EP1820942A1 - Vorrichtung zur Einstellung der Zentrierung eines Synchronisationsrings zur Steuerung von schwenkbaren Leitradschaufeln einer Strömungsmaschine - Google Patents

Vorrichtung zur Einstellung der Zentrierung eines Synchronisationsrings zur Steuerung von schwenkbaren Leitradschaufeln einer Strömungsmaschine Download PDF

Info

Publication number
EP1820942A1
EP1820942A1 EP07101657A EP07101657A EP1820942A1 EP 1820942 A1 EP1820942 A1 EP 1820942A1 EP 07101657 A EP07101657 A EP 07101657A EP 07101657 A EP07101657 A EP 07101657A EP 1820942 A1 EP1820942 A1 EP 1820942A1
Authority
EP
European Patent Office
Prior art keywords
ring
control ring
turbomachine
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.)
Granted
Application number
EP07101657A
Other languages
English (en)
French (fr)
Other versions
EP1820942B1 (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 EP1820942A1 publication Critical patent/EP1820942A1/de
Application granted granted Critical
Publication of EP1820942B1 publication Critical patent/EP1820942B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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.
  • FIG 1 partially shows a turbomachine compressor.
  • the compressor comprises a stator envelope 10 which is centered on the longitudinal axis X-X 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 control, the rod 34 of the shoe carrier 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 tapped hole 36 corresponding 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 throughout and substantially perpendicular 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 Vorrichtung zur Einstellung der Zentrierung eines Synchronisationsrings zur Steuerung von schwenkbaren Leitradschaufeln einer Strömungsmaschine Active EP1820942B1 (de)

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 true EP1820942A1 (de) 2007-08-22
EP1820942B1 EP1820942B1 (de) 2009-04-22

Family

ID=37507755

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07101657A Active EP1820942B1 (de) 2006-02-09 2007-02-02 Vorrichtung zur Einstellung der Zentrierung eines Synchronisationsrings zur Steuerung von schwenkbaren Leitradschaufeln einer Strömungsmaschine

Country Status (7)

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2983924A1 (fr) * 2011-12-09 2013-06-14 Snecma Carter annulaire pour un compresseur de turbomachine
FR3029562A1 (fr) * 2014-12-09 2016-06-10 Snecma Anneau de commande d’un etage d’aubes a calage variable pour une turbomachine
FR3072430A1 (fr) * 2017-10-16 2019-04-19 Safran Aircraft Engines Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE550521T1 (de) * 2003-05-06 2012-04-15 Honeywell Int Inc System, das eine garantiekalibriereinrichtung, insbesondere für einen turbolader mit verstellbaren leitschaufeln, enthält
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
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
US20140093362A1 (en) 2012-09-28 2014-04-03 United Technologies Corporation Gas turbine engine components and method of assembly
WO2014052842A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Synchronization ring runner with cradle
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
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
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

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
US5387080A (en) * 1992-12-23 1995-02-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Rotationally guided control ring for pivotable vanes in a turbomachine
EP1403467A2 (de) * 2002-09-30 2004-03-31 United Technologies Corporation Sicherung eines Unterlegekeils
WO2005045202A1 (de) * 2003-11-03 2005-05-19 Mtu Aero Engines Gmbh Vorrichtung zum verstellen von leitschaufeln eines turbotriebwerks

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
FR2683851A1 (fr) * 1991-11-20 1993-05-21 Snecma Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor.
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
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
US5387080A (en) * 1992-12-23 1995-02-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Rotationally guided control ring for pivotable vanes in a turbomachine
EP1403467A2 (de) * 2002-09-30 2004-03-31 United Technologies Corporation Sicherung eines Unterlegekeils
WO2005045202A1 (de) * 2003-11-03 2005-05-19 Mtu Aero Engines Gmbh Vorrichtung zum verstellen von leitschaufeln eines turbotriebwerks

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2983924A1 (fr) * 2011-12-09 2013-06-14 Snecma Carter annulaire pour un compresseur de turbomachine
US9212666B2 (en) 2011-12-09 2015-12-15 Snecma Annular casing for a turbine engine compressor
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
CN107002504A (zh) * 2014-12-09 2017-08-01 赛峰飞机发动机公司 用于涡轮发动机的控制可变设置轮叶的级的环
CN107002504B (zh) * 2014-12-09 2019-04-16 赛峰飞机发动机公司 用于涡轮发动机的控制可变设置轮叶的级的环
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
FR3072430A1 (fr) * 2017-10-16 2019-04-19 Safran Aircraft Engines Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine

Also Published As

Publication number Publication date
JP2007211775A (ja) 2007-08-23
DE602007000927D1 (de) 2009-06-04
CA2577593C (fr) 2013-05-07
US20070183889A1 (en) 2007-08-09
CA2577593A1 (fr) 2007-08-09
FR2897121B1 (fr) 2008-05-02
RU2007104917A (ru) 2008-08-20
FR2897121A1 (fr) 2007-08-10
EP1820942B1 (de) 2009-04-22
US7677866B2 (en) 2010-03-16
RU2420663C2 (ru) 2011-06-10

Similar Documents

Publication Publication Date Title
EP1820942B1 (de) Vorrichtung zur Einstellung der Zentrierung eines Synchronisationsrings zur Steuerung von schwenkbaren Leitradschaufeln einer Strömungsmaschine
EP1696134B1 (de) Regeleinrichtung zur Zentrierung des Verstellringes für die verstellbaren Leitschaufeln einer Turbomaschine.
EP1764483B1 (de) Buchse für die Drehschaft einer verstellbaren Statorschaufel einer Turbomaschine, und entsprechende Statorbeschaufelung, Verdichter, und Turbomaschine
EP0146449B1 (de) Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln
CA2418230C (fr) Dispositif de commande d'aube a angle de calage variable a liaison par pincement
FR2882577A1 (fr) Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
EP1887188B1 (de) Steuervorrichtung einer Schaufel mit verstellbaren Winkel für eine Turbomachine mit zylindrischer Pleuelstange
EP1577495B1 (de) Wälzlagereinheit einer Turbomaschine mit reduziertem Platzbedarf
FR3014152A1 (fr) Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procede d'assemblage d'un tel dispositif
FR3009335A1 (fr) Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine
EP1867841A1 (de) Stator einer Strömungsmaschine, der eine Stufe mit Leitschaufeln umfasst, die von einem Drehzahnkranz mit automatischer Zentrierung angetrieben werden
FR2696500A1 (fr) Turbomachine équipée de moyens de réglage du jeu entre les redresseurs et le rotor d'un compresseur.
EP3230602B1 (de) Ring zur steuerung einer phase von leitschaufeln mit variablen einstellungen für einen turbinenmotor
CA2518355A1 (fr) Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
FR3111161A1 (fr) Systeme de verrouillage d'aubes de soufflante a calage variable
EP1491725B1 (de) Lagervorrichtung für eine verstellbare Schaufel
FR3072719A1 (fr) Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine
FR2897120A1 (fr) Pivot d'aube a angle de calage variable de turbomachine et dispositif de commande d'une telle aube
FR3054006A1 (fr) Ensemble pour la commande d'aubes a calage variable dans une turbomachine
FR2874977A1 (fr) Douille de support pivotant pour pivot d'aube a calage variable de turbomachine
FR2949138A1 (fr) Turbomachine comportant des moyens d'anti-rotation d'un ecrou de palier
FR3027072A1 (fr) Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine
EP1439283A1 (de) Montageanordnung von Schwenkachsen verstellbarer Leitschaufeln
FR2992376A1 (fr) Soufflante a calage variable par rotation differentielle des disques de soufflante
EP1674707A1 (de) Düse mit veränderlichem Querschnitt mit einstückiger Steuerhebelhalterung für eine Turbomaschine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20070202

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE FR GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 602007000927

Country of ref document: DE

Date of ref document: 20090604

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20100125

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170707

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240123

Year of fee payment: 18

Ref country code: GB

Payment date: 20240123

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240123

Year of fee payment: 18