EP1696134A2 - Regeleinrichtung zur Zentrierung des Verstellringes für die verstellbaren Leitschaufeln einer Turbomaschine. - Google Patents

Regeleinrichtung zur Zentrierung des Verstellringes für die verstellbaren Leitschaufeln einer Turbomaschine. Download PDF

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Publication number
EP1696134A2
EP1696134A2 EP06110207A EP06110207A EP1696134A2 EP 1696134 A2 EP1696134 A2 EP 1696134A2 EP 06110207 A EP06110207 A EP 06110207A EP 06110207 A EP06110207 A EP 06110207A EP 1696134 A2 EP1696134 A2 EP 1696134A2
Authority
EP
European Patent Office
Prior art keywords
shoe
ring
control ring
pad
shoe holder
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
EP06110207A
Other languages
English (en)
French (fr)
Other versions
EP1696134B1 (de
EP1696134A3 (de
Inventor
Alain Bromann
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 EP1696134A2 publication Critical patent/EP1696134A2/de
Publication of EP1696134A3 publication Critical patent/EP1696134A3/de
Application granted granted Critical
Publication of EP1696134B1 publication Critical patent/EP1696134B1/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
    • 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
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters

Definitions

  • the present invention relates to the general field of devices for adjusting the centering of a synchronization ring controlling turbomachine pivoting vanes on the axis thereof.
  • stator vane stages In a turbomachine, it is known to use one or more stages of stator vanes for adjusting the flow and the flow direction of the gases passing through the compression section as a function of the operating speed of the turbomachine.
  • stator vane stages comprise a plurality of blades (called variable pitch vanes) which are pivotable about their stator connection axis so that their stall angle can be varied according to the operating speed of the stator. the turbomachine.
  • Known devices for controlling the variable pitch vanes usually comprise a control member in the form of a ring surrounding a casing of the turbomachine and a plurality of levers or links, each link having a first end connected to the control ring by a hinge and a second end mounted on the pivot of a respective blade.
  • the synchronized modification of the angular position of the blades is thus achieved by rotation of the ring around the axis of the turbomachine.
  • each pad is secured to a shoe holder with a rod which passes through the ring from one side and which is screwed into the ring from below it. Also, due to the presence of the casing shell, it is no longer possible to disassemble a pad from below the ring.
  • the main object of the present invention is thus to overcome such disadvantages by proposing a device for adjusting the centering of the ring that is simple, reliable and which saves time during assembly and disassembly.
  • a device for adjusting the centering of a control ring of turbine engine pivoting blades comprising a plurality of pads intended to come into contact with a circular surface coaxial with the ring, each pivoting blade. being connected to the control ring by means of a rod having a first end fixed to the control ring by a pin disposed radially on said ring and a second end mounted on a pivot of the blade, said pads being secured each of a shoe holder, characterized in that each shoe holder is fixed under the control ring by means of fastening systems which are intended to be assembled from above the ring.
  • Fixing under the control ring means a fixing of the shoe holder against an inner surface of the ring.
  • assembly from above the control ring is meant an assembly of fastening systems from the outside of the ring.
  • the device may further comprise means for adjusting the radial position of the pads.
  • the shoe holder advantageously comprises a substantially tubular portion which extends longitudinally from the control ring towards the inside thereof and which is adapted to receive a complementary tubular portion of the shoe, the device further comprising a screw intended to be screwed into the tubular portion of the pad so as to allow adjustment of the radial position of the pad.
  • the device may also comprise means for locking the pad in rotation in the shoe-holder.
  • the device may also comprise means for locking the screw in the pad.
  • a spring is interposed between the tubular portion of the shoe-holder and the tubular portion of the shoe so as to ensure damping of the shoe on the circular surface.
  • Each shoe-holder may be disposed in the radial extension of the dovetail pin with which it is associated.
  • each shoe holder can be advantageously fixed on the control ring by means of two attachment systems which are arranged symmetrically on either side of the blade of the blade with which it is associated.
  • each shoe-holder may be angularly offset relative to the pin of the blade with which it is associated.
  • the fastening systems each consist of a screw to be screwed into the control ring from above and a clamping nut.
  • FIG. 1 partially represents a turbomachine compressor of axis X-X.
  • the compressor comprises an annular stator envelope 10 which is centered on the X-X axis of the turbomachine and which surrounds an annular rotor 12 so as to define an annular stream 14 of gas flow.
  • the compressor further comprises a plurality of blades which form several stages in the flow channel 14, some of which are formed of variable-pitch vanes 16. These variable-pitch vanes 16 are pivotable about an axis 18 which passes through the stator casing 10.
  • Each axis (or pivot) 18 of the variable-pitch vanes 16 is connected to one end of a rod or control lever 20 via a nozzle 22.
  • the other end of the rods 20 is articulated around pins 24 arranged radially on a control ring 26 which surrounds a circular surface 28 centered on the axis XX of the turbomachine and to which it must be coaxial.
  • the invention relates to a device for adjusting the centering of the control ring 26 relative to the axis XX of the turbomachine. More specifically, such a device must be able to maintain a fixed radial spacing between the control ring 26 and the circular surface 28 which is centered on the axis XX.
  • the device for adjusting the centering of the control ring 26 comprises in particular a plurality of pads 30 intended to come into contact with the circular surface 28.
  • FIG. 2 The embodiment of the device of the invention illustrated in FIG. 2 will now be described.
  • Each shoe 30 is integral with a shoe holder 32.
  • the shoe holder 32 has a substantially tubular portion 34 which extends longitudinally from an inner surface 26a of the control ring 26 inwardly thereof.
  • the shoe 30 is for example crimped at the free end of the tubular portion 34.
  • tubular portion 34 of the shoe holder 32 ends with two fastening flanges 36 which come into contact with the inner surface 26a of the ring 26.
  • fastening systems 38 make it possible to fix the shoe holder 32 under the control ring 26.
  • screw 38a and radially pass through the ring 26 and tightening nuts 38b are screwed at their free end against the fastening flanges 36 of the shoe holder 32.
  • the screws 38a of these fastening systems 38 are assembled from the top of the ring, that is to say from the outside towards the inside thereof, and the nuts 38b are fixed under the control ring 26.
  • the shoe holder 32 may be disposed in the radial extension of the pin 24 of the blade with which it is associated.
  • the shoe holder 32 is advantageously fixed under the control ring 26 by means of two fastening systems 38 which are arranged symmetrically on either side of the trunnion 24 of the blade with which it is associated .
  • the shoe holder can be angularly offset relative to the pin of the blade with which it is associated.
  • the tubular portion 34 of the shoe-holder 30 which extends longitudinally from the control ring 26 inwardly thereof and which terminates in the two fastening flanges 36 is adapted to receive, for example by sliding, a complementary tubular portion 40 of the pad 30.
  • the pad 30 is crimped at a free end of its tubular portion 40.
  • the device further comprises a screw 42 intended to be screwed into the tubular portion 40 of the pad 30 so as to allow adjustment of the radial position thereof.
  • the tubular portion 40 of the shoe 30 has an internal thread (not shown in the figures) complementary to that of the screw.
  • the adjusting screw 42 extends longitudinally from the control ring 26 inwardly thereof. As illustrated in FIG. 3, the head of the screw 42 is thus trapped between the inner surface 26a of the ring 26 and the tubular portion 34 of the shoe holder 32.
  • Locking means of the adjusting screw 42 in the pad 30 are also provided to ensure a locking of the radial position thereof.
  • these locking means are in the form of a self-braking sleeve 44 interposed between the screw 42 and the tubular portion 40 of the shoe 30.
  • these locking means could be composed an elliptical deformation of the tapping or a self-braking insert thread or any other known means of braking a screw in a threaded passage.
  • the respective tubular portions 34, 40 of the shoe holder 32 and the shoe 30 each have a substantially polygonal cross-section so as to lock the shoe 30 in rotation in the shoe holder 32.
  • these straight sections are thus substantially square shape. Alternatively, they could be rectangular, triangular, hexagonal, etc.
  • the adjustment of the radial position of the pad 30 with respect to the circular surface 28 is effected as follows.
  • the device is first fixed under the control ring 26 by means of the attachment systems 38.
  • the screw 42 By screwing more or less the screw 42 in the tubular portion 40 of the pad, the latter slides (without rotation) in the tubular portion 34 of the shoe holder 32 which is fixed.
  • the pad 30 can thus move radially relative to the circular surface 28.
  • the self-braking sleeve 44 (or any other equivalent means) then allows to block the adjustment of the pad thus made.
  • the access to the adjusting screw 42 can be effected either by dismounting beforehand the control lever 20 and the pin 24 which is associated with it when the shoe holder 32 is disposed in the radial extension thereof. (case of Figure 3), or directly through a passage in the ring (not shown in the figures).
  • the device for adjusting the centering of the control ring further comprises a spring 46 which is interposed between the respective tubular portions 34, 40 of the shoe holder 32 and the shoe 30.

Landscapes

  • 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)
EP06110207.5A 2005-02-25 2006-02-21 Regeleinrichtung zur Zentrierung des Verstellringes für die verstellbaren Leitschaufeln einer Turbomaschine. Active EP1696134B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0501931A FR2882578B1 (fr) 2005-02-25 2005-02-25 Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine

Publications (3)

Publication Number Publication Date
EP1696134A2 true EP1696134A2 (de) 2006-08-30
EP1696134A3 EP1696134A3 (de) 2012-11-14
EP1696134B1 EP1696134B1 (de) 2014-04-02

Family

ID=35266811

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06110207.5A Active EP1696134B1 (de) 2005-02-25 2006-02-21 Regeleinrichtung zur Zentrierung des Verstellringes für die verstellbaren Leitschaufeln einer Turbomaschine.

Country Status (7)

Country Link
US (1) US7244098B2 (de)
EP (1) EP1696134B1 (de)
JP (1) JP4887059B2 (de)
CN (1) CN1824957B (de)
CA (1) CA2537435C (de)
FR (1) FR2882578B1 (de)
RU (1) RU2395694C2 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2481892A2 (de) * 2011-02-01 2012-08-01 United Technologies Corporation Verstellringabstandhalter fur Gasturbine
FR3024996A1 (fr) * 2014-08-22 2016-02-26 Snecma Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine
FR3029562A1 (fr) * 2014-12-09 2016-06-10 Snecma Anneau de commande d’un etage d’aubes a calage variable pour une turbomachine
US10494937B2 (en) 2016-08-23 2019-12-03 MTU Aero Engines AG Inner ring for an annular guide vane assembly of a turbomachine
FR3119859A1 (fr) * 2021-02-15 2022-08-19 Safran Aircraft Engines Anneau de commande d’un etage d’aubes a calage variable pour une turbomachine

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2897121B1 (fr) * 2006-02-09 2008-05-02 Snecma Sa Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
US8092157B2 (en) * 2007-12-19 2012-01-10 United Technologies Corporation Variable turbine vane actuation mechanism having a bumper ring
EP2107217A1 (de) * 2008-03-31 2009-10-07 Siemens Aktiengesellschaft Verstellringanordnung für ein axiales Verdichtergehäuse
US8794910B2 (en) * 2011-02-01 2014-08-05 United Technologies Corporation Gas turbine engine synchronizing ring bumper
EP2900955B1 (de) 2012-09-28 2017-08-30 United Technologies Corporation Synchronisationsringläufer mit basis
US20140093362A1 (en) 2012-09-28 2014-04-03 United Technologies Corporation Gas turbine engine components and method of assembly
CA2959993A1 (en) 2014-09-12 2016-03-17 General Electric Company Axi-centrifugal compressor with variable outlet guide vanes
EP3000985B1 (de) * 2014-09-29 2021-05-26 Rolls-Royce North American Technologies, Inc. Verstellring-selbstzentrierer und verfahren zur zentralisierung
RU2561371C1 (ru) * 2014-10-15 2015-08-27 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Статор компрессора газотурбинного двигателя
JP6674763B2 (ja) * 2015-11-04 2020-04-01 川崎重工業株式会社 可変静翼操作装置
GB2557565A (en) * 2016-07-18 2018-06-27 Rolls Royce Plc Variable stator vane mechanism
GB201614803D0 (en) * 2016-09-01 2016-10-19 Rolls Royce Plc Variable stator vane rigging
US10753224B2 (en) * 2017-04-27 2020-08-25 General Electric Company Variable stator vane actuator overload indicating bushing
DE102017109952A1 (de) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung einer Strömungsmaschine
FR3077851B1 (fr) 2018-02-09 2020-01-17 Safran Aircraft Engines Ensemble de commande d'un etage d'aubes a calage variable pour une turbomachine
US10801362B2 (en) 2018-06-19 2020-10-13 General Electric Company Self centering unison ring
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
US10815820B2 (en) 2019-02-05 2020-10-27 Raytheon Technologies Corporation Integral shear locking bumper for gas turbine engine
US11505306B2 (en) 2021-04-05 2022-11-22 General Electric Company Variable pitch fan assembly with remote counterweights
US11920482B2 (en) * 2022-03-10 2024-03-05 General Electric Company Device for fixing position of adjustable rows of guide vanes of turbomachine
CN116733609B (zh) * 2023-08-16 2023-10-31 成都市鸿侠科技有限责任公司 一种航空发动机进气道支板减震结构

Citations (4)

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Publication number Priority date Publication date Assignee Title
FR2617544A1 (fr) 1987-06-30 1989-01-06 Rolls Royce Plc Dispositif d'aubage variable de stator pour compresseur
EP0375593A1 (de) 1988-12-21 1990-06-27 United Technologies Corporation Einstellbare Distanzschraube
EP0741247A2 (de) 1995-05-04 1996-11-06 DEUTSCHE FORSCHUNGSANSTALT FÜR LUFT- UND RAUMFAHRT e.V. Verstellring
EP1403467A2 (de) 2002-09-30 2004-03-31 United Technologies Corporation Sicherung eines Unterlegekeils

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JPS6121840A (ja) * 1984-07-10 1986-01-30 Nissan Motor Co Ltd 車両の開閉体シ−ル構造
US4826399A (en) * 1988-05-06 1989-05-02 General Motors Corporation Unison ring mounting arrangement
CA2082709A1 (en) * 1991-12-02 1993-06-03 Srinivasan Venkatasubbu Variable stator vane assembly for an axial flow compressor of a gas turbine engine
FR2699595B1 (fr) * 1992-12-23 1995-01-20 Snecma Dispositif de guidage en rotation d'un anneau de commande d'aubes pivotantes.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2617544A1 (fr) 1987-06-30 1989-01-06 Rolls Royce Plc Dispositif d'aubage variable de stator pour compresseur
EP0375593A1 (de) 1988-12-21 1990-06-27 United Technologies Corporation Einstellbare Distanzschraube
EP0741247A2 (de) 1995-05-04 1996-11-06 DEUTSCHE FORSCHUNGSANSTALT FÜR LUFT- UND RAUMFAHRT e.V. Verstellring
EP1403467A2 (de) 2002-09-30 2004-03-31 United Technologies Corporation Sicherung eines Unterlegekeils

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2481892A2 (de) * 2011-02-01 2012-08-01 United Technologies Corporation Verstellringabstandhalter fur Gasturbine
EP2481892A3 (de) * 2011-02-01 2013-12-18 United Technologies Corporation Verstellringabstandhalter fur Gasturbine
FR3024996A1 (fr) * 2014-08-22 2016-02-26 Snecma Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine
FR3029562A1 (fr) * 2014-12-09 2016-06-10 Snecma Anneau de commande d’un etage d’aubes a calage variable pour une turbomachine
WO2016092172A1 (fr) 2014-12-09 2016-06-16 Snecma Anneau de commande d'un étage d'aubes à calage variable pour une turbomachine
RU2705128C2 (ru) * 2014-12-09 2019-11-05 Сафран Эркрафт Энджинз Кольцо управления ступени лопаток с изменяющимся углом установки для газотурбинного двигателя
US10662805B2 (en) 2014-12-09 2020-05-26 Snecma Control ring for a stage of variable-pitch vanes for a turbine engine
US10494937B2 (en) 2016-08-23 2019-12-03 MTU Aero Engines AG Inner ring for an annular guide vane assembly of a turbomachine
FR3119859A1 (fr) * 2021-02-15 2022-08-19 Safran Aircraft Engines Anneau de commande d’un etage d’aubes a calage variable pour une turbomachine

Also Published As

Publication number Publication date
RU2395694C2 (ru) 2010-07-27
EP1696134B1 (de) 2014-04-02
US20060193720A1 (en) 2006-08-31
CA2537435A1 (fr) 2006-08-25
RU2006105521A (ru) 2007-08-27
EP1696134A3 (de) 2012-11-14
US7244098B2 (en) 2007-07-17
CN1824957B (zh) 2012-05-16
FR2882578B1 (fr) 2007-05-25
CA2537435C (fr) 2013-06-18
FR2882578A1 (fr) 2006-09-01
JP4887059B2 (ja) 2012-02-29
JP2006233969A (ja) 2006-09-07
CN1824957A (zh) 2006-08-30

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