EP1696104A2 - Betätigungseinrichtung für Leitgitter variabler Geometrie einer Turbomaschine - Google Patents

Betätigungseinrichtung für Leitgitter variabler Geometrie einer Turbomaschine Download PDF

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Publication number
EP1696104A2
EP1696104A2 EP06290158A EP06290158A EP1696104A2 EP 1696104 A2 EP1696104 A2 EP 1696104A2 EP 06290158 A EP06290158 A EP 06290158A EP 06290158 A EP06290158 A EP 06290158A EP 1696104 A2 EP1696104 A2 EP 1696104A2
Authority
EP
European Patent Office
Prior art keywords
blade
rod
axis
drive square
orifice
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
EP06290158A
Other languages
English (en)
French (fr)
Other versions
EP1696104B1 (de
EP1696104A3 (de
Inventor
François Ribassin
Dominique Raulin
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
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1696104A2 publication Critical patent/EP1696104A2/de
Publication of EP1696104A3 publication Critical patent/EP1696104A3/de
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Publication of EP1696104B1 publication Critical patent/EP1696104B1/de
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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
    • 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
    • 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

Definitions

  • the invention relates to a variable-pitch blade control device in a turbomachine, such as an aircraft turbojet for example.
  • flow vane straightening stage stages are mounted between the stages of the compressor and turbine wheels. These straightening vanes are carried by their stator and are adjustable in position about their axis to optimize the flow of gases in the vein.
  • Each rectifying blade, or variable pitch blade comprises a cylindrical rotating guide shank, mounted in a cylindrical passage of the turbojet engine housing and terminating in a driving square on which is engaged a corresponding orifice formed at one end of the turbojet engine. a link.
  • the other end of the link comprises a cylindrical radial finger mounting on a control ring which surrounds the casing externally and which is connected to a means for driving in rotation about the axis of the turbojet engine, this drive means being usually a cylinder or an electric motor.
  • the rotation of the control ring is transmitted by the links to the cylindrical shanks of the vanes and rotates about their axes.
  • the axes of the blade tails and the axes of the fingers of the rods are parallel, which allows a play-free assembly of the rods on the control ring and on the tails of the blades, by a radial translation movement.
  • the axes of the fingers of the rods are radial and the axis of the tails of the vanes are inclined relative to a radial direction.
  • the rods are engaged on the control ring and on the tails of the blades by a radial translational movement, which makes it possible to mount the finger of each link without play on the control ring, but imposes to provide a game at the other end of the link to engage the orifice formed at this other end on the drive square provided at the end of the tail of the blade.
  • the present invention is intended in particular to eliminate this disadvantage, simply, economically and efficiently.
  • a variable-pitch blade control device in a turbomachine, in particular in an aircraft turbojet, comprising a control ring rotatably mounted around the casing of the turbomachine and connected by rods to the blades variable setting, each rod having at one end a radial mounting finger on the control ring and at its other end a mounting hole on a drive square formed at the end of a cylindrical tail of the blade, guided in rotation in a cylindrical passage of the casing, characterized in that, the axis of the cylindrical tail of the blade being inclined relative to the axis of the radial finger of the rod, the mounting hole of the rod presents in the longitudinal direction of the link, a dimension greater than that of the driving square and determines therewith, in the aforesaid direction, a game which varies over the height of the driving square; and said mounting port between a value sufficient to engage the mounting port on the drive square by moving the link parallel to the axis of its radial finger and a very small value or almost zero when
  • the device according to the invention allows on the one hand the mounting of a connecting rod by engagement on the control ring and on a blade tail by a radial translational movement, with the aid of a sufficient clearance between the orifice of the rod and the drive square of the blade in the longitudinal direction of the rod, and secondly the precise angular positioning of the blade around its axis, with the aid of a very low or near zero once the link is in place on the dawn drive square.
  • the aforementioned game is, in one embodiment, substantially triangular in a plane passing through the axis of the drive tail and oriented parallel to the longitudinal direction of the link .
  • the aforesaid game is formed between a straight face of the driving square, parallel to the axis of rotation of the blade, and an oblique surface of the mounting hole of the rod, inclined relative to this axis of rotation.
  • the dimension of the mounting hole, in the longitudinal direction of the rod, then decreases progressively from the radially inner end of this orifice to the vicinity of its radially outer end, and is constant until this radially outer end.
  • the aforementioned clearance is formed between a straight surface of the rod mounting hole, parallel to the axis of rotation of the blade, and an oblique face of the drive square. , inclined relative to the axis of rotation of the blade.
  • the dimension of the drive square, in the longitudinal direction of the rod, then increases progressively from its radially outer end to the vicinity of its radially inner end, then is constant to this radially inner end.
  • FIG. 1 diagrammatically shows, in axial section, a portion of a variable-pitch blade for a high-pressure compressor of a turbomachine, in particular an airplane turbojet or turboprop engine, comprising fixed blade stages 10 of straightening of the gas flow path in the compressor, alternating with stages of moving blades 12 carried by the rotor of the compressor.
  • Each straightening blade 10 comprises a blade 14 and a cylindrical tail 16 radially external mounted in a cylindrical passage 18 of a housing 20 of the compressor and formed at its radially outer end with a drive square 22 on which is engaged a corresponding orifice 24 formed at one end of a control rod 26.
  • the other end of the link 26 comprises a radial cylindrical finger 28 mounted on a control ring 30 which surrounds externally housing 20 and which is associated with an actuating means (not shown) for rotating in one direction or the other around the axis of the turbomachine to drive the blades 10 of a rectifying stage in rotation about their axes 32.
  • the cylindrical shank 16 of the blade 10 is centered and guided in rotation in the cylindrical passage 18 by means of a cylindrical sleeve 34 extending in the passage 18 over a major part of its longitudinal dimension and having at its radially outer end an outer annular flange 36 resting on the radially outer edge 38 of the wall of the passage 18.
  • a guide washer 40 is mounted around the tail 16 of the blade, between an annular surface 42 of the blade, perpendicular to its axis 32, and a corresponding annular surface 44 of the housing 20, and has on its inner edge a external cylindrical rim 46 extending around the shank 16.
  • the axis 32 of the blade is inclined relative to a radial direction while the axis 48 of the cylindrical finger 28 of the rod 26 connecting the blade 10 to the control ring 30 is radial.
  • the rod 26 is engaged on the control ring 30 and on the drive square 22 of the blade 10 by a radial translational movement, schematically represented by the arrows 50, which allows to mount substantially without play the finger 28 of the rod on the control ring 30, but requires to provide a game 52 at the other end of the rod between its orifice 24 and the drive square 22 of the blade, in the longitudinal direction of the connecting rod 26.
  • the orifice of the connecting rod 60 cooperating with the driving square 22 of the blade is formed by a cavity 62 opening on the radially inner face 64 of the end of the link 26 and extending over a major part of the thickness thereof, the bottom 66 of this cavity 62 having a passage opening of a screw 68 screwed in an axial hole 70 tapped from the tail of the dawn.
  • Figure 3 is a top view of the link 60 of Figure 2 and illustrates a mounting position of the rod 60 on the drive square 22 of the blade.
  • the rod After mounting on the drive square, the rod can take any position relative to the drive square in the longitudinal direction of the rod, that is to say that the rod can be in contact with the square of driving by one of the aforementioned faces 72, 76 of the orifice of the rod, as shown in Figure 1, or take an intermediate position, as shown in Figure 3. This results for each of its positions a distance L different between the axis 48 of the finger 28 of the rod and the axis 32 of the blade.
  • FIG. 4 diagrammatically shows the influence of the above-mentioned distance L on the angle of rotation of a blade, for a given rotation of the control ring.
  • the point 82 is the trace of the axis 32 of the blade in the plane of the drawing
  • the point 84 and the arc 86 represent, respectively, the trace of the axis 48 of the finger 28 of the rod and its trajectory in rotation about the axis 32 of the blade for a given rotation 88 of the control ring
  • the distance L mentioned above may vary, due to the mounting clearance, between a value L - s, and L + ⁇ 2 corresponding to the extreme positions mentioned above. of the rod relative to the training square of the dawn.
  • the blades may have the same angular orientation for a given position of the control ring, and take different angular orientations when the control ring is rotated.
  • the device according to the invention provides a simple, effective and economical solution to this problem.
  • the aforementioned set of mounting of the orifice of the connecting rod on the driving square is formed, in the longitudinal direction of the link 26, between a straight surface 90 of the orifice 24 of the rod, the opposite side to the finger 28 of the rod and parallel to the axis 32 of the blade, and an oblique face 92 of the drive square, which is opposite the surface 90 and inclined outwards towards the axis 32 of the blade.
  • This face 92 may be formed by removal of material on a radially outer portion of the drive square, the remaining radially inner portion of the drive square forming a straight face 94 parallel to the axis of the blade, and facing the surface 90 at a distance 96 very low or almost zero thereof and a height 98 sufficient to ensure the longitudinal retention of the rod relative to the blade before tightening. This height is typically about 0.5 mm.
  • the play is formed in the longitudinal direction of the link between a right side 100 of the drive square of the blade, which is parallel to the axis 32 of the blade and opposite the finger 28 of the rod, and an oblique surface 102 of the orifice of the rod, which is opposite the face 100 and inclined outwards in direction of the axis 32 of the dawn.
  • This surface 102 may be formed by removing material on the end face of the orifice 24 of the link over a portion of the height of this end face, from the inside.
  • the remaining radially outer portion of this end face is a straight face 104 parallel to the axis 32 of the blade, and opposite the face 100 of the drive square at a distance 106 very small or almost zero from that and a height 108 sufficient to ensure the longitudinal retention of the rod relative to the blade.
  • This height is typically about 0.5 mm.
  • the aforementioned game in a plane passing through the axis 32 of the blade and oriented parallel to the longitudinal direction of the rod, may have a triangular shape, curved or otherwise.
  • the clearance J at the radially outer end of the orifice of the connecting rod (in FIG. 5) or at the radially inner end of this orifice (FIG. 6) is sufficient to allow the assembly of the link on the drive square by radial displacement of the link.
  • the angular wedge defect of the blade corresponding to ⁇ 0 - ⁇ 1 and ⁇ 0 - ⁇ 2 in FIG. 4 was ⁇ 0.31 °.
  • the invention makes it possible to reduce this calibration defect to ⁇ 0.09 °, and therefore to reduce it by about 70%.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Toys (AREA)
EP06290158A 2005-02-25 2006-01-26 Betätigungseinrichtung für Leitgitter variabler Geometrie einer Turbomaschine Active EP1696104B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0501922A FR2882570B1 (fr) 2005-02-25 2005-02-25 Dipositif de commande d'aubes a calage variable dans une turbomachine

Publications (3)

Publication Number Publication Date
EP1696104A2 true EP1696104A2 (de) 2006-08-30
EP1696104A3 EP1696104A3 (de) 2009-01-28
EP1696104B1 EP1696104B1 (de) 2012-08-08

Family

ID=35148803

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06290158A Active EP1696104B1 (de) 2005-02-25 2006-01-26 Betätigungseinrichtung für Leitgitter variabler Geometrie einer Turbomaschine

Country Status (4)

Country Link
US (1) US7530784B2 (de)
EP (1) EP1696104B1 (de)
FR (1) FR2882570B1 (de)
RU (1) RU2365765C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
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CN111765035A (zh) * 2020-04-17 2020-10-13 湖南湘投清水塘水电开发有限责任公司 水轮机导水机构控制环装配结构

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US9353643B2 (en) * 2007-04-10 2016-05-31 United Technologies Corporation Variable stator vane assembly for a turbine engine
US8215902B2 (en) * 2008-10-15 2012-07-10 United Technologies Corporation Scalable high pressure compressor variable vane actuation arm
US8668444B2 (en) * 2010-09-28 2014-03-11 General Electric Company Attachment stud for a variable vane assembly of a turbine compressor
US8714916B2 (en) * 2010-09-28 2014-05-06 General Electric Company Variable vane assembly for a turbine compressor
US10030533B2 (en) * 2012-09-21 2018-07-24 United Technologies Corporation Flanged bushing for variable vane
FR3015594B1 (fr) * 2013-12-19 2018-04-06 Safran Aircraft Engines Compresseur de turbomachine, en particulier de turbopropulseur ou de turboreacteur d'avion
US10393145B2 (en) 2016-03-02 2019-08-27 General Electric Company Asymmetric alignment system for a variable stator vane
US10526911B2 (en) * 2017-06-22 2020-01-07 United Technologies Corporation Split synchronization ring for variable vane assembly
US10815818B2 (en) * 2017-07-18 2020-10-27 Raytheon Technologies Corporation Variable-pitch vane assembly
US10590795B2 (en) * 2017-10-17 2020-03-17 United Technologies Corporation Vane arm with tri-wedge circular pocket
DE102017222209A1 (de) * 2017-12-07 2019-06-13 MTU Aero Engines AG Leitschaufelanbindung sowie Strömungsmaschine
JP2019163728A (ja) * 2018-03-20 2019-09-26 本田技研工業株式会社 軸流圧縮機の可変静翼構造
CN113623271A (zh) * 2020-05-06 2021-11-09 中国航发商用航空发动机有限责任公司 燃气轮机、可调导叶调节机构及其联动环限位装置
CN114233401B (zh) * 2021-12-21 2024-06-11 中国航发沈阳发动机研究所 一种具有加长叶片旋转轴功能的叶片摇臂结构

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US4979874A (en) 1989-06-19 1990-12-25 United Technologies Corporation Variable van drive mechanism
US5024580A (en) 1989-06-17 1991-06-18 Rolls-Royce Plc Control of variable stator vanes

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US5492446A (en) * 1994-12-15 1996-02-20 General Electric Company Self-aligning variable stator vane
GB2301867A (en) * 1995-06-05 1996-12-18 Rolls Royce Plc Supporting unison rings in pivotable vane actuating mechanisms
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
FR2835295B1 (fr) * 2002-01-29 2004-04-16 Snecma Moteurs Dispositif de commande d'aube a angle de calage variable a liaison par pincement pour redresseur de compresseur de turbomachine
US6619916B1 (en) * 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow
GB2400416B (en) * 2003-04-12 2006-08-16 Rolls Royce Plc Improvements in or relating to control of variable stator vanes in a gas turbine engine
FR2853930B1 (fr) * 2003-04-16 2007-02-23 Snecma Moteurs Dispositif de commande d'aubes a calage variable dans une turbomachine
FR2854648B1 (fr) * 2003-05-07 2005-07-15 Snecma Moteurs Fixation avec rattrapage de jeu d'un levier de commande sur des aubes a angle de calage variable
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US5024580A (en) 1989-06-17 1991-06-18 Rolls-Royce Plc Control of variable stator vanes
US4979874A (en) 1989-06-19 1990-12-25 United Technologies Corporation Variable van drive mechanism

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111765035A (zh) * 2020-04-17 2020-10-13 湖南湘投清水塘水电开发有限责任公司 水轮机导水机构控制环装配结构
CN111765035B (zh) * 2020-04-17 2022-07-08 湖南湘投清水塘水电开发有限责任公司 水轮机导水机构控制环装配结构

Also Published As

Publication number Publication date
EP1696104B1 (de) 2012-08-08
US20060285969A1 (en) 2006-12-21
EP1696104A3 (de) 2009-01-28
FR2882570A1 (fr) 2006-09-01
RU2365765C2 (ru) 2009-08-27
FR2882570B1 (fr) 2007-04-13
US7530784B2 (en) 2009-05-12
RU2006105379A (ru) 2007-09-27

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