公开(公告)号：US12272190B2

公开(公告)日：2025-04-08

申请号：US17632472

申请日：2020-08-06

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Josselin Xavier Coupard ,  Alrick Patrick Michel Jacques Verrier

IPC: B64F5/00 ,  B64D45/00 ,  G07C5/08 ,  B64D47/08

Abstract: A method for monitoring an aircraft component, including the following steps: receiving, from a video acquisition device, a video stream that represents at least one portion of the component; in the event that the realization of a predetermined condition is detected, extracting a portion of the video stream to form a sequence of interest; identifying, within the extracted sequence of interest, at least one image of interest; including a signature, obtained using each image of interest, with at least one predetermined signature from a library of signatures; and generating an anomaly detection signal if the result of the comparison meets a predetermined criterion.

公开(公告)号：US11655735B2

公开(公告)日：2023-05-23

申请号：US16441790

申请日：2019-06-14

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Alméric Pierre Louis Garnier ,  Josselin Xavier Coupard

IPC: F01D25/32 ,  F01D25/18 ,  B64D33/00 ,  F02C7/00 ,  B64C25/00

CPC classification number: F01D25/32 ,  B64C25/001 ,  B64D33/00 ,  F01D25/18 ,  F02C7/00 ,  F05D2220/323 ,  F05D2260/602

Abstract: An onboard system and a method for draining an aeroengine. The onboard system comprises a buffer tank having an admission passage for admitting under gravity fluid coming from the aeroengine, a primary tank situated above the buffer tank and having an emptying passage for emptying the fluid coming from the aeroengine, and a lift circuit connecting the buffer tank to the primary tank in order to transfer the fluid coming from the aeroengine from the buffer tank to the primary tank.

公开(公告)号：US12117364B2

公开(公告)日：2024-10-15

申请号：US17753376

申请日：2020-09-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Josselin Xavier Coupard ,  Valentin Francis Joël Facquet ,  Julien Christian Pascal Griffaton

IPC: G01M13/028 ,  G01M13/021

CPC classification number: G01M13/028 ,  G01M13/021

Abstract: A method for monitoring an epicyclic gear train of an aircraft includes the following steps: acquiring, at a predetermined sampling frequency, first values (5(ti)) of a signal formed by a progressive mechanical wave generated in the epicyclic gear train; measuring, at a plurality of successive instants, values (Vmes _r(tj)) of a speed of rotation of at least one of the toothed wheels of the gear train; calculating values (Vc(tj)) of a speed of rotation of a point of contact between two toothed wheels of the epicyclic gear train; determining second values (S(ç½)) of the signal formed by a progressive mechanical wave generated in the epicyclic gear train, the second values being sampled depending on a phase of the point of contact and forming secondary mechanical wave data; and using the secondary mechanical wave data (S(ç½)) to detect an anomaly related to the operation of the epicyclic gear train.

公开(公告)号：US12012230B2

公开(公告)日：2024-06-18

申请号：US17251409

申请日：2019-06-07

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Alméric Pierre Louis Garnier ,  Josselin Xavier Coupard

IPC: B64F5/40 ,  B64C1/14 ,  G01N33/28 ,  G05D1/00 ,  F01M11/04 ,  F01M11/10 ,  F16N31/00

CPC classification number: B64F5/40 ,  B64C1/1453 ,  G01N33/2888 ,  G05D1/0088 ,  F01M11/0458 ,  F01M11/10 ,  F16N31/004 ,  F16N2200/00 ,  F16N2200/04 ,  F16N2200/12 ,  F16N2210/02 ,  F16N2250/18 ,  F16N2250/36

Abstract: The invention relates to the field of aeronautical propulsion, and more specifically to an emptying and monitoring device and method for emptying and monitoring a fluid drained from an aircraft engine. The emptying and monitoring device comprises at least one first intake passage for receiving, directly from the aircraft, fluid drained from the engine, and a first quality sensor assembly for detecting at least one quality parameter of the fluid drained from the engine, having been admitted through the first intake passage.

公开(公告)号：US12210010B2

公开(公告)日：2025-01-28

申请号：US17995838

申请日：2021-04-08

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Josselin Xavier Coupard ,  Alméric Pierre Louis Garnier ,  François Maurice Marcel Demaison ,  Franck Serge Jacques Liotte

IPC: G01N33/28 ,  G01N1/10 ,  G01N1/20 ,  G01N15/00 ,  G01N15/06

Abstract: Analysis device for detecting solid particles in suspension in a lubricant, the analysis device comprising one or more ferromagnetic solid particle sensors, one or more other sensors able to detect non-ferromagnetic solid particles, and one or more magnets. The ferromagnetic solid particle sensors are offset in a direction perpendicular to a main direction of flow of the lubricant in relation to the other sensors, and the magnets are arranged so as to attract ferromagnetic solid particles towards the sensors of ferromagnetic solid particles by drawing them away from the other sensors.

公开(公告)号：US12012231B2

公开(公告)日：2024-06-18

申请号：US17593785

申请日：2020-03-16

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Guillaume Rémi Bonnet ,  Josselin Xavier Coupard

IPC: B64F5/60 ,  B64D45/00 ,  F02C6/20

CPC classification number: B64F5/60 ,  B64D45/00 ,  F02C6/20 ,  B64D2045/0085 ,  F05D2270/11 ,  F05D2270/44

Abstract: The invention relates to a method for monitoring at least one aircraft engine, said method including an acquisition (100) according to the first and second sets of measurements of respectively endogenous and exogenous variables. The method also includes:



a normalization (200) of the measurements of the first set relative to the measurements of the second set,
a generation (300) of a current model representative of the evolution of the behavior of the engine based on the normalized measurements,
a detection (400) of potential abnormality in the behavior of the engine based on a comparison of the current model with a reference model,
a generation (500) of a maintenance message,
a transmission (600) of said ground message,

the acquisition, normalization, generation of a current model, the detection and generation of a maintenance message being made on board the aircraft.

公开(公告)号：US12276567B2

公开(公告)日：2025-04-15

申请号：US17437978

申请日：2020-02-27

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Josselin Xavier Coupard ,  Alméric Pierre Louis Garnier

IPC: G01M13/021 ,  G01M15/14

Abstract: A method for monitoring a status of a reduction gear of a gas turbine includes the steps of: obtaining measurements of parameters accomplished during an operating phase of the gas turbine, these parameters including temperatures of a lubricating oil of the reduction gear at the inlet and at the outlet of the reduction gear, a parameter representing a speed of the gas turbine, as well as at least one context parameter; selecting measurements; normalizing temperatures of the lubricating oil using the measurements of the context parameter; evaluating a thermal efficiency of the reduction gear by using a physical model defining the thermal efficiency based on a difference between the temperature of the lubricating oil; and determining a status of the reduction gear depending on a step of comparing the evaluated thermal efficiency with respect to a reference signature.

公开(公告)号：US12072261B2

公开(公告)日：2024-08-27

申请号：US17904342

申请日：2021-02-18

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Josselin Xavier Coupard ,  François Maurice Marcel Demaison ,  Valentin Francis Joël Facquet ,  Marion Marguerite Jedruszek

IPC: G01M15/14 ,  F02C7/266

CPC classification number: G01M15/14 ,  F02C7/266 ,  F05D2220/323 ,  F05D2260/80

Abstract: Method for monitoring an ignition system of an aircraft turbine engine, the ignition system including a combustion chamber fitted with a spark plug and an ignition casing, the turbine engine including an accelerometer and an acoustic sensor. The method includes steps of: acquiring accelerometric and acoustic data representative of spark plug breakdown noises from signals generated by the accelerometer and the acoustic sensor, detecting breakdown peak times from the accelerometric data and the acoustic data, correlating the breakdown peak times detected from the accelerometric data and the breakdown peak times detected from the acoustic data, and establishing a diagnosis of the health of the ignition casing and a diagnosis for the spark plug on the basis of the correlation results.

公开(公告)号：US11628946B2

公开(公告)日：2023-04-18

申请号：US17251356

申请日：2019-06-14

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Josselin Xavier Coupard ,  Alméric Pierre Louis Garnier

IPC: B64D37/20 ,  F01M11/04

Abstract: The invention relates to the field of aeronautical propulsion, and more particularly an on-board drainage reservoir of an aircraft engine, the on-board reservoir including a first compartment with a first intake passage for receiving fluid drained from the engine, a first closeable emptying passage, and a first quality sensor assembly for detecting at least one quality parameter of the fluid drained from the engine.