Turbine engine monitoring method and corresponding turbine engine

Abstract

This invention relates to a method for monitoring a turbine engine, the method comprising the steps of: - measuring a temperature difference (ΔT) between a first temperature (T1) upstream of a heat transfer fluid flow and a second temperature (T2) downstream of the heat transfer fluid flow, the heat transfer fluid flow passing through an air-fluid heat exchange component (10) of the turbine engine, the air-fluid heat exchange component being exposed to an airflow capable of transporting solid or liquid water; - comparing the measured temperature difference (ΔT) with a reference value (ΔT). 参考 The comparison is made to determine the presence of solid water ingested in the air-fluid heat exchange member (10), or the presence of ice affecting the air-fluid heat exchange member (10).

Description

Technical Field

[0001] This disclosure generally relates to the field of aircraft turbine engines, and more specifically to turbofans or three-flow adaptive cycle engines. In particular, this disclosure proposes a method for monitoring changes in ingress of objects and / or weather conditions in components of a turbine engine. Background Technology

[0002] Air entering a turbine engine can include foreign object damage (FOD), which is an object that may pose a risk of damaging internal components of the turbine engine. Water droplets and hail, sand, and small birds are particularly noteworthy among these objects. It is necessary to monitor the intake of such objects that may obstruct air passages or damage parts of the engine. It is also desirable to detect the type and quantity of the ingested material to warn the pilot of potential risks and trigger the venting of the ingested material via one or more variable bleed valves (VBVs).

[0003] Weather conditions such as icing and the formation of ice crystals from ingested water can also damage the engine or require actions such as changing the speed of the high-pressure compressor and / or opening the vent valve, and therefore must be monitored.

[0004] It is also desirable to estimate potential damage caused by intakes and conditions encountered by the engine during flight. This estimation allows maintenance checks to be programmed based on the engine's exposure to such hazards.

[0005] Typically, water intake and icing are determined by measuring the temperature T30 at the outlet of a high-pressure compressor. However, in current turbofan or three-flow turbine engines, the amount of water intake and icing can occur in areas with complex geometries. These geometries affect the airflow and water volume entering these areas. In such machines, measuring temperature T30 is nearly inaccurate, difficult, or even impossible. Furthermore, such measurements do not provide information about the type of external hazard and cannot determine, for example, the amount of a specific ingested substance (such as hail) or the size of the ingested object. Summary of the Invention

[0006] One object of the present invention is to provide a method for monitoring objects containing water in various possible forms (e.g., hail or water droplets) and ingested in the pipes of a turbine engine, the method being particularly suitable for turbine fans or three-flow turbine engines.

[0007] Therefore, the present invention proposes a method for monitoring a turbine engine, comprising the following steps: • Measurement of the temperature difference between a first temperature upstream of the heat transfer fluid flow and a second temperature downstream of the heat transfer fluid flow passing through an air-fluid heat exchange component of the turbine engine, the air-fluid heat exchange component being exposed to an airflow capable of transporting solid or liquid water. • Compare the measured temperature difference with the reference value. • Based on the comparison, determine the presence of solid water ingested in the component, or determine the presence of ice affecting the component.

[0008] Advantageously, the method further includes comparing a temperature difference measurement between the first temperature and the second temperature with a reference temperature difference list, and determining, based on the comparison, the type of object selected from ice crystals and hail ingested in the air-fluid heat exchange member, or determining the icing affecting the air-fluid heat exchange member.

[0009] Preferably, the method further includes determining the amount of water ingested into the component based on the comparison.

[0010] Advantageously, the method also includes determining, based on the comparison, changes in weather conditions that cause external hazards of solid or liquid water to the component.

[0011] Advantageously, the air-fluid heat exchange component is arranged at least partially in a secondary or tertiary duct through which the airflow passes, or in a housing support exposed to the airflow.

[0012] Preferably, the first temperature and the second temperature are measured by a thermocouple or an optical fiber sensor.

[0013] The heat transfer fluid can be oil.

[0014] Preferably, the method further includes determining the rate of change of the temperature difference measurement between the first temperature and the second temperature.

[0015] Advantageously, the method further includes the step of opening at least one relief valve based on a temperature difference measurement between the first temperature and the second temperature.

[0016] Preferably, the method further includes the step of changing the speed of the compressor of the turbine engine based on the measured temperature difference between the first temperature and the second temperature.

[0017] The method may also include the steps of bypassing or activating the heat exchanger, or activating the anti-icing system based on a temperature difference measurement between the first temperature and the second temperature.

[0018] The present invention also relates to an aircraft turbine engine, comprising: • An air-fluid heat exchange component exposed to an airflow capable of transporting solid or liquid water, through which a heat transfer fluid flows. • A first sensor, configured to measure a first temperature upstream of the heat transfer fluid flow, and • A second sensor, configured to measure a second temperature downstream of the heat transfer fluid flow, and • A control system configured to determine the difference between the first temperature and the second temperature and compare the temperature difference with at least one reference temperature difference, and based on the comparison determine the presence of solid water ingested in the component or the presence of something affecting the freezing of the component. Attached Figure Description

[0019] Other features and advantages of the invention will become apparent from the following detailed description with reference to the accompanying drawings, in which: Figure 1A It is a cross-sectional view of a turbine engine including the main airflow duct and the duct for the secondary airflow.

[0020] Figure 1B It is a cross-sectional view of a turbine engine including the main airflow duct and ducts for secondary and tertiary airflow.

[0021] Figure 2 It is a cross-sectional view of a three-stage airflow duct including a direct heat exchanger.

[0022] Figure 3 It is a cross-sectional view of a three-stage airflow duct including a curved heat exchanger.

[0023] Figure 4 It is a cross-sectional view of a three-stage airflow duct including a heat exchanger, which also includes additional sensors.

[0024] Figure 5 The steps of the monitoring method are shown. Detailed Implementation

[0025] In the following description, the terms "internal" and "external" refer to the positioning relative to the longitudinal axis of rotation of the turbine engine. The axial direction corresponds to the direction along the longitudinal axis of rotation of the turbine engine. The radial direction is perpendicular to the longitudinal axis X. The terms "upstream" and "downstream" should be understood as the flow direction of the heat transfer fluid in the heat exchanger relative to the flow circulating between the temperature sensors.

[0026] Figure 1A and Figure 1BThis is a cross-sectional view of an aircraft turbine engine. The turbine engine comprises a gas turbine that drives a fan arranged along the longitudinal axis X of the turbine engine. The main duct V1 is used to deliver the main airflow circulating in the gas turbine.

[0027] Reference Figure 1A The turbine engine can be a turbofan type, meaning it generates a primary hot flow through the turbine engine's combustion chamber, and a secondary cold flow from the fan, flowing in an annular channel called the secondary duct V2, formed between the external and internal structures of the nacelle, outside the core portion of the turbine engine. Both airflows flow together longitudinally toward the nacelle's exhaust nozzles. For example, a turbofan turbine engine is described in patent application EP2075194A1.

[0028] refer to Figure 1B The turbine engine can also be a three-flow type, in which case it includes a main duct V1, a secondary duct V2, and a tertiary duct V3. The tertiary airflow flowing in the tertiary duct V3 is separated from the secondary airflow and can converge with and / or diverge from the main airflow. For example, a three-flow turbine engine is described in patent application WO202399527A1. Generally, each duct is a stationary component, i.e., it does not rotate during turbine engine operation.

[0029] Typically, turbocharged engines include an air-cooled oil cooler (ACOC) in which oil from the lubrication circuit flows. The ACOC is usually located in the secondary airflow duct or, as... Figure 1B The three-stage piping shown uses cooling oil. Alternatively, ACOC can be integrated into, for example... Figure 1A The separation nozzle 16 is shown. In some embodiments, other heat exchangers, including heat transfer fluid flows, are arranged in secondary or tertiary piping.

[0030] Some areas of the aircraft, particularly the hull struts, are exposed to external hazards such as rain, hail, ice, and impacts from objects (e.g., sand) on its outer walls. Other components may also be involved, such as stator and rotor blades in ducts, shell rings on the outer portion of the duct, cones, fan blades, and outlet guide vanes. An air-fluid heat exchange component 10 is arranged inside at least one of the exposed areas. The air-fluid heat exchange component includes a flow of heat transfer fluid circulating in the area exposed to external hazards.

[0031] For example, in a housing support, oil can circulate in a channel located within the support and in contact with the support's walls exposed to airflow. Therefore, the housing support integrates an air-fluid heat exchange component.

[0032] Figure 2 An air-fluid heat exchange member 10 is shown arranged in the airflow duct of a turbine engine. The heat exchange member can be arranged such that it is exposed to the airflow that may carry foreign matter. In other words, foreign matter such as water in a solid or liquid state is easily transported by the airflow exposed to the heat exchange member.

[0033] The heat exchanger can be arranged wholly or partially in the airflow duct. At least a portion of the duct in which the heat transfer fluid flows is arranged inside the air-fluid heat exchange component of the turbine engine.

[0034] The first temperature sensor C1 is positioned upstream of the heat transfer fluid flow. The second temperature sensor C2 is positioned downstream of the heat transfer fluid flow.

[0035] By way of non-limiting illustration, the temperature sensor may be an optical fiber. The use of an optical fiber allows for good local resolution within the heat exchange component. In other embodiments, the temperature sensor is a thermocouple. Thermocouples have the advantage of being easy to place in different locations within the heat exchange component. The temperature sensor may also be other devices for measuring temperature, such as an infrared thermometer or other types of thermometers.

[0036] Each temperature sensor may be located externally on the component in which the heat exchanger is disposed. Alternatively, one or more temperature sensors may be located at the inlet where the heat transfer fluid enters the component and / or at the outlet where the heat transfer fluid exits the component. One or more temperature sensors may also be disposed inside the component.

[0037] The heat transfer fluid flows between the first sensor C1 and the second sensor C2. For ACOC type exchangers, the heat transfer fluid is oil. In other embodiments, the heat transfer fluid can be another fluid, such as fuel oil, hydraulic fluid, or water. This fluid can be advantageous because it has a lower thermal inertia than oil.

[0038] The path taken by the heat transfer fluid can be straight, such as... Figure 2 As shown. Alternatively, as Figure 3 As shown, the path taken by the heat transfer fluid includes bends and / or is longer than the diameter of the component in which it is positioned. In some cases, the travel path is complex to facilitate heat exchange. For example, the travel path can be designed with a structure having bends and coils. During the use of the heat exchanger, the heat transfer fluid permanently flows between the first temperature sensor C1 and the second temperature sensor C2. The heat transfer fluid flow between the first temperature sensor C1 and the second temperature sensor C2 flows at least partially within the heat exchange component.

[0039] like Figure 2As shown, the first temperature sensor C1 and the second temperature sensor C2 can be arranged on two opposite sides of the heat exchange component, or as... Figure 3 As shown, the first temperature sensor C1 and the second temperature sensor C2 can be arranged on only one side or in any other geometric configuration. The thermal sensors are arranged such that fluid flows through the component along the travel path between the first temperature sensor C1 and the second temperature sensor C2.

[0040] In some embodiments, refer to Figure 4 One or more additional thermal sensors C3, C4 can be arranged along the travel path of the heat transfer fluid to measure additional temperatures. In some embodiments, additional measurements are performed using other temperature sensors C2, C3. These additional measurements enable an increase in the accuracy of the monitoring method.

[0041] The aircraft turbine engine may include one or more temperature sensors suitable for measuring the temperature in the compressor and / or the external temperature and / or the temperature at other points on the aircraft.

[0042] Additionally, the turbine engine includes a control system that communicates with a first temperature sensor C1 and a second temperature sensor C2. The control system is configured to calculate the difference ΔT between the first and second temperatures, i.e., to perform a temperature difference measurement. Advantageously, the control system communicates with at least one additional temperature sensor, such as a temperature sensor arranged to measure the temperature within the compressor, or a sensor suitable for measuring the temperature outside the turbine engine. The control system can be a system dedicated to the method of the invention, or a Full Automatic Digital Engine Control (FADEC) system for an aircraft. When the control system communicating with each temperature sensor is a dedicated system, it preferably communicates with a FADEC.

[0043] The use of FADEC as a control system enables the use of existing communication paths, as well as direct communication with other components of the turbine engine, such as for de-icing in the event of ingested objects or water intake in cryogenic environments.

[0044] Dedicated control systems can be placed in optimized locations for processing temperature data and allow for configuration using simpler systems.

[0045] The control system includes software for comparing temperature difference measurements with a database. The software has access to the database of temperature difference measurements. In the database, each temperature difference measurement is associated with one or more types of objects that may be ingested in the airflow duct and / or with different types of weather conditions. Therefore, comparison with the database allows the type of ingested object or weather condition to be determined based on the difference between a first temperature and a second temperature. The database may include additional information such as the temperature inside the compressor, the temperature outside the turbine engine, and / or the rate of change of the temperature difference measurements.

[0046] The database can be built based on test measurements performed on an engine, part of an aircraft, or on an aircraft on the ground. The database may also include temperature difference measurements recorded on a working turbine engine. The database may include data created by an artificial intelligence system that takes into account local weather data used to determine temperature difference measurements during flight. Throughout its use, the database can be refined and improved in terms of accuracy.

[0047] Additionally, the turbine engine includes a compressor that includes one or more variable-bleed valves (VBVs). Each VBV is configured to move between a closed position and an open position; in the closed position, it prevents the main airflow from flowing toward other flow streams; in the open position, it allows the main airflow to flow toward one or more additional flow streams. In the open position, the VBV also allows the ejection of centrifugal debris contained in the airflow. The VBVs can be used to vent one or more ingested objects, or, for example, to vent water after de-icing or melting ingested hail.

[0048] The vent valve is typically driven by the computer system (FADEC) responsible for controlling the aircraft's engines. The vent valve can be driven based on parameters transmitted by a control system communicating with a first temperature sensor and a second temperature sensor. For example, the degree to which one or more vent valves open can be controlled based on the type and / or quantity of the ingested object, determined by comparing the difference between the first and second temperatures with a database.

[0049] A turbine engine typically includes a low-pressure compressor 22, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine in the main duct V1. When one or more objects are ingested, it may be necessary to increase the speed of the high-pressure compressor to prevent icing and to prevent shock during combustion chamber shutdown. Increasing the compressor speed to increase compression and thus temperature and airflow ensures that the air entering the combustion chamber no longer contains any solid or liquid water. In particular, the speed of the high-pressure compressor can be increased without increasing the speed of the low-pressure compressor. This prevents any ice crystals from entering the combustion chamber without increasing the thrust of the turbine engine.

[0050] The compressor's rotational speed is driven by a computer system (FADEC) responsible for controlling the aircraft's engines. This rotational speed can be driven based on parameters transmitted by a control system communicating with a first temperature sensor and a second temperature sensor. For example, the compressor's rotational speed may be reduced based on the type and / or quantity of the ingested object, determined by comparing the difference between the first and second temperatures with a database.

[0051] Aircraft typically include an anti-icing system. This anti-icing system may include heating pads disposed on one or more surfaces of the aircraft and / or turbine engine nacelles and / or inside the turbine engine, or any other system adapted to heat one or more surfaces to melt hail and / or ice formed when water present on these surfaces freezes. Typically, the anti-icing system is activated and driven by a computer system (FADEC) responsible for controlling the aircraft's engines. The anti-icing system can be driven based on parameters transmitted by a control system communicating with each temperature sensor. For example, the anti-icing system may be activated or its temperature adjusted based on the type and / or quantity of ingested objects.

[0052] Specifically, the system is activated when icing conditions are detected, particularly when water is present in the air flowing through the pipes where heat exchange components are arranged. In particular, contact between subcooled water and the heat exchange components can lead to icing. The system can be selectively activated under cold conditions and in the presence of subcooled water in the air flowing through the components.

[0053] For example, water can enter in the form of rain or hail. The type and quantity of the ingested object are determined by comparing the difference between a first temperature and a second temperature with a database.

[0054] A method for monitoring turbine engines is now described.

[0055] When the turbine engine is running, airflow from outside the turbine engine is delivered through a main duct. This airflow can be separated into a main airflow, a secondary airflow, and, in some cases, a secondary stream through one or more separation nozzles. Therefore, any object from outside the turbine engine can be delivered through the secondary duct and / or secondary conduit.

[0056] Different thermal effects may occur when one or more objects are ingested.

[0057] Complete or partial blockage of air passages causes an increase in temperature in the components involved. Typically, the temperature increase depends on the severity of the blockage. Conversely, the intake of hail or cold water can lead to cooling of the heat exchangers located within the components.

[0058] In both cases, the temperature changes of the heat transfer fluid inside the pipe allow for the acquisition of information about the type and quantity of the ingested substance.

[0059] Other components of the turbine engine, such as casing struts, are exposed to weather conditions on their outer surfaces. These components are generally unaffected by the ingestion of objects. However, when water droplets or hail are deposited on the surface of these areas, thermal effects can occur within the components involved.

[0060] In this case, the temperature change of the heat transfer fluid makes it possible to obtain information about the weather conditions outside the component involved.

[0061] Figure 5 This is a schematic diagram of the steps of a monitoring method during flight. In step 1, temperatures T1 and T2 are measured using each temperature sensor. Preferably, temperatures T1 and T2 are measured continuously. In some cases, temperatures can be measured at short time intervals to obtain quasi-continuous measurements. Simultaneously, the temperatures outside the compressor and / or inside the compressor are measured. In some cases, the rate of change is determined from the temperature difference measurements.

[0062] In step 2, the control system determines one or more differences ΔT between two corresponding temperatures T1 and T2.

[0063] If one or more additional sensors C3, C4 are present, then several temperature differences ΔT can be determined between the temperatures measured by the corresponding sensors C1, C2, C3. 12 ΔT 23 ΔT 13 .

[0064] In step 3, the control system calculates the reference thermal difference ΔT based on one or more parameters of the environment of the aircraft and turbine engine. 参考 For example, the reference thermal difference ΔT can be calculated based on the external temperature and the aircraft's speed and altitude. 参考 .

[0065] In step 4, the control system determines the measured temperature difference ΔT between two corresponding temperatures T1 and T2 and the reference thermal difference ΔT. 参考 The difference between them. If there are several detectors, then the corresponding temperature difference ΔT for each will be... 12 ΔT 23 ΔT 13 thermal difference ΔT from the reference 参考 Compare them.

[0066] When the thermal behavior of the heat transfer fluid is further altered based on the intake of one or more objects, humidity, or specific weather conditions, the difference ΔT between the first and second temperatures differs from the reference thermal difference ΔT. 参考In step 5, the control system determines the type and quantity of the ingested object based on the thermal behavior in the form of an equation or by comparison with a database including reference thermal measurements.

[0067] The magnitude, rate, and temporal trend of the temperature difference measurement ΔT depend on the type and quantity of the ingested object and / or the severity of changes in weather conditions. Analysis of the thermal difference and its comparison with a reference value allows for the determination of the quantity and form of ingested water, such as hail, ice, or liquid water. For example, under dry conditions, the temperature difference measurement ΔT is close to the reference thermal difference ΔT. 参考 Under humid conditions, the measured temperature difference ΔT is typically greater than the reference thermal difference ΔT. 参考 .

[0068] For an air-oil type heat exchanger arranged in a duct through which the airflow flows, the thermal behavior of the heat transfer fluid can be described by the following equation:

[0069] in: T1 represents the temperature upstream of the heat exchanger. T2 is the temperature downstream of the heat exchanger. The subscript FC indicates the heat transfer fluid. W FC The flow rate of the heat transfer fluid. The heat capacity of the heat transfer fluid. L is the length of the fluid channel between measurement points T1 and T2. D c The outer diameter of the fluid passage in the heat exchanger. d c The thickness of the fluid channels in the heat exchanger. T 空气 The total temperature of the air upstream of the heat exchanger. W 空气 The airflow rate upstream of the heat exchanger. H 空气 Let be the convective heat transfer coefficient of air. This coefficient is a known function of the air velocity and the liquid water content (LWC) of the air upstream of the heat exchanger. H FC The convective heat transfer coefficient of the heat transfer fluid is denoted as . λ ACOC The thermal conductivity of the heat exchanger substrate.

[0070] According to this equation, the control system can estimate the liquid water content (LWC) and hail water content (HWC) in the pipes of an ACOC turbine engine equipped with two temperature sensors.

[0071] As a non-limiting observation, by comparing the measured temperature difference ΔT and the reference thermal difference ΔT 参考 It can detect 0.1g / m in the pipeline. 3 and <3.0g / m 3 The liquid water content between and 1g / m 3 and 20g / m 3 The hail water content between [amount] and [amount]. A similar method can be used to detect 1 g / m³. 3 Up to 3g / m 3 Intake of crystalline forms between [the two].

[0072] Information regarding the different forms of water content and external temperature allows for the estimation of the risk of ice formation on different parts of the turbine engine. The measured temperature difference ΔT between the first temperature T1 and the second temperature T2 is compared with a reference thermal difference ΔT. 参考 The time trend of the comparison makes it possible to determine the objects passing through the cloud, especially water droplets, hail, or sand.

[0073] If multiple detectors T1, T2, T3, and T4 are present, thermal mapping of the interior of the components forming the heat exchanger can be performed. Fiber optic sensors are particularly suitable for such localized measurements. This arrangement makes it easier to detect thermal effects that may cancel each other out, such as ice crystals blocking air passages in the exchanger, which heat the heat transfer fluid due to slower airflow reducing heat exchange between the air and the heat transfer fluid, and simultaneously cooling the heat transfer fluid due to heat exchange between the fluid and the ice accumulating on the exchanger.

[0074] Using time trends and / or with reference temperature difference ΔT 参考 After comparing and estimating the temperature difference measurement ΔT, information about the type and quantity of objects ingested in the pipe can now be obtained.

[0075] The control system can analyze this information, along with other data such as external temperature, aircraft speed, and altitude, at step 6 to determine the state of the turbine engine's exposure to external hazards and trigger possible actions to expel ingested objects and / or to limit damage caused by ingestion and / or by detected weather conditions.

[0076] For example, a control system can determine the risk of ice formation based on the temperature and quantity of the ingested water. In this case, the control system can trigger the activation of the anti-icing system and / or adjust the temperature and other parameters of the anti-icing system.

[0077] In other situations where there is a risk of freezing or icing, or conversely, where there is a risk of further effects from excessively high temperatures, activation of the heat exchanger or bypass of the heat exchanger may be driven by the control system.

[0078] In another example, the control system can determine the amount of water, sand, or other objects ingested in the pipe that need to be emptied by a variable vent valve. Depending on the type and / or quantity of the ingested object, the control system can trigger one or more vent valves to open partially or fully. This allows for optimized venting of the ingested object, thereby minimizing the impact on airflow for said venting.

[0079] In cases where one or more impacts pose a risk of damaging both the high-pressure and low-pressure compressors, the rotational speed of each compressor in the turbine engine can be modified via a control system, for example, by modifying the rotational speed over a predefined time period or by a time determined based on the acoustic characteristics of the ingested object.

[0080] By minimizing the impact on airflow in the duct and the operation of the turbine engine, measurements suitable for the type and quantity of inhaled material allow for optimization of venting, de-icing, and any other actions.

[0081] Data recorded during turbine engine operation and temperature difference measurements ΔT can also be used as part of the turbine engine's maintenance plan. For example, in the event of specific ingestions such as hail that may have a strong impact, a plan for shorter maintenance intervals can be triggered. These maintenance intervals can be specific to the turbine engine components involved, such as the fan rotor and the low-pressure compressor.

[0082] References EP2075194A1 WO202399527A1

Claims

1. A method for monitoring a turbine engine, comprising the following steps: The measurement of the temperature difference (ΔT) between a first temperature (T1) upstream of the heat transfer fluid flow and a second temperature (T2) downstream of the heat transfer fluid flow, the heat transfer fluid flow passing through the air-fluid heat exchange component (10) of the turbine engine, the air-fluid heat exchange component being exposed to an airflow capable of transporting solid or liquid water. o Compare the measured temperature difference (ΔT) with the reference value (ΔT) 参考 ) for comparison, Based on the comparison, the presence of solid water ingested in the air-fluid heat exchange member (10) is determined, or the presence of ice affecting the air-fluid heat exchange member (10) is determined.

2. The method of claim 1 further comprises comparing a temperature difference measurement (ΔT) between the first temperature (T1) and the second temperature (T2) with a reference temperature difference list, and determining, based on the comparison, the type of object selected from ice crystals and hail ingested in the component (10), or determining the icing of the component (10).

3. The method according to any one of claims 1 and 2, further comprising determining the amount of water ingested in the component (10) based on the comparison.

4. The method according to any one of claims 1 to 3, further comprising determining, based on the comparison, changes in weather conditions that cause external hazards to the component (10) caused by solid or liquid water.

5. The method according to any one of claims 1 to 4, wherein, The air-fluid heat exchange component (10) is at least partially arranged in a secondary pipe (V2) or a tertiary pipe (V3) through which the airflow passes, or arranged in a shell support exposed to the airflow.

6. The method according to any one of claims 1 to 5, wherein, The first temperature (T1) and the second temperature (T2) are measured by thermocouples or fiber optic sensors.

7. The method according to any one of claims 1 to 6, wherein, The heat transfer fluid is oil.

8. The method according to any one of claims 1 to 7, further comprising determining the rate of change of a measured temperature difference (ΔT) between the first temperature (T1) and the second temperature (T2).

9. The method according to any one of claims 1 to 8, further comprising the step of opening at least one relief valve based on a measured temperature difference (ΔT) between the first temperature (T1) and the second temperature (T2).

10. The method according to any one of claims 1 to 9, further comprising the step of changing the speed of the compressor of the turbine engine based on the measured temperature difference (ΔT) between the first temperature and the second temperature.

11. The method according to any one of claims 1 to 10, further comprising the step of activating the anti-icing system based on a temperature difference measurement (ΔT) between the first temperature (T1) and the second temperature (T2).

12. An aircraft turbine engine, comprising: o An air-fluid heat exchange component (10) is exposed to an airflow capable of transporting solid or liquid water, through which a heat transfer fluid flows. o First sensor (C1), the first sensor is configured to measure a first temperature (T1) upstream of the heat transfer fluid flow. o Second sensor (C2), the second sensor is configured to measure a second temperature (T2) downstream of the heat transfer fluid flow, and The control system is configured to determine the difference between the first temperature (T1) and the second temperature (T2) and compare the temperature difference with at least one reference temperature difference (ΔT). 参考 The comparison is made to determine the presence of solid water ingested in the component (10) or the presence of ice affecting the component (10).

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