FR2936561B1 - Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came - Google Patents

Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came Download PDF

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Publication number
FR2936561B1
FR2936561B1 FR0856589A FR0856589A FR2936561B1 FR 2936561 B1 FR2936561 B1 FR 2936561B1 FR 0856589 A FR0856589 A FR 0856589A FR 0856589 A FR0856589 A FR 0856589A FR 2936561 B1 FR2936561 B1 FR 2936561B1
Authority
FR
France
Prior art keywords
controlling
gas turbine
turbine engine
cam mechanism
variable geometry
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
FR0856589A
Other languages
English (en)
Other versions
FR2936561A1 (fr
Inventor
Baptiste Benoit COLOTTE
Bruno Robert Gaully
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
Safran Aircraft Engines SAS
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 Safran Aircraft Engines SAS, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR0856589A priority Critical patent/FR2936561B1/fr
Priority to US12/566,325 priority patent/US8333546B2/en
Publication of FR2936561A1 publication Critical patent/FR2936561A1/fr
Application granted granted Critical
Publication of FR2936561B1 publication Critical patent/FR2936561B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D17/20—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F02C9/22—Control of working fluid flow by throttling; by adjusting vanes by adjusting turbine vanes
    • 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
    • F05D2270/00—Control
    • F05D2270/50—Control logic embodiments
    • F05D2270/58—Control logic embodiments by mechanical means, e.g. levers, gears or cams
FR0856589A 2008-09-30 2008-09-30 Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came Active FR2936561B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR0856589A FR2936561B1 (fr) 2008-09-30 2008-09-30 Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came
US12/566,325 US8333546B2 (en) 2008-09-30 2009-09-24 System for controlling at least two variable-geometry equipments of a gas turbine engine, particularly by cam mechanism

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0856589 2008-09-30
FR0856589A FR2936561B1 (fr) 2008-09-30 2008-09-30 Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came

Publications (2)

Publication Number Publication Date
FR2936561A1 FR2936561A1 (fr) 2010-04-02
FR2936561B1 true FR2936561B1 (fr) 2018-10-26

Family

ID=40565621

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0856589A Active FR2936561B1 (fr) 2008-09-30 2008-09-30 Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came

Country Status (2)

Country Link
US (1) US8333546B2 (fr)
FR (1) FR2936561B1 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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.
FR2936559B1 (fr) * 2008-09-30 2013-11-22 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine faisant partie de corps differents.
FR2936558B1 (fr) * 2008-09-30 2016-11-11 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet.
FR2936556B1 (fr) * 2008-09-30 2015-07-24 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine, notamment par guignols.
FR2947310B1 (fr) 2009-06-26 2014-08-29 Snecma Dispositif et methode de positionnement d'un equipement a geometrie variable pour une turbomachine, utilisant un verin a mesure relative.
US8011114B2 (en) * 2009-12-04 2011-09-06 Superior Investments, Inc. Vehicle dryer with butterfly inlet valve
US9039355B2 (en) 2012-05-31 2015-05-26 United Technologies Corporation Actuator mounted to torque box
US9103283B2 (en) 2012-06-20 2015-08-11 United Technologies Corporation Spherical-link end damper system with near constant engagement
US9518513B2 (en) * 2012-10-12 2016-12-13 General Electric Company Gas turbine engine two degree of freedom variable bleed valve for ice extraction
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
US11168583B2 (en) * 2016-07-22 2021-11-09 General Electric Company Systems and methods for cooling components within a gas turbine engine
EP3502485A1 (fr) * 2017-12-19 2019-06-26 Siemens Aktiengesellschaft Liaison de réglage
EP3502484A1 (fr) * 2017-12-19 2019-06-26 Siemens Aktiengesellschaft Liaison de réglage
US10662804B2 (en) * 2018-02-28 2020-05-26 United Technologies Corporation Profiled bellcrank vane actuation system
FR3108933B1 (fr) 2020-04-02 2022-03-11 Safran Aircraft Engines Dispositif de dégivrage d’un toboggan de carter
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
US11686211B2 (en) 2021-08-25 2023-06-27 Rolls-Royce Corporation Variable outlet guide vanes
US11879343B2 (en) 2021-08-25 2024-01-23 Rolls-Royce Corporation Systems for controlling variable outlet guide vanes
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

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4292802A (en) * 1978-12-27 1981-10-06 General Electric Company Method and apparatus for increasing compressor inlet pressure
US4569199A (en) * 1982-09-29 1986-02-11 The Boeing Company Turboprop engine and method of operating the same
US4461145A (en) * 1982-10-08 1984-07-24 The United States Of America As Represented By The Secretary Of The Air Force Stall elimination and restart enhancement device
US4992946A (en) * 1988-06-20 1991-02-12 General Electric Company Data link for gas turbine engine control
US5259187A (en) * 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes
US6742324B2 (en) * 2002-09-13 2004-06-01 General Electric Company Methods and apparatus for supporting variable bypass valve systems
GB0314123D0 (en) * 2003-06-18 2003-07-23 Rolls Royce Plc A gas turbine engine
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
GB2473578B (en) * 2006-01-20 2011-08-03 Rolls Royce Power Eng Gas turbine engine system
EP2019914A4 (fr) * 2006-05-04 2013-08-14 Volvo Aero Corp Dispositif permettant de faire pivoter au moins un élément pivotant dans une turbine à gaz

Also Published As

Publication number Publication date
US20100158663A1 (en) 2010-06-24
US8333546B2 (en) 2012-12-18
FR2936561A1 (fr) 2010-04-02

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