EP3938627A1 - Procede de detection d'une fuite eventuelle de carburant dans un circuit d'huile d'un moteur d'aeronef - Google Patents
Procede de detection d'une fuite eventuelle de carburant dans un circuit d'huile d'un moteur d'aeronefInfo
- Publication number
- EP3938627A1 EP3938627A1 EP20725832.8A EP20725832A EP3938627A1 EP 3938627 A1 EP3938627 A1 EP 3938627A1 EP 20725832 A EP20725832 A EP 20725832A EP 3938627 A1 EP3938627 A1 EP 3938627A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- pair
- measurements
- aircraft
- measurement
- engine
- 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.)
- Pending
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 63
- 238000000034 method Methods 0.000 title claims abstract description 46
- 238000005259 measurement Methods 0.000 claims abstract description 135
- 239000012530 fluid Substances 0.000 claims abstract description 51
- 238000009530 blood pressure measurement Methods 0.000 claims abstract description 39
- 238000009529 body temperature measurement Methods 0.000 claims abstract description 36
- 239000003921 oil Substances 0.000 claims description 117
- 238000001514 detection method Methods 0.000 claims description 59
- 238000012545 processing Methods 0.000 claims description 28
- 238000004364 calculation method Methods 0.000 claims description 15
- 238000004891 communication Methods 0.000 claims description 11
- 238000012790 confirmation Methods 0.000 claims description 11
- 239000000203 mixture Substances 0.000 claims description 8
- 238000011282 treatment Methods 0.000 claims description 8
- 238000004590 computer program Methods 0.000 claims description 6
- 238000009472 formulation Methods 0.000 claims description 5
- 239000010705 motor oil Substances 0.000 claims description 4
- 230000006870 function Effects 0.000 description 20
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- 238000005461 lubrication Methods 0.000 description 6
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- 238000010276 construction Methods 0.000 description 1
- 238000011109 contamination Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
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- 238000006073 displacement reaction Methods 0.000 description 1
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
-
- 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
Definitions
- An aircraft engine comprises many elements requiring, during operation of the aircraft, to be dynamically lubricated by oil, such as for example bearings, pistons, gears, etc., this in order to reduce any friction between them.
- an aircraft engine conventionally comprises an oil circuit.
- Such an oil circuit forms a closed circuit comprising one or more pumps configured to set the oil in motion within the pipes of said oil circuit.
- the latter also has a reservoir, in which the oil is stored when the engine is not running, and in which the oil is pumped for circulation in the pipes.
- the oil circuit In addition to being configured to allow oil circulation, the oil circuit also has the function, via said oil circulation and the
- regulating the temperature one refers here to the fact of evacuating calories, or, in other words, to cool.
- the present invention aims to remedy all or part of the
- the invention relates to a method for detecting a possible fuel leak in an oil circuit of an aircraft engine, said aircraft comprising at least one pair of identical engines and equipped with respective oil circuits, said pair of motors being associated with at least one quadruple of measurements previously acquired in a measurement instant during operation of the motors of the pair and corresponding to a pressure measurement and a temperature measurement of the fluid contained in each of the oil circuits of the engines of the pair.
- said detection method comprises:
- the detection of a possible leak according to the invention is carried out in connection with the study of parameters (pressure, temperature) in a single measurement instant, and not in connection with the study of the variation of one or more parameters at a plurality of measurement instants.
- the two motors of the pair thus form a measurement reference system evaluated at a given measurement instant, the operation of one of the motors being determined according to the other motor.
- all of the steps of the method can be implemented by a processing device external to the engines, for example located in a ground station, so that there is no need to modify the configuration. engine material.
- the detection method may also include one or more of the following characteristics, taken in isolation or in any technically possible combination.
- the step of determining the quantity Q comprises:
- the quantity Q is calculated according to the following formulation:
- said method comprises, after the step of determining the quantity Q and before the step of comparison, a step of updating the quantity Q in which the quantity Q put à jour corresponds to the absolute value of the quantity Q previously determined.
- said method comprises
- a step of issuing an alert message following the detection step and when a leak is detected, a step of issuing an alert message.
- said method comprises, following the detection step and when a leak is detected, a step of identifying a faulty motor among the motors of the pair, said step identification including:
- said alert message when an alert message is sent, said alert message includes an identifier of the identified faulty engine.
- each motor of the pair is also associated with at least two measurements of the volume of fluid contained in the oil circuit of said motor of the pair and previously acquired in two respective measuring instants distinct during operation of the aircraft, a measurement instant prior to take-off of the aircraft and a measurement instant subsequent to the landing of the aircraft.
- said method comprises, for at least one motor of the pair:
- a step of determining a difference V between the two measurements of the volume of fluid associated with said motor a step of comparing the difference V with a threshold value determined as a function of a theoretical average oil consumption of the faulty engine and of a period separating said distinct measuring instants,
- measurements are considered, at least the steps of determining a quantity Q, comparing the quantity Q with a threshold value and detecting a possible leak being iterated for each of said measurement quadruplets.
- the aircraft comprises several pairs of identical engines, at least the steps of determining a quantity Q, of comparing the quantity Q with a threshold value and of detecting a possible leak being iterated for each of said pairs.
- the invention relates to a computer program comprising a set of program code instructions which, when executed by a processor, configure said processor to implement a detection method according to invention.
- the invention relates to a recording medium readable by a computer on which is recorded a computer program according to the invention.
- the invention relates to a processing device for the detection of a possible fuel leak in an oil circuit of an aircraft engine, said aircraft comprising at least one pair of identical engines. and equipped with respective oil circuits, said pair of motors being associated with at least one quadruple of measurements previously acquired in a measurement instant during operation of the motors of the pair and
- the treatment device comprises:
- a determination module configured to determine a quantity Q representative of a possible difference in operation between the motors of the pair, as a function of the measurement quadruple,
- a comparison module configured to compare the quantity Q with a predetermined threshold value, so as to obtain a comparison result
- a detection module configured to detect a possible fuel leak in the oil circuit of one of the engines of the pair, depending on the comparison result.
- the processing device may further include one or more of the following characteristics, taken in isolation or in any technically possible combination.
- said device comprises a
- identification module configured for, when a leak is detected:
- each motor of the pair is also associated with at least two measurements of the volume of fluid contained in the oil circuit of said motor of the pair and previously acquired in two distinct respective measuring instants during of the operation of the aircraft, an instant of measurement prior to take-off of the aircraft and an instant of measurement subsequent to the landing of the aircraft.
- said device comprises: a determination module, configured to determine a difference V between the two fluid volume measurements associated with a motor of the pair,
- a comparison module configured to compare the deviation V with a threshold value determined as a function of the theoretical average oil consumption of the faulty engine and of a period between said separate measurement instants,
- a confirmation module configured to possibly confirm, depending on the result of the comparison of the deviation V with the threshold value, the identity of the engine identified as faulty.
- the invention relates to a system for detecting a possible fuel leak in an oil circuit of an aircraft engine, said aircraft comprising at least one pair of identical engines and equipped with respective oil circuits.
- said detection system comprises:
- - acquisition means configured to acquire at least one quadruple of measurements in a measurement instant during operation of the motors of the pair and corresponding to a pressure measurement and a temperature measurement of the fluid contained in each of the oil circuits motors of the pair,
- said acquisition means are also configured to acquire, for each engine of the pair, at least two measurements of the volume of fluid contained in the oil circuit of said engine in two measurement instants. respective distinct during operation of the aircraft, a measurement instant prior to take-off of the aircraft and a measurement instant subsequent to the landing of the aircraft, said processing device being in accordance with the invention, and the means communication systems also being configured to transmit the fluid volume measurements to the processing device.
- the invention relates to an aircraft comprising a
- FIG. 1 diagrammatically represents an exemplary embodiment of a detection system according to the invention of a possible fuel leak in an oil circuit of an aircraft engine, said aircraft comprising at least one pair of identical engines;
- FIG. 2 represents a flowchart of an embodiment of a method for detecting according to the invention of a possible fuel leak in an oil circuit of an engine of said aircraft, from measurements pressure and temperature;
- FIG. 3 represents a preferred embodiment according to the invention of the method of FIG. 2, during which, when a leak is detected, a faulty engine is identified among the engines of the aircraft;
- FIG. 4 shows a preferred embodiment according to the invention of the detection method, from measurements of pressure, temperature and volume of fluid, and during which, when a faulty engine has been identified, a
- the present invention finds its place in the field of monitoring the operation of an aircraft engine, for an aircraft (not shown in the figures) comprising at least one pair of identical engines.
- each engine of the aircraft is equipped with a
- the oil circuit of each engine forms a closed circuit comprising one or more pumps configured to set the oil in motion within pipes of said oil circuit.
- the latter also comprises a reservoir, in which the oil is stored when the engine that it equips is not in operation, and in which the oil is pumped for putting into circulation in the pipes.
- the oil circuit of an engine of the aircraft is also in contact, at a plurality of interfaces, such as for example seals, walls, equipment, etc., with a circuit fuel from said engine.
- Figure 1 schematically shows an embodiment of a
- an aircraft of the airplane type equipped with two identical engines of the turboshaft type, such as, for example, turboprop engines. Since the aircraft has a pair of engines, the number of oil circuits is therefore also equal to two, these oil circuits also being identical to each other.
- turbojet but also, and more generally, engines which are not turboshaft engines, such as, for example, piston engines.
- the invention is in fact applicable to any type of engine for which it is desired to monitor any possible contamination of its oil circuit by fuel. There is also nothing to exclude considering an aircraft of another type, such as a helicopter.
- the aircraft can have two pairs of engines, so as to be equipped with a total of four engines which can either all be identical to each other (in other words the pairs are identical to each other), or correspond to two different pairs between them , the motors within the same pair being nevertheless identical to each other.
- the aircraft also having, in addition to one or more pairs of identical engines, one or more engines which, considered individually, differ from all the other engines.
- the detection system 10 comprises acquisition means 11 configured to acquire measurements of pressure and temperature of the fluid contained in each of the oil circuits of the engines of said pair.
- fluid contained in an oil circuit, we refer here to a liquid circulating in the pipes of said circuit.
- the fluid contained in the oil circuit Under nominal operating conditions, that is to say when no fuel leak affects an oil circuit, the fluid contained in the oil circuit naturally corresponds only to oil. Conversely, when a fuel leak occurs, the fluid contained in the oil circuit corresponds to a mixture of oil and fuel.
- respective oil pressures and temperatures in each of the oil circuits are substantially identical and follow the same trends. This results from the fact that the engines of the pair receive identical commands, such as a displacement command during taxiing, a flight command during the cruise phase, etc., and are therefore supposed to be subjected to the same operating conditions. .
- the acquisition means 1 1 comprise dedicated sensors for each type of measurement, each motor then comprising a pressure sensor and a temperature sensor, also called a temperature probe.
- sensors can be chosen depending on the oil used as well as the sizing characteristics of the engines.
- oil pressure corresponds to a relative pressure
- the measurements acquired by the acquisition means 11 are performed in at least one measurement instant during the operation of the engines of the aircraft.
- operation of the engines of the aircraft reference is made here to the fact that the engines of the aircraft have started.
- Such a configuration naturally covers the taxiing phases before and after landing (phases still referred to as "taxi” in the English literature), the cruising phase, but also the phases during which the aircraft has not yet left its parking lot before. take-off or has already reached its parking lot after landing, its engines nonetheless being operating.
- this measurement quadruple corresponding to a pressure measurement and to a temperature measurement of the fluid contained in each of the oil circuits of the engines of said pair.
- the acquisition means 11 of the detection system 10 are also configured to acquire, in addition to the pressure and temperature measurements, and for each motor of the pair, at least two measurements of the volume of fluid contained in the engine oil circuit considered in two distinct respective measuring instants.
- the acquisition means 11 also include sensors dedicated to volume measurements, typically level probes. It should be noted that the fluid volume measurements do not require the aircraft engines to be in operation, and conventionally correspond to the volumes of fluid respectively contained in the engine tanks.
- the processing device 13 can perform processing aimed at detecting a possible fuel leak in an oil circuit of one of the engines of the pair, by implementing a detection method such a possible leak.
- the processing device 13 comprises for example one or more
- processors and storage means magnetic hard disk, electronic memory, optical disk, etc.
- data and a computer program are stored, in the form of a set of program code instructions to be executed for implement all or part of the stages of method of detecting a possible leak.
- the processing device 13 also comprises one or more programmable logic circuits, of the FPGA, PLD, etc. type, and / or specialized integrated circuits (ASIC), and / or a set of discrete electronic components, etc. suitable for implementing all or part of the steps of the process for detecting a possible leak.
- the processing device 13 comprises a set of means configured in software (specific computer program) and / or hardware (FPGA, PLD, ASIC, etc.) to implement the various steps of the process for detecting a possible leak.
- treatment 13 is located on the ground, for example in the premises of the manufacturer of the engines equipping the aircraft, or in the premises of the airline to which the aircraft belongs, or even in the premises of an airport and dedicated to the analysis of flights departing / arriving at this airport.
- said communication means 12 are configured to transmit the measurements acquired within the aircraft to the processing device 13 on the ground.
- said communication means 12 comprise ACARS units (acronym of the English expression “Airline Communications, Addressing and Reporting System”), respectively equipping the aircraft and the processing device 13, and configured to communicate according to the ARINC standard. (acronym of the Anglo-Saxon expression “Aeronautical Radio Incorporated”).
- the processing device 13 is integrated into the aircraft.
- said communication means 12 are for example wired or wireless, and configured to transmit the measurements acquired to the processing device 13 according to any protocol.
- the processing device 13 implements the detection method on each reception of one of the
- quadruplets are recorded in the storage means of the processing device 13, and analyzed in deferred time via said detection method.
- the detection system 10 comprises ancillary storage means, such as for example a database stored on a local server on the ground. These storage means are not integrated into the processing device 13, and receive measurements acquired, for example thanks to the transmissions of an ACARS unit, to store them and only then transmit them to the processing device 13 with a view to their analysis.
- ancillary storage means such as for example a database stored on a local server on the ground.
- a single measurement instant is considered, for example a
- the two motors of the pair are respectively denoted Mi and M 2 .
- the quadruplet, for its part, is denoted (Pi, P 2 , T ,, T 2 ) where:
- FIG. 2 represents a flowchart of an embodiment of the method for detecting a possible fuel leak in an oil circuit of an engine of the pair, from measurements of pressure and of temperature.
- the detection method comprises several steps. In principle
- the method consists first of all in quantifying, as a function of the measurement quadruplet (Pi, P 2 , Ti, T 2 ), any difference in operation between the motors M 1 and M 2 of the pair.
- This quantification is carried out by calculating a metric representative of the phenomenon considered (fuel leak in an oil circuit), this metric then serving as a decision criterion as to the existence or not of a fuel leak.
- the detection method firstly comprises a step 100 of determining a quantity Q representative of a possible difference in operation between the motors M 1 and M 2 of the pair, as a function of the quadruple. of measurements (Pi, P 2 , Ti, T 2 ).
- Quantity Q we refer here to the fact that Q is a real number.
- the detection of a possible leak in this mode of implementation is carried out in connection with the study of parameters, which are the pressure and the temperature, in a single instant of measurement, and not in connection with the study of the variation of one or more parameters at a plurality of measurement instants.
- the two motors M 1 and M 2 thus form a measurement reference evaluated at a given measurement instant, the operation of one of the motors being determined as a function of the other motor.
- processing device 13 when integrated into the aircraft, may be located outside said engines, for example in the cockpit.
- the step of determining the quantity Q comprises the calculation of a first quantity Qi representative of a pressure difference between the two motors M-, and M 2 , as a function of measurements of pressure P-, and P 2 of the quadruplet. It also includes the calculation of a second quantity Q 2 representative of a temperature difference between the two motors M 1 and M 2 , as a function of the temperature measurements Ti and T 2 of the quadruplet. The quantity Q is finally calculated as a function of the quantities Q 1 and
- quantity Q depends, in particular, on the threshold value with which it is compared, as described later.
- threshold values that are homogeneous to the product of a pressure and a temperature, for example following calculations carried out from measurements regularly recorded during aircraft flights or even following numerical simulations, the determination of the quantity Q is carried out in correspondence with the units of these threshold values.
- the quantity Q is calculated according to the following formulation:
- - Q 2 is calculated equal to the difference between the temperature measurements of the quadruplet, that is to say equal to Ti-T 2 (or else T 2 -Ti, the order in the subtraction not constituting a limitation) .
- the norm of this vector determines the norm of a vector whose components are Q 1 and Q 2 .
- Q corresponds to the computation of the quadratic norm L 2 of this vector.
- the norm of this vector is substantially zero given that the quantities Q 1 and Q 2 are respectively substantially zero.
- the norm of this vector makes it possible to quantify the operating difference between the two motors of the pair, thus forming a characteristic metric of the phenomenon of fuel leakage in the oil circuit of one of said engines.
- the higher the quantity Q calculated in this way the greater the probability of the existence of a leak, and the greater the importance of the possible leak.
- magnitude of the leak we refer here to the flow of fuel contaminating the affected oil circuit.
- the quantity Q in a different way. For example, it is possible to consider a quantity Q 1 (respectively Q 2 ) representative of a pressure difference (respectively a temperature difference) assigned a weighting coefficient, the respective weighting coefficients of the quantities Qi and Q 2 being different. According to another example, possibly taken in combination with the previous one aimed at weighting the quantities Q 1 and Q 2 , it is also possible to consider a quantity Q corresponding to the calculation of the norm L p (Lebesgue space of index p), with p an integer greater than or equal to 1, of the vector whose components are Qi and Q 2 .
- L p Lebesgue space of index p
- the detection method supplies the quantity Q, so that it becomes possible to assess whether a fuel leak does indeed affect one of the two engines Mi and M 2 .
- the method comprises a step 200 of comparing the quantity Q with a predetermined threshold value, so as to obtain a comparison result.
- comparison with a threshold value reference is made here to determining whether the quantity Q is less than or indeed greater than said threshold value.
- the comparison result therefore corresponds to the fact that the quantity Q is less than or much greater than the threshold value.
- the threshold value corresponds, for example, to a value obtained following a test campaign. According to another example, the threshold value is set following digital simulations modeling the operation of the engines of the aircraft.
- the choice of a threshold value depends on the desired tolerance in the face of possible false leak detections.
- the threshold value is representative of the accepted tolerance with respect to any variations in the quantity Q. It is in fact understood that, in the case where the quantity Q is calculated so as to be a number greater than or equal to zero, the closer the threshold value is to the lower limit of the quantity Q, the greater the risk of obtaining false detections, via the detection method. For example, in the case where the quantity Q is calculated, as described above, equal to the quadratic norm L 2 of the vector whose
- setting the threshold value equal to zero amounts to considering a high tolerance in the face of possible false leak detections. Indeed, at the slightest variation in pressure and / or temperature, the quantity becomes strictly positive, and therefore greater than the threshold value. Conversely, setting a threshold value that is too high may lead to not taking into account certain variations in pressure and / or temperature between the oil circuits of the engines, and therefore in fine in not detecting a fuel leak while it is this is happening.
- the method comprises, after
- the quantity Q can be determined according to the following formulation:
- the detection method then comprises a step 300 of detecting a possible fuel leak in the oil circuit of one of the engines of the pair, as a function of the comparison result.
- the detection is carried out according to the result of the comparison.
- the detection of a possible leak corresponds here to the result of a comparison between numerical quantities (quantity Q and threshold value).
- the information according to which a possible leak has occurred corresponds to digital information, typically expressed in the form of digital bits, which is for example recorded by the storage means of the monitoring device. processing 13 to be analyzed in real time or in deferred time.
- the method comprises, following the detection step 300 and when a leak is detected, a step 400 of sending a message from alert.
- Such an alert message can be sent in any form whatsoever, the choice of a particular form of emission constituting only one variant of the implementation of the invention.
- the message can be transmitted in text format in order to be displayed by display means such as a computer screen, a tablet, a smartphone, an aircraft dashboard dial.
- the alert message is emitted in sound format.
- the pilot of the aircraft once notified of the detection of a leak, can then consider shortening the flight time, or even not taking off if necessary.
- the transmission of the alert message can take place in real time, as soon as the leak is detected, or even in deferred time, for example once the aircraft has landed.
- FIG. 3 represents a preferred embodiment of the method of FIG. 2 during which, when a leak is detected, a faulty motor is identified among the motors of the pair.
- the method comprises, consecutively to
- This step 350 firstly comprises a comparison of the pressure measurements and / or a comparison of the temperature measurements of the quadruple associated respectively with the motors of the pair.
- step 350 comprises an identification of a faulty engine as a function of said comparison of the pressure measurements and / or of said comparison of the pressure measurements. temperature measurements.
- the pressure measurements are compared with each other and the temperature measurements are compared with each other.
- the identification of the engine affected by the fuel leak makes it possible to generate information, comprising for example an identifier of the faulty engine, and which, when it is transmitted to an operator, for example via the alert message emitted, leads to a more precise identification of the leak.
- the operator can, depending on the operational context, implement an action plan to minimize or repair the fuel leak.
- alert message is sent in text format to display means controlled by an aircraft engine maintenance operator, this operator is able, once the aircraft is on the ground and once the alert message lu, to carry out maintenance operations aimed at repairing the leak by precisely targeting the faulty engine. Thus, said operator is not required to carry out preliminary examinations aimed at identifying the faulty engine.
- step 350 of identifying the faulty engine from being carried out without any warning message being issued.
- FIG. 4 represents a preferred embodiment of the detection method, from measurements of pressure, temperature and volume of fluid, and during which, when a faulty engine has been identified, a possible confirmation identification of this faulty engine is sought.
- the acquisition means 1 1 of the detection system 10 have acquired, for each motor of the pair (Mi, M 2 ), at least two measurements of the volume of fluid contained in the oil circuit of said engine in two distinct respective measuring instants during operation of the aircraft.
- each of the motors of the pair is associated with two measurements of the volume of fluid contained in its oil circuit.
- the two measurement instants associated with an engine of the pair correspond respectively to a measurement instant prior to take-off of the aircraft and a measurement instant subsequent to the landing of the aircraft. According to a more specific example, these measurement instants take place when the aircraft is in the taxiing phase, respectively before take-off and after landing.
- the detection method comprises, following the step 350 of identifying the faulty engine, a step 500 of determining a difference V between the two fluid volume measurements associated with said motor.
- said deviation V is determined by subtracting the measurements from
- said difference V corresponds to the absolute value of a subtraction of the measurements of the volume of fluid.
- the method then comprises a step 600 of comparing the difference V
- a threshold value determined as a function of a theoretical average oil consumption of the faulty engine and of a period between said separate measuring instants.
- the theoretical average consumption of oil is a physical quantity homogeneous at a flow rate, that is to say the unit of which corresponds to a volume divided by a duration, for example expressed in liters per hour.
- the term “theoretical” here refers to oil consumption under nominal conditions, that is, when the engine is not faulty.
- said theoretical average oil consumption is provided by the company in charge of the engine design.
- the consumption provided by said company is obtained by a statistical method on the basis of previous oil consumption readings, so as to increase the robustness and the precision of the comparison step 600.
- the theoretical average consumption being determined otherwise, for example on the sole basis of the technical specifications of the engine.
- this is for example substantially equal, in absolute value, to the product between said theoretical average consumption and the duration separating the instants of measurement.
- Theoretical average consumption and the time between the instants of measurement makes it possible to refine the tolerance targeted for taking into account false fault detections, or, conversely, non-detection of a real fault.
- Said comparison consists in evaluating the difference between the difference V and the threshold value. Under nominal operating conditions, such a difference is substantially zero if the threshold value is equal, in absolute value, to the product between said theoretical average consumption and the time separating the instants of measurement. On the other hand, in the event of a fuel leak in the oil circuit, the quantity of fluid increases in said oil circuit, which is closed, so that the measurement of the volume of fluid in the instant subsequent to landing is greater than the measurement of fluid volume at the instant prior to takeoff.
- the method then comprises a step 700 of possible confirmation, as a function of the result of the comparison of the deviation V with the threshold value, of the identity of the engine identified as faulty.
- Said step 700 thus consists in testing whether the engine identified as faulty at the end of step 350 is also identified as faulty on the basis of the value of the difference between the deviation V and the threshold value. Typically, if this difference is judged to be too high, for example by comparing it to yet another threshold value, the engine concerned is again identified as faulty, thus confirming the diagnosis obtained at the end of step 350. Such a manner proceeding makes it possible to increase the criticality of the identification resulting from step 350.
- step 700 makes it possible to carry out an additional verification of the possible presence of a fuel leak in an engine of the aircraft.
- step 700 does not confirm a failure identification resulting from step 350, different scenarios can be considered, such as, for example, considering additional measurements (pressure, temperature, volume) to reiterate the process.
- steps 500, 600 and 700 have been described, with reference to FIG. 4, as being executed successively, following the identification step 350. None excludes that they may also be consecutive to the transmission of an alert message generated by the step 400. There is also nothing to exclude having a transmission of a message at the end of the. step 700, the one that can include a confirmation or else an invalidation of a previous message sent during a step 400.
- steps 500 and 600 are executed in parallel with the other steps as indicated above, to iterate the steps 500 and 600 for each motor of the pair. In this way, one avoids carrying out an execution of steps 500 and 600 for an engine which will ultimately not be identified at the end of step 350.
- the pressure and temperature measurements are carried out repeatedly, following a constant time step between two measurement instants. It is thus possible to precisely monitor the state of the engine oil circuits.
- the smaller the time step the easier it is to identify the true instant at which the fuel leak occurred, which thus improves experience feedback and therefore also corrective actions to consider to avoid potential further fuel leaks.
- each engine is shown in two separate pairs also helps identify a failing engine in case a fuel leak occurs. Indeed, if a leak is detected during a first iteration of the method for one of the two motors of the pair (Mi, M 2 ), then also during a second iteration of the method for one of the motors of the pair (M 2 , M 3 ), then the motor M 2 will be identified as faulty.
- step 350 This identification result can be compared with that of step 350, when the latter is executed, so as to further increase the robustness of the identification of a faulty engine.
- other pairs of motors can be considered, such as for example only (Mi, M 2 ) and (M 3 , M 4 ).
- the present method of detecting a possible fuel leak in an oil circuit of an aircraft engine can be carried out in an automated manner without the intervention of an operator at any stage whatsoever. It can be implemented without limitation, depending on the operational context, within a ground station as described above, within an aircraft, within an autonomous software suite dedicated to the monitoring of the operation of aircraft engines, or be integrated into a distributed processing chain for “cloud services” type monitoring services.
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Application Number | Priority Date | Filing Date | Title |
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FR1902657A FR3093806B1 (fr) | 2019-03-15 | 2019-03-15 | Procédé de détection d’une fuite éventuelle de carburant dans un circuit d’huile d’un moteur d’aéronef |
PCT/FR2020/050446 WO2020188179A1 (fr) | 2019-03-15 | 2020-03-05 | Procede de detection d'une fuite eventuelle de carburant dans un circuit d'huile d'un moteur d'aeronef |
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EP3938627A1 true EP3938627A1 (fr) | 2022-01-19 |
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EP20725832.8A Pending EP3938627A1 (fr) | 2019-03-15 | 2020-03-05 | Procede de detection d'une fuite eventuelle de carburant dans un circuit d'huile d'un moteur d'aeronef |
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US (1) | US20220178272A1 (fr) |
EP (1) | EP3938627A1 (fr) |
CN (1) | CN113518851A (fr) |
CA (1) | CA3130266A1 (fr) |
FR (1) | FR3093806B1 (fr) |
WO (1) | WO2020188179A1 (fr) |
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GB202015023D0 (en) | 2020-09-23 | 2020-11-04 | Rolls Royce Plc | System and method for determining high oil consumption in gas turbine engine |
FR3133896A1 (fr) * | 2022-03-23 | 2023-09-29 | Psa Automobiles Sa | Véhicule automobile avec boîte de vitesses et procédé de surveillance automatique |
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FR2691255B1 (fr) * | 1992-05-13 | 1994-07-01 | Snecma | Dispositif de detection d'une fuite de carburant dans un echangeur de chaleur huile-carburant monte sur un circuit de lubrification d'un moteur. |
EP2072762B1 (fr) * | 2007-12-21 | 2012-05-30 | Techspace Aero SA | Méthode de contrôle de la consommation et de détection de fuites dans un système de lubrification de turbomachine |
US20120048000A1 (en) * | 2010-08-31 | 2012-03-01 | Joseph Kirzhner | Method and system to detect and measure piping fuel leak |
WO2013037865A1 (fr) * | 2011-09-15 | 2013-03-21 | Universite Libre De Bruxelles | Procédé et dispositif de surveillance de système de lubrification |
FR2980238B1 (fr) | 2011-09-20 | 2013-09-20 | Snecma | Procede et dispositif de detection d'une contamination du circuit d'huile d'un turboreacteur par du carburant |
FR3021350B1 (fr) * | 2014-05-20 | 2016-07-01 | Snecma | Procede de detection de fuite de fluide dans une turbomachine et systeme de distribution de fluide |
DE102014119210A1 (de) * | 2014-12-19 | 2016-06-23 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zur Ermittlung eines Treibstofflecks eines Treibstoffsystems eines wenigstens zwei Triebwerke aufweisenden Flugzeugs |
FR3031141B1 (fr) * | 2014-12-24 | 2017-02-10 | Snecma | Procede de detection de fuite de fluide dans une turbomachine et systeme de distribution de fluide |
US9865101B2 (en) * | 2015-10-30 | 2018-01-09 | Wipro Limited | Methods for detecting one or more aircraft anomalies and devices thereof |
FR3061324B1 (fr) * | 2016-12-22 | 2019-05-31 | Electricite De France | Procede de caracterisation d'une ou plusieurs defaillances d'un systeme |
US10704734B2 (en) * | 2017-08-22 | 2020-07-07 | General Electric Company | Method and apparatus for determining lubricant contamination or deterioration in an engine |
US11151810B2 (en) * | 2018-10-12 | 2021-10-19 | Aurora Flight Sciences Corporation | Adaptable vehicle monitoring system |
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2019
- 2019-03-15 FR FR1902657A patent/FR3093806B1/fr active Active
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2020
- 2020-03-05 WO PCT/FR2020/050446 patent/WO2020188179A1/fr active Application Filing
- 2020-03-05 US US17/435,460 patent/US20220178272A1/en active Pending
- 2020-03-05 CA CA3130266A patent/CA3130266A1/fr active Pending
- 2020-03-05 EP EP20725832.8A patent/EP3938627A1/fr active Pending
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CN113518851A (zh) | 2021-10-19 |
CA3130266A1 (fr) | 2020-09-24 |
FR3093806B1 (fr) | 2021-04-02 |
FR3093806A1 (fr) | 2020-09-18 |
WO2020188179A1 (fr) | 2020-09-24 |
US20220178272A1 (en) | 2022-06-09 |
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