Gas turbine engine, diagnostic method of starting system, diagnostic system, and medium

Abstract

The invention relates to a gas turbine engine, a diagnostic method of a starting system, a diagnostic system, and a computer readable medium. The diagnosis method comprises the following steps: S1, judging the working state of the starting system; s2, if the judgment result in the step S1 is that the working state of the starting system is non-working, according to air inlet pressure data, sensed by the air pressure sensor, of the air turbine starter, environment pressure data are compared, and the relation between the difference value of the two data and a threshold value is obtained; if the judgment result of S1 is that the working state of the starting system is working, comparing environment pressure data according to the air inlet pressure data, sensed by the air pressure sensor, of the air turbine starter to obtain the relation between the difference value and the threshold value and the relation between the rotating speed of the engine and the threshold value.

Description

Technical Field

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

[0002] Before the gas turbine engine is ignited, the starting system needs to drive the engine rotor (usually the high-pressure compressor and high-pressure turbine) to rotate at high speed so that the combustion chamber can obtain sufficient high-pressure air. The starting system of the gas turbine engine mainly includes air turbine starter (ATS), starting air valve and air duct.

[0003] The starting system is one of the important systems of gas turbine engines. Its normal operation is directly related to whether the engine can start normally. At the same time, the starting system also plays an indispensable role when the engine encounters an emergency in the air. However, the starting system is also one of the systems with a higher failure rate in gas turbine engines, which greatly affects the flight punctuality and economic benefits of airlines.

[0004] Therefore, there is a need in the art for a diagnostic method for a starting system to achieve rapid and reliable diagnosis of the starting system, thereby ensuring timely starting of the gas turbine engine and corresponding flight punctuality and economic benefits for the airline. Summary of the invention

[0005] An object of the present invention is to provide a method for diagnosing a gas turbine engine starting system.

[0006] An object of the present invention is to provide a system for a gas turbine engine starting system.

[0007] An object of the present invention is to provide a gas turbine engine.

[0008] An object of the present invention is to provide a computer readable medium.

[0009] According to a first aspect of the present invention, a diagnostic method for a gas turbine engine starting system is provided, wherein the starting system comprises a starting air valve, a gas pressure sensor, an air turbine starter, a controller and an air duct, wherein air first passes through the starting air valve and then enters the air turbine starter through the air duct, wherein the starting air valve is electrically connected to the controller, and the gas pressure sensor is arranged on the starting air valve, or the air turbine starter, or the air duct for sensing the air flow through the starting air valve; wherein the diagnostic method comprises: S1. determining the working state of the starting system; S2. if the result of S1 is that the working state of the starting system is non-working, comparing the intake pressure data of the air turbine starter sensed by the gas pressure sensor with the ambient pressure data to obtain the relationship between the difference between the two and a threshold value; if the result of S1 is that the working state of the starting system is working, comparing the intake pressure data of the air turbine starter sensed by the gas pressure sensor with the ambient pressure data to obtain the relationship between the difference between the two and a threshold value, as well as the relationship between the engine speed and the threshold value.

[0010] In one or more embodiments, in S2, if the judgment result of S1 is that the working state of the starting system is non-working: if the difference between the intake pressure of the air turbine starter sensed by the gas pressure sensor and the ambient pressure is greater than the first threshold value, the intake pressure of the air turbine starter is greater than the ambient pressure, then the diagnosis result is that the starting air valve is poorly closed; if the difference between the intake pressure of the air turbine starter sensed by the gas pressure sensor and the ambient pressure is greater than the first threshold value, the intake pressure of the air turbine starter is less than the ambient pressure, then the diagnosis result is that the air turbine starter is not normally disengaged.

[0011] In one or more embodiments, in S2, if the judgment result of S1 is that the working state of the starting system is working: if the difference between the intake pressure of the air turbine starter sensed by the gas pressure sensor and the ambient pressure is less than the second threshold value, the diagnostic result is that the starting air valve is not opened normally; if the difference between the intake pressure of the air turbine starter sensed by the gas pressure sensor and the ambient pressure is greater than the second threshold value, and the engine speed is less than the third threshold value, the diagnostic result is an air turbine starter failure.

[0012] In one or more embodiments, the diagnostic method also includes: S3. If the diagnostic result of S2 is that the starting air valve and the air turbine starter are normal, the output torque of the air turbine starter is obtained according to the digital twin model of the air turbine starter and the intake pressure gauge of the air turbine starter sensed by the gas pressure sensor; S4. According to the digital twin model of the gas turbine engine, the resistance torque of the gas turbine engine starting is obtained, and the theoretical acceleration of the gas turbine engine starting is obtained by combining the output torque of the air turbine starter obtained in S3; and according to the speed obtained by the speed sensor of the gas turbine engine, the actual acceleration of the gas turbine engine starting is obtained; and the theoretical acceleration is compared with the actual acceleration to diagnose the attenuation of the air turbine starter.

[0013] 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.

[0014] According to a third aspect of the present invention, a diagnostic system for a gas turbine engine starting system comprises a starting air valve, a gas pressure sensor, an air turbine starter, a controller and an air duct, wherein air first passes through the starting air valve and then enters the air turbine starter through the air duct, wherein the starting air valve is electrically connected to the controller, and a gas pressure sensor is disposed on the starting air valve, or the air turbine starter, or the air duct for sensing the airflow through the starting air valve; 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 claimed in any one of claims 1 to 4.

[0015] In one or more embodiments, the diagnostic system further includes a display module for displaying the diagnostic result obtained by the processor.

[0016] In one or more embodiments, the memory also stores a parameter database of the air turbine starter and the gas turbine engine; the processor is also configured to establish a digital twin model of the air turbine starter and the gas turbine engine based on the parameter database.

[0017] In one or more embodiments, the controller of the starting system and the processor of the diagnostic system are integrated into a full authority digital engine controller.

[0018] A gas turbine engine according to a fourth aspect of the present invention comprises the diagnostic system and the starting system as described in the third aspect.

[0019] The beneficial effects of the present invention include, but are not limited to, using the air turbine starter intake pressure fed back by the gas pressure sensor for diagnosis, which can quickly and accurately locate the starting system fault, with high diagnostic efficiency; and facilitate troubleshooting of the starting system fault. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] 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:

[0021] Figure 1 It is a structural schematic diagram of a starting system corresponding to diagnosis in one embodiment of the present application.

[0022] Figure 2 It is a flowchart of a diagnostic method according to an embodiment of the present application.

[0023] Figure 3 It is a flowchart of a diagnostic method according to another embodiment of the present application.

[0024] Figure 4 It is a flowchart of a diagnostic method according to another embodiment of the present application.

[0025] Figure 5 It is a schematic block diagram of the structure of a diagnostic system according to an embodiment of the present application.

[0026] Reference numerals:

[0027] 100-Gas Turbine Engine Starting System

[0028] 1-Starting air valve

[0029] 2-Gas pressure sensor

[0030] 3-Air Turbine Starter

[0031] 4-Controller

[0032] 5- Air duct

[0033] 200-Gas Turbine Engine Starting System Diagnostic System

[0034] 201-Memory

[0035] 202-Processor

[0036] 203-Display module. DETAILED DESCRIPTION

[0037] 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.

[0038] 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.

[0039] It should be noted that in the following embodiments, the gas turbine engine described in the following embodiments takes an aircraft and its turbofan engine as an example, but is not limited to this. For example, ships and their gas turbine engines can also be applied to the starting control described in the following embodiments.

[0040] refer to Figure 1 As shown, the starting system 100 of the gas turbine engine includes a starting air valve 1 , a gas pressure sensor 2 , an air turbine starter 3 , a controller 4 and an air duct 5 .

[0041] When the gas turbine engine is started, the air supply from the aircraft auxiliary power unit (APU), ground air source or cross-bleed air first enters the starting air valve 1, and then enters the air turbine starter 3 through the air duct 5. The air turbine starter 3 converts the internal energy of the gas into mechanical energy to drive the high-pressure rotor of the gas turbine engine to rotate. For example, the high-pressure rotor can be driven to rotate through the accessory gearbox (Accessory Gearbox, AGB) of the gas turbine engine.

[0042] The starting air valve 1 is electrically connected to the controller 4, for example, it can be electrically connected by wire or wirelessly. The starting air valve 1 receives instructions from the electronic controller 4 to control the air supply of the air turbine starter 3. The starting air valve 1 can include components such as a solenoid valve, a control valve, a butterfly valve and an air flow channel, and a manual override device. The manual override device is directly connected to the disc plate rotating shaft of the starting air valve, and is used to manually control the opening of the disc plate and can lock the position.

[0043] like Figure 1As shown, the gas pressure sensor 2 uses a conduit to draw out the gas between the air turbine starter 3 and the starting air valve 1 and then measures the pressure. The gas pressure sensor 2 is integrated in the starting air valve 1, or the air turbine starter 3, or is set in the air conduit 5. The sensing object of the gas pressure sensor 2 can be the total pressure of the gas or the static pressure of the gas. Figure 1 As shown, the gas pressure sensor 2 adopts A\B dual-channel data transmission, which has good reliability.

[0044] Continue to refer Figure 1 As shown, the data transmission of the controller 4 can also be an A / B dual-channel structure. The controller 4 controls the actuation of the starting air valve 1 according to the engine status and the starting instruction, adjusts the air supply of the air turbine starter 3, and monitors the status and diagnoses faults of the starting system 100 at the same time.

[0045] refer to Figure 1 as well as Figure 2 In one or more embodiments, a gas turbine engine startup control method includes:

[0046] S1. Determine the working status of the starting system 100;

[0047] S2. If the result of S1 is that the working state of the starting system 100 is non-working, the intake pressure Pq data of the air turbine starter 3 sensed by the gas pressure sensor 2 is compared with the ambient pressure P0 data to obtain the relationship between the difference between the two and the threshold value;

[0048] If the judgment result of S1 is that the working state of the starting system 100 is working, the intake pressure Pq data of the air turbine starter 3 sensed by the gas pressure sensor 2 is compared with the relationship between the ambient pressure P0 data and the difference threshold between the two, as well as the relationship between the engine speed and the speed threshold.

[0049] The thresholds of the difference between the ambient pressure intake pressure Pq and the ambient pressure P0 corresponding to the non-operating state and the operating state described above are not necessarily the same. The ambient pressure P0 refers to the atmospheric pressure of the environment near the starting system 100. If the start is on the ground, the ambient pressure measured at the airport on the day can be directly introduced.

[0050] refer to Figure 2 As shown, in S2, if the result of S1 is that the working state of the starting system 100 is non-working:

[0051] If the difference between the intake pressure of the air turbine starter 3 sensed by the gas pressure sensor 2 and the ambient pressure is greater than the first threshold, the intake pressure of the air turbine starter 3 is greater than the ambient pressure, then the diagnosis result is that the starting air valve 1 is not closed properly, for example, it cannot be closed or is not closed tightly.

[0052] If the difference between the intake pressure of the air turbine starter 3 sensed by the gas pressure sensor 2 and the ambient pressure is greater than the first threshold, and the intake pressure of the air turbine starter 3 is lower than the ambient pressure, the diagnosis result is that the air turbine starter 3 is not normally disengaged.

[0053] The "normal disengagement" here means that the clutch device inside the air turbine starter 3 works to disengage the turbine end from the output shaft. After disengagement, the output shaft remains connected to the accessory gearbox, so this part of the starter is in turn driven by the high-pressure rotor, and by closing the starting air valve and removing the air source power, the disengaged turbine end part will stop rotating. If the starter cannot be disengaged normally, the accident of "starter shaft breakage" may occur.

[0054] Continue to refer Figure 2 As shown, in S2, if the result of S1 is that the working state of the starting system 100 is working:

[0055] If the difference between the intake pressure of the air turbine starter 3 sensed by the gas pressure sensor 2 and the ambient pressure is less than the second threshold value, the diagnosis result is that the starting air valve 1 is not opened normally;

[0056] If the difference between the intake pressure of the air turbine starter 3 sensed by the gas pressure sensor 2 and the ambient pressure is greater than the second threshold, and the engine speed is less than the third threshold, the diagnosis result is that the air turbine starter 3 is faulty.

[0057] Although the first threshold and the second threshold above are both thresholds of the difference between the intake pressure and the ambient pressure, since the corresponding states are the non-working state and the working state, respectively, the first threshold and the second threshold can be different, and the third threshold is the corresponding threshold of the engine speed.

[0058] The above-mentioned working state is working, which may include engine starting, cold running, passing through oil sealing and unsealing, etc. The oil sealing and unsealing here refer to the process in which the starter drives the engine to rotate and inject fuel into or expel fuel from the engine. The engine cold running refers to the process in which the starter drives the engine to rotate, but the engine is not fueled and ignited.

[0059] The beneficial effect of adopting the above embodiment is that by using the air turbine starter intake pressure fed back by the gas pressure sensor for diagnosis, the starting system fault can be quickly and accurately located with high diagnostic efficiency; and starting system fault troubleshooting is also convenient.

[0060] refer to Figure 4 As shown, in some embodiments, the diagnostic method further comprises:

[0061] S3. If the diagnostic result in S2 is that the starting air valve 1 and the air turbine starter 3 are normal, the output torque of the air turbine starter 3 is obtained according to the digital twin model of the air turbine starter 3 and the intake pressure gauge of the air turbine starter 3 sensed by the gas pressure sensor 2;

[0062] S4. According to the digital twin model of the gas turbine engine, the resistance torque of the gas turbine engine starting is obtained, and combined with the output torque of the air turbine starter 3 obtained in S3, the theoretical acceleration of the gas turbine engine starting is obtained; and according to the speed obtained by the speed sensor of the gas turbine engine, the actual acceleration of the gas turbine engine starting is obtained; the theoretical acceleration is compared with the actual acceleration to diagnose the attenuation of the air turbine starter 1.

[0063] The meaning of the digital twin model here is similar to that in the art, that is, the mapping of the air turbine starter 3 and the gas turbine engine in the virtual space. The method of constructing the digital twin model of the air turbine starter 3 and the gas turbine engine based on the parameter database can also adopt the conventional modeling method in the art, which will not be repeated here. Generally speaking, the parameters of the air turbine starter 3 and the gas turbine engine include structural parameters and performance parameters, such as the material, size, assembly relationship, fatigue life and other parameters of each component, the speed, torque, power and other parameters corresponding to the temperature and pressure, etc. Therefore, the digital twin model of the air turbine starter 3 and the gas turbine engine is generally essentially an equivalent of the structure and performance of the air turbine starter 3 and the gas turbine engine.

[0064] By comparing the theoretical acceleration with the actual acceleration, the threshold between the theoretical acceleration and the actual acceleration can be obtained according to different models of air turbine starters 3 through durability tests or simulation calculations. For example, for a certain model of air turbine starter 3, the threshold is 90%, that is, if the actual acceleration is less than 90% of the theoretical acceleration, then the diagnostic structure indicates that the performance of the air turbine starter 3 is severely degraded and it should be replaced, repaired and maintained in time to ensure the reliability of the starting process of the gas turbine engine.

[0065] 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.

[0066] According to another aspect of the present invention, a computer-readable medium is also provided.

[0067] 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 diagnostic method of the gas turbine engine starting system described in the above embodiment.

[0068] refer to Figure 5 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 diagnostic method of the gas turbine engine starting system as described in the above embodiments.

[0069] In addition, the memory 201 can also store a parameter database of the air turbine starter 3 and the gas turbine engine; the processor 202 is also configured to establish a digital twin model of the air turbine starter 3 and the gas turbine engine according to the parameter database to diagnose the attenuation of the air turbine starter 3.

[0070] 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 gas turbine engine monitoring and maintenance workers can timely know the operation status or fault location of the starting system 100, or provide the aircraft operator with the operation status of the starter to help him pay attention to the reliability of the starting system in time. The display module 203 can have a variety of forms of expression. 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 a maintenance person.

[0071] 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 the controller 4, and the two can also be integrated together into the full authority digital engine control (FADEC) to further improve the integration of the diagnostic system.

[0072] In summary, the beneficial effects of the gas turbine engine, the diagnostic method of the starting system, the diagnostic system and the computer-readable medium introduced in the above embodiments include but are not limited to the following: by using the air turbine starter intake pressure fed back by the gas pressure sensor for diagnosis, the starting system fault can be quickly and accurately located, the diagnostic efficiency is high, and the starting system fault is convenient to troubleshoot. The fast and reliable diagnosis of the starting system is achieved, and the timely starting of the gas turbine engine is ensured, as well as the corresponding flight punctuality rate and economic benefits of the airline.

[0073] 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.

[0074] 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.

[0075] 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 a gas turbine engine starting system (100), characterized in that: The starting system (100) comprises a starting air valve (1), a gas pressure sensor (2), an air turbine starter (3), a controller (4) and an air duct (5), wherein air first passes through the starting air valve (1) and then enters the air turbine starter (3) through the air duct (5), the starting air valve (1) is electrically connected to the controller (4), and the gas pressure sensor (2) is arranged on the starting air valve (1), or the air turbine starter (3), or the air duct (5) to sense the air flow passing through the starting air valve (1); wherein the diagnostic method comprises: S1. Determine the working state of the starting system (100); S2. If the result of S1 is that the working state of the starting system (100) is non-working, the relationship between the difference between the two and the threshold value is obtained by comparing the intake pressure data of the air turbine starter (3) sensed by the gas pressure sensor (2) with the ambient pressure data; If the result of S1 is that the working state of the starting system (100) is working, the relationship between the difference between the two and the threshold value, as well as the relationship between the engine speed and the threshold value, is obtained by comparing the intake pressure data of the air turbine starter (3) sensed by the gas pressure sensor (2) with the ambient pressure data.

2. The diagnostic method according to claim 1, characterized in that In S2, if the result of S1 is that the operating state of the starting system (100) is non-operating: If the difference between the intake pressure of the air turbine starter (3) sensed by the gas pressure sensor (2) and the ambient pressure is greater than a first threshold value, and the intake pressure of the air turbine starter (3) is greater than the ambient pressure, then the diagnosis result is that the starting air valve (1) is not closed properly; If the difference between the intake pressure of the air turbine starter (3) sensed by the gas pressure sensor (2) and the ambient pressure is greater than a first threshold value, and the intake pressure of the air turbine starter (3) is less than the ambient pressure, then the diagnosis result is that the air turbine starter (3) is not normally disengaged.

3. The diagnostic method according to claim 1, characterized in that In S2, if the result of S1 is that the operating state of the starting system (100) is working: If the difference between the intake pressure of the air turbine starter (3) sensed by the gas pressure sensor (2) and the ambient pressure is less than a second threshold value, the diagnosis result is that the starting air valve (1) is not opened normally; If the difference between the intake pressure of the air turbine starter (3) sensed by the gas pressure sensor (2) and the ambient pressure is greater than a second threshold, and the engine speed is less than a third threshold, the diagnosis result is that the air turbine starter (3) is faulty.

4. The diagnostic method according to claim 1, characterized in that The diagnostic method further comprises: S3. If the diagnosis result in S2 is that the starting air valve (1) and the air turbine starter (3) are both normal, the output torque of the air turbine starter (3) is obtained according to the digital twin model of the air turbine starter (3) and the intake pressure gauge of the air turbine starter (3) sensed by the gas pressure sensor (2); S4. Based on the digital twin model of the gas turbine engine, the resistance torque of the gas turbine engine starting is obtained, and combined with the output torque of the air turbine starter (3) obtained in S3, the theoretical acceleration of the gas turbine engine starting is obtained; and based on the rotation speed obtained by the rotation speed sensor of the gas turbine engine, the actual acceleration of the gas turbine engine starting is obtained; and the theoretical acceleration is compared with the actual acceleration to diagnose the attenuation of the air turbine starter (3).

5. 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 4.

6. A diagnostic system (200) for a gas turbine engine starting system (100), characterized in that: The starting system (100) comprises a starting air valve (1), a gas pressure sensor (2), an air turbine starter (3), a controller (4) and an air duct (5); air first passes through the starting air valve (1) and then enters the air turbine starter (3) through the air duct (5); the starting air valve (1) is electrically connected to the controller (4); the gas pressure sensor (2) is arranged on the starting air valve (1), or the air turbine starter (3), or the air duct (5) to sense the air flow passing through the starting air valve (1); 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 4.

7. The diagnostic system (200) according to claim 6, characterized in that It also includes a display module (203) for displaying the diagnosis result obtained by the processor (202).

8. The diagnostic system (200) according to claim 6, characterized in that: The memory (201) also stores a parameter database of the air turbine starter (3) and the gas turbine engine; The processor (202) is also configured to establish a digital twin model of the air turbine starter (3) and the gas turbine engine according to the parameter database.

9. The diagnostic system (200) according to claim 6, characterized in that: The controller (4) of the starting system (100) and the processor (202) of the diagnostic system (200) are integrated into a Full Authority Digital Engine Control (FADEC).

10. A gas turbine engine, characterized in that: It comprises a diagnostic system (200) as claimed in any one of claims 6 to 9 and a starting system (100).

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