FR3107318B1 - Turbomachine d’aéronef à double flux équipée d’un dispositif d’arrêt en survitesse du rotor - Google Patents

Turbomachine d’aéronef à double flux équipée d’un dispositif d’arrêt en survitesse du rotor Download PDF

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Publication number
FR3107318B1
FR3107318B1 FR2001545A FR2001545A FR3107318B1 FR 3107318 B1 FR3107318 B1 FR 3107318B1 FR 2001545 A FR2001545 A FR 2001545A FR 2001545 A FR2001545 A FR 2001545A FR 3107318 B1 FR3107318 B1 FR 3107318B1
Authority
FR
France
Prior art keywords
dual
shutdown device
aircraft turbomachine
openings
rotor overspeed
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
FR2001545A
Other languages
English (en)
Other versions
FR3107318A1 (fr
Inventor
Quentin Bruno Guy André Emile Lievoux
Pragash Douglas
Bruno Marc-Etienne Loisel
Vijeay Patel
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
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 filed Critical Safran Aircraft Engines SAS
Priority to FR2001545A priority Critical patent/FR3107318B1/fr
Publication of FR3107318A1 publication Critical patent/FR3107318A1/fr
Application granted granted Critical
Publication of FR3107318B1 publication Critical patent/FR3107318B1/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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • 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
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • 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
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)

Abstract

Le dispositif comprend un obturateur (20) tel qu’une grille mobile (21) devant des ouvertures (24) d’un carter (10) extérieur à une veine primaire (11) pour obturer ces ouvertures (24) ou au contraire les exposer à une pression extérieure réduite. Des clapets (22) équipant la face extérieure des supports (14) des anneaux d’étanchéité (13) s’ouvrent alors aussi, grâce au différentiel de pression. L’évacuation du gaz hors de la veine primaire (11) évite alors une survitesse et force éventuellement l’extinction du moteur. Le dispositif évite tout dommage au rotor par une collision entre pièces fixes et mobiles, sa commande et ses effets peuvent être très rapides, et il n’impose pas de perturber l’agencement de la turbine. Figure pour l’abrégé : Figure 2.
FR2001545A 2020-02-17 2020-02-17 Turbomachine d’aéronef à double flux équipée d’un dispositif d’arrêt en survitesse du rotor Active FR3107318B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2001545A FR3107318B1 (fr) 2020-02-17 2020-02-17 Turbomachine d’aéronef à double flux équipée d’un dispositif d’arrêt en survitesse du rotor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2001545 2020-02-17
FR2001545A FR3107318B1 (fr) 2020-02-17 2020-02-17 Turbomachine d’aéronef à double flux équipée d’un dispositif d’arrêt en survitesse du rotor

Publications (2)

Publication Number Publication Date
FR3107318A1 FR3107318A1 (fr) 2021-08-20
FR3107318B1 true FR3107318B1 (fr) 2022-01-14

Family

ID=70295430

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2001545A Active FR3107318B1 (fr) 2020-02-17 2020-02-17 Turbomachine d’aéronef à double flux équipée d’un dispositif d’arrêt en survitesse du rotor

Country Status (1)

Country Link
FR (1) FR3107318B1 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3940248A1 (de) * 1989-04-17 1990-10-18 Gen Electric Verfahren und einrichtung zum regeln eines gasturbinentriebwerkes
CA2472604A1 (fr) * 2002-01-09 2003-07-24 The Nordam Group, Inc. Tuyere a noyau central a surface variable
FR2916483B1 (fr) 2007-05-25 2013-03-01 Snecma Systeme de dissipation d'energie en cas de rupture d'arbre de turbine dans un moteur a turbine a gaz
DE102008024022A1 (de) 2008-05-16 2009-11-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinentriebwerk, insbesondere Flugtriebwerk
FR3021692B1 (fr) 2014-05-27 2016-05-13 Snecma Platine d'etancheite a fonction de fusible

Also Published As

Publication number Publication date
FR3107318A1 (fr) 2021-08-20

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