FR3040070B1 - METHOD FOR DETECTING AN ASCENSIONAL THRUST CONTROL OF AN AIRCRAFT AND APPARATUS AND METHOD FOR CONTROLLING COOLING AIR FLOW RATE OF A RELATIVE LOW PRESSURE TURBINE - Google Patents

METHOD FOR DETECTING AN ASCENSIONAL THRUST CONTROL OF AN AIRCRAFT AND APPARATUS AND METHOD FOR CONTROLLING COOLING AIR FLOW RATE OF A RELATIVE LOW PRESSURE TURBINE Download PDF

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Publication number
FR3040070B1
FR3040070B1 FR1557672A FR1557672A FR3040070B1 FR 3040070 B1 FR3040070 B1 FR 3040070B1 FR 1557672 A FR1557672 A FR 1557672A FR 1557672 A FR1557672 A FR 1557672A FR 3040070 B1 FR3040070 B1 FR 3040070B1
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FR
France
Prior art keywords
thrust control
aircraft
detecting
ascensional
flow rate
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
FR1557672A
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French (fr)
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FR3040070A1 (en
Inventor
Patrick Jacques Roger Everwyn Alexandre
Arnaud Rodhain
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
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Application filed by Safran Aircraft Engines SAS, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1557672A priority Critical patent/FR3040070B1/en
Publication of FR3040070A1 publication Critical patent/FR3040070A1/en
Application granted granted Critical
Publication of FR3040070B1 publication Critical patent/FR3040070B1/en
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics
    • 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
    • F05D2260/00—Function
    • F05D2260/82—Forecasts
    • F05D2260/821—Parameter estimation or prediction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)

Abstract

Un procédé de détection d'une requête de passage en phase de commande de poussée ascensionnelle d'un aéronef, comprenant : a) une réception (100) d'un signal de commande de poussée correspondant à la position angulaire de la manette de commande de poussée, b) une comparaison (110) dudit signal de commande de poussée à une première position angulaire de référence de la manette de commande de poussée, c) une émission (120) d'un signal d'activation d'une phase de commande de décollage de l'aéronef si la valeur de la position angulaire du signal de commande de poussée est supérieure ou égale à ladite première position angulaire de référence (αref1), et d) une détection (125) d'une première commande de poussée ascensionnelle à la suite d'une réception d'un signal d'activation d'une phase de commande de décollage.A method of detecting a request for passage of an ascending thrust control phase of an aircraft, comprising: a) receiving (100) a thrust control signal corresponding to the angular position of the throttle control lever; thrust, b) a comparison (110) of said thrust control signal at a first reference angular position of the thrust control lever, c) a transmission (120) of an activation signal of a control phase take off of the aircraft if the value of the angular position of the thrust control signal is greater than or equal to said first reference angular position (αref1), and d) a detection (125) of a first thrust control following receipt of an activation signal of a take-off control phase.

FR1557672A 2015-08-11 2015-08-11 METHOD FOR DETECTING AN ASCENSIONAL THRUST CONTROL OF AN AIRCRAFT AND APPARATUS AND METHOD FOR CONTROLLING COOLING AIR FLOW RATE OF A RELATIVE LOW PRESSURE TURBINE Active FR3040070B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1557672A FR3040070B1 (en) 2015-08-11 2015-08-11 METHOD FOR DETECTING AN ASCENSIONAL THRUST CONTROL OF AN AIRCRAFT AND APPARATUS AND METHOD FOR CONTROLLING COOLING AIR FLOW RATE OF A RELATIVE LOW PRESSURE TURBINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1557672 2015-08-11
FR1557672A FR3040070B1 (en) 2015-08-11 2015-08-11 METHOD FOR DETECTING AN ASCENSIONAL THRUST CONTROL OF AN AIRCRAFT AND APPARATUS AND METHOD FOR CONTROLLING COOLING AIR FLOW RATE OF A RELATIVE LOW PRESSURE TURBINE

Publications (2)

Publication Number Publication Date
FR3040070A1 FR3040070A1 (en) 2017-02-17
FR3040070B1 true FR3040070B1 (en) 2019-05-10

Family

ID=54207581

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1557672A Active FR3040070B1 (en) 2015-08-11 2015-08-11 METHOD FOR DETECTING AN ASCENSIONAL THRUST CONTROL OF AN AIRCRAFT AND APPARATUS AND METHOD FOR CONTROLLING COOLING AIR FLOW RATE OF A RELATIVE LOW PRESSURE TURBINE

Country Status (1)

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FR (1) FR3040070B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2104966B (en) * 1981-06-26 1984-08-01 United Technologies Corp Closed loop control for tip clearance of a gas turbine engine
US8186945B2 (en) * 2009-05-26 2012-05-29 General Electric Company System and method for clearance control
US20140058644A1 (en) * 2012-08-23 2014-02-27 General Electric Company Method, system, and apparatus for reducing a turbine clearance
FR2997443B1 (en) * 2012-10-31 2015-05-15 Snecma CONTROL UNIT AND METHOD FOR CONTROLLING THE AUBES TOP SET

Also Published As

Publication number Publication date
FR3040070A1 (en) 2017-02-17

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