Gas turbine engine, surge diagnostic method, diagnostic system, and medium

Abstract

The invention relates to a gas turbine engine, a surge diagnosis method, a surge diagnosis system and a medium. The diagnosis method comprises the steps that S1, rotating speed data N2 measured by a third sensor are obtained, a real-time rotating speed surge judgment value A0 is obtained according to the measured rotating speed data, and if the rotating speed surge judgment value A0 exceeds a rotating speed surge judgment threshold value A corresponding to the rotating speed, the output diagnosis result is surge; and S2, pressure data P31, measured by the first sensor, of the outlet section of the gas compressor are obtained, a real-time pressure surge judgment value B0 is obtained according to the measured pressure data, and if the pressure surge judgment value B0 exceeds a pressure surge judgment threshold value B corresponding to pressure, the output diagnosis result is surge.

Description

Technical Field

[0001] The present invention relates to the field of gas turbine engines, and in particular to a gas turbine engine, a surge diagnosis method, a diagnosis system, and a computer-readable medium. Background Art

[0002] Gas turbine engines, such as typical civil turbofan aircraft engines, are usually of double bypass configuration, such as Figure 1 As shown, after the air flows into the engine from the aircraft air intake, it first passes through the fan 1 and enters the engine body, and then flows through the splitter ring and is divided into two parts, one part passes through the outer duct and is discharged from the engine, and the other part passes through the supercharged stage blade and the support plate transition section channel 2 and flows into the high-pressure compressor, wherein the section 25 is the interface between the high-pressure and low-pressure compressors, that is, the section 25 is the compressor inlet section 25; the airflow is compressed inside the high-pressure compressor 3 body to form a high-temperature and high-pressure gas, and enters the combustion chamber 5, wherein the section 31 is the interface between the high-pressure compressor and the combustion chamber, that is, the compressor outlet section 31. After the airflow is fully burned, it is discharged from the engine through the high-pressure turbine 5, wherein the section 44 is the high-pressure turbine outlet section 44. When the aircraft engine is tested or working normally, airborne sensors are usually arranged at the sections 25, 31, and 44 to monitor the airflow parameters of these sections, such as the temperature and pressure of the airflow. For example, a first sensor is arranged at the compressor outlet section 31, which can sense the pressure of the compressor outlet section, and a second sensor is arranged at the turbine outlet section 44, which can sense the temperature of the turbine outlet section. Once an abnormality occurs, the engine can be shut down during testing, and emergency landing and other measures can be taken during flight, which can minimize the damage to the engine or aircraft caused by the abnormal situation.

[0003] The most typical failure mode is surge. When the engine surges, the airflow oscillates axially inside the engine, the flow field deteriorates sharply, the airflow pressure at the outlet section 31 drops sharply, the temperature at the turbine outlet section 44 rises sharply, the turbine performance deteriorates sharply, the power generated by the turbine decreases, and the engine physical speed drops.

[0004] In the existing scheme, the diagnosis of engine surge generally relies on detecting the rate of change of the pressure at the compressor outlet section 31 to diagnose and determine whether there is surge.

[0005] The inventors have found that the diagnosis based on detecting the change rate of the pressure at the compressor outlet section 31 has the following problems:

[0006] 1. There is a risk of failure in the pressure sensor measurement of this section, which makes it impossible to carry out surge detection;

[0007] 2. If there is an operational error during the execution of the pressure signal calculation and analysis, it may also cause misjudgment or missed judgment, resulting in failure to detect surge faults or frequent detection of surge faults, such as Figure 2 As shown, the horizontal axis is time, and the vertical axis is the pressure of the compressor outlet section 31. When the engine is stalling (a physical phenomenon with a short duration and less damage to the engine, which can be exited), or when the engine is actively slowing down, the pressure of the compressor outlet section will also decrease.

[0008] Therefore, there is a need in the art for a gas turbine engine, a surge diagnosis method, a diagnosis system, and a medium to form a surge diagnosis method with better robustness and improve the accuracy of engine surge diagnosis results. Summary of the invention

[0009] An object of the present invention is to provide a surge diagnosis method for a gas turbine engine.

[0010] An object of the present invention is to provide a surge diagnostic system for a gas turbine engine.

[0011] An object of the present invention is to provide a gas turbine engine.

[0012] An object of the present invention is to provide a computer readable medium.

[0013] According to a first aspect of the present invention, a gas turbine engine surge diagnosis method is provided, wherein the gas turbine engine is provided with a first sensor at a compressor outlet section, capable of sensing the pressure of the compressor outlet section, a second sensor is provided at a turbine outlet section, capable of sensing the temperature of the turbine outlet section, and the gas turbine engine has a third sensor, capable of sensing the rotation speed of the gas turbine engine; wherein the diagnosis method comprises:

[0014] S1. Obtain the speed data N2 measured by the third sensor, and obtain a real-time speed surge judgment value A0 according to the measured speed data. If the speed surge judgment value A0 exceeds the speed surge judgment threshold A corresponding to the speed, the diagnosis result is output as surge;

[0015] S2. Obtain the pressure data P31 of the compressor outlet cross section measured by the first sensor, and obtain a real-time pressure surge judgment value B0 according to the measured pressure data. If the pressure surge judgment value B0 exceeds the pressure surge judgment threshold B corresponding to the pressure, the diagnosis result is output as surge;

[0016] S3. Obtain the temperature data T44 of the turbine outlet section measured by the second sensor, and obtain a real-time temperature surge judgment value C0 according to the measured temperature data. If the temperature surge judgment value C0 exceeds the temperature surge judgment threshold C corresponding to the temperature, the diagnosis result is output as surge;

[0017] When the output diagnosis structure of any one of S1, S2, and S3 is surge, the gas turbine engine is diagnosed as surge.

[0018] In one or more embodiments, in S1, the real-time speed surge judgment value A0 is obtained according to the following: A0=fN2dot(k)=a*fN2dot(k-1)+b*N2dot(k-1); N2dot(k-1)=(N2(K)-N2(K-1)) / T; wherein k is the data number recorded at the current moment, N2(K) and N2(K-1) are the engine physical speed signals at the current moment and the previous moment respectively collected by the third sensor, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, wherein 0.5≤a≤1, 0≤b≤0.5.

[0019] In one or more embodiments, the speed surge judgment threshold value A ranges from -0.02 to -0.005.

[0020] In one or more embodiments, in S2, the real-time pressure surge judgment value B0 is obtained according to the following: B0=fP31dot(k)=a*fP31dot(k-1)+b*P31dot(k-1); P31dot(k-1)=(P31(K)-P31(K-1)) / T; wherein k is the data number recorded at the current moment, P31(K) and P31(K-1) are the compressor outlet section pressures at the current moment and the previous moment respectively collected by the sensor, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, 0.5≤a≤1, 0≤b≤0.5.

[0021] In one or more embodiments, the pressure surge judgment threshold B ranges from -3.5 to -1.

[0022] In one or more embodiments, in S3, the real-time temperature surge judgment value C0 is obtained according to the following: C0=fT44dot(k)=a*fT44dot(k-1)+b*T44dot(k-1); T44dot(k-1)=(T44(K)-T44(K-1)) / T; wherein k is the data number recorded at the current moment, T44(K) and T44(K-1) are the turbine outlet section temperatures at the current moment and the previous moment respectively collected by the sensor, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, 0.5≤a≤1, 0≤b≤0.5.

[0023] In one or more embodiments, the temperature surge judgment threshold C ranges from 0.1 to 0.2.

[0024] A computer readable medium according to a second aspect of the present invention has a computer program thereon, and the program is executed by a processor to implement the steps of the diagnostic method as described in the first aspect.

[0025] According to a third aspect of the present invention, a surge diagnostic system for a gas turbine engine is provided, wherein the gas turbine engine is provided with a first sensor at a compressor outlet section, capable of sensing the pressure of the compressor outlet section, a second sensor is provided at a turbine outlet section, capable of sensing the temperature of the turbine outlet section, and the gas turbine engine has a third sensor capable of sensing the rotational speed of the gas turbine engine; wherein the diagnostic system comprises: a memory for storing instructions executable by a processor; and a processor for executing the instructions to implement the diagnostic method as described in the first aspect.

[0026] In one or more embodiments, the diagnostic system further includes a display module for displaying the diagnostic result obtained by the processor.

[0027] In one or more embodiments, the processor of the diagnostic system is integrated into a full authority digital engine controller.

[0028] A gas turbine engine according to a fourth aspect of the present invention comprises the diagnostic system according to the third aspect.

[0029] The beneficial effects of the present invention include but are not limited to, by using the rotational speed, compressor outlet cross-sectional pressure, and turbine outlet temperature as diagnostic conditions for diagnosis, any diagnostic condition outputting a surge diagnostic result can diagnose the engine as surging, which is more robust than the existing solutions introduced above. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0031] Figure 1 It is a schematic diagram of the structure of a turbofan engine;

[0032] Figure 2 It is the trend curve of compressor outlet pressure changing with time corresponding to three different phenomena: surge, stall and emergency stop;

[0033] Figure 3 is a flow chart of a surge diagnosis method according to an embodiment;

[0034] Figure 4 It is the change trend of the speed surge judgment value A0 calculated within 2 seconds when an active emergency stop occurs;

[0035] Figure 5 It is the change trend of the speed surge judgment value A0 calculated within 2 seconds when the stall phenomenon occurs;

[0036] Figure 6 It is the change trend of the speed surge judgment value A0 calculated within 2 seconds when surge occurs;

[0037] Figure 7 It is the change trend of the pressure surge judgment value B0 calculated within 2 seconds when the active emergency stop occurs;

[0038] Figure 8 It is the change trend of the pressure surge judgment value B0 calculated within 2 seconds when the stall phenomenon occurs;

[0039] Fig. 9 It is the change trend of the pressure surge judgment value B0 calculated within 2 seconds when surge occurs;

[0040] Fig.10 It is the change trend of the temperature surge judgment value C0 calculated within 2 seconds when the active emergency stop occurs;

[0041] Fig.11 It is the change trend of the temperature surge judgment value C0 calculated within 2 seconds when the stall phenomenon occurs;

[0042] Fig.12 It is the change trend of the temperature surge judgment value C0 calculated within 2 seconds when surge occurs;

[0043] Fig.13 It is a schematic block diagram of the structure of a diagnostic system according to an embodiment.

[0044] Reference numerals:

[0045] 1: Fan; 2: Boost stage, support plate and transition section flow passage; 3: High-pressure compressor; 4: Combustion chamber; 5: Turbine; 25: Compressor inlet section; 31: Compressor outlet section; 44: Turbine outlet section. DETAILED DESCRIPTION

[0046] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0047] At the same time, the present application uses specific words to describe the embodiments of the present application, such as "one embodiment", "an embodiment", and / or "some embodiments" to refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" mentioned twice or more in different locations in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0048] It should be noted that in the following embodiments, the gas turbine engine described in the following embodiments takes the turbofan engine of an aircraft as an example, but is not limited to this. For example, ships and their gas turbine engines can also be applied to the surge diagnosis method described in the following embodiments.

[0049] refer to Figure 1 As shown, the gas turbine engine is provided with a first sensor at the compressor outlet section 31, which can sense the pressure of the compressor outlet section, a second sensor is provided at the turbine outlet section 44, which can sense the temperature of the turbine outlet section, and the gas turbine engine has a third sensor, which can sense the speed of the gas turbine engine. The speed of the engine here is the speed of the high-pressure compressor.

[0050] Although the above method is illustrated and described as a series of actions for simplicity of explanation, it should be understood and appreciated that these steps are not limited by the order of the actions, because according to one or more embodiments, some actions may occur in a different order and / or concurrently with other actions from those illustrated and described herein or not illustrated and described herein but understandable to those skilled in the art.

[0051] refer to Figure 3 As shown, the gas turbine engine surge diagnosis method includes:

[0052] S1. Obtain the speed data N2 measured by the third sensor, and obtain a real-time speed surge judgment value A0 according to the measured speed data. If the speed surge judgment value A0 exceeds the speed surge judgment threshold A corresponding to the speed, the diagnosis result is output as surge;

[0053] S2. Obtain the pressure data P31 of the compressor outlet cross section measured by the first sensor, and obtain a real-time pressure surge judgment value B0 according to the measured pressure data. If the pressure surge judgment value B0 exceeds the pressure surge judgment threshold B corresponding to the pressure, the diagnosis result is output as surge;

[0054] S3. Obtain the temperature data T44 of the turbine outlet section measured by the second sensor, and obtain a real-time temperature surge judgment value C0 according to the measured temperature data. If the temperature surge judgment value C0 exceeds the temperature surge judgment threshold C corresponding to the temperature, the diagnosis result is output as surge;

[0055] When the output diagnosis structure of any one of S1, S2, and S3 is surge (ie, S1, S2, and S3 are OR operations), the gas turbine engine is diagnosed as surge, and then other subsequent operations are performed.

[0056] In some embodiments, in S1, the real-time speed surge judgment value A0 is obtained according to:

[0057] A0=fN2dot(k)=a*fN2dot(k-1)+b*N2dot(k-1)

[0058] N2dot(k-1)=(N2(K)-N2(K-1)) / T

[0059] Wherein, k is the data number recorded at the current moment, N2(K) and N2(K-1) are the engine physical speed signals collected by the third sensor at the current moment and the previous moment respectively, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, where 0.5≤a≤1, 0≤b≤0.5. Here, a=0.5 and b=0.5 are taken as an example, but the present invention is not limited thereto.

[0060] Preferably, in some embodiments, the speed surge judgment threshold value A ranges from -0.02 to -0.005. This has the beneficial effect of accurately distinguishing surge from stall and active emergency stop. Figure 6 and Figure 4 , Figure 5 As shown, compared to Figure 4 The emergency stop phenomenon shown in the figure Figure 5 The stall phenomenon shown, Figure 6In the surge phenomenon shown, the speed surge judgment value A0 is -0.02 to -0.005, and the corresponding Figure 4 , Figure 5 The values ​​are all greater than -0.005, that is, the absolute value is less than 0.005. Therefore, surge, stall and active emergency stop can be distinguished more accurately, further improving the accuracy of surge diagnosis results.

[0061] In some embodiments, at S2, the real-time pressure surge judgment value B0 is obtained according to:

[0062] B0=fP31dot(k)=a*fP31dot(k-1)+b*P31dot(k-1)

[0063] P31dot(k-1)=(P31(K)-P31(K-1)) / T

[0064] Among them, k is the data number recorded at the current moment, P31(K) and P31(K-1) are the compressor outlet section pressures collected by the sensor at the current moment and the previous moment respectively, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, 0.5≤a≤1, 0≤b≤0.5. Here, a=0.5, b=0.5 is taken as an example, but it is not limited to this.

[0065] Preferably, in some embodiments, the pressure surge judgment threshold B ranges from -3.5 to -1. This has the beneficial effect of accurately distinguishing surge from stall and active emergency stop. Fig. 9 and Figure 7 , Figure 8 As shown, compared to Figure 7 The emergency stop phenomenon shown in the figure Figure 8 The stall phenomenon shown, Fig. 9 In the surge phenomenon shown, the pressure surge judgment value B0 is -3.5 to -1, and the corresponding Figure 7 , Figure 8 The values ​​are all above -0.5, that is, the absolute value is less than 0.5, so surge can be distinguished from stall and active emergency stop more accurately, further improving the accuracy of surge diagnosis results.

[0066] In some embodiments, at S3, the real-time temperature surge judgment value C0 is obtained according to:

[0067] C0=fT44dot(k)=a*fT44dot(k-1)+b*T44dot(k-1)

[0068] T44dot(k-1)=(T44(K)-T44(K-1)) / T

[0069] Among them, k is the data number recorded at the current moment, T44(K) and T44(K-1) are the turbine outlet section temperatures collected by the sensor at the current moment and the previous moment respectively, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, 0.5≤a≤1, 0≤b≤0.5. Here, a=0.5, b=0.5 is taken as an example, but it is not limited to this.

[0070] Preferably, in some embodiments, the temperature surge judgment threshold C ranges from 0.1 to 0.2, which has the beneficial effect of accurately distinguishing surge from stall and active emergency stop. Fig.12 and Fig.10 , Fig.11 As shown, compared to Fig.10 The emergency stop phenomenon shown in the figure Fig.11 The stall phenomenon shown, Fig.12 In the surge phenomenon shown in FIG. 1 , the temperature surge judgment value C0 is about -0.2 to 0.1, and the absolute value can be taken, that is, the temperature surge judgment threshold C is 0.1 to 0.2, and in Fig.10 The emergency stop phenomenon shown in the figure Fig.11 In the stall phenomenon shown, the temperature surge judgment value C0 is basically a straight line of 0, so surge can be distinguished from stall and active emergency stop more accurately, further improving the accuracy of surge diagnosis results.

[0071] According to another aspect of the present invention, a computer readable medium is also provided. The computer readable medium provided by the present disclosure has computer instructions thereon. When the computer instructions are executed by a processor, the program can be executed by the processor to implement the steps executed by the program in the gas turbine engine surge diagnosis method described in the above embodiment.

[0072] refer to Fig.13 As shown, in some embodiments, the diagnostic system 200 includes: a memory 201 for storing instructions executable by a processor; a processor 202 for executing the instructions to implement the steps performed by the program in the surge diagnostic method for the gas turbine engine as described in the above embodiments.

[0073] In addition, the diagnostic system 200 may also include a display module 203 for displaying the diagnostic results obtained by the processor 202, so that the test operator of the gas turbine engine can timely know whether surge operation occurs and the fault time of surge, or provide the aircraft operator with information on whether surge occurs, so as to help him pay attention to the alarm information of engine surge in time. The display module 203 can have a variety of forms, for example, in an aircraft, the display module 203 can be a dashboard or a display screen, or even a head-up display (HUD) of a pilot's helmet, and on the ground, the display module 203 can be a computer screen, a mobile screen, etc. of the test operator.

[0074] It can be understood that the processor 202 in the previous embodiment, such as a system on a chip (SOC), a microcontroller, a microprocessor (such as a single-chip microcomputer), a reduced instruction set computer (RISC), an application-specific integrated circuit (ASIC), an application-specific instruction integrated processor (ASIP), a central processing unit (CPU), a graphics processing unit (GPU), a physical processing unit (PPU), a microcontroller unit, a digital signal processor (DSP), a field programmable gate array (FPGA), an advanced RISC machine (ARM), a programmable logic device (PLD), any circuit or processor capable of performing one or more functions, etc., is a combination of one or more. For example, in an aircraft, the processor 202 can be integrated into a full authority digital engine control (FADEC) to further improve the integration of the diagnostic system.

[0075] In summary, the beneficial effects of the gas turbine engine, surge diagnosis method, diagnostic system and computer-readable medium introduced in the above embodiments include but are not limited to, by using the rotational speed, compressor outlet cross-sectional pressure and turbine outlet temperature as diagnostic conditions for diagnosis, any diagnostic condition outputting a surge diagnosis result can diagnose the engine as surge, which is more robust than the existing solutions introduced above.

[0076] The steps of the method described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software module may reside in a RAM memory, a flash memory, a ROM memory, an EPROM memory, an EEPROM memory, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read and write information from / to the storage medium. In an alternative, a storage medium may be integrated into a processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and the storage medium may reside in a user terminal as discrete components.

[0077] In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented as a computer program product in software, each function may be stored on or transmitted by a computer-readable medium as one or more instructions or codes. Computer-readable media include both computer storage media and communication media, including any medium that facilitates the transfer of a computer program from one place to another. Storage media may be any available medium that can be accessed by a computer. As an example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, disk storage or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of an instruction or data structure and can be accessed by a computer. Any connection is also properly referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwaves, the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwaves are included in the definition of the medium. Disk and disc as used herein include compact disc (CD), laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu-ray disc, wherein disk often reproduces data magnetically, while disc reproduces data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.

[0078] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A method for diagnosing surge of a gas turbine engine, characterized in that: The gas turbine engine is provided with a first sensor at a compressor outlet section (31) capable of sensing the pressure of the compressor outlet section, a second sensor is provided at a turbine outlet section (44) capable of sensing the temperature of the turbine outlet section, and the gas turbine engine has a third sensor capable of sensing the rotation speed of the gas turbine engine; wherein the diagnostic method comprises: S1. Obtain the speed data N2 measured by the third sensor, and obtain a real-time speed surge judgment value A0 according to the measured speed data. If the speed surge judgment value A0 exceeds the speed surge judgment threshold A corresponding to the speed, the diagnosis result is output as surge; S2. Obtain the pressure data P31 of the compressor outlet cross section measured by the first sensor, and obtain a real-time pressure surge judgment value B0 according to the measured pressure data. If the pressure surge judgment value B0 exceeds the pressure surge judgment threshold B corresponding to the pressure, the diagnosis result is output as surge; S3. Obtain the temperature data T44 of the turbine outlet section measured by the second sensor, and obtain a real-time temperature surge judgment value C0 according to the measured temperature data. If the temperature surge judgment value C0 exceeds the temperature surge judgment threshold C corresponding to the temperature, the diagnosis result is output as surge; When the output diagnosis structure of any one of S1, S2, and S3 is surge, the gas turbine engine is diagnosed as surge.

2. The diagnostic method according to claim 1, characterized in that In S1, the real-time speed surge judgment value A0 is obtained according to the following: A0=fN2dot(k)=a*fN2dot(k-1)+b*N2dot(k-1) N2dot(k-1)=(N2(K)-N2(K-1)) / T Wherein, k is the data number recorded at the current moment, N2(K) and N2(K-1) are the engine physical speed signals collected by the third sensor at the current moment and the previous moment respectively, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, where 0.5≤a≤1, 0≤b≤0.

5.

3. The diagnostic method according to claim 2, characterized in that The speed surge judgment threshold value A ranges from -0.02 to -0.

005.

4. The diagnostic method according to claim 1, characterized in that In S2, the real-time pressure surge judgment value B0 is obtained according to the following: B0=fP31dot(k)=a*fP31dot(k-1)+b*P31dot(k-1) P31dot(k-1)=(P31(K)-P31(K-1)) / T Among them, k is the data number recorded at the current moment, P31(K) and P31(K-1) are the compressor outlet section pressures collected by the sensor at the current moment and the previous moment respectively, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, 0.5≤a≤1, 0≤b≤0.

5.

5. The diagnostic method according to claim 4, characterized in that The pressure surge judgment threshold value B ranges from -3.5 to -1.

6. The diagnostic method according to claim 1, characterized in that In S3, the real-time temperature surge judgment value C0 is obtained according to the following: C0=fT44dot(k)=a*fT44dot(k-1)+b*T44dot(k-1) T44dot(k-1)=(T44(K)-T44(K-1)) / T Wherein, k is the data number recorded at the current moment, T44(K) and T44(K-1) are the turbine outlet section temperatures collected by the sensor at the current moment and the previous moment respectively, T is the sampling time interval between the two, a and b are empirical parameters, and the relationship between the two is a+b=1, 0.5≤a≤1, 0≤b≤0.

5.

7. The diagnostic method according to claim 1, characterized in that The temperature surge judgment threshold C ranges from 0.1 to 0.

2.

8. A readable medium having a computer program thereon, characterized in that The program is executed by a processor to implement the steps of the diagnostic method according to any one of claims 1 to 7.

9. A gas turbine engine surge diagnosis system (200), characterized in that: The gas turbine engine is provided with a first sensor at a compressor outlet section (31) capable of sensing the pressure of the compressor outlet section, a second sensor is provided at a turbine outlet section (44) capable of sensing the temperature of the turbine outlet section, and the gas turbine engine has a third sensor capable of sensing the rotation speed of the gas turbine engine; wherein the diagnostic system (200) comprises: A memory (201) for storing instructions executable by a processor; A processor (202) is used to execute the instructions to implement the diagnosis method according to any one of claims 1 to 7.

10. The diagnostic system (200) according to claim 9, characterized in that It also includes a display module (203) for displaying the diagnosis result obtained by the processor (202).

11. The diagnostic system (200) according to claim 9, characterized in that: The processor (202) of the diagnostic system (200) is integrated into a Full Authority Digital Engine Control (FADEC).

12. A gas turbine engine, characterized in that: Comprising a diagnostic system (200) as claimed in any one of claims 9 to 11.

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