Turbine service life prediction method, system and equipment and storage medium

Abstract

The invention discloses a turbine service life prediction method, system and device and a storage medium, and relates to the technical field of engines, and the method comprises the steps: fitting a stress spectrum according to the actual working rotating speed spectrum of a turbine and the relation between the rotating speed and the stress; calculating the total fatigue damage at the blade root of the turbine blade after the target working duration based on the stress spectrum; calculating the total creep damage at the blade root of the turbine blade after the target working duration based on the stress spectrum, the rotating speed spectrum of actual operation and the temperature spectrum; and predicting the comprehensive life of the turbine according to the total fatigue damage and the total creep damage. According to the method, the fatigue creep comprehensive life prediction method under the given actual road spectrum is constructed, the working life of the supercharger turbine can be predicted more accurately by comprehensively considering various influence factors of the turbine under the actual working condition, and therefore the performance and safety of the turbine are improved, and stable operation of the turbine is guaranteed.

Description

Technical Field

[0001] The present invention relates to the field of engines, and in particular to a turbine life prediction method, system, device and storage medium. Background Art

[0002] As an important component of the engine, the turbine works under high temperature, high pressure and high speed for a long time. The superposition of mechanical fatigue and thermal fatigue on the turbine blades leads to the generation of thermomechanical fatigue. In order to ensure that the turbine can work stably for a long time and prevent the failure caused by the damage of the turbine due to thermomechanical fatigue, it is necessary to predict the life of the turbine.

[0003] The existing technology usually conducts component testing directly on the whole machine, which is extremely risky and will result in high testing costs. Summary of the invention

[0004] The main purpose of the present invention is to provide a turbine life prediction method, system, device and storage medium. Compared with the prior art, the present invention constructs a fatigue creep comprehensive life prediction method under a given actual road spectrum, which can more accurately predict the working life of the supercharger turbine by comprehensively considering various influencing factors of the turbine under actual working conditions, thereby improving the performance and safety of the turbine and ensuring the stable operation of the turbine.

[0005] In order to achieve the above objectives, the embodiments of the present application provide the following technical solutions:

[0006] According to a first aspect of an embodiment of the present application, a turbine life prediction method is provided, the method comprising:

[0007] Fit the stress spectrum according to the actual working speed spectrum of the turbine and the relationship between speed and stress;

[0008] Calculating total fatigue damage at the blade root of the turbine blade after a target operating time based on the stress spectrum;

[0009] Calculating the total creep damage at the blade root of the turbine blade after the target operating time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum;

[0010] The comprehensive life of the turbine is predicted according to the total fatigue damage and the total creep damage.

[0011] Optionally, calculating the total fatigue damage at the blade root of the turbine blade after the target working time based on the stress spectrum includes:

[0012] The stress spectrum is analyzed by using a rain flow counting method to obtain the number of working cycles under several stress levels;

[0013] The total fatigue damage under one working cycle is calculated using the fatigue characteristic curve of the turbine blade material;

[0014] Based on the relationship between the number of working cycles and the engine working time, the total fatigue damage at the root of the turbine blade is calculated according to the total fatigue damage under the said one working cycle and the expected number of working cycles within the target working time.

[0015] Optionally, the calculating of the total fatigue damage under one working cycle by using the fatigue characteristic curve of the turbine blade material includes:

[0016] Determining fatigue life at several stress levels according to a fatigue characteristic curve of the turbine blade material; wherein the fatigue characteristic curve represents the relationship between stress level and fatigue life;

[0017] Based on the fatigue life and working cycle number under the several stress levels, the predicted life and fatigue damage under each stress level are calculated;

[0018] The fatigue damage under several stress levels is accumulated to calculate the total fatigue damage under one working cycle.

[0019] Optionally, the calculating the total creep damage at the blade root of the turbine blade after the target working time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum includes:

[0020] Derivation of the relationship between the endurance life and the temperature and stress based on the rotation speed spectrum and temperature spectrum of the actual operation;

[0021] Performing frequency statistics on the stress spectrum at the root of the turbine blade to obtain statistical results;

[0022] Performing probability fitting on the statistical results to obtain a stress probability density function at the root of the turbine blade;

[0023] The total creep damage at the blade root of the turbine blade within a target time period is calculated by using the stress probability density function, combining the maximum stress distribution at the blade root, the blade temperature, and the relationship between the material life, temperature and stress.

[0024] Optionally, the relationship between the material endurance life and temperature and stress is as follows:

[0025] Collect the speed data of the turbine in actual operation to form a speed spectrum;

[0026] Collect temperature data of turbine inlet and outlet gases to form a temperature spectrum;

[0027] Based on the temperature spectrum and temperature spectrum, the average values ​​of the inlet and outlet gas temperatures are calculated;

[0028] When the gas temperature variation amplitude is within a set range, determining the temperature of the turbocharger turbine blade according to the average value of the inlet and outlet gas temperatures;

[0029] Through the relationship between the thermal strength and stress of the material, and the relationship between the thermal strength, temperature and time, the relationship between the material's endurance life, temperature and stress is derived.

[0030] Optionally, the maximum stress distribution at the blade root is obtained by counting and fitting the occurrence frequency of each stress in the stress spectrum; the blade temperature at the blade root is obtained by analyzing the actual operating speed spectrum and temperature spectrum.

[0031] Optionally, predicting the comprehensive life of the turbine according to the total fatigue damage and the total creep damage comprises:

[0032] According to the linear damage accumulation principle, the total fatigue damage and total creep damage within the target working time of the turbine are accumulated to obtain the total damage value;

[0033] The comprehensive life of the turbine is predicted based on the relationship between the total damage value and the life.

[0034] According to a second aspect of an embodiment of the present application, a turbine life prediction system is provided, the system comprising:

[0035] A stress spectrum fitting module is used to fit the stress spectrum according to the actual working speed spectrum of the turbine and the relationship between the speed and stress;

[0036] A total fatigue damage module, used for calculating the total fatigue damage at the blade root of the turbine blade after the target working time based on the stress spectrum;

[0037] A total creep damage module, used for calculating the total creep damage at the blade root of the turbine blade after the target operating time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum;

[0038] The life prediction module is used to predict the comprehensive life of the turbine according to the total fatigue damage and the total creep damage.

[0039] According to a third aspect of an embodiment of the present application, an electronic device is provided, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method described in the first aspect above.

[0040] According to a fourth aspect of an embodiment of the present application, a computer-readable storage medium is provided, on which computer-readable instructions are stored. The computer-readable instructions can be executed by a processor to implement the method described in the first aspect above.

[0041] In summary, the embodiments of the present application provide a method, system, device and storage medium for predicting the life of a turbine. By fitting a stress spectrum according to the actual working speed spectrum of the turbine and the relationship between speed and stress; calculating the total fatigue damage at the root of the turbine blade after the target working time based on the stress spectrum; calculating the total creep damage at the root of the turbine blade after the target working time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum; predicting the comprehensive life of the turbine based on the total fatigue damage and the total creep damage. A fatigue creep comprehensive life prediction method under a given actual road spectrum is constructed. By comprehensively considering various influencing factors of the turbine under actual working conditions, the working life of the supercharger turbine can be predicted more accurately, thereby improving the performance and safety of the turbine and ensuring the stable operation of the turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0043] The structures, proportions, sizes, etc. illustrated in this specification are only used to match the contents disclosed in the specification so as to facilitate understanding and reading by persons familiar with the technology. They are not used to limit the conditions under which the present invention can be implemented, and therefore have no substantial technical significance. Any structural modification, change in proportion or adjustment of size shall still fall within the scope of the technical contents disclosed in the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0044] Figure 1 A schematic flow chart of a turbine life prediction method provided in an embodiment of the present application;

[0045] Figure 2 The overall logic diagram of turbine life calculation provided by the embodiment of the present application;

[0046] Figure 3 A structural diagram of a turbine life prediction system provided in an embodiment of the present application;

[0047] Figure 4 A structural diagram of an electronic device provided in an embodiment of the present application is shown;

[0048] Figure 5 A diagram showing a computer-readable storage medium provided by an embodiment of the present application.

[0049] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0050] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0052] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0053] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0054] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0055] The main failure mode of the supercharger turbine is the fracture failure of the turbine blade root caused by the interaction of fatigue and creep. In the existing technology, the life prediction is mostly carried out under fixed working conditions, or only fatigue damage is considered. Therefore, it is very necessary to carry out fatigue creep comprehensive life prediction under the actual road spectrum.

[0056] Figure 1A turbine life prediction method provided by an embodiment of the present application is shown, the method comprising:

[0057] Step 101: fitting a stress spectrum according to the actual operating speed spectrum of the turbine and the relationship between the speed and the stress;

[0058] Step 102: calculating the total fatigue damage at the blade root of the turbine blade after the target working time based on the stress spectrum;

[0059] Step 103: calculating the total creep damage at the blade root of the turbine blade after the target operating time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum;

[0060] Step 104: predicting the comprehensive life of the turbine according to the total fatigue damage and the total creep damage.

[0061] In a possible implementation manner, in step 102, calculating the total fatigue damage at the blade root of the turbine blade after the target working time based on the stress spectrum includes:

[0062] The stress spectrum is analyzed by using a rain flow counting method to obtain the number of working cycles under several stress levels; the total fatigue damage under one working cycle is calculated using a fatigue characteristic curve of the turbine blade material; based on the relationship between the number of working cycles and the engine working time, the total fatigue damage at the root of the turbine blade is calculated according to the total fatigue damage under one working cycle and the expected number of working cycles within a target working time.

[0063] In a possible implementation manner, in step 102, calculating the total fatigue damage under one working cycle using the fatigue characteristic curve of the turbine blade material includes:

[0064] According to the fatigue characteristic curve of the turbine blade material, the fatigue life under several stress levels is determined; the fatigue characteristic curve represents the relationship between the stress level and the fatigue life; based on the fatigue life and the number of working cycles under the several stress levels, the predicted life and fatigue damage under each stress level are calculated; the fatigue damage under several stress levels is accumulated to calculate the total fatigue damage under one working cycle.

[0065] Suppose there is a turbine whose actual operating speed spectrum shows that the stress at the root of the blade increases significantly when running under high load. Through the method of the embodiment of the present application, the stress spectrum is first fitted according to the relationship between the speed and stress, and the stress level at the root of the blade at different speeds is determined. The stress spectrum is analyzed by the rain flow counting method to obtain the number of working cycles at different stress levels. Then, based on the fatigue characteristic curve of the turbine blade material, the fatigue damage corresponding to the number of working cycles at these stress levels is calculated. Finally, combined with the expected number of working cycles within the target working time, the total fatigue damage at the root of the blade is calculated. Combined with the stress spectrum, speed spectrum and temperature spectrum, the total creep damage at the root of the blade after the target working time is calculated. The comprehensive results predict the comprehensive life of the turbine.

[0066] With this method, if the prediction results show that the turbine will reach the critical point of its fatigue life in the next 6 months, engineers can plan maintenance, replacement or repair of the blades in 5 months to avoid potential failures. This not only improves the operational safety of the turbine, but also optimizes maintenance costs and plans. By comprehensively considering factors such as stress, speed, temperature, etc. of the turbine under actual working conditions, the fatigue damage and creep damage at the root of the turbine blades can be accurately calculated, thereby predicting the comprehensive life of the turbine.

[0067] In a possible implementation manner, in step 103, the total creep damage at the blade root of the turbine blade after the target operating time is calculated based on the stress spectrum, the actual operating speed spectrum, and the temperature spectrum, including:

[0068] Based on the speed spectrum and temperature spectrum of the actual operation, the relationship between the endurance life and the temperature and stress is derived; the stress spectrum at the root of the turbine blade is subjected to frequency statistics to obtain statistical results; the statistical results are subjected to probability fitting to obtain the stress probability density function at the root of the turbine blade; the stress probability density function is used in combination with the maximum stress distribution at the root of the blade, the blade temperature, and the relationship between the material life and the temperature and stress to calculate the total creep damage at the root of the turbine blade within the target duration.

[0069] The stress spectrum at the root of the turbine blade is counted and the stress probability density function is obtained through probability fitting to provide accurate stress distribution data for the calculation of creep damage. The stress probability density function is used in combination with the maximum stress distribution at the root of the blade, the blade temperature, and the relationship between material life and temperature and stress to calculate the total creep damage at the root of the turbine blade within the target time, thus achieving a comprehensive assessment of the creep damage of the turbine blade.

[0070] In a possible implementation manner, in step 103, the relationship between the material endurance life and temperature and stress is as follows:

[0071] The speed data of the turbine in actual operation is collected to form a speed spectrum; the temperature data of the turbine inlet and outlet gas is collected to form a temperature spectrum; the average values ​​of the inlet and outlet gas temperatures are calculated based on the temperature spectrum and the temperature spectrum; when the gas temperature variation amplitude is within a set range, the temperature of the supercharger turbine blade is determined based on the average values ​​of the inlet and outlet gas temperatures; the relationship between the material's thermal strength and stress, and the relationship between the thermal strength, temperature and time, is used to derive the relationship between the material's endurance life, temperature and stress.

[0072] The speed and temperature data of the turbine in actual operation are collected and analyzed to form a speed spectrum and a temperature spectrum, and then the relationship between the material's endurance life and temperature and stress is derived, providing a scientific basis for the calculation of creep damage.

[0073] In a possible implementation, in step 103, the maximum stress distribution at the blade root is obtained by counting and fitting the occurrence frequency of each stress in the stress spectrum; the blade temperature at the blade root is obtained by analyzing the actual operating speed spectrum and temperature spectrum.

[0074] Suppose there is a turbine whose working conditions include high temperature and high speed, which have a significant effect on the creep damage at the blade root. Using this technical solution, first collect the speed data of the turbine in actual operation and the temperature data of the inlet and outlet gases to form a speed spectrum and a temperature spectrum. Then, calculate the average value of the inlet and outlet gas temperatures to determine the temperature of the supercharger turbine blade. Next, the relationship between the material's thermal strength and stress, and the relationship between the thermal strength and temperature and time, is derived to derive the relationship between the material's endurance life and temperature and stress. The stress spectrum at the root of the turbine blade is frequency counted, and the stress probability density function is obtained by probability fitting. This function describes the probability of stress occurrence at different stress levels and provides key data for the calculation of creep damage. Using the stress probability density function, combined with the maximum stress distribution and blade temperature at the blade root, and the relationship between the material's endurance life and temperature and stress, the total creep damage at the root of the turbine blade within the target duration is calculated.

[0075] By combining the actual operating data of the turbine (including the speed spectrum and temperature spectrum), as well as the relationship between the material's endurance life and temperature and stress, the total creep damage at the root of the turbine blade after the target operating time can be accurately calculated.

[0076] In a possible implementation, in step 104, predicting the comprehensive life of the turbine according to the total fatigue damage and the total creep damage includes:

[0077] According to the linear damage accumulation principle, the total fatigue damage and the total creep damage within the target working time of the turbine are accumulated to obtain the total damage value; based on the relationship between the total damage value and the life, the comprehensive life of the turbine is predicted.

[0078] According to the actual working conditions of the turbine, the total fatigue damage and total creep damage within the target working time are calculated. Then, according to the principle of linear damage accumulation, these two damage values ​​are added to obtain the total damage value. Finally, based on the relationship between the total damage value and the life, the comprehensive life of the turbine is predicted. For example, if the prediction results show that the turbine will reach the critical point of its total damage in the next two years, engineers can plan maintenance, replacement or repair of blades in one and a half years to avoid potential failures. In this way, not only the operational safety of the turbine is improved, but also the maintenance cost and plan are optimized.

[0079] In summary, the present invention proposes an innovative comprehensive life prediction method specifically for evaluating the service life of a supercharger turbine. It not only takes into account the fatigue damage at the failure risk position of the turbine blade root, but also takes into account the creep damage. By superimposing these two types of damage, the comprehensive predicted life of the turbine is obtained. The service life of the turbine is predicted by comprehensively considering the fatigue characteristics and creep characteristics of the failure risk position of the turbine blade root.

[0080] Specifically, the first aspect: fatigue damage calculation. First, the speed spectrum of the supercharger and the relationship data between speed and stress are needed. With these data, a stress spectrum can be constructed, and the SN curve and rain flow counting method can be used to calculate the total fatigue damage of the risky parts of the blade root failure of the turbine blade under a given speed spectrum. This process follows the Miner linear damage accumulation principle to ensure the accuracy of fatigue damage calculation. In order to unify the life scale of fatigue damage, this method introduces the relationship between the number of working cycles and the working time, and converts the fatigue damage that was originally based on the number of working cycles as the life scale into a life scale based on time, thereby realizing damage comparison under different conditions.

[0081] The second aspect: creep damage calculation. In the calculation of creep damage, the relationship between the long-term thermal strength and stress of the turbine blade material, as well as the relationship between thermal strength, temperature and time, are combined to obtain the relationship between the material's long-term life and temperature and stress. By analyzing the stress distribution at the risk of failure of the turbine blade root and the temperature of the turbine blade, the total creep damage under a given speed spectrum and temperature spectrum can be calculated. Among them, the stress distribution at the risk of failure of the turbine blade root is obtained by statistically fitting the frequency of occurrence of each stress in the stress spectrum, while the temperature of the turbine blade is determined based on the turbine inlet gas temperature spectrum and the outlet gas temperature spectrum. When the gas temperature variation is small, this method uses the average of the average values ​​of the turbine inlet gas temperature and the outlet gas temperature when the vehicle is in normal driving state as the temperature of the turbocharger turbine blade.

[0082] The third aspect: Calculate the predicted life of the turbine based on fatigue damage and creep damage. This comprehensive life prediction method combines fatigue damage and creep damage to calculate the total damage, and derives the predicted life of the turbine based on the relationship between damage and life. This method provides a more accurate and comprehensive means for predicting the life of the turbocharger turbine, which helps to improve the reliability and safety of the turbine.

[0083] Figure 2 The overall logic of turbine comprehensive fatigue creep life prediction shown provides a comprehensive analysis method for calculating the fatigue damage and creep damage of the turbine within t hours of operation. These two types of damage are evaluated separately and finally accumulated to obtain the comprehensive predicted life of the turbine.

[0084] The first step in fatigue damage prediction is to obtain the SN curve of the material fatigue characteristics of the turbine at the operating temperature through experiments. Subsequently, the relationship between the turbine speed and stress is determined through engine tests. Using the actual working speed spectrum, the maximum stress spectrum under one working cycle of the engine can be fitted. Next, the rain flow counting method is used to calculate the predicted life and fatigue damage under each load, and based on the Miner linear damage accumulation principle, the total fatigue damage under one working cycle is obtained. Finally, by introducing the relationship between the number of working cycles and the engine working time, the total fatigue damage is converted into a representation in units of time, thereby obtaining the total fatigue damage at the root of the blade when the turbine works for t hours.

[0085] Creep damage prediction obtains the relationship between the material thermal strength Q and stress s, as well as the relationship between thermal strength Q, temperature θ, and time t from the material manual. Combining these two relationships, the relationship between the material endurance life t, temperature θ, and stress s can be obtained. Considering the non-uniformity of turbine stress, the probability distribution integral method is used to calculate the total creep damage. The probability density function of the maximum stress at the root of the turbine blade is obtained by performing frequency statistics and probability fitting on the maximum stress spectrum. Considering the changing characteristics of the turbine thermal load, when the gas temperature changes slightly, the average value of the average value of the turbine inlet gas temperature and the average value of the outlet gas temperature during normal vehicle driving is used as the temperature of the turbocharger turbine blade. Combining the maximum stress distribution and blade temperature at the blade root, as well as the relationship between the material life t, temperature θ, and stress s, the total creep damage at the root of the turbine blade within t hours can be obtained by integration.

[0086] According to Miner's linear damage accumulation principle, the total damage of a turbine within t hours of operation is the cumulative value of the total fatigue damage and the total creep damage within this time. By calculating the total damage within t hours, the comprehensive fatigue creep prediction life of the turbine can be obtained. The fatigue and creep rupture failure of the turbine under the three-phase load of centrifugal-thermal-aerodynamic is considered, and a method for predicting the comprehensive fatigue creep life of the turbine under the actual road spectrum is provided, which is of great significance for improving the reliability and safety of the turbine.

[0087] In summary, the embodiment of the present application provides a method for predicting the life of a turbine, by fitting a stress spectrum according to the actual operating speed spectrum of the turbine and the relationship between speed and stress; calculating the total fatigue damage at the root of the turbine blade after the target operating time based on the stress spectrum; calculating the total creep damage at the root of the turbine blade after the target operating time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum; predicting the comprehensive life of the turbine based on the total fatigue damage and the total creep damage. A fatigue creep comprehensive life prediction method under a given actual road spectrum is constructed, which can more accurately predict the working life of the supercharger turbine by comprehensively considering various influencing factors of the turbine under actual working conditions, thereby improving the performance and safety of the turbine and ensuring the stable operation of the turbine.

[0088] Based on the same technical concept, the embodiment of the present application also provides a turbine life prediction system, such as Figure 3 As shown, the system comprises:

[0089] A stress spectrum fitting module 301 is used to fit the stress spectrum according to the actual working speed spectrum of the turbine and the relationship between the speed and the stress;

[0090] A total fatigue damage module 302 is used to calculate the total fatigue damage at the blade root of the turbine blade after the target working time based on the stress spectrum;

[0091] A total creep damage module 303 is used to calculate the total creep damage at the blade root of the turbine blade after the target operating time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum;

[0092] The life prediction module 304 is used to predict the comprehensive life of the turbine according to the total fatigue damage and the total creep damage.

[0093] The present application also provides an electronic device corresponding to the method provided in the above embodiment. Figure 4 , which shows an electronic device diagram provided by some embodiments of the present application. The electronic device 20 may include: a processor 200, a memory 201, a bus 202 and a communication interface 203, wherein the processor 200, the communication interface 203 and the memory 201 are connected via the bus 202; the memory 201 stores a computer program that can be run on the processor 200, and the processor 200 executes the method provided by any of the aforementioned embodiments of the present application when running the computer program.

[0094] The memory 201 may include a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk memory. The communication connection between the system network element and at least one other network element is realized through at least one physical port (which may be wired or wireless), and the Internet, wide area network, local area network, metropolitan area network, etc. may be used.

[0095] The bus 202 may be an ISA bus, a PCI bus, or an EISA bus, etc. The bus may be divided into an address bus, a data bus, a control bus, etc. The memory 201 is used to store programs, and the processor 200 executes the programs after receiving execution instructions. The method disclosed in any implementation of the aforementioned embodiment of the present application may be applied to the processor 200, or implemented by the processor 200.

[0096] The processor 200 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by the hardware integrated logic circuit or software instructions in the processor 200. The above processor 200 can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a readily available programmable gate array (FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The methods, steps and logic block diagrams disclosed in the embodiments of the present application can be implemented or executed. The general-purpose processor can be a microprocessor or the processor can also be any conventional processor, etc. The steps of the method disclosed in the embodiments of the present application can be directly embodied as a hardware decoding processor to be executed, or the hardware and software modules in the decoding processor can be executed. The software module can be located in a mature storage medium in the field such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, etc. The storage medium is located in the memory 201, and the processor 200 reads the information in the memory 201 and completes the steps of the above method in combination with its hardware.

[0097] The electronic device provided in the embodiment of the present application and the method provided in the embodiment of the present application are based on the same inventive concept and have the same beneficial effects as the method adopted, operated or implemented by them.

[0098] The present application also provides a computer-readable storage medium corresponding to the method provided in the above embodiment. Figure 5 The computer-readable storage medium shown is a CD 30 on which a computer program (ie, a program product) is stored. When the computer program is run by a processor, the method provided in any of the aforementioned embodiments is executed.

[0099] It should be noted that examples of the computer-readable storage medium may also include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other optical or magnetic storage media, which are not listed here one by one.

[0100] The computer-readable storage medium provided in the above-mentioned embodiments of the present application and the method provided in the embodiments of the present application are based on the same inventive concept and have the same beneficial effects as the method adopted, run or implemented by the application program stored therein.

[0101] It should be noted that the above embodiments illustrate the present application rather than limit the present application, and that those skilled in the art may design alternative embodiments without departing from the scope of the appended claims. In the claims, any reference symbol between brackets should not be constructed as a limitation to the claims. The word "comprising" does not exclude the presence of elements or steps not listed in the claims. The word "one" or "an" preceding an element does not exclude the presence of multiple such elements. The present application may be implemented by means of hardware including several different elements and by means of a suitably programmed computer. In a unit claim that lists several devices, several of these devices may be embodied by the same hardware item. The use of the words first, second, and third, etc. does not indicate any order. These words may be interpreted as names.

[0102] The above is only a preferred specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

[0103] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A turbine life prediction method, characterized in that: The method comprises: Fit the stress spectrum according to the actual working speed spectrum of the turbine and the relationship between speed and stress; Calculating total fatigue damage at the blade root of the turbine blade after a target operating time based on the stress spectrum; Calculating the total creep damage at the blade root of the turbine blade after the target operating time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum; The comprehensive life of the turbine is predicted according to the total fatigue damage and the total creep damage.

2. The method according to claim 1, characterized in that The calculating the total fatigue damage at the blade root of the turbine blade after the target working time based on the stress spectrum includes: The stress spectrum is analyzed by using a rain flow counting method to obtain the number of working cycles under several stress levels; The total fatigue damage under one working cycle is calculated using the fatigue characteristic curve of the turbine blade material; Based on the relationship between the number of working cycles and the engine working time, the total fatigue damage at the root of the turbine blade is calculated according to the total fatigue damage under the said one working cycle and the expected number of working cycles within the target working time.

3. The method according to claim 2, characterized in that The method of calculating the total fatigue damage under one working cycle by using the fatigue characteristic curve of the turbine blade material includes: Determining fatigue life at several stress levels according to a fatigue characteristic curve of the turbine blade material; wherein the fatigue characteristic curve represents the relationship between stress level and fatigue life; Based on the fatigue life and working cycle number under the several stress levels, the predicted life and fatigue damage under each stress level are calculated; The fatigue damage under several stress levels is accumulated to calculate the total fatigue damage under one working cycle.

4. The method according to claim 2, characterized in that The total creep damage at the blade root of the turbine blade after the target working time is calculated based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum, comprises: Derivation of the relationship between the endurance life and the temperature and stress based on the rotation speed spectrum and temperature spectrum of the actual operation; Performing frequency statistics on the stress spectrum at the root of the turbine blade to obtain statistical results; Performing probability fitting on the statistical results to obtain a stress probability density function at the root of the turbine blade; The total creep damage at the blade root of the turbine blade within a target time period is calculated by using the stress probability density function, combining the maximum stress distribution at the blade root, the blade temperature, and the relationship between the material life, temperature and stress.

5. The method according to claim 4, characterized in that The relationship between the material's endurance life, temperature and stress is as follows: Collect the speed data of the turbine in actual operation to form a speed spectrum; Collect temperature data of turbine inlet and outlet gases to form a temperature spectrum; Based on the temperature spectrum and temperature spectrum, the average values ​​of the inlet and outlet gas temperatures are calculated; When the gas temperature variation amplitude is within a set range, determining the temperature of the turbocharger turbine blade according to the average value of the inlet and outlet gas temperatures; Through the relationship between the thermal strength and stress of the material, and the relationship between the thermal strength, temperature and time, the relationship between the material's endurance life, temperature and stress is derived.

6. The method according to claim 4, characterized in that The maximum stress distribution at the blade root is obtained by counting and fitting the occurrence frequency of each stress in the stress spectrum; the blade temperature at the blade root is obtained by analyzing the speed spectrum and temperature spectrum of the actual operation.

7. The method according to claim 1, characterized in that The method of predicting the comprehensive life of a turbine according to the total fatigue damage and the total creep damage comprises: According to the linear damage accumulation principle, the total fatigue damage and total creep damage within the target working time of the turbine are accumulated to obtain the total damage value; The comprehensive life of the turbine is predicted based on the relationship between the total damage value and the life.

8. A turbine life prediction system, characterized in that: The system comprises: A stress spectrum fitting module is used to fit the stress spectrum according to the actual working speed spectrum of the turbine and the relationship between the speed and stress; A total fatigue damage module, used for calculating the total fatigue damage at the blade root of the turbine blade after the target working time based on the stress spectrum; A total creep damage module, used for calculating the total creep damage at the blade root of the turbine blade after the target operating time based on the stress spectrum, the actual operating speed spectrum and the temperature spectrum; The life prediction module is used to predict the comprehensive life of the turbine according to the total fatigue damage and the total creep damage.

9. An electronic device, comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: Computer-readable instructions are stored thereon, and the computer-readable instructions can be executed by a processor to implement the method according to any one of claims 1-7.

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