CN118333603A - Method, device, equipment and medium for monitoring EGT state of aircraft engine - Google Patents
Method, device, equipment and medium for monitoring EGT state of aircraft engine Download PDFInfo
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Abstract
The invention discloses a method, a device, equipment and a medium for monitoring the EGT state of an aircraft engine, which comprise the following steps: acquiring QAR data and decoding to obtain key parameters of an aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed; calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period; and triggering early warning to send a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions. The embodiment of the invention is beneficial to the predictive maintenance of the aircraft engine, prevents the occurrence of functional faults and avoids delay or air parking events.
Description
Technical Field
The invention relates to the field of aeroengine running state data analysis, in particular to an aircraft engine EGT state monitoring method, device, equipment and medium.
Background
EGT (Exhaust Gas Temperature ) is an important monitored parameter of the engine, which refers to the temperature of the gas after the low pressure turbine, reflecting changes in engine performance. When an EGT abnormally fluctuates, it is generally represented that the engine is in an abnormal state.
The existing monitoring of EGT is mainly based on trend type monitoring of engine EGTM (Exhaust Gas Temperature Margin, exhaust temperature margin), namely, a manufacturer calculates engine EGTM according to a message of an aircraft fixing stage, thereby establishing EGTM monitoring based on flights, and setting up maintenance work of the engine by observing whether a EGTM curve or point set has a descending trend or not. However, the monitoring can only take flights as a benchmark, and the analysis and the early warning of the EGT indication in the air section cannot be established, and the monitoring of the whole air section EGT, whether based on the instantaneous change monitoring of single EGT or the double difference monitoring, still has certain limitation. Meanwhile, the engine manufacturer does not disclose EGTM specific calculation methods, and the airline company must rely on monitoring software provided by the manufacturer to obtain EGTM.
Disclosure of Invention
The invention provides a method, a device, equipment and a medium for monitoring the EGT state of an aircraft engine, which are beneficial to the predictive maintenance of the aircraft engine, prevent functional faults and avoid delay or air parking events.
In order to achieve the above object, an embodiment of the present invention provides a method for monitoring an EGT state of an aircraft engine, including:
Acquiring QAR data and decoding to obtain key parameters of an aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed;
Calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period;
and triggering early warning to send a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions.
As an improvement of the above solution, the calculating the fluctuation value of the aircraft engine according to the parameter and the preset jitter period includes:
performing difference processing on the left exhaust temperature and the right exhaust temperature to obtain a first difference value;
and in each jitter period, carrying out root mean square error calculation on the first difference value to obtain a fluctuation value of the aircraft engine.
As an improvement of the above solution, the calculating the rate of change of the rotational speed of the aircraft engine according to the parameter and a preset shake period includes:
performing difference processing on the rotating speed of the left engine core and the rotating speed of the right engine core to obtain a second difference value;
and in each shaking period, carrying out root mean square error calculation on the second difference value to obtain the rotating speed change rate of the aircraft engine.
As an improvement of the above solution, the calculating the temperature difference value of the aircraft engine according to the parameter and the preset jitter period includes:
And in each shaking period, performing difference processing on maximum and minimum values of the left air emission temperature and the right air emission temperature to obtain a temperature difference value of the aircraft engine.
As a modification of the above, the jitter period is set to 10 seconds.
As an improvement of the above-described aspect, the abnormal shake condition includes the core engine rotational speed change rate being less than 0.1, the fluctuation value being 8 or more, and the temperature difference value being 20 or more.
As an improvement of the scheme, the content of the message comprises the shaking moment, the shaking duration and the shaking amplitude of abnormal shaking of the aircraft engine in the navigation section.
In order to achieve the above object, an embodiment of the present invention further provides an apparatus for monitoring an EGT state of an aircraft engine, including:
the data acquisition module is used for acquiring QAR data and decoding to obtain key parameters of the aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed;
The data calculation module is used for calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period;
And the abnormality alarm module is used for triggering early warning and sending a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions.
To achieve the above object, an embodiment of the present invention further provides an aircraft engine EGT status monitoring apparatus, including a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, the processor implementing the above aircraft engine EGT status monitoring method when executing the computer program.
To achieve the above object, embodiments of the present invention also provide a computer-readable storage medium including a stored computer program; the computer program controls the equipment where the computer readable storage medium is located to execute the aircraft engine EGT state monitoring method when running.
To achieve the above object, embodiments of the present invention also provide a computer program product comprising a computer program; the computer program controls equipment where the program product is located to execute the aircraft engine EGT state monitoring method when running.
The embodiment of the invention has the following beneficial effects:
The method, the device, the equipment and the storage medium for monitoring the EGT state of the aircraft engine provided by the embodiment of the invention acquire QAR data and decode the QAR data to obtain key parameters of the aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed; calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period; and triggering early warning to send a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions. The embodiment of the invention is beneficial to the predictive maintenance of the aircraft engine, prevents the occurrence of functional faults and avoids delay or air parking events.
Drawings
FIG. 1 is a flow chart of an aircraft engine EGT condition monitoring method provided by an embodiment of the invention;
FIG. 2 is a schematic diagram of a fluctuation value calculation process provided by an embodiment of the present invention;
FIG. 3 is a schematic diagram of screening for meeting abnormal jitter conditions according to an embodiment of the present invention;
FIG. 4 is a partial enlarged view of screening for meeting abnormal jitter conditions according to an embodiment of the present invention;
FIG. 5 is a block diagram of an aircraft engine EGT condition monitoring device provided by an embodiment of the present invention;
fig. 6 is a block diagram of an aircraft engine EGT condition monitoring apparatus according to an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that step numbers are used herein only for convenience of explanation of specific embodiments, and are not used as a limitation of the execution sequence of steps.
Referring to fig. 1, fig. 1 is a flowchart of an aircraft engine EGT state monitoring method according to an embodiment of the present invention, where the aircraft engine EGT state monitoring method includes steps S1 to S3, and specifically includes the following steps:
S1, acquiring QAR data and decoding to obtain key parameters of an aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed;
s2, calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period;
And S3, triggering early warning and sending a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions.
It can be understood that the key parameters of the aircraft engine include, besides the FLIGHT segment flightphase, the left engine exhaust temperature EGT1, the right engine exhaust temperature EGT2, the left engine core rotation speed N21, the right engine core rotation speed N22, a left engine fuel flow FF1 and a right engine fuel flow FF2 for assisting in determining a short-term stable operating state of the engine core.
In the embodiment of the invention, through processing QAR (Quick Access Recorder, quick storage recorder) data, under the condition that the rotation speed of the engine core machine is stable, double-emission EGT data are analyzed, after reaching the warning standard, a pre-alarm message is triggered to send out a foreseeing maintenance requirement, the characteristics of small-range abnormal shake, abrupt change and the like of an EGT indicating system can be captured, ground engineering personnel can better know the condition of the EGT indicating system, the foreseeing maintenance of the aircraft engine is facilitated, the occurrence of functional faults is prevented, and delay or air parking events are avoided.
In an alternative embodiment, the calculating the fluctuation value of the aircraft engine according to the parameter and the preset jitter period includes:
performing difference processing on the left exhaust temperature and the right exhaust temperature to obtain a first difference value;
and in each jitter period, carrying out root mean square error calculation on the first difference value to obtain a fluctuation value of the aircraft engine.
In the embodiment of the invention, the difference between the left hair-emission temperature and the right hair-emission temperature is processed, so that the difference influence on the double hair performance of the aircraft can be eliminated; the RMSE (Root Mean Square Error ) of the difference in each period of dithering is then calculated to reflect the change in exhaust temperature over a short period of time, which is helpful in assessing the stability and performance of the engine when running.
Exemplary, as shown in fig. 2, fig. 2 is a schematic diagram of a fluctuation value calculation process, where EGT1 is a left exhaust temperature, EGT2 is a right exhaust temperature, EGT1-2 is a first difference between the left exhaust temperature and the right exhaust temperature, and 8000s is a total duration; wherein the calculation formula of the fluctuation value sigma is as follows:
Where x i denotes the i-th EGT difference, N denotes the number of 1HZ data recorded in the jitter period t=10s, and μ denotes the average value of the EGT differences in the jitter period.
In an alternative embodiment, the calculating the rate of change of the rotational speed of the aircraft engine according to the parameter and the preset dithering cycle includes:
performing difference processing on the rotating speed of the left engine core and the rotating speed of the right engine core to obtain a second difference value;
and in each shaking period, carrying out root mean square error calculation on the second difference value to obtain the rotating speed change rate of the aircraft engine.
In an alternative embodiment, the calculating the temperature difference value of the aircraft engine according to the parameter and the preset dithering cycle includes:
And in each shaking period, performing difference processing on maximum and minimum values of the left air emission temperature and the right air emission temperature to obtain a temperature difference value of the aircraft engine.
In the embodiment of the invention, the difference between the maximum value and the minimum value of the engine exhaust temperature in the specific shaking period screened by the algorithm is recorded, so that the inching of the EGT in the slow vehicle caused by the fluctuation of the bleed air pressure can be eliminated.
The temperature difference value is calculated by the following formula:
T_w＝EGTmax-EGTmin
Where t_w represents a temperature difference, EGT max and EGT min are maximum and minimum values of left and right exhaust temperatures, respectively, in each of the shaking periods.
In an alternative embodiment, the jitter period is set to 10 seconds.
It will be appreciated that the jitter period t=10 seconds is a major parameter of the jitter data characteristics that is summarized by analyzing historical faults and leading flight jitter moments.
In an alternative embodiment, the abnormal vibration condition includes the core rotational speed change rate being less than 0.1, the fluctuation value being 8 or more, and the temperature difference value being 20 or more.
It can be understood that by performing root mean square error calculation on the difference between the left air outlet temperature and the right air outlet temperature of the past failed flight, and analyzing the fluctuation value, i.e. the sigma value, which can distinguish the normal EGT change from the abnormal jitter, the accuracy of more than 97% can be ensured when the sigma value is selected as 8.
In the embodiment of the invention, the automatic identification and monitoring of the aircraft engine in the running or ground double-test and sliding process can be realized by setting the autonomous monitoring logic of the abnormality of the engine EGT indicating system. When the related logic is triggered (i.e. the abnormal jitter condition is met), a pre-alarm message can be sent through a mail to inform and assist an engineer in judging the fault state, so as to make a foreseeing maintenance requirement and avoid generating an abnormal event.
As shown in fig. 3 and 4, the abscissa represents the fluctuation value σ, the ordinate represents the rate of change of the core rotation speed N2, and fig. 3 differs from fig. 4 in terms of the range, and fig. 4 is an enlargement of the bottom of fig. 3. The dot does not meet the abnormal shaking condition, the fork number meets the condition that the change rate of the rotating speed of the core machine in the abnormal shaking strip is smaller than 0.1 and the fluctuation value is larger than or equal to 8.
In an alternative embodiment, the content of the message includes a shake moment, a shake duration and a shake amplitude of the aircraft engine when abnormal shake occurs in the leg.
It can be understood that the jitter time is time information of occurrence of abnormal EGT abnormal jitter; the dithering time length is the duration time length meeting the abnormal dithering condition; the jitter amplitude is the temperature difference over the duration of the jitter occurrence.
In the embodiment of the invention, engineering personnel can identify and evaluate the EGT abnormal jitter state according to the acquired message data and send out the foreseeing maintenance instruction, thereby realizing accurate maintenance, reducing the faults of an engine EGT indicating system and ensuring the safety of an airplane and the correct flight.
By way of example, a type of engine is taken as an aerial passenger A320 series aircraft. The engine EGT indicates that the system temperature sensor monitors the exhaust gas temperature signal, which is embodied in the decoded data as a 1Hz digital signal. When the FADEC (Full Authority DIGITAL ENGINE Control) is powered up, the sensor begins recording engine EGT parameters and stores them into a fast storage recorder, i.e., QAR, via EIU (ENGINE INTERFACE Unit, engine interface component) and FDIMU (FLIGHT DATA INTERFACE MANAGEMENT Unit, flight data interface and management component). After the aircraft lands the engine and shuts down, the data stored in QAR parameter data are transmitted to a ground server for data decoding, then the data are transmitted to a data analysis platform for data preprocessing and model analysis, when an alarm threshold value of an event logic is triggered (namely, abnormal jitter conditions are met), the data are issued by a monitoring platform, data mail and relevant engineering parameters are transmitted to corresponding user terminals, and after the user terminals receive the message mail, the analysis message makes corresponding measures.
The format sample of the message mail may be as follows:
"test mail: abnormal jittering of the XXXX engine EGT is detected by the method B-1800,1. The fleet engine engineers are asked to check.
Number of machine: B-180U
The base: hunan province
Model: a320
An engine: XXXX
Flight number: CZ5113
Starting: 2023/05/19 09:52:39
Ending: 2023/05/19 12:31:51
Early warning information:
1. Engine EGT1 dithers and dithers recording
Time [1282,1329,1414,1654]
Duration [10,8,6,40]
Jitter amplitude [30.0,32.0,78.0,98.0]
2. Transmitting QAR decoded csv file, parameters including
·EGT1\2
·FF1\2
·N21\22
·FLIGHT_PHASE
3. Accessories: QAR.CSV file for detecting flights
4. Treatment advice:
(1) Non-test run data;
(2) The model judges the CFM56-5B engine EGT indication fluctuation presented by QAR data through real-time monitoring, and assists in judging system faults;
(3) The main monitoring parameter of the model is EGT; threshold a=8;
(4) The model is classified into a real-time class H-2 class, and if decoding confirms that the fault phenomenon needs post-voyage troubleshooting;
(5) Decoding is needed, and in combination with FF changes, whether the EGT indicates a system failure is judged according to examples in the troubleshooting advice. If the FF has no obvious difference at the moment of the jitter of the EGT, the EGT can be judged to indicate the system fault;
(6) The number of single-shot shake of the flight is more than or equal to 2 times or the shake amplitude exceeds 20 ℃, namely the length of the detection time sequence is more than or equal to 2 or the maximum value of the shake amplitude sequence is more than 20;
(7) Based on the qar.csv file in the mail attachment, a comparison is made with the following typical fault interpretation map (remark) to determine whether the real EGT indicates a fault. If the treatment is properly performed according to the troubleshooting advice. "
According to the aircraft engine EGT state monitoring method provided by the embodiment of the invention, QAR data are firstly obtained and decoded to obtain key parameters of an aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed; calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period; and triggering early warning to send a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions. The embodiment of the invention is beneficial to the predictive maintenance of the aircraft engine, prevents the occurrence of functional faults and avoids delay or air parking events.
Referring to fig. 5, fig. 5 is a block diagram of an aircraft engine EGT status monitoring apparatus 10 according to an embodiment of the present invention, where the aircraft engine EGT status monitoring apparatus 10 includes:
The data acquisition module 11 is used for acquiring QAR data and decoding to obtain key parameters of the aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed;
A data calculation module 12, configured to calculate a fluctuation value, a rotation speed change rate, and a temperature difference value of the aircraft engine according to the parameter and a preset shake period;
and the abnormality alarm module 13 is used for triggering early warning and sending a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions.
Optionally, the calculating the fluctuation value of the aircraft engine according to the parameter and the preset jitter period includes:
performing difference processing on the left exhaust temperature and the right exhaust temperature to obtain a first difference value;
and in each jitter period, carrying out root mean square error calculation on the first difference value to obtain a fluctuation value of the aircraft engine.
Optionally, the calculating the speed change rate of the aircraft engine according to the parameter and the preset jitter period includes:
performing difference processing on the rotating speed of the left engine core and the rotating speed of the right engine core to obtain a second difference value;
and in each shaking period, carrying out root mean square error calculation on the second difference value to obtain the rotating speed change rate of the aircraft engine.
Optionally, the calculating the temperature difference value of the aircraft engine according to the parameter and the preset jitter period includes:
And in each shaking period, performing difference processing on maximum and minimum values of the left air emission temperature and the right air emission temperature to obtain a temperature difference value of the aircraft engine.
Optionally, the jitter period is set to 10 seconds.
Optionally, the abnormal jitter condition includes the speed change rate of the core engine being less than 0.1, the fluctuation value being greater than or equal to 8, and the temperature difference value being greater than or equal to 20.
Optionally, the content of the message includes a shaking moment, a shaking duration and a shaking amplitude of abnormal shaking of the aircraft engine at the leg.
It should be noted that, the working process of each module in the aircraft engine EGT state monitoring device 10 according to the embodiment of the present invention may refer to the working process of the aircraft engine EGT state monitoring method according to the above embodiment, and will not be described herein.
The aircraft engine EGT state monitoring device provided by the embodiment of the invention firstly acquires QAR data and decodes the QAR data to obtain key parameters of an aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed; calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period; and triggering early warning to send a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions. The embodiment of the invention is beneficial to the predictive maintenance of the aircraft engine, prevents the occurrence of functional faults and avoids delay or air parking events.
Furthermore, the embodiment of the invention also provides a computer readable storage medium, which comprises a stored computer program; the computer program controls the equipment where the computer readable storage medium is located to execute the aircraft engine EGT state monitoring method when running.
Embodiments of the present invention also provide a computer program product comprising a computer program; the computer program controls equipment where the computer program product is located to execute the aircraft engine EGT state monitoring method when running.
Referring to fig. 6, fig. 6 is a block diagram of an aircraft engine EGT status monitoring apparatus 20 according to an embodiment of the present invention, where the aircraft engine EGT status monitoring apparatus 20 includes: a processor 21, a memory 22 and a computer program stored in said memory 22 and executable on said processor 21. The processor 21, when executing the computer program, implements the steps of the above-described embodiment of the aircraft engine EGT condition monitoring method. Or the processor 21, when executing the computer program, performs the functions of the modules/units in the above-described device embodiments.
Illustratively, the computer program may be partitioned into one or more modules/units that are stored in the memory 22 and executed by the processor 21 to complete the present invention. The one or more modules/units may be a series of computer program instruction segments capable of performing specific functions for describing the execution of the computer program in the aircraft engine EGT condition monitoring apparatus 20.
The aircraft engine EGT condition monitoring device 20 may include, but is not limited to, a processor 21, a memory 22. It will be appreciated by those skilled in the art that the schematic illustration is merely an example of the aircraft engine EGT condition monitoring apparatus 20 and is not limiting of the aircraft engine EGT condition monitoring apparatus 20, and may include more or fewer components than illustrated, or may combine certain components, or different components, e.g., the aircraft engine EGT condition monitoring apparatus 20 may also include input and output devices, network access devices, buses, etc.
The Processor 21 may be a central processing unit (Central Processing Unit, CPU), but may also be other general purpose processors, digital signal processors (DIGITAL SIGNAL Processor, DSP), application SPECIFIC INTEGRATED Circuit (ASIC), field-Programmable gate array (Field-Programmable GATE ARRAY, FPGA) or other Programmable logic device, discrete gate or transistor logic device, discrete hardware components, or the like. The general purpose processor may be a microprocessor or the processor may be any conventional processor or the like, and the processor 21 is the control center of the aircraft engine EGT condition monitoring apparatus 20 and connects the various parts of the entire aircraft engine EGT condition monitoring apparatus 20 using various interfaces and lines.
The memory 22 may be used to store the computer programs and/or modules, and the processor 21 may implement the various functions of the aircraft engine EGT condition monitoring apparatus 20 by executing or executing the computer programs and/or modules stored in the memory 22 and invoking data stored in the memory 22. The memory 22 may mainly include a storage program area and a storage data area, wherein the storage program area may store an operating system, an application program (such as a sound playing function, an image playing function, etc.) required for at least one function, and the like; the storage data area may store data (such as audio data, phonebook, etc.) created according to the use of the handset, etc. In addition, the memory 22 may include high-speed random access memory, and may also include non-volatile memory, such as a hard disk, memory, plug-in hard disk, smart memory card (SMART MEDIA CARD, SMC), secure Digital (SD) card, flash memory card (FLASH CARD), at least one magnetic disk storage device, flash memory device, or other volatile solid-state storage device.
Wherein the integrated modules/units of the aircraft engine EGT condition monitoring device 20, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the present invention may implement all or part of the flow of the method of the above embodiment, or may be implemented by a computer program to instruct related hardware, where the computer program may be stored in a computer readable storage medium, and the computer program may implement the steps of each of the method embodiments described above when executed by the processor 21. Wherein the computer program comprises computer program code which may be in source code form, object code form, executable file or some intermediate form etc. The computer readable medium may include: any entity or device capable of carrying the computer program code, a recording medium, a U disk, a removable hard disk, a magnetic disk, an optical disk, a computer Memory, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), an electrical carrier signal, a telecommunications signal, a software distribution medium, and so forth.
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that changes and modifications may be made without departing from the principles of the invention, such changes and modifications are also intended to be within the scope of the invention.
Claims (10)
1. A method for monitoring the EGT status of an aircraft engine, comprising:
Acquiring QAR data and decoding to obtain key parameters of an aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed;
Calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period;
and triggering early warning to send a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions.
2. The aircraft engine EGT condition monitoring method of claim 1, wherein said calculating the aircraft engine surge value based on the parameter and a preset dithering cycle comprises:
performing difference processing on the left exhaust temperature and the right exhaust temperature to obtain a first difference value;
and in each jitter period, carrying out root mean square error calculation on the first difference value to obtain a fluctuation value of the aircraft engine.
3. The aircraft engine EGT condition monitoring method of claim 1, wherein said calculating a rate of change of rotational speed of said aircraft engine based on said parameter and a preset dithering cycle comprises:
performing difference processing on the rotating speed of the left engine core and the rotating speed of the right engine core to obtain a second difference value;
and in each shaking period, carrying out root mean square error calculation on the second difference value to obtain the rotating speed change rate of the aircraft engine.
4. The aircraft engine EGT condition monitoring method of claim 1, wherein said calculating a temperature difference value of said aircraft engine based on said parameter and a preset dithering cycle comprises:
And in each shaking period, performing difference processing on maximum and minimum values of the left air emission temperature and the right air emission temperature to obtain a temperature difference value of the aircraft engine.
5. The aircraft engine EGT condition monitoring method of claim 1, wherein the dithering period is set to 10 seconds.
6. The aircraft engine EGT condition monitoring method of claim 1, wherein the abnormal jitter condition includes the core engine speed change rate being less than 0.1, the surge value being 8 or more, and the temperature difference value being 20 or more.
7. The aircraft engine EGT status monitoring method of claim 1, wherein the content of the message includes a jitter time, a jitter duration, and a jitter amplitude of the aircraft engine when abnormal jitter occurs in the leg.
8. An aircraft engine EGT condition monitoring apparatus comprising:
the data acquisition module is used for acquiring QAR data and decoding to obtain key parameters of the aircraft engine; the key parameters comprise a navigation section, left engine exhaust temperature, right engine exhaust temperature, left engine core machine rotating speed and right engine core machine rotating speed;
The data calculation module is used for calculating the fluctuation value, the rotating speed change rate and the temperature difference value of the aircraft engine according to the parameters and the preset shaking period;
And the abnormality alarm module is used for triggering early warning and sending a message when the fluctuation value, the rotating speed change rate and the temperature difference value meet abnormal jitter conditions.
9. An aircraft engine EGT condition monitoring apparatus comprising a processor, a memory and a computer program stored in the memory and configured to be executed by the processor, the processor implementing the aircraft engine EGT condition monitoring method as claimed in any one of claims 1 to 7 when the computer program is executed.
10. A computer readable storage medium, wherein the computer readable storage medium comprises a stored computer program; wherein the computer program, when run, controls a device in which the computer readable storage medium is located to perform the aircraft engine EGT condition monitoring method according to any one of claims 1 to 7.
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| CN202410405683.2A CN118333603A (en) | 2024-04-07 | 2024-04-07 | Method, device, equipment and medium for monitoring EGT state of aircraft engine |
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| CN202410405683.2A CN118333603A (en) | 2024-04-07 | 2024-04-07 | Method, device, equipment and medium for monitoring EGT state of aircraft engine |
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2024
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