FR3115018B1 - Method for checking the operability of a mechanical part of a turbojet engine for aircraft - Google Patents

Method for checking the operability of a mechanical part of a turbojet engine for aircraft Download PDF

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Publication number
FR3115018B1
FR3115018B1 FR2010286A FR2010286A FR3115018B1 FR 3115018 B1 FR3115018 B1 FR 3115018B1 FR 2010286 A FR2010286 A FR 2010286A FR 2010286 A FR2010286 A FR 2010286A FR 3115018 B1 FR3115018 B1 FR 3115018B1
Authority
FR
France
Prior art keywords
mechanical part
configuration
operability
aircraft
checking
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
FR2010286A
Other languages
French (fr)
Other versions
FR3115018A1 (en
Inventor
Christian Haddad
Corre Yannis Le
Augustin Haas
Gautier Irénée Alexis Grayel
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 FR2010286A priority Critical patent/FR3115018B1/en
Publication of FR3115018A1 publication Critical patent/FR3115018A1/en
Application granted granted Critical
Publication of FR3115018B1 publication Critical patent/FR3115018B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/72—Maintenance
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2260/81—Modelling or simulation

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)

Abstract

Ce procédé de contrôle de l’opérationnalité d’une pièce mécanique d’un turboréacteur pour aéronef, suite à un passage de la pièce mécanique d’une première configuration à une deuxième configuration, comprend les étapes suivantes : - une étape de génération automatisée d’une première pluralité de données relatives à la première configuration et d’une deuxième pluralité de données relatives à la deuxième configuration (E1) ; - une étape de comparaison entre la première pluralité de données et la deuxième pluralité de données (E2) ; - une étape d’identification des modifications de la pièce mécanique mises en œuvre pour passer de la première configuration à la deuxième configuration (E2) et, lorsque les modifications sont aptes à altérer l’opérationnalité de la pièce mécanique, une correction de la deuxième configuration (E6). Figure pour l’abrégé : Fig 2This method for checking the operability of a mechanical part of a turbojet engine for aircraft, following a passage of the mechanical part from a first configuration to a second configuration, comprises the following steps: - an automated generation step of a first plurality of data relating to the first configuration and a second plurality of data relating to the second configuration (E1); - a step of comparing the first plurality of data and the second plurality of data (E2); - a step of identifying the modifications of the mechanical part implemented to pass from the first configuration to the second configuration (E2) and, when the modifications are capable of altering the operationality of the mechanical part, a correction of the second setup (E6). Figure for abstract: Fig 2

FR2010286A 2020-10-08 2020-10-08 Method for checking the operability of a mechanical part of a turbojet engine for aircraft Active FR3115018B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2010286A FR3115018B1 (en) 2020-10-08 2020-10-08 Method for checking the operability of a mechanical part of a turbojet engine for aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2010286 2020-10-08
FR2010286A FR3115018B1 (en) 2020-10-08 2020-10-08 Method for checking the operability of a mechanical part of a turbojet engine for aircraft

Publications (2)

Publication Number Publication Date
FR3115018A1 FR3115018A1 (en) 2022-04-15
FR3115018B1 true FR3115018B1 (en) 2023-04-07

Family

ID=74045727

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2010286A Active FR3115018B1 (en) 2020-10-08 2020-10-08 Method for checking the operability of a mechanical part of a turbojet engine for aircraft

Country Status (1)

Country Link
FR (1) FR3115018B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020188494A1 (en) * 2002-05-24 2002-12-12 United Technologies Corporation Method and apparatus for managing an operation
US20090178278A1 (en) * 2008-01-16 2009-07-16 Quinn Daniel E Method of reverse engineering
FR2957164B1 (en) * 2010-03-03 2012-05-11 Airbus Operations Sas METHODS AND DEVICES FOR CONFIDURING VALIDATION OF A COMPLEX MULTICLEUM SYSTEM
US20200317370A1 (en) * 2019-04-05 2020-10-08 United Technologies Corporation Aircraft component repair system and process

Also Published As

Publication number Publication date
FR3115018A1 (en) 2022-04-15

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