EP1637742A2 - Stellhebel an der Schwenkachse einer verstellbaren Leitschaufel in einer Strömungsmaschine. - Google Patents

Stellhebel an der Schwenkachse einer verstellbaren Leitschaufel in einer Strömungsmaschine. Download PDF

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Publication number
EP1637742A2
EP1637742A2 EP05291889A EP05291889A EP1637742A2 EP 1637742 A2 EP1637742 A2 EP 1637742A2 EP 05291889 A EP05291889 A EP 05291889A EP 05291889 A EP05291889 A EP 05291889A EP 1637742 A2 EP1637742 A2 EP 1637742A2
Authority
EP
European Patent Office
Prior art keywords
lever
intermediate portion
control lever
thickness
turbomachine
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
EP05291889A
Other languages
English (en)
French (fr)
Other versions
EP1637742B1 (de
EP1637742A3 (de
Inventor
Sébastien Bourgoin
Christophe Follonier
Claude Lejars
Christophe Tourne
Bruce Pontoizeau
Nicolas Triconnet
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1637742A2 publication Critical patent/EP1637742A2/de
Publication of EP1637742A3 publication Critical patent/EP1637742A3/de
Application granted granted Critical
Publication of EP1637742B1 publication Critical patent/EP1637742B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium

Definitions

  • the present invention relates to a lever for controlling the angular setting of a stator blade in a turbomachine and a turbomachine compressor comprising a plurality of stator vanes with variable pitch angle equipped with these control levers.
  • Adjusting the angular setting of the stator vanes in a turbomachine such as a turbojet engine is intended to optimize the efficiency of this turbomachine and to reduce its fuel consumption in the various flight configurations.
  • This adjustment is effected by means of a lever which comprises a first end fixedly mounted on a pivot of the blade to drive it in rotation about its longitudinal axis, a second end comprising a cylindrical pin for mounting on a control ring which externally surrounds the stator of the turbomachine and which is rotatable about the longitudinal axis of the stator by a motor means such as a cylinder or an electric motor, and a flat intermediate portion connecting the first and second ends of the lever.
  • a lever which comprises a first end fixedly mounted on a pivot of the blade to drive it in rotation about its longitudinal axis, a second end comprising a cylindrical pin for mounting on a control ring which externally surrounds the stator of the turbomachine and which is rotatable about the longitudinal axis of the stator by a motor means such as a cylinder or an electric motor, and a flat intermediate portion connecting the first and second ends of the lever.
  • the control lever which is rotated by the control ring and which is fixed on the pivot of the blade, is subjected to bending and torsion forces which are exerted mainly at its intermediate portion and its second end.
  • these control levers are subjected to vibrations due in particular to the passages of the rotor blades in front of the stator vanes, the frequencies of these vibrations varying with the speed of rotation of the rotor.
  • the present invention aims to prevent the occurrence of cracks or cracks in a lever of the aforementioned type, without significantly modifying the stiffness of the lever.
  • a lever for controlling the angular setting of a stator blade in particular in a turbomachine compressor, comprising a first end intended to be fixedly mounted on a blade pivot, a second end comprising a cylindrical pin. on a drive means, and a flat intermediate portion connecting the first and second ends, said first end having a thickness and a width greater than those of the intermediate portion and the second end of the lever, characterized in that the shapes and dimensions of the intermediate portion and the second end are determined to increase the natural frequencies of the lever in bending and torsion above the vibratory frequencies of the turbomachine upstream of the lever and to maintain the stiffness of the lever.
  • the second end of the control lever has a thickness greater than that of the intermediate portion, and the intermediate portion locally has a width less than that of the second end of the lever.
  • Increasing the thickness of the second end of the control lever makes it possible to better withstand the stresses during crimping of the cylindrical pin, and to limit the appearance and propagation of cracks or cracks. It causes an increase in the overall stiffness of the lever, which is compensated by a local decrease in the width of the intermediate portion so that the control lever retains the same stiffness and requires the same operating power as before.
  • the intermediate portion of the lever is of constant thickness and is connected to the ends of the lever by areas of progressively increasing thickness.
  • the intermediate portion of the lever has curved longitudinal edges of concave shape which allow progressive transitions between portions of different widths by avoiding stress concentrations in parts of the lever whose width varies abruptly and discontinuously.
  • control lever shape and dimensions of the control lever are dynamically optimized to increase the eigenfrequencies of the lever in bending and torsion beyond the vibratory frequencies of the turbomachine upstream, and statically by reducing the local concentrations of stresses.
  • control lever according to the invention is advantageously subjected at least partially to shot blasting, this treatment making it possible to harden the surface of the lever and thus to protect it against shocks or possible blows during its handling and its mounting on the blade pivot and on the control ring, these shocks and blows can be the cause of cracks or microcracks.
  • the invention also proposes a turbomachine compressor, for example a turbojet engine comprising a plurality of variable-pitch vanes equipped with control levers of the aforementioned type.
  • FIG. 1 shows a portion of a high-pressure compressor 10 of a turbomachine, in which each stage of the compressor comprises a row of guide vanes 12 mounted on the stator and a row of vanes 14 carried by the rotor.
  • the blades 12 of the stator are rectifiers whose orientation or angular setting is adjustable using control levers 16 driven by a control ring 18 actuated by motor means (not shown) of the type jack or electric motor.
  • Each control lever 16 comprises a first end 20 fixed on a radial pin 22 of a blade 12, guided in rotation in a bearing 24 mounted in a radial chimney of an outer casing 26, a second end 28 and a flat intermediate portion Connecting the ends 20 and 28.
  • the second end 28 of the control lever 16 carries a cylindrical pin 32 which is crimped on this end 28 and is guided in rotation in a cylindrical sleeve 34 of the control ring 18.
  • the first end 20 of the lever 16 has a thickness and a width greater than those of the intermediate portion 34 and the second end 28 of the lever 16.
  • the thickness of the first end 20 is about 10 mm and its width is about 22 mm.
  • the second end 28 of the lever 16 which carries the cylindrical mounting pin 32 on the control ring 18 has a circular edge extending about 180 ° around the crimped head of the cylindrical pin 32.
  • the thickness of the second end is about 1.1 mm and its width is about 10 mm.
  • the intermediate portion 34 which connects the first and second ends 20 and 28 has the same thickness as the second end 28 and a triangular shape and is connected to the first end 20 by a connecting zone 38 of gradually increasing thickness.
  • the thickness of the intermediate portion 34 is about 1.1 mm and its width varies between about 10 and 22 mm.
  • the eigenfrequencies of the levers 16 in flexion and torsion may coincide with the vibratory frequencies of the upstream part of the compressor and then cause significant vibrations of the levers 16 resulting in the formation of cracks or cracks , in particular at the crimping zones of the cylindrical pins 32 on the second ends 28 of the levers 16.
  • This vibratory frequency depends on the speed of rotation of the rotor and is about 6500 Hz for a particular example of a high-pressure compressor considered.
  • the shapes and dimensions of the intermediate portion 34 and the second end 28 are modified so that the frequencies of the lever 16 in flexion and in torsion are greater than the vibratory frequencies of the upstream part of the compressor, without appreciably increasing the stiffness of the lever.
  • Figure 3 shows schematically and in perspective an embodiment of a control lever 40 according to the invention.
  • the second end 42 of the lever 40 has a thickness greater than that of the second end 28 of the lever 16 of the prior art to better withstand the stresses due to the crimping of the cylindrical pin 32 and delay the propagation of cracks or fissures. For example, this thickness is about 1.8 mm.
  • the shape of the second end 42 has also been modified by increasing the angular extent of its rounded edge which extends over more than 180 °.
  • This rounded edge may have one or more radii of curvature varying for example between 6 and 15 mm.
  • the intermediate portion 44 of the lever 40 is of constant thickness, greater than that of the intermediate portion 34 of the lever 16 of the prior art but lower than that of the second end 42 of the lever 40.
  • the thickness of the part intermediate 44 of the lever 40 is about 1.4 mm.
  • the increase in stiffness of the lever 40 due to the increase in the thickness of the intermediate portion 44 and the second end 42 is compensated by a decrease in the width of at least a portion 46 of the intermediate portion 44 of the lever 40, which allows to maintain the same overall stiffness as in the prior art, this portion 46 being connected to the second end 42 of the lever.
  • the portion 46 has a width of about 8 mm, less than that of the second end 42 and is delimited by substantially parallel longitudinal edges.
  • the intermediate portion 44 of the lever 40 is connected to the first end 48 by a connecting zone 50 of short length and gradually increasing thickness which is substantially identical to the connecting zone 38 of the lever 16 of the prior art and whose thickness varies between that of the intermediate portion 44 of the lever 40 and that of its first end 48.
  • Another zone 52 of progressively increasing thickness connects the portion 46 of the intermediate portion 44 to the second end 42 of the lever 40.
  • edges 54, 56 of the connecting zones 50 and 52 and the intermediate portion 44 are curved and concave and connected to the straight edges of the portion 46 mentioned above.
  • the edges 54 may have one or more radii of curvature which are typically between 6 and 15 mm for example, and the edges 56 may also have one or more radii of curvature which are typically between 15 and 30 mm for example.
  • the radii of curvature of the edges 54, 56 thus increase from the second end 42 of the lever 40 towards the first end 48.
  • the control lever 40 according to the invention is preferably treated at least partially by shot-blasting, for example on the intermediate portion 44 and / or on the second end 42 of the lever 40.
  • This treatment makes it possible to harden the surface of the lever and therefore of improve its protection against shocks or blows that may occur during the mounting of the control lever 40 and may cause crack initiation or cracking.
  • control lever 40 according to the invention is advantageously made of titanium.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP05291889.3A 2004-09-21 2005-09-13 Verstellhebel zur Winkelverstellung einer Leitschaufel in einer Strömungsmaschine. Active EP1637742B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0409945A FR2875559B1 (fr) 2004-09-21 2004-09-21 Levier de commande du calage angulaire d'une aube de stator dans une turbomachine

Publications (3)

Publication Number Publication Date
EP1637742A2 true EP1637742A2 (de) 2006-03-22
EP1637742A3 EP1637742A3 (de) 2014-03-12
EP1637742B1 EP1637742B1 (de) 2016-11-23

Family

ID=34949015

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05291889.3A Active EP1637742B1 (de) 2004-09-21 2005-09-13 Verstellhebel zur Winkelverstellung einer Leitschaufel in einer Strömungsmaschine.

Country Status (7)

Country Link
US (1) US7524165B2 (de)
EP (1) EP1637742B1 (de)
JP (1) JP4832839B2 (de)
CN (1) CN1789673B (de)
CA (1) CA2520078C (de)
FR (1) FR2875559B1 (de)
RU (1) RU2311541C2 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2481891A2 (de) * 2011-02-01 2012-08-01 United Technologies Corporation Verstellringabstandhalter fur Gasturbine
DE102016224523A1 (de) * 2016-12-08 2018-06-14 MTU Aero Engines AG Leitschaufelverstellung mit seitlich montiertem Verstellhebel
EP3431718A1 (de) * 2017-07-19 2019-01-23 Rolls-Royce plc Verstellringanordnung
DE102017222209A1 (de) * 2017-12-07 2019-06-13 MTU Aero Engines AG Leitschaufelanbindung sowie Strömungsmaschine
FR3097007A1 (fr) * 2019-06-06 2020-12-11 Safran Aircraft Engines Dispositif d’actionnement d’aubes à calage variable de turbomachine, turbomachine munie de celui-ci

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2921100B1 (fr) * 2007-09-13 2009-12-04 Snecma Levier d'entrainement en rotation autour de son pivot d'aube de stator a calage variable de turbomachine
US8215902B2 (en) * 2008-10-15 2012-07-10 United Technologies Corporation Scalable high pressure compressor variable vane actuation arm
US8714916B2 (en) * 2010-09-28 2014-05-06 General Electric Company Variable vane assembly for a turbine compressor
US8668444B2 (en) * 2010-09-28 2014-03-11 General Electric Company Attachment stud for a variable vane assembly of a turbine compressor
KR102106888B1 (ko) 2015-01-13 2020-05-06 한화에어로스페이스 주식회사 가변 베인 구동용 레버암 조립체
DE102015004649A1 (de) * 2015-04-15 2016-10-20 Man Diesel & Turbo Se Leitschaufelverstellvorrichtung und Strömungsmaschine
DE102015004648A1 (de) * 2015-04-15 2016-10-20 Man Diesel & Turbo Se Leitschaufelverstellvorrichtung und Strömungsmaschine
FR3055374B1 (fr) * 2016-08-23 2018-08-03 Safran Aircraft Engines Piece d'interface pour reconditionner un anneau de commande d'un compresseur de moteur, et procede de reconditionnement associe
US10753224B2 (en) * 2017-04-27 2020-08-25 General Electric Company Variable stator vane actuator overload indicating bushing
US10590795B2 (en) * 2017-10-17 2020-03-17 United Technologies Corporation Vane arm with tri-wedge circular pocket
DE102018202119A1 (de) 2018-02-12 2019-08-14 MTU Aero Engines AG Hebelanbindung einer Leitschaufelverstellung für Strömungsmaschinen
DE102018211808A1 (de) * 2018-07-16 2020-01-16 Ziehl-Abegg Se Ventilator und Leiteinrichtung für einen Ventilator
FR3100272A1 (fr) * 2019-08-27 2021-03-05 Safran Aircraft Engines Guignol pour un dispositif de calage variable d’une turbomachine
FR3109959B1 (fr) * 2020-05-06 2022-04-22 Safran Helicopter Engines Compresseur de turbomachine comportant une paroi fixe pourvue d’un traitement de forme
CN114109916B (zh) * 2021-08-19 2024-03-01 鑫磊压缩机股份有限公司 一种便于维修更换的进口导叶调节器

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US4652208A (en) * 1985-06-03 1987-03-24 General Electric Company Actuating lever for variable stator vanes
EP0223194A1 (de) * 1985-11-14 1987-05-27 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Leitschaufel für Turbomaschinen
US4767264A (en) * 1986-10-31 1988-08-30 United Technologies Corporation Vane lever arm construction
US4979874A (en) * 1989-06-19 1990-12-25 United Technologies Corporation Variable van drive mechanism
US5492446A (en) * 1994-12-15 1996-02-20 General Electric Company Self-aligning variable stator vane
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
EP1400658A1 (de) * 2002-09-20 2004-03-24 BorgWarner Inc. Turbolader

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JPH08121108A (ja) * 1994-10-31 1996-05-14 Ishikawajima Harima Heavy Ind Co Ltd 静翼の支持構造
US6422818B2 (en) * 1998-08-07 2002-07-23 General Electric Company Lubricating system for thermal medium delivery parts in a gas turbine
US6146093A (en) * 1998-12-16 2000-11-14 General Electric Company Variable vane seal and washer
US6450766B1 (en) * 1999-08-09 2002-09-17 United Technologies Corporation Stator vane blank and method of forming the vane blank
US6318070B1 (en) * 2000-03-03 2001-11-20 United Technologies Corporation Variable area nozzle for gas turbine engines driven by shape memory alloy actuators
US6402469B1 (en) * 2000-10-20 2002-06-11 General Electric Company Fan decoupling fuse
CN2536821Y (zh) * 2001-12-06 2003-02-19 重庆通用工业(集团)有限责任公司 离心式制冷压缩机的进口可调导叶和可调扩压器联动装置
JP2003214399A (ja) * 2002-01-18 2003-07-30 Ishikawajima Harima Heavy Ind Co Ltd 圧縮機静翼の固有振動数可変機構
US6984104B2 (en) * 2002-12-16 2006-01-10 United Technologies Corporation Variable vane arm/unison ring attachment system
GB0326544D0 (en) * 2003-11-14 2003-12-17 Rolls Royce Plc Variable stator vane arrangement for a compressor

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4652208A (en) * 1985-06-03 1987-03-24 General Electric Company Actuating lever for variable stator vanes
EP0223194A1 (de) * 1985-11-14 1987-05-27 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Leitschaufel für Turbomaschinen
US4767264A (en) * 1986-10-31 1988-08-30 United Technologies Corporation Vane lever arm construction
US4979874A (en) * 1989-06-19 1990-12-25 United Technologies Corporation Variable van drive mechanism
US5492446A (en) * 1994-12-15 1996-02-20 General Electric Company Self-aligning variable stator vane
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
EP1400658A1 (de) * 2002-09-20 2004-03-24 BorgWarner Inc. Turbolader

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2481891A2 (de) * 2011-02-01 2012-08-01 United Technologies Corporation Verstellringabstandhalter fur Gasturbine
EP2481891A3 (de) * 2011-02-01 2013-12-18 United Technologies Corporation Verstellringabstandhalter fur Gasturbine
EP2824286A1 (de) * 2011-02-01 2015-01-14 United Technologies Corporation Gasturbinenmotorsynchronringstoßfänger
DE102016224523A1 (de) * 2016-12-08 2018-06-14 MTU Aero Engines AG Leitschaufelverstellung mit seitlich montiertem Verstellhebel
US10830090B2 (en) 2016-12-08 2020-11-10 MTU Aero Engines AG Vane actuating mechanism having a laterally mounted actuating lever
EP3431718A1 (de) * 2017-07-19 2019-01-23 Rolls-Royce plc Verstellringanordnung
DE102017222209A1 (de) * 2017-12-07 2019-06-13 MTU Aero Engines AG Leitschaufelanbindung sowie Strömungsmaschine
US10982558B2 (en) 2017-12-07 2021-04-20 MTU Aero Engines AG Guide vane connection
FR3097007A1 (fr) * 2019-06-06 2020-12-11 Safran Aircraft Engines Dispositif d’actionnement d’aubes à calage variable de turbomachine, turbomachine munie de celui-ci

Also Published As

Publication number Publication date
JP4832839B2 (ja) 2011-12-07
FR2875559B1 (fr) 2007-02-23
US7524165B2 (en) 2009-04-28
CN1789673A (zh) 2006-06-21
CN1789673B (zh) 2010-09-15
US20060062667A1 (en) 2006-03-23
EP1637742B1 (de) 2016-11-23
CA2520078C (fr) 2011-04-19
RU2005129352A (ru) 2007-03-27
JP2006090319A (ja) 2006-04-06
CA2520078A1 (fr) 2006-03-21
EP1637742A3 (de) 2014-03-12
RU2311541C2 (ru) 2007-11-27
FR2875559A1 (fr) 2006-03-24

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