An automatic diagnosis method, device and electronic equipment for rotor block dropping of an aeroengine

Abstract

The present application discloses an automatic diagnosis method, device and electronic equipment for rotor block dropping of an aeroengine. The method includes the steps of: S1, obtaining the measured operating parameters of the aeroengine during a test run, including the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, the gas generator rotor speed Ng, the power turbine rotor speed Np, the fundamental frequency vibration Fz-ng of the gas generator rotor, and the fundamental frequency vibration Fz-np of the power turbine rotor; S2, judging the position where rotor block dropping occurs in the aeroengine according to the corresponding trend changes that occur simultaneously when the current values of the respective operating parameters are compared with the average values at a previous set time. The present application has the advantages of fast fault discovery speed, relatively comprehensive coverage of the full operating state of the engine, easy implementation and good feasibility, so as to judge the block dropping fault in advance, timely reduce the engine state or stop the engine, and avoid further damage.

Description

Technical Field

[0001] The present application relates to the technical field of aero-engines, and in particular, to an automatic diagnosis method, device and electronic equipment for rotor block loss of an aero-engine. Background Art

[0002] An aero-engine operates at a high rotational speed, and the high-speed blades contain great energy. When there is a fault and a block is lost from a blade, it may cause minor and serious consequences:

[0003] 1) Serious consequences. The blade fragments shatter many other blades around and downstream. This type of block loss will be accompanied by a long-term abnormal increase in vibration, rotor jamming or overspeeding, damage to the engine function, inability to generate a large or continuous power, endangering the safety of the test run. For such a fault, the operator can only make an emergency stop.

[0004] 2) Minor consequences. The blade fragments injure individual blades around and downstream, and then fly out of the engine along the main flow path. This type of block loss will be accompanied by a short-term sudden increase in vibration and a performance decline, but the engine function is normal and it can continue to work for a short time. It is very difficult for the operator to find such a minor block loss phenomenon by monitoring parameters and almost no targeted operation will be carried out. However, this type of fault is often the most overlooked. If it continues to be used, it is very likely to cause greater damage to the engine and increase the subsequent test run risk. Therefore, it is necessary to detect and remind the operator in time.

[0005] Currently, it is only possible to determine whether the engine is abnormal by abnormal vibration, but there are many faults that cause large vibration and it is impossible to accurately locate the block loss of the blade. Therefore, there is a lack of a logic and countermeasure for automatically judging the rotor block loss during the test run, so as to judge the block loss fault in advance, reduce the engine state or stop in time, and avoid further damage. Summary of the Invention

[0006] One aspect of the present application provides an automatic diagnosis method for rotor block loss of an aero-engine to solve the technical problem in the prior art that there is no automatic judgment of rotor block loss during the test run and it is impossible to discover and avoid risks in advance.

[0007] The technical solution adopted by the present application is as follows:

[0008] An automatic diagnosis method for rotor block loss of an aero-engine includes the following steps:

[0009] S1. Obtain the measured operating parameters of the aero-engine during the test run, including the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, the gas generator rotor speed Ng, the power turbine rotor speed Np, the fundamental frequency vibration Fz-ng of the gas generator rotor, and the fundamental frequency vibration Fz-np of the power turbine rotor;

[0010] S2. Determine the position where a rotor block drops in the aero-engine based on the corresponding trend changes that occur simultaneously in the current values of each operating parameter compared to the average value over the previous set time.

[0011] Further, step S2 specifically includes the steps:

[0012] S201. During the starting phase, when the following trend changes occur simultaneously in the current values of each operating parameter compared to the average value over the previous set time, it is determined that a compressor blade has dropped:

[0013] The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration of the gas generator rotor Fz-ng increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration of the power turbine rotor Fz-np increases by 50% or is greater than 80% of the Fz-np limit value.

[0014] Further, step S2 specifically includes the steps:

[0015] S211. During the steady state phase, when the following trend changes occur simultaneously in the current values of each operating parameter compared to the average value over the previous set time, it is determined that a gas turbine blade has dropped:

[0016] The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 decreases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration of the gas generator rotor Fz-ng increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration of the power turbine rotor Fz-np increases by 50% or is greater than 80% of the Fz-np limit value.

[0017] Further, step S2 specifically includes the steps:

[0018] S221. During the load increase and decrease phase, when the following trend changes occur simultaneously in the current values of each operating parameter compared to the average value over the previous set time, it is determined that a power turbine blade has dropped:

[0019] The compressor outlet temperature T3 increases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 increases, the gas generator rotor speed Ng increases, the power turbine rotor speed Np increases, and the fundamental frequency vibration of the power turbine rotor Fz-np increases by 50% or is greater than 80% of the Fz-np limit value.

[0020] Further, in step S2, the average value over the previous set time specifically refers to: the corresponding trend changes that occur simultaneously compared to the average value over the previous 3 to 5 seconds.

[0021] On the other hand, the present application also provides an automatic diagnosis device for rotor block dropping of an aeroengine, including:

[0022] An operating parameter acquisition module, configured to acquire the measured operating parameters of the aeroengine during a test run, including the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, the gas generator rotor speed Ng, the power turbine rotor speed Np, the fundamental frequency vibration Fz-ng of the gas generator rotor, and the fundamental frequency vibration Fz-np of the power turbine rotor;

[0023] A rotor block dropping position judgment module, configured to judge the position where rotor block dropping occurs in the aeroengine according to the corresponding trend changes that occur simultaneously when the current values of the respective operating parameters are compared with the average values of the previous set time.

[0024] Further, the rotor block dropping position judgment module includes:

[0025] A first rotor block dropping position judgment sub-module, configured to, during the starting stage, when the following trend changes occur simultaneously when the current values of the respective operating parameters are compared with the average values of the previous set time, determine that a compressor blade has dropped:

[0026] The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration Fz-ng of the gas generator rotor increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0027] Further, the rotor block dropping position judgment module includes:

[0028] A second rotor block dropping position judgment sub-module, configured to, during the steady state stage, when the following trend changes occur simultaneously when the current values of the respective operating parameters are compared with the average values of the previous set time, determine that a gas turbine blade has dropped:

[0029] The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 decreases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration Fz-ng of the gas generator rotor increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0030] Further, the rotor block dropping position judgment module includes:

[0031] The third rotor block-drop position judgment sub-module is used in the load addition and subtraction stage. When the current values of each operating parameter change simultaneously in the following trends compared with the average value in the previous set time, it is determined that there is a block-drop in the power turbine blade:

[0032] The compressor outlet temperature T3 rises, the compressor outlet pressure P3 rises, the power turbine inlet temperature T45 rises, the power turbine inlet pressure P45 rises, the gas generator rotor speed Ng rises, the power turbine rotor speed Np rises, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0033] On the other hand, the present application also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the steps of the automatic diagnosis method for the rotor block-drop of the aero-engine are implemented.

[0034] On the other hand, the present application also provides a storage medium. The storage medium includes a stored program. When the program runs, it controls the device where the storage medium is located to execute the steps of the automatic diagnosis method for the rotor block-drop of the aero-engine.

[0035] Compared with the prior art, the present application has the following beneficial effects:

[0036] The present application provides an automatic diagnosis method for the rotor block-drop of an aero-engine. This method combines different combinations such as the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, vibration parameters, and the comparison method of the current value of the measured parameter with the previous average value, etc. Different judgment logics are formulated for different rotors to judge the rotor block-drop position, so as to discover and avoid risks in advance. This application is applicable to scenarios such as engine ground test stands and in-flight test flights. It has the advantages of fast fault discovery speed, relatively comprehensive coverage of the full working state of the engine, easy implementation, and good feasibility, so as to judge the block-drop fault in advance, timely reduce the engine state or stop the engine, and avoid further damage.

[0037] In addition to the purposes, features, and advantages described above, the present application has other purposes, features, and advantages. The following will refer to the drawings for a further detailed description of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The schematic embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation to the present application. In the drawings:

[0039] Figure 1 is a schematic flow chart of an automatic diagnosis method for the rotor block-drop of an aero-engine in a preferred embodiment of the present application;

[0040] Figure 2 It is a schematic diagram of the engine structure and the distribution of measured parameters in the mainstream path;

[0041] Figure 3 It is a schematic diagram of the modules of an automatic diagnosis device for rotor block dropping of an aero-engine in a preferred embodiment of the present application;

[0042] Figure 4 It is a schematic block diagram of the entity of an electronic device in a preferred embodiment of the present application;

[0043] Figure 5 It is a schematic internal structure diagram of a computer device in a preferred embodiment of the present application.

[0044] In the figure: 1. Engine inlet; 2. Compressor inlet; 3. Compressor outlet; 4. Gas turbine inlet; 45. Power turbine inlet; 5. Power turbine outlet. Specific implementation manners

[0045] The following will describe the embodiments of the present application in detail with reference to the accompanying drawings. However, the present application can be implemented in many different ways defined and covered by the following.

[0046] As Figure 1 shown, a preferred embodiment of the present application provides an automatic diagnosis method for rotor block dropping of an aero-engine, including the following steps:

[0047] S1. Obtain the measured operating parameters of the aero-engine during the test run, including the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, the gas generator rotor speed Ng, the power turbine rotor speed Np, the fundamental frequency vibration Fz-ng of the gas generator rotor, and the fundamental frequency vibration Fz-np of the power turbine rotor;

[0048] S2. Judge the position where rotor block dropping occurs in the aero-engine according to the corresponding trend changes that occur simultaneously when the current values of the respective operating parameters are compared with the average values at the previous set time.

[0049] To judge whether the aero-engine has a block dropped, it is necessary to monitor in real time the measured operating parameters of the aero-engine during the test run. The main measurement parameters, symbols, and the typical sectional views and cross-sections of the aero-engine are as Figure 2 shown, including the engine inlet 1, the compressor inlet 2, the compressor outlet 3, the gas turbine inlet 4, the power turbine inlet 45, and the power turbine outlet 6. In order to automatically judge the rotor block dropping, it is necessary to measure the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, etc.

[0050] This embodiment provides an automatic diagnosis method for rotor block loss of an aeroengine. This method combines different combinations of the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, vibration parameters, etc., and the comparison method of the current values of the measured parameters with the previous average values, etc. Different judgment logics are formulated for different rotors to judge the position of rotor block loss, so as to discover and avoid risks in advance. This application is applicable to scenarios such as engine ground test stands and in-flight test flights. It has the advantages of fast fault discovery speed, relatively comprehensive coverage of the full operating state of the engine, easy implementation, and good feasibility, so as to judge the block loss fault in advance, timely reduce the engine state or stop the engine, and avoid further damage.

[0051] Preferably, step S2 specifically includes the steps:

[0052] S201. During the starting stage, when the current values of each operating parameter change simultaneously in the following trends compared with the average values in the previous 3 seconds, it is determined that the compressor blades have block loss:

[0053] The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration Fz-ng of the gas generator rotor increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0054] When there is block loss of the compressor blades, it will cause a decrease in the compressor efficiency. The fragments may damage other compressor blades and turbine blades, and the vibration value increases. Therefore, in this embodiment, when the current values of the measured operating parameters change simultaneously in the above trends compared with the average values in the previous 3 seconds, it can be accurately determined that there is block loss of the compressor blades.

[0055] Preferably, step S2 specifically includes the steps:

[0056] S211. During the steady state stage, when the current values of each operating parameter change simultaneously in the following trends compared with the average values in the previous 3 seconds, it is determined that the gas turbine blades have block loss:

[0057] The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 decreases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration Fz-ng of the gas generator rotor increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0058] When a piece breaks off from a gas turbine blade, it will cause a reduction in the efficiency of the gas turbine. The broken pieces may damage other blades of the gas turbine and the power turbine blades, and the vibration value will increase. Therefore, in this embodiment, when the current values of the measured operating parameters change simultaneously in the above trends compared with the average value in the previous 3 seconds, it can be accurately determined that a piece has broken off from the gas turbine blade.

[0059] Preferably, step S2 specifically includes the steps of:

[0060] S221. During the loading and unloading stage, when the current values of each operating parameter change simultaneously in the following trends compared with the average value in the previous set time, it is determined that a piece has broken off from the power turbine blade:

[0061] The compressor outlet temperature T3 rises, the compressor outlet pressure P3 rises, the power turbine inlet temperature T45 rises, the power turbine inlet pressure P45 rises, the gas generator rotor speed Ng rises, the power turbine rotor speed Np rises, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0062] When a piece breaks off from the power turbine blade, it will cause a reduction in the efficiency of the power turbine. The broken pieces may damage the power turbine blades, and the vibration value will increase. Therefore, in this embodiment, when the current values of the measured operating parameters change simultaneously in the above trends compared with the average value in the previous 3 seconds, it can be accurately determined that a piece has broken off from the power turbine blade.

[0063] As Figure 3 shown, another preferred embodiment of the present application further provides an automatic diagnosis device for rotor block dropping of an aeroengine, including:

[0064] An operating parameter acquisition module, configured to acquire the measured operating parameters of the aeroengine during the test run, including the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, the gas generator rotor speed Ng, the power turbine rotor speed Np, the fundamental frequency vibration Fz-ng of the gas generator rotor, and the fundamental frequency vibration Fz-np of the power turbine rotor;

[0065] A rotor block dropping position judgment module, configured to judge the position where the rotor block drops in the aeroengine according to the corresponding trend changes of the current values of each operating parameter compared with the average value in the previous set time.

[0066] Preferably, the rotor block dropping position judgment module includes:

[0067] A first rotor block dropping position judgment sub-module, configured to, during the starting stage, when the current values of each operating parameter change simultaneously in the following trends compared with the average value in the previous set time, determine that a piece has broken off from the compressor blade:

[0068] The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration Fz-ng of the gas generator rotor increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0069] Preferably, the rotor block-drop position judgment module includes:

[0070] A second rotor block-drop position judgment sub-module, which is used in the steady state stage. When the current values of each operating parameter change simultaneously in the following trends compared with the average value of the previous set time, it is determined that a gas turbine blade has dropped:

[0071] The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 decreases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration Fz-ng of the gas generator rotor increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0072] Preferably, the rotor block-drop position judgment module includes:

[0073] A third rotor block-drop position judgment sub-module, which is used in the loading and unloading stage. When the current values of each operating parameter change simultaneously in the following trends compared with the average value of the previous set time, it is determined that a power turbine blade has dropped:

[0074] The compressor outlet temperature T3 increases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 increases, the gas generator rotor speed Ng increases, the power turbine rotor speed Np increases, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

[0075] As Figure 4 shown, another preferred embodiment of the present application further provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the steps of the automatic diagnosis method for the rotor block-drop of an aeroengine in the above embodiment are implemented.

[0076] As Figure 5 shown, another preferred embodiment of the present application further provides a computer device. This computer device can be a terminal or a living body detection server, and its internal structure diagram can be as Figure 5As shown in the figure. The computer device includes a processor, a memory, and a network interface connected by a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with other external computer devices through a network connection. When the computer program is executed by the processor, it realizes the steps of the above-mentioned automatic diagnosis method for rotor block dropping of an aeroengine.

[0077] Those skilled in the art can understand that Figure 5 the structure shown in the figure is only a block diagram of some structures related to the solution of this application, and does not constitute a limitation on the computer device to which the solution of this application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements.

[0078] A preferred embodiment of this application also provides a storage medium. The storage medium includes a stored program. When the program runs, it controls the device where the storage medium is located to execute the steps of the automatic diagnosis method for rotor block dropping of an aeroengine in the above-mentioned embodiment.

[0079] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. And although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0080] If the functions described in the method of this embodiment are implemented in the form of software function units and sold or used as independent products, they can be stored in one or more computer-readable storage media. Based on such an understanding, the part that makes a contribution to the prior art or the part of this technical solution in the embodiments of this application can be embodied in the form of a software product. The software product is stored in a storage medium and includes several instructions to enable a computing device (which can be a personal computer, a server, a mobile computing device, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. And the foregoing storage media include: USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks, or optical discs and other various media that can store program codes.

[0081] Those skilled in the art should understand that the embodiments of the present application can be provided as a method, a system, or a computer program product. Therefore, the present application can take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that contain computer-usable program code. The solutions in the embodiments of the present application can be implemented in various computer languages. For example, object-oriented programming languages such as Java and interpreted scripting languages such as JavaScript, etc.

[0082] The present application is described with reference to the flowcharts and / or block diagrams of methods, apparatuses (systems), and computer program products according to the embodiments of the present application. It should be understood that each flow and / or block in the flowchart and / or block diagram, and the combination of flows and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing devices generate means for implementing the functions specified in Figure 1 one flow or multiple flows and / or blocks Figure 1 one block or multiple blocks.

[0083] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer-readable memory generate a manufactured article including instruction means, and the instruction means implements the functions specified in Figure 1 one flow or multiple flows and / or blocks Figure 1 one block or multiple blocks.

[0084] These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process, and thus the instructions executed on the computer or other programmable device provide steps for implementing the functions specified in Figure 1 one flow or multiple flows and / or blocks Figure 1 one block or multiple blocks.

[0085] Where the present application is not described in detail, it is common knowledge to those skilled in the art. Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application and not to limit them. Although the present application has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present application can be modified or equivalently replaced without departing from the purpose and scope of the technical solutions of the present application, and they should all be covered by the scope of the claims of the present application.

Claims

1. An automatic diagnosis method for rotor block shedding of an aeroengine, characterized in that, It includes the following steps: S1. Obtain the measured operating parameters of the aero-engine during the test run, including the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, the gas generator rotor speed Ng, the power turbine rotor speed Np, the fundamental frequency vibration Fz-ng of the gas generator rotor, and the fundamental frequency vibration Fz-np of the power turbine rotor; S2. Judge the position where rotor block shedding occurs in the aero-engine according to the corresponding trend changes that occur simultaneously when the current values of each operating parameter are compared with the average value at the previous set time. Step S2 specifically includes the steps: S201. During the starting stage, when the following trend changes occur simultaneously when the current values of each operating parameter are compared with the average value at the previous set time, it is determined that the compressor blade has block shedding: The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration Fz-ng of the gas generator rotor increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value; S211. During the steady state stage, when the following trend changes occur simultaneously when the current values of each operating parameter are compared with the average value at the previous set time, it is determined that the gas turbine blade has block shedding: The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 decreases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration Fz-ng of the gas generator rotor increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value; S221. During the load increase and decrease stage, when the following trend changes occur simultaneously when the current values of each operating parameter are compared with the average value at the previous set time, it is determined that the power turbine blade has block shedding: The compressor outlet temperature T3 increases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 increases, the gas generator rotor speed Ng increases, the power turbine rotor speed Np increases, and the fundamental frequency vibration Fz-np of the power turbine rotor increases by 50% or is greater than 80% of the Fz-np limit value.

2. The automatic diagnosis method for the rotor block dropping of an aeroengine according to claim 1, wherein In step S2, the average value compared with the previous set time is specifically: the corresponding trend changes that occur simultaneously when compared with the average value in the previous 3 to 5 seconds.

3. An automatic diagnosis device for rotor block dropping of an aero-engine, characterized in that, It includes: An operating parameter acquisition module, which is used to obtain the measured operating parameters of the aero-engine during the test run, including the compressor outlet temperature T3 and pressure P3, the power turbine inlet temperature T45 and pressure P45, the gas generator rotor speed Ng, the power turbine rotor speed Np, the fundamental frequency vibration Fz-ng of the gas generator rotor, and the fundamental frequency vibration Fz-np of the power turbine rotor; A rotor block shedding position judgment module, which is used to judge the position where rotor block shedding occurs in the aero-engine according to the corresponding trend changes that occur simultaneously when the current values of each operating parameter are compared with the average value at the previous set time; The rotor block-drop position judgment module includes: The first rotor block-drop position judgment sub-module, which is used in the starting stage. When the current values of each operating parameter change simultaneously in the following trends compared with the average value in the previous set time, it is determined that there is a block-drop of the compressor blade: The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration of the gas generator rotor Fz-ng increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration of the power turbine rotor Fz-np increases by 50% or is greater than 80% of the Fz-np limit value; The second rotor block-drop position judgment sub-module, which is used in the steady state stage. When the current values of each operating parameter change simultaneously in the following trends compared with the average value in the previous set time, it is determined that there is a block-drop of the gas turbine blade: The compressor outlet temperature T3 decreases, the compressor outlet pressure P3 decreases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 decreases, the gas generator rotor speed Ng decreases, the fundamental frequency vibration of the gas generator rotor Fz-ng increases by 50% or is greater than 80% of the Fz-ng limit value, and the fundamental frequency vibration of the power turbine rotor Fz-np increases by 50% or is greater than 80% of the Fz-np limit value; The third rotor block-drop position judgment sub-module, which is used in the loading and unloading stage. When the current values of each operating parameter change simultaneously in the following trends compared with the average value in the previous set time, it is determined that there is a block-drop of the power turbine blade: The compressor outlet temperature T3 increases, the compressor outlet pressure P3 increases, the power turbine inlet temperature T45 increases, the power turbine inlet pressure P45 increases, the gas generator rotor speed Ng increases, the power turbine rotor speed Np increases, and the fundamental frequency vibration of the power turbine rotor Fz-np increases by 50% or is greater than 80% of the Fz-np limit value.

4. An electronic device, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, When the processor executes the computer program, it realizes the steps of the automatic diagnosis method for the rotor block-drop of the aero-engine as described in any one of claims 1 to 2.

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