacent blades and thus each advantageous flow conditions are shown and a performance and a suction limit are improved.

The blade grid has in a known manner an adjusting device with an adjusting means in the form of a (adjusting) adjusting ring 50 for the common, reversible and in the same direction adjusting the blades 10, 20, 30 and 40 from the first to the second position with which the first Blade 10 via a first coupling element in the form of a (first) adjusting lever 51, the second blade 20 via a second coupling element in the form of a (second) adjusting lever 52 and the other or other blades 30, 40 in an analogous manner via a further coupling element in each case Form of a (further or different) adjusting lever 53 and 54 are coupled.

Like comparing the Fig. 1 , 2 shows and in Fig. 1 , 2 Indicated by corresponding movement arrows, the (Ver) adjusting ring 50 can be rotatory and thus positively coupled translationally in itself, in particular from the DE 103 51 202 A1 can be adjusted in a known manner.

For this purpose, the adjusting levers 51 - 54 are (rotationally) fixed with the corresponding pivot axes 12, 22, 32 and 42 of the blades 10, 20, 30 and 40 and are connected to the (adjusting) adjusting ring 50 by a joint 61 - 64 each, in particular the first adjusting lever 51 by a first swivel and sliding joint 61 with a rotational degree of freedom in the radial direction (perpendicular to the image plane of the Fig. 1 ) and a translational degree of freedom in the axial direction (vertical in Fig. 1 ) and the second adjusting lever 52 by a second swivel joint 62 with a rotational degree of freedom in the radial direction. A swivel and slide joint 61, 63 can be implemented in one embodiment by a sliding block which slides in an axial groove and to which the adjusting lever 51 or 53 is rotatably connected.

The first joint 61 and the joints 63 aligned therewith in the circumferential direction are spaced apart from the second joint 62 and the joints 64 aligned therewith in the circumferential direction away from the blades 10, 20, 30, 40 in the axial direction. Correspondingly, a lever arm length l _{51 of} the first adjusting lever 51 is smaller than a lever arm length l _{52 of} the second adjusting lever 52.

To adjust the vane grille, the rotation of the adjusting ring 50 around the (in Fig. 1 vertical) machine axis and with this a forced displacement in the axial direction, the first and second blades 10, 20 together from the first position (cf. Fig. 1 ) in the second position (cf. Fig. 2 ) adjusted, in which the airfoil profile sections 11, 21 have the different second stagger angles β _2B , β _2A , or vice versa, adjusted from the second position to the first position in which the airfoil profile sections 11, 21 have the same first stagger angles β _1B , β _1A exhibit.

Although exemplary embodiments have been explained in the preceding description, it should be pointed out that a large number of modifications are possible. It should also be pointed out that the exemplary designs are merely examples that are not intended to restrict the scope of protection, the applications and the structure in any way. Rather, the preceding description provides a person skilled in the art with guidelines for the implementation of at least one exemplary embodiment, with various changes, in particular with regard to the function and arrangement of the components described, being able to be made without departing from the scope of protection as it emerges from the claims and these equivalent combinations of features.

List of reference symbols

10

first shovel

11

Airfoil section of the first blade

12

Pivot axis / pivot bearing of the first blade

20th

second shovel

21st

Airfoil section of the second blade

22nd

Pivot axis / pivot bearing of the second blade

30; 40

another / other shovel

32; 42

Pivot axis / pivot bearing of the further / other blade

50

Adjusting ring (adjusting means)

51

first control lever (first coupling link)

52

second control lever (second coupling link)

53; 54

Control lever

61

first swivel and sliding joint

62

second swivel joint

63

Swivel and sliding joint

64

Swivel joint

A.

second distance

B.

first distance

l ₅₁

Lever arm length of first setting lever

l ₅₂

Lever arm length of the second setting lever

β _1B

first stagger angle of the first blade

β _1A

first stagger angle of the second blade

β _2B

second stagger angle of the first blade

β _2A

second stagger angle of the second blade

Claims (12)

1. Adjustable blade cascade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, comprising
   at least one first blade which has a first distance (B) in the circumferential direction from at least one blade (30) that is adjacent in the circumferential direction,
   at least one second blade, in particular stator blade (20), which has a second distance (A) in the circumferential direction from at least one blade (40) that is adjacent in the circumferential direction, which second distance is smaller than the first distance (B), and an adjustment device (50-54) for jointly adjusting the first and second blade from a first position, in which at least one airfoil profile section (11) of the first blade (10) and one airfoil profile section (21) of the second blade (20) each have a first stagger angle (β_1B; β_1A), into a second position, in which these airfoil profile sections (11,21) have second stagger angles (β_2B; β_2A),
   characterized in that the first stagger angle (β_1B) of the first blade (10) is equal to the first stagger angle (β_1A) of the second blade (20), and
   the second stagger angle (β_2B) of the first blade (10) differing from the second stagger angle (β_2A) of the second blade (20), in particular being larger than the second stagger angle (β_2A) of the second blade (20).
2. Adjustable blade cascade according to claim 1, characterized in that the first stagger angle (β_1B) of the first blade (10) differs from the first stagger angle (β_1A) of the second blade (20), in particular is smaller or larger than the first stagger angle (β_1A) of the second blade (20).
3. Adjustable blade cascade according to either of the preceding claims, characterized in that the first stagger angle (β_1B) of the first blade (10) is smaller or largerthan the second stagger angle (β_2B) of the first blade (10) and/or the first staggerangle (β_1A) of the second blade (20) is smaller or larger than the second stagger angle (β_2A) of the second blade (20).
4. Adjustable blade cascade according to any of the preceding claims, characterized in that the adjustment device comprises an adjustment means (50) for jointly and/or reversibly adjusting the first and second blade (10, 20) from the first position into the second position, to which adjustment means the first blade (10) is coupled via at least one first coupling member (51) and the second blade (20) is coupled via at least one second coupling member (52).
5. Adjustable blade cascade according to the preceding claim, characterized in that the adjustment means (50) is rotatably and/or translationally adjustable and/or is connected to the first coupling member (51) by a first joint (61) and/or to the second coupling member (52) by a second joint (62).
6. Adjustable blade cascade according to the preceding claim, characterized in that the first and/or second joint (61, 62) is a revolute and/or prismatic joint and/or has at least one rotational and/orat least one translational degree of freedom.
7. Adjustable blade cascade according to either of the two preceding claims, characterized in that the first joint (61) is spaced apart from the second joint (62) in the axial direction.
8. Adjustable blade cascade according to any of the preceding claims 4 to 7, characterized in that a lever arm length (1₅₁) of the first coupling member (51) differs from a lever arm length (1₅₂) of the second coupling member (52), in particular is smaller or larger than the lever arm length (1₅₂) of the second coupling member (52).
9. Adjustable blade cascade according to any of the preceding claims, characterized in that an adjustment axis (12) of the first blade (10) and an adjustment axis (22) of the second blade (20) are aligned with one another in the circumferential direction.
10. Adjustable blade cascade according to any of the preceding claims, characterized in that the distance of the first blade (10) in the circumferential direction from the at least one blade (30) that is adjacent in the circumferential direction is a distance between a or the adjustment axis (12) of the first blade (10) and a or the adjustment axis (32) of this adjacent blade (30) and/or in that the distance of the second blade (20) in the circumferential direction from the at least one blade (40) that is adjacent in the circumferential direction is a distance between a or the adjustment axis (22) of the second blade (20) and a or the adjustment axis (42) of this adjacent blade (40).
11. Turbomachine, in particular a gas turbine, having at least one adjustable blade cascade according to any of the preceding claims.
12. Method for adjusting a blade cascade according to any of claims 1 to 10, wherein the first and second blade (10, 20) are adjusted, in particular jointly and/or reversibly, from the first position into the second position in which the airfoil profile sections (11, 21) have the second stagger angles (β_2B; β_2A) that differfrom one another.

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