Device for characterizing wear on a gas turbine engine

Abstract

Device (1) for characterizing wear on a gas turbine engine comprising: - an abradable material (8) having a wear end (80) adapted to be in contact with a gaseous fluid flow (F) flowing from upstream to downstream of the gas turbine engine when the gas turbine engine is running, the abradable material (8) being electrically conductive; - a magnetic field generator (7) adapted to emit a magnetic field in the abradable material (8); - an electronic board (10) configured to calculate information enabling the characterization of the wear of the gas turbine engine from data relating to a physical response of said abradable material (8) to said magnetic field. Figure for the abbreviation: Figure 2.

Description

Title of the invention: Device for characterizing wear on a gas turbine engine FIELD OF INVENTION

[0001] The present invention relates to the field of gas turbine engines. More specifically, it relates to a device for characterizing wear in a gas turbine engine. STATE OF THE ART

[0002] Wear, i.e., erosion, is a mode of damage to gas turbine engines, particularly aircraft engines. It involves the removal of material by abrasion of particles carried along in the gaseous fluid flow circulating from the upstream to the downstream side of the gas turbine engine (air stream). This wear primarily affects the profiles of the blades and vanes of the fixed and moving parts of compressors and turbines.

[0003] Depending on the environments in which the aircraft operates, particularly for a helicopter, if the engine air intake is not equipped with a filtration system, in a desert environment, wear can be significant and reduce the interval between two major maintenance to a few dozen flight hours.

[0004] One common solution for ensuring that the wear level is below the certified limit guaranteeing the engine's operability throughout its entire flight envelope is to insert a videoscope equipped with a camera into the engine's airflow channel through endoscopic ports designed for this purpose and to inspect the interior via a control panel and its screen using the video feed provided by the videoscope. The acquired image allows the technician to determine the level of internal engine wear and thus determine whether maintenance is required.

[0005] Furthermore, as proposed in patent application no. FR3006013, it is possible to position an abradable material in the air stream that wears down as quickly as the engine part being monitored. This abradable material is visually inspected regularly to determine engine wear.

[0006] Most of the known methods require the use of a maintenance technician and specific tools. These methods are not automatic.

[0007] Automated wear measurement methods also exist, but these are implemented only by gas turbine engine manufacturers and are mainly used for break-in tests before delivery to customers. These tests are therefore carried out under very specific and controlled conditions.

[0008] However, the constraints to which aircraft operators are subjected require a technology that allows the wear of the various parts of gas turbine engines to be characterized in a more precise, robust, reliable and reproducible way.

[0009] There is therefore no satisfactory technology at present allowing for the measurement in real time, in a precise, robust, reliable and reproducible manner of wear in gas turbine engines. Description of the invention

[0010] One object of the invention is to characterize, in particular to measure, the wear of a gas turbine engine in a precise, robust, reliable and reproducible manner.

[0011] According to a first aspect, a device is proposed for characterizing the wear of a gas turbine engine comprising:

[0012] - an abradable material comprising a wear end adapted to be arranged in contact with a flow of gaseous fluid circulating from upstream to downstream of the gas turbine engine when the gas turbine engine is in operation, the abradable material being electrically conductive;

[0013] - a magnetic field generator adapted to emit a magnetic field in the abradable material;

[0014] - an electronic card configured to calculate information enabling characterize the wear of the gas turbine engine from a data relating to a physical response of said abradable material to said magnetic field.

[0015] According to advantageous and non-limiting features, taken alone or in any combination: - the magnetic field generator is adapted to be electrically connected to an energy source so as to form an electrical circuit, said data relating to a physical response of said abradable material to said magnetic field being a data relating to an inductance of the electrical circuit; - the device includes a capacitor electrically connected to the magnetic field generator and adapted to be in the electrical circuit, in which the data relating to the inductance of the electrical circuit is the resonant frequency of the electrical circuit and in which the electronic board is configured to measure said resonant frequency; - the magnetic field generator is a coil; - the magnetic field generator is in contact with the abradable material; - The device includes a communication module connected to the card electronic and configured to transmit information characterizing the wear of the gas turbine engine to a processing module data configured to characterize gas turbine engine wear based on information enabling the characterization of gas turbine engine wear.

[0016] According to a second aspect, a gas turbine engine is proposed comprising at least one device as previously presented, the device being arranged so that the wear end of the abradable material is in contact with a flow of gaseous fluid circulating from upstream to downstream of the gas turbine engine when the gas turbine engine is in operation.

[0017] Advantageously, the device is arranged in a hole drilled in the gas turbine engine, in particular the device is arranged in an endoscopic port of the gas turbine engine.

[0018] According to a third aspect, an aircraft comprising a gas turbine engine as previously presented is proposed.

[0019] According to a fourth aspect, a system is proposed for characterizing the wear of a gas turbine engine comprising:

[0020] - a device as previously described;

[0021] - a data processing module connected to the device, the processing module data being configured to determine a level of wear of the gas turbine engine from the information allowing to characterize the wear of the gas turbine engine.

[0022] According to a fifth aspect, a method is proposed for characterizing wear on a gas turbine engine using a system as described above, the method comprising the steps of:

[0023] - calculation, by the electronic card, of information enabling the characterization wear and tear on the gas turbine engine,

[0024] - determination, by the data processing module, of a wear level of the gas turbine engine based on information allowing the characterization of gas turbine engine wear. DESCRIPTION OF THE FIGURES

[0025] Other features and advantages of the present invention will become apparent from the following description of a preferred embodiment. This description will be given with reference to the accompanying figures, including:

[0026] - Figure 1 schematically illustrates a gas turbine engine comprising at least one device to characterize wear on the gas turbine engine;

[0027] - Figure [Fig. Ibis] schematically illustrates another embodiment of a gas turbine engine including at least one device for characterizing wear on the gas turbine engine;

[0028] - Figure 2 schematically illustrates a device for characterizing wear on a turbine engine gas arranged on an engine casing, the wear end of the abradable electronic board of the device being unworn;

[0029] - Figure 3 schematically illustrates a device for characterizing wear on a turbine engine gas arranged on an engine casing, the wear end of the device's abradable electronic circuit board being partially worn

[0030] - Figure 4 schematically illustrates a device for characterizing wear on a turbine engine gas arranged on an engine casing, the wear end of the abradable electronic board of the device being completely worn;

[0031] - [Fig.5] schematically shows a top view of a magnetic field generator;

[0032] - [Fig. 6] is an exploded and schematic view of a part of the device according to a another mode of implementation;

[0033] - Figure 7 schematically illustrates a system for characterizing wear on a turbine engine gas;

[0034] - Figure 8 shows the steps of a process for characterizing wear on a gas turbine engine. DETAILED DESCRIPTION OF THE INVENTION Motor and device

[0035] With reference to [Fig. 1], a gas turbine engine 2, or turbomachine, is proposed, which includes a gas generator 24 and optionally, particularly in the case of an aircraft engine, a fan 22, which may be shrouded or unshrouded.

[0036] In the example illustrated in [Fig.1], the gas generator 24 comprises, from upstream to downstream, the gases (gaseous fluid flow) flowing within the gas turbine engine 2 from upstream to downstream, a compressor 24A (or compressor section 24A), a combustion chamber 24B, a turbine 24C (or turbine section 24C) and an exhaust nozzle 26.

[0037] The blower 22 can be driven in rotation directly by a shaft 23 of the gas generator 24, for example a shaft of a low pressure body, or via a gearbox GB (“Gear Box”) or RGB (Anglo-Saxon acronym for “Reduction Gear Box”) mechanically connected to the compressor 24A.

[0038] The gas generator 24 can be of the twin-body type and comprise a low-pressure body and a high-pressure body.

[0039] The low-pressure body may include a low-pressure compressor 241A rotationally coupled with a low-pressure turbine 24IC via a low-pressure shaft, not shown.

[0040] The high-pressure body may include a high-pressure compressor 242A disposed downstream of the low-pressure compressor 241A and upstream of the chamber of combustion 24B, and a high-pressure turbine 242C, disposed downstream of the combustion chamber 24B and upstream of the low-pressure turbine 241C, and coupled in rotation with the high-pressure compressor 242A via a high-pressure shaft, not shown.

[0041] The compressor 24A of the gas generator 24 may include the low and high pressure compressors 241A and 242A. The turbine 24C of the gas generator 24 may include the low and high pressure turbines 241C and 242C.

[0042] The [Fig. 1] is schematic, each compressor and each turbine being able to have one or more stages, each stage comprising a moving wheel (rotor) and a stator.

[0043] The exhaust nozzle 26 allows the exhaust gases that have circulated in the gas turbine engine 2 to exit the gas turbine engine 2.

[0044] The gas turbine engine 2 further comprises a casing 17 corresponding to its outer shell.

[0045] The casing 17 can be in contact, on its external surface, with the exterior of the gas turbine engine 2 and, on its internal surface, with the air stream. The casing 17 can be composed of all or some of the fixed parts (i.e., the stators or the housings of the compressor impellers) of the compressors and turbines.

[0046] The internal surfaces of the housing 17 may or may not be coated with an abradable layer 14. This abradable layer 14 ensures good contact behavior, particularly when a rotor, for example of a compressor, comes into contact with the housing of this compressor.

[0047] Figure 1bis illustrates another embodiment of a gas turbine engine 2. This gas turbine engine 2 is particularly suitable for helicopters. This engine does not include a fan. It comprises a gas generator section with a centrifugal compressor 30 comprising two compression wheels 31, 32 respectively integral with a first coaxial turbine 33. The compression wheels 31, 32 are respectively designated first compressor 31 and second compressor 32. The air stream 37 inside the casing 17 is annular and extends from an air inlet 37a which guides the air to the axial inlet of the first compressor 31. The air inlet 37a may be axial or annular. The air compressed by the first compressor 31 is guided radially through a diffuser 37b. The air stream then forms a bend 37c so as to bring the air back towards the axis of the engine 2 to the axial inlet of the second compressor 32.The air is then guided to a combustion chamber 35 which supplies the first turbine 33 with hot gas. The expansion of the gases continues in a second turbine 34 of a second rotor attached to a power take-off shaft 23 for driving the load. The air stream is delimited by two coaxial walls, one of which is an internal wall 37i of the casing 17. In [Fig. Ibis], the bend 37c of the air stream is visible, downstream of the diffuser 37b. This bend... 37ci's function is to deflect the airflow from the diffuser towards the machine's axis. The gases are then expelled through the exhaust nozzle 26.

[0048] The gas turbine engine 2 includes a device 1 for characterizing wear of the gas turbine engine 2.

[0049] Figure 1 schematically illustrates a gas turbine engine 2 particularly suitable for airplanes, and Figure 1bis schematically illustrates a gas turbine engine 2 particularly suitable for helicopters. However, device 1 is not limited to use in a particular type of gas turbine engine 2.

[0050] The gas turbine engine 2, more specifically its internal components such as the compressor(s) and turbine(s), can wear, i.e., erode, due to particles present in the gaseous fluid flow F circulating within the gas turbine engine 2. The gaseous fluid may include air and / or exhaust gases. The particles are volatile particles such as sand or gravel that are stirred up when the aircraft incorporating the gas turbine engine 2 lands or takes off on unprepared surfaces. This wear leads to malfunctions of the gas turbine engine. It is therefore necessary to characterize it, in particular to measure it, so as to be able to precisely identify when engine maintenance is required.

[0051] By "characterizing wear on the gas turbine engine 2," it is understood that one or more characteristics of the wear are to be determined. Preferably, the aim is to determine a level of wear on the gas turbine engine 2. This level of wear can be determined, for example, from the wear thickness of the engine. The wear thickness of the engine can refer to a thickness of material in the gas turbine engine 2 that has disappeared through wear, i.e., erosion, or a remaining thickness of material in the gas turbine engine 2.

[0052] Device 1 is thus adapted to calculate information enabling the characterization of the wear of the gas turbine engine 2. From this information, which will be detailed later, a level of wear of the gas turbine engine 2 can be determined.

[0053] Furthermore, by "characterizing wear on the gas turbine engine 2", it is understood that one seeks to determine wear on at least one part of the gas turbine engine 2, in particular the part which is located near the device 1. However, this wear may allow the wear of another part of the gas turbine engine 2 to be determined.

[0054] With reference to Figures 2 to 4, the device 1 for characterizing wear on the gas turbine engine 2 comprises an abradable material 8. The abradable material 8 includes a wear end 80 adapted to be arranged in contact with a flow of gaseous fluid F circulating from upstream to downstream of the gas turbine engine 2 when the gas turbine engine 2 is in operation. In Figures 2 to 4, the device 1 is shown arranged on a housing 17 of the engine 2.

[0055] By "in operation" is meant a state of the gas turbine engine 2 in which the moving parts (rotors) of the turbines and compressors are driven in rotation so that an air circulation from upstream to downstream of the gas turbine engine 2 takes place.

[0056] More specifically, in the case of the gas turbine engine 2 illustrated in [Fig. 1], the fan 22 is driven in rotation by a turbine, advantageously the low-pressure turbine 241C, resulting in air circulation from the upstream to the downstream side of the gas turbine engine 2. Part of the air passing through the fan 22 (air stream) passes successively through the low-pressure compressor 241A, the high-pressure compressor 242A, and is then injected into the combustion chamber 24B. In the combustion chamber 24B, the air is mixed with fuel. The combustion of the fuel generates exhaust gases which circulate successively through the high-pressure turbine 242C, then through the low-pressure turbine 241C, and are discharged via the exhaust nozzle 26.

[0057] In the case of the gas turbine engine 2 illustrated in [Fig. Ibis], air flows in the air stream 37, from the air inlet 37a, to the first compressor 31, then to the rectifier 37b, then through the elbow 37c, then through the second compressor 32 and is injected into the combustion chamber 35. In the combustion chamber 35, the air is mixed with fuel. The combustion of the fuel generates exhaust gases which flow successively through the first turbine 33, then through the second turbine, and are discharged via the exhaust nozzle 26.

[0058] By "abradable," it is understood that the abradable material 8 can be worn, i.e., eroded. Advantageously, the abradable material 8 is made of a material that wears, due to particles in the gaseous fluid flow F, at the same rate as the gas turbine engine element 2 for which wear is to be characterized, or at a rate proportional to the wear rate of the gas turbine engine element 2 for which wear is to be characterized. Thus, it is easy to establish a correlation between the wear of the abradable material 8 and the wear of the gas turbine engine element 2 for which wear is to be characterized.

[0059] The abradable material 8 is electrically conductive. Preferably, the abradable material 8 comprises or is made of an electrically conductive metal.

[0060] In addition, the abradable material 8 is made of a material in which a magnetic field can circulate.

[0061] The abradable material 8 can take several forms. The shape is preferably adapted so as not to impair the aerodynamics of the airflow in the air stream. For example, it can take the form of a parallelepiped, a cylinder, or a progressive shape such as a teardrop. The shape of the cross-section of the abradable material 8 can be a polygon as illustrated for example in figures 2 and 4. Optionally, the polygon may include arcs of circles. In [Fig.2], the cross-section of the abradable material 8 has a rectangular shape (this may for example be the case for an abradable material 8 having the shape of a cylinder).

[0062] Advantageously, the abradable material 8 takes the form of a cylinder. In this case, the device 1 takes the form of an endoscopic plug and can therefore be arranged directly in an endoscopic port of the motor 2. This facilitates the use of the device 1 and avoids modification of the motor 2, thus allowing wear to be determined more economically.

[0063] Advantageously, to enhance the sensitivity of the device 1, the thickness of the abradable material 8 is advantageously kept to a minimum. Advantageously, the wear thickness is between 0.2 mm and 2 mm.

[0064] The abradable material 8 includes a wear end 80 adapted to be in contact with the gaseous fluid stream F when the gas turbine engine 2 is operating. Advantageously, the wear end 80 is adapted to protrude from the abradable material 8 into the gaseous fluid stream F. The wear end 80 is therefore the part of the abradable material 8 adapted to wear away, potentially to the point of disappearance.

[0065] As illustrated in [Fig.2], the abradable material 8 is complete and therefore unworn. Similarly, the abradable layer 14 coating the housing 17 is unworn.

[0066] Figure 3 illustrates the abradable material 8 being worn due to the flow of gaseous fluid F; it can be seen that the abradable material 8 has lost material. Similarly, the abradable layer 14 coating the housing 17 is worn and therefore thinner.

[0067] According to one embodiment, the abradable material 8 of [Fig.3] could correspond to a complete and therefore unworn abradable material 8.

[0068] Figure 4 illustrates the completely worn abradable material 8, i.e., the wear end 80 has disappeared. Similarly, the abradable layer 14 coating the housing 17 has disappeared.

[0069] The abradable layer 14, possibly present on the part of the motor 2 under study, is advantageously made of a material that erodes at the same rate as the abradable material 8. Consequently, the abradable layer 14 will be completely worn away if the abradable material 8 is completely worn away (i.e., the wear end 80 has disappeared), and vice versa. Thus, the wear of the abradable material 8 is directly representative of the wear of the part of the motor 2 under study. However, the abradable layer 14 can be made of a material that does not erode at the same rate as the abradable material 8. Therefore, the abradable material 8 may erode faster or slower than the abradable layer 14. Preferably, if the abradable layer 14 is made of a material that does not erode at the same rate as the abradable material 8, the abradable layer 14 is made of a material which erodes at a rate proportional to the wear rate of the abradable material 8.

[0070] The device 1 further includes a magnetic field generator 7 adapted to emit a magnetic field in the abradable material 8. An example of a magnetic field generator 7 is illustrated in [Fig.5].

[0071] The magnetic field generator 7 is preferably a coil 72.

[0072] The coil can be a solenoid, that is to say a long coil, more precisely a coil whose length exceeds ten times its radius.

[0073] The magnetic field generator 7 can be a coil in the form of a spring.

[0074] Advantageously, the coil comprises at least 10 turns, preferably at least 20 turns, and even more preferably at least 50 turns. The coil may comprise 100 turns. In [Fig. 5], the coil 72 comprises ten turns.

[0075] Alternatively, the magnetic field generator 7 can be a coil 72 printed on a circuit board (PCB) as illustrated in [Fig.5]. In other words, the coil 72 is flat.

[0076] The magnetic field generator 7 may comprise several layers, each layer comprising a set of a plurality of printed turns, the set of turns in each layer being electrically connected to at least one set of turns in another layer. Advantageously, the magnetic field generator 7 comprises four interconnected layers, each layer comprising ten turns as illustrated in [Fig. 6]. According to the embodiment illustrated in [Fig. 6], the magnetic field generator 7 is made of a plurality (four) of interconnected printed circuit boards (PCBs).

[0077] Advantageously, the magnetic field generator 7 has an inductance of at least 1 pH, preferably of at least 10 pH.

[0078] Advantageously, the magnetic field generator 7 comprises an electrically conductive material.

[0079] Advantageously, the magnetic field generator 7 comprises or is made of copper. In the case where the magnetic field generator 7 is a PCB, the magnetic field generator comprises an electrically insulating layer 71 such as epoxy or ceramic on which the coil 72, for example made of copper, is arranged.

[0080] Preferably, the magnetic field generator 7 is located near the abradable material 8. Preferably, the magnetic field generator 7 is less than 2 cm, and even more preferably less than 1 cm, from the abradable material 8. This ensures that the magnetic field generated by the magnetic field generator 7 reaches the abradable material 8 without being significantly attenuated. In other words, This ensures that the magnetic field generated by the magnetic field generator 7 will circulate in the abradable material 8 so as to induce eddy currents of sufficient intensity to be measured and / or so that a resonance frequency can be measured as will be described later.

[0081] Advantageously, the magnetic field generator 7 is in contact with the abradable material 8.

[0082] The magnetic field generator 7 can, for example, be glued to the abradable material 8. In such a way, the magnetic field generator 7 is considered to be in contact with the abradable material 8.

[0083] By "in contact," it is preferably understood that the magnetic field generator 7, in particular its electrically conductive parts such as turns, is separated from the abradable material 8 solely by an electrically insulating layer. For example, the electrically insulating layer may be an electrically insulating varnish or an electrically insulating adhesive. An electrically insulating adhesive is, in particular, free of metallic particles.

[0084] The magnetic field generator 7 is adapted to be supplied with electrical energy by an energy source 6, the generator thus being adapted to form an electrical circuit CE with the energy source 6.

[0085] According to an advantageous embodiment, the device 1 comprises the power source 6 electrically connected to the magnetic field generator 7 so as to form the electrical circuit CE.

[0086] Advantageously, the energy source 6 is a component capable of storing electrical energy, such as a battery. According to a preferred embodiment, the energy source 6 is capable of being charged remotely by an RFID (Radio Frequency Identification) reader.

[0087] Thus, advantageously, the device 1 includes an RFID receiver module, the power source 6 being connected and capable of being recharged via the RFID receiver module.

[0088] Advantageously, the device 1 further comprises a capacitor 5 electrically connected to the magnetic field generator 7. The capacitor 5 is therefore advantageously in the electrical circuit CE. In other words, the capacitor 5 is integrated into the electrical circuit CE. The capacitor 5 makes it possible to obtain, when the electrical circuit CE is powered, a resonant electrical circuit. The electrical circuit is of the LC type. The capacitor 5 advantageously has a capacitance that makes it possible to obtain an electrical circuit with a resonant frequency between 10 kHz and 10 MHz. This makes it possible to obtain a resonant frequency of the circuit high enough to be measurable. We will see from the following that this resonance frequency is representative of the inductance of the circuit and representative of the wear of the abradable material 8.

[0089] The device 1 includes an electronic card 10 configured to calculate information enabling the characterization of the wear of the gas turbine engine 2 from a data relating to a physical response of said abradable material 8 to the magnetic field.

[0090] Advantageously, the electronic board 10 includes the capacitor 5 as illustrated in figures 2 to 4.

[0091] Advantageously, the electronic card 10 is configured to measure the data relating to a physical response of said abradable material 8 to the magnetic field.

[0092] Alternatively, the electronic board 10 can be connected to a measurement module configured to measure data relating to the physical response of said abradable material 8 to the magnetic field. In this case, the device 1 therefore includes the measurement module adapted to be connected to the electronic board 10 so as to allow the transmission of data.

[0093] The electronic card 10 is advantageously electrically connected to the magnetic field generator 7. The electronic card 10 is advantageously connected to the electrical circuit CE, if applicable.

[0094] The electrical connection between the electronic board 10 and the magnetic field generator 7 is made in a known way, for example via electrical wires 73 or pins.

[0095] According to one embodiment, the electronic board 10 and the magnetic field generator 7 are the same physical object. In other words, the electronic board 10 and the magnetic field generator 7 are the same electrical / electronic component, said component having the functions of an electronic board 10 and a magnetic field generator 7.

[0096] The data relating to a physical response of said abradable material 8 to the magnetic field emitted by the magnetic field generator 7 may be, for example, a value of or data relating to a:

[0097] - inductance (for example in henries) of the electrical circuit CE;

[0098] - resonant frequency (for example in hertz) of the electrical circuit CE, particularly when the electrical circuit CE includes a capacitor 5;

[0099] - intensity (for example in tesla) of a magnetic field resulting from the field magnetic field emitted by the magnetic field generator 7 and a magnetic field created by an electric current induced in the abradable material 8;

[0100] - intensity (for example in amperes) of an electric current induced in the material abradable 8.

[0101] These data are in practice physically linked to each other. For example, the data relating to a physical response of said abradable material 8 may be a data relating to the inductance of the electrical circuit CE and this data relating to the inductance may be a resonance frequency value of the electrical circuit CE.

[0102] Advantageously, the electronic card 10 includes or is configured to be connected to a measurement module configured to measure an inductance, a resonant frequency, an intensity of a magnetic field (the module would therefore correspond to a magnetometer) and / or an electric current.

[0103] The information enabling the characterization of the wear of the gas turbine engine 2 may be the data relating to a physical response of said abradable material 8 to the magnetic field (see the examples listed above) or may be a data which derives from the data relating to a physical response of said abradable material 8 to the magnetic field.

[0104] For example, the data relating to a physical response of said abradable material 8 to the magnetic field emitted by the magnetic field generator 7 may be a resonance frequency value of the electrical circuit CE and the information enabling the characterization of the wear of the gas turbine engine 2 may be an inductance value of the electrical circuit CE, said inductance being calculated from the resonance frequency value using the following known formulas:

[0105] f = 1 2n\[LC

[0106] £=-¼ C(2nf)

[0107] with f the resonant frequency of the electrical circuit CE,

[0108] L the inductance of the electrical circuit CE, and

[0109] C the capacity of the electrical circuit CE.

[0110] The electronic card 10 is advantageously configured to calculate the information enabling the characterization of the wear of the gas turbine engine 2 from the data relating to a physical response of said abradable material 8 to the magnetic field emitted by the magnetic field generator 7.

[0111] The information enabling the characterization of the wear of the gas turbine engine 2 can be the wear thickness of the device 1.

[0112] The expression "wear thickness" can refer to several quantities. The wear thickness can be the worn thickness, i.e. the thickness that has disappeared, of the device 1.

[0113] The wear thickness can be the worn thickness of the abradable material 8. The worn thickness of the device 1 corresponds in practice to the worn thickness of the abradable material 8.

[0114] The wear thickness can be the remaining thickness of the device 1, in practice of the abradable material 8.

[0115] The wear thickness can be the instantaneous thickness of the abradable material 8.

[0116] By "instantaneous," it is understood to mean "current." In other words, an instantaneous value is a point value measured at a precise instant. The instantaneous thickness corresponds to a thickness at the instant when a magnetic field is generated by the magnetic field generator 7 in the abradable material 8.

[0117] The instantaneous thickness of the abradable material 8 (or remaining thickness of the abradable material 8) advantageously corresponds to the distance between a point on the surface of the wear end 80 and a point on the opposite surface (this surface being, in practice, the surface of the abradable material 8 adapted to face the magnetic field generator 7). The wear thickness can be an average wear thickness, as the abradable material 8 may not wear uniformly over its entire wear end 80.

[0118] The information enabling the characterization of the wear of the gas turbine engine 2 can be a wear volume of the abradable material 8.

[0119] The expression "wear volume" can refer to several quantities. The wear volume can be the worn volume, i.e. the volume lost, of the abradable material 8.

[0120] The wear volume can be the remaining volume of the abradable material 8.

[0121] The wear volume can be the instantaneous volume of the abradable material 8.

[0122] The instantaneous volume corresponds to a volume of the abradable material 8 at the instant to which a magnetic field is generated by the magnetic field generator 7 in the abradable material 8.

[0123] Thus, according to one embodiment, the electronic card 10 is configured to calculate the information enabling the characterization of the wear of the gas turbine engine 2 (which can be, for example, the wear thickness of the device 1 or the wear volume of the abradable material 8) from the data relating to a physical response of said abradable material 8 to the magnetic field emitted by the magnetic field generator 7.

[0124] Advantageously, the electronic card 10 is configured to access one or more charts which match the information enabling the characterization of the wear of the gas turbine engine 2 to a data relating to a physical response of said abradable material 8 to the magnetic field emitted by the magnetic field generator 7.

[0125] Advantageously, the electronic card 10 is configured to access one or more nomograms that correlate, on the one hand, the information enabling the characterization of the wear of the gas turbine engine 2 with, on the other hand, an inductance value of the electrical circuit CE, a resonance frequency value of the electrical circuit CE, and an intensity value of a magnetic field resulting from the magnetic field emitted by the magnetic field generator 7 and a magnetic field created by a current electric current induced in the abradable material 8 and / or an intensity value of an electric current induced in the abradable material 8.

[0126] The electronic board 10 can be configured to calculate information for characterizing the wear of the gas turbine engine 2 using a nomogram and data to which the electronic board 10 has access. For example, the electronic board can be configured to calculate the worn thickness of the abradable material 8 from the instantaneous thickness of the abradable material 8 (the instantaneous thickness may have been determined by the electronic board 10 using a nomogram). The worn thickness can be calculated using the following formula: initial thickness - instantaneous thickness. The initial thickness would therefore be, in this case, data accessible to the electronic board 10.

[0127] In the case where the data relating to a physical response of said abradable material 8 to the magnetic field is the resonant frequency, the device 1 advantageously includes an inductance converter component. This component is capable of supplying power to the electrical circuit CE and measuring a resonant frequency value. The inductance converter therefore includes the power source 6 and the electronic board 10, so that the electrical circuit CE is very simple and optimized. Advantageously, the inductance converter is configured to supply power to the electrical circuit CE such that the resonant frequency is between 10 kHz and 10 MHz.

[0128] The device 1 preferably includes a communication module 11 connected to the electronic card 10 and configured to transmit to an electronic data collection system 3 the information enabling the characterization of the wear of the gas turbine engine 2.

[0129] The communication module 11 can transmit information in a wired manner, for example with a wired CAN (Analog-to-Digital Converter) link or wirelessly, for example according to an RFID (Radio Frequency Identification) process.

[0130] When the communication module 11 is configured to transmit information wirelessly, it can be configured to be connected wirelessly to different devices 1 (more precisely, to different electronic boards 10). Thus, when a gas turbine engine 2 comprises several devices 1, only one communication module 11 needs to be present, said module 11 being configured to transmit information characterizing the wear of the engine 2 as determined by the respective electronic boards 10 of the devices 1. The engine 2 is therefore lighter.

[0131] The communication module 11 can therefore be an RFID transceiver which allows both data exchange and the supply of electrical energy to the device 1.

[0132] The communication module 11 is configured to allow the transmission of information enabling the characterization of the wear of the gas turbine engine 2 so that it can be analyzed in order to determine a level of wear of the engine 2 and thus to determine the need or not for maintenance of the engine 2.

[0133] The device 1 for characterizing wear of the gas turbine engine 2 advantageously comprises a body 9 adapted to carry the abradable material 8 and the magnetic field generator 7. The body 9 ensures the overall mechanical strength of the device 1 and the sealing of the device 1.

[0134] According to one embodiment, the magnetic field generator 7 is fixed to the body 9 and the abradable material 8 is fixed to the magnetic field generator 7. The abradable material 8 is therefore carried by the body 9 via the magnetic field generator 7.

[0135] According to one embodiment, the body 9 carries, on the one hand, the magnetic field generator 7 and, on the other hand, the abradable material 8, such that the magnetic field generator 7 and the abradable material 8 are in close proximity to each other or even in contact with each other. For example, the magnetic field generator 7 and the abradable material 8 can be inserted into the same cavity formed in the body 9.

[0136] Advantageously, the body 9 is adapted to further carry the electronic card 10 and / or the communication module 11.

[0137] The body 9 is advantageously adapted to carry the abradable material 8 and the magnetic field generator 7 so that a magnetic field emitted by the magnetic field generator 7 can penetrate the abradable material 8. In other words, the body 9 is advantageously adapted to carry the abradable material 8 and the magnetic field generator 7 so that the magnetic field generator 7 is oriented with respect to the abradable material 8 so as to promote the penetration of the magnetic field into the abradable material 8.

[0138] Advantageously, the body 9 is made of an electrically insulating material so as to prevent the magnetic field emitted by the magnetic field generator 7 from penetrating and attenuating the body 9. The body 9 can, for example, be made of ceramic.

[0139] The body 9 may include a cavity to accommodate the magnetic field generator 7 such that the magnetic field generator 7 is protected by the body 9. In addition, the abradable material 8 may also be embedded in the cavity. By embedded, it is understood that the abradable material 8 is partially embedded in the body 9, at least the wear end 80 of the abradable material 8 not being embedded in the body 9 so that the wear end 80 can be exposed to the gaseous fluid flow. This embodiment makes it possible, in particular, to avoid damaging the magnetic field generator 7 and / or the abradable material 8 when the device 1 is installed on the gas turbine engine 2.

[0140] Advantageously, the body 9 is adapted to separate the magnetic field generator 7 and, preferably still, the abradable material 8 from the housing 17 of the motor 2 to prevent the magnetic field from circulating in the housing 17 of the motor 2. Advantageously, the body 9 circumferentially surrounds the magnetic field generator 7. Advantageously, the body 9 circumferentially surrounds, at least partially, the abradable material 8.

[0141] The magnetic field generator can be glued, welded or sprayed onto the body 9.

[0142] The magnetic field generator 7 can be attached to the body 9 at once by insertion and by gluing and / or welding.

[0143] According to an embodiment illustrated in figures 2 to 4, the body 9 comprises an internal part 90 overmolded around the magnetic field generator 7 and the electronic board 10.

[0144] Advantageously, the internal part 90 is electrically insulating. Thus, advantageously, the internal part 90 comprises or is composed of resin or ceramic or any other electrically insulating material.

[0145] Alternatively, the inner portion 90 comprises or is composed of an electrically conductive material, the electrical wires 73 passing through the inner portion 90 being surrounded by an electrically insulating sheath. For example, the inner portion 90 may comprise or be made of a commercially available FR-4 type fiberglass and copper composite material and / or a metal.

[0146] As illustrated in figures 2 to 4, this internal part 90 preferably encloses the magnetic field generator 7, the electronic board 10, optionally a part of the abradable material 8 (preferably the part of the abradable material 8 which is not the wear end 80), the electrical wires 73 connecting the electronic board 10 to the magnetic field generator 7, and optionally the power source 6 and the communication module 11.

[0147] The internal part 90 allows the electrical wires 73 to be kept in position despite temperature variations and vibrations related to the operation of the gas turbine engine 2 or related to the transport and storage of the device 1. When the device 1 is arranged on the engine, the temperatures can vary, depending on the outside temperatures and the operation of the engine (for example if the engine is running, has been switched off recently or has been switched off for a sufficient time to cool down completely), between 0°C (or even less) and 150°C, or even greater than 200°C.

[0148] The body 9 advantageously comprises an external part 92 arranged around the internal part 90.

[0149] The external part 92 is preferably rigid.

[0150] By "rigid", it is understood that the external part 92 is rigid so that its modulus of elasticity (i.e. Young's modulus) is greater than 100GPa.

[0151] The external part 92 is preferably made of a metallic material.

[0152] Advantageously, the external part 92 is robust enough to withstand the same mechanical stresses as the housing (i.e., the fixed part of the motor 2) to which the device 1 is attached. The external part 92 may be made of Z15CNS25-20 type stainless steel, particularly when the internal part 90 is electrically insulating.

[0153] As illustrated in figures 2 to 4, this external part 92 surrounds the internal part 90 at least circumferentially. The external part 92 leaves at least the wear end 80 free.

[0154] The external part 92 may include one or more means of fastening, such as one or more screws, for fixing the device 1 to the gas turbine engine 2.

[0155] The external part 92 ensures the overall mechanical strength of device 1, the sealing of device 1.

[0156] According to one embodiment, the body 9 is a single piece. In other words, the body 9 is made from a single piece. The inner part 90 and the outer part 92 are therefore not physically separate. In this case, the body 9 is advantageously overmolded. Advantageously, the body 9 is rigid.

[0157] Device 1 is advantageously arranged on a fixed part of the gas turbine engine 2. Preferably, device 1 is arranged on the engine 2 so as to be accessible from outside the engine 2 to facilitate maintenance and data acquisition.

[0158] Advantageously, the device 1 is adapted to be arranged in an endoscopic port of the motor 2 and is therefore adapted to replace an endoscopic plug of the motor 2. The body 9, and more generally the device 1, therefore advantageously has the shape of a plug.

[0159] Advantageously, the abradable material 8 is fixed reversibly with respect to the device 1, where appropriate with respect to the body 9, so that the abradable material 8 can be exchanged, when it is too worn, for another abradable material 8.

[0160] Advantageously, the magnetic field generator 7 is also reversibly fixed with respect to the device 1, where appropriate with respect to the body 9, so that the magnetic field generator 7 can be exchanged, for example when it is no longer working, for another magnetic field generator 7.

[0161] According to one embodiment, the abradable material 8 is irreversibly fixed to the magnetic field generator 7 (for example, when the material abradable 8 is bonded or overmolded to the magnetic field generator 7). In this case, advantageously, the assembly comprising the abradable material 8 and the magnetic field generator 7 is fixed reversibly with respect to the other components of the device 1.

[0162] Similarly, the other components of device 1 are preferably interchangeable.

[0163] Thus, device 1 can be easily repaired without having to change all of these components.

[0164] As illustrated in Figures 1 and 1bis, the device 1 is advantageously arranged on fixed parts of the gas turbine engine 2, for example on the casing 17 of the gas turbine engine 2.

[0165] Here, it is understood that the device 1 is arranged on the motor 2 at least in its operating configuration, i.e., when a wear measurement is to be performed. Certain elements such as the electronic board 10, the communication module 11, and / or the magnetic field generator 7 can be deactivated or removed (and thus physically detached from the body 9 and the abradable material 8) when no wear measurement is being carried out. Thus, the electronic board 10, the communication module 11, and / or the magnetic field generator 7 can be attached to the body 9 only when a wear measurement is required, so that these elements are not permanently attached to the body 9, and therefore not permanently installed on the motor 2, even when the motor 2 is running.On the other hand, it is understood that the abradable material 8 and, where applicable, the body 9 remain in the same position on the motor 2 even if the electronic board 10 and / or the communication module 11 are removed.

[0166] Advantageously, the device 1 is arranged on the gas turbine engine 2 so that the wear end 80 of the abradable material 8 is in contact with a flow of gaseous fluid F circulating from upstream to downstream of the gas turbine engine 2 when the gas turbine engine 2 is in operation.

[0167] Preferably, the device 1 is arranged so that the electronic board 10 and the communication module 11 are not in contact with a gaseous fluid flow F when the gas turbine engine 2 is running. This protects these components. For example, the electronic board 10 and the communication module 11 can be arranged outside the gas turbine engine 2.

[0168] Advantageously, the device 1 is arranged so that the magnetic field generator 7 is not in contact with the gaseous fluid flow F when the gas turbine engine 2 is operating. Advantageously, the magnetic field generator 7 is laterally surrounded by a housing of the engine 2 as illustrated in Figures 2 to 4.

[0169] Thus, preferably, the device 1 is fixed to a housing so that a part of the device 1 is outside the engine and another part is inside the engine.

[0170] According to a preferred embodiment, if the electronic board 10 and / or the communication module 11 are permanently fixed to the body 9, they are protected by another housing and are therefore not in contact with the outside. This prevents wear on these components.

[0171] According to a preferred embodiment, the device 1 is arranged in an endoscopic port 21 of the gas turbine engine 2. Indeed, endoscopic ports are generally provided in the gas turbine engine 2 to allow inspection of the inside of the gas turbine engine 2 by means of an endoscope inserted into the engine 2 from the outside of the engine 2. These ports are generally, when not in use for inspection, plugged with endoscopic plugs. The device 1 can therefore replace an endoscopic plug. Thus, it is not necessary to modify a gas turbine engine 2 to allow its inspection by means of the device 1.

[0172] Alternatively, the device 1 can be arranged in a hole drilled in a casing of the gas turbine engine 2. The drilled hole gives access to the air stream, i.e. to the gas flow.

[0173] The device 1 can be arranged in different locations on the gas turbine engine 2, depending on the area of ​​the engine that one wishes to monitor.

[0174] For example, as illustrated in Figures 1 and 1bis, the device 1 can be arranged at the stator of the low-pressure compressor or at the rotor of the low-pressure compressor.

[0175] Device 1 can also be arranged at the leading edge of a compressor stator or at the leading edge of a compressor diffuser. In this case, device 1 is more exposed to particles in the gas flow (90° angle of attack) without generating any additional aerodynamic wake. Consequently, device 1 has no impact on the aerodynamic flow and therefore does not affect the performance of the gas turbine engine 2.

[0176] Device 1 can be arranged at an air inlet, for example air inlet 37a shown in [Fig. Ibis]. This position is advantageous because it is easy to arrange device 1 there.

[0177] Figures 1 and 1bis schematically illustrate different possible positions of device 1 in the gas turbine engine 2.

[0178] The gas turbine engine 2 may include several devices 1. System

[0179] With reference to [Fig.7], a system 100 is proposed for characterizing wear of a gas turbine engine 2.

[0180] The system 100 includes at least one device 1 as previously described.

[0181] The system 100 advantageously includes an electronic data collection system 3 adapted to be connected to the device 1. The electronic data collection system 3 can be connected to the device 1, more specifically to the communication module 11, by wired or wireless means.

[0182] For example, the system 100 may include a wireless reading system 4 adapted to be connected to the electronic data collection system 3 and configured to receive data from the communication module 11 using an RFID method. The wireless reading system 4 advantageously comprises an antenna and a reader connected to each other. In another embodiment, the electronic data collection system 3 includes the wireless reading system 4, i.e., the functions of the electronic data collection system 3 and the wireless reading system 4 are implemented by the same physical system.

[0183] The electronic data collection system 3 can be an electronic data collection box (Data Collector Box, DCB) or simply a memory, in general.

[0184] The system 100 includes a data processing module 12 adapted to be connected to the communication module 11 of the device 1, optionally via the electronic data collection system 3. The data processing module 12 can be integrated into the electronic data collection system 3.

[0185] The data processing module 12 is configured to characterize the wear of the gas turbine engine 2 from the information enabling the characterization of the wear of the gas turbine engine 2 and therefore from the data relating to a physical response of the abradable material 8 to the magnetic field of the magnetic field generator 7.

[0186] It is thus understood that, based on data relating to the physical response of the abradable material 8 to the magnetic field, the wear of the motor 2 can be characterized. Indeed, when the magnetic field generator 7 is powered, it emits a magnetic field. This first magnetic field induces an electric current (i.e., eddy currents) in the abradable material 8, and this electric current creates a second magnetic field. This second magnetic field will oppose the first magnetic field.

[0187] The more the abradable material 8 is worn, the more its volume decreases, and consequently, the lower the intensity of the electric current induced in the abradable material 8 and the weaker the second magnetic field created by this electric current. Thus, the more the abradable material 8 wears, the lower the intensity of the current created in the abradable material 8, the higher the intensity of the magnetic field resulting from the first and second magnetic fields, the higher the inductance of the electrical circuit, and the lower the resonant frequency. Therefore, there is a relationship between the wear of the abradable material 8, itself representative of the wear of the gas turbine engine 2, and the data relating to a physical response of the abradable material 8 to the magnetic field of the magnetic field generator 7.

[0188] Advantageously, the data processing module 12 is configured to determine a wear level of the engine 2 from the information enabling the characterization of the wear of the gas turbine engine 2.

[0189] The data processing module 12 is advantageously configured to analyze the information enabling the characterization of the wear of the gas turbine engine 2 and to deduce the level of wear of the gas turbine engine 2. For this purpose, the data processing module 12 is advantageously configured to determine, from the information, a data representative of the level of wear enabling the determination of the level of wear, possibly from a nomogram as will be described later.

[0190] The data representing the level of wear can be the information itself or be calculated from the information.

[0191] For example, the data relating to a physical response of said abradable material 8 to the magnetic field may be a resonance frequency value of the electrical circuit CE, the information allowing the wear of the gas turbine engine 2 to be characterized may also be this resonance frequency value of the electrical circuit CE and the data representing the wear level allowing the wear level to be determined, said data being determined by the data processing module 12, may be an inductance value of the electrical circuit CE determined from the information.

[0192] As a second example, the data representing the wear level can be the wear thickness of the device 1, which can be, for example, the worn thickness of the abradable material 8. This representative data may have been calculated from information that would be the instantaneous thickness. This information could have been determined by the electronic board 10 from data relating to a physical response of said abradable material 8 to the magnetic field emitted by the magnetic field generator 7, which would be the resonance frequency of the electrical circuit CE.

[0193] Thus, calculations (of data, information, etc.) can be performed by the electronic board 10 and / or by the data processing module 12. The electronic board 10 can be configured to simply take measurements, and the module 12 performs calculations based on those measurements. Alternatively, the electronic board 10 can be configured to measure and perform calculations based on its measurements, and the data processing module 12 can be configured to perform calculations based on the results provided by the electronic board 10. Consequently, different types of components can be chosen for the electronic board 10 and the data processing module 12, depending on the desired computing capacity of each.

[0194] Advantageously, the data processing module 12 is configured to determine a wear level of the gas turbine engine 2 from the representative wear level data and therefore, directly or indirectly, from the information enabling the characterization of the wear of the gas turbine engine 2.

[0195] The wear level of the gas turbine engine 2 can, for example, be expressed as a percentage, with 100% corresponding to an unworn engine so that the engine reaches 100% of its maximum performance and 0% corresponding to a worn engine so that the engine is out of service or can no longer be operated over its entire range of use with the same performance guarantees.

[0196] The wear level of the gas turbine engine 2 can also be expressed as the remaining service life of the gas turbine engine 2. For example, the wear level could be the number of days remaining before maintenance. Maintenance could be, for example, a simple inspection of the engine 2 or the replacement of a component of the engine 2, possibly following an inspection.

[0197] The level of wear can be expressed according to a class belonging to a group of classes such as: not worn, slightly worn, worn, very worn. The worn and very worn classes could correspond to wear requiring engine maintenance.

[0198] The wear level is used to indicate to an operator whether or not engine maintenance is required. Alternatively, or equally, the operator may be informed of the remaining time before maintenance and possibly the nature of the maintenance.

[0199] Advantageously, the data processing module 12 is configured to determine the wear level of the engine from a predetermined nomogram indicating a correspondence between the data representing the wear level obtained from the information enabling the characterization of the wear of the gas turbine engine 2 and a wear level of a gas turbine engine.

[0200] Advantageously, the nomogram indicates a correspondence between, on the one hand, the wear thickness of the device 1, i.e. the worn thickness of the abradable material 8 or the instantaneous thickness of the abradable material 8, and, on the other hand, a level of wear of the gas turbine engine 2. Advantageously, the nomogram indicates a correspondence between, on the one hand, the wear thickness of the device 1, i.e. the worn thickness of the abradable material 8, and, on the other hand, a level of wear of the gas turbine engine 2.

[0201] Alternatively, the nomogram indicates a correspondence between, on the one hand, the wear volume of the abradable material 8, and, on the other hand, a wear level of the gas turbine engine 2.

[0202] According to an advantageous embodiment in which the wear rate of the motor 2 is proportional to the wear rate of the abradable material 8, the nomogram is a conversion table linking the wear of the abradable material 8 to the wear of the motor 2. The conversion table results from internal knowledge and tests carried out on the abradable material and the motor 2.

[0203] Alternatively, the nomogram indicates a correspondence between, on the one hand, the resonance frequency of the electrical circuit CE or the inductance of the electrical circuit CE, and, on the other hand, a level of wear of the gas turbine engine 2.

[0204] The nomogram considered has been advantageously constructed on the basis of a gas turbine engine 2 having similar properties, or even being identical, to the gas turbine engine 2 that one seeks to monitor.

[0205] The nomogram under consideration was advantageously constructed using a gas turbine engine 2 in an environment similar to that in which the gas turbine engine 2 being monitored is used. The nomogram is therefore advantageously associated with a type of environment. An environment can be characterized by various parameters such as the nature of the soils and the type of volatile particles present. The environment can, for example, be associated with categories, such as "low erosion," "erosion," or "high erosion." There can therefore be several nomograms for the same engine 2, with a different nomogram being used depending on the environment. The environment can be determined, for example, based on the aircraft's GPS position.

[0206] The nomogram(s) can be stored by the electronic data collection system 3 or by the data processing module 12. The nomogram(s) can therefore be carried on board the aircraft or not, depending on whether the electronic data collection system 3 or the module 12 is carried on board or not.

[0207] The data processing module 12 is therefore preferably configured to determine the wear level of the gas turbine engine 2 corresponding to the representative wear level data from the nomogram (this data can be directly the information allowing to characterize the wear of the gas turbine engine 2).

[0208] The system 100 can be configured to determine the wear level automatically at regular intervals. Alternatively or in addition, the wear level determination can be implemented following an operator command.

[0209] For example, the system 100 may include a maintenance console 13 adapted to be connected to the data processing module 12 and adapted to be connected to the electronic data collection system 3 which would allow the operator to control and monitor the wear level.

[0210] The operator can be the aircraft pilot himself. Indeed, the entire system 100 can be carried on board the aircraft.

[0211] Alternatively, part of system 100, for example the data processing module 12 and the maintenance console 13, might not be included in the aircraft and only present at maintenance sites. The electronic data collection system 3, the wireless reading system 4 and even the communication module 11, the power source 6, the electronic board 10 and / or the magnetic field generator 7 may not be permanently installed in the aircraft. Process

[0212] With reference to [Fig.8], a method is further proposed for characterizing wear of a gas turbine engine 2 by means of a system 100 as previously presented.

[0213] The method can be implemented when the gas turbine engine 2 is running or stopped.

[0214] The process includes a step a) of emission, by the magnetic field generator 7, of a magnetic field called the first magnetic field.

[0215] In the embodiment illustrated in [Fig. 6], the first magnetic field is generated by layers comprising turns, thus forming a coil. The coil is supplied with an electric current that flows through each layer of turns of the coil in the SC direction. The coil thus generates the first magnetic field, which flows in the DC direction.

[0216] The first magnetic field penetrates the abradable material 8. The first magnetic field induces an electric current (eddy current phenomenon) in the abradable material 8. This electric current creates a second magnetic field which opposes the magnetic field emitted by the magnetic field generator 7 (i.e. the first magnetic field).

[0217] In the case where device 1 includes a capacitor 5, the electrical circuit CE is resonant and the electrical circuit CE can be characterized by a resonance frequency.

[0218] The process advantageously includes a step b) of measuring data relating to a physical response of the abradable material 8 to the magnetic field emitted by the magnetic field generator 7.

[0219] This data can be, for example, as explained previously, a resonance frequency value of the electrical circuit CE.

[0220] The measurement is advantageously implemented by the measurement module connected to the electronic card 10 or included in the electronic card 10.

[0221] The method includes a step c) of calculating, by the electronic board 10 of the device 1, information enabling the wear of the gas turbine engine 2 to be characterized from the data relating to a physical response of the abradable material 8 to the magnetic field. Said data was advantageously measured in step b).

[0222] As explained previously, this information can be for example one of the following quantities: the wear thickness of the device 1, the wear volume of the abradable material 8, the resonance frequency of the electrical circuit CE, the inductance of the electrical circuit CE, etc.

[0223] The method advantageously includes a step d) of calculating a data representative of the wear level by the data processing module 12 from the information.

[0224] Preferably, the method includes a step e) of determining a wear level of the gas turbine engine 2 as a function of the representative wear level data and the predetermined nomogram indicating a correspondence between the representative wear level data and a wear level of a gas turbine engine. Preferably, the determination step e) is implemented by the data processing module 12.

[0225] Thus, it is possible to monitor in real time and above all in a very simple and efficient way the state of wear of a gas turbine engine 2.

Claims

Demands

1. Device (1) for characterizing wear of a gas turbine engine (2) comprising: - an abradable material (8) including a wear end (80) adapted to be arranged in contact with a flow of gaseous fluid (F) flowing from upstream to downstream of the gas turbine engine (2) when the gas turbine engine (2) is in operation, the abradable material (8) being electrically conductive; - a magnetic field generator (7) adapted to emit a magnetic field in the abradable material (8); - an electronic card (10) configured to calculate information enabling the characterization of the wear of the gas turbine engine (2) from a data relating to a physical response of said abradable material (8) to said magnetic field.

2. Device (1) according to claim 1, wherein the magnetic field generator (7) is adapted to be electrically connected to an energy source (6) so as to form an electrical circuit (EC), said data relating to a physical response of said abradable material (8) to said magnetic field being data relating to an inductance of the electrical circuit (EC).

3. Device (1) according to claim 2, comprising a capacitor (5) electrically connected to the magnetic field generator (7) and adapted to be in the electrical circuit (EC), wherein the data relating to the inductance of the electrical circuit (EC) is the resonant frequency of the electrical circuit (EC) and wherein the electronic board (10) is configured to measure said resonant frequency.

4. Device (1) according to any one of claims 1 to 3, wherein the magnetic field generator (7) is a coil and / or is in contact with the abradable material (8).

5. Device (1) according to any one of claims 1 to 4, comprising a communication module (11) connected to the electronic board (10) and configured to transmit information enabling the characterization of the wear of the gas turbine engine (2) to a data processing module (12) configured to characterize the wear of the gas turbine engine (2) from the information enabling the characterization of the wear of the gas turbine engine (2).

6. Gas turbine engine (2) comprising at least one device (1) according to any one of claims 1 to 5, the device (1) being arranged so that the wear end (80) of the abradable material (8) is in contact with a flow of gaseous fluid (F) flowing from upstream to downstream of the gas turbine engine (2) when the gas turbine engine (2) is in operation.

7. Motor according to claim 6, wherein the device (1) is arranged in a hole drilled in the gas turbine motor (2), in particular the device (1) is arranged in an endoscopic port (21) of the gas turbine motor (2).

8. Aircraft comprising a gas turbine engine (2) according to any one of claims 6 and 7.

9. System (100) for characterizing wear of a gas turbine engine (2) comprising: - a device (1) according to any one of claims 1 to 5; - a data processing module (12) connected to the device (1), the data processing module (12) being configured to determine a level of wear of the gas turbine engine (2) from the information enabling the characterization of the wear of the gas turbine engine (2).

10. A method for characterizing the wear of a gas turbine engine (2) by means of a system (100) according to claim 9, the method comprising the steps of: - calculation (c), by the electronic card (10), of information enabling the characterization of the wear of the gas turbine engine (2), - determination (e), by the data processing module (12), of a level of wear of the gas turbine engine (2) from the information enabling the characterization of the wear of the gas turbine engine (2).

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