Diagnostic method for temperature parameter abnormity of gas behind turbine of aero-engine control system

Abstract

The diagnosis method for the abnormal temperature parameters of the gas behind the turbine of the aero-engine control system comprises the steps that the state of an aero-engine is judged through the aero-engine control system; when the state of the aero-engine is in a steady state, collecting gas temperature data T of each redundancy behind a turbine of the aero-engine, and obtaining a threshold value of a turbulence degree difference value of the gas temperature of each redundancy behind the turbine; numerical value comparison is carried out, abnormal gas temperature data are filtered, and the total temperature of all redundancy gas temperatures behind the turbine is obtained; the turbulence degree of each redundancy fuel gas temperature behind the turbine and the average turbulence degree of each redundancy fuel gas temperature behind the turbine are calculated; calculating the difference value between the turbulence degree of each redundancy gas temperature and the average turbulence degree; and comparing the difference value with a threshold value, and if the difference value is greater than the threshold value, judging that the vehicle is abnormal. Through analysis processing of abnormal data and calculation and comparison of turbulence degree, temperature fluctuation caused by poor contact is identified and processed, the judgment basis is comprehensive, and the judgment result is reliable, timely and accurate.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine control, and in particular to a method for diagnosing abnormal temperature parameters of post-turbine combustion gas in an aero-engine control system. Background Art

[0002] The after-turbine gas temperature of an aircraft engine is one of the core parameters of an aircraft engine, which is related to engine performance, safety and maintenance, thermal stress protection of turbine components, combustion efficiency optimization and fuel economy, bleed air system diagnosis, structural integrity monitoring, automated fault diagnosis, and flight operation decision support. In the aircraft engine control system, the after-turbine gas temperature has a corresponding limit temperature. When the after-turbine temperature measurement is abnormal (too high), it will affect the fuel supply pattern of the control system, that is, reducing the fuel supply to lower the after-turbine gas temperature. Reducing the fuel supply will lead to lower engine speed and thrust. When the after-turbine gas temperature fluctuates abnormally, it will cause abnormalities such as engine speed fluctuations and thrust fluctuations. The controller of the engine control system generally uses broken wire detection for the after-turbine temperature measurement system, and there is no better detection method for temperature fluctuations caused by poor contact.

[0003] However, the existing method for judging abnormal engine temperature takes too few factors into consideration. It only judges by comparing the temperature of the gas after the turbine with the threshold, which still cannot solve the problem of abnormal temperature fluctuation caused by poor contact.

[0004] For example, patent document CN105781767A discloses a method and device for determining engine startup overtemperature. The method collects the engine's turbine exhaust gas temperature sequentially according to a set collection cycle throughout the engine startup process. The exhaust gas temperature is compared with threshold temperatures corresponding to at least two pre-set temperature status judgment zones. If the exhaust gas temperature exceeds the threshold temperature a certain number of times and the exhaust gas temperature exceeds the set engine startup overtemperature protection point, the engine is determined to have overheated during startup. However, temperature fluctuations caused by poor contact cannot be detected.

[0005] Therefore, it is necessary to design a technical solution that can determine the abnormal temperature of the after-turbine gas of an aircraft engine caused by temperature fluctuations caused by poor contact. Summary of the Invention

[0006] To address the technical problem that controllers in conventional aircraft engine control systems lack effective means for detecting temperature fluctuations caused by poor contact, the present application provides a method for diagnosing abnormal temperature parameters of turbine exhaust gas in aircraft engine control systems. The method is implemented based on the aircraft engine control system and includes the following: Determining the state of the aircraft engine through the aircraft engine control system; When the aircraft engine is in a steady state, collecting the fuel gas temperature data T of each margin after the aircraft engine turbine, and setting a threshold value of the turbulence degree difference of the fuel gas temperature of each margin after the turbine; According to the gas temperature data T of each degree of redundancy, numerical comparison is performed, abnormal gas temperature data is filtered, and the total temperature of each degree of redundancy gas temperature after the turbine is obtained. ; According to the total temperature of each redundant gas temperature after the turbine , calculate the turbulence degree of each redundant gas temperature after the turbine and the average turbulence of each redundant gas temperature after the turbine ; According to the turbulence and average turbulence , calculate the turbulence degree of each redundant gas temperature and average turbulence The difference ; The difference Compare with the threshold, if the difference If the value is greater than the threshold, it is judged as abnormal, and the controller will transmit an alarm signal to the aircraft engine control system.

[0007] Furthermore, the average turbulence The calculation formula is expressed as: , where m is the total number of redundancies; i is the i-th redundancy, i=1, 2, 3...m.

[0008] Furthermore, the turbulence The calculation formula is expressed as: in, is the average total temperature of the turbine after-gas temperature at the i-th margin position; n is the number of sampling points; j is the sampling of the j-th measuring point, j=1, 2, 3...n.

[0009] Furthermore, the calculation formula of the total temperature average total temperature at the turbine post-gas temperature margin position is expressed as: .

[0010] Furthermore, the abnormal gas temperature data refers to gas temperature data that is obviously lower in the numerical comparison and fluctuates.

[0011] Furthermore, the filtering of abnormal gas temperature data is to delete the values ​​that are obviously too low in the numerical comparison, and use the fluctuating gas temperature data for subsequent calculation and judgment.

[0012] Furthermore, when the abnormal gas temperature data is a value that is obviously lower in the numerical comparison, it indicates that the post-turbine gas temperature circuit corresponding to the margin has hit a wall.

[0013] Furthermore, when the abnormal gas temperature data is fluctuating gas temperature data, it indicates that there is poor contact in the post-turbine gas temperature circuit corresponding to the margin.

[0014] Furthermore, the threshold value can be adjusted according to different models of turbines.

[0015] The beneficial effects of the present invention are as follows: when the engine is in a steady state, data analysis and processing are performed on the collected temperature of the after-turbine gas of the aviation engine, and the processed data is judged. After it is determined to be abnormal data, the abnormal data is filtered, and the excess temperature data of the abnormal data caused by hitting the wall is deleted and not used. Instead, the abnormal data caused by poor contact is used for subsequent calculation and judgment, thereby solving the technical problem that temperature fluctuations caused by poor contact cannot be identified and processed; by calculating the difference between the turbulence degree of each excess gas temperature and the average turbulence degree, and comparing it with the threshold value obtained in advance, it is judged whether it is abnormal, taking into account comprehensive factors, and the judgment result is reliable, timely and accurate. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The present invention provides a flow chart of a method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system. DETAILED DESCRIPTION

[0017] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0018] An embodiment of the present invention provides a method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system. The method is implemented based on the aircraft engine control system and includes the following steps: The aircraft engine control system is used to determine the aircraft engine state; the aircraft engine state includes a shutdown state, a startup state, an idling state, an acceleration / deceleration state, a stable operating state, a maximum state, and a parking process, wherein the stable operating state is a steady state.

[0019] The aircraft engine control system sends the aircraft engine status parameters to the aircraft engine health management device, which determines the status of the aircraft engine based on the aircraft engine status parameters and feeds the result back to the aircraft engine control system.

[0020] When the aircraft engine is in a steady state, gas temperature data T of each degree of redundancy after the aircraft engine turbine is collected, and a threshold value of the turbulence difference of each degree of redundancy after the turbine is set; the number of sampling points of the gas temperature data T is n, and the number of redundancy is m.

[0021] The threshold value can be adjusted according to different models of turbines. For example, the threshold value can be set to 10%.

[0022] According to the gas temperature data T of each degree of redundancy, numerical comparison is performed, abnormal gas temperature data is filtered, and the total temperature of each degree of redundancy gas temperature after the turbine is obtained. ; The abnormal gas temperature data refers to gas temperature data that is obviously lower in the numerical comparison and fluctuates.

[0023] The filtering of abnormal gas temperature data is to delete the values ​​that are obviously too low in the numerical comparison, and retain the fluctuating gas temperature data for subsequent calculations.

[0024] When the abnormal gas temperature data is a value that is obviously lower than the value comparison, it indicates that the corresponding margin post-turbine gas temperature circuit has hit a wall. When the abnormal gas temperature data is fluctuating gas temperature data, it indicates that the post-turbine gas temperature circuit corresponding to the margin has poor contact.

[0025] Specifically: If abnormal gas temperature data appears, it means that the corresponding redundant turbine post-gas temperature circuit has poor contact or hits the wall, resulting in abnormal temperature data; when hits the wall, the abnormal gas temperature data is a value that is significantly lower than the value comparison; when poor contact exists, the abnormal gas temperature data is gas temperature data that fluctuates in the value comparison; When a collision occurs, the health management device will send a corresponding alarm message to the aircraft engine control system for subsequent maintenance and inspection; When there is poor contact, the data showing fluctuations are retained for subsequent calculation to determine whether there is an abnormality. If it is determined to be abnormal, an alarm signal is transmitted to the aircraft engine control system.

[0026] According to the total temperature of each redundant gas temperature after the turbine , calculate the turbulence degree of each redundant gas temperature after the turbine and the average turbulence of each redundant gas temperature after the turbine ; The average turbulence The calculation formula is expressed as: , where m is the total number of redundancies; i is the i-th redundancy, i=1, 2, 3...m.

[0027] The turbulence The calculation formula is expressed as: in, is the average total temperature of the turbine after-gas temperature at the i-th margin position; n is the number of sampling points; j is the sampling of the j-th measuring point, j=1, 2, 3...n.

[0028] The calculation formula of the total temperature average total temperature at the turbine post-gas temperature i margin position is expressed as: .

[0029] According to the turbulence and average turbulence , calculate the turbulence degree of each redundant gas temperature and average turbulence The difference ; The difference Compare with the threshold, if the difference If the value is greater than the threshold, it is judged as abnormal, and the controller will transmit an alarm signal to the aircraft engine control system.

[0030] The embodiment of the present invention performs data analysis and processing on the collected aero-engine turbine exhaust gas temperature when the engine is in a steady state, judges the processed data, and after determining that it is abnormal data, filters the abnormal data, deletes the excess temperature data of the abnormal data caused by hitting the wall, and does not use it. Instead, the abnormal data caused by poor contact is used for subsequent calculation and judgment, thereby solving the technical problem that temperature fluctuations caused by poor contact cannot be identified and processed; by calculating the difference between the turbulence degree of each excess gas temperature and the average turbulence degree, and comparing it with the threshold value obtained in advance, it is judged whether it is abnormal, considering all factors, and the judgment result is reliable, timely and accurate.

[0031] The above disclosures are only a few specific embodiments of the present invention. However, the present invention is not limited thereto. Any changes that can be conceived by those skilled in the art should fall within the scope of protection of the present invention.

Claims

1. A method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system, characterized in that: Based on the aircraft engine control system, the diagnostic method includes the following contents: Determining the state of the aircraft engine through the aircraft engine control system; When the aircraft engine is in a steady state, collecting the fuel gas temperature data T of each margin after the aircraft engine turbine, and setting a threshold value of the turbulence degree difference of the fuel gas temperature of each margin after the turbine; According to the gas temperature data T of each degree of redundancy, numerical comparison is performed, abnormal gas temperature data is filtered, and the total temperature of each degree of redundancy gas temperature after the turbine is obtained. ; According to the total temperature of each redundant gas temperature after the turbine , calculate the turbulence degree of each redundant gas temperature after the turbine and the average turbulence of each redundant gas temperature after the turbine ; According to the turbulence and average turbulence , calculate the turbulence degree of each redundant gas temperature and average turbulence The difference ; The difference Compare with the threshold, if the difference If the value is greater than the threshold, it is judged as abnormal and the controller will transmit an alarm signal to the aircraft engine control system.

2. The method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system according to claim 1, characterized in that: The average turbulence The calculation formula is expressed as: , where m is the total number of redundancies; i is the i-th redundancy, i=1, 2, 3...m.

3. The method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system according to claim 2, characterized in that: The turbulence The calculation formula is expressed as: in, is the average total temperature of the turbine after-gas temperature at the i-th margin position; n is the number of sampling points; j is the sampling of the j-th measuring point, j=1, 2, 3...n.

4. The method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system according to claim 3, characterized in that: The calculation formula of the total temperature average total temperature at the turbine post-gas temperature i margin position is expressed as: 。 5. The method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system according to claim 1, characterized in that: The abnormal gas temperature data refers to gas temperature data that is obviously lower in the numerical comparison and fluctuates.

6. The method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system according to claim 5, characterized in that: The filtering of abnormal gas temperature data is to delete the values ​​that are obviously too low in the numerical comparison, and use the fluctuating gas temperature data for subsequent calculation and judgment.

7. The method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system according to claim 5, characterized in that: When the abnormal gas temperature data is a value that is obviously lower in the numerical comparison, it indicates that a corresponding margin post-turbine gas temperature circuit has hit a wall.

8. The method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system according to claim 5, characterized in that: When the abnormal gas temperature data is fluctuating gas temperature data, it indicates that the post-turbine gas temperature circuit corresponding to the margin has poor contact.

9. The method for diagnosing abnormal temperature parameters of turbine exhaust gas in an aircraft engine control system according to claim 1, characterized in that: The threshold value can be adjusted according to different models of turbines.

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