EP3524781A1 - Dispositif de raccordement pour une aube réglable d'une turbine à gaz - Google Patents

Dispositif de raccordement pour une aube réglable d'une turbine à gaz Download PDF

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Publication number
EP3524781A1
EP3524781A1 EP19156113.3A EP19156113A EP3524781A1 EP 3524781 A1 EP3524781 A1 EP 3524781A1 EP 19156113 A EP19156113 A EP 19156113A EP 3524781 A1 EP3524781 A1 EP 3524781A1
Authority
EP
European Patent Office
Prior art keywords
connecting device
lever
pin
receptacle
clamping
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
EP19156113.3A
Other languages
German (de)
English (en)
Other versions
EP3524781B1 (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 EP3524781A1 publication Critical patent/EP3524781A1/fr
Application granted granted Critical
Publication of EP3524781B1 publication Critical patent/EP3524781B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection

Definitions

  • the present invention relates to a connecting device for an adjustable blade of a gas turbine, in particular an aircraft gas turbine, comprising a pin member connected to a respective blade and a lever member connected to the pin member, wherein the lever member and the pin member are movable together about a pin rotation axis.
  • a threaded portion is formed on the pin member, in particular at its axial end which is remote from the blade, or otherwise made a change in shape, such as bevels and the like to connect the pin portion with the lever member can. Examples of this are from the EP 2 177 771 A2 or the WO 2015/031058 A1 known.
  • the object underlying the invention is seen to provide a connecting device in which the above disadvantages can be avoided.
  • the connecting device has a clamping element which is arranged between the lever element and the pin element is, so that a frictional connection between the pin member, the clamping element and the lever member can be produced or manufactured.
  • This allows a particularly space-saving design of the connected to the connecting device blade assembly, as further fastening means can be used, but at the same time the blade and the blade pin can be made smaller.
  • the tensioning element a safe power transmission between the lever element and the pin element, so that the existing Verstelltimien can be transferred to smaller compressors or turbines with Verstellleitschaufeln.
  • the clamping element has a plurality of recesses along its circumference, such that a respective elastically movable clamping section is formed between adjacent recesses.
  • the clamping element may be stretched in the assembled state due to the frictional connection and / or have a bias.
  • At least two diametrically opposed recesses in the clamping element can be dimensioned such that they form a clamping receptacle in which the positioning element is received. Accordingly, the positioning element is arranged in an assembled state of the connecting device so that it is arranged in the clamping receptacle, the pin receptacle and the lever receptacle.
  • the clamping receptacle, the pin receptacle and the lever receptacle can be aligned in a simple manner to each other by the positioning without a readjustment during assembly is necessary.
  • the clamping portions may be formed such that they have a conical outer contact surface.
  • the radially inner contact surface of the coupling portion of the lever member and the radially outer contact surfaces of the clamping portions abut each other and be mutually braced.
  • connection device in the connection device, the lever element and the pin member are aligned by means of a positioning element to each other, wherein the positioning element is received in a pin receiving and a lever receptacle.
  • the pin receptacle thus serves as a receptacle of the positioning element in the pin element, while the lever receptacle serves as a receptacle of the positioning element in the lever element.
  • the positioning element may be formed, for example, as a plate-like key.
  • the positioning element is used in particular to allow alignment of the lever element and the pin element in the circumferential direction with respect to the pin rotation axis. In this case, this alignment takes place by means of the positioning element before the connection device is tightened.
  • By using a separate positioning element weakening or changing the cross section of the pin element can be avoided in particular in areas in which forces, in particular rotational forces are transmitted from the lever element to the pin member in the assembled state of the connecting device.
  • the pin receptacle and the lever receptacle are arranged in alignment with one another. This allows a particularly simple and cost-effective production of the positioning and the corresponding recordings and thus facilitates the assembly.
  • the positioning element is formed symmetrically to a plane passing through the pin rotation axis. This also facilitates the production and makes it possible to disregard an installation direction of the positioning during assembly.
  • the pin receptacle may preferably be formed in an axial end portion of the pin member.
  • the positioning element can advantageously be connected first to the pin element during assembly, which facilitates subsequent placement of the lever element, in particular its coupling section, on or on the pin element.
  • the pin receptacle is designed as a slot.
  • the slot may have an axial depth which is slightly larger than the axial extent or height of the positioning element, which passes through the pin receptacle.
  • the clamping element may have a threaded portion to which a nut is fastened or fastened.
  • the threaded portion is located at an axial portion of the clamping element, which faces away from the pin member.
  • the lever element may have a sleeve-like coupling portion, wherein the coupling portion and the pin member are arranged concentrically with each other.
  • the coupling portion may be formed in particular circular. Externally, the coupling portion has a substantially cylindrical shape.
  • the lever receptacle can be formed in an axial edge section of the coupling section.
  • the lever receptacle may be formed by two diametrically opposite lever receiving portions.
  • the lever receiving portions may be provided as radially extending slots in the edge portion.
  • the positioning member is in an assembled state of the connecting means in the lever receiving portions.
  • the lever holder can simply slide over the positioning, so that always an exact alignment of the lever or an additional clamping element described in more detail below is made possible.
  • the coupling portion may have a radially inner contact surface, which is conical.
  • the radially inner contact surface faces the pin element.
  • the contact surface surrounds the pin member, wherein between the contact surface and the pin member a distance is present.
  • the connecting device may comprise a securing sleeve, which is arranged in the axial direction on the coupling portion.
  • the securing sleeve may have a peripheral edge which extends in the axial direction slightly above the coupling portion of the lever member. This can ensure that the positioning element in the assembled state of the connecting device can not be removed from this.
  • the locking sleeve may be disposed between the nut and the coupling portion such that a force exerted by the nut is transmitted in the axial direction to the locking sleeve and the coupling portion. Due to the interaction of its radially inner contact surface with the contact surfaces of the clamping sections, an axial force acting on the coupling section of the lever element substantially presses the clamping sections radially into the pin element, so that the pin element is frictionally held by the clamping sections.
  • the positioning element can be received without force transmission in the assembled state of the connecting device.
  • a frictional connection between the lever element and the pin element can be produced, wherein the positioning element during assembly for correct alignment of the lever element and the pin member to each other.
  • the positioning element In one of the lever element to be transmitted to the pin element rotational movement about the pin rotation axis, the positioning element is rotated, but it does not transmit any forces from the lever element on the pin member.
  • the blades mentioned here can be, in particular, adjustable blades of a compressor of the gas turbine.
  • the invention also relates to a gas turbine, in particular an aircraft gas turbine, with a plurality of adjacently arranged in the turbine circumferential direction adjustable blades, in particular vanes, wherein on each blade a connecting device is arranged according to one of the preceding claims, and wherein the lever elements of the connecting means with a along the circumferential direction of the gas turbine are coupled movable adjusting ring.
  • the adjacently arranged in the turbine circumferential direction adjustable blades can be assigned to a compressor stage.
  • Such an adjustable blade ring can also be provided several times on a gas turbine, so that a ring with adjustable blades can be provided for any type of compressor, such as low pressure, medium pressure or high pressure compressor on any compressor stages.
  • Fig. 1 shows schematically and simplified an aircraft gas turbine 10, which is illustrated purely by way of example as a turbofan engine.
  • the gas turbine 10 comprises a fan 12, which is surrounded by an indicated jacket 14.
  • the compressor 12 is adjoined by a compressor 16, which is accommodated in an indicated inner housing 18 and may be of single-stage or multi-stage design.
  • the combustion chamber 20 connects. Hot exhaust gas flowing out of the combustion chamber then flows through the adjoining turbine 22, which may be designed in one or more stages.
  • the turbine 22 includes a high-pressure turbine 24 and a low-pressure turbine 26.
  • a hollow shaft 28 connects the high-pressure turbine 24 with the compressor 16, in particular a high-pressure compressor 29 so that they are driven together or rotated.
  • a further internal shaft 30 in the radial direction TRR of the turbine connects the low-pressure turbine 26 with the fan 12 and with a low-pressure compressor 32, so that they are driven together or rotated.
  • the turbine 22 is followed by a thrust nozzle 33, which is only indicated here.
  • a turbine intermediate housing 34 is arranged between the high-pressure turbine 24 and the low-pressure turbine 26, which is arranged around the shafts 28, 30. In its radially outer region 36, the turbine intermediate housing 34 is flowed through by hot exhaust gases from the high-pressure turbine 24. The hot exhaust gas then passes into an annular space 38 of the low-pressure turbine 26.
  • example blade rings 27 are shown.
  • Guide vane rings 31 are shown by way of example only for the compressor 32 for reasons of clarity.
  • adjustable guide vanes which may for example be part of an overall adjustable vane ring 31.
  • adjustable guide vane rings 31 may also be provided in other compressors or possibly also in turbines, even if this in the Fig. 1 only exemplified for the compressor 32 is shown.
  • Fig. 2 shows a schematic perspective view of a connecting device 50 for an adjustable guide vane of a gas turbine.
  • the guide vane 51 which is indicated here only partially and in broken lines, adjoins in the axial direction AR of the connecting device 50 a pin element 52, which in the Fig. 2 only partially shown.
  • the pin member 52 and the associated blade 51, in particular guide vane are integrally connected to one another.
  • the connecting device 50 comprises a lever element 54.
  • the lever element 54 is in Fig. 2 (and in Fig. 1 ) is shown only partially, with the lever member 54 being illustrated cut off at 56.
  • the lever element 54 is configured to rotate the pin element 52 about the pin rotation axis ZD parallel to the axial direction AR in an assembled state of the connection device 50.
  • the pin member 52 has a pin receptacle 60 at its end remote from the blade 51 axial end 58.
  • the pin receptacle is designed in particular as a slot.
  • the lever element 54 has a sleeve-like coupling portion 62.
  • the coupling portion 62 and the pin member 52 are in particular arranged concentrically with each other.
  • a lever receptacle 66 is formed in an axial edge portion 64 of the coupling portion 62.
  • the lever receptacle 66 is formed in particular by two diametrically opposite lever receiving portions 66a, 66b.
  • a positioning element 68 is received in the lever receptacle 66 and the pin receptacle 60.
  • the positioning member 68 serves to align the pin member 52 and the lever member 54 with respect to the circumferential direction UR of the connecting device 50 to each other.
  • the positioning element 68 is designed in particular as a plate-like or flat-rod-like component.
  • the positioning element 68 may also be referred to as a feather key.
  • the connecting device 50 further comprises a clamping element 70, which in Fig. 3 alone and in Fig. 1 is shown together with other components of the connecting device 50.
  • the clamping element 70 has at its the blade 51 facing the axial end 72 a plurality of clamping portions 74a, 74b, 74c.
  • the clamping element 70 has four clamping sections, of which, however, in the Fig. 1 and 3 only the three clamping sections 74a, 74b, 74c are visible. It should be noted that the clamping element 70 could also have a different number of clamping sections, for example six or eight.
  • a respective recess 76a and 76b is provided between two adjacent clamping portions 74a, 74b and 74a, 74c.
  • the tensioning sections 74a, 74b, 74c are elastically movable or deflectable, in particular in the radial direction, in particular toward or away from the pin element 52.
  • the recess 76b and a diametrically opposite another recess, which in the selected representation of Fig. 3 is not visible, are dimensioned such that they form a clamping receptacle 78, in which the positioning element 68 can be received during assembly of the connecting device 50 and is received in the assembled state of the connecting device 50.
  • the clamping portions 74a, 74b, 74c have a respective outer contact surface 80.
  • the contact surfaces 80 are conical along the axial direction AR.
  • the clamping element 70 has a varying diameter in the region of its clamping sections 74a, 74b, 74c.
  • the outer contact surfaces 80 are in an assembled state of the connecting device 50 in contact with a radially inner contact surface 82 of the lever member 54.
  • the radially inner contact surface 82 is arranged in particular in the region of the coupling portion 62.
  • the radially inner contact surface 82 may be conical. Accordingly, the sleeve-like coupling portion 62 in the region of the inner contact surface 82 has a varying inner diameter.
  • the radially outer contact surface 80 of the clamping portions 74a, 74b, 74c and the radially inner contact surface 82 of the coupling portion 62 are formed complementary to each other.
  • the clamping element 70 has an axially adjoining the clamping portions 74a, 74b, 74c threaded portion 84.
  • the threaded portion 84 has a in the FIGS. 1 and 3 not shown external thread on. With the threaded portion 84, a nut 86 is connectable or connected, as in Fig. 1 is shown.
  • a securing sleeve 88 is arranged in the axial direction between the nut 86 and the lever element 54, in particular the clamping portion 62. A force exerted by the nut 86 in the axial direction AR is transmitted to the locking sleeve 88 and the coupling portion 62.
  • the in Fig. 2 shown assembled state of the connecting device 50 is in Fig. 5 in a sectional view approximately corresponding to the section line VV of Fig. 1 shown.
  • the connection device 50 in an outer region of structural components 90 of a gas turbine 10 (FIG. Fig. 1 ), in particular aircraft gas turbine, attached.
  • the structural members 90 may be part of an inner housing 18 as shown in FIG Fig. 1 is illustrated.
  • the Fig. 5 are the same reference numerals used as in the FIGS. 2 to 4 to designate the same elements, although not necessarily with reference to the Fig. 5 be described again. In that regard, the previous description of the Fig. 2 to 4 also in conjunction with the Fig. 5 can be read and understood.
  • Fig. 5 the lever element 54 is shown completely (not cut off).
  • the lever element 54 has a further coupling section 92 at its end remote from the connecting device 50.
  • the coupling portion 92 is connected to an adjusting device 94.
  • the adjusting device 94 comprises an adjusting ring 96 and a plurality of adjusting pins 98.
  • the adjusting pins 98 and the adjusting ring 96 are movable back and forth along a turbine circumference. This translational adjustment movement along the circumferential direction the turbine causes a pivoting of the lever element 54 about the axis of rotation ZD of the pin member 52.
  • a connected to the pin member 52 blade 51 (FIG. Fig. 2 ) are rotated to a desired position.
  • the clamping element 70 of the connecting device 50 rests on a guide sleeve 100.
  • the guide sleeve forms in this example, a radial bearing for the pin member 52.
  • the axial direction AR of the connecting device corresponds with respect to the gas turbine a radial direction TRR of the gas turbine.
  • Fig. 6 shows an enlarged area approximately corresponding to the dashed area VI of Fig. 5 , The Fig. 6 serves in particular to describe the size ratios of the positioning element 68 to other elements.
  • the positioning element 68 has a length VL extending in the radial direction RR.
  • the length VL of the positioning member 68 is set to be slightly smaller than the diameter DK of the substantially circular coupling portion 62 and the outer diameter of the axial edge portion 64, which is annular.
  • the positioning element 68 has a width VB which is smaller than the axial extent or depth ZT of the pin receptacle 60. Furthermore, the width VB of the positioning element 68 is also selected so that it is smaller than the axial extent or depth HT of the lever receptacle 66 or the individual lever receiving portions 66a, 66b.
  • the securing sleeve 88 has an edge portion 102 which has an axial length which is greater than the width of the positioning element 68.
  • the edge portion 102 bears with its axially lower end against an outer circumference of the coupling portion 62. This ensures that the positioning member 68 is not removable in the radial direction of the connecting device 50.
  • the positioning element 68 is received in the assembled state of the connecting device 50 substantially force-transfer free.
  • the positioning element 68 does not transmit rotational movements introduced by the lever element 54 onto the pin element 52.
  • the forces acting in the axial direction AR from the utter 86 are transmitted via the securing sleeve 88, the lever member 54 and its coupling portion 62 on the clamping element 70 and its clamping portions 74a to 74d, so that the clamping portions 74a to 74d are pressed against the pin member 52.
  • the positioning member 68 is dimensioned so that when assembling the connecting device 50, a correct positioning of pin member 52, lever member 54 and clamping element 70 allows each other, in particular in the circumferential direction UR of the connecting device 50, but that it is not included in the power transmission when assembled State of the connecting device 50 is a frictional connection between the lever member 54 and the pin portion 52 is made.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP19156113.3A 2018-02-09 2019-02-08 Dispositif de raccordement pour une aube réglable d'une turbine à gaz Active EP3524781B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018202082.5A DE102018202082A1 (de) 2018-02-09 2018-02-09 Verbindungseinrichtung für eine verstellbare Schaufel einer Gasturbine

Publications (2)

Publication Number Publication Date
EP3524781A1 true EP3524781A1 (fr) 2019-08-14
EP3524781B1 EP3524781B1 (fr) 2020-09-09

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19156113.3A Active EP3524781B1 (fr) 2018-02-09 2019-02-08 Dispositif de raccordement pour une aube réglable d'une turbine à gaz

Country Status (3)

Country Link
US (1) US11125115B2 (fr)
EP (1) EP3524781B1 (fr)
DE (1) DE102018202082A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4130441A1 (fr) 2021-08-05 2023-02-08 MTU Aero Engines AG Dispositif de liaison d'une aube à calage variable d'une turbine à gaz et turbine à gaz

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Publication number Priority date Publication date Assignee Title
DE102018202494A1 (de) * 2018-02-19 2019-08-22 MTU Aero Engines AG Lagerkammergehäuse für eine strömungsmaschine
US12000292B1 (en) 2022-12-30 2024-06-04 Rolls-Royce North American Technologies Inc. Systems and methods for multi-dimensional variable vane stage rigging
US12000293B1 (en) 2022-12-30 2024-06-04 Rolls-Royce North American Technologies Inc. Systems and methods for multi-dimensional variable vane stage rigging utilizing coupling mechanisms
US11982193B1 (en) 2022-12-30 2024-05-14 Rolls-Royce North American Technologies Inc. Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable inclined mechanisms
US11834966B1 (en) 2022-12-30 2023-12-05 Rolls-Royce North American Technologies Inc. Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable alignment mechanisms

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Publication number Priority date Publication date Assignee Title
US20040240990A1 (en) * 2003-05-27 2004-12-02 Rockley Christopher I. Variable vane arrangement for a turbomachine
US20080031729A1 (en) * 2006-08-02 2008-02-07 Snecma Cylindrical-rod device for controlling a variable-pitch vane of a turbomachine
DE60319612T2 (de) * 2002-01-29 2009-04-02 Snecma Steuereinrichtung für Statorschaufel

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US5104287A (en) 1989-09-08 1992-04-14 General Electric Company Blade tip clearance control apparatus for a gas turbine engine
US6146093A (en) * 1998-12-16 2000-11-14 General Electric Company Variable vane seal and washer
DE10352099B4 (de) * 2003-11-08 2017-08-24 MTU Aero Engines AG Vorrichtung zum Verstellen von Leitschaufeln
US8215902B2 (en) * 2008-10-15 2012-07-10 United Technologies Corporation Scalable high pressure compressor variable vane actuation arm
US10385719B2 (en) 2013-08-28 2019-08-20 United Technologies Corporation Variable vane bushing
EP2960438B1 (fr) 2014-06-26 2020-09-02 MTU Aero Engines GmbH Système d'aubes de guidage variables pour une turbine à gaz et turbine à gaz dotée d'un tel système

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Publication number Priority date Publication date Assignee Title
DE60319612T2 (de) * 2002-01-29 2009-04-02 Snecma Steuereinrichtung für Statorschaufel
US20040240990A1 (en) * 2003-05-27 2004-12-02 Rockley Christopher I. Variable vane arrangement for a turbomachine
US20080031729A1 (en) * 2006-08-02 2008-02-07 Snecma Cylindrical-rod device for controlling a variable-pitch vane of a turbomachine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4130441A1 (fr) 2021-08-05 2023-02-08 MTU Aero Engines AG Dispositif de liaison d'une aube à calage variable d'une turbine à gaz et turbine à gaz

Also Published As

Publication number Publication date
US11125115B2 (en) 2021-09-21
DE102018202082A1 (de) 2019-08-14
US20190249572A1 (en) 2019-08-15
EP3524781B1 (fr) 2020-09-09

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