Device for characterizing gas turbine engine wear

Abstract

Device (1) for characterizing gas turbine engine wear, comprising: - an abradable electronic board (8) comprising at least one abradable electronic track (81), the abradable electronic board (8) being designed to be arranged in contact with a flow of gaseous fluid flowing from upstream to downstream of the gas turbine engine when the gas turbine engine is in operation; - a measurement electronic board (7) electrically connected to the abradable electronic track (81) so as to form an electric circuit (CE), the measurement electronic board (7) being suitable for determining information that enables the wear of the gas turbine engine (2) to be characterized.

Description

[0001] DESCRIPTION

[0002] TITLE: Device for characterizing wear on a gas turbine engine

[0003] FIELD OF INVENTION

[0004] 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.

[0005] STATE OF THE ART

[0006] Wear, or erosion, is a mode of damage to gas turbine engines, particularly those in aircraft. It involves the removal of material through abrasion of particles carried in the gaseous fluid flow circulating from the upstream to the downstream end of the gas turbine engine (air stream). This wear primarily affects the profiles of the blades and vanes of the stationary and moving parts of compressors and turbines.

[0007] 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 desert environments, wear can be significant and reduce the interval between two major maintenance operations to a few dozen flight hours.

[0008] One common solution to ensure 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 dedicated endoscopic ports and inspect the internal components via a control panel and monitor, using the video feed provided by the videoscope. The acquired image allows the technician to determine the engine's internal wear level and thus determine if maintenance is required.

[0009] Furthermore, as proposed in patent application no. FR3006013, it is possible to position an abradable material in the airflow channel that wears down as quickly as the engine part being monitored. This abradable material is visually inspected regularly to determine engine wear.

[0010] Most of the known methods require a maintenance technician and specific tools. These methods are not automatic.

[0011] Automated wear measurement methods also exist, but these are implemented only by gas turbine engine manufacturers and are primarily used for break-in tests before delivery to customers. These tests are therefore carried out under very specific and controlled conditions. However, the stresses faced by aircraft operators require a technology that can characterize the wear of the various components of gas turbine engines more precisely, robustly, reliably, and reproducibly.

[0012] Therefore, there is currently no satisfactory technology that allows for real-time, accurate, robust, reliable and reproducible measurement of wear in gas turbine engines.

[0013] DESCRIPTION OF THE INVENTION

[0014] One aim 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.

[0015] According to one aspect, a device is proposed to characterize the wear of a gas turbine engine comprising:

[0016] - an abradable electronic board comprising at least one abradable electronic track, the abradable electronic board being 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;

[0017] - an electronic measurement card electrically connected to the abradable electronic track so as to form an electrical circuit, the electronic measurement card being adapted to determine information enabling the characterization of the wear of the gas turbine engine.

[0018] According to advantageous and non-limiting features, taken alone or in any combination: the information enabling the characterization of the wear of the gas turbine engine is a measurement of the resistance of the electrical circuit; the device comprises a stack of several abradable electronic tracks, each abradable electronic track being electrically connected to the measuring electronic board, the abradable electronic tracks being electrically mounted in parallel with each other; the device comprises a body adapted to carry the abradable electronic board and the measuring electronic board, the body comprising an inner part overmolded around the abradable electronic board and the measuring electronic board, said inner part being flexible, and an outer part arranged around the inner part and being rigid;The device includes a communication module connected to the electronic measurement board and configured to transmit information to characterize the wear of the gas turbine engine to a data processing module configured to characterize the wear of the gas turbine engine from the information used to characterize the wear of the gas turbine engine.

[0019] According to a second aspect, a gas turbine engine is proposed comprising at least one device for characterizing wear of a gas turbine engine as previously presented, the device being arranged so that the abradable electronic board 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.

[0020] According to advantageous and non-limiting features, 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 engine.

[0021] According to a third aspect, an aircraft is proposed that includes a gas turbine engine as previously presented.

[0022] According to a fourth aspect, a system is proposed for characterizing the wear of a gas turbine engine comprising: a device for characterizing the wear of a gas turbine engine as previously presented; a data processing module connected to the device, the data processing module being configured to determine a level of wear of the gas turbine engine from the information enabling the characterization of the wear of the gas turbine engine.

[0023] According to a fifth aspect, a method is proposed for characterizing the wear of a gas turbine engine using a system for characterizing the wear of a gas turbine engine as described previously. The method comprises the steps of: (a) determining, by the electronic measurement board, information enabling the characterization of the wear of the gas turbine engine; and (b) determining, by the data processing module, a wear level of the gas turbine engine from the information enabling the characterization of the wear of the gas turbine engine. DESCRIPTION OF FIGURES

[0024] 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, of which: Figure 1 schematically illustrates a gas turbine engine comprising at least one device for characterizing wear of the gas turbine engine; Figure 1 bis schematically illustrates another embodiment of a gas turbine engine comprising at least one device for characterizing wear of the gas turbine engine; Figure 2 schematically illustrates a device for characterizing wear of the gas turbine engine arranged on an engine casing, the wear end of the abradable electronic board of the device being unworn; Figure 2 bis schematically illustrates, according to another embodiment, a device for characterizing wear of the gas turbine engine arranged on an engine casing, the wear end of the abradable material of the device being unworn;Figure 3 schematically illustrates a device for characterizing wear on a gas turbine engine mounted on an engine casing, with the wear end of the device's abradable electronic board partially worn; Figure 4 schematically illustrates a device for characterizing wear on a gas turbine engine mounted on an engine casing, with the wear end of the device's abradable electronic board completely worn; Figure 5 schematically illustrates the device in more detail than in Figures 2 to 4; Figure 6 schematically illustrates an example of an abradable electronic track on the abradable electronic board; Figure 7 is an exploded view of a measurement electronic board connected to several tracks of an abradable electronic board of the device; Figure 8 schematically illustrates a measurement electronic board connected to several tracks of an abradable electronic board of the device.Figure 9 schematically represents a system for characterizing wear on a gas turbine engine; Figure 10 represents the evolution of the resistance of an electrical circuit formed by an electronic measuring board and an abradable electronic board including an abradable electronic track as a function of the wear of the abradable electronic board; Figure 11 represents the evolution of the resistance of an electrical circuit formed by an electronic measuring board and an abradable electronic board including four abradable electronic tracks as a function of the wear of the abradable electronic board; Figure 12 represents the steps of a process for characterizing wear on a gas turbine engine.

[0025] DETAILED DESCRIPTION OF THE INVENTION

[0026] Motor and device

[0027] With reference to Figure 1, a gas turbine engine 2, or turbomachine, is proposed, which includes a gas generator 24 and possibly, particularly in the case of an aircraft engine, a fan 22, which may be shrouded or unshrouded.

[0028] In the example illustrated in Figure 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.

[0029] 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.

[0030] The 24 gas generator can be of the twin-body type and include a low-pressure body and a high-pressure body.

[0031] The low-pressure unit may include a low-pressure compressor 241 A rotationally coupled with a low-pressure turbine 241 C via a low-pressure shaft, not shown.

[0032] The high-pressure body may include a high-pressure compressor 242A disposed downstream of the low-pressure compressor 241 A and upstream of the combustion chamber 24B, and a high-pressure turbine 242C, disposed downstream of the combustion chamber 24B and upstream of the low-pressure turbine 241 C, and coupled in rotation with the high-pressure compressor 242A by means of a high-pressure shaft, not shown.

[0033] The compressor 24A of the gas generator 24 may include the low-pressure and high-pressure compressors 241A and 242A. The turbine 24C of the gas generator 24 may include the low-pressure and high-pressure turbines 241C and 242C. Figure 1 is schematic; each compressor and each turbine may have one or more stages, each stage comprising a rotating wheel (rotor) and a stator.

[0034] The exhaust nozzle 26 allows the exhaust gases that have circulated in the gas turbine engine 2 to exit the gas turbine engine 2.

[0035] The gas turbine engine 2 further includes a casing 17 corresponding to its outer shell.

[0036] 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 stationary parts (i.e., the stators) of the compressors and turbines.

[0037] 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.

[0038] Figure 1 bis illustrates another embodiment of a gas turbine engine 2. This gas turbine engine 2 is particularly suitable for helicopters. Notably, this engine does not include a fan. It comprises a gas generator section with a centrifugal compressor 30 including two compression wheels 31 and 32, respectively attached to a first coaxial turbine 33. The compression wheels 31 and 32 are referred to as the first compressor 31 and second compressor 32, respectively. 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 can 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, which is connected to a power take-off shaft 23 for driving the load. The air stream is delimited by two coaxial walls, including an internal wall 37i of the casing 17. In Figure 1 bis, the bend 37c of the air stream is shown, downstream of the diffuser 37b. This bend 37c serves to deflect the airflow from the diffuser towards the machine's axis. The gases are then expelled through the exhaust nozzle 26.

[0039] The gas turbine engine 2 includes a device 1 for characterizing wear of the gas turbine engine 2 illustrated in figures 2 to 5.

[0040] Figure 1 schematically represents a gas turbine engine 2, particularly suitable for airplanes, and Figure 1 bis schematically represents 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.

[0041] 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 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 containing the gas turbine engine 2 lands or takes off on unprepared surfaces. This wear leads to malfunctions in the gas turbine engine. It is therefore necessary to characterize it, particularly by measuring it, in order to precisely identify when engine maintenance is required.

[0042] By "characterizing the wear of the gas turbine engine 2," we mean determining one or more characteristics of the wear. Preferably, we seek 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 the thickness of material in the gas turbine engine 2 that has been removed by wear, i.e., by erosion, or to the remaining thickness of material in the gas turbine engine 2.

[0043] Furthermore, by "characterizing wear on the gas turbine engine 2", it is understood that we seek to determine wear on at least one part of the gas turbine engine 2, in particular the part which is located near device 1. However, this wear may allow us to determine the wear on another part of the gas turbine engine 2.

[0044] Device 1 is thus advantageously suited to determine information enabling the characterization of the wear of the gas turbine engine 2.

[0045] Advantageously, this information is a resistance measurement of an abradable electronic board 8. Thus, advantageously, device 1 is suitable for measuring the resistance of an abradable electronic board 8 which will allow the wear of motor 2 to be characterized.

[0046] The information can be another quantity, for example a worn thickness of the abradable electronic board 8 or an instantaneous thickness of the abradable electronic board 8.

[0047] From this information, a representative value for the wear level of the gas turbine engine 2 (which is advantageously a value relating to the wear of the abradable electronic board 8) can be determined. From this value, we will see later that a wear level of the gas turbine engine 2 can be determined.

[0048] With reference to Figures 2 to 5, the device 1 for characterizing wear on the gas turbine engine 2 comprises an abradable electronic circuit board 8. The abradable electronic circuit board 8 is adapted to be, at least partially, arranged in contact with the flow of gaseous fluid F circulating from upstream to downstream of the gas turbine engine 2 when the gas turbine engine 2 is operating. In Figures 2 to 4, the device 1 is shown arranged on a housing 17 of the engine 2.

[0049] 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 air circulates from upstream to downstream of the gas turbine engine 2.

[0050] More specifically, in the case of the gas turbine engine 2 illustrated in Figure 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 end 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 that circulate successively through the high-pressure turbine 242C, then through the low-pressure turbine 241C, and are discharged via the exhaust nozzle 26.

[0051] In the case of the gas turbine engine 2 illustrated in Figure 1 bis, 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.

[0052] By "abradable," it is understood that the abradable electronic board 8 can be worn, i.e., eroded. Advantageously, the abradable electronic board 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.

[0053] The abradable circuit board 8 comprises at least one abradable circuit trace 81. The abradable circuit trace 81 is electrically conductive. In Figures 2 to 5, the abradable circuit board 8 is shown schematically, and the abradable circuit trace(s) 81 are not shown. Figure 5 illustrates a schematic cross-sectional view of the abradable circuit traces 81. Some abradable circuit traces 81 are clearly visible in Figures 6 and 7.

[0054] Preferably, the abradable electronic track(s) 81 comprise or are made of copper, aluminum and / or some other electrical conductor.

[0055] The abradable electronic track 81 can take several forms. For example, it can take the form of a spiral as illustrated in Figure 6.

[0056] Advantageously, the abradable electronic track 81 has a resistance greater than or equal to 1 pO, preferably greater than or equal to 1000 pO.

[0057] Preferably, the abradable electronic track 81 has a length greater than or equal to 1 cm, preferably greater than or equal to 10 cm. Thus, the abradable electronic track 81 has a resistance high enough to allow for its measurement.

[0058] Preferably, the abradable electronic track 81 has a width greater than or equal to 5 pm, preferably greater than or equal to 100 pm.

[0059] Preferably, the abradable electronic track 81 has a thickness greater than or equal to 5 pm, preferably greater than or equal to 100 pm.

[0060] Advantageously, this abradable electronic track 81 is supported by a support layer 82 which is electrically insulating.

[0061] The support layer 82 can, for example, be made of resin.

[0062] Advantageously, the abradable electronic track 81 is arranged homogeneously on the support layer 82. In other words, the abradable electronic track 81 is preferably not positioned on only a part (for example not only on one half) of the support layer 82.

[0063] The abradable electronic track 81, and the support layer 82 if present, may be coated with an abradable layer (which may be similar to the abradable layer 14 of the housing 17) in order to reduce the wear rate in the event that the abradable electronic track 81 wears too rapidly relative to the gas turbine engine 2 (or the monitored portion of the gas turbine engine 2). Advantageously, only the outermost abradable electronic track 81, i.e., the first track of a new device 1 that will wear, is coated with such an abradable layer.

[0064] In one embodiment, the support layer 82 may further comprise fiberglass. This makes it possible to obtain an abradable electronic track 80 that is more resistant to high temperatures (for example, above 150°C or even above 400°C in the case of a helicopter's air stream). This makes it possible to reduce the wear rate in the event that the abradable electronic track 81 wears too rapidly relative to the gas turbine engine 2 (or the monitored part of the gas turbine engine 2).

[0065] According to an embodiment illustrated in Figures 5 and 7, the abradable electronic board 8 comprises a stack of several abradable electronic tracks 81. Each abradable electronic track 81 is electrically connected to the measuring electronic board 7. The abradable electronic tracks 81 are electrically connected in parallel with each other. Figure 8 schematically illustrates the parallel connection of the abradable electronic tracks 81.

[0066] The abradable electronic tracks 81 can be identical or different from each other in terms of shape, size and arrangement.

[0067] Each abradable electronic track 81 is advantageously separated from another abradable electronic track 81 by an electrically insulating support layer 82. This prevents any short circuit between the abradable electronic tracks 81.

[0068] Device 1 further includes an electronic measuring card 7 electrically connected to the abradable electronic track 81, thus forming an electrical circuit CE.

[0069] Advantageously, the electronic measuring board 7 is electrically connected to the abradable electronic track 81 via electrical wires 71.

[0070] The electronic measuring card 7 is adapted to determine information enabling the characterization of engine wear 2.

[0071] Advantageously, this information is a resistance measurement of the electrical circuit. The measuring electronic board 7 is therefore preferably configured to measure the resistance of the electrical circuit. The measuring electronic board 7 is advantageously an ohmmeter.

[0072] If the abradable electronic board 8 includes a single abradable electronic track 81, the measuring electronic board 7 is therefore suitable for measuring the resistance of said abradable electronic track 81.

[0073] The electronic measuring board 7 is therefore adapted to generate the flow of an electric current in the electrical circuit CE (i.e. in the abradable electronic track(s) 81) and thus to measure its resistance.

[0074] Preferably, the electronic measuring card 7 has a sensitivity of 0.1 pO.

[0075] As shown schematically in Figures 5, 7, and 8, when the device 1 comprises several abradable electronic tracks 81, each track is electrically connected to the measuring electronic board 7, forming an electrical circuit in which each abradable electronic track 81 is mounted in parallel with the other tracks 81. Figure 7 illustrates an exploded view of a measuring electronic board 7 connected to several abradable electronic tracks 81 of an abradable electronic board 8. The abradable electronic board 8 includes a wear end 80 that is adapted to be in contact with the gaseous fluid stream F when the gas turbine engine 2 is running. Advantageously, the wear end 80 is adapted to protrude from the abradable electronic board 8 into the gaseous fluid stream F. The wear end 80 is therefore the part of the abradable electronic board 8 that is adapted to wear away, potentially to the point of disappearance.

[0076] The wear end 80 advantageously includes all the abradable electronic tracks 81 of the abradable electronic board 8. In other words, the abradable electronic tracks 81 are intended to be worn.

[0077] As illustrated in Figures 2 and 2bis, the abradable electronic board 8 is complete and therefore unworn. Similarly, the abradable layer 14 coating the housing 17 is unworn.

[0078] Figure 3 illustrates the abradable electronic board 8 undergoing wear due to the gaseous fluid flow F. It can be seen that the abradable electronic board 8 has lost material. Some abradable electronic traces 81 and support layers 82 are worn. Similarly, the abradable layer 1 coating the housing 17 is worn and therefore thinner.

[0079] According to one embodiment, the abradable electronic board 8 of figure 3 could correspond to a complete and therefore unworn abradable electronic board 8.

[0080] Figure 4 illustrates the completely worn abradable electronic board 8, i.e., the wear end 80, and consequently all the abradable electronic traces 81, have disappeared. Similarly, the abradable layer 14 coating the housing 17 has disappeared.

[0081] 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 circuit board 8. Consequently, the abradable layer 14 will be completely worn if the abradable circuit board 8 is completely worn (i.e., the wear end 80 has disappeared), and vice versa. Thus, the wear of the abradable circuit board 8 is directly representative of the wear of the part of the motor 2 under study. However, the abradable layer 14 may be made of a material that does not erode at the same rate as the abradable circuit board 8. Consequently, the abradable circuit board 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 that erodes at a rate proportional to the wear rate of the abradable material 8.

[0082] Advantageously, the device 1 includes a communication module 11 connected to the electronic measurement board 7. The communication module 11 is configured to transmit to a data processing module 12, optionally via an electronic data collection system 3, a resistance measurement of the electrical circuit CE.

[0083] We will see later that the data processing module 12 and the electronic data collection system 3 may or may not be carried on board the aircraft.

[0084] The communication module 11 can transmit information wired, for example with a wired ADC (Analog-to-Digital Converter) link or wirelessly, for example using an RFID (Radio Frequency Identification) process.

[0085] The communication module 11 can be the electronic measuring board 7 itself. In other words, the electronic measuring board 7 can be configured to transmit the information enabling the characterization of the wear of the motor 2 (advantageously the resistance measurements of the electrical circuit CE) which the electronic measuring board 7 determines itself.

[0086] The device 1 for characterizing wear of the gas turbine engine 2 advantageously includes a body 9 adapted to carry the abradable electronic board 8 and the measuring electronic board 7.

[0087] Advantageously, the body 9 includes an internal part 90 overmolded around the abradable electronic board 8 and the measuring electronic board 7. The internal part 90 is preferably flexible.

[0088] By "flexible", it is understood that the internal part 90 is flexible so that its modulus of elasticity (i.e. Young's modulus) is less than 100 GPa.

[0089] Advantageously, the internal part 90 is electrically insulating. Thus, advantageously, the internal part 90 comprises or is composed of resin, ceramic, or any other electrically insulating material.

[0090] Alternatively, the inner portion 90 comprises or is composed of an electrically conductive material, the electrical wires 71 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.

[0091] As illustrated in figures 2, 3, 4 and 5, this internal part 90 preferably encloses the electronic measuring board 7, a part of the abradable electronic board 8 (preferably the part of the abradable electronic board 8 which is not the wear end 80) and the electrical wires 71 connecting the electronic measuring board 7 to the abradable electronic board 8.

[0092] In the embodiment shown in Figure 2bis, the inner portion 90 encloses the measuring electronic board 7 and the electrical wires 71 connecting the measuring electronic board 7 to the abradable electronic board 8. The abradable electronic board 8 is not enclosed, making it suitable for direct contact with the housing 17 of the gas turbine engine 2. This improves aerodynamics. In this case, the abradable electronic board 8 can, for example, be bonded and / or soldered to the inner portion 90.

[0093] The internal part 90 allows the electrical wires 71 to remain 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, temperatures can vary, depending on the outside temperatures and whether the engine is running or not, between 0°C (or even less) and 150°C, or even 200°C.

[0094] The body 9 advantageously comprises an external part 92 arranged around the internal part 90.

[0095] The external part 92 is preferably rigid.

[0096] By "rigid", it is understood that the external part 92 is rigid such that its modulus of elasticity (i.e. Young's modulus) is greater than 100GPa.

[0097] Advantageously, the external part 92 is robust enough to withstand the same mechanical stresses as the housing (i.e., the fixed part of the engine 2) to which the device 1 is attached. Advantageously, the external part 92 is made of Z15CNS25-20 type stainless steel.

[0098] As illustrated in figures 2 to 5, this external part 92 surrounds at least, partially or not, circumferentially the internal part 90. The external part 92 leaves at least the wear end 80 free.

[0099] 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.

[0100] The external part 92 ensures the overall mechanical strength of device 1, the sealing of device 1.

[0101] 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.

[0102] Advantageously, the device 1 is adapted to be arranged in an endoscopic port of the motor 2 and is therefore suitable 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.

[0103] As illustrated in Figures 1 and 1 bis, 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. Advantageously, the device 1 is arranged on the gas turbine engine 2 so that the wear end 80 of the abradable electronic board 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.

[0104] Preferably, the device 1 is arranged so that the electronic measuring board 7 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 measuring board 7 and the communication module 11 can be arranged outside the gas turbine engine 2.

[0105] Therefore, preferably, device 1 is fixed to the casing so that one part of device 1 is outside the engine and another part is inside the engine.

[0106] In a preferred embodiment, 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 using an endoscope inserted into the engine 2 from the outside. These ports are generally, when not in use for inspection, plugged with endoscopic plugs. Device 1 can therefore replace an endoscopic plug. Thus, it is not necessary to modify a gas turbine engine 2 to allow its inspection using device 1.

[0107] Alternatively, device 1 can be arranged in a hole drilled in a casing of the gas turbine engine 2.

[0108] 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.

[0109] For example, as illustrated in figures 1 and 1 bis, device 1 can be arranged at the stator of the low pressure compressor or at the rotor of the low pressure compressor.

[0110] 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 no impact on the performance of the gas turbine engine 2.

[0111] Device 1 can be arranged at an air inlet, for example air inlet 37a shown in Figure 1 bis. This position is advantageous because it is easy to arrange Device 1 there. Figures 1 and 1 bis schematically illustrate different possible positions of Device 1 in the gas turbine engine 2.

[0112] The gas turbine engine 2 can include several devices 1.

[0113] System

[0114] With reference to figure 9, a system 100 is proposed to characterize wear on a gas turbine engine 2.

[0115] System 100 includes at least one device 1 as previously described.

[0116] 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.

[0117] For example, 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; that is, the functions of the electronic data collection system 3 and the wireless reading system 4 are implemented by the same physical system.

[0118] The electronic data collection system 3 can be an electronic data collection box (Data Collector Box, DCB) or simply a memory, in general.

[0119] The system 100 includes a data processing module 12 adapted to be connected to the device 1, possibly via the electronic data collection system 3. The data processing module 12 can be integrated into the electronic data collection system 3.

[0120] The data processing module 12 is configured to determine a wear level of the gas turbine engine 2 from the information enabling the characterization of the wear of the engine 2. More precisely, the data processing module 12 is advantageously configured to calculate a data representative of the wear level of the engine 2 from the information.

[0121] According to one embodiment, the information enabling the characterization of the wear of the motor 2 is a resistance measurement of the electrical circuit CE and the data relates to the wear of the abradable electronic board 8. From the resistance measurement, it is possible to determine a data relating to the wear of the abradable electronic board 8 (which can be, for example, its worn thickness) and to deduce a wear of the gas turbine motor 2 as will be described below.

[0122] Each abradable electronic trace 81 of the abradable electronic board 8 is considered to be of significant length. The resistance of each abradable electronic trace 81 is therefore expressed as follows: with R the resistance of the abradable electronic track 81, p L the linear resistivity of the abradable electronic track 81, l the width of the abradable electronic track 81, and e the thickness of the abradable electronic track 81.

[0123] The thickness of an abradable electronic trace 81 can therefore be expressed as follows:

[0124] PL el * R

[0125] If the abradable electronic board 8 comprises a single abradable electronic track 81, the resistance of the electrical circuit CE, denoted R CE , is expressed as the resistance of a single track, that is to say:

[0126] Figure 10 illustrates the evolution of the CE circuit resistance as a function of a data point relating to the wear of the abradable electronic board 8. The resistance is expressed, for example, in ohms. The data point relating to the wear of the abradable electronic board 8 could, for example, be the worn (i.e., disappearant) thickness of the abradable electronic board 8 or its instantaneous thickness.

[0127] The thickness of the abradable electronic track 81 can therefore be expressed as follows:

[0128] Thus, there is a correlation between the thickness of a track 81 and its resistance. Knowing the resistance of the abradable electronic track 81 allows us to determine its thickness and, consequently, a value related to its wear and therefore to the wear of the abradable electronic board 8. We will see that this value is representative of the wear level of the gas turbine engine 2.

[0129] The more the abradable electronic board 8 wears, the more the thickness of the exposed abradable electronic trace 81 in contact with the gaseous fluid flow F decreases. Furthermore, as can be understood from the formula above, a decrease in thickness e is indicated by an increase in resistance.

[0130] Thus, depending on the resistance of the electrical circuit CE, the data processing module 12 can determine a data relating to the wear of the abradable electronic board 8, which is a data representative of the wear level of the gas turbine engine 2. The data relating to the wear of the abradable electronic board 8 can be the instantaneous thickness of the abradable electronic board 8 or the worn thickness (i.e., the eroded, disappeared thickness) of the abradable electronic board 8. Alternatively, the data relating to the wear of the abradable electronic board 8 can be the resistance measurement of the electrical circuit CE.

[0131] By "instantaneous," we mean "current." In other words, an instantaneous value is a point value measured at a precise moment.

[0132] The instantaneous thickness corresponds to the effective thickness of the abradable electronic board 8 at the instant when a resistance measurement is implemented by the electronic measuring board 7.

[0133] According to one embodiment, the data processing module 12 is advantageously configured to determine the instantaneous thickness of the abradable electronic board 8 as a function of the thickness of the abradable electronic track 81 and parameters relating to the abradable electronic board 8 such as the thickness of the support layer(s) 82, parameters to which the data processing module 12 has access.

[0134] According to one embodiment, the data processing module 12 is advantageously configured to determine the worn thickness of the abradable electronic board 8, in particular from the initial thickness of the abradable electronic board 8 (i.e. before the abradable electronic board 8 is worn) and the instantaneous thickness of the abradable electronic board 8.

[0135] In the case of an abradable electronic board 8 comprising several abradable electronic traces 81, for example four traces 81, the relationship between the resistance of the electrical circuit CE, denoted R CE , and the resistances of each abradable electronic track 81, denoted R , R2, R3 and R4, are expressed as follows: with R t the resistance of a first track 81,

[0136] R2, the resistance of a second track 81,

[0137] R3, the resistance of a third track 81, and

[0138] R4, the resistance of a fourth track 81. The tracks are arranged in a stack so that the first track is the first to wear out. Then, once the first track is gone, the second track will be the next to wear out, and so on.

[0139] Therefore, R CE is expressed in the following way:

[0140] Resistance R t for each track 81 with index i is expressed: with p L i the linear resistivity of the track with index i,

[0141] Let I be the width of the track with index i, and g be the thickness of the track with index i.

[0142] Figure 11 illustrates the evolution of the CE circuit resistance as a function of the wear of the abradable electronic board 8, and therefore as a function of the wear of the abradable electronic traces 81. Plateaus PÀ1, PÀ2, and PÀ3 are observed, which are reached at the end of the wear of a trace 81 (i.e., when a trace 81 has disappeared) and which correspond to the wear of a support layer 82. When the resistance increases again, it means that a support layer 82 has disappeared due to wear and that a new trace 81 is being worn. PÀ1 is reached when the first trace (the first to be worn, which is the one with resistance R4 in Figure 8) has disappeared due to wear. PÀ2 is reached when the second trace (the one with resistance R2 in Figure 8) has disappeared due to wear. PÀ3 is reached when the third trace (the one with resistance R3 in Figure 8) has disappeared due to wear. PA4 is reached when a fourth track (the resistance track R4 in figure 8) has disappeared due to wear.

[0143] The formula for determining the resistance of the electrical circuit CE comprising several abradable electronic tracks 81 can obviously be adapted according to the number of abradable electronic tracks 81.

[0144] As explained previously, the data processing module 12 is advantageously configured to determine, from the measured resistance of the electrical circuit CE, a data representative of the wear level of the motor 2 which is preferably a data relating to the wear of the abradable electronic board 8.

[0145] To this end, the data processing module 12 advantageously has access to certain parameters. For example, the data processing module 12 can access the initial resistance values ​​R i o of each track i when each track is not worn, to the initial thicknesses of the tracks and, where applicable, to the thicknesses of the support layers 82.

[0146] Thus, for example, in the case of an abradable electronic board 8 comprising four tracks 81, if the resistance R CE The measured value of the electrical circuit CE is such that: And then the data processing module 12 determines that the first track 81 of resistance R ± has disappeared, that the second and third traces 81 of resistors R3 and R4 are still new (unworn). This situation corresponds, in Figure 11, to the portion of the curve between PÀ1 and PÀ2. Thus, the data processing module 12 can deduce that it is the second abradable electronic trace 81 that is about to wear out, is currently wearing out, or has just disappeared due to wear. Using the initial thicknesses of the unworn traces, the initial thickness of the disappeared trace, where applicable the thicknesses of the unworn and disappeared support layers 82, and the instantaneous resistance measurement R CE, the data processing module 12 can calculate the instantaneous thickness of the abradable electronic board 8 and possibly, therefore, the worn (i.e. disappeared) thickness of the abradable electronic board 8.

[0147] It should be noted that the information used to characterize the wear of the gas turbine engine 2 can be directly the worn thickness of the abradable electronic board 8 or the instantaneous thickness of the abradable electronic board 8. In other words, the measuring electronic board 7 can be configured to calculate one and / or the other of these thicknesses and transmit them, via the communication module 11, to the data processing module 12. The information used to characterize the wear of the gas turbine engine 2 and the data representing the wear level of the engine can thus be the same quantity.

[0148] The data processing module 12 is advantageously configured to determine a wear level of the gas turbine engine 2 based on the representative wear level data.

[0149] Indeed, based on tests on gas turbine engines 2, a correlation can be established between the data representing the wear level of engine 2 and a wear level of the gas turbine engine 2 (or a specific part of the gas turbine engine 2). Thus, a predetermined nomogram establishing a correspondence between the data representing the wear level of engine 2 and a wear level of the gas turbine engine 2 is advantageously known to the data processing module 12 or adapted to be obtained by the data processing module 12.

[0150] For example, the nomogram can therefore match the instantaneous thickness of the abradable electronic board 8 with the wear level of the gas turbine engine 2. Alternatively, the nomogram can match the worn thickness of the abradable electronic board 8 with the wear level of the gas turbine engine 2.

[0151] According to another embodiment, the data representing the wear level of the engine 2 is the resistance measurement of the electronic circuit CE and the nomogram therefore matches said resistance measurement with the wear level of the gas turbine engine 2.

[0152] The nomogram in question was advantageously constructed on the basis of a gas turbine engine 2 having similar, or even identical, properties to the gas turbine engine 2 that we seek to monitor.

[0153] The nomogram in question 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 soil type and the type of volatile particles present. The environment can, for example, be categorized, such as "low erosion," "erosion," or "high erosion." Therefore, there can 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.

[0154] 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.

[0155] The data processing module 12 is preferably configured to determine the wear level of the gas turbine engine 2 corresponding to the worn thickness of the abradable electronic board 8, using the nomogram. In other words, the data representing the engine wear level is a data point relative to the wear of the abradable electronic board 8, this relative data point being the worn thickness of the abradable electronic board 8.

[0156] For example, the wear level of the gas turbine engine 2 can 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.

[0157] 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.

[0158] The level of wear can be expressed according to a class belonging to a group of classes such as: unworn, slightly worn, worn, very worn. The worn and very worn classes could correspond to wear requiring engine maintenance.

[0159] The wear level indicates to an operator whether engine maintenance is required. Alternatively, or equally, the operator can be informed of the remaining time before maintenance and, if applicable, the nature of the maintenance required.

[0160] System 100 can be configured to determine the wear level automatically at regular intervals. Alternatively, or in addition, wear level determination can be implemented following an operator command.

[0161] For example, system 100 may include a maintenance console 13 connected to the data processing module 12 and connected to the electronic data collection system 3 which would allow the operator to control and monitor the wear level.

[0162] The operator can be the aircraft pilot himself. Indeed, the entire System 100 can be carried on board the aircraft.

[0163] Alternatively, parts of system 100, for example the data processing module 12 and the maintenance console 13, might not be installed on the aircraft and could be located only at maintenance sites. The electronic data collection system 3, the wireless reading system 4, and even the communication module 11, the electronic circuit 10, and / or the transceiver 7 might not be permanently installed on the aircraft.

[0164] Process

[0165] With reference to Figure 12, a method is further proposed for characterizing wear of a gas turbine engine 2 using a system 100 as previously presented.

[0166] The process can be implemented when the gas turbine engine 2 is running or stopped.

[0167] The process includes a step a) of determining, or even measuring, by the electronic measuring card 7, information enabling the characterization of the wear of the motor 2. Preferably, step a) is a step of measuring a resistance of the electrical circuit CE formed by the electronic measuring card 7, the abradable electronic card 8 and the electrical wires 71 connecting them electrically.

[0168] To this end, the electronic measuring board 7 sends an electrical current into the electrical circuit CE and thus to the abradable electronic track(s) 81. The electronic board 7 then measures the resistance of the electrical circuit CE. The communication module 11 of the device 1 advantageously transmits the information to the data processing module 12. According to one embodiment, the information is first transmitted to the electronic data collection system 3, and the electronic data collection system 3 transmits the information to the data processing module 12 when the data processing module 12 requests it.

[0169] Then, in step b), the data processing module 12 determines a wear level of the gas turbine engine 2 from the information.

[0170] More specifically, the data processing module 12 advantageously calculates a representative value for the wear level of the engine 2, which is preferably a value relating to the wear of the abradable electronic board 8, based on the information provided. Then, the data processing module 12 deduces a wear level for the gas turbine engine 2 from the data and from the predetermined nomogram showing a correspondence between a representative value for the wear level of the engine 2 and a wear level for a gas turbine engine. Thus, it is possible to monitor the wear status of a gas turbine engine 2 in real time and, above all, in a very simple manner.

Claims

DEMANDS 1. Device (1) for characterizing wear on a gas turbine engine (2) comprising: - an abradable electronic card (8) comprising at least one abradable electronic track (81), the abradable electronic card (8) being 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; - an electronic measuring card (7) electrically connected to the abradable electronic track (81) so as to form an electrical circuit (CE), the electronic measuring card (7) being adapted to determine information enabling the characterization of the wear of the gas turbine engine (2); - a body (9) adapted to carry the abradable electronic board (8) and the electronic measuring board (7), the body (9) comprising an internal part (90) overmolded around the abradable electronic board (8) and the electronic measuring board (7), said internal part (90) being flexible, and an external part (92) arranged around the internal part (90) and being rigid.

2. Device according to claim 1, wherein the information enabling the characterization of the wear of the gas turbine engine (2) is a resistance measurement of the electrical circuit (CE).

3. Device according to any one of claims 1 and 2, comprising a stack of several abradable electronic tracks (81), each abradable electronic track (81) being electrically connected to the electronic measuring board (7), the abradable electronic tracks (81) being electrically mounted in parallel with each other.

4. Device according to any one of claims 1 to 3, comprising a communication module (11) connected to the electronic measurement board (7) 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).

5. Gas turbine engine (2) comprising at least one device (1) according to any one of claims 1 to 4, the device (1) being arranged so that the abradable electronic board (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.

6. Motor according to claim 5, 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 motor.

7. Aircraft comprising a gas turbine engine (2) according to any one of claims 5 and 6.

8. System (100) for characterizing wear of a gas turbine engine (2) comprising: a device (1) according to any one of claims 1 to 4; 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).

9. Method for characterizing wear of a gas turbine engine (2) by means of a system (100) according to claim 8, the method comprising the steps of: determination (a), by the electronic measuring card (7), of information enabling the characterization of the wear of the gas turbine engine (2), determination (b), by the data processing module (12), of a wear level 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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