Monitoring device and method for cooperatively detecting failure of engine bearing based on wall temperature and scraps

Abstract

The invention discloses an aero-engine bearing failure monitoring device and method based on wall temperature and scrap cooperative detection. The device comprises a magnetic chip detector mounted on a lubricating oil outlet pipeline and at least two temperature sensors mounted on the outer surface of a bearing shell, and a signal processing and warning device receives and processes sensor signals. The method comprises the following steps: carrying out abrasion state screening by regularly checking the size of metal chips captured by the magnetic chip detector; the temperature of the bearing shell is monitored in real time through a multi-sensor fusion strategy, and temperature alarm is carried out by adopting multi-stage delay threshold logic; and when the temperature alarm is triggered at the same time and the metal filing exceeding the threshold value is detected, judging that the bearing enters a substantive failure stage based on a two-dimensional cross validation principle. Through mutual verification of physical evidences and thermal anomaly signals, the accuracy and reliability of fault judgment are remarkably improved, a scientific decision basis is provided for on-condition maintenance and emergency shutdown of the engine, and flight safety is effectively guaranteed.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine fault monitoring technology, and relates to an aero-engine bearing failure monitoring device and method based on the coordinated detection of wall temperature and debris. Background Technology

[0002] As a core component of aircraft, the reliability of aero-engines directly determines flight safety and mission efficiency. Bearings, as the core supporting component of the engine rotor system, are crucial for ensuring the high-speed and stable operation of the rotor and transmitting radial and axial loads. Aero-engine bearings are typically assembled in a closed bearing cavity, operating in an extremely harsh environment: on the one hand, they must withstand the enormous centrifugal force, impact loads, and alternating stresses generated by the high-speed rotation of the rotor (speeds can reach tens of thousands of revolutions per minute), operating under high-load conditions for extended periods; on the other hand, bearings rely on a lubricating oil system for lubrication and heat dissipation, and fluctuations in the flow rate, pressure, and cleanliness of the lubricating oil can exacerbate bearing wear. Simultaneously, temperature gradient changes within the bearing cavity (from room temperature to hundreds of degrees Celsius) further increase the risk of material fatigue and performance degradation.

[0003] From the perspective of failure modes, the failure of aero-engine bearings is not instantaneous, but rather a gradual process from early damage to functional loss. Among these, metal spalling and abnormal temperature rise are the two most representative precursors. Microcracks caused by fatigue in the bearing raceway or rolling elements gradually expand into metal fragments. These spalled fragments, circulating with the lubricating oil, may further exacerbate bearing wear, forming a vicious cycle of damage-spalling-more severe damage. At the same time, the increased friction, lubrication failure, or assembly abnormalities caused by spalling can directly lead to an abnormal rise in bearing housing temperature. If not intervened in time, this will eventually lead to bearing seizure, rotor imbalance, and even catastrophic accidents such as engine in-flight shutdown.

[0004] However, current monitoring technologies for aero-engine bearings have limited monitoring dimensions and cannot capture the collaborative characteristics of failures, thus having significant limitations and failing to meet the stringent requirements of the aviation industry for high reliability and high safety. Summary of the Invention

[0005] To address the problems existing in the prior art, this invention provides a failure monitoring device and method for aero-engine bearings based on the synergistic detection of wall temperature and chip debris. Starting from the failure mode of the bearing, it identifies two abnormal characteristics of the failure process, and performs separate monitoring and comprehensive evaluation of characteristics such as bearing spalling and abnormal temperature rise, so as to achieve effective monitoring of bearing failure and prevent the bearing from developing from failure to functional loss during use.

[0006] This invention is achieved through the following technical solution: A monitoring device for engine bearing failure based on the combined detection of wall temperature and chip debris includes the following steps: At the lubricating oil outlet line of the aircraft engine bearing, check the detection head assembly of the magnetic debris detector to see if metal debris is adsorbed; if metal debris is present, determine whether its size exceeds the preset threshold. The bearing housing temperature is monitored by a temperature sensor, and a temperature alarm is triggered when the temperature meets the preset alarm conditions. When a temperature alarm is triggered, or when the size of metal chips exceeds a preset threshold, the bearing is determined to have entered a substantial failure stage.

[0007] Preferably, the conditions for triggering a temperature alarm are: The conditions for triggering a temperature alarm are: when the housing temperature is greater than the first temperature threshold and the duration exceeds the first duration, or when the housing temperature is greater than the second temperature threshold and the duration exceeds the second duration, a temperature alarm is triggered; otherwise, a temperature alarm is not triggered. Wherein the second temperature threshold is greater than the first temperature threshold, and the second duration is less than the first duration; The conditions for canceling the temperature alarm are: the shell temperature is less than the third temperature threshold and the duration exceeds the third duration.

[0008] Preferably, the first temperature threshold is 170°C and the first duration is 5 seconds; the second temperature threshold is 185°C and the second duration is 3 seconds; the third temperature threshold is 150°C and the third duration is 3 seconds.

[0009] Preferably, the preset threshold is determined by statistical analysis of bearing damage morphology and at least three sets of bearing fatigue propagation test results; the size of the metal shavings is measured by a stereomicroscope.

[0010] Preferably, at least two temperature sensors are used to monitor the temperature. The temperature value selection strategy is as follows: if the deviation of multiple sensor readings is within ±5℃, the average value is taken; otherwise, the larger value is taken.

[0011] Preferably, before triggering a temperature alarm, the validity of the temperature sensor signal is checked, and the detection method includes one or more of line BIT detection, parameter range detection, and slope detection.

[0012] A monitoring device for engine bearing failure based on the combined detection of wall temperature and chip debris includes: Magnetic debris detector, temperature sensor, and signal processing and alarm device; The magnetic chip detector is installed in the lubricating oil outlet pipeline of the aircraft engine bearing to capture metal chips generated by bearing shedding. At least two temperature sensors are used, both of which are installed on the outer surface of the bearing housing to detect the temperature of the bearing housing. The signal processing and alarm device is connected to the magnetic debris detector and the temperature sensor respectively. It is used to receive temperature signals, perform validity detection, execute combinational logic judgment, and output alarm control signals.

[0013] Preferably, the magnetic debris detector includes a detection head assembly and a housing assembly that cooperate with each other; the detection head assembly is equipped with a permanent magnet, and the detection head assembly can be installed or detached from the housing assembly by rotation.

[0014] Preferably, the temperature sensor is a platinum resistance thermometer that outputs a resistance signal.

[0015] Preferably, the signal processing and alarm device includes a processor, a line BIT module, a wall temperature alarm light, and a cockpit alarm light; the line BIT module, the wall temperature alarm light, and the cockpit alarm light are all electrically connected to the processor, and the temperature sensor is electrically connected to the processor via a line.

[0016] Compared with the prior art, the present invention has the following beneficial technical effects: This invention aims to provide a bearing failure monitoring device and method for aero-engines based on the coordinated detection of wall temperature and metal debris. The proposed bearing failure monitoring device includes a magnetic debris detector, a temperature sensor, and a signal processing and alarm device. The magnetic debris detector is installed in the lubricating oil outlet pipeline and includes a rotatable and detachable detection head and housing assembly for capturing metal debris detached from the bearing. The temperature sensor is a platinum resistance type, installed on the outer surface of the bearing housing, and its reliability is improved through a dual-redundancy design. This invention starts with the bearing failure mode, identifying two abnormal characteristics of the failure process, and separately monitoring and comprehensively evaluating characteristics such as bearing spalling and abnormal temperature rise, achieving effective monitoring of bearing failure. The monitoring method of this invention screens wear status by periodically checking the size of the metal debris captured by the magnetic debris detector; it monitors the bearing housing temperature in real time through a multi-sensor fusion strategy and uses multi-level delay threshold logic for temperature alarms; when a temperature alarm is triggered simultaneously and metal debris exceeding the threshold is detected, the bearing is determined to have entered the substantial failure stage based on the principle of dual-dimensional cross-validation. The core idea of ​​dual-dimensional cross-validation is proposed, combining offline, periodic wear debris with online, real-time temperature and thermal anomaly signals. This invention breaks through the single monitoring mode by collaboratively capturing two major failure characteristics: spalling and temperature anomalies, significantly improving the comprehensiveness of monitoring. Through standardized threshold settings and logical judgments, it replaces manual experience-based judgment, reducing the false alarm rate. A two-dimensional cross-validation mechanism can accurately identify substantial failures, preventing the escalation of faults. This solution effectively fills the technological gap in early warning of aero-engine bearing failures, provides authoritative evidence for emergency shutdown maintenance, and has significant practical value for improving engine operational safety and reducing maintenance costs.

[0017] Furthermore, employing multiple sensors and developing a data fusion strategy (mean / maximum value) significantly improves the redundancy and robustness of the temperature measurement subsystem. Even if a single sensor deviates or fails, the system can ensure, through comparison and logical judgment, that the final temperature value used for alarm is the most conservative and safest, thereby greatly enhancing the system's fault tolerance and overall reliability.

[0018] Furthermore, a multi-level temperature alarm logic with time-sequence requirements was established. By setting different temperature thresholds and duration conditions (such as shorter trigger times for higher temperatures), the alarm mechanism is both sensitive and effectively suppresses false alarms caused by short-term temperature fluctuations, ensuring the rigor and anti-interference capabilities of the alarms. At the same time, the alarm cancellation conditions are clearly defined to avoid frequent alarm jumps at critical temperature points, ensuring stable status indication. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 The image shows the bearing and housing model that need to be monitored. Figure 2 This is a schematic diagram of a magnetic debris detector. Figure 3 This is a logic diagram for a bearing housing temperature monitoring device. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0022] Example 1 The specific implementation method is as follows: Step 1: Establish a three-dimensional model of the bearing and housing of a certain type of aero-engine that need to be monitored, see... Figure 1 .

[0023] Step 2: Based on the 3D model, install one magnetic debris detector and two temperature sensors near the bearing in the oil return path of the aero-engine bearing. The magnetic debris detector is installed on the lubricating oil outlet pipe to monitor bearing debris; the temperature sensors are installed on the outer surface of the bearing housing to monitor abnormal temperature increases in the housing. The temperature sensors are general-purpose platinum resistance thermometers that can output resistance signals. The structure of the magnetic debris detector is shown in [link to magnetic debris detector structure]. Figure 2 The detection head assembly contains a permanent magnet, and the detection head can be installed or removed from the housing assembly by rotation.

[0024] Step 3: Bearing Failure and Spalling Monitoring. During the service interval of the aero-engine bearing, unscrew the magnetic debris detector head assembly and visually inspect for any adhering metal. If metal debris is present, use a stereomicroscope to determine whether the size of the metal debris exceeds a preset threshold. This serves as a preliminary screening basis for the bearing's normal wear condition and early failure risk.

[0025] Setting the metal chip size threshold: By statistically analyzing the bearing damage morphology and combining the results of three sets of bearing fatigue propagation tests, the standard for monitoring by the magnetic chip detector was determined, and this standard value was set as the threshold for monitoring the size of metal chips.

[0026] Step 4: Monitoring abnormal bearing temperature rise. (Following...) Figure 3 As shown, a temperature measurement device is constructed. Each temperature sensor undergoes validity testing via circuit bit analysis, parameter range verification, and slope determination to ensure a valid signal participates in the temperature alarm function. During engine operation, two temperature sensors measure the bearing housing temperature. If the temperature deviation between the two sensors is within ±5℃, the average value is taken; otherwise, the larger value is used. The measurement data is comprehensively analyzed, and logical judgments are made based on the status of the two temperature sensors. When the temperature meets the alarm conditions, an alarm signal is output, illuminating the wall-mounted warning light.

[0027] The temperature signal uses combinational logic for alarm generation. The specific settings are as follows: 1) Conditions for generating a temperature alarm: If the collected casing temperature is greater than 170°C for 5 seconds or greater than 185°C for 3 seconds, a temperature alarm will be generated; otherwise, it will not be triggered. 2) Temperature alarm cancellation conditions: The temperature of the housing is less than 150℃ for 3 consecutive seconds, otherwise the alarm will not be cancelled.

[0028] Step 5: Bearing Failure Determination. When the monitoring device detects that the casing temperature detection module has triggered a preset alarm threshold, the wall alarm light illuminates. Following the emergency testing procedure, the magnetic debris detector head assembly is removed. If, through visual inspection and composition analysis, it is confirmed that metal debris particles with bearing characteristic elements have been adsorbed and the size of the metal debris exceeds the preset threshold, then based on the dual-dimensional cross-verification logic of "thermal anomaly - wear physical characteristics," it is accurately determined that the aero-engine bearing has entered a substantial failure stage. This provides authoritative diagnostic evidence for subsequent emergency shutdown maintenance and to prevent the escalation of the fault, ensuring engine operation safety and the scientific nature of maintenance decisions.

[0029] This approach changes the traditional single-parameter monitoring mode, significantly improving the accuracy and reliability of bearing failure judgment, effectively avoiding false alarms due to a single signal, and providing an authoritative and scientific basis for emergency shutdown decisions. This effectively prevents catastrophic failures and ensures flight safety. The scientific basis for setting the wear threshold (statistical analysis + fatigue testing) is clearly defined. This ensures that the threshold is not estimated based on experience, but rather on objective and quantifiable standards based on a large amount of experimental data. This makes the early risk screening conclusions based on chip size more scientific and reliable, improving the repeatability and authority of the diagnostic results.

[0030] Example 2 The present invention provides a failure monitoring device for aero-engine bearings based on the combined detection of wall temperature and chip debris, as follows: 1. Failure monitoring device First, based on the accurate three-dimensional model of the aero-engine bearing and housing (see appendix) Figure 1 Determine the installation location and method of the magnetic debris detector and temperature sensor.

[0031] The magnetic debris detector is a set, installed via a threaded connection on the lubricating oil outlet pipe of the engine bearing cavity, located downstream of the bearing and as close as possible to the bearing body, to capture ferromagnetic wear debris generated by the bearing in the lubricating oil. The detector's detection head assembly has an embedded permanent magnet, which can be unscrewed from or installed from the housing assembly by rotation, facilitating offline inspection. Its structure is shown in the attached figure. Figure 2 .

[0032] Two temperature sensors, Pt100 platinum resistance temperature sensors capable of outputting resistance signals, are fixedly mounted at different measuring points on the outer surface of the bearing housing for real-time monitoring of housing temperature changes. All sensor signals are connected to a signal processing and alarm unit located on the engine casing.

[0033] The advantage of using platinum resistance temperature sensors lies in leveraging the inherent high precision, high stability, and excellent linear output characteristics of platinum resistance. Its output resistance signal has strong anti-interference capabilities, making it ideal for the harsh electromagnetic environment of engine compartments and long-distance transmission, ensuring the accuracy and consistency of temperature measurement data.

[0034] The signal processing and alarm system includes a processor, a line BIT module, a wall temperature alarm light, and a cockpit alarm light. All three are electrically connected to the processor, and the temperature sensor is also electrically connected to the processor via wiring. The line BIT module is dedicated to hardware self-testing, the processor handles the core algorithm, and the separate wall and cockpit alarm lights provide tiered alarms for ground crew and pilots, creating a clear and accurate alarm system that ensures fault information is reliably transmitted to the correct personnel.

[0035] 2. Bearing wear condition monitoring (offline) During routine engine maintenance or specified service intervals, monitor wear condition according to the following steps: Manually unscrew and remove the detection head assembly of the magnetic debris detector from the lubricating oil outlet line.

[0036] Visually inspect the surface of the permanent magnet inside the detection head assembly to determine if any metal shavings are adsorbed.

[0037] If metal shavings are found, they are observed and measured using a stereomicroscope, and the maximum size of the shavings is compared with a preset threshold. The threshold is a standard value determined by statistical analysis of bearing damage morphology and combined with the results of three sets of bearing fatigue propagation tests.

[0038] Judgment criteria: If the size of the metal shavings does not exceed the threshold, it is considered normal wear; if the size exceeds the threshold, it indicates that the bearing is at risk of early failure and should be included in the key monitoring list.

[0039] 3. Bearing temperature anomaly monitoring (online) When the engine is running, the temperature monitoring function is automatically activated and operates according to the following logic: The system performs continuous self-tests on the signals from each temperature sensor, and determines their validity by checking the line bit status, signal range, and rate of change. Only signals whose validity is confirmed are used in subsequent processing.

[0040] Data Acquisition and Fusion: The system reads two valid temperature values ​​(T1, T2). If |T1-T2|≤5°C, the average value is taken as the monitored temperature value; if |T1-T2|>5°C, the larger of the two values ​​is automatically selected as the monitored temperature value.

[0041] The temperature alarm logic uses a combined judgment method: The temperature alarm will be triggered immediately and the alarm light will illuminate when the monitored temperature value meets any of the following conditions: (a) The temperature exceeds the first temperature threshold of 170°C for a first duration of 5 seconds; (b) If the temperature exceeds the second temperature threshold of 185°C for a duration of 3 seconds, it will not be triggered; otherwise, it will not be triggered. Alarm cancellation conditions: The alarm signal will be automatically cancelled and the alarm light will turn off after the monitored temperature value is below the third temperature threshold of 150°C for three consecutive 3-second periods; otherwise, it will not be cancelled. 4. Bearing failure determination (two-dimensional cross-validation) When the system triggers a temperature alarm, the failure determination is performed according to the following procedure: According to the emergency testing procedure, the detection head assembly of the magnetic debris detector should be removed immediately.

[0042] Laboratory analysis of the captured debris: (a) Visual inspection confirmed the presence of metal shavings; (b) Composition analysis was performed using a spectrometer or similar instrument to confirm that the metal scrap contained characteristic elements of bearing steel; (c) Use a microscope to verify the size and confirm that the size exceeds the preset threshold.

[0043] Final determination: If the temperature alarm condition is met, and the magnetic shavings detection confirms the presence of metal shavings with the same composition and exceeding the size limit, then based on the dual-dimensional cross-verification logic of "thermal anomaly - wear physical characteristics", it is determined that the engine bearing has entered the stage of substantial failure, and an emergency shutdown maintenance operation should be performed immediately.

[0044] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0045] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0046] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixation," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a communication connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances. When a component is said to be "fixed to" another component, it can be directly on the other component or there may be an intervening component. When a component is considered to be "connected" to another component, it can be directly connected to the other component or there may be an intervening component. When a component is considered to be "set on" another component, it can be directly set on the other component or there may be an intervening component.

[0047] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0048] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0049] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0050] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Those skilled in the art can readily implement the present invention based on the accompanying drawings and the above description. However, any modifications, alterations, or variations made by those skilled in the art without departing from the scope of the present invention, utilizing the disclosed technical content, are equivalent embodiments of the present invention. Furthermore, any modifications, alterations, or variations made to the above embodiments based on the essential technology of the present invention are still within the protection scope of the present invention.

Claims

1. A monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris, characterized in that, Includes the following steps: At the lubricating oil outlet line of the aircraft engine bearing, check the detection head assembly of the magnetic debris detector to see if metal debris is adsorbed; if metal debris is present, determine whether its size exceeds the preset threshold. The bearing housing temperature is monitored by a temperature sensor, and a temperature alarm is triggered when the temperature meets the preset alarm conditions. When a temperature alarm is triggered, or when the size of metal chips exceeds a preset threshold, the bearing is determined to have entered a substantial failure stage.

2. The monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris as described in claim 1, characterized in that, The conditions for triggering a temperature alarm are: when the housing temperature is greater than the first temperature threshold and the duration exceeds the first duration, or when the housing temperature is greater than the second temperature threshold and the duration exceeds the second duration, a temperature alarm is triggered. Wherein the second temperature threshold is greater than the first temperature threshold, and the second duration is less than the first duration; The conditions for canceling the temperature alarm are: the shell temperature is less than the third temperature threshold and the duration exceeds the third duration.

3. The monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris as described in claim 2, characterized in that, The first temperature threshold is 170°C and the first duration is 5 seconds; the second temperature threshold is 185°C and the second duration is 3 seconds; the third temperature threshold is 150°C and the third duration is 3 seconds.

4. The monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris as described in claim 1, characterized in that, The preset threshold is determined by statistical analysis of bearing damage morphology and at least three sets of bearing fatigue propagation test results; the size of the metal chips is measured by stereomicroscopy.

5. The monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris as described in claim 1, characterized in that, At least two temperature sensors are used to monitor the temperature. The temperature value selection strategy is as follows: if the deviation of multiple sensor readings is within ±5℃, the average value is taken; otherwise, the larger value is taken.

6. The monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris as described in claim 1, characterized in that, Before triggering a temperature alarm, the validity of the temperature sensor signal is checked. The detection methods include one or more of line bit detection, parameter range detection, and slope detection.

7. A monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris, wherein the monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris as described in any one of claims 1-6 is characterized in that, include: Magnetic debris detector, temperature sensor, and signal processing and alarm device; The magnetic chip detector is installed in the lubricating oil outlet pipeline of the aircraft engine bearing to capture metal chips generated by bearing shedding. At least two temperature sensors are used, both of which are installed on the outer surface of the bearing housing to detect the temperature of the bearing housing. The signal processing and alarm device is connected to the magnetic debris detector and the temperature sensor respectively. It is used to receive temperature signals, perform validity detection, execute combinational logic judgment, and output alarm control signals.

8. The monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris as described in claim 7, characterized in that, The magnetic debris detector includes a detection head assembly and a housing assembly that cooperate with each other; the detection head assembly is equipped with a permanent magnet, and the detection head assembly can be installed or removed from the housing assembly by rotation.

9. The monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris as described in claim 7, characterized in that, The temperature sensor is a platinum resistance thermometer that outputs a resistance signal.

10. The monitoring device for engine bearing failure based on the synergistic detection of wall temperature and chip debris according to claim 7, characterized in that, The signal processing and alarm device includes a processor, a line BIT module, a wall temperature alarm light, and a cockpit alarm light; the line BIT module, the wall temperature alarm light, and the cockpit alarm light are all electrically connected to the processor, and the temperature sensor is electrically connected to the processor via a line.

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