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 PDFInfo
- 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
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
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)
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 |
-
2020
- 2020-10-08 FR FR2010286A patent/FR3115018B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3115018A1 (en) | 2022-04-15 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20220415 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
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PLFP | Fee payment |
Year of fee payment: 4 |