Aero-engine surge early warning method and device, electronic equipment and storage medium

Abstract

The invention discloses an aero-engine surge early warning method and device, electronic equipment and a storage medium. The method comprises the steps that a dynamic pressure signal of an aero-engine is obtained in real time; performing correlation analysis on the dynamic pressure signals obtained in real time to obtain correlation coefficients; continuously calculating the mean value mu of the correlation coefficients of the aero-engine rotor rotating for X circles and the standard deviation sigma of the correlation coefficients of the aero-engine rotor rotating for one circle; continuously calculating a dimensionless offset U according to the mean value mu and the standard deviation sigma to obtain a dimensionless offset U sequence; performing logic counting on the dimensionless offset U sequence according to a set counting condition; and when the logic count value calculated in real time meets a uniformly set threshold condition, a surge alarm signal is sent out. According to the method, an early warning signal can be sent out before surge occurs, and safe operation of the aero-engine is guaranteed; meanwhile, a unified logic count value threshold value can be set as a surge alarm threshold value of different engines and different rotating speeds, and the unified threshold value is achieved.

Description

Technical Field

[0001] This application relates to the field of aero-engine technology, and in particular to an aero-engine surge warning method, device, electronic equipment, and storage medium. Background Technology

[0002] Surge (a phenomenon similar to the "water hammer effect" in metal water pipes, which can easily cause engine failure) is a matter of engine safety, and airworthiness regulations explicitly prohibit excessive damage caused by compressor surge. Active surge control technology is a technology that can improve engine safety and compressor efficiency, and it is one of the core technologies of future intelligent engines.

[0003] Active surge control technology is an active control that takes place before surge occurs. Active control can issue early warning signals before aero-engine surge, ensuring that the control system intervenes in advance to prevent surge from occurring or reduce the harm of surge even if it occurs, thus ensuring the safe operation of aero-engines. However, the determination of the relevant judgment thresholds for existing active control varies depending on the engine speed or engine type, making it impossible to provide a uniform threshold. Therefore, it lacks universality and has poor adaptability. Summary of the Invention

[0004] This application provides a method for early warning of surge in aero-engines, which addresses the technical problem that existing aero-engine surge warning technologies cannot provide a uniform threshold for active surge control, lacking universality and adaptability.

[0005] This application is achieved through the following solution:

[0006] A method for early warning of surge in aircraft engines includes the following steps:

[0007] Real-time acquisition of dynamic pressure signals from aero engines;

[0008] Correlation analysis was performed on the real-time acquired dynamic pressure signals to obtain the correlation coefficient;

[0009] The mean μ of the correlation coefficient for the aero-engine rotor after X revolutions and the standard deviation σ of the correlation coefficient for the aero-engine rotor after 1 revolution are continuously calculated.

[0010] The dimensionless offset U sequence is obtained by continuously calculating the dimensionless offset U based on the mean μ and standard deviation σ;

[0011] The dimensionless offset U sequence is logically counted according to the set counting conditions;

[0012] When the real-time calculated logic count value meets the uniformly set threshold condition, a surge alarm signal is issued.

[0013] Furthermore, the calculation process for the correlation coefficient is as follows:

[0014]

[0015] Where t represents the sampling time, x i It is the dynamic pressure signal value measured during the first revolution of the compressor, y i It is the dynamic pressure signal value measured during the current revolution of the compressor. This is the average value of the dynamic pressure signal during the first revolution of the compressor. This is the average value of the dynamic pressure signal during the current revolution of the compressor.

[0016] Furthermore, the mean μ of the correlation coefficient for the aero-engine rotor after X revolutions is specifically as follows:

[0017]

[0018] The standard deviation σ of the correlation coefficient for one revolution of the aero-engine rotor is as follows:

[0019]

[0020] Where X≥100, N represents the number of dynamic pressure signal points collected when the aero-engine rotor rotates 1 revolution, and the sampling time interval Δt is calculated based on the sampling rate of the dynamic pressure sensor. Then the sequence of sampling time t is: 0, 1Δt, 2Δt, ..., (N-1)Δt.

[0021] Furthermore, the dimensionless offset U is continuously calculated based on the mean μ and standard deviation σ to obtain the dimensionless offset U sequence as follows:

[0022]

[0023] SFM is a preset constant used to prevent the denominator of the formula for calculating the dimensionless offset U from being zero.

[0024] Furthermore, the logical counting of the dimensionless offset U sequence according to the set counting conditions specifically includes the following steps:

[0025] When the dimensionless offset U at the current moment in the dimensionless offset U sequence is greater than the set value U0 and the dimensionless offset U at the current moment is greater than the dimensionless offset U at the previous moment and continues to increase, the counter is incremented by 1; otherwise, the counter is cleared to 0.

[0026] Furthermore, when the real-time calculated logic count value meets a uniformly set threshold condition, issuing a surge alarm signal specifically includes the following steps:

[0027] Set the logic count threshold Z0 as the surge alarm threshold;

[0028] When the real-time calculated logic count value is greater than Z0, and exceeds Z0 M times within the set time t0, a surge alarm signal is issued, M≥3.

[0029] Furthermore, when the real-time calculated logic count value meets a uniformly set threshold condition, issuing a surge alarm signal specifically includes the following steps:

[0030] Determine whether to stop the alarm. If the alarm stops, enter the surge alarm standby state.

[0031] This application also provides an aircraft engine surge warning device, characterized in that it includes:

[0032] The signal acquisition module is used to acquire the dynamic pressure signal of the aero-engine in real time.

[0033] The correlation analysis module is used to perform correlation analysis on the real-time acquired dynamic pressure signals and obtain the correlation coefficient.

[0034] The mean and standard deviation calculation module is used to continuously calculate the mean μ of the correlation coefficient of the aero-engine rotor after X revolutions and the standard deviation σ of the correlation coefficient of the aero-engine rotor after 1 revolution.

[0035] The dimensionless offset calculation module is used to continuously calculate the dimensionless offset U based on the mean μ and standard deviation σ to obtain the dimensionless offset U sequence;

[0036] The logic counting module is used to perform logical counting on the dimensionless offset U sequence according to the set counting conditions.

[0037] The early warning module is used to issue a surge warning signal when the real-time calculated logical count value meets the uniformly set threshold conditions.

[0038] This application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and running on the processor, wherein the processor executes the computer program to implement the steps of the aircraft engine surge warning method.

[0039] This application also provides a storage medium including a stored program that, when the program is executed, controls the device where the storage medium is located to perform the steps of the aircraft engine surge warning method.

[0040] Compared with the prior art, this application has the following advantages:

[0041] The surge warning method for aero-engines provided in this application has better universality than existing correlation coefficient threshold setting methods. Traditional correlation coefficient thresholds vary depending on the engine speed or engine, making it impossible to provide a uniform threshold. However, this application uses logical counting based on the trend change of dimensionless offset, and the counter only increases when the trend continues to deteriorate. Therefore, the threshold setting is universal. Based on the analysis of a large amount of surge test data, it can be seen that this application can set the same logical count value threshold as the surge alarm threshold for different engines and different engine speeds, achieving a uniform threshold and possessing universality and strong adaptability.

[0042] In addition to the purposes, features, and advantages described above, this application has other purposes, features, and advantages. A further detailed description of this application will be provided below with reference to the figures. Attached Figure Description

[0043] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0044] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort, wherein:

[0045] Figure 1 This is a schematic flowchart of a preferred embodiment of the aircraft engine surge early warning method of this application;

[0046] Figure 2 This is a schematic diagram of the verification results of the surge warning method for aero-engines proposed in this application, which is a test of a high-load combined compressor component.

[0047] Figure 3 This is a schematic diagram showing the verification results of the surge warning method for a certain aero-engine under a complete engine test (time 0 is the time when surge occurs);

[0048] Figure 4 This is a schematic diagram of the aircraft engine surge warning device module according to a preferred embodiment of this application;

[0049] Figure 5 This is a schematic block diagram of an electronic device according to a preferred embodiment of this application;

[0050] Figure 6 This is an internal structural diagram of a computer device according to a preferred embodiment of this application. Detailed Implementation

[0051] It should be understood that the specific embodiments described herein are merely illustrative of the technical solutions of this application and are not intended to limit this application.

[0052] To better understand the technical solution of this application, a detailed description will be provided below in conjunction with the accompanying drawings and specific implementation methods.

[0053] It should be noted that the executing entity in this embodiment can be a computing service device with data processing, network communication, and program execution functions, such as a tablet computer, personal computer, or mobile phone, or an aircraft engine surge warning device capable of performing the above functions. The following description uses an aircraft engine surge warning device as the executing entity to illustrate this embodiment and the subsequent embodiments.

[0054] like Figure 1 As shown, a preferred embodiment of this application provides a method for early warning of surge in an aircraft engine, including the following steps:

[0055] S1. Acquire the dynamic pressure signal of the aero-engine in real time from the engine dynamic pressure sensor;

[0056] S2. Perform correlation analysis on the real-time acquired dynamic pressure signals to obtain the correlation coefficient;

[0057] S3. Continuously calculate the mean μ of the correlation coefficient of the aero-engine rotor after X revolutions and the standard deviation σ of the correlation coefficient of the aero-engine rotor after 1 revolution;

[0058] S4. Calculate the dimensionless offset U continuously based on the mean μ and standard deviation σ to obtain the dimensionless offset U sequence;

[0059] S5. Perform logical counting on the dimensionless offset U sequence according to the set counting conditions;

[0060] S6. When the real-time calculated logic count value meets the uniformly set threshold condition, a surge alarm signal is issued.

[0061] Compared to existing correlation coefficient threshold setting methods, the aircraft engine surge warning method of this embodiment has better universality. Traditional correlation coefficient thresholds vary depending on the engine speed or engine type, making it impossible to provide a uniform threshold. However, this embodiment uses logical counting based on the trend change of dimensionless offset, and the counter only increases when the trend continues to worsen. Therefore, the threshold setting is universal. Based on the analysis of a large amount of surge test data, it can be seen that this embodiment can set the same logical count value threshold as the surge alarm threshold for different engines and different engine speeds, achieving a uniform threshold and possessing universality and strong adaptability.

[0062] Specifically, the calculation process for the correlation coefficient is as follows:

[0063]

[0064] Where t represents the sampling time, x i It is the dynamic pressure signal value measured during the first revolution of the compressor (there are n measurements per revolution), y i It is the dynamic pressure signal value measured during the current revolution of the compressor. This is the average value of the dynamic pressure signal during the first revolution of the compressor. This is the average value of the dynamic pressure signal during the current revolution of the compressor.

[0065] This embodiment uses the dynamic pressure signal value xi measured in the previous revolution of the compressor and the dynamic pressure signal value y measured in the current revolution of the compressor. i The average value of the dynamic pressure signal during the first revolution of the compressor. The average dynamic pressure signal value of the compressor during the current revolution The correlation coefficient c(t) is calculated together to express the degree of linear correlation between dynamic pressure signal values ​​obtained at different sampling times.

[0066] Specifically, the mean μ of the correlation coefficient for the aero-engine rotor after X revolutions is as follows:

[0067]

[0068] The standard deviation σ of the correlation coefficient for one revolution of the aero-engine rotor is as follows:

[0069]

[0070] Where X≥100, N represents the number of dynamic pressure signal points collected when the aero-engine rotor rotates 1 revolution, and the sampling time interval Δt is calculated based on the sampling rate of the dynamic pressure sensor. Then the sequence of sampling time t is: 0, 1Δt, 2Δt, ..., (N-1)Δt.

[0071] Preferably, the dimensionless offset U sequence is obtained by continuously calculating the dimensionless offset U based on the mean μ and standard deviation σ as follows:

[0072]

[0073] SFM = 1 × 10 -5 ;

[0074] SFM is a preset constant used to prevent the denominator of the formula for calculating the dimensionless offset U from being zero. In this embodiment, it is set to 1 × 10⁻⁶. -5 However, no specific value is restricted. The purpose is to prevent the denominator from being 0 in the formula for calculating the dimensionless offset U.

[0075] Specifically, the logical counting of the dimensionless offset U sequence according to the set counting conditions includes the following steps:

[0076] S51. When the dimensionless offset U at the current moment in the dimensionless offset U sequence is greater than or equal to the set value U0 and the dimensionless offset U at the current moment is greater than the dimensionless offset U at the previous moment and continues to increase, the counter is incremented by 1; otherwise, the counter is cleared to 0. Here, U0 can be 1.5, 2 or 3. In this embodiment, U0 is 1.5.

[0077] Specifically, when the real-time calculated logical count value meets a uniformly set threshold condition, issuing a surge alarm signal includes the following steps:

[0078] S61. Set the logic count threshold Z0 (e.g., Z0 is 3) as the surge alarm threshold;

[0079] S62. When the real-time calculated logic count value is greater than Z0, and exceeds Z0 M times (e.g., M is 3) within a set time t0 (e.g., within 1 second), a surge alarm signal is issued.

[0080] Preferably, issuing a surge alarm signal when the real-time calculated logic count value meets a uniformly set threshold condition further includes the following steps:

[0081] S63. Determine whether to stop the alarm. If the alarm stops, enter the surge alarm standby state.

[0082] The principles of the above embodiments will be briefly explained below.

[0083] Before compressor surge occurs, rotational stall will occur first, and before rotational stall, there will be signs of stall.

[0084] The aforementioned correlation coefficient c(t) decreases when stall precursors and rotational stall occur, while the dimensionless offset U increases. When U is greater than 1.5 (or greater than 2 or 3) and continues to increase, the logic count value begins to rise. When the logic count value is greater than Z0, and exceeds Z0 M times (e.g., M = 3) within a certain time t0 (e.g., within 1 second), a surge alarm signal is issued. Because the alarm is issued when stall precursors or rotational stall occur, before the surge occurs, a surge warning is achieved. Additionally, it can be determined whether to stop the alarm; if so, the system enters a surge alarm standby state.

[0085] The above embodiment utilizes the normal distribution probability problem P(μ-1.5σ≤X≤μ+1.5σ)=86.64%. Theoretically, when U is greater than 1.5 under normal compressor conditions, the probability that the correlation coefficient c(t) falls within the 1.5σ interval is 86.64% (the probability of falling outside the 1.5σ interval is small, but not zero, meaning there is a probability of false surge under normal compressor operation). When the compressor experiences rotating stall, the probability that the correlation coefficient c(t) falls outside the 1.5σ interval increases, and the calculated value of U will be greater than 1.5. When U is greater than 1.5 times and continues to increase, the logic count value (integer, such as 0, 1, 2, 3, 4, 5, 6...) begins to rise. To reduce the false surge rate, this application adds a restriction that the number of times the logic count value is greater than Z0, M, must be greater than or equal to 3 times. This is similar to the hit rate of a missile being 70%, then the hit rate of three missiles is 1-(1-0.7)^3=97.3%. Since the number of times the logic count value is greater than Z0, M, must be greater than or equal to 3, based on statistics, when M=3 in the above embodiment, the accuracy of the alarm in this application is about 99.76%, thereby further ensuring a certain level of early warning accuracy.

[0086] This application has passed the test verification of the compressor components and the whole machine of the aircraft engine, proving that the method is feasible!

[0087] Test and verification at the compressor component level of aero-engines:

[0088] The surge warning method for aero-engines provided in this application was used to conduct surge warning on a test specimen of a high-load combined compressor component. The results are as follows: Figure 2 As shown, Z0=3, M=3, which can provide an early warning of surge about 1 second in advance.

[0089] Overall testing and verification of aero-engine compressor:

[0090] The surge warning method for aero-engines provided in this application was used to perform surge warning on a complete aero-engine test component, and the results are as follows: Figure 3 As shown, Z0=3, M=3, which can provide an early warning of surge approximately 0.7 seconds in advance.

[0091] As can be seen, the engine surge warning provided in this application can not only issue a warning signal before engine surge occurs, ensuring that the control system intervenes in advance to prevent surge from occurring or reduce the harm of surge even if it occurs, thus ensuring the safe operation of the engine; at the same time, it can also set the same logic count value threshold as the surge alarm threshold for different engines and different speeds, achieving a unified threshold, which is universal, highly adaptable, and widely applicable.

[0092] like Figure 4As shown, this application also provides an aircraft engine surge warning device, characterized in that it includes:

[0093] The signal acquisition module is used to acquire the dynamic pressure signal of the aero-engine in real time.

[0094] The correlation analysis module is used to perform correlation analysis on the real-time acquired dynamic pressure signals and obtain the correlation coefficient.

[0095] The mean and standard deviation calculation module is used to continuously calculate the mean μ of the correlation coefficient of the aero-engine rotor after X revolutions and the standard deviation σ of the correlation coefficient of the aero-engine rotor after 1 revolution.

[0096] The dimensionless offset calculation module is used to continuously calculate the dimensionless offset U based on the mean μ and standard deviation σ to obtain the dimensionless offset U sequence;

[0097] The logic counting module is used to perform logical counting on the dimensionless offset U sequence according to the set counting conditions.

[0098] The early warning module is used to issue a surge warning signal when the real-time calculated logical count value meets the uniformly set threshold conditions.

[0099] The aero-engine surge warning device provided in this application, employing the aero-engine surge warning method described in the above embodiments, can solve the technical problems of existing aero-engine surge warning technologies, which cannot provide a uniform threshold for active surge control, lacking universality and adaptability. Compared with the prior art, the beneficial effects of the aero-engine surge warning device provided in this application are the same as those of the aero-engine surge warning method provided in the above embodiments, and other technical features in the aero-engine surge warning device are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0100] like Figure 5 As shown, a preferred embodiment of this application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the steps of the aircraft engine surge warning method in the above embodiments.

[0101] The electronic device provided in this application employs the aircraft engine surge warning method described in the above embodiments, which solves the technical problem that existing aircraft engine surge warning technologies cannot provide a uniform threshold for active surge control, lacking universality and adaptability. Compared with the prior art, the beneficial effects of the electronic device provided in this application are the same as those of the aircraft engine surge warning method provided in the above embodiments, and other technical features of the electronic device are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0102] like Figure 6 As shown, a preferred embodiment of this application also provides a computer device, which may be a terminal or a liveness detection server, and its internal structure diagram may be as follows. Figure 6 As shown. The computer device includes a processor, memory, and a network interface connected via a system bus. The processor provides computing and control capabilities. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage medium. The network interface is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it implements the steps of the aforementioned aircraft engine surge warning method.

[0103] Those skilled in the art will understand that Figure 6 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0104] The computer equipment provided in this application, employing the aircraft engine surge warning method described in the above embodiments, can solve the technical problems of existing aircraft engine surge warning technologies, which cannot provide a uniform threshold for active surge control, lacking universality and adaptability. Compared with the prior art, the beneficial effects of the computer equipment provided in this application are the same as those of the aircraft engine surge warning method provided in the above embodiments, and other technical features in the electronic equipment are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0105] A preferred embodiment of this application also provides a storage medium including a stored program that, when the program is executed, controls the device where the storage medium is located to perform the steps of the aircraft engine surge warning method described in the above embodiments.

[0106] It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be executed in a different order than that shown here.

[0107] If the functions described in this embodiment are implemented as software functional units and sold or used as independent products, they can be stored in one or more computing device-readable storage media. Based on this understanding, the parts of this application's embodiments that contribute to the prior art or the technical solutions can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computer, server, mobile computing device, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage media include: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0108] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of this application can be implemented using various computer languages, such as the object-oriented programming language C++ and the embedded programming language C.

[0109] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0110] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0111] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0112] This application also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the aircraft engine surge warning method described above.

[0113] The computer program product provided in this application can solve the technical problem that existing aero-engine surge warning technologies cannot provide a uniform threshold for active surge control, lacking universality and adaptability. Compared with the prior art, the beneficial effects of the computer program product provided in this application are the same as those of the aero-engine surge warning method provided in the above embodiments, and will not be repeated here.

[0114] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0115] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A method for early warning of surge in aero-engines, characterized in that, Including the following steps: Real-time acquisition of dynamic pressure signals from aero engines; Correlation analysis was performed on the real-time acquired dynamic pressure signals to obtain the correlation coefficient; The mean μ of the correlation coefficient for the aero-engine rotor after X revolutions and the standard deviation σ of the correlation coefficient for the aero-engine rotor after 1 revolution are continuously calculated. The dimensionless offset U sequence is obtained by continuously calculating the dimensionless offset U based on the mean μ and standard deviation σ; The dimensionless offset U sequence is logically counted according to the set counting conditions; When the real-time calculated logic count value meets the uniformly set threshold condition, a surge alarm signal is issued.

2. The method for early warning of surge in aero-engines according to claim 1, characterized in that, The correlation coefficient is calculated as follows: Where t represents the sampling time, x i It is the dynamic pressure signal value measured during the first revolution of the compressor, y i It is the dynamic pressure signal value measured during the current revolution of the compressor. This is the average value of the dynamic pressure signal during the first revolution of the compressor. This is the average value of the dynamic pressure signal during the current revolution of the compressor.

3. The method for early warning of surge in aero-engines according to claim 1 or 2, characterized in that, The mean μ of the correlation coefficient for the aero-engine rotor after X revolutions is as follows: The standard deviation σ of the correlation coefficient for one revolution of the aero-engine rotor is as follows: Where X≥100, N represents the number of dynamic pressure signal points collected when the aero-engine rotor rotates 1 revolution, and the sampling time interval Δt is calculated based on the sampling rate of the dynamic pressure sensor. Then the sequence of sampling time t is: 0, 1Δt, 2Δt, ..., (N-1)Δt.

4. The method for early warning of surge in aero-engines according to claim 3, characterized in that, The dimensionless offset U sequence is obtained by continuously calculating the dimensionless offset U based on the mean μ and standard deviation σ: SFM is a preset constant used to prevent the denominator of the formula for calculating the dimensionless offset U from being zero.

5. The method for early warning of surge in aero-engines according to claim 4, characterized in that, The logical counting of the dimensionless offset U sequence according to the set counting conditions specifically includes the following steps: When the dimensionless offset U at the current moment in the dimensionless offset U sequence is greater than the set value U0 and the dimensionless offset U at the current moment is greater than the dimensionless offset U at the previous moment and continues to increase, the counter is incremented by 1; otherwise, the counter is cleared to 0.

6. The method for early warning of surge in aero-engines according to claim 5, characterized in that, When the real-time calculated logic count value meets the uniformly set threshold condition, a surge alarm signal is issued, specifically including the following steps: Set the logic count threshold Z0 as the surge alarm threshold; When the real-time calculated logic count value is greater than Z0, and exceeds Z0 M times within the set time t0, a surge alarm signal is issued, M≥3.

7. The method for early warning of surge in aero-engines according to claim 6, characterized in that, When the real-time calculated logic count value meets the uniformly set threshold condition, the surge alarm signal is issued, which further includes the following steps: Determine whether to stop the alarm. If the alarm stops, enter the surge alarm standby state.

8. An aircraft engine surge warning device, characterized in that, include: The signal acquisition module is used to acquire the dynamic pressure signal of the aero-engine in real time. The correlation analysis module is used to perform correlation analysis on the real-time acquired dynamic pressure signals and obtain the correlation coefficient. The mean and standard deviation calculation module is used to continuously calculate the mean μ of the correlation coefficient of the aero-engine rotor after X revolutions and the standard deviation σ of the correlation coefficient of the aero-engine rotor after 1 revolution. The dimensionless offset calculation module is used to continuously calculate the dimensionless offset U based on the mean μ and standard deviation σ to obtain the dimensionless offset U sequence; The logic counting module is used to perform logical counting on the dimensionless offset U sequence according to the set counting conditions. The early warning module is used to issue a surge warning signal when the real-time calculated logical count value meets the uniformly set threshold conditions.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the steps of the aircraft engine surge warning method as described in any one of claims 1 to 7.

10. A storage medium comprising a stored program, characterized in that, When the program is running, it controls the device containing the storage medium to perform the steps of the aircraft engine surge warning method as described in any one of claims 1 to 7.

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