EP3524778A1 - Connexion à levier d'un positionnement d'aube directrice pour turbomachines et procédé de fabrication associé - Google Patents

Connexion à levier d'un positionnement d'aube directrice pour turbomachines et procédé de fabrication associé Download PDF

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Publication number
EP3524778A1
EP3524778A1 EP19156350.1A EP19156350A EP3524778A1 EP 3524778 A1 EP3524778 A1 EP 3524778A1 EP 19156350 A EP19156350 A EP 19156350A EP 3524778 A1 EP3524778 A1 EP 3524778A1
Authority
EP
European Patent Office
Prior art keywords
lever
connection
blade shank
shank
vane
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.)
Granted
Application number
EP19156350.1A
Other languages
German (de)
English (en)
Other versions
EP3524778B1 (fr
Inventor
Werner Humhauser
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
Original Assignee
MTU Aero Engines AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP3524778A1 publication Critical patent/EP3524778A1/fr
Application granted granted Critical
Publication of EP3524778B1 publication Critical patent/EP3524778B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • 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
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/79—Bearing, support or actuation arrangements therefor

Definitions

  • the invention relates to a lever connection of a vane adjustment of a turbomachine for establishing a connection between a guide vane and an actuator according to the preamble of patent claim 1, a method for establishing a connection between a vane and an actuator and a turbomachine.
  • Compressors in axial flow machines generally comprise a vane adjustment in the area of the front compressor stages or in the high-pressure compressor. Due to the vane adjustment, the guide vanes of the relevant guide vane row are adjusted speed-dependent about their vertical axis, so that an absolute Leitradabströmwinkel is changeable. As a result, a stall during startup of the turbomachine or at low speeds can be prevented. A step load is reduced. Alternatively, a stall could be realized by an adjustment of the blades of the compressor stages, but this is technically much more complicated, so that the adjustment of the vanes has prevailed.
  • the adjustment of the guide vanes of a row of vanes is conventionally carried out mechanically by actuation of an actuator.
  • the actuator acts via an adjusting ring and one adjusting lever on the guide vanes.
  • the adjusting ring is arranged outside the turbomachine and usually positioned in the flow direction behind and coaxial with the row of guide blades. It is displaceable in the circumferential direction and in the axial direction of the turbomachine.
  • the adjusting rings are actuated at the same time via a control lever of the actuator which is mounted rotatably on the compressor housing and which extends in the axial direction of the turbomachine and is connected to the adjusting rings.
  • the adjusting lever hereinafter also referred to simply as a lever for simplicity, is inserted in the radial direction of the turbomachine onto a vane shaft extending in the vertical direction of the vane. Thereafter, the lever is fixed in a form-fitting manner at a contact region of the blade shank and by a screw connection secured in position.
  • the screwing can be done by an internal thread or by an external thread.
  • This type of lever connection requires a sufficiently thick blade shank for the design of the contact surfaces.
  • the shaft diameter can hardly be greater than the smallest possible external thread due to the geometric boundary conditions such as small flow channel diameter and high number of blades.
  • the displacement lever has a claw-type connection section for connection to a blade shank.
  • the connecting portion has two opposing jaw members extending from an underside of the adjusting lever and defining a slot extending in the lever longitudinal direction.
  • the slot is open at its two end faces over its entire cross section.
  • a slot is introduced that represents an opening to the top of the adjusting lever.
  • the lever is pushed with its slot over the blade shank, until the opposite jaw surfaces are in rotationally fixed positive engagement with corresponding shank surfaces. Subsequently, the lever is secured by means of a screwed into an internally threaded bore of a free end of the blade shank screw on the blade shank radially, which is guided through the slot.
  • a lever connection with a slot in a connecting portion of an adjusting lever is also in the patent EP 2 273 074 B1 shown.
  • the slot is bounded by side hook elements, which engage in the mounted state in lateral grooves of a blade shank.
  • the slot is opened via a bore to the top of the adjusting lever for performing a screw.
  • the object of the invention is to provide a lever connection of a vane adjustment of a turbomachine for establishing a connection between a guide vane and an actuator, which eliminates the disadvantages mentioned.
  • An inventive lever connection of a vane adjustment of a turbomachine for establishing a connection between a vane and an actuator wherein the vane has a vane shank which extends along its vertical axis and which can be brought by means of a lever with an adjusting ring of the actuator in connection, provides that the blade shank has a contact region which is reduced in cross-section with respect to a radially outer shank region.
  • the lever has a connecting portion with a slot and a threading opening.
  • the slot has opposite key surfaces for non-rotatable operative connection with contact surfaces of the contact area.
  • the blade shank diameter in the region radially outside of the shaft-lever connection point may have the same diameter as radially inside.
  • the height of the contact surfaces for transmitting the torque of the adjusting forces via the lever does not affect the outer diameter of the blade shank, as is the case with conventional compounds such as wedge surfaces or cone geometries.
  • a minimum diameter of 5 mm driven by a M5 lock nut shank nut can be realized.
  • the radially outer part of the blade shaft can have the exact same diameter as the radially inner part of the blade shaft.
  • the diameter of the contact area need not be greater than the outer diameter of the radially outer shank area, whereby the lever connection according to the invention is also suitable for very small shank diameters.
  • the blade shank diameter is therefore no longer the decisive factor in the formation of the contact region.
  • a reliable connection of the lever to the blade shank is possible even with a small shovel shaft diameter.
  • the lever connection is particularly suitable for use in compressors of turbomachines that require a high number of blades with a small available space, such as aircraft engines or compact industrial gas turbines. Due to the virtually non-existent geometric boundary conditions of the blade shank, the shank diameter can be significantly reduced.
  • a positive connection between the connecting portion of the lever and the contact region of the blade shank is achieved in one embodiment in that the key surfaces and corresponding contact surfaces are each parallel surfaces.
  • the contact surfaces are the same in size and shape.
  • the key surfaces are preferably also the same size and shape for assembly reasons.
  • the key surfaces and the contact surfaces may be set at an angle to each other.
  • the wrench flats and contact surfaces viewed in the longitudinal direction of the blade shank, viewed in the same way as the legs of an isosceles triangle can be made to be quasi roof-shaped relative to one another.
  • a multi-angle, trapezoidal and similar orientation and the like are also conceivable.
  • the wrench flats and / or the contact surfaces can be adjusted such that in the transition region from the threading hole into the slot insertion bevels are formed, which form a kind tapering in the mounting direction funnel and facilitate the transition of the blade shank from the threading into the slot during assembly , It is essential that the key surfaces and the contact surfaces are not rotationally symmetrical to the vertical axis, and that the form-fitting is free of play. In principle, a key surface and a corresponding contact surface already suffice to achieve a rotationally fixed locking.
  • the contact surfaces can be easily produced by cross-sectional tapering of the blade shank. For example, they can be made by milling. Due to the design as cross-sectional tapers, shoulder surfaces which act as a support for the connecting section in the mounted state also arise in the transition region of the contact surfaces to a shaft region radially adjacent to the contact region.
  • the lever can be additionally braced with the blade shank.
  • the screw can for example be a nut which cooperates with the radially outer shaft portion, in particular a free end of the blade shank.
  • the nut is preferably self-locking.
  • an internal thread can be formed with appropriate adjustment of the mother.
  • a securing element can additionally be provided for the arrangement between the connecting section and the screw element, which has, for example, an angled arm for lateral contact with the screw element and / or the connecting section.
  • the at least one arm can be applied after tightening without the use of additional tools on the screw and / or the connecting portion. In particular, several arms may be provided, so that when a poor arm still a reliable backup is guaranteed.
  • the transmission of the torque from the actuator for adjusting the blades is preferably carried out exclusively via the positive connection.
  • the screw is used primarily to secure the lock.
  • the lever can cooperate with an adjusting ring pin which is adapted to mount the lever by means of a radial movement on the adjusting ring.
  • the lever has a passage or through hole through which the respective adjusting ring pin is guided. This allows a fast and safe installation.
  • the adjusting ring pin can have, for example, an annular shoulder which acts as a pushing-on or insertion limit.
  • the Verstellringit is fixed after reaching its desired position on the lever.
  • a vane shank that extends extends along its vertical axis and is brought by means of a lever directly or indirectly with an adjusting ring of the actuator
  • the lever is pushed radially from a first mounting direction on the blade shank and then locked by a movement in a second mounting direction with the shovel shaft form-fitting manner.
  • the second mounting direction and the second mounting direction are different.
  • the first mounting direction and the second mounting direction preferably extend orthogonal to each other, for example, the second mounting direction extends in the axial direction. Due to the different second mounting direction is already without a bracing a lock.
  • the lever can now neither lifted, move neither radially inward nor radially outward.
  • a turbomachine according to the invention has a multiplicity of the lever connections according to the invention for establishing a connection between guide vanes of an adjusting blade row and an actuator. Due to the lever connections according to the invention, vane adjustments in guide vanes with a very small shaft diameter and / or in a very close distance from each other are possible. For example, the vane adjustments of the front compressor stages or of the high-pressure compressor such lever connections, so that the turbomachine can be equipped with a very powerful or performance-optimized compressor.
  • information such as “radial”, “radially outside”, “radially inward”, “coaxial” and “circumferential direction” refers to a machine longitudinal axis X of the turbomachine according to the invention, which represents the axis of rotation of a rotor of the turbomachine.
  • FIG. 1 shows a vane adjustment of vanes of an adjustable row of blades of a turbomachine. Due to the selected view from the outside on a housing portion of the turbomachine of the blades only one of the blade radially outwardly leading blade shank 1 is shown.
  • the blade shank 1 is usually also referred to as a radially outer bearing journal.
  • the guide vane has an airfoil which is located in a flow channel of the turbomachine through which the main flow passes. About a radial direction to the inner blade bearing journal, the guide vane is mounted in an inner ring which engages around a rotor shaft radially spaced.
  • the turbomachine is, for example, an aircraft engine and the vane row is arranged in the compressor of the aircraft engine.
  • the vane has the vane shank 1 extending radially outward from the vane blade, which is led out of the flow channel of the turbomachine and out of its housing 4, and which runs along the vertical axis H of the vane.
  • the blade shank 1 By means of a located outside of the main flow path of the turbomachine adjusting lever or lever 6 of the lever connection 2 is the blade shank 1 and thus the guide vane in operative connection with a Leitschaufelsch Herbert coaxial and outside the main flow path of the turbomachine adjusting ring arranged 8.
  • the adjusting ring 8 is in FIG. 6 outlined.
  • the connection of the lever 6 with the adjusting ring 8 via Verstellringite 10.
  • the tension of the lever 6 on the blade shank 1 by means of a screw 12, for example, a self-locking nut.
  • the lever 6 has a connecting portion 14 for connection to a in the FIGS. 4 and 5 shown contact area 16 of the blade shank 1 and a connecting portion 18 for connection to the Verstellringit 12.
  • the connecting portion 18 for connection to the Verstellringit 12 is called for clarity in the following connection section.
  • the connecting portion 14 and the connecting portion 18 form the two ends of the lever 6 and are connected to each other via a strip-like lever portion 20.
  • the axis of rotation of the connecting portion 14 about the vertical axis H and the axis of rotation of the connecting portion 18 about a longitudinal axis of the Verstellringainss 10 are parallel and preferably extend in the radial direction.
  • a possible radial offset of the connecting portion 14 and the connecting portion 18 can be compensated by the strip-like lever portion 20 by the lever portion 20 is arranged at each of the connecting portion 14 and the connecting portion 18 angled, as shown in FIG. 2 is shown. This angle can be 90 °. Preferably, however, a longitudinal extent of the lever portion 20 deviates from the substantially perpendicular Lot between the two axes of rotation. This facilitates the assembly of the lever. 6
  • the connecting portion 14 is formed thickened relative to the strip-like lever portion 20 and has a in the longitudinal direction L of the lever 6 extending rectangular shape. It has a keyhole-like recess 22, which in its thickness direction (in FIG. 2 perpendicular to the plane) penetrated from its top to the bottom.
  • the recess 22 is formed by a slot 24 that extends in the lever longitudinal direction L and two opposite key surfaces 26, 28 has.
  • the wrench flats 26, 28 are here designed as plane parallel surfaces, which are spaced apart from each other by a constant distance and extend in the direction of the lever longitudinal axis L. About a concave surface 30, they are connected near the strip-like lever portion 20 with each other.
  • the recess 22 is formed by a threading opening 32.
  • the Einfädelötician 32 is from the perspective of the strip-like lever portion 20 behind the slot 24 and is open to the circumference. In other words, the threading opening 32 merges with the end remote from the concave surface 30 of the elongated hole 24 in this.
  • the threading opening 32 is formed as a through hole with a circular cross section. Compared with the slot 24, the threading opening 32 in the width direction B of the lever 6 is enlarged cross-section. It has a cross section such that the blade shank 1 with his in the FIGS. 4 and 5 shown radially outer free end 34 can be passed or the lever 6 can be pushed onto the free end 34 of the blade shank 1.
  • the connecting portion 18 is thickened relative to the strip-like lever portion 20, but not as strong as the connecting portion 14. He has a through hole 36 for performing the Verstellringites 10 and the radial sliding of the lever 6 on the Verstellringit 10th
  • the strip-like lever portion 20 is designed here with a constant thickness and width. To compensate for radial heights with respect to the shaft-lever connection point and the adjusting ring pin-lever connection point, a height compensation between the connecting section 14 and the connection section 16 can take place via the strip-like lever section 20 by a corresponding deformation
  • the shovel-side contact region 16 for engagement of the lever-side connecting portion 14 has two contact surfaces 38, 40 facing away from each other.
  • the contact surfaces 38, 40 are formed corresponding to the wrench surfaces 26, 28 of the oblong hole 24 and thus planar parallel surfaces. They are flattened peripheral portions of the blade shank 1 and connected to each other via unchanged convex peripheral surfaces 42 of the blade shank 1. Due to the perspective only a peripheral surface 42 can be seen.
  • the contact surfaces 38, 40 local cross-sectional tapers of the blade shank 8, which are spaced apart from each other such that in the assembled state a play-free or almost play-free positive connection with the key surfaces 26, 28 takes place.
  • the contact region 16 is not rotationally symmetrical to the vertical axis H, which fundamentally permits a secure fastening of the lever 6 by positive locking.
  • shoulder surfaces 46, 48 are formed in the transition region of the contact surfaces 38, 40 to the radially inwardly adjacent original shaft portion 44.
  • the shoulder surfaces 46, 48 form supports for the connecting portion 14 in the clamped state and limit a radial position of the lever 6 on the blade shank 1. They allow in the first place the tension with the screw 12th
  • the free end 34 of the blade shank 1 is provided for cooperation with the screw 12 with an external thread, not shown, and thus designed as a threaded portion.
  • the external thread or the free end 34 is spaced from the contact region 16 via an annular groove 50.
  • FIG. 6 the locking and tensioning of the lever 6 on the blade shank 1 in the contact region 16 is shown in section. It can be clearly seen how the blade shank 1 is not arranged in the threading opening 32 but in the oblong hole 24 and penetrates it in particular.
  • the concave surface 30 of the slot 24 acts as an axial stop for the blade shank 1.
  • a system is not absolutely necessary. Rather, the slot 24 allows the compensation of manufacturing and assembly tolerances, so that the blade shank 1 can also be basically spaced in its mounted position from the concave surface 30, as long as it is in the slot 24.
  • the tension of the lever 6 can be seen by means of the screw 12.
  • the connecting portion 14 is clamped between the shoulder surfaces 46, 48 and the screw 12 and thereby radially spaced from the housing 4 of the turbomachine.
  • a washer 52 may be placed on the blade shank 1.
  • the blade shank 1 is guided by a bearing bush 54, which is inserted into the housing 4.
  • the shunting shank-side connection is located radially inward to the adjustment ring-side connection.
  • the shaft-lever connection point is also arranged behind the Verstellringit-lever connection point viewed in the flow direction here. However, viewed in the flow direction, the shaft / lever connection point can also be arranged in front of the adjusting ring pin / lever connection point. Among other things, the axial position of the connection points determines a free mounting space outside the housing 4.
  • the lever 6 is thus moved radially after assembly of the Verstellringlochs 10 until it is with its connecting portion 14 in contact with the contact region 16 of the blade shank 1. The movement in the second mounting direction but only when all the levers 6 are placed on the respective blade shank 1 and threaded into the adjusting ring 8
  • indications such as "radial” refer to the machine longitudinal axis X of the turbomachine according to the invention, which represents the axis of rotation of a rotor of the turbomachine.
  • an adjusting ring pin 10 is attached to the respective lever 6.
  • the adjusting ring pin 10 is guided to the annular shoulder 56 through the through hole 36 of the connection portion 18 and then connected thereto.
  • the lever 6 is clamped by means of the screw 12 against the shoulder surfaces 46, 48 of the blade shank 1.
  • the screw 12 is screwed onto the external thread of the free end 34. Due to the radial support on the shoulder surfaces 46, 48 of the blade shank 1, the connecting section 14 can not escape radially inward. As a result, the connecting portion 14 is pressed against the shoulder surfaces 46, 48.
  • the washer 52 may be formed as a lock washer with, for example, lateral arms which are laterally applied to the screw member 12 and / or inserted into the threading opening 32.
  • the invention also includes embodiments in which the Verstellringite 10 are not pre-assembled with the levers 6.
  • the adjusting ring pins 10 can be previously mounted on the adjusting ring 8 and then the lever 6 are pushed onto the respective adjustment ring pin 10 mounted on the adjusting ring 8.
  • a lever connection of a vane adjustment for connecting a guide vane of a turbomachine with an adjusting ring of an actuator, which is set up such that an adjusting lever of the lever connection is pushed from a first mounting direction relative to a machine longitudinal axis of the turbomachine radially on a blade shank of the vane and by means of a movement is locked in a second mounting direction with the blade shank positively and in particular rotationally fixed, an assembly process and a turbomachine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19156350.1A 2018-02-12 2019-02-11 Connexion à levier d'un positionnement d'aube directrice pour turbomachines et procédé de fabrication associé Active EP3524778B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018202119.8A DE102018202119A1 (de) 2018-02-12 2018-02-12 Hebelanbindung einer Leitschaufelverstellung für Strömungsmaschinen

Publications (2)

Publication Number Publication Date
EP3524778A1 true EP3524778A1 (fr) 2019-08-14
EP3524778B1 EP3524778B1 (fr) 2020-09-09

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US (1) US10876425B2 (fr)
EP (1) EP3524778B1 (fr)
DE (1) DE102018202119A1 (fr)

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WO2023020655A1 (fr) * 2021-08-18 2023-02-23 MTU Aero Engines AG Aube directrice réglable pour une turbine à gaz, turbine à gaz et procédé d'assemblage d'une aube directrice réglable pour une turbine à gaz
FR3139857A1 (fr) * 2022-09-16 2024-03-22 Safran Aircraft Engines Ensemble d’un dispositif d'aubes à calage variable

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DE102022114072A1 (de) 2022-06-03 2023-12-14 MTU Aero Engines AG Leitschaufelvorrichtung, Montagewerkzeug, sowie Strömungsmaschine und Verfahren zum Verbinden und Lösen der Leitschaufelvorrichtung
DE102023121106A1 (de) 2023-08-08 2025-02-13 MTU Aero Engines AG Leitschaufelanordnung einer Strömungsmaschine und Verfahren zur Montage einer Leitschaufelanordnung

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EP3524778B1 (fr) 2020-09-09
US10876425B2 (en) 2020-12-29

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