EP0765992A1 - Betätigungseinrichtung für verstellbare Statorschaufeln - Google Patents

Betätigungseinrichtung für verstellbare Statorschaufeln Download PDF

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Publication number
EP0765992A1
EP0765992A1 EP96402040A EP96402040A EP0765992A1 EP 0765992 A1 EP0765992 A1 EP 0765992A1 EP 96402040 A EP96402040 A EP 96402040A EP 96402040 A EP96402040 A EP 96402040A EP 0765992 A1 EP0765992 A1 EP 0765992A1
Authority
EP
European Patent Office
Prior art keywords
cams
control
articulated
fixed
cam
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
EP96402040A
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English (en)
French (fr)
Other versions
EP0765992B1 (de
Inventor
Jean-Louis Charbonnel
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0765992A1 publication Critical patent/EP0765992A1/de
Application granted granted Critical
Publication of EP0765992B1 publication Critical patent/EP0765992B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

Definitions

  • the invention relates to a device for controlling a stage of pivoting or variable-pitch blades.
  • the pivots of the blades, which pass through the stator, are joined to control levers all connected to a control ring which surrounds the stator and which a control mechanism rotates.
  • control mechanisms which involve the use of an actuating member such as a jack and a transmission mechanism composed of levers, connecting rods, etc.
  • the characteristics of these transmissions are quite varied and some allow non-linear control of the blades, that is to say that the rotation of the latter is not proportional to the movement of the actuator.
  • the invention belongs to this kind of control devices and its essential advantage is that the transmission is particularly simple.
  • the invention relates to a device for controlling a stage of variable-pitch vanes provided with levers joined to a control ring, the control ring being articulated to a cam pivoting around a first fixed axis, characterized in that the cam is joined to a control crank rotating around a second fixed axis parallel to the first axis by a link articulated to the cam and to the rotating crank at points distinct from the fixed axes.
  • the control device can moreover relate to several stages of blades and several control rings at the same time.
  • there are other cams articulated by pivoting around other first axes fixed to other control rings of other stages of blades with variable setting the other cams being interconnected and to the rotating crank by a synchronization bar articulated to the other cams and to the crank in identical positions with respect to the other first fixed axes and to the second fixed axis.
  • FIG. 1 represents the inlet of a turbomachine with in particular a low pressure compressor section 1 and a high pressure compressor section 2. It is on this that the invention is established.
  • Each of the compressors is above all composed of stages of fixed vanes 3 and movable vanes 4 which alternate, some attached to a stator 5 which surrounds the annular vein 6 of gas circulation and the others fixed to a rotor 7 delimiting vein 6, and turning with it.
  • the fixed blades 3 can actually pivot around a pivot 8 passing through the stator 5.
  • the pivot 8 of each of the blades 3 is terminated by a lever 9.
  • the levers 9 of each of the blade stages are united to a ring of command 10 common.
  • a pin 17 fixed on the stator is established at the elbow of the cam 15 to allow it to rotate, and its other arm 18 extends opposite the transmission rod 12 and carries at its end another articulation 19 intended to support a synchronization bar 20 perpendicular to the control ring 10, that is to say arranged in the axial direction of the machine.
  • the synchronization bar 20 is similarly articulated to other cams 15 assigned to the control of other stages of fixed blades 3 by transmissions similar to that just described and which notably include a control ring 10 for each of the floors.
  • the only difference is that the other cams, noted 15a, 15b, 15c, etc., have arms 16a, 16b or 16c, etc.
  • the control mechanism unlike a solution previously adopted by the applicant, does not consist of a lever fixed to the fixed axis 17 of the cam 15 considered first, and the purpose of which is to rotate the latter to pull or push on the control rods 12 via all the cams 15 and the synchronization bar 20. Instead, there is a crank 21 rotating around a second fixed axis 26 parallel to the first fixed axes 17, 17a, 17b, 17c, etc., and a connecting rod 22 whose ends are articulated, for the first 23 at the end of the crank 21, and for the second 24 to a part of the second arm 18 distant from the fixed axis 17.
  • the angle ⁇ is therefore a sinusoidal function of the angle ⁇ .
  • the crank 21 can be turned by the rod 27 of a jack 28 articulated at a fixed point 29, according to a usual design.
  • angles ⁇ of rotation imposed on the levers 9 and on the blades 3 are different for the various stages, and more precisely, they are proportional to the lengths l, la, lb, lc, etc., of the arms 16 between the fixed axis 17 and the articulation 14 of the transmission rod 12, that is to say that the laws of rotation are all sinusoidal.
  • the cam 15, now denoted 115 is not connected to the synchronization bar 20 and its second arm 18 is replaced by an arm 118 of another shape intended to receive a joint 123 uniting it at one end of a connecting rod 122 similar or similar to the connecting rod 22 and the other end of which is joined by a joint 124 to a protrusion 125 formed on a cam 115a moreover similar to the cam 15a and situated in the same place.
  • Another difference consists in that the fixed axis 117a of articulation of the cam 115a is not an inert axis but a control axis dependent on the actuator member.
  • the crank 21 of the previous embodiment is eliminated and the cam 115a is a motor lever.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Transmission Devices (AREA)
EP96402040A 1995-09-27 1996-09-26 Betätigungseinrichtung für verstellbare Statorschaufeln Expired - Lifetime EP0765992B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9511301 1995-09-27
FR9511301A FR2739137B1 (fr) 1995-09-27 1995-09-27 Dispositif de commande d'un etage d'aubes a calage variable

Publications (2)

Publication Number Publication Date
EP0765992A1 true EP0765992A1 (de) 1997-04-02
EP0765992B1 EP0765992B1 (de) 2001-08-29

Family

ID=9482943

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96402040A Expired - Lifetime EP0765992B1 (de) 1995-09-27 1996-09-26 Betätigungseinrichtung für verstellbare Statorschaufeln

Country Status (4)

Country Link
US (1) US5692879A (de)
EP (1) EP0765992B1 (de)
DE (1) DE69614794T2 (de)
FR (1) FR2739137B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1724472A2 (de) * 2005-05-17 2006-11-22 Snecma Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine
US8915703B2 (en) 2011-07-28 2014-12-23 United Technologies Corporation Internally actuated inlet guide vane for fan section
WO2021038161A1 (fr) * 2019-08-27 2021-03-04 Safran Aircraft Engines Guignol pour un dispositif de calage variable d'une turbomachine

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2856424B1 (fr) * 2003-06-20 2005-09-23 Snecma Moteurs Dispositif de calage variable de deux etages d'aubes fixes sur un turboreacteur
DE102007012119A1 (de) * 2007-03-13 2008-09-18 Rolls-Royce Deutschland Ltd & Co Kg Drosselgradabhängige Schaufelverstellung bei Strömungsarbeitsmaschinen
GB0907461D0 (en) * 2009-05-01 2009-06-10 Rolls Royce Plc Control mechanism
RU2474698C1 (ru) * 2011-10-28 2013-02-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Система управления ступенями поворотных лопаток статора компрессора высокого давления
US20140010637A1 (en) * 2012-07-05 2014-01-09 United Technologies Corporation Torque box and linkage design
US9885291B2 (en) * 2012-08-09 2018-02-06 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9879561B2 (en) * 2012-08-09 2018-01-30 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
DE102012021876A1 (de) 2012-11-07 2014-05-22 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelverstellvorrichtung einer Gasturbine
FR3033007B1 (fr) * 2015-02-19 2018-07-13 Safran Aircraft Engines Dispositif pour le reglage individuel d'une pluralite d'aubes radiales fixes a calage variable dans une turbomachine
US10519797B2 (en) 2016-06-27 2019-12-31 General Electric Company Turbine engine and stator vane pitch adjustment system therefor
US10704412B2 (en) * 2018-10-05 2020-07-07 Raytheon Technologies Corporation Bell crank and bar assembly
FR3107319B1 (fr) * 2020-02-19 2022-08-12 Safran Aircraft Engines Module de turbomachine equipe de systeme de changement de pas des pales d’aubes de stator
US11560810B1 (en) 2021-07-20 2023-01-24 Rolls-Royce North American Technologies Inc. Variable vane actuation system and method for gas turbine engine performance management
US11788429B2 (en) * 2021-08-25 2023-10-17 Rolls-Royce Corporation Variable tandem fan outlet guide vanes
US11802490B2 (en) * 2021-08-25 2023-10-31 Rolls-Royce Corporation Controllable variable fan outlet guide vanes
DE102021123772A1 (de) * 2021-09-14 2023-03-16 MTU Aero Engines AG Verstellanordnung für verstellschaufeln einer strömungsmaschine
DE102022103922A1 (de) 2022-02-18 2023-08-24 MTU Aero Engines AG Hebel zum verstellen einer verstellschaufel
US12000293B1 (en) 2022-12-30 2024-06-04 Rolls-Royce North American Technologies Inc. Systems and methods for multi-dimensional variable vane stage rigging utilizing coupling mechanisms
US11834966B1 (en) 2022-12-30 2023-12-05 Rolls-Royce North American Technologies Inc. Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable alignment mechanisms
US12000292B1 (en) 2022-12-30 2024-06-04 Rolls-Royce North American Technologies Inc. Systems and methods for multi-dimensional variable vane stage rigging
US11982193B1 (en) 2022-12-30 2024-05-14 Rolls-Royce North American Technologies Inc. Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable inclined mechanisms

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2999630A (en) * 1957-08-08 1961-09-12 Gen Electric Compressor
DE1601625A1 (de) * 1966-01-10 1970-08-06 Rolls Royce Schaufelbetaetigungsmechanismus,insbesondere fuer Leitradschaufeln in Gasturbinenstrahltriebwerken
US4295784A (en) * 1979-09-26 1981-10-20 United Technologies Corporation Variable stator
US4400135A (en) * 1981-04-06 1983-08-23 General Motors Corporation Vane actuation system
EP0094296A1 (de) * 1982-05-04 1983-11-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Einrichtung zur Regelung des Druckgefälles über mindestens eine Strömung einer Mehrströmungsturbine
GB2187237A (en) * 1986-02-28 1987-09-03 Mtu Muenchen Gmbh Independently adjustable vanes of a tandem guide vane array in a turbocompressor

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2227527B (en) * 1989-01-25 1993-06-09 Rolls Royce Plc A variable stator vane arrangement for an axial flow compressor
DE3913102C1 (de) * 1989-04-21 1990-05-31 Mtu Muenchen Gmbh
FR2681640B1 (fr) * 1991-09-25 1993-11-19 Snecma Turbomachine a aubes de stator a calage variable.
FR2708311B1 (fr) * 1993-07-28 1995-09-01 Snecma Stator de turbomachine à aubes pivotantes et anneau de commande.

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2999630A (en) * 1957-08-08 1961-09-12 Gen Electric Compressor
DE1601625A1 (de) * 1966-01-10 1970-08-06 Rolls Royce Schaufelbetaetigungsmechanismus,insbesondere fuer Leitradschaufeln in Gasturbinenstrahltriebwerken
US4295784A (en) * 1979-09-26 1981-10-20 United Technologies Corporation Variable stator
US4400135A (en) * 1981-04-06 1983-08-23 General Motors Corporation Vane actuation system
EP0094296A1 (de) * 1982-05-04 1983-11-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Einrichtung zur Regelung des Druckgefälles über mindestens eine Strömung einer Mehrströmungsturbine
GB2187237A (en) * 1986-02-28 1987-09-03 Mtu Muenchen Gmbh Independently adjustable vanes of a tandem guide vane array in a turbocompressor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1724472A2 (de) * 2005-05-17 2006-11-22 Snecma Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine
EP1724472A3 (de) * 2005-05-17 2009-01-21 Snecma Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine
US8915703B2 (en) 2011-07-28 2014-12-23 United Technologies Corporation Internally actuated inlet guide vane for fan section
WO2021038161A1 (fr) * 2019-08-27 2021-03-04 Safran Aircraft Engines Guignol pour un dispositif de calage variable d'une turbomachine
FR3100272A1 (fr) * 2019-08-27 2021-03-05 Safran Aircraft Engines Guignol pour un dispositif de calage variable d’une turbomachine
US12055051B2 (en) 2019-08-27 2024-08-06 Safran Aircraft Engines Bellcrank for a variable adjustment device for a turbomachine

Also Published As

Publication number Publication date
EP0765992B1 (de) 2001-08-29
DE69614794D1 (de) 2001-10-04
DE69614794T2 (de) 2002-05-23
US5692879A (en) 1997-12-02
FR2739137B1 (fr) 1997-10-31
FR2739137A1 (fr) 1997-03-28

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