Aircraft engine reverse thrust thermal insulation layer damage monitoring method and system
By constructing a monitoring model, real-time monitoring of engine pod temperature, identifying abnormal data and determining defect types, the problem of the existing technology failing to effectively monitor the low pod temperature, and the identification and alarm of damaged defects of the reverse thrust insulation layer are achieved, and unsafe events and economic losses are reduced during flight.
Patent Information
- Application Number
- CN202311250077.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-09-26
- Publication Date
- 2025-03-28
AI Technical Summary
The prior art fails to effectively monitor the low temperature of the aircraft engine pod, resulting in the failure of the reverse thrust insulation layer that is not identified, increasing unsafe events and economic losses during flight.
By determining monitoring parameters, obtaining data and maintenance records in the historical flight database, building training data, performing data cleaning and feature extraction, establishing monitoring models based on big data analysis methods, monitoring engine operation data in real time, identifying abnormal data and determining defect types, and generating alarms and maintenance plans.
The low temperature of the aircraft engine pod is realized, and the damage defects of the reverse thrust insulation layer are identified, which reduces unsafe events and economic losses in flight, and improves the safety and economicality of fleet operation.
Smart Images
Figure CN119719613A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of aircraft fault monitoring, and in particular to a method and system for monitoring damage of a reverse thrust insulation layer of an aircraft engine. Background Art
[0002] The engine pod temperature sensor is located between the two reverse thrust C-DUCTs at the rear of the fan casing in the bottom area of the engine. It mainly monitors the temperature of the engine core area. The temperature range of the sensor is generally between 0°C and 350°C. The actual temperature is displayed on the engine page of the ECAM. When the temperature exceeds the predicted advisory temperature (260°C), the indicator flashes green to alert the crew in an advisory manner.
[0003] As a secondary parameter for monitoring the engine, the nacelle temperature mainly monitors the temperature changes inside the engine casing to achieve the purpose of monitoring component leakage. The TRENT700 engine of the Airbus A330 aircraft often has problems with the fall-off of the reverse thrust insulation layer and the fuel nozzle sealing defects. In the daily operation of the aircraft, the abnormal temperature of the nacelle can often indirectly reflect such problems, especially the excessive fall-off of the reverse thrust insulation layer. Since it involves the structural defects of the engine nacelle, it is often necessary to replace the entire reverse thrust due to excessive damage, causing great economic losses and flight impacts to the airline. The abnormal nacelle temperature is mainly manifested as the temperature exceeding the normal range. Different temperature abnormalities can often reflect different engine structural defects.
[0004] Because currently aircraft manufacturers only provide over-temperature advisories for high engine nacelle temperatures, and do not monitor or apply data for low engine nacelle temperatures during flight. In the history of China Eastern Airlines' A330 fleet operations, there have been many incidents of structural damage such as the engine core's external fairing or fireproof insulation layer, which can easily lead to unsafe incidents during flight, and even the risk of being unable to effectively extinguish the fire after the engine catches fire. Summary of the invention
[0005] The purpose of the present invention is to overcome the defects of the above-mentioned prior art and to provide an aircraft engine thrust reverser thermal insulation layer damage monitoring method and system for monitoring low nacelle temperature, identifying thrust reverser thermal insulation layer damage defects, and reducing the occurrence of unsafe incidents during aircraft flight.
[0006] The purpose of the present invention can be achieved by the following technical solutions:
[0007] A method for monitoring damage of a reverse thrust insulation layer of an aircraft engine comprises the following steps:
[0008] Determine monitoring parameters, obtain data and maintenance records of the monitoring parameters from a historical flight database of the aircraft, and construct training data;
[0009] The training data is cleaned to extract effective data features; based on the big data analysis method, according to the actual working state of the aircraft engine bleed air system, the change trend of abnormal data is identified and analyzed, and the relationship between the abnormal data and the corresponding defect type is determined, so as to establish a monitoring model;
[0010] The monitoring model is used to monitor the real-time data of the engine operation, identify abnormal data, and determine the corresponding defect type, and generate corresponding alarms and maintenance plans according to the determined fault type;
[0011] The monitoring model is optimized according to the actual operation results and feedback of the monitoring model.
[0012] Furthermore, the monitoring parameters include pod temperature, and the abnormal data identified by the monitoring model includes pod temperature being lower than a preset pod low temperature threshold. If the pod temperature is lower than the preset pod low temperature threshold, the corresponding defect type is determined to include damage to the reverse thrust fire insulation layer.
[0013] Furthermore, the nacelle temperature is monitored by a temperature sensor disposed in the exhaust annular gap of the aircraft.
[0014] Furthermore, the abnormal data identified by the monitoring model also includes a pod temperature higher than a preset pod high temperature threshold. If the pod temperature is higher than the preset pod high temperature threshold, it is determined that the corresponding defect type includes an engine component air leakage fault.
[0015] Furthermore, generating corresponding alarms and maintenance plans specifically includes: generating alarm prompts and maintenance plans according to the fault type, and pushing the maintenance plan to the maintenance site to inspect the area corresponding to the fault type.
[0016] The present invention also provides an aircraft engine thrust reverse insulation layer damage monitoring system, comprising:
[0017] A data acquisition module, used to determine monitoring parameters, obtain data and maintenance records of the monitoring parameters from the aircraft's historical flight database, and construct training data;
[0018] A model building module is used to clean the training data and extract effective data features; based on the big data analysis method, according to the actual working state of the aircraft engine bleed air system, identify and analyze the change trend of abnormal data, determine the relationship between abnormal data and corresponding defect types, and thus establish a monitoring model;
[0019] A real-time monitoring module, used to monitor the real-time data of engine operation through the monitoring model, identify abnormal data, and determine the corresponding defect type, and generate corresponding alarms and maintenance plans according to the determined fault type;
[0020] The result feedback module is used to optimize the monitoring model according to the actual operation results and feedback of the monitoring model.
[0021] Furthermore, the monitoring parameters include pod temperature, and the abnormal data identified by the monitoring model includes pod temperature being lower than a preset pod low temperature threshold. If the pod temperature is lower than the preset pod low temperature threshold, the corresponding defect type is determined to include damage to the reverse thrust fire insulation layer.
[0022] Furthermore, the nacelle temperature is monitored by a temperature sensor disposed in the exhaust annular gap of the aircraft.
[0023] Furthermore, the abnormal data identified by the monitoring model also includes a pod temperature higher than a preset pod high temperature threshold. If the pod temperature is higher than the preset pod high temperature threshold, it is determined that the corresponding defect type includes an engine component air leakage fault.
[0024] Furthermore, the alarm and maintenance plan generated by the real-time monitoring module are specifically as follows: an alarm prompt and a maintenance plan are generated according to the fault type, and the maintenance plan is pushed to the maintenance site to inspect the area corresponding to the fault type.
[0025] Compared with the prior art, the present invention has the following advantages:
[0026] (1) The present invention takes into account that damage to the thermal insulation blanket will lead to the collapse of the internal fixed structure IFS of the thrust reverser. If the collapsed IFS presses on the core casing, an abnormal EGT failure will occur. The drop in nacelle temperature is often accompanied by damage to the IFS, which causes the outer duct air to enter ZONE 3 and cause the temperature of this area to drop. Therefore, by constructing a monitoring model, the low nacelle temperature is monitored, the damage defects of the thrust reverser thermal insulation layer are identified, and the occurrence of unsafe incidents during aircraft flight is reduced.
[0027] (2) Currently, aircraft and engine manufacturers mainly monitor engine parameters at specific times through ACMS real-time messages. When the pod temperature exceeds the monitoring threshold, they notify the airline to implement troubleshooting. Such notifications are mainly for high pod temperatures, requiring inspection of fuel nozzle seals and other engine component leaks. However, monitoring of low pod temperatures has always been a gap in aircraft and engine manufacturers' monitoring. Such phenomena often cause damage to the reverse thrust fire insulation layer during operation, leading to unsafe incidents. This monitoring solution fills this technical gap.
[0028] (3) Due to strict release standards for insulation damage, high cost of replacing reverse thrust components, and long time to arrange aviation materials and tooling on the ground, sudden failures can easily cause flight impacts and economic losses. Through this monitoring solution, defects can be discovered in advance and maintenance opportunities can be reasonably arranged, greatly reducing economic losses.
[0029] (4) Currently, QAR data monitoring covers all flight data. This solution monitors the abnormally low temperature of the TRENT700 engine nacelle throughout the flight and compares the abnormal EGT temperature to monitor the damage of the reverse thrust insulation layer. It has been used on TRENT700 engine models and has achieved relatively good operating results. BRIEF DESCRIPTION OF THE DRAWINGS
[0030] Figure 1 A schematic flow chart of a method for monitoring damage of a reverse thrust insulation layer of an aircraft engine provided in an embodiment of the present invention;
[0031] Figure 2 A schematic diagram of the location of an engine nacelle temperature sensor provided in an embodiment of the present invention;
[0032] Figure 3 A schematic diagram of an engine fireproof and heat-insulating layer decomposition provided in an embodiment of the present invention;
[0033] Figure 4 It is a three-dimensional schematic diagram of an engine anti-fire insulation layer provided in an embodiment of the present invention. DETAILED DESCRIPTION
[0034] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.
[0035] 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 invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.
[0036] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.
[0037] Example 1
[0038] like Figure 1 As shown, this embodiment provides a method for monitoring damage of a reverse thrust insulation layer of an aircraft engine, comprising the following steps:
[0039] S1: Determine monitoring parameters, obtain monitoring parameter data and maintenance records from the aircraft's historical flight database, and construct training data;
[0040] S2: Clean the training data and extract effective data features; based on the big data analysis method and the actual working status of the aircraft engine bleed air system, identify and analyze the changing trend of abnormal data, determine the relationship between abnormal data and corresponding defect types, and thus establish a monitoring model;
[0041] S3: Monitor the real-time data of engine operation through the monitoring model, identify abnormal data, and determine the corresponding defect type, and generate corresponding alarms and maintenance plans according to the determined fault type;
[0042] S4: Optimize the monitoring model based on the actual operation results and feedback of the monitoring model.
[0043] Through long-term data monitoring and research, the present invention finds that the engine nacelle temperature can effectively detect such defects in advance. Through the development and application of this data, the losses caused to the company by unsafe incidents in fleet operations can be effectively avoided.
[0044] Specifically, after combing through historical data and maintenance records, when the TRENT700 engine EGT temperature indication is normal but the nacelle temperature is low, and the EGT temperature also changes abnormally, ground inspections generally reveal that the engine reverse thrust fire insulation layer is damaged. Figure 3 and 4 As shown in the figure. Damage to the thermal blanket will cause the collapse of the reverse thrust internal fixed structure IFS (Inner Fixed Structure). If the collapsed IFS presses the core casing, an abnormal EGT failure will occur. Figure 2 As shown in the figure, the temperature drop of the pod is often accompanied by the damage of IFS, which causes the outer duct air to enter ZONE 3 and cause the temperature of this area to drop. Using this feature, a monitoring scheme for the damage of the reverse thrust insulation layer of the TRENT700 engine is established.
[0045] Specifically, the monitoring parameters include the pod temperature, and the abnormal data identified by the monitoring model includes the pod temperature being lower than a preset pod low temperature threshold. If the pod temperature is lower than the preset pod low temperature threshold, the corresponding defect type is determined to include damage to the reverse thrust fire insulation layer.
[0046] The nacelle temperature can be monitored by a temperature sensor placed in the aircraft exhaust annular gap.
[0047] Preferably, the abnormal data identified by the monitoring model also includes a nacelle temperature higher than a preset nacelle high temperature threshold. If the nacelle temperature is higher than the preset nacelle high temperature threshold, it is determined that the corresponding defect type includes an engine component air leakage fault.
[0048] In step S3, generating corresponding alarms and maintenance plans specifically includes: generating alarm prompts and maintenance plans according to the fault type, and pushing the maintenance plan to the maintenance site to inspect the area corresponding to the fault type.
[0049] A specific example of the above scheme is provided below:
[0050] The program includes the following steps:
[0051] a. Collect relevant parameters (T20, P20, T25, T30, P30, NACELLE TEMP, P50, EGT, etc.), map and view the QAR parameter configuration information of each aircraft, and count the number of flights available in China Eastern Airlines' historical flight database. Based on the working principle of the engine and data relationship, merge maintenance records and conduct analysis.
[0052] b. Combine the flight data decoding platform to clean the engine-related parameters, extract and construct effective data features, and deeply understand the actual working status of the air bleed system under specific flight conditions based on big data analysis methods, analyze the changing trend of abnormal data, reflect the relevant defects from the perspective of data analysis, and establish a monitoring model;
[0053] c. The model monitors the real-time data of engine operation. When abnormal parameters occur, the model can automatically identify the defect type and push different types of alarms and related inspection procedures to the maintenance unit for corresponding technical intervention and correct the damage defects found in combination with the preset logic;
[0054] d. According to the defect feedback from the maintenance unit on site, the model is optimized to improve the model accuracy.
[0055] During the specific implementation, an A330 aircraft monitored that the temperature of the left engine pod was abnormally low. After the alarm was triggered, the plan was pushed to arrange the aircraft to the after-flight maintenance site for inspection. The maintenance unit inspected the relevant areas of the engine and found that the insulation blanket fragments had fallen, causing the insulation layer to be damaged beyond the standard. At that time, the crew of the aircraft did not report any faults, and there were no alarm prompts in the cockpit of the aircraft. While avoiding unsafe aircraft incidents, it also maximized the economic efficiency of the fleet operation, effectively controlled the relevant defects, and planned the handling of defects.
[0056] Example 2
[0057] This embodiment provides a system for monitoring damage of a reverse thrust insulation layer of an aircraft engine, comprising:
[0058] The data acquisition module is used to determine the monitoring parameters, obtain the data of the monitoring parameters and maintenance records from the aircraft's historical flight database, and construct training data;
[0059] The model building module is used to clean the training data and extract effective data features. Based on the big data analysis method, according to the actual working status of the aircraft engine bleed air system, it identifies and analyzes the changing trend of abnormal data, determines the relationship between abnormal data and corresponding defect types, and thus establishes a monitoring model.
[0060] The real-time monitoring module is used to monitor the real-time data of engine operation through the monitoring model, identify abnormal data, and determine the corresponding defect type, and generate corresponding alarms and maintenance plans according to the determined fault type;
[0061] The result feedback module is used to optimize the monitoring model according to the actual operation results and feedback of the monitoring model.
[0062] The monitoring parameters include the pod temperature. The abnormal data identified by the monitoring model include the pod temperature being lower than the preset pod low temperature threshold. If the pod temperature is lower than the preset pod low temperature threshold, the corresponding defect type is determined to include damage to the reverse thrust fire insulation layer. The pod temperature can be monitored by a temperature sensor set in the aircraft exhaust annular gap.
[0063] The abnormal data identified by the monitoring model also includes a pod temperature higher than a preset pod high temperature threshold. If the pod temperature is higher than the preset pod high temperature threshold, it is determined that the corresponding defect type includes an engine component air leakage failure.
[0064] The alarm and maintenance plan generated by the real-time monitoring module are specifically as follows: an alarm prompt and maintenance plan are generated according to the fault type, and the maintenance plan is pushed to the maintenance site for inspection of the area corresponding to the fault type.
[0065] It should be noted that the specific content and beneficial effects of the system of the present application can be found in the above-mentioned method embodiment, which will not be repeated here.
[0066] The preferred specific embodiments of the present invention are described in detail above. It should be understood that a person skilled in the art can make many modifications and changes based on the concept of the present invention without creative work. Therefore, any technical solution that can be obtained by a person skilled in the art through logical analysis, reasoning or limited experiments based on the concept of the present invention on the basis of the prior art should be within the scope of protection determined by the claims.
Claims
1. A method for monitoring damage of a reverse thrust insulation layer of an aircraft engine, characterized in that: The following steps are involved: Determine monitoring parameters, obtain data and maintenance records of the monitoring parameters from a historical flight database of the aircraft, and construct training data; Performing data cleaning on the training data to extract effective data features; Based on big data analysis methods, according to the actual working status of the aircraft engine bleed air system, the changing trend of abnormal data is identified and analyzed, and the relationship between abnormal data and corresponding defect types is determined, so as to establish a monitoring model; The monitoring model is used to monitor the real-time data of the engine operation, identify abnormal data, and determine the corresponding defect type, and generate corresponding alarms and maintenance plans according to the determined fault type; The monitoring model is optimized according to the actual operation results and feedback of the monitoring model.
2. A method for monitoring damage of a reverse thrust insulation layer of an aircraft engine according to claim 1, characterized in that: The monitoring parameters include pod temperature, and the abnormal data identified by the monitoring model includes pod temperature being lower than a preset pod low temperature threshold. If the pod temperature is lower than the preset pod low temperature threshold, it is determined that the corresponding defect type includes damage to the reverse thrust fire insulation layer.
3. A method for monitoring damage of reverse thrust insulation layer of an aircraft engine according to claim 2, characterized in that: The nacelle temperature is monitored by a temperature sensor disposed in the aircraft exhaust annular gap.
4. The method for monitoring damage of reverse thrust insulation layer of an aircraft engine according to claim 2, characterized in that: The abnormal data identified by the monitoring model also includes that the pod temperature is higher than a preset pod high temperature threshold. If the pod temperature is higher than the preset pod high temperature threshold, it is determined that the corresponding defect type includes an engine component air leakage fault.
5. The method for monitoring damage of reverse thrust insulation layer of an aircraft engine according to claim 1, characterized in that: Generating the corresponding alarm and maintenance plan specifically includes: generating an alarm prompt and a maintenance plan according to the fault type, and pushing the maintenance plan to the maintenance site to inspect the area corresponding to the fault type.
6. An aircraft engine thrust reverse insulation layer damage monitoring system, characterized in that: include: A data acquisition module, used to determine monitoring parameters, obtain data and maintenance records of the monitoring parameters from the aircraft's historical flight database, and construct training data; A model building module is used to clean the training data and extract effective data features; Based on big data analysis methods, according to the actual working status of the aircraft engine bleed air system, the changing trend of abnormal data is identified and analyzed, and the relationship between abnormal data and corresponding defect types is determined, so as to establish a monitoring model; A real-time monitoring module, used to monitor the real-time data of engine operation through the monitoring model, identify abnormal data, and determine the corresponding defect type, and generate corresponding alarms and maintenance plans according to the determined fault type; The result feedback module is used to optimize the monitoring model according to the actual operation results and feedback of the monitoring model.
7. The aircraft engine thrust reverser insulation layer damage monitoring system according to claim 6, characterized in that: The monitoring parameters include pod temperature, and the abnormal data identified by the monitoring model includes pod temperature being lower than a preset pod low temperature threshold. If the pod temperature is lower than the preset pod low temperature threshold, it is determined that the corresponding defect type includes damage to the reverse thrust fire insulation layer.
8. The aircraft engine thrust reverser insulation layer damage monitoring system according to claim 7, characterized in that: The nacelle temperature is monitored by a temperature sensor disposed in the aircraft exhaust annular gap.
9. The aircraft engine thrust reverser insulation layer damage monitoring system according to claim 7, characterized in that: The abnormal data identified by the monitoring model also includes that the pod temperature is higher than a preset pod high temperature threshold. If the pod temperature is higher than the preset pod high temperature threshold, it is determined that the corresponding defect type includes an engine component air leakage fault.
10. The aircraft engine thrust reverser insulation layer damage monitoring system according to claim 6, characterized in that: The alarm and maintenance plan generated by the real-time monitoring module are specifically: generating an alarm prompt and a maintenance plan according to the fault type, and pushing the maintenance plan to the maintenance site to check the area corresponding to the fault type.