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

Abstract

The invention belongs to the technical field of engine surge early warning, and provides an aero-engine surge early warning method, system and device and a storage medium, and the method comprises the steps: obtaining a dynamic pressure signal, a rotating speed signal and a sampling rate of an engine; obtaining a post-processing signal based on the dynamic pressure signal, the rotating speed signal and the sampling rate; setting an alarm threshold value of the post-processing signal; the number of times that the post-processing signal exceeds an alarm threshold is judged, when the post-processing signal exceeds the alarm threshold y times, an alarm signal is sent out, and y is larger than 1; sending a stall suppression instruction or a surge suppression instruction based on the alarm signal until the alarm is stopped; and judging whether to stop alarming, and if so, entering an alarming standby state. According to the method, an early warning signal can be sent out before the aero-engine surges, it is guaranteed that a control system intervenes in advance, surges are prevented, or harms of surges can be reduced even if surges occur, and safe operation of the aero-engine is guaranteed.

Description

Technical Field

[0001] The present invention belongs to the technical field of engine surge warning, and particularly relates to a method, system, device and storage medium for warning of aeroengine surge. Background Art

[0002] Surge (a phenomenon similar to the "water hammer effect" of metal water pipes, which is extremely likely to cause engine scrapping) is related to engine safety. The airworthiness regulations clearly stipulate that excessive harm is not allowed to occur after compressor surge. The active surge control technology is a technology that can improve the safety of the engine and the efficiency of the compressor. This technology is one of the core technologies of future intelligent engines.

[0003] The design orientation of modern turbomachinery is developing towards high load, high efficiency and wide stable operating range. Higher single-stage pressure ratio and efficiency, and achieving higher load with fewer stages have become the key technologies for compressor / fan design. However, the higher the stage load of the compressor, the more demanding the requirements for its stable operating conditions. The stable operating range of the compressor is determined by its surge margin, that is, the possible flow rate and pressure ratio change range between the operating point and the surge boundary point of the compressor. If the surge margin of the compressor is too small, once rotating stall or surge occurs, it will cause a sharp deterioration of the engine performance at least, and at worst, the engine will flame out or the whole engine will be damaged due to blade fracture. Therefore, broadening the stable operating range of the compressor and delaying the air flow stall have become one of the key technologies for designing high-load compressors. Traditional surge control methods belong to passive control technologies, and their core is to ensure that there is enough margin between the operating point of the compressor and the surge boundary, so that the compressor operates far from the surge boundary point. However, the surge boundary is often affected by factors such as flight conditions, engine operating conditions, and inlet flow field distortion, making it difficult to accurately determine. The determination of the surge margin seriously reduces the performance of the compressor. With the increase of the compressor load, the contradiction between performance and surge margin becomes more prominent, and the idea of active surge control emerged under such circumstances.

[0004] The existing surge control of aeroengines is a passive control after surge occurs. When designing, a large surge margin (the "distance" from the design point to the surge boundary) needs to be reserved. This kind of control cannot avoid the occurrence of surge, so it cannot avoid the harm brought by surge (such as engine failure, aircraft crash, etc.). Summary of the Invention

[0005] In order to solve the problems in the background art, the present invention proposes a method, system, device and storage medium for warning of aeroengine surge.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] An aeroengine surge warning method, comprising the following steps:

[0008] Acquisition step: Obtain the dynamic pressure signal, rotational speed signal and sampling rate of the engine;

[0009] Obtain a post-processing signal based on the dynamic pressure signal, rotational speed signal and sampling rate;

[0010] Set the alarm threshold of the post-processing signal;

[0011] Judge the number of times the post-processing signal exceeds the alarm threshold. When the post-processing signal exceeds the alarm threshold y times (y > 1), send an alarm signal;

[0012] Execution step: Based on the alarm signal, issue a stall suppression instruction or a surge suppression instruction until the alarm stops;

[0013] Judge whether the alarm stops. If the alarm stops, enter the alarm standby state and return to the acquisition step. If the alarm does not stop, return to the execution step.

[0014] Preferably, obtaining the post-processing signal based on the dynamic pressure signal, rotational speed signal and sampling rate includes the following steps:

[0015] Obtain the total number of dynamic pressure points collected when the engine rotor rotates one circle based on the sampling rate and rotational speed signal;

[0016] Obtain the number of dynamic pressure points collected by x blade channels based on the number of blades of the engine rotor and the rotational speed signal (z ≥ x ≥ 1, z is the number of all blade channels, and the total number of blade channels is equal to the total number of blades);

[0017] Calculate the post-processing signal based on the dynamic pressure signal, the total number of dynamic pressure points collected when the engine rotor rotates one circle, and the number of dynamic pressure points collected by x blade channels.

[0018] Preferably, the total number of dynamic pressure points collected when the engine rotor rotates one circle satisfies:

[0019] M = f s / n s = 60f s / n;

[0020] In the formula, M represents the total number of dynamic pressure points collected when the engine rotor rotates one circle; f s is the sampling rate; n is the rotational speed of the engine rotor per minute, with the unit of rpm; n s represents the number of circles the engine rotor rotates per second.

[0021] Preferably, the number of dynamic pressure points collected by x blade channels satisfies:

[0022] N = 60 × x × fs / (m × n);

[0023] Wherein, N represents the number of dynamic pressure points collected by x blade channels; m represents the number of single-row blades of the engine rotor; f s is the sampling rate; n is the rotational speed of the engine rotor per minute, with the unit of rpm; x represents x blade channels.

[0024] Preferably, the post-processing signal satisfies:

[0025]

[0026] Wherein, S(t) represents the post-processing signal at time t; M represents the total number of dynamic pressure points collected when the rotor rotates one circle; N represents the number of dynamic pressure points collected by x blade channels, N < M; i = t - N represents the time corresponding to the engine rotor pushing forward x blade channels before time t; P i represents the dynamic pressure signal at time i, with the pressure being gauge pressure and the unit being PSI; P i-M represents the dynamic pressure signal at time i - M; i - M represents the time corresponding to M dynamic pressure points before time i.

[0027] Preferably, the stall suppression instruction is to control the jet or bleed at the rotor tip;

[0028] The surge suppression instruction is to open the anti-surge bleed valve.

[0029] Preferably, the sampling rate is greater than 10 times the blade passing frequency;

[0030] The blade passing frequency is equal to the blade rotation frequency multiplied by the number of blades.

[0031] An aero-engine surge warning system, comprising:

[0032] An acquisition unit, configured to acquire the dynamic pressure signal, rotational speed signal, and sampling rate of the engine;

[0033] A processing unit, configured to obtain a post-processing signal based on the dynamic pressure signal, rotational speed signal, and sampling rate;

[0034] A setting unit, configured to set the alarm threshold of the post-processing signal;

[0035] A first judgment unit, configured to judge the number of times the post-processing signal exceeds the alarm threshold. When the post-processing signal exceeds the alarm threshold y times, an alarm signal is issued, where y > 1;

[0036] A control unit, configured to issue a stall suppression instruction or a surge suppression instruction based on the alarm signal until the alarm stops;

[0037] A second judgment unit, configured to judge whether to stop the alarm. If the alarm is stopped, it enters the alarm standby state.

[0038] Preferably, the processing unit includes:

[0039] A first processing module, configured to obtain the total number of dynamic pressure points collected when the engine rotor rotates one circle based on the sampling rate and the rotational speed signal;

[0040] A second processing module, configured to obtain the number of dynamic pressure points collected by x blade channels based on the number of blades of the engine rotor and the rotational speed signal, where z≥x≥1, z is the total number of all blade channels, and the total number of blade channels is equal to the total number of blades;

[0041] A third processing module, configured to calculate a post-processing signal based on the dynamic pressure signal, the total number of dynamic pressure points collected when the engine rotor rotates one circle, and the number of dynamic pressure points collected by x blade channels.

[0042] A device includes:

[0043] A memory, configured to store a computer program;

[0044] A processor, configured to implement the above-mentioned aeroengine surge warning method when executing the program stored in the memory.

[0045] A computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the above-mentioned aeroengine surge warning method is implemented.

[0046] Advantages of the present invention:

[0047] 1. The aeroengine surge warning method provided by the present invention can send a warning signal before the aeroengine surges, ensuring that the control system intervenes in advance, preventing the occurrence of surges or reducing the harm of surges even if the engine enters a surge state, and ensuring the safe operation of the aeroengine;

[0048] 2. The post-processing signal of the present invention takes into account the influence of various factors such as the dynamic pressure signal, rotational speed signal, and sampling rate of the engine, and can provide a more accurate prediction for the surge warning of the engine after calculation.

[0049] Other features and advantages of the present invention will be described in the following specification, and part of them will become obvious from the specification, or will be understood by implementing the present invention. The objectives and other advantages of the present invention can be realized and obtained through the structures pointed out in the specification and the drawings. Description of the Drawings

[0050] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the accompanying drawings required for the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other accompanying drawings can also be obtained based on these drawings.

[0051] Figure 1 Shows a flowchart of a surge warning method for an aeroengine of the present invention;

[0052] Figure 2 Shows a schematic diagram of active control and passive control during engine stall;

[0053] Figure 3 Shows a verification result graph of a certain high-load combined compressor component test based on "Algorithm 1";

[0054] Figure 4 Shows a verification result graph of a certain aeroengine overall test based on "Algorithm 1";

[0055] Figure 5 Shows a structural diagram of a surge warning system for an aeroengine of the present invention. Detailed implementation manners

[0056] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

[0057] As Figure 1 shown, it is a surge warning method for an aeroengine, characterized by including the following steps:

[0058] S1: Obtain the dynamic pressure signal, rotational speed signal, and sampling rate of the engine.

[0059] S2: Obtain a post-processing signal based on the dynamic pressure signal, rotational speed signal, and sampling rate.

[0060] S3: Set the alarm threshold of the post-processing signal.

[0061] S4: Determine the number of times the post-processing signal exceeds the alarm threshold. When the post-processing signal exceeds the alarm threshold y times (y > 1), send an alarm signal.

[0062] S5: Based on the alarm signal, issue a stall suppression instruction or a surge suppression instruction until the alarm stops;

[0063] S6: Determine whether to stop the alarm. If the alarm is stopped, enter the alarm standby state and return to S1. If the alarm is not stopped, return to S5.

[0064] It should be noted that the dynamic pressure signal can be collected by the dynamic pressure sensor of the engine, the rotational speed signal can be obtained by the rotational speed sensor of the engine, and the sampling rate can be set in advance.

[0065] Further, S2 includes the following steps:

[0066] S201: Obtain the total number of dynamic pressure points collected when the engine rotor rotates one circle based on the sampling rate and the rotational speed signal. S202: Obtain the number of dynamic pressure points collected by x blade channels based on the number of blades of the engine rotor and the rotational speed signal, where z ≥ x ≥ 1 and z is the number of all blade channels. S203: Calculate the post-processing signal based on the dynamic pressure signal, the total number of dynamic pressure points collected when the engine rotor rotates one circle, and the number of dynamic pressure points collected by x blade channels.

[0067] Optionally, set the rotational speed n of the engine rotor, and the unit is usually revolutions per minute (rpm). Convert the rotational speed per minute to the rotational speed per second, that is, n s = n / 60, where n s represents the number of circles the rotor rotates per second. Additionally, set the sampling rate to f s , and the unit is Hertz (Hz), that is, the number of points collected per second. Therefore, in S201:

[0068] M = f s / n s = 60f s / n; (1)

[0069] In the formula, M represents the total number of dynamic pressure points collected when the engine rotor rotates one circle.

[0070] For example, if the rotational speed of the engine rotor is 3000 rpm and the sampling rate of the dynamic pressure signal is 10000 Hz, then the total number of dynamic pressure points collected when the rotor rotates one circle is: M = 60 × 10000 / 3000 = 200 (points).

[0071] Optionally, based on formula (1), set the number of blades of the rotor to m. Then the number of blades passing through one blade channel per second is m × ns. Therefore, the number of dynamic pressure points N1 collected by one blade channel is:

[0072] N1 = 60fs / (m × n); (2)

[0073] The number of dynamic pressure points N collected by x blade channels is:

[0074] N = 60 × x × fs / (m × n); (3)

[0075] For example, for an engine rotor speed of 3600 rpm, 10 blades, and a dynamic pressure signal sampling rate of 12000 Hz, if we want to calculate the number of dynamic pressure points collected from 5 blade channels, then:

[0076] N1 = 12000 / 600 = 20 (points);

[0077] N = 12000 × 5 / 600 = 100 (points).

[0078] Based on formulas (1) and (3), the post - processed signal satisfies:

[0079]

[0080] In the formula, S(t) represents the post - processed signal at time t; M represents the total number of dynamic pressure points collected when the rotor rotates one circle; N represents the number of dynamic pressure points collected from x blade channels, N < M; i = t - N represents the time corresponding to the rotor of the engine pushing forward x blade channels before time t; P i represents the dynamic pressure signal at time i, the pressure is gauge pressure, and the unit is PSI; P i-M represents the dynamic pressure signal at time i - M; i - M represents the time corresponding to M dynamic pressure points before time i. Based on the sampling time interval Δt calculated from the dynamic pressure sensor sampling rate, the sequence of t is 0, 1Δt, 2Δt,..., (k - 1)Δt.

[0081] It should be noted that before the compressor surges, rotating stall will occur first, and before rotating stall, stall precursors will occur first. In formula (4), when stall precursors and rotating stall occur, the value of S(t) will increase. When the post - processed signal S(t) calculated in real - time is greater than the alarm threshold "Scr" y times (y > 1), an alarm signal is sent. Therefore, the larger the value of S(t), the greater the risk or probability of surge. Because the alarm is sent when stall precursors or rotating stall occur, which is earlier than the occurrence of surge, early warning before surge is achieved. The engine control system issues stall suppression or surge suppression instructions according to the alarm signal, and takes corresponding suppression measures according to whether the alarm signal stops until the alarm stops.

[0082] Such as Figure 2As shown, it reflects the difference between active control and passive control. In the figure, the abscissa is the command flow rate, and the ordinate is the pressure ratio. The constant speed lines pass through the surge line without active control and the surge line with active control, and the gray area is the active control stability expansion region. When the operating point is point A on the constant speed line, since it is below the surge line without active control, active control cannot be carried out. Point B in the gray area belongs to the point where active control is possible, and the interval between point A and point B belongs to the performance improvement.

[0083] Furthermore, the methods of stall suppression mainly include measures such as jetting or bleeding at the rotor tip. This measure uses high-speed airflows to improve the flow field structure in the tip region and effectively delays the airflow separation; or a bleeding strategy is adopted to discharge some low-energy airflows to reduce the degree of airflow blockage inside the compressor, thereby maintaining stable aerodynamic performance.

[0084] In addition, the measures for surge suppression mainly include measures such as opening the anti-surge bleed valve. This measure can quickly release the high-pressure gas accumulated inside the compressor, break the energy feedback cycle of surge occurrence, re-establish a stable flow-pressure balance relationship, and ensure the safe and stable operation of the engine. The opening degree of the anti-surge bleed valve for surge suppression is determined whether to continue to increase according to the situation of exiting the surge (similar to whether to increase the depth of stepping on the brake in the braking system).

[0085] Furthermore, the sampling rate is greater than 10 times the blade pass frequency (BPF, blade pass frequency) so as to be able to identify the stall precursor. This blade pass frequency is equal to the rotation frequency of the blade multiplied by the number of blades, usually taking 200 kHz. For example, if the blade rotation speed is 6000 revolutions per minute, the number of blades n = 20, the blade rotation frequency = 6000 / 60 = 100 Hz, then the blade pass frequency = 100 Hz * 20 = 2000 Hz, and the required sampling rate should be greater than 10 * 2000 Hz = 20000 Hz = 20 kHz.

[0086] As Figure 3 shown, the "Algorithm 1" is used to carry out surge warning on a certain high-load combined compressor component test piece, where the "Algorithm 1" is the above formula (4). Specifically, Figure 3 the ordinate represents the calculation result of S(t), the abscissa represents the relative time, the alarm threshold is set to 0.0032, the upper curve is the dynamic pressure signal P s corresponding curve, and the lower curve is the curve corresponding to S(t). When S(t) shows obvious pulsations and exceeds 0.0032, a warning will be issued, and then a surge warning signal will be sent, and a 163 ms pre-surge warning can be achieved.

[0087] As Figure 4 shown, the "Algorithm 1" is used to carry out surge warning on a certain aero-engine whole-machine test piece, and the result is asFigure 4 as shown, where the alarm threshold is 0.0015, and P jin2 represents the dynamic static pressure, S(t) is the post-processing signal at time t. When S(t) shows obvious pulsation (exceeding 0.0015), a surge warning signal is sent (at 670 ms), and finally a surge occurs at 1100.4 ms, with a 430.4 ms pre-warning before the surge.

[0088] Such as Figure 5 shown, is a surge warning system for an aero-engine, including an acquisition unit, a processing unit, a setting unit, a first judgment unit, a control unit, and a second judgment unit. The acquisition unit is used to obtain the dynamic pressure signal, rotational speed signal, and sampling rate of the engine; the processing unit is used to obtain the post-processing signal based on the dynamic pressure signal, rotational speed signal, and sampling rate; the setting unit is used to set the alarm threshold of the post-processing signal; the first judgment unit is used to judge the number of times the post-processing signal exceeds the alarm threshold. When the post-processing signal exceeds the alarm threshold y times (y > 1), an alarm signal is sent; the control unit is used to issue a stall suppression instruction or a surge suppression instruction based on the alarm signal until the alarm stops; the second judgment unit is used to judge whether to stop the alarm. If the alarm stops, it enters the alarm standby state.

[0089] Further, the processing unit includes a first processing module, a second processing module, and a third processing module. The first processing module is used to obtain the total number of dynamic pressure points collected when the engine rotor rotates one circle based on the sampling rate and rotational speed signal; the second processing module is used to obtain the number of dynamic pressure points collected in x blade channels based on the number of blades of the engine rotor and the rotational speed signal, where z ≥ x ≥ 1, z is the total number of all blade channels, and the total number of blade channels is equal to the total number of blades; the third processing module is used to calculate the post-processing signal based on the dynamic pressure signal, the total number of dynamic pressure points collected when the engine rotor rotates one circle, and the number of dynamic pressure points collected in x blade channels.

[0090] A device includes a memory and a processor. The memory is used to store a computer program, and when the processor executes the program stored on the memory, it realizes Figure 1 a surge warning method for an aero-engine as described

[0091] It should be noted that the memory may include a random access memory (Random Access Memory, abbreviated as RAM), or may also include a non-volatile memory, such as at least one disk memory.

[0092] The above-mentioned processor may be a general-purpose processor, including a Central Processing Unit (CPU for short), a Network Processor (NP for short), etc.; it may also be a Digital Signal Processor (DSP for short), an Application Specific Integrated Circuit (ASIC for short), a Field-Programmable Gate Array (FPGA for short), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0093] A computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it implements Figure 1 one of the aeroengine surge warning methods in

[0094] It should be noted that the computer-readable storage medium may be included in the device / device described in the above embodiments; it may also exist alone without being assembled into the device / device. The above computer-readable storage medium carries one or more programs. When the above one or more programs are executed, one of the aeroengine surge warning methods according to the embodiments of the present invention is implemented.

[0095] According to the embodiments of the present invention, the computer-readable storage medium may be a non-volatile computer-readable storage medium, for example, it may include: portable computer disks, hard disks, random access memories (RAM), read-only memories (ROM), erasable programmable read-only memories (EPROM or flash memories), portable compact disk read-only memories (CD-ROMs), optical storage devices, magnetic storage devices, or any suitable combination of the above. In the present invention, the computer-readable storage medium may be any tangible medium that contains or stores a program, and the program may be used by or in combination with an instruction execution system, device, or device.

[0096] Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for surging warning of an aeroengine, characterized in that, It includes the following steps: Acquisition step: Obtain the dynamic pressure signal, rotational speed signal, and sampling rate of the engine; Obtain the post - processed signal based on the dynamic pressure signal, rotational speed signal, and sampling rate; Set the alarm threshold of the post - processed signal; Judge the number of times the post - processed signal exceeds the alarm threshold. When the post - processed signal exceeds the alarm threshold y times (y > 1), send an alarm signal; Execution step: Based on the alarm signal, send a stall suppression instruction or a surge suppression instruction until the alarm stops; Judge whether the alarm stops. If the alarm stops, enter the alarm standby state and return to the acquisition step. If the alarm does not stop, return to the execution step.

2. The surge warning method for an aeroengine according to claim 1, wherein Obtain the post - processed signal based on the dynamic pressure signal, rotational speed signal, and sampling rate, including the following steps: Based on the sampling rate and rotational speed signal, obtain the total number of dynamic pressure points collected when the engine rotor rotates one circle; Based on the number of blades of the engine rotor and the rotational speed signal, obtain the number of dynamic pressure points collected from x blade channels (z ≥ x ≥ 1, z is the number of all blade channels, and the total number of blade channels is equal to the total number of blades); Calculate the post - processed signal based on the dynamic pressure signal, the total number of dynamic pressure points collected when the engine rotor rotates one circle, and the number of dynamic pressure points collected from x blade channels.

3. The aero-engine surge warning method according to claim 2, wherein The total number of dynamic pressure points collected when the engine rotor rotates one circle satisfies: M = f s / n s = 60f s / n; Where M represents the total number of dynamic pressure points collected when the engine rotor rotates one circle; f s is the sampling rate; n is the rotational speed of the engine rotor per minute, with the unit of rpm; n s represents the number of circles the engine rotor rotates per second.

4. A method for surging warning of an aeroengine according to claim 2, characterized in that, The number of dynamic pressure points collected from x blade channels satisfies: N = 60×x×fs / (m×n); Wherein, N represents the number of dynamic pressure points collected by x blade channels; m represents the number of single-row blades of the engine rotor; f s is the sampling rate; n is the rotational speed of the engine rotor per minute, with the unit of rpm; x represents x blade channels.

5. A method for surging warning of an aeroengine according to claim 2, characterized in that, The post - processed signal satisfies: Wherein, S(t) represents the post-processing signal at time t; M represents the total number of dynamic pressure points collected when the rotor rotates one circle; N represents the number of dynamic pressure points collected from x blade channels, N < M; i = t - N represents the time corresponding to the engine's rotor pushing forward x blade channels before time t; P i represents the dynamic pressure signal at time i, the pressure is gauge pressure, and the unit is PSI; P i-M represents the dynamic pressure signal at time i - M; i - M represents the time corresponding to M dynamic pressure points before time i.

6. The surge warning method for an aeroengine according to claim 1, wherein The stall suppression instruction is to control the jet or bleed at the rotor tip; The surge suppression instruction is to open the anti - surge bleed valve; 7. A method for surging warning of an aero-engine according to claim 2, characterized in that, The sampling rate is greater than 10 times the blade passing frequency; The blade passing frequency is equal to the blade rotation frequency multiplied by the number of blades.

8. An aeroengine surge warning system, characterized in that, It includes: An acquisition unit for obtaining the dynamic pressure signal, rotational speed signal, and sampling rate of the engine; A processing unit for obtaining the post - processed signal based on the dynamic pressure signal, rotational speed signal, and sampling rate; A setting unit for setting the alarm threshold of the post - processed signal; A first judgment unit for judging the number of times the post - processed signal exceeds the alarm threshold. When the post - processed signal exceeds the alarm threshold y times (y > 1), send an alarm signal; A control unit for sending a stall suppression instruction or a surge suppression instruction based on the alarm signal until the alarm stops; A second judgment unit for judging whether the alarm stops. If the alarm stops, enter the alarm standby state.

9. The surge warning system for an aeroengine according to claim 8, wherein, The processing unit includes: A first processing module for obtaining the total number of dynamic pressure points collected when the engine rotor rotates one circle based on the sampling rate and rotational speed signal; A second processing module for obtaining the number of dynamic pressure points collected from x blade channels based on the number of blades of the engine rotor and the rotational speed signal (z ≥ x ≥ 1, z is the number of all blade channels, and the total number of blade channels is equal to the total number of blades); A third processing module for calculating the post - processed signal based on the dynamic pressure signal, the total number of dynamic pressure points collected when the engine rotor rotates one circle, and the number of dynamic pressure points collected from x blade channels.

10. An apparatus, characterized in that, It includes: A memory for storing a computer program; A processor for implementing the method for predicting surge of an aero - engine according to any one of claims 1 - 7 when executing the program stored in the memory.

11. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements a surge warning method for an aeroengine according to any one of claims 1-7.

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