A monitoring method and system for a low-pressure oil sensing system of an aircraft engine

Abstract

The present invention discloses a monitoring method and system for a low-pressure lubricating oil sensing system of an aircraft engine. The method includes: monitoring first engine parameters during the starting stage and shutdown stage of the engine, and performing event trigger condition detection; when the event trigger conditions are met, obtaining second engine parameters, generating a warning message based on the second engine parameters; performing cumulative analysis on the warning message, and performing fault prediction on the low-pressure lubricating oil sensor according to the cumulative analysis result of the warning message. The present invention can realize automatic identification and monitoring of abnormal states of the low-pressure lubricating oil sensor, can detect faults of the engine low-pressure lubricating oil sensor in a timely and accurate manner, thereby avoiding the occurrence of delay events and ensuring the safety of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engines, and in particular to a monitoring method and system for a low-pressure lubricating oil sensing system of an aircraft engine. Background Art

[0002] At present, civil aviation engines mainly use turbofan engines, and the lubricating oil system is one of the key systems of a turbofan engine, mainly playing roles such as lubrication, cleaning, cooling, anti-corrosion, vibration damping and buffering. Since the lubricating oil system plays a key role in each system of the engine, once the lubricating oil system malfunctions, it will cause irreversible damage to the rotating components of the engine at best, and at worst, it will cause the engine to stop in the air, that is, the so-called air stop, posing a great threat to flight safety. Therefore, aircraft engines are all designed and installed with an engine low-pressure lubricating oil sensing system to monitor whether the lubricating oil system of the engine is working properly.

[0003] Taking the low-pressure lubricating oil sensing system of a V2500 engine as an example, it consists of a low-pressure lubricating oil sensor, related pipelines, and related warning computers. The low-pressure lubricating oil sensor is a separate sensor established independently of the lubricating oil pressure indicating system, used to monitor the working pressure of the lubricating oil system, and also used to provide signals representing the operating state of the engine for each system of the aircraft on the ground. The low-pressure lubricating oil sensor is connected to the supply and return oil pipelines, and the operating pressure is 58 - 62 PSI; when the pressure difference between the two lubricating oil pipelines is lower than 58 - 62 PSI, the internal spring of the low-pressure lubricating oil sensor will stretch, and the internal pin will act in the direction of the return oil pipeline. The actuation of the pin will cause the bellows to follow, and the internal circuit will return to the closed position. When the engine is not running, the internal circuit of the low-pressure lubricating oil sensor is in the closed state. When the engine is running, when the lubricating oil pressure sensed by the low-pressure lubricating oil sensor is higher than the preset value, the low-pressure lubricating oil sensor actuates, and the internal circuit of the low-pressure lubricating oil sensor is in the open state. At this time, it indicates that the engine is in the running state, and this signal is given to each system of the aircraft through the EIU. If the lubricating oil pressure drops below 60 PSI ± 1 PSI (decrease) when the engine is running, the low-pressure lubricating oil sensor closes, and the low-pressure discrete information will be given to the FWC computer and, according to the working state of the engine at that time, determine whether to trigger a warning message for low-pressure lubricating oil to prompt the crew that the lubricating oil system is malfunctioning. The crew makes a judgment according to the crew operation manual and decides whether to shut down the engine to protect the engine and avoid serious damage to the engine or even safety problems due to the abnormality of the lubricating oil system.

[0004] In the existing A320 series aircraft V2500 fleet, the engine oil low pressure sensor fails at the high pressure level, which will cause the engine oil low pressure sensor to send out high pressure parameters when the engine is not running. Each system of the aircraft receives false engine running signals, and the FWC will determine that there is a hydraulic system failure. At the same time, it will also trigger abnormal heating faults of the windshield and probes. This fault does not trigger any fault record information and is not easily detected during routine line inspections. Once the engine oil low pressure sensor fails on the ground, it will cause a cockpit effect. The fault phenomena are abnormal heating of the windshield, abnormal heating of the probes, the two hydraulic warning system fault lights are on, and the CVR test is abnormal. The MMEL cannot be released, which is extremely likely to cause flight irregularities. At this time, the engine oil low pressure sensor fault always remains at the high pressure level, losing the monitoring function of the actual oil low pressure state of the oil system. Once a real oil low pressure situation occurs, no alarm will be generated, which is extremely likely to cause serious damage and safety problems to the engine. It can be seen that the existing triggering method of the engine oil low pressure sensor fault design has problems such as untimely fault discovery, strong randomness, and unpredictability, which are extremely likely to cause flight delays and even lay a hidden danger for more serious faults. Summary of the Invention

[0005] An embodiment of the present invention provides a monitoring method and system for an oil low pressure sensing system of an aircraft engine, which can detect engine oil low pressure sensor faults in a timely and accurate manner, thereby avoiding the occurrence of delay events and ensuring aircraft safety.

[0006] In a first aspect, an embodiment of the present invention provides a monitoring method for an oil low pressure sensing system of an aircraft engine, including:

[0007] Monitoring first engine parameters during the engine starting stage and shutdown stage; wherein, the first engine parameters are related to the oil system and the oil low pressure sensor;

[0008] Performing event trigger condition detection according to the first engine parameters during the engine starting stage and shutdown stage;

[0009] When the event trigger condition is satisfied, obtaining second engine parameters and generating a warning message according to the second engine parameters;

[0010] Performing cumulative analysis on the warning message and performing fault prediction on the oil low pressure sensor according to the cumulative analysis result of the warning message.

[0011] As an improvement of the above solution, the first engine parameters include flight segment, corrected N2 speed of the left engine, corrected N2 speed of the right engine, left engine oil temperature, right engine oil temperature, left engine oil low pressure sensor status, right engine oil low pressure sensor status, left engine oil pressure, and right engine oil pressure.

[0012] As an improvement to the above solution, the event trigger condition detection based on the first engine parameters of the engine during the starting phase and the engine shutdown phase includes:

[0013] Monitoring the starting phase conditions according to the first engine parameters of the engine during the starting phase; wherein, the starting phase conditions include the left engine starting phase conditions and the right engine starting phase conditions;

[0014] When the left engine starting phase conditions are met, the first cumulative duration value is incremented by one;

[0015] When the right engine starting phase conditions are met, the second cumulative duration value is incremented by one;

[0016] Monitoring the engine shutdown phase conditions according to the first engine parameters of the engine during the engine shutdown phase; wherein, the engine shutdown phase conditions include the left engine shutdown phase conditions and the right engine shutdown phase conditions;

[0017] When the left engine shutdown phase conditions are met, the third cumulative duration value is incremented by one;

[0018] When the right engine shutdown phase conditions are met, the fourth cumulative duration value is incremented by one;

[0019] Judging whether the event trigger conditions are met according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value.

[0020] As an improvement to the above solution, the judging whether the event trigger conditions are met according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value includes:

[0021] Judging whether the preset duration comparison conditions are met according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value; wherein, the duration comparison conditions include: the first cumulative duration value is greater than a preset first duration threshold, the second cumulative duration value is greater than a preset second duration threshold, the third cumulative duration value is greater than a preset third duration threshold, and the fourth cumulative duration value is greater than a preset fourth duration threshold;

[0022] When at least one of the duration comparison conditions is met, it is determined that the event trigger conditions are met;

[0023] When none of the duration comparison conditions is met, it is determined that the event trigger conditions are not met.

[0024] As an improvement to the above solution, the conditions for the left engine starting phase include: the flight segment is within a preset first flight segment threshold range, the corrected N2 speed of the left engine is less than the first speed threshold, the lubricating oil pressure of the left engine is less than the first pressure threshold, the lubricating oil temperature of the left engine is greater than the first temperature threshold, and the state of the low-pressure lubricating oil sensor of the left engine is a high-pressure parameter.

[0025] As an improvement to the above solution, the conditions for the right engine starting phase include: the flight segment is within a preset first flight segment threshold range, the corrected N2 speed of the right engine is less than the second speed threshold, the lubricating oil pressure of the right engine is less than the second pressure threshold, the lubricating oil temperature of the right engine is greater than the second temperature threshold, and the state of the low-pressure lubricating oil sensor of the right engine is a high-pressure parameter.

[0026] As an improvement to the above solution, the conditions for the left engine shutdown phase include: the flight segment is within a preset second flight segment threshold range, the corrected N2 speed of the left engine is less than the third speed threshold, the lubricating oil pressure of the left engine is less than the third pressure threshold, and the state of the low-pressure lubricating oil sensor of the left engine is a high-pressure parameter.

[0027] As an improvement to the above solution, the conditions for the right engine shutdown phase include: the flight segment is within a preset second flight segment threshold range, the corrected N2 speed of the right engine is less than the fourth speed threshold, the lubricating oil pressure of the right engine is less than the fourth pressure threshold, and the state of the low-pressure lubricating oil sensor of the right engine is a high-pressure parameter.

[0028] As an improvement to the above solution, the fault prediction of the low-pressure lubricating oil sensor according to the cumulative analysis result of the warning message includes:

[0029] When the cumulative analysis result of the warning message meets the preset functional fault critical condition, it is predicted that the low-pressure lubricating oil sensor will switch from the potential fault state to the functional fault critical state;

[0030] Among them, the functional fault critical condition includes: the fault trigger time for generating the warning message exceeds the fifth time threshold, the warning message is triggered both in the starting phase and the shutdown phase, and the warning message is triggered in consecutive multiple flight segments.

[0031] In a second aspect, an embodiment of the present invention provides a monitoring system for a low-pressure lubricating oil sensing system of an aircraft engine, including:

[0032] A data monitoring module for monitoring first engine parameters of the engine in the starting phase and the shutdown phase; wherein, the first engine parameters are related to the lubricating oil system and the low-pressure lubricating oil sensor;

[0033] An event trigger detection module for detecting event trigger conditions based on first engine parameters during the engine starting phase and engine shutdown phase;

[0034] An early warning module for obtaining second engine parameters and generating an early warning message based on the second engine parameters when the event trigger conditions are met; wherein the second engine parameters are related to the lubricating oil system and the critical engine.

[0035] A fault prediction module for cumulatively analyzing the early warning message and predicting faults of the lubricating oil low pressure sensor based on the cumulative analysis result of the early warning message.

[0036] Compared with the prior art, the beneficial effects of the embodiments of the present invention are as follows:

[0037] By monitoring the first engine parameters during the engine starting phase and engine shutdown phase, event trigger conditions are detected; when the event trigger conditions are met, second engine parameters are obtained and an early warning message is generated based on the second engine parameters; the early warning message is cumulatively analyzed, and faults of the lubricating oil low pressure sensor are predicted based on the cumulative analysis result of the early warning message. The present invention can realize automatic identification and monitoring of abnormal states of the lubricating oil low pressure sensor in the lubricating oil low pressure sensing system, is applicable to different aircraft models, and has good versatility; at the same time, by cumulatively analyzing the second engine parameters of the early warning message, monitoring and trend analysis of the second engine parameters of the early warning message are realized, and further, the performance degradation of the lubricating oil low pressure sensor can be determined, and faults of the engine lubricating oil low pressure sensor can be detected timely and accurately, thereby avoiding the occurrence of delay events and ensuring the safety of the aircraft. Description of the Drawings

[0038] In order to more clearly illustrate the technical solutions of the present invention, the drawings to be used in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention, and those of ordinary skill in the art can obtain other drawings based on these drawings without creative efforts.

[0039] Figure 1 It is a flowchart of a method for monitoring a lubricating oil low pressure sensing system of an aircraft engine provided by an embodiment of the present invention;

[0040] Figure 2 It is a flowchart of engine starting phase monitoring provided by an embodiment of the present invention;

[0041] Figure 3 It is a flowchart of engine shutdown phase monitoring provided by an embodiment of the present invention;

[0042] Figure 4It is the flowchart of the fault alarm of the low-pressure lubricating oil sensor provided by the embodiment of the present invention;

[0043] Figure 5 It is the schematic block diagram of a monitoring system for the low-pressure lubricating oil sensing system of an aircraft engine provided by the embodiment of the present invention. Specific embodiments

[0044] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative work shall fall within the protection scope of the present invention.

[0045] For the convenience of understanding, the following explanations are made for the parameters involved in this article:

[0046] PHASE1: Flight segment;

[0047] N2C261: Left engine N2 speed correction value;

[0048] N2C262: Right engine N2 speed correction value;

[0049] OIT1: Left engine lubricating oil temperature;

[0050] OIT2: Right engine lubricating oil temperature;

[0051] OILPRS1: Left engine low-pressure lubricating oil sensor status;

[0052] OILPRS2: Right engine low-pressure lubricating oil sensor status;

[0053] ENG 1MASTER: Left engine main switch;

[0054] ENG 2MASTER: Right engine main switch;

[0055] OIP1: Left engine lubricating oil pressure;

[0056] OIP2: Right engine lubricating oil pressure.

[0057] Embodiment 1

[0058] Please refer to Figure 1 , which is the flowchart of a method for monitoring the low-pressure lubricating oil sensing system of an aircraft engine provided by the embodiment of the present invention.

[0059] The method for monitoring the low-pressure lubricating oil sensing system of the aircraft engine includes:

[0060] S1: Monitor the first engine parameters during the engine start-up phase and the engine shutdown phase; wherein, the first engine parameters are related to the lubricating oil system and the low lubricating oil pressure sensor;

[0061] Wherein, the first engine parameters include flight segment, corrected N2 speed of the left engine, corrected N2 speed of the right engine, lubricating oil temperature of the left engine, lubricating oil temperature of the right engine, status of the low lubricating oil pressure sensor of the left engine, status of the low lubricating oil pressure sensor of the right engine, lubricating oil pressure of the left engine, and lubricating oil pressure of the right engine.

[0062] The 9 stages that an aircraft may include within a flight segment are, in sequence, before engine start, after engine start, taxiing before takeoff, takeoff, cruise, descent, landing, taxiing after landing, and engine shutdown. A flight segment represents the entire process of a flight from standstill to flight and then back to standstill.

[0063] S2: Detect event trigger conditions based on the first engine parameters during the engine start-up phase and the engine shutdown phase;

[0064] S3: When the event trigger conditions are met, obtain the second engine parameters and generate a warning message based on the second engine parameters;

[0065] Wherein, the second engine parameters include flight segment, corrected N2 speed of the left engine, corrected N2 speed of the right engine, lubricating oil temperature of the left engine, lubricating oil temperature of the right engine, status of the low lubricating oil pressure sensor of the left engine, status of the low lubricating oil pressure sensor of the right engine, lubricating oil pressure of the left engine, lubricating oil pressure of the right engine, main switch of the left engine, and main switch of the right engine. The second engine parameters trigger a warning message according to a preset message format and / or output the second engine parameters by email.

[0066] S4: Conduct cumulative analysis on the warning message and perform fault prediction on the low lubricating oil pressure sensor based on the cumulative analysis result of the warning message.

[0067] Exemplarily, in the embodiments of the present invention, a QAR (Quick access recorder) may be used to collect the first engine parameters of the aircraft engine during the starting phase and the shutdown phase. Then, the monitoring logic of the above steps S1 - S4 is executed through a QAR decoding platform to monitor the status of the low - pressure oil sensor, realize the automatic identification and monitoring of the abnormal status of the low - pressure oil sensor, be applicable to different aircraft models, and have good versatility; at the same time, the information of the sensor in the abnormal state and the relevant parameters required for fault analysis can be extracted in the first time. Through cumulative analysis, the monitoring and trend analysis of the second engine parameters of the warning message are realized, and then the performance degradation of the low - pressure oil sensor can be determined, and the fault of the engine low - pressure oil sensor can be detected in a timely and accurate manner, so as to avoid the occurrence of delay events and ensure the safety of the aircraft.

[0068] In an alternative embodiment, S2: Detect the event trigger conditions according to the first engine parameters of the engine during the starting phase and the shutdown phase, including:

[0069] S21: Monitor the starting - phase conditions according to the first engine parameters of the engine during the starting phase; wherein, the starting - phase conditions include the starting - phase conditions of the left engine and the starting - phase conditions of the right engine;

[0070] Among them, the starting - phase conditions of the left engine include: the flight segment is within the preset first flight - segment threshold range, the corrected N2 speed of the left engine is less than the first speed threshold, the oil pressure of the left engine is less than the first pressure threshold, the oil temperature of the left engine is greater than the first temperature threshold, and the status of the low - pressure oil sensor of the left engine is a high - pressure parameter.

[0071] The starting - phase conditions of the right engine include: the flight segment is within the preset first flight - segment threshold range, the corrected N2 speed of the right engine is less than the second speed threshold, the oil pressure of the right engine is less than the second pressure threshold, the oil temperature of the right engine is greater than the second temperature threshold, and the status of the low - pressure oil sensor of the right engine is a high - pressure parameter.

[0072] S22: When the starting - phase conditions of the left engine are met, the first cumulative duration value is incremented by one;

[0073] S23: When the starting - phase conditions of the right engine are met, the second cumulative duration value is incremented by one;

[0074] S24: Monitor the shutdown - phase conditions according to the first engine parameters of the engine during the shutdown phase; wherein, the shutdown - phase conditions include the shutdown - phase conditions of the left engine and the shutdown - phase conditions of the right engine;

[0075] Among them, the shutdown stage conditions of the left engine include: the flight segment is within a preset second flight segment threshold range, the corrected N2 speed value of the left engine is less than a third speed threshold, the lubricating oil pressure of the left engine is less than a third pressure threshold, and the state of the low-pressure lubricating oil sensor of the left engine is a high-pressure parameter.

[0076] The shutdown stage conditions of the right engine include: the flight segment is within a preset second flight segment threshold range, the corrected N2 speed value of the right engine is less than a fourth speed threshold, the lubricating oil pressure of the right engine is less than a fourth pressure threshold, and the state of the low-pressure lubricating oil sensor of the right engine is a high-pressure parameter.

[0077] S25: When the shutdown stage conditions of the left engine are satisfied, the third cumulative duration value is incremented by one;

[0078] S26: When the shutdown stage conditions of the right engine are satisfied, the fourth cumulative duration value is incremented by one;

[0079] S27: Determine whether the event trigger condition is satisfied according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value.

[0080] Further, determining whether the event trigger condition is satisfied according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value includes:

[0081] Determine whether a preset duration comparison condition is satisfied according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value; among them, the duration comparison condition includes: the first cumulative duration value is greater than a preset first duration threshold, the second cumulative duration value is greater than a preset second duration threshold, the third cumulative duration value is greater than a preset third duration threshold, and the fourth cumulative duration value is greater than a preset fourth duration threshold;

[0082] When at least one of the duration comparison conditions is satisfied, it is determined that the event trigger condition is satisfied;

[0083] When none of the duration comparison conditions is satisfied, it is determined that the event trigger condition is not satisfied.

[0084] It should be noted that in the embodiments of the present invention, the specific numerical ranges of the first flight segment threshold range, the second flight segment threshold range, the first rotational speed threshold, the first pressure threshold, the first temperature threshold, the second rotational speed threshold, the second pressure threshold, the second temperature threshold, the third rotational speed threshold, the third pressure threshold, the fourth rotational speed threshold, the fourth pressure threshold, the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value are not specifically limited. Users can customize the settings according to actual needs. For example, the first flight segment threshold range is [1, 2], the second flight segment threshold range is [9, 10], the first rotational speed threshold is 22, the first pressure threshold is 50, the first temperature threshold is 0, the second rotational speed threshold is 22, the second pressure threshold is 50, the second temperature threshold is 0, the third rotational speed threshold is 25, the third pressure threshold is 50, the fourth rotational speed threshold is 25, the fourth pressure threshold is 50, the first cumulative duration value is 1 s, the second cumulative duration value is 1 s, the third cumulative duration value is 1 s, and the fourth cumulative duration value is 1 s. Among them, the initial values of the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value are 0.

[0085] Exemplarily, the monitoring logic for the engine starting phase is as follows:

[0086] (1) For the left engine starting phase: When 1 ≤ PHASE1 ≤ 2, N2C261 < the first rotational speed threshold, OIP1 < the first pressure threshold, OIT1 > the first temperature threshold, and OILPRS1 = high-pressure parameter are satisfied, the custom parameter first cumulative duration value is incremented by one. If the first cumulative duration value > the first duration threshold, it is determined that an event is triggered in the left engine starting phase, as Figure 2 shown.

[0087] (2) For the right engine starting phase: When 1 ≤ PHASE1 ≤ 2, N2C262 < the second rotational speed threshold, OIP2 < the second pressure threshold, OIT2 > the second temperature threshold, and OILPRS2 = high-pressure parameter are satisfied, the custom parameter second cumulative duration value is incremented by one. If the second cumulative duration value > the second duration threshold, it is determined that an event is triggered in the right engine starting phase.

[0088] The monitoring logic for the engine shutdown phase is as follows:

[0089] (3) For the left engine shutdown phase: 9 ≤ PHASE1 ≤ 10, N2C261 < the third rotational speed threshold, OIP1 < the third pressure threshold, and OILPRS1 = high pressure parameter, then the custom parameter third cumulative duration value is incremented by one. If the third cumulative duration value > the third duration threshold, then it is determined that an event is triggered in the left engine shutdown phase, such as Figure 3 as shown.

[0090] (4) For the right engine shutdown phase: 9 ≤ PHASE1 ≤ 10, N2C262 < the fourth rotational speed threshold, OIP2 < the fourth pressure threshold, and OILPRS2 = high pressure parameter, then the custom parameter fourth cumulative duration value is incremented by one. If the fourth cumulative duration value > the fourth duration threshold, then it is determined that an event is triggered in the right engine shutdown phase.

[0091] According to the above engine startup phase monitoring logic and engine shutdown phase monitoring logic, as long as one of the four cumulative duration values, namely the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value, is greater than 1 s, the event trigger condition is satisfied.

[0092] In an alternative embodiment, S4: Perform a fault prediction on the low oil pressure sensor according to the cumulative analysis result of the warning message, including:

[0093] When the cumulative analysis result of the warning message meets the preset functional fault critical condition, predict that the low oil pressure sensor transitions from a potential fault state to a functional fault critical state;

[0094] Among them, the functional fault critical condition includes: the fault trigger time for generating the warning message exceeds the fifth duration threshold, warning messages are triggered both in the startup phase and the shutdown phase, and warning messages are triggered in consecutive multiple flight segments.

[0095] Among them, the fifth duration threshold is 20 s. Exemplarily, after the QAR data is decoded by the QAR data ground server, it is sent to the data analysis platform, such as the QAR decoding platform. The data is preprocessed and analyzed on the data analysis platform, and when the functional fault critical condition is triggered, the data is sent by email to the corresponding user terminal. Among them, data preprocessing includes the processing of abnormal point data and skipped frame data in the first engine parameter to avoid false alarms caused by false data.

[0096] The fault prediction principle of the low oil pressure sensor is as follows:

[0097] The fault trigger time exceeds 20 seconds; among them, the fault trigger time is the cumulative duration starting from the triggering of the warning message;

[0098] During the engine startup phase: 1 ≤ flight segment one ≤ 2, during the engine shutdown phase: 9 ≤ flight segment two ≤ 10, at this time it is determined that both the engine shutdown and the next startup phases trigger an alarm;

[0099] Alarms are triggered in 5 consecutive flight segments.

[0100] When the above three conditions are met simultaneously, it is determined that predictive maintenance of the low oil pressure sensor is required. The specific process is as Figure 4 shown.

[0101] Taking the V2500 engine of the Airbus A320 series aircraft as an example, the low oil pressure sensor of the V2500 engine can output two parameters: high pressure parameter and low pressure parameter, which are reflected in the decoded data corresponding to the conversion between the two states of "1" and "0". As long as the engine is running, the parameter information of this sensor will be stored in the QAR (Quick Access Recorder) through the EIU (Engine Interface Unit) and FDIMU (Flight Data Interface and Management Unit). When the aircraft lands and the engine shuts down, the parameter data stored in the QAR will be transmitted to the ground server as analysis data. After the QAR data is decoded by the QAR data ground server, it is sent to the QAR decoding platform. Data preprocessing and analysis are carried out on the QAR decoding platform. When the event trigger condition is met, the data is sent to the corresponding user terminal by email. After the user terminal receives the message email, the message is analyzed to formulate corresponding measures.

[0102] By collecting decoded data to analyze the historical low oil pressure sensor failure cases of the fleet, analyzing the N2 speed and OIP data of the engine when the low oil pressure sensor is in the high pressure position at the engine startup and shutdown moments, and at the same time comparing and collecting the engine parameters corresponding to the moment when the low oil pressure sensor outputs the high pressure parameter under normal engine startup and shutdown conditions. And considering the characteristics of low temperature in winter in the north and high viscosity of the engine oil before flight, the event trigger condition is corrected using the engine oil temperature parameter. The monitoring logic of this sensor failure is as follows. When condition (a) or condition (b) is met, a warning is output:

[0103] (a) During the engine startup phase, the engine oil temperature is greater than 0 °C, N2C26 is less than 22%, the engine oil pressure is less than 50, and at the same time the low oil pressure sensor outputs the high pressure parameter;

[0104] (b) During the engine shutdown phase, N2C26 is less than 25%, the engine oil pressure is less than 50, and at the same time the low oil pressure sensor outputs the high pressure parameter;

[0105] Through the retrospective analysis of the fleet data and the accumulation of fault data, it is found that the impending functional fault situation is related to the triggering frequency and duration of the prediction models (a) and (b). After meeting the following conditions, the predicted low oil pressure sensor is about to convert from a potential fault to a critical state of functional fault, and troubleshooting is required. Therefore, the principle for issuing the predictive maintenance instruction is set as:

[0106] The fault trigger time exceeds 20 seconds;

[0107] Alarms are triggered during both the engine shutdown and the next startup phases;

[0108] Alarms are triggered in 5 consecutive flight segments;

[0109] After the implementation of this item through data statistics, no functional faults of the low oil pressure sensor have occurred in the fleet. It can be seen that the embodiment of the present invention can effectively improve the working reliability of the engine oil system and reduce the misreplacement of the low oil pressure sensor.

[0110] The sample example of the message format of the early warning message is as follows:

[0111] Aircraft number: XXX;

[0112] Base: XXX;

[0113] Aircraft type: XXX;

[0114] Engine: XXX;

[0115] APU: XXX;

[0116] Flight number: XXX;

[0117] Start time: XXX;

[0118] End time: XXX;

[0119] Abnormal data recording time: XXX;

[0120] Warning information:

[0121] The start failure time of the left engine low oil pressure switch is 0 seconds;

[0122] The shutdown failure time of the left engine low oil pressure switch is 0 seconds;

[0123] The start failure time of the right engine low oil pressure switch is 3 seconds;

[0124] The shutdown failure time of the right engine low oil pressure switch is 140 seconds;

[0125] Monitoring logic and remarks information:

[0126] 1. During engine shutdown, the V2500 engine oil low pressure switch (4000EN) fails in the high pressure position (normally, a low pressure signal should be output).

[0127] 2. On the ground, it may cause the blue pump and the engine hydraulic drive pump fault lights on one side to light up, and there is no sound during the CVR test or the windshield ground heating fails.

[0128] 3. Immediately screen the spare parts for the oil low pressure switch. The outstation can take appropriate measures to release the aircraft.

[0129] 4. Currently, the model is affected by the main switch and is prone to wild point false alarms. It is recommended to verify by decoding before troubleshooting. Generally, alarms are triggered during the start-up process and the shutdown process, and the probability of switch failure is high. If an engine frequently triggers an alarm, the probability of switch failure is high.

[0130] 5. If a warning message is triggered, it is recommended to measure the low pressure switch circuit on the ground, that is, the resistance value of the No. 1 and No. 2 pins of the vehicle body. Under normal ground conditions, the No. 1 and No. 2 pins of the low pressure switch are in the connected state. When a fault occurs, the resistance value of the No. 1 and No. 2 pins deviates or is infinite.

[0131] Compared with the prior art, the beneficial effects of the embodiments of the present invention are as follows:

[0132] The embodiments of the present invention can automatically identify and monitor the abnormal state of the oil low pressure sensor in the oil low pressure sensing system, are applicable to different aircraft models, and have good versatility. At the same time, by cumulatively analyzing the second engine parameters of the warning message, the monitoring and trend analysis of the second engine parameters of the warning message are realized. Furthermore, the performance degradation of the oil low pressure sensor can be determined, and the engine oil low pressure sensor fault can be detected in a timely and accurate manner, thereby avoiding delays and ensuring the safety of the aircraft and the on-time arrival of flights.

[0133] The embodiments of the present invention can monitor the health status of the oil low pressure sensing system of the V2500 engine, enabling engineering personnel to better understand the condition of the oil low pressure sensing system, which is conducive to predictive maintenance of the oil low pressure sensing system, preventing functional failures from occurring, and avoiding delays. For example, when the monitored conditions meet the critical conditions of the functional failure, it is predicted that the oil low pressure sensor will switch from the potential failure state to the critical state of the functional failure, providing data support for engineering personnel to perform maintenance and realizing precise maintenance.

[0134] Embodiment 2

[0135] Please refer to Figure 5 , the embodiments of the present invention provide a monitoring system for the oil low pressure sensing system of an aircraft engine, including:

[0136] The data monitoring module 1 is used to monitor the first engine parameters during the engine starting phase and the engine shutdown phase; wherein, the first engine parameters are related to the lubricating oil system and the low lubricating oil pressure sensor;

[0137] The event trigger detection module 2 is used to perform event trigger condition detection according to the first engine parameters during the engine starting phase and the engine shutdown phase;

[0138] The warning module 3 is used to obtain the second engine parameters and generate a warning message according to the second engine parameters when the event trigger condition is satisfied; wherein, the second engine parameters are related to the lubricating oil system and the key engine.

[0139] The fault prediction module 4 is used to perform cumulative analysis on the warning message and perform fault prediction on the low lubricating oil pressure sensor according to the cumulative analysis result of the warning message.

[0140] In an optional embodiment, the first engine parameters include flight segment, corrected N2 speed of the left engine, corrected N2 speed of the right engine, lubricating oil temperature of the left engine, lubricating oil temperature of the right engine, status of the low lubricating oil pressure sensor of the left engine, status of the low lubricating oil pressure sensor of the right engine, lubricating oil pressure of the left engine, and lubricating oil pressure of the right engine.

[0141] In an optional embodiment, the event trigger detection module 2 includes:

[0142] The first condition monitoring unit is used to perform starting phase condition monitoring according to the first engine parameters during the engine starting phase; wherein, the starting phase conditions include the starting phase conditions of the left engine and the starting phase conditions of the right engine;

[0143] The first duration accumulation unit is used to increment the first accumulated duration value by one when the starting phase conditions of the left engine are satisfied;

[0144] The second duration accumulation unit is used to increment the second accumulated duration value by one when the starting phase conditions of the right engine are satisfied;

[0145] The second condition monitoring unit is used to perform shutdown phase condition monitoring according to the first engine parameters during the engine shutdown phase; wherein, the shutdown phase conditions include the shutdown phase conditions of the left engine and the shutdown phase conditions of the right engine;

[0146] The third duration accumulation unit is used to increment the third accumulated duration value by one when the shutdown phase conditions of the left engine are satisfied;

[0147] The fourth duration accumulation unit is used to increment the fourth accumulated duration value by one when the shutdown phase conditions of the right engine are satisfied;

[0148] A third condition monitoring unit, configured to determine whether the event trigger condition is satisfied according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value.

[0149] In an alternative embodiment, the third condition monitoring unit is specifically configured to:

[0150] Determine whether a preset duration comparison condition is satisfied according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value; wherein, the duration comparison condition includes: the first cumulative duration value is greater than a preset first duration threshold, the second cumulative duration value is greater than a preset second duration threshold, the third cumulative duration value is greater than a preset third duration threshold, and the fourth cumulative duration value is greater than a preset fourth duration threshold;

[0151] When at least one of the duration comparison conditions is satisfied, it is determined that the event trigger condition is satisfied;

[0152] When none of the duration comparison conditions is satisfied, it is determined that the event trigger condition is not satisfied.

[0153] In an alternative embodiment, the left engine start-up phase conditions include: the flight segment is within a preset first flight segment threshold range, the corrected N2 speed of the left engine is less than a first speed threshold, the lubricating oil pressure of the left engine is less than a first pressure threshold, the lubricating oil temperature of the left engine is greater than a first temperature threshold, and the status of the left engine lubricating oil low-pressure sensor is a high-pressure parameter.

[0154] In an alternative embodiment, the right engine start-up phase conditions include: the flight segment is within a preset first flight segment threshold range, the corrected N2 speed of the right engine is less than a second speed threshold, the lubricating oil pressure of the right engine is less than a second pressure threshold, the lubricating oil temperature of the right engine is greater than a second temperature threshold, and the status of the right engine lubricating oil low-pressure sensor is a high-pressure parameter.

[0155] In an alternative embodiment, the left engine shutdown phase conditions include: the flight segment is within a preset second flight segment threshold range, the corrected N2 speed of the left engine is less than a third speed threshold, the lubricating oil pressure of the left engine is less than a third pressure threshold, and the status of the left engine lubricating oil low-pressure sensor is a high-pressure parameter.

[0156] In an alternative embodiment, the right engine shutdown phase conditions include: the flight segment is within a preset second flight segment threshold range, the corrected N2 speed of the right engine is less than a fourth speed threshold, the lubricating oil pressure of the right engine is less than a fourth pressure threshold, and the status of the right engine lubricating oil low-pressure sensor is a high-pressure parameter.

[0157] In an alternative embodiment, the fault prediction module 4 includes:

[0158] A fourth condition monitoring unit, configured to predict that the lubricating oil low-pressure sensor converts from a potential fault state to a functional fault critical state when the cumulative analysis result of the warning message meets a preset functional fault critical condition;

[0159] Wherein, the functional fault critical condition includes: the fault trigger time for triggering the generation of the warning message exceeds a fifth duration threshold, the warning message is triggered both in the starting stage and the shutdown stage, and the warning message is triggered in multiple consecutive flight segments.

[0160] It should be noted that the technical principle and the achieved technical effect of the embodiment of the present invention are the same as those of the first embodiment, and will not be elaborated here.

[0161] It should be noted that the device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units. They may be located in one place or distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. In addition, in the attached drawings of the device embodiments provided by the present invention, the connection relationship between the modules indicates that they have a communication connection, which can be specifically implemented as one or more communication buses or signal lines. Those of ordinary skill in the art can understand and implement without creative efforts.

[0162] The above is the preferred embodiment of the present invention. It should be pointed out that for those of ordinary skill in the art in this technical field, without departing from the principle of the present invention, many improvements and refinements can still be made, and these improvements and refinements are also regarded as the protection scope of the present invention.

Claims

1. A monitoring method for the low-pressure oil sensing system of an aircraft engine, characterized in that, it includes: monitoring first engine parameters during the starting phase and shutdown phase of the engine; wherein, the first engine parameters are related to the oil system and the low-pressure oil sensor; performing event trigger condition detection based on the first engine parameters during the starting phase and shutdown phase of the engine; when the event trigger conditions are met, obtaining second engine parameters and generating a warning message based on the second engine parameters; performing cumulative analysis on the warning message and performing fault prediction on the low-pressure oil sensor based on the cumulative analysis result of the warning message.

2. The monitoring method for the low-pressure oil sensing system of an aircraft engine according to claim 1, characterized in that, the first engine parameters include flight segment, corrected N2 speed of the left engine, corrected N2 speed of the right engine, oil temperature of the left engine, oil temperature of the right engine, status of the low-pressure oil sensor of the left engine, status of the low-pressure oil sensor of the right engine, oil pressure of the left engine, and oil pressure of the right engine.

3. The monitoring method for the low-pressure oil sensing system of an aircraft engine according to claim 2, characterized in that, the performing event trigger condition detection based on the first engine parameters during the starting phase and shutdown phase of the engine includes: performing starting phase condition monitoring based on the first engine parameters during the starting phase of the engine; wherein, the starting phase conditions include the starting phase condition of the left engine and the starting phase condition of the right engine; when the starting phase condition of the left engine is met, the first cumulative duration value is incremented by one; when the starting phase condition of the right engine is met, the second cumulative duration value is incremented by one; performing shutdown phase condition monitoring based on the first engine parameters during the shutdown phase of the engine; wherein, the shutdown phase conditions include the shutdown phase condition of the left engine and the shutdown phase condition of the right engine; when the shutdown phase condition of the left engine is met, the third cumulative duration value is incremented by one; when the shutdown phase condition of the right engine is met, the fourth cumulative duration value is incremented by one; judging whether the event trigger conditions are met according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value.

4. The monitoring method for the low-pressure oil sensing system of an aircraft engine according to claim 3, characterized in that, the judging whether the event trigger conditions are met according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value includes: judging whether the preset duration comparison conditions are met according to the first cumulative duration value, the second cumulative duration value, the third cumulative duration value, and the fourth cumulative duration value; wherein, the duration comparison conditions include: the first cumulative duration value is greater than a preset first duration threshold, the second cumulative duration value is greater than a preset second duration threshold, the third cumulative duration value is greater than a preset third duration threshold, and the fourth cumulative duration value is greater than a preset fourth duration threshold; When at least one of the duration comparison conditions is satisfied, it is determined that the event trigger condition is satisfied; When none of the duration comparison conditions is satisfied, it is determined that the event trigger condition is not satisfied.

5. The method for monitoring the low oil pressure sensing system of an aircraft engine according to claim 3, characterized in that the left engine start-up phase conditions include: the flight segment is within a preset first flight segment threshold range, the corrected N2 speed of the left engine is less than a first speed threshold, the oil pressure of the left engine is less than a first pressure threshold, the oil temperature of the left engine is greater than a first temperature threshold, and the state of the low oil pressure sensor of the left engine is a high-pressure parameter.

6. The method for monitoring the low oil pressure sensing system of an aircraft engine according to claim 3, characterized in that the right engine start-up phase conditions include: the flight segment is within a preset first flight segment threshold range, the corrected N2 speed of the right engine is less than a second speed threshold, the oil pressure of the right engine is less than a second pressure threshold, the oil temperature of the right engine is greater than a second temperature threshold, and the state of the low oil pressure sensor of the right engine is a high-pressure parameter.

7. The method for monitoring the low oil pressure sensing system of an aircraft engine according to claim 3, characterized in that the left engine shutdown phase conditions include: the flight segment is within a preset second flight segment threshold range, the corrected N2 speed of the left engine is less than a third speed threshold, the oil pressure of the left engine is less than a third pressure threshold, and the state of the low oil pressure sensor of the left engine is a high-pressure parameter.

8. The method for monitoring the low oil pressure sensing system of an aircraft engine according to claim 3, characterized in that the right engine shutdown phase conditions include: the flight segment is within a preset second flight segment threshold range, the corrected N2 speed of the right engine is less than a fourth speed threshold, the oil pressure of the right engine is less than a fourth pressure threshold, and the state of the low oil pressure sensor of the right engine is a high-pressure parameter.

9. The method for monitoring the low oil pressure sensing system of an aircraft engine according to claim 1, characterized in that the fault prediction of the low oil pressure sensor according to the cumulative analysis result of the warning message includes: when the cumulative analysis result of the warning message satisfies a preset functional fault critical condition, it is predicted that the low oil pressure sensor will convert from a potential fault state to a functional fault critical state; wherein, the functional fault critical condition includes: the fault trigger time for triggering the generation of the warning message exceeds a fifth duration threshold, the warning message is triggered in both the start-up phase and the shutdown phase, and the warning message is triggered in multiple consecutive flight segments.

10. A monitoring system for the low oil pressure sensing system of an aircraft engine, characterized in that it includes: a data monitoring module for monitoring first engine parameters of the engine in the start-up phase and the shutdown phase; wherein, the first engine parameters are related to the oil system and the low oil pressure sensor; an event trigger detection module for detecting event trigger conditions according to the first engine parameters of the engine in the start-up phase and the shutdown phase. An early warning module, configured to obtain second engine parameters when the event triggering condition is satisfied, and generate an early warning message based on the second engine parameters; wherein, the second engine parameters are related to the lubricating oil system and the critical engine. A fault prediction module, configured to perform cumulative analysis on the early warning message, and perform fault prediction on the lubricating oil low pressure sensor according to the cumulative analysis result of the early warning message.

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