EP3189216A1 - Mécanisme d'entraînement d'organes de réglage de l'orientation des pales - Google Patents

Mécanisme d'entraînement d'organes de réglage de l'orientation des pales

Info

Publication number
EP3189216A1
EP3189216A1 EP15767220.5A EP15767220A EP3189216A1 EP 3189216 A1 EP3189216 A1 EP 3189216A1 EP 15767220 A EP15767220 A EP 15767220A EP 3189216 A1 EP3189216 A1 EP 3189216A1
Authority
EP
European Patent Office
Prior art keywords
gear
wheel
stage
turbomachine
adjusting
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.)
Pending
Application number
EP15767220.5A
Other languages
German (de)
English (en)
French (fr)
Inventor
Pierre-Alain Francis Claude Sebrecht
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3189216A1 publication Critical patent/EP3189216A1/fr
Pending legal-status Critical Current

Links

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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • 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
    • F05D2260/53—Kinematic linkage, i.e. transmission of position using gears

Definitions

  • the invention relates to a drive mechanism for adjusting the orientation of the blades of several stages of a turbomachine rectifier.
  • the invention relates more particularly to a drive mechanism of two adjusting members for simultaneously driving the two adjusting members with different speeds of movement of one actuator relative to the other.
  • the compressor and / or the turbine of a turbomachine consist of several stages, each stage comprising a rectifier of the gas flow.
  • the modification of the orientation of the stator blades is controlled by means of an actuator comprising a control shaft which cooperates with a member associated with each blade or a control unit of the orientation of the blades.
  • the use of a control box is adaptable to any size of turbomachine.
  • this solution has a large number of components, which reduces the accuracy of the system because of the accumulation of games between the many components and their respective deformations.
  • the object of the invention is to provide a drive mechanism for adjusting the orientation of the blades which is both of reduced size, and having a reduced number of parts.
  • turbomachine rectifier which comprises means for simultaneously driving the two adjusting members in displacement in the turbomachine
  • a single driving wheel which simultaneously drives the first adjusting member and the second adjusting member and comprises two gear stages which are arranged between the driving wheel and one or the other of the first member adjusting member and the second adjusting member and having different transmission ratios.
  • Such a drive mechanism makes it possible to concentrate the drive and variability functions of the transmission ratios in a small number of components, thereby reducing the mass of the drive mechanism.
  • the transmission ratio of the gear stage associated with the second adjustment member is variable as a function of the angular position of the driving wheel in the turbomachine.
  • the gear stage associated with the second adjustment member comprises a first gear which is engaged with the driving wheel, a second gear which is engaged with a toothed portion of the second adjustment member and means for adjusting the gear. coupling the two wheels together to vary the transmission ratio of the gear stage.
  • the gear stage associated with the second adjustment member is designed to vary the transmission ratio of the gear stage in a non-linear manner.
  • the axes of rotation of the two wheels of the gear stage associated with the second adjustment member are parallel and offset relative to one another.
  • one of the two wheels comprises a groove and the other wheel comprises a finger protruding axially from said other wheel, the finger being received in the groove and being adapted to cooperate with the groove to transmit a torque from the first wheel to the second wheel.
  • the groove is formed in the first gear and the finger is carried by the second gear.
  • the gear stage associated with the first adjustment member comprises a third gear which is engaged with the driving wheel and a complementary toothed portion of the first adjustment member.
  • the invention also relates to an aircraft turbomachine having two stages of rectifier whose orientation of the blades can be modified, characterized in that each stage of rectifier comprises a device for adjusting the orientation of the blades of said stage of rectifier, the two control members being rotatable in the turbomachine about the main axis of the turbomachine and being rotated by a drive mechanism according to the invention.
  • each adjusting member comprises a first toothed potion associated with the associated gear stage and a second toothed portion which meshes with a toothed wheel carried by each blade of the associated stator stage.
  • a mechanism 10 for driving an adjusting member 12 of the orientation of the blades 14 of a first stage 16 of the turbomachine rectifier and an adjusting member 18 of the orientation blades 20 of a second stage 22 of the turbomachine rectifier is shown in the single figure.
  • the adjusting members 12, 18 of the orientation of the blades 14, 20 each consist of a ring associated with each stage 16, 22 of the rectifier, which is rotatable in the turbomachine around the main axis of the turbomachine (no represent).
  • An axial end 12a, 18a of each ring 12, 18 comprises a toothed portion which cooperates with a toothed wheel carried by each blade 14, 20.
  • the orientation of the blades 14, 20 of the two stages of rectifier 16, 22 must be modified simultaneously to optimize the performance of the turbomachine. Also, the blades 14 of the first rectifier stage 16 pivot at a different angle with respect to the pivot angle of the blades 20 of the second rectifier stage 22.
  • the driving mechanism 10 of the adjusting rings 12, 18 is designed to simultaneously drive the two rings 12, 18 in motion and that the displacement amplitude of the first ring 12, associated with the first stage of the rectifier 16 is different from the amplitude of displacement of the second ring 18 which is associated with the second stage 22 of the rectifier.
  • the driving mechanism 10 comprises a single driving wheel 24 which is coupled to the two rings 12, 18 via two gear stages 26, 28.
  • the first gear stage 26 is associated with the first ring 12 of the first stage 16 of the rectifier and has a single gear 30 which is engaged with the drive wheel 24 and with the first ring 12.
  • the second gear stage 28 is associated with the second ring 18 and has a first gear 32 which is engaged with the driving wheel 24 and a second gear 34 which is engaged with the second ring 18.
  • the two gear wheels the second gear stage 28 cooperate with each other to transmit drive forces from the first gear 32 to the second gear 34.
  • each ring 12, 18 has for this purpose a toothed portion 44 which cooperates with the wheel 30, 34 of the first gear stage 26 or the second gear stage 28 associated therewith.
  • the first wheel 32 and the second wheel 34 are coupled to each other to provide a different transmission ratio of the transmission ratio provided by the gear wheel 30 of the first gear stage 26.
  • the transmission ratio provided by the gear wheel 30 of the first gear stage 26 is linear and is constant regardless of the angular position of the drive wheel 24.
  • the gear ratio supplied by the second gear stage 28 is thus nonlinear.
  • the transmission ratio of the second gear stage 28 is variable and varies according to the angular position of the driving wheel 24, and therefore of the first wheel 32.
  • the first wheel 32 and the second wheel 34 are arranged parallel to each other and their respective axes of rotation 36, 38 are parallel and are radially offset relative to each other.
  • the two wheels 32, 34 are coupled by means making it possible to vary the transmission ratio of the second gear stage 28.
  • These coupling means here consist of a set of groove 40 and follower pin 42 each of which is carried respectively by one or the other of the first or the second wheel 32, 34.
  • the groove 40 is formed in the first wheel 32 and is of radial main orientation relative to the axis 36 of rotation of the first wheel 32.
  • the finger 42 is carried by the second wheel 34, projecting axially compared to a radial face 34a of the second wheel 34 vis-à-vis the first wheel 32 and is received in the groove 40.
  • the invention is not limited to this single configuration of the groove 40 and the finger 42 and that the groove 40 may not be rectilinear, to obtain a given law defining the transmission ratio of the second stage of gears 28.
  • the axis of rotation of the driving wheel 24 is generally perpendicular to the axes of rotation 36, 38 of the wheels 30, 32, 34 of the gear stages 26, 28.
  • the axes of rotation of the different wheels 24, 30, 32, 34 are parallel.
  • turbomachine (not shown) comprising the stages of rectifier 16, 22 and the drive mechanism 10 defined above is then of simpler structure.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gear Transmission (AREA)
  • Transmission Devices (AREA)
  • Supercharger (AREA)
EP15767220.5A 2014-09-05 2015-09-03 Mécanisme d'entraînement d'organes de réglage de l'orientation des pales Pending EP3189216A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1458344A FR3025577B1 (fr) 2014-09-05 2014-09-05 Mecanisme d'entrainement d'organes de reglage de l'orientation des pales
PCT/FR2015/052325 WO2016034816A1 (fr) 2014-09-05 2015-09-03 Mécanisme d'entraînement d'organes de réglage de l'orientation des pales

Publications (1)

Publication Number Publication Date
EP3189216A1 true EP3189216A1 (fr) 2017-07-12

Family

ID=51932450

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15767220.5A Pending EP3189216A1 (fr) 2014-09-05 2015-09-03 Mécanisme d'entraînement d'organes de réglage de l'orientation des pales

Country Status (9)

Country Link
US (1) US10502088B2 (zh)
EP (1) EP3189216A1 (zh)
JP (1) JP6621807B2 (zh)
CN (1) CN106687665B (zh)
BR (1) BR112017003746B1 (zh)
CA (1) CA2959879C (zh)
FR (1) FR3025577B1 (zh)
RU (1) RU2705529C2 (zh)
WO (1) WO2016034816A1 (zh)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018029835A1 (ja) * 2016-08-10 2018-02-15 三菱日立パワーシステムズ株式会社 軸受装置および回転機械
FR3057327B1 (fr) * 2016-10-07 2018-12-07 Safran Aircraft Engines Mecanisme d'entrainement d'organes de reglage de l'orientation des pales
AU2020376271B9 (en) * 2019-10-31 2023-11-09 Daikin Industries, Ltd. Inlet guide vane actuator assembly

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
GB706139A (en) * 1950-10-07 1954-03-24 Hellmut Weinrich Improvements in continuous, automatically regulating gears
US5174716A (en) * 1990-07-23 1992-12-29 General Electric Company Pitch change mechanism
US5498135A (en) * 1995-01-17 1996-03-12 Newport News Shipbuilding And Dry Dock Company Actuator for a variable pitch propeller
US6039534A (en) * 1998-09-21 2000-03-21 Northern Research And Engineering Corp Inlet guide vane assembly
FR2856424B1 (fr) 2003-06-20 2005-09-23 Snecma Moteurs Dispositif de calage variable de deux etages d'aubes fixes sur un turboreacteur
FR2885969B1 (fr) * 2005-05-17 2007-08-10 Snecma Moteurs Sa Systeme de commande d'etages d'aubes de stator a angle de calage variable de turbomachine
US7665959B2 (en) * 2005-07-20 2010-02-23 United Technologies Corporation Rack and pinion variable vane synchronizing mechanism for inner diameter vane shroud
CN100393985C (zh) * 2006-10-13 2008-06-11 成都发动机（集团）有限公司 精确调节顶压和紧急全关静叶的调节机构
US8240983B2 (en) * 2007-10-22 2012-08-14 United Technologies Corp. Gas turbine engine systems involving gear-driven variable vanes
CN202250255U (zh) * 2011-08-04 2012-05-30 中国南方航空工业(集团)有限公司 涡轮机导向叶片调节器
GB201202383D0 (en) * 2012-02-13 2012-03-28 Rolls Royce Plc A unison ring gear assembly
FR3030649B1 (fr) * 2014-12-18 2017-01-27 Snecma Mecanisme d'entrainement d'organes de reglage de l'orientation des pales

Non-Patent Citations (2)

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Title
None *
See also references of WO2016034816A1 *

Also Published As

Publication number Publication date
CN106687665A (zh) 2017-05-17
JP6621807B2 (ja) 2019-12-18
FR3025577A1 (fr) 2016-03-11
CA2959879C (fr) 2022-09-20
US10502088B2 (en) 2019-12-10
JP2017527736A (ja) 2017-09-21
WO2016034816A1 (fr) 2016-03-10
US20170260870A1 (en) 2017-09-14
RU2705529C2 (ru) 2019-11-07
RU2017111042A (ru) 2018-10-05
CA2959879A1 (fr) 2016-03-10
FR3025577B1 (fr) 2016-12-23
CN106687665B (zh) 2019-06-14
BR112017003746A2 (pt) 2017-12-05
BR112017003746B1 (pt) 2022-10-18
RU2017111042A3 (zh) 2019-03-14

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