EP1820942B1 - Dispositif de réglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine - Google Patents

Dispositif de réglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine Download PDF

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Publication number
EP1820942B1
EP1820942B1 EP07101657A EP07101657A EP1820942B1 EP 1820942 B1 EP1820942 B1 EP 1820942B1 EP 07101657 A EP07101657 A EP 07101657A EP 07101657 A EP07101657 A EP 07101657A EP 1820942 B1 EP1820942 B1 EP 1820942B1
Authority
EP
European Patent Office
Prior art keywords
ring
turbomachine
synchronisation
adjusting
slot
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.)
Active
Application number
EP07101657A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1820942A1 (fr
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
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1820942A1 publication Critical patent/EP1820942A1/fr
Application granted granted Critical
Publication of EP1820942B1 publication Critical patent/EP1820942B1/fr
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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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation

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 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 vanes (called variable-pitch vanes) which can pivot about their axis of connection to the stator so as to modify their angle of registration as a function of the operating speed of the turbomachine.
  • Known devices for controlling the variable pitch vanes usually comprise a ring surrounding a cylindrical casing of the turbine engine casing 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.
  • the blade control ring is centered on the axis of the turbomachine. It is further arranged coaxially with the casing of the casing of the turbomachine and generally rests thereon by means of a plurality of pads regularly distributed over its entire circumference.
  • the coaxial control devices of the control ring generally use pads mounted on threaded rods which are screwed into the control ring.
  • Document is also known US5,387,080 pads whose radial position is adjusted using a double screw mounted on the ring and whose two portions have slightly different helix angles.
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing a device for adjusting the coaxiality of the control ring which is simple in design and reliable during all the operating phases of the turbomachine.
  • a device for adjusting the centering of a turbomachine pivoting blade control ring comprising a control ring centered on a longitudinal axis of the turbomachine and provided with a plurality of threaded holes extending in a radial direction, and a plurality of shoe carriers each having a threaded rod screwed into one of the threaded holes of the ring, each shoe-holder carrying at an inner end a pad intended to come into contact with an envelope cylindrical coaxial with the ring, and wherein, in accordance with the invention, the control ring further comprises a plurality of slots extending in a tangential direction and radially through the ring, each slot communicating with one tapped holes of the ring, and the device comprises clamping means in a longitudinal direction of each of the slots so as to lock in position of the shoe carriers.
  • control ring further comprises a plurality of orifices extending in a longitudinal direction, each orifice communicating with one of the slots of the ring, and the device comprises a plurality of bolting systems each screwed into one of the orifices of the ring so as to effect a nip in a longitudinal direction of the corresponding slot.
  • each slot opens at one of its tangential ends in one of the tapped holes of the control ring.
  • each slot may open at its tangential end opposite the tapped hole in a smooth passage passing radially through the control ring.
  • the invention also relates to a turbomachine comprising at least one device for adjusting the centering of a pivoting vanes control ring as defined above.
  • the figure 1 partially represents a turbomachine compressor.
  • the compressor comprises a stator envelope 10 which is centered on the longitudinal axis XX of the turbomachine and which surrounds a rotor 12 so as to define therewith an annular vein 14 for the flow of gases.
  • the compressor further comprises a plurality of blades which form several stages in the flow channel 14. Some of these stages are formed of variable-pitch vanes 16. These blades 16 are pivotable about a radial 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.
  • the latter surrounds a cylindrical casing 28 of the casing of the turbomachine which is centered on the longitudinal axis XX thereof.
  • the control ring 26 and the cylindrical envelope 28 are arranged concentrically with respect to each other.
  • the invention relates to a device for adjusting the centering of the control ring 26 relative to the longitudinal axis X-X of the turbomachine. More specifically, such a device is capable of maintaining a fixed radial spacing between the control ring 26 and the cylindrical casing 28 of the casing of the turbomachine.
  • 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 cylindrical casing 28 of the casing of the turbomachine.
  • the pads 30 are regularly distributed over the entire circumference of the control ring 26 and are for example arranged between two adjacent pins 24 ( figure 1 ).
  • Each shoe 30 is secured to an inner end of a shoe holder 32 on which it is for example crimped.
  • Each shoe holder 32 consists of a threaded rod 34 which is screwed into a threaded hole 36 through the control ring 26 from one side and extending in a radial direction relative thereto. Once screwed into the ring of control, the rod 34 of the shoe carriers 32 protrudes radially relative to the ring ( figures 3 and 5 ).
  • control ring 26 further comprises a plurality of slots 38 which extend in a tangential (or circumferential) direction of the ring and which traverse the ring radially from one side to the other. Furthermore, each slot 38 communicates with one of the threaded holes 36 of the ring.
  • each slot 38 opens at one of its tangential ends in the corresponding threaded hole 36 of the ring.
  • the device for adjusting the centering of the control ring 26 further comprises gripping means in a longitudinal direction of each of the slots 38 so as to lock in position the shoe carriers 32.
  • control ring 26 comprises a plurality of orifices 40 (for example smooth) extending in a longitudinal direction (that is to say, parallel to the longitudinal axis XX of the turbomachine) and communicating each with one of the slots 38 of the ring.
  • each orifice 40 passes through one of the slots 38 from one side to the other and substantially perpendicularly thereto.
  • the device also comprises a plurality of bolting systems 42 which are each screwed into one of the orifices 40 of the ring, each bolting system 42 consisting of a screw 42a and a clamping nut 42b.
  • each slot 38 may open at its tangential end opposite the threaded hole 36 through which the threaded rod 34 passes through a smooth passage 44 passing radially through the control ring 26 from one side to the other.
  • the role of these smooth passages 44 is to allow the machining of slots 38 (indeed, the slot machining tool must be able to lead to the two tangential ends of the slots).
  • each pad 30 The adjustment of the radial position of each pad 30 relative to the cylindrical casing 28 is effected by more or less screwing the threaded rod 34 of the shoe holder 32 in the corresponding threaded hole 36 of the control ring 26.
  • the screw 42a is screwed into the corresponding hole 40 and the nut 42b is tightened on the free end thereof so as to lock by pinching in its optimal position the shoe holder 32.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP07101657A 2006-02-09 2007-02-02 Dispositif de réglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine Active EP1820942B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0650461A FR2897121B1 (fr) 2006-02-09 2006-02-09 Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine

Publications (2)

Publication Number Publication Date
EP1820942A1 EP1820942A1 (fr) 2007-08-22
EP1820942B1 true EP1820942B1 (fr) 2009-04-22

Family

ID=37507755

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07101657A Active EP1820942B1 (fr) 2006-02-09 2007-02-02 Dispositif de réglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine

Country Status (7)

Country Link
US (1) US7677866B2 (ru)
EP (1) EP1820942B1 (ru)
JP (1) JP2007211775A (ru)
CA (1) CA2577593C (ru)
DE (1) DE602007000927D1 (ru)
FR (1) FR2897121B1 (ru)
RU (1) RU2420663C2 (ru)

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AU2003229779A1 (en) * 2003-05-06 2004-06-30 Honeywell International Inc. Tamperproof and calibration device, especially for a turbocharger with a variable nozzle device
US8092157B2 (en) * 2007-12-19 2012-01-10 United Technologies Corporation Variable turbine vane actuation mechanism having a bumper ring
EP2107217A1 (en) * 2008-03-31 2009-10-07 Siemens Aktiengesellschaft Unison ring assembly for an axial compressor casing
FR2936557B1 (fr) * 2008-09-30 2017-04-21 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison par pistes de guidage.
US8864450B2 (en) * 2011-02-01 2014-10-21 United Technologies Corporation Gas turbine engine synchronizing ring bumper
FR2983924B1 (fr) * 2011-12-09 2013-11-22 Snecma Carter annulaire pour un compresseur de turbomachine
WO2014052842A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Synchronization ring runner with cradle
US20140093362A1 (en) 2012-09-28 2014-04-03 United Technologies Corporation Gas turbine engine components and method of assembly
US9422825B2 (en) 2012-11-05 2016-08-23 United Technologies Corporation Gas turbine engine synchronization ring
US9617869B2 (en) * 2013-02-17 2017-04-11 United Technologies Corporation Bumper for synchronizing ring of gas turbine engine
RU2561371C1 (ru) * 2014-10-15 2015-08-27 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Статор компрессора газотурбинного двигателя
FR3029562B1 (fr) * 2014-12-09 2016-12-09 Snecma Anneau de commande d’un etage d’aubes a calage variable pour une turbomachine
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
FR3072430B1 (fr) * 2017-10-16 2019-10-18 Safran Aircraft Engines Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine
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
CN110529432A (zh) * 2019-08-13 2019-12-03 中国航发贵阳发动机设计研究所 一种改进航空发动机风扇进口导叶调节的机匣
CN116255358A (zh) * 2023-02-27 2023-06-13 中国航发湖南动力机械研究所 一种压气机调节机构的支撑限位装置

Family Cites Families (10)

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JPS6056276B2 (ja) * 1978-10-20 1985-12-09 株式会社日立製作所 ガイドベ−ン保護装置
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
FR2683851A1 (fr) * 1991-11-20 1993-05-21 Snecma Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor.
FR2699595B1 (fr) * 1992-12-23 1995-01-20 Snecma Dispositif de guidage en rotation d'un anneau de commande d'aubes pivotantes.
US6092984A (en) * 1998-12-18 2000-07-25 General Electric Company System life for continuously operating engines
JP2002081416A (ja) * 2000-07-06 2002-03-22 Iwata Seisakusho:Kk 取付け固定具
JP4032376B2 (ja) * 2001-11-01 2008-01-16 可陽工業株式会社 締付け具
US6884025B2 (en) * 2002-09-30 2005-04-26 United Technologies Corporation Shim lock/pin anti-rotation bumper design
DE10351202A1 (de) * 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln
FR2882578B1 (fr) * 2005-02-25 2007-05-25 Snecma Moteurs Sa Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine

Also Published As

Publication number Publication date
FR2897121B1 (fr) 2008-05-02
JP2007211775A (ja) 2007-08-23
RU2420663C2 (ru) 2011-06-10
US7677866B2 (en) 2010-03-16
FR2897121A1 (fr) 2007-08-10
EP1820942A1 (fr) 2007-08-22
DE602007000927D1 (de) 2009-06-04
CA2577593A1 (fr) 2007-08-09
US20070183889A1 (en) 2007-08-09
CA2577593C (fr) 2013-05-07
RU2007104917A (ru) 2008-08-20

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