FR3120604B1 - ASSEMBLY COMPRISING A MECHANICAL PART OF AN AIRCRAFT TURBOMACHINE AND A MONITORING DEVICE FOR THE AIRCRAFT TURBOMACHINE - Google Patents

ASSEMBLY COMPRISING A MECHANICAL PART OF AN AIRCRAFT TURBOMACHINE AND A MONITORING DEVICE FOR THE AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3120604B1
FR3120604B1 FR2102545A FR2102545A FR3120604B1 FR 3120604 B1 FR3120604 B1 FR 3120604B1 FR 2102545 A FR2102545 A FR 2102545A FR 2102545 A FR2102545 A FR 2102545A FR 3120604 B1 FR3120604 B1 FR 3120604B1
Authority
FR
France
Prior art keywords
mechanical part
zone
aircraft turbomachine
monitoring device
turbomachine
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
FR2102545A
Other languages
French (fr)
Other versions
FR3120604A1 (en
Inventor
Florent Jeannesson
Josselin Xavier Coupard
Ioannis Stasinopoulos
Oscar D'almeida
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
Safran SA
Original Assignee
Safran Aircraft Engines SAS
Safran SA
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, Safran SA filed Critical Safran Aircraft Engines SAS
Priority to FR2102545A priority Critical patent/FR3120604B1/en
Publication of FR3120604A1 publication Critical patent/FR3120604A1/en
Application granted granted Critical
Publication of FR3120604B1 publication Critical patent/FR3120604B1/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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
    • G01H1/00—Measuring characteristics of vibrations in solids by using direct conduction to the detector
    • G01H1/003—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines
    • G01H1/006—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines of the rotor of turbo machines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
    • G01H9/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by using radiation-sensitive means, e.g. optical means
    • G01H9/004—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by using radiation-sensitive means, e.g. optical means using fibre optic sensors
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/334—Vibration measurements
    • 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

Abstract

L’invention concerne un ensemble (300) pour une turbomachine d’aéronef comprenant une pièce mécanique (302) et un dispositif de surveillance (304) de la turbomachine. Le dispositif de surveillance (304) comporte une zone de mesure (306) configurée pour mesurer au moins une température et/ou une déformation de la pièce mécanique (302) et une zone d’interconnexion (308) configurée pour le connecter à une unité de traitement de l’aéronef. La pièce mécanique (302) est située dans une zone, dite zone fan, allant d’une entrée d’air de la turbomachine jusqu’à une zone d’éjection dudit flux d’air sans passage par une zone de combustion et le dispositif de surveillance (304) est monté sur la pièce mécanique (302). Figure pour l'abrégé : Figure 3AThe invention relates to an assembly (300) for an aircraft turbomachine comprising a mechanical part (302) and a turbomachine monitoring device (304). The monitoring device (304) comprises a measurement zone (306) configured to measure at least one temperature and/or deformation of the mechanical part (302) and an interconnection zone (308) configured to connect it to a unit processing of the aircraft. The mechanical part (302) is located in a zone, called a fan zone, going from an air inlet of the turbomachine to an ejection zone of said air flow without passing through a combustion zone and the device monitoring (304) is mounted on the mechanical part (302). Figure for abstract: Figure 3A

FR2102545A 2021-03-15 2021-03-15 ASSEMBLY COMPRISING A MECHANICAL PART OF AN AIRCRAFT TURBOMACHINE AND A MONITORING DEVICE FOR THE AIRCRAFT TURBOMACHINE Active FR3120604B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2102545A FR3120604B1 (en) 2021-03-15 2021-03-15 ASSEMBLY COMPRISING A MECHANICAL PART OF AN AIRCRAFT TURBOMACHINE AND A MONITORING DEVICE FOR THE AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2102545 2021-03-15
FR2102545A FR3120604B1 (en) 2021-03-15 2021-03-15 ASSEMBLY COMPRISING A MECHANICAL PART OF AN AIRCRAFT TURBOMACHINE AND A MONITORING DEVICE FOR THE AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3120604A1 FR3120604A1 (en) 2022-09-16
FR3120604B1 true FR3120604B1 (en) 2023-08-25

Family

ID=75690516

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2102545A Active FR3120604B1 (en) 2021-03-15 2021-03-15 ASSEMBLY COMPRISING A MECHANICAL PART OF AN AIRCRAFT TURBOMACHINE AND A MONITORING DEVICE FOR THE AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3120604B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9803586B1 (en) * 2016-05-31 2017-10-31 The Boeing Company Secondary systems and methods of control for variable area fan nozzles
US10794387B2 (en) * 2016-09-02 2020-10-06 Raytheon Technologies Corporation Damping characteristic determination for turbomachine airfoils
US10480345B2 (en) * 2017-07-18 2019-11-19 United Technologies Corporation Wear indication sensor designs and methods of integration
US10815904B2 (en) * 2019-03-06 2020-10-27 General Electric Company Prognostic health management control for adaptive operability recovery for turbine engines

Also Published As

Publication number Publication date
FR3120604A1 (en) 2022-09-16

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