FR3040069B1 - Procede de detection d'une augmentation du regime d'une turbine basse pression d'un reacteur d'un aeronef au cours d'une phase de croisiere et dispositif et procede de regulation du debit d'air de refroidissement d'une turbine basse pression associes - Google Patents

Procede de detection d'une augmentation du regime d'une turbine basse pression d'un reacteur d'un aeronef au cours d'une phase de croisiere et dispositif et procede de regulation du debit d'air de refroidissement d'une turbine basse pression associes

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Publication number
FR3040069B1
FR3040069B1 FR1557671A FR1557671A FR3040069B1 FR 3040069 B1 FR3040069 B1 FR 3040069B1 FR 1557671 A FR1557671 A FR 1557671A FR 1557671 A FR1557671 A FR 1557671A FR 3040069 B1 FR3040069 B1 FR 3040069B1
Authority
FR
France
Prior art keywords
low pressure
pressure turbine
regimen
reactor
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
FR1557671A
Other languages
English (en)
Other versions
FR3040069A1 (fr
Inventor
Alexandre Patrick Jacques Roger Everwyn
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
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1557671A priority Critical patent/FR3040069B1/fr
Priority to US15/232,975 priority patent/US10339729B2/en
Publication of FR3040069A1 publication Critical patent/FR3040069A1/fr
Application granted granted Critical
Publication of FR3040069B1 publication Critical patent/FR3040069B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
    • G07C5/0816—Indicating performance data, e.g. occurrence of a malfunction
    • 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
    • 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
    • F01D17/145—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 by means of valves, e.g. for steam turbines
    • G—PHYSICS
    • G08—SIGNALLING
    • G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
    • G08B21/00—Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for
    • G08B21/18—Status alarms
    • G08B21/182—Level alarms, e.g. alarms responsive to variables exceeding a threshold
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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
FR1557671A 2015-08-11 2015-08-11 Procede de detection d'une augmentation du regime d'une turbine basse pression d'un reacteur d'un aeronef au cours d'une phase de croisiere et dispositif et procede de regulation du debit d'air de refroidissement d'une turbine basse pression associes Active FR3040069B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1557671A FR3040069B1 (fr) 2015-08-11 2015-08-11 Procede de detection d'une augmentation du regime d'une turbine basse pression d'un reacteur d'un aeronef au cours d'une phase de croisiere et dispositif et procede de regulation du debit d'air de refroidissement d'une turbine basse pression associes
US15/232,975 US10339729B2 (en) 2015-08-11 2016-08-10 Method for detecting an increase in the rating of a low-pressure turbine of an aircraft reactor during a cruising flight phase, and associated device and method for regulating the cooling air flow rate of a low-pressure turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1557671A FR3040069B1 (fr) 2015-08-11 2015-08-11 Procede de detection d'une augmentation du regime d'une turbine basse pression d'un reacteur d'un aeronef au cours d'une phase de croisiere et dispositif et procede de regulation du debit d'air de refroidissement d'une turbine basse pression associes

Publications (2)

Publication Number Publication Date
FR3040069A1 FR3040069A1 (fr) 2017-02-17
FR3040069B1 true FR3040069B1 (fr) 2017-09-01

Family

ID=54186204

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1557671A Active FR3040069B1 (fr) 2015-08-11 2015-08-11 Procede de detection d'une augmentation du regime d'une turbine basse pression d'un reacteur d'un aeronef au cours d'une phase de croisiere et dispositif et procede de regulation du debit d'air de refroidissement d'une turbine basse pression associes

Country Status (2)

Country Link
US (1) US10339729B2 (fr)
FR (1) FR3040069B1 (fr)

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 (fr) * 2012-10-31 2015-05-15 Snecma Unite de commande et procede de pilotage de jeu en sommet d'aubes

Also Published As

Publication number Publication date
US20170046886A1 (en) 2017-02-16
FR3040069A1 (fr) 2017-02-17
US10339729B2 (en) 2019-07-02

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