EP1489267A1 - Verstelleinrichtung für zwei Leitschaufelstufen einer Turbomaschine - Google Patents

Verstelleinrichtung für zwei Leitschaufelstufen einer Turbomaschine Download PDF

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Publication number
EP1489267A1
EP1489267A1 EP04102806A EP04102806A EP1489267A1 EP 1489267 A1 EP1489267 A1 EP 1489267A1 EP 04102806 A EP04102806 A EP 04102806A EP 04102806 A EP04102806 A EP 04102806A EP 1489267 A1 EP1489267 A1 EP 1489267A1
Authority
EP
European Patent Office
Prior art keywords
groove
synchronization
stages
horn
rod
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
EP04102806A
Other languages
English (en)
French (fr)
Other versions
EP1489267B1 (de
Inventor
Florent Raine
Dominique Raulin
Alain Jean Charles Chatel
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 Moteurs SA
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 Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1489267A1 publication Critical patent/EP1489267A1/de
Application granted granted Critical
Publication of EP1489267B1 publication Critical patent/EP1489267B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes

Definitions

  • the invention relates to a device for variable setting of two stator stages on a turbojet.
  • the circular stages of blades mounted on the stator of turbojet engines are often calibrated variable, that is to say that the blades are capable of rotate around their axis to vary the flow correction features they impose on gases.
  • the adjustment device is mounted at outside the housing and includes a mechanism actuator as well as a transmission mechanism to paddle pivots.
  • a mechanism actuator as well as a transmission mechanism to paddle pivots.
  • the way actuator is connected to the ring through a transmission that may include a bar of synchronization from the cylinder rod, a connecting rod articulated to the ring and a puppet joining the bar of synchronization to the control rod of the ring and articulated to them.
  • the horns are pivoting parts around a central axis and equipped with two branches forming an angle, one of which is connected to the bar of synchronization and the other to the control rod.
  • the cylinder movement moves the synchronization bar, which turns the horn.
  • the movement is communicated to the connecting rod, which pulls or pushes on the ring synchronization and rotate it around the housing, by finally tipping the control levers of pivoting of the blades.
  • US 3,083,892 A discloses a device where the cylinder rod is connected to a cam it turns.
  • the cam carries a groove in which is engaged a pin of a rod used for the control of the synchronization ring. It is so possible to impose nonlinear control laws, sinusoidal for example, between the cylinder rod and the synchronization ring.
  • a single blade stage is controlled by the aforementioned means of the rotating cam and by a few others that have nothing to do with the invention.
  • the rotating cam is added only for obtain the nonlinear control law. She should probably have a large area to accommodate a groove allowing irregular control laws or large amplitude.
  • the different order of two blade stages by a single actuator means is not resolved by this patent.
  • the rotating cam looks like shape to a puppet, and the adaptation of a groove and a ergot y sliding in an existing puppet would disadvantageous for controlling several stages at a time, the increase in the area of the horns being problematic because of their proximity to the crankcase.
  • the important efforts to develop in the guignol discourage weakening it by a groove long.
  • the invention relates to a device allowing a calibration with nonlinear and different laws several stages of blades at a time by a device also different from that of the aforementioned prior art.
  • variable setting device of two stages of stator vanes, arranged on a housing and comprising an actuating mechanism and, for each of floors, a pivoting horn on an axle of the housing and a stage control rod connected to a branch of the horn, a synchronization bar being connected to another branch of at least one of the horns for driving it, characterized in that one of the bars synchronization is connected to the housing by a link with groove and sliding pin in the groove, and the horn that it leads by a link with groove and pin sliding in the groove.
  • a turbojet casing bears the reference 1; blades (only one of which is shown) 2 are mounted indoors on external pivots 3 passing through the housing 1 and on internal pivots not shown and united by a ring link ; each of the blades 2 is adjusted by the device that will now be described.
  • levers 4 mounted on the outer pivots 3, synchronization rings 5 each associated with a floor blades 2, extending next to them and to which the ends of the levers 4 are mounted so rotary, control rods 6 which are screw turnbuckles and which extend tangentially to rings 5, and as shown in Figure 2, horns 7 and 8 to which the ends of the rods 6 opposed to synchronization rings 5 are mounted rotatively, a synchronization bar 9 and a cylinder 10 having a rod 11 actuating one of the horns 7 and whose body is mounted on a casing 12 of the casing 1, pivotally about a pin 13.
  • the synchronization bar 9 unites two branches 15 and 16 horns 7 and 8 being hinged thereto, said branches 15 and 16 being opposed to branches 17 and 18 to which the connecting rods 6 are articulated; the guignol 7 still includes a branch 19 to which the rod 11 is hinged to control the movement of the whole mechanism.
  • the horns 7 and 8 are rotatably mounted on the housing 12, around axes 20 and 21 parallel to each other.
  • the movements of the rod 11 cause a rotation of the horn 7, and another of the horn 8 by the synchronization bar 9; the rotations of the horns 7 and 8 move in turn the rods 6, the rings 5, the levers 4 and the blades 2 by rotating them of the desired quantity, the control law depending in particular lengths and angles of the branches 15, 16, 17 and 18.
  • the bar of synchronization 9 is lined with a pin 22 which penetrates in a groove 23 dug in the housing 12. From more, a second groove 26 is operated in the second guignol 8 to receive a lug 27 at the end of the synchronization bar 9.
  • the direction of the synchronization bar 9 is imposed on all deployment positions of the rod 11 of the cylinder 10 by the groove 23.
  • the angles of rotation of horns 7 and 8 vary in values different.
  • the groove 23 has a shape and a direction determined to give the desired control law for the blade stage associated with the second horn. is important to note that thanks to the length of lever provided by the synchronization bar 9, of small gaps in the groove 23 can produce large angle variations of the second hornet 8.
  • the second groove 26 has the function of restoring isostaticity of the mechanism while contributing to define the control law. A second groove 26 short, not extending the second horn 8, will be often enough.
  • Figures 3a, 3b and 3c illustrate a situation where the end pin 27 of the bar synchronization 9 is close to the same end of the second groove 26 at the extreme positions of the rod 11 of the cylinder 10 (in Figures 3a 3c), while it is close of the opposite end of the second groove 26 for a average deployment of the rod 11 ( Figure 3b).
  • the control law generally depends on a many factors, mainly directions and shapes of the grooves 23 and 26 and their positions with respect to horns 7 and 8. In the example considered here, we can distinguish two stages of the movement.
  • the first groove 23 is first roughly parallel to the path of the point of articulation of the synchronization bar 9 to first horn 7, so that the bar of synchronization 9 lowers without much change inclination; but the direction of the second groove induces a greater rotation of the second horn 8 than that of the first horn 7 as the pin 27 moves in the second groove 26.
  • the invention could be implemented in other situations, and especially to order a greater number of blade stages. She would be then implemented in a number of bars synchronization. These synchronization bars could, according to existing arrangements, be to be successive, that is to say to connect the horns neighbors and extend in a chain, ie be parallel and extend to a common puppet or even up to the actuator element itself. This is without consequence for the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04102806A 2003-06-20 2004-06-18 Verstelleinrichtung für zwei Leitschaufelstufen einer Turbomaschine Expired - Lifetime EP1489267B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0350237 2003-06-20
FR0350237A FR2856424B1 (fr) 2003-06-20 2003-06-20 Dispositif de calage variable de deux etages d'aubes fixes sur un turboreacteur

Publications (2)

Publication Number Publication Date
EP1489267A1 true EP1489267A1 (de) 2004-12-22
EP1489267B1 EP1489267B1 (de) 2006-12-20

Family

ID=33396882

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04102806A Expired - Lifetime EP1489267B1 (de) 2003-06-20 2004-06-18 Verstelleinrichtung für zwei Leitschaufelstufen einer Turbomaschine

Country Status (7)

Country Link
US (1) US7037070B2 (de)
EP (1) EP1489267B1 (de)
JP (1) JP4050252B2 (de)
CA (1) CA2470081C (de)
DE (1) DE602004003744T2 (de)
FR (1) FR2856424B1 (de)
RU (1) RU2338932C2 (de)

Cited By (9)

* 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
EP1808579A2 (de) * 2006-01-17 2007-07-18 General Electric Company Betätigungssystem für verstellbare Leitschaufeln
WO2010031768A2 (en) * 2008-09-18 2010-03-25 Siemens Aktiengesellschaft Method, system, device for variable guide vanes
FR2982653A1 (fr) * 2011-11-14 2013-05-17 Snecma Systeme de transmission a arbre cannele.
EP2258926A3 (de) * 2009-05-01 2015-01-14 Rolls-Royce plc Steuerungsmechanismus
WO2016034816A1 (fr) * 2014-09-05 2016-03-10 Snecma Mécanisme d'entraînement d'organes de réglage de l'orientation des pales
WO2016207513A1 (fr) 2015-06-25 2016-12-29 Safran Aircraft Engines Système de commande d'aubes à calage variable pour une turbomachine
WO2017203158A1 (fr) 2016-05-25 2017-11-30 Safran Aircraft Engines Dispositif de commande d'elements a calage variable dans une turbomachine
FR3133214A1 (fr) 2022-03-03 2023-09-08 Safran Aircraft Engines Systeme ameliore de commande d’aubes de redresseurs d’un compresseur pour turbomachine d’aeronef

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2885968B1 (fr) * 2005-05-17 2007-08-10 Snecma Moteurs Sa Systeme de commande d'etages d'aubes de stator a angle de calage variable de turbomachine
DE102007011990B4 (de) * 2007-03-09 2019-01-10 Tlt-Turbo Gmbh Vorrichtung zum hydraulischen Verstellen der Laufschaufeln eines Laufrades eines Axialventilators
US8727697B2 (en) * 2010-03-27 2014-05-20 Rolls-Royce Corporation Variable vane actuation system and method
RU2465465C2 (ru) * 2010-08-05 2012-10-27 Закрытое акционерное общество "Уральский турбинный завод" Механизм поворота направляющих лопаток
IT1401664B1 (it) * 2010-08-31 2013-08-02 Nuova Pignone S R L Dispositivo di centraggio e sistema per anello di guida.
US9039355B2 (en) 2012-05-31 2015-05-26 United Technologies Corporation Actuator mounted to torque box
US20140010637A1 (en) * 2012-07-05 2014-01-09 United Technologies Corporation Torque box and linkage design
US20140205424A1 (en) * 2012-08-29 2014-07-24 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US20140064911A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
DE102012021876A1 (de) 2012-11-07 2014-05-22 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelverstellvorrichtung einer Gasturbine
US10161407B2 (en) 2013-06-14 2018-12-25 United Technologies Corporation Radial fastening of tubular synchronizing rings
KR101549470B1 (ko) * 2014-01-29 2015-09-03 국방과학연구소 가변 입구 안내익과 가변 정익의 구동장치
FR3031772B1 (fr) * 2015-01-19 2017-01-13 Snecma Systeme de commande d’aubes a calage variable pour une turbomachine
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
US9885314B2 (en) * 2015-03-02 2018-02-06 The Boeing Company Dual-cam bellcrank mechanism
DE102015004649A1 (de) 2015-04-15 2016-10-20 Man Diesel & Turbo Se Leitschaufelverstellvorrichtung und Strömungsmaschine
US10415596B2 (en) * 2016-03-24 2019-09-17 United Technologies Corporation Electric actuation for variable vanes
US10502091B2 (en) 2016-12-12 2019-12-10 United Technologies Corporation Sync ring assembly and associated clevis including a rib
US10815818B2 (en) * 2017-07-18 2020-10-27 Raytheon Technologies Corporation Variable-pitch vane assembly
GB201717091D0 (en) * 2017-10-18 2017-11-29 Rolls Royce Plc A variable vane actuation arrangement
FR3076325B1 (fr) * 2017-12-29 2019-11-29 Safran Aircraft Engines Dispositif de calage variable d'au moins deux rangees annulaires d'aubes fixes pour une turbomachine
US10662804B2 (en) * 2018-02-28 2020-05-26 United Technologies Corporation Profiled bellcrank vane actuation system
DE102018217435B4 (de) * 2018-10-11 2021-04-01 Rolls-Royce Deutschland Ltd & Co Kg Verstelleinrichtung mit wenigstens einer Führungseinrichtung für die Verstellung mehrerer Leitschaufeln eines Triebwerks
FR3100273B1 (fr) 2019-08-27 2021-10-15 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
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
FR3121952B1 (fr) 2021-04-20 2023-04-28 Safran Aircraft Engines Systeme a guignol pour un dispositif de calage variable d’une turbomachine
US20220341342A1 (en) * 2021-04-21 2022-10-27 General Electric Company Variable vane apparatus
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
DE102021123772A1 (de) * 2021-09-14 2023-03-16 MTU Aero Engines AG Verstellanordnung für verstellschaufeln einer strömungsmaschine

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US3066488A (en) * 1959-11-04 1962-12-04 Bendix Corp Power output control for a gas turbine engine
US4403912A (en) * 1981-03-23 1983-09-13 Avco Corporation Integrated multiplane actuator system for compressor variable vanes and air bleed valve
US5044879A (en) * 1989-01-25 1991-09-03 Rolls-Royce Plc Variable stator vane arrangement for an axial flow compressor

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US3873230A (en) * 1974-04-10 1975-03-25 United Aircraft Corp Stator vane actuating mechanism
US5190439A (en) * 1991-07-15 1993-03-02 United Technologies Corporation Variable vane non-linear schedule for a gas turbine engine
FR2739137B1 (fr) * 1995-09-27 1997-10-31 Snecma Dispositif de commande d'un etage d'aubes a calage variable
US6092984A (en) * 1998-12-18 2000-07-25 General Electric Company System life for continuously operating engines

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Publication number Priority date Publication date Assignee Title
US2924375A (en) * 1955-05-18 1960-02-09 Gen Electric Positioning device
US3066488A (en) * 1959-11-04 1962-12-04 Bendix Corp Power output control for a gas turbine engine
US4403912A (en) * 1981-03-23 1983-09-13 Avco Corporation Integrated multiplane actuator system for compressor variable vanes and air bleed valve
US5044879A (en) * 1989-01-25 1991-09-03 Rolls-Royce Plc Variable stator vane arrangement for an axial flow compressor

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2885969A1 (fr) * 2005-05-17 2006-11-24 Snecma Moteurs Sa Systeme de commande d'etages d'aubes de stator a angle de calage variable de turbomachine
US7322790B2 (en) 2005-05-17 2008-01-29 Snecma System for controlling stages of variable-pitch stator vanes in a turbomachine
EP1724472A3 (de) * 2005-05-17 2009-01-21 Snecma Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine
EP1724472A2 (de) * 2005-05-17 2006-11-22 Snecma Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine
EP1808579A3 (de) * 2006-01-17 2013-11-20 General Electric Company Betätigungssystem für verstellbare Leitschaufeln
EP1808579A2 (de) * 2006-01-17 2007-07-18 General Electric Company Betätigungssystem für verstellbare Leitschaufeln
US9890655B2 (en) 2008-09-18 2018-02-13 Siemens Aktiengesellschaft Adjusting device for variable guide vanes and method of operation
WO2010031768A2 (en) * 2008-09-18 2010-03-25 Siemens Aktiengesellschaft Method, system, device for variable guide vanes
WO2010031768A3 (en) * 2008-09-18 2011-02-10 Siemens Aktiengesellschaft Adjusting device for variable guide vanes and method of operation
RU2509897C2 (ru) * 2008-09-18 2014-03-20 Сименс Акциенгезелльшафт Регулировочное устройство направляющих лопаток осевого компрессора, система поворотных направляющих лопаток осевого компрессора и способ регулирования направляющих лопаток осевого компрессора
CN102159794A (zh) * 2008-09-18 2011-08-17 西门子公司 用于可变导向叶片的方法、系统和装置
EP2258926A3 (de) * 2009-05-01 2015-01-14 Rolls-Royce plc Steuerungsmechanismus
FR2982653A1 (fr) * 2011-11-14 2013-05-17 Snecma Systeme de transmission a arbre cannele.
US10502088B2 (en) 2014-09-05 2019-12-10 Safran Aircraft Engines Mechanism for driving members for adjusting the orientation of blades
RU2705529C2 (ru) * 2014-09-05 2019-11-07 Сафран Эркрафт Энджинз Приводной механизм и турбомашина летательного аппарата, содержащая такой механизм
FR3025577A1 (fr) * 2014-09-05 2016-03-11 Snecma Mecanisme d'entrainement d'organes de reglage de l'orientation des pales
WO2016034816A1 (fr) * 2014-09-05 2016-03-10 Snecma Mécanisme d'entraînement d'organes de réglage de l'orientation des pales
FR3038018A1 (fr) * 2015-06-25 2016-12-30 Snecma Systeme de commande d'aubes a calage variable pour une turbomachine
US10648359B2 (en) 2015-06-25 2020-05-12 Safran Aircraft Engines System for controlling variable-setting blades for a turbine engine
WO2016207513A1 (fr) 2015-06-25 2016-12-29 Safran Aircraft Engines Système de commande d'aubes à calage variable pour une turbomachine
CN107771250A (zh) * 2015-06-25 2018-03-06 赛峰飞机发动机公司 用于涡轮发动机的用于控制可调设置叶片的系统
FR3051826A1 (fr) * 2016-05-25 2017-12-01 Snecma Dispositif de commande d'elements a calage variable dans une turbomachine
GB2565699A (en) * 2016-05-25 2019-02-20 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
WO2017203158A1 (fr) 2016-05-25 2017-11-30 Safran Aircraft Engines Dispositif de commande d'elements a calage variable dans une turbomachine
US10837308B2 (en) 2016-05-25 2020-11-17 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
GB2565699B (en) * 2016-05-25 2021-09-01 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
FR3133214A1 (fr) 2022-03-03 2023-09-08 Safran Aircraft Engines Systeme ameliore de commande d’aubes de redresseurs d’un compresseur pour turbomachine d’aeronef

Also Published As

Publication number Publication date
RU2338932C2 (ru) 2008-11-20
FR2856424B1 (fr) 2005-09-23
US7037070B2 (en) 2006-05-02
JP2005009497A (ja) 2005-01-13
CA2470081A1 (fr) 2004-12-20
DE602004003744D1 (de) 2007-02-01
JP4050252B2 (ja) 2008-02-20
US20050129510A1 (en) 2005-06-16
RU2004118678A (ru) 2006-01-10
CA2470081C (fr) 2011-08-02
EP1489267B1 (de) 2006-12-20
FR2856424A1 (fr) 2004-12-24
DE602004003744T2 (de) 2007-10-11

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