EP3269941B1 - Grille d'aube réglable pour turbomachines - Google Patents

Grille d'aube réglable pour turbomachines Download PDF

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Publication number
EP3269941B1
EP3269941B1 EP17180807.4A EP17180807A EP3269941B1 EP 3269941 B1 EP3269941 B1 EP 3269941B1 EP 17180807 A EP17180807 A EP 17180807A EP 3269941 B1 EP3269941 B1 EP 3269941B1
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EP
European Patent Office
Prior art keywords
blade
stagger angle
adjustable
circumferential direction
distance
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17180807.4A
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German (de)
English (en)
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EP3269941A1 (fr
Inventor
Alexander Halcoussis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Publication of EP3269941A1 publication Critical patent/EP3269941A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/129—Cascades, i.e. assemblies of similar profiles acting in parallel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall

Definitions

  • 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.
  • a device for adjusting guide vanes of a gas turbine 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.
  • 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.
  • 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
  • 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.
  • 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 lat
  • 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.
  • 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.
  • 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.
  • stagger angle 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • the first and / or second position of the first and / or second blade limits their (respective) adjustment range on one or both sides.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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 coup
  • 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.
  • 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.
  • 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.
  • 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.
  • the aforementioned is in particular supplementary DE 103 51 202 A1 Referenced.
  • 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.
  • 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.
  • 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.
  • advantageous adjustment kinematics can be represented in one embodiment, in particular different lever arm lengths can be compensated for in a development.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • advantageous flow characteristics and / or adjustment kinematics can be represented and / or undesired resonances between adjacent blades can be reduced.
  • 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.
  • 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.
  • At least the airfoil profile section 11 of the first blade 10 has a first staggering angle ⁇ 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 ⁇ 1A of the same size and in the same direction (of the second blade 20).
  • At least the airfoil profile section 11 of the first blade 10 has a second stagger angle ⁇ 2B (of the first blade 10)
  • at least the airfoil profile section 21 of the second blade 20 has a second stagger angle ⁇ 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 ⁇ 2B of the first blade 10 or its airfoil profile section 11 is greater than the second stagger angle ⁇ 2A of the second blade 20 or its airfoil profile section 21, and on the other hand that the first stagger angle ⁇ 1B of the first blade 10 or its airfoil profile section 11 smaller than the second stagger angle ⁇ 2B of the first blade 10 or its airfoil profile section 11 and the first stagger angle ⁇ 1A of the second blade 20 or its airfoil profile section 21 smaller than the second stagger angle ⁇ 2A of the second blade 20 or its airfoil section 21 is.
  • 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.
  • 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
  • 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.
  • 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.
  • 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.

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Claims (12)

  1. Grille d'aube réglable pour turbomachines, en particulier un étage de compresseur ou de turbine d'une turbine à gaz, comprenant au moins une première aube, présentant une première distance (B) dans le sens circonférentiel par rapport à au moins une aube adjacente (30) dans le sens circonférentiel, au moins une seconde aube, en particulier une aube directrice (20), présentant dans le sens circonférentiel une seconde distance (A) par rapport à au moins une aube (40) adjacente dans le sens circonférentiel, laquelle seconde distance est inférieure à la première distance (B), et un dispositif de réglage (50-54) servant à régler conjointement les première et secondeaubes à partir d'une première position, dans laquelle au moins une section de profil de pale d'aube (11) de la première aube (10) et une section de profil de pale d'aube (21) de la seconde aube (20) présentent chacune un premier angle de décalage (β1B ; β1A), dans une seconde position, dans laquelle lesdites sections de profil de pale d'aube (11, 21) présentent des seconds angles de décalage (β2B; β2A), caractérisée en ce que le premier angle de décalage (β1B) de la première aube (10) est égal au premier angle de décalage (β1A) de la seconde aube (20), et dans laquelle le second angle de décalage (β2B) de la première aube (10) est différent du second angle de décalage (β2A) de la seconde aube (20), en particulier est supérieur au second angle de décalage (β2A) de la seconde aube (20).
  2. Grille d'aube réglable selon la revendication 1, caractérisée en ce que le premier angle de décalage (β1B) de la première aube (10) est différent du premier angle de décalage (β1A) de la seconde aube (20), en particulier est inférieur ou supérieurau premier angle de décalage (β1A) de la seconde aube (20).
  3. Grille d'aube réglable selon l'une des revendications précédentes, caractérisée en ce que le premier angle de décalage (β1B) de la première aube (10) est inférieur ou supérieur au second angle de décalage (β2B) de la première aube (10) et/ou en ce que le premier angle de décalage (β1A) de la seconde aube (20) est inférieur ou supérieur au second angle de décalage (β2A) de la seconde aube (20).
  4. Grille d'aube réglable selon l'une des revendications précédentes, caractérisée en ce que le dispositif de réglage comporte un moyen de réglage (50) pour régler conjointement et/ou réversiblement les première et seconde aubes(10,20) de la première à la seconde position, la première aube (10) étant accouplée audit moyen de réglage par l'intermédiaire d'au moins un premier élément d'accouplement (51) et la seconde aube (20) étant accouplée audit moyen de réglage par l'intermédiaire d'au moins un second élément d'accouplement (52).
  5. Grille d'aube réglable selon la revendication précédente, caractérisée en ce que le moyen de réglage (50) est réglable en rotation et/ou en translation et/ou est relié au premier élément d'accouplement (51) par un premier joint (61) et/ou au second élément d'accouplement (52) parun second joint (62).
  6. Grille d'aube réglable selon la revendication précédente, caractérisée en ce que le premier et/ou le second joint (61, 62) est un joint rotatif et/ou de poussée et/ou présente au moins un degré de liberté en rotation et/ou au moins en translation.
  7. Grille d'aube réglable selon l'une des deux revendications précédentes, caractérisée en ce que le premier joint (61) est espacé du second joint (62) dans le sens axial.
  8. Grille d'aube réglable selon l'une des revendications 4 à 7 précédentes, caractérisée en ce que la longueur de bras de levier (151) du premier élément d'accouplement (51) est différente d'une la longueur de bras de levier (152) du second élément d'accouplement (52), en particulier inférieure ou supérieure à la longueur de bras de levier (152) du second élément d'accouplement (52).
  9. Grille d'aube réglable selon l'une des revendications précédentes, caractérisée en ce qu'un axe de réglage (12) de la première aube (10) et un axe de réglage (22) de la seconde aube (20) sont alignés dans le sens circonférentiel.
  10. Grille d'aube réglable selon l'une des revendications précédentes, caractérisée en ce que la distance entre la première aube (10) et l'au moins une aube adjacente (30) dans le sens circonférentiel est une distance entre un ou l'axe de réglage (12) de la première aube (10) et un ou l'axe de réglage (32) de ladite aube adjacente (30) et/ou en ce que la distance entre la seconde aube (20) et l'au moins une aube adjacente (40) dans le sens circonférentiel est une distance entre un ou l'axe de réglage (22) de la seconde aube (20) et un ou l'axe de réglage (42) de ladite aube adjacente (40).
  11. Turbomachine, en particulier turbine à gaz, comprenant au moins une grille d'aubes réglable selon l'une des revendications précédentes.
  12. Procédé de réglage d'une grille d'aube selon l'une des revendications 1 à 10, dans laquelle les première et seconde aubes (10, 20) sont réglées, en particulier conjointement et/ou réversiblement, de la première position à la seconde position dans laquelle les sections de profil de pale d'aube (11, 21) comportent des seconds angles de décalage (β2B ; β2A) différents.
EP17180807.4A 2016-07-13 2017-07-11 Grille d'aube réglable pour turbomachines Active EP3269941B1 (fr)

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DE102016212767.5A DE102016212767A1 (de) 2016-07-13 2016-07-13 Verstellbares Turbomaschinen-Schaufelgitter

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DE102018119704A1 (de) * 2018-08-14 2020-02-20 Rolls-Royce Deutschland Ltd & Co Kg Schaufelrad einer Strömungsmaschine
US11168580B2 (en) * 2020-01-08 2021-11-09 GM Global Technology Operations LLC Engine system including pivoting vane turbocharger having vane(s) that are adjustable to one position while other vane(s) of the turbocharger are adjusted to another position
DE102021123772A1 (de) 2021-09-14 2023-03-16 MTU Aero Engines AG Verstellanordnung für verstellschaufeln einer strömungsmaschine
US11840987B2 (en) * 2022-04-05 2023-12-12 General Electric Company Cascade thrust reverser assembly for a gas turbine engine

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US3861822A (en) * 1974-02-27 1975-01-21 Gen Electric Duct with vanes having selectively variable pitch
GB1511723A (en) * 1975-05-01 1978-05-24 Rolls Royce Variable stator vane actuating mechanism
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EP3269941A1 (fr) 2018-01-17
US10711798B2 (en) 2020-07-14
DE102016212767A1 (de) 2018-01-18
US20180017081A1 (en) 2018-01-18

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