EP3269941A1 - Adjustable cascade for turbomachine - Google Patents

Abstract

The present invention relates to an adjustable vane grille for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one first vane, in particular vane (10), which has a first distance (B) in the circumferential direction from a circumferentially adjacent vane (30). comprising, at least one second blade, in particular stator blade (20), which has a second distance (A) in the circumferential direction from a circumferentially adjacent blade (40), which is smaller than the first distance (B), and an adjusting device (50). 54) for, in particular common and / or reversible, adjusting the first and second blades from a first position, in the at least one airfoil profile section (11) of the first blade (10) and a blade profile section (21) of the second blade (20) each one first staking angle (² 1B; ² 1A), to a second position in which these airfoil profiles second (11, 21) second stagger angle (² 2B; 2A), wherein the second stagger angle (2B) of the first blade (10) is different from the second stagger angle (2A) of the second blade (20), in particular greater than the second stagger angle (2A) of the second blade (20 ).

Description

The present invention relates to an adjustable blade grid for a turbomachine, in particular a compressor or turbine stage of a gas turbine, a turbomachine, in particular gas turbine, with the adjustable blade grid and a method for adjusting the blade grid.

From the DE 103 51 202 A1 a device for adjusting vanes of a gas turbine is known in which vanes are pivotally connected via adjusting levers with a collar, all the vanes of the same vane ring are uniformly pivoted on the collar.

From the US 2015/0159551 A1 For example, a vane ring with variable vanes is known wherein two vanes are circumferentially spaced apart from each other by two other cyclic spacing vanes.

An 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 grid having the features of claim 1. Claims 11, 12 provide protection for 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 turbomachine, in particular for a compressor or turbine stage of a gas turbine, in particular at least one adjustable vane grille of a turbomachine, in particular at least one compressor and / or at least one turbine stage of a gas turbine, (at least) a presently referred to as a first blade without restriction of generality blade, in particular stator or housing-side and / or vane, of one or both in the circumferential direction adjacent, in particular further, blade (s), in particular (further) stator or housing-side and / or vane (s), in the circumferential direction (each) a present herein without limitation of the generality referred to as the first distance distance, and at least one present without Restriction of the general public as a second blade designated blade, in particular stator or housing-side and / or vane, of one or both circumferentially adjacent, in particular other, blade (s), in particular (other) stator or housing side and / or vane (n), in the circumferential direction (in each case) has a distance referred to herein as a second distance without limiting the generality. The invention can be used with particular advantage in guide vane grids, in particular of compressor stages, in particular high-pressure compressor stages, of gas turbines, without being limited thereto.

According to an 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, in particular undesirable resonances between adjacent blades can be reduced.

According to one embodiment of the present invention, the blade grid has an adjusting device, by which the first blade, in particular reversibly, of a present without limitation of generality as the first position (the first blade, in particular the blade grid) position, in particular angular position, in the at least an airfoil profile section of the first blade has a staggering angle, referred to herein as a first staggering angle (the first blade), into a position, in particular an angular position, referred to herein as a second position (the first blade or the blade lattice) without limiting the generality (at least) this airfoil profile section (of the first blade) has a staggering angle, referred to herein as a second staggering angle (the first blade), without restriction of generality, and, in particular together with the first Shovel and / or reversible and / or in the same direction, the second blade of one or the present without limitation of generality as the first position (the second blade or the blade lattice) designated position, in particular angular position, in the at least one airfoil profile section of the second blade one presently referred to as the first staggering angle (of the second blade), without being limited to the generality, into the position (in particular angular position) which is presently referred to without restriction of generality as the second position (the second blade or the blade grille) in which (at least) this airfoil profile section (the second blade) has a staggering angle referred to herein as a second staggering angle (the second blade), adjustable, in particular pivotable or rotatable, is or adjusted, in particular pivoted or turned, is or hi erzu is set up or is used.

According to an embodiment of the present invention, the second staggering angle of the first blade is different from the, in particular equidirectional, second staggering angle of the second blade, in particular greater than the second staggering angle of the second blade, in particular at least 1 °, in particular at least 5 °, and / or by at least 1%, in particular at least 5%, of the first or second staggering angle of the first or second blade and / or by at most 45 °, in particular at most 25 °, and / or at most 50%, in particular at most 25%, of the first or second Stagger angle of the first or second blade.

In this way, in an embodiment with different positions of the blade grid or of the first and second blades, respectively advantageous flow conditions can be represented and improved in a development, a performance and / or suction limit or vice versa deterioration of the flow conditions can be reduced by adjusting the blade grid. In particular, in one embodiment, at smaller or more open staggering angles, advantageous outflows, in particular outflow angles, and / or advantageous ratios, in particular free flow cross sections between adjacent blades, can be represented for larger or more closed staggering angles.

As staggering angle or "stagger angle" is in this case in a customary manner the angle designated by the pressure side tangent to the respective airfoil profile section or the (pressure side) profile tangent or cord ("cord line") includes the axial direction. In one embodiment, the stagger angle β in the usual way is equal to half the sum of 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 blade or of their respective blade is in one embodiment an airfoil profile section at the same radial height, in particular an airfoil section cut at the blade leaf root, at the blade tip or at half the radial blade blade height. Accordingly, in one embodiment in the first position of the first and second blades, at least one airfoil profile intersection of the first airfoil has the first stagger angle of the first blade and a second blade airfoil 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 blade or the blade lattice of this airfoil profile section of the first blade on the second staggering angle of the first blade and this airfoil profile section of the second blade on the second staggering angle of the second blade.

As an axial direction, a direction parallel to a rotational or (main) machine axis of the turbomachine or gas turbine (in particular) is present, in particular in the usual way, in particular from a turbomachine or blade grate inlet or inlet to a turbomachine or blade air outlet ., denotes, as a radial direction corresponding to a direction of rotation or (main) machine axis perpendicular direction away from this axis, as a circumferential direction according to a rotation or rotation about this axis or a rotor of the turbomachine or gas turbine ( nstufe), in particular the adjustable blade grid or an adjustable blade vane axially adjacent blade lattice.

As a distance or pitch between two circumferentially adjacent blades in the circumferential direction is present in particular in the usual way an angle between adjusting, in particular pivoting or rotating axes, the two adjacent blades or a corresponding circumferential or segment length referred to, in particular a scope - or segment length between 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 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 on at least one radial height.

Similarly, in one embodiment, the first stagger angle of the first blade may be different from the, in particular equidirectional, first stagger angle of the second blade, in particular greater or, preferably, less than the first stagger angle of the second blade, in particular at least 1 °, in particular at least 5 °, and / or at least 1%, in particular at least 5%, of the first or second staggering angle of the first or second blade and / or at most 45 °, in particular at most 25 °, and / or 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 cut in at least one (second) position a larger and in at least one (first) position a smaller staggering angle than the second blade or its at least one airfoil profile section. In another embodiment, the stagger angle of the first blade or of its at least one airfoil profile section is always or over the entire adjustment greater or smaller than the second staggering angle of the second blade or its at least one airfoil profile section.

In this way, in an embodiment with different positions of the blade grid or of the first and second blades, respectively advantageous flow conditions can be represented and improved in a development, a performance and / or suction limit or vice versa deterioration of 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 its (respective) adjustment range on one or both sides. Likewise, in one embodiment, the first vane may extend from the first position beyond the second position and / or from the second position beyond the first position and / or the second vane may extend beyond the second position and / or from the second position Be adjustable position beyond the first position or be adjusted or be set up for this purpose.

In this way, in an embodiment with different positions of the blade grid or of the first and second blades, respectively advantageous flow conditions can be represented and improved in a development, a performance and / or suction limit or vice versa deterioration of the flow conditions can be reduced by adjusting the blade grid.

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

In this way, in an embodiment with different positions of the blade grid or of the first and second blades, respectively advantageous flow conditions can be represented and improved in a development, a performance and / or suction limit or vice versa deterioration of the flow conditions can be reduced by adjusting the blade grid.

In one embodiment, the adjusting device has a one- or multi-part adjusting means, in particular a (Ver) adjusting ring, for common and / or reversible, in particular co-original, adjusting the first and second blades from the first to the second position, with which the first blade via at least one presently known without limitation of generality as a first coupling member coupling member, in particular a (first) lever, and the second blade via at least one present herein without limiting the generality as a second coupling member called coupling member, in particular a (second) lever is coupled. In this regard, in addition to the above-mentioned DE 103 51 202 A1 Reference is made and the content thereof is expressly made the subject of the present disclosure.

In one embodiment, the first and second blades can advantageously be adjusted by means of such an adjustment means, in particular common ones, and so the blade grid can be adapted to different boundary conditions, in particular operating conditions and / or flow conditions. In one embodiment, the corresponding adjustment of the blade airfoil sections is advantageous and thus the adjustment of their (first or second) stagger angles.

In one development, the adjusting means is or is rotatory and / or, in particular simultaneously, in particular force-coupled, translationally adjusted or adjustable or adapted thereto, in particular rotates about the axial direction or rotation or (main) machine axis of the turbomachine and / or or displaceable in this direction or parallel thereto. Additionally or alternatively, in one embodiment, the adjusting means with the first coupling member by a, in particular in one, herein without limiting the generality as a first joint designated joint and / or with the second coupling member by a, in particular in one, present connected without restriction of generality as a second joint called joint. In a development, the first coupling member is non-rotatably connected to a pivot axis of the first blade and / or the second coupling member rotatably connected to a pivot axis of the second blade. In this regard, as mentioned, in particular supplementary to the above-mentioned DE 103 51 202 A1 Referenced.

As a result, in one embodiment, the first and second blades are advantageously adjusted and so the blade grid at different marginal, especially operating and / or flow conditions are adjusted, in one embodiment at the same time advantageously the corresponding adjustment of the airfoil profile sections and thus the setting of the ( first or second) stagger 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 about 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 about the radial direction, and / or at least one translational or sliding degree of freedom, especially in the axial direction, on.

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

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

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

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 larger 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%, the lever arm length of the first or second coupling member. As Hebelarmlänge is present in particular in the usual way a (Cartesian) distance between a connection of the coupling member to the adjustment and a connection of the coupling member to the corresponding blade, in particular their adjustment, in particular pivot or rotation axis or a coupled (further) coupling member , Understood.

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

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

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

According to one embodiment of the present invention, for adjusting a blade grid described here, the first and second blades, in particular in common, in particular by rotation and / or translation of the adjusting means, from the first position to the second position and so the at least one airfoil profile section of the first and second second bucket of the respective first in the respective second staggering angle adjusted, in particular pivoted or rotated, and / or from the second position to the first position and so the at least one airfoil profile section of the first and the second blade of the respective second again in the respective first staggered angle adjusted, 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 other, blades, wherein two or more first blades and / or two or more second blades in groups or in Circumferential direction (in pairs) may be adjacent.

As a result, in one embodiment, an advantageous flow characteristic and / or adjustment kinematics can be represented and / or unwanted 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 will become apparent from the dependent claims and the following description of preferred embodiments. This shows, partially schematized:

Fig. 1

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

Fig. 2

the paddle grid in Fig. 1 corresponding representation in a second position.

Fig. 1 shows a portion of a development of an adjustable blade, in particular Leitgitters, a turbomachine, 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 grid has a plurality of circumferentially (horizontally in Fig. 1 ) adjacent blades, in particular vanes, of which in Fig. 1 only six are shown by way of example.

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

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

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, respectively, in which the blades 10, 20, 30 and 40 are rotatably mounted and the in Fig. 1 are indicated by crosses.

The blades 10, 20, 30 and 40 are common by an adjusting, reversible and in the same direction of a first, in Fig. 1 represented, position, in a second, in Fig. 2 shown, adjustable position or about their respective pivot axes 12, 22, 32 and 42 rotatable.

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 (the first blade 10) between its dash-dot-line pressure side profile tangent and the dash-and-dot direction indicated axial direction (vertically from bottom to top in FIG Fig. 1 ), at least the airfoil profile section 21 of the second blade 20 an equal and same direction first stagger angle β _1A (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 staggering angle β _2B (the first blade 10), at least the airfoil profile section 21 of the second blade 20 has a second staggering angle β _2A (the second blade 20) which is in the same direction.

The comparison of 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, secondly, that the first stagger angle β _{1B of} the first blade 10 or its airfoil profile section 11 is 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 their Airfoil profile section 21 is.

As a result, smaller or more open stagger angles (cf. Fig. 1 ) advantageous outflow angle and larger or more closed stagger angles (see. Fig. 2 ) realized advantageous flow cross-sections between adjacent blades and so each advantageous flow conditions are shown and a performance and a suction limit can be improved.

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

How the comparison of Fig. 1 . 2 shows and in Fig. 1 . 2 indicated by corresponding movement arrows, the (Ver) collar 50 rotatory and thus forcibly coupled translational in itself, in particular from the DE 103 51 202 A1 , be known manner be adjusted.

For this purpose, the adjusting levers 51-54 are fixedly connected to the corresponding pivot axes 12, 22, 32 and 42 of the blades 10, 20, 30 and 40 (rotating) and to the (locking) adjusting ring 50 by a respective joint 61-64. in particular the first adjusting lever 51 by a first rotary and sliding joint 61 with a rotational degree of freedom in the radial direction (perpendicular to the image plane of Fig. 1 ) and a translatory degree of freedom in the axial direction (vertically in Fig. 1 ) and the second adjusting lever 52 by a second pivot 62 with a rotational degree of freedom in the radial direction. One Rotary and thrust joint 61, 63 may be realized in one embodiment by a sliding block which slides in an axial groove and with which the adjusting lever 51 and 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 circumferentially aligned joints 64 in the axial direction away from the blades 10, 20, 30, 40. Accordingly, a Hebelarmlänge l _{51 of} the first actuating lever 51 is smaller than a Hebelarmlänge l _{52 of} the second actuating lever 52nd

To adjust the blade grid are by the movement arrows indicated by rotation of the (Ver) adjusting ring 50 to the (in Fig. 1 vertical) machine axis and thus force-coupled displacement in the axial direction of the first and second blades 10, 20 together from the first position (see. Fig. 1 ) in the second position (see. Fig. 2 ), in which the airfoil profile cuts 11, 21 have the mutually different second staggering angles β _2B , β _2A , or vice versa, from the second position to the first position, in which the airfoil profile cuts 11, 21 have the same first staking angles β _1B , β _1A exhibit.

Although exemplary embodiments have been explained in the foregoing description, it should be understood that a variety of modifications are possible. It should also be noted that the exemplary embodiments are merely examples that are not intended to limit the scope, applications and construction in any way. Rather, the expert is given by the preceding description, a guide 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, can be made without departing from the scope, as it turns out according to the claims and these equivalent combinations of features.

LIST OF REFERENCE NUMBERS

10

first shovel

11

Airfoil profile section of the first blade

12

Swivel axle / pivot bearing of the first blade

20

second shovel

21

Airfoil profile section of the second blade

22

Swivel axle / pivot bearing of the second blade

30; 40

further / other shovel

32; 42

Swivel axle / pivot bearing of the other / other bucket

50

(Ver) adjusting ring (adjusting means)

51

first lever (first link)

52

second lever (second link)

53; 54

lever

61

first turning and sliding joint

62

second pivot

63

Turning and sliding joint

64

swivel

A

second distance

B

first distance

₅₁

Lever arm length of first lever

₅₂

Lever arm length second lever

β _1B

first stagger angle of the first shovel

β _1A

first stagger angle of the second blade

β _2B

second stagger angle of the first shovel

β _2A

second stagger angle of the second blade

Claims (12)

Adjustable vane grille for a turbomachine, in particular a compressor or turbine stage of a gas turbine, with at least one first vane, in particular vane (10) having a first distance (B) from at least one circumferentially adjacent vane (30) in the circumferential direction, at least one second vane, in particular vane (20), which has a second distance (A) which is smaller than the first distance (B) from at least one circumferentially adjacent vane (40) in the circumferential direction, and an adjusting device (50-54) for in particular common and / or reversible, adjusting the first and second blades from a first position, in which at least one airfoil section cut (11) of the first blade (10) and a blade airfoil section (21) of the second blade (20) each have a first skip angle (FIG. β _1B , β _1A ), into a second position in which these airfoil profile sections (11, 21) second stagger angles (β _2B ; β _2A ), wherein the second stagger angle (β _2B ) of the first blade (10) differs from the second stagger angle (β _2A ) of the second blade (20), in particular greater than the second stagger angle (β _2A ) of the second blade (20 ). An adjustable vane grille according to claim 1, characterized in that the first stagger angle (β _1B ) of the first vane (10) is equal to the first stagger angle (β _1A ) of the second vane (20). An adjustable vane grille according to claim 1, characterized in that the first stagger angle (β _1B ) of the first vane (10) is different from the first stagger angle (β _1A ) of the second vane (20), in particular smaller or larger than the first stagger angle (β _1A ) of the second blade (20). Adjustable vane grille according to one of the preceding claims,
characterized in that the first stagger angle (β _1B ) of the first blade (10) is less than or greater than the second stagger angle (β _2B ) of the first blade (10) and / or the first stagger angle (β _1A ) of the second blade (20) is smaller or larger than the second stagger angle (β _2A ) of the second blade (20). Adjustable vane grille according to one of the preceding claims,
characterized in that the adjusting device has an adjusting means (50) for the common and / or reversible adjustment of the first and second blades (10, 20) from the first to the second position, with which the first blade (10) via at least one first coupling member (51) and the second blade (20) is coupled via at least one second coupling member (52). Adjustable vane grille according to the preceding claim, characterized in that the adjusting means (50) rotatably and / or translationally adjustable and / or with the first coupling member (51) by a first joint (61) and / or with the second coupling member (52) a second hinge (62) is connected. Adjustable vane grille according to the preceding claim, characterized in that the first and / or second joint (61, 62) is a rotary and / or sliding joint and / or has at least one rotational and / or at least one translational degree of freedom. Adjustable vane grille according to one of the two preceding claims, characterized in that the first joint (61) is spaced from the second joint (62) in the axial direction. Adjustable vane grille according to one of the preceding claims 5 to 8, characterized in that a Hebelarmlänge (l ₅₁ ) of the first coupling member (51) of a Hebelarmlänge (l ₅₂ ) of the second coupling member (52) different, in particular smaller or larger than the Hebelarmlänge ( l ₅₂ ) of the second coupling member (52). Adjustable vane grille according to one 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) in the circumferential direction are aligned. Turbomachine, in particular gas turbine, with at least one adjustable blade grid according to one of the preceding claims. Method for adjusting a vane grille according to one of the preceding claims, wherein the first and second vane (10, 20), in particular jointly and / or reversibly, are moved from the first position to the second position in which the vane profile sections (11, 21) have the mutually different second stagger angles (β _2B , β _2A ).

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