A method for verifying a key part life test result and related equipment

Abstract

This invention relates to the field of low-cycle fatigue life testing technology for aero-engines, and discloses a method and related equipment for verifying the life test results of key components. The method includes: acquiring the flight conversion rate and cycle consumption number between engine flight time and cycle count; analyzing the test results of a used key component equipped with a cycle parameter recorder; calculating the predetermined safe cycle life of the component; comparing the calculated life with the standard cycle count given in the design to obtain preliminary verification results; and for used key components of engines that fail the preliminary verification or are equipped with cycle parameter recorders, analyzing the results and calculating the verification threshold using the life divergence coefficient to complete the verification of the predetermined safe cycle life of the key component. This invention solves the technical problem of low accuracy in determining the life of key components in the prior art.

Description

Technical Field

[0001] This invention relates to the field of low-cycle fatigue life testing technology for aero-engines, specifically to a method and related equipment for verifying the life test results of key components. Background Technology

[0002] The reliability of critical components of an aircraft engine directly determines the engine's operational safety. Failure can trigger a major accident, seriously threatening flight safety. Therefore, the approved safe service life of such critical components must be clearly defined. When these components reach their approved service life, they must be forcibly withdrawn from service to avoid dangerous failures such as fatigue damage. It is evident that their service life indicators are one of the core indicators for ensuring aviation flight safety.

[0003] Currently, determining the predetermined safe cycle life of critical components for aero-engines typically follows a rigorous life management plan. After a new component completes low-cycle fatigue testing and its predetermined safe cycle life (PSCL) is determined, its recommended safe service life is not released all at once, but rather in stages until the predetermined safe cycle life is reached. The standard procedure is as follows: the initial predetermined safe cycle life for critical components is set at half of the total approved predetermined safe cycle life; subsequently, based on the actual operating conditions of the engine, sampling inspections are conducted on critical components after they enter service to comprehensively assess various factors affecting component life, and the rationality of the initially given predetermined safe cycle life is verified through relevant tests; only after the fatigue life test verification of the component after use is completed and the results are qualified can its predetermined safe cycle life be fully released.

[0004] Although fatigue life tests have been conducted in China on key components of newly produced aero-engines based on relevant life determination methods, the field of testing and verification of key components after a certain period of service remains blank. Specifically, there is a lack of practical experience in core technical aspects such as process control for the gradual release of key components and confirmation of release life after use. A complete system and method have not yet been established to scientifically analyze and standardize the test results of key components after use.

[0005] Meanwhile, fatigue life tests on newly manufactured key components suffer from insufficient sample size. To accurately determine the safe life of new components, a sufficient number of tests are required to ensure data reliability. In foreign countries, the sample size for life tests on similar key components generally reaches more than 2 pieces (times), and some key components even undergo more than 10 pieces (times) of tests. However, due to various limitations in China, the sample size for life tests on newly manufactured key components is generally only 1 to 2 pieces (times), resulting in insufficient representativeness of the test data. This not only affects the accuracy of determining the safe life but also makes the economic cost of determining the safe life of new components too high and the time span too long, making it difficult to meet the needs of the efficient development of the aero-engine industry. Summary of the Invention

[0006] In order to overcome the defects of the prior art, the purpose of this invention is to provide a method and related equipment for verifying the life test results of key components, so as to solve the technical problem of low accuracy in determining the life of key components in the prior art.

[0007] This invention is achieved through the following technical solution: In a first aspect, the present invention provides a method for verifying the life test results of key components, comprising: The flight conversion rate and cycle consumption between engine flight time and cycle number are obtained. The flight conversion rate is the ratio of cycle number to flight time. The flight conversion rate is distinguished between deterministic and indeterminate types depending on whether the engine is equipped with a cycle parameter recorder, and the corresponding deterministic value or distribution range of cycle consumption is obtained. Based on the deterministic flight conversion rate and cycle consumption, the test results of the key components equipped with cycle parameter recorders after use were analyzed, the verification predetermined safe cycle life of the components was calculated, and the preliminary verification results were obtained by comparing them with the standard cycle number given in the design. Based on the preliminary verification results, for the key components of engines that failed the preliminary verification or were equipped with cycle parameter recorders, a progressive analysis method was adopted, which included single-piece testing of key components under random conditions, pre-test evaluation of multiple components, processing of multiple test results, and verification of crack propagation life. The verification threshold was calculated by combining the life divergence coefficient to complete the verification of the predetermined safe cycle life of the key components.

[0008] Preferably, the specific process for obtaining the flight conversion rate includes combining the number of cycles consumed during factory testing, the number of cycles consumed during actual flight, and the clipping factor; for engines equipped with a cycle parameter recorder, the flight conversion rate is a fixed value, and the corresponding number of cycles consumed by the parts after use is also a fixed value; for engines not equipped with a cycle parameter recorder, the flight conversion rate follows a log-normal distribution, and its distribution range in [-3σ, +3σ] is [γ]. min η max [, combined with engine field usage time] T The distribution range of the cycle consumption number in [-3σ, +3σ] is [γ]. min η max ].

[0009] Preferably, the analysis of test results for key components after use, equipped with a cyclic parameter recorder, specifically includes: Assume the conversion rate for engine field flight equipped with a cyclic parameter recorder is [value missing]. E Take and use until T If an engine is tested for 24 hours with a test load factor of α, the expression for the number of cycles consumed is as follows: ; Let the number of cycles of the part testing machine after use be... N 2. The divergence coefficient is Y The verified predetermined safe cycle life is expressed as follows: =

[0010] Among them, if F r1 If the number of cycles exceeds the standard cycle number given in the design, the safe life of the part can be extended to that standard cycle number; if F r1 If the number of cycles is less than the standard number given in the design, it will be processed according to the result analysis method under random conditions.

[0011] Preferably, single-piece test verification specifically includes: Assume that the field usage time of the engine without a cycle parameter recorder when it returns to the factory is... T The distribution range of the number of cycles consumed [γ] min η max The corresponding minimum value expression is as follows:

[0012] The maximum value expression is as follows:

[0013] Where α is the test load factor; Let F be the predetermined number of safe loops to be verified. The total number of loops is expressed as follows:

[0014] Where Y is the lifetime divergence coefficient; The number of test cycles required to meet the verification requirements is expressed as follows: Z1= -

[0015] Among them, if the number of tester cycles obtained from the verification test N>Z 1, then allow the predetermined safety cycle number F; if N < Z 1. Then, perform supplementary tests using multiple test methods.

[0016] Preferably, the pre-test evaluation for multiple specimens specifically includes a decrease in the lifetime divergence coefficient as the number of specimens increases, and a decrease when the number of specimens approaches infinity. Y =2.45, evaluated with 3 test specimens, this is the divergence coefficient corresponding to the minimum lifetime. Y min=2.71; Let the number of cycles for the first test piece be the minimum lifespan piece. Z 3. If Z 3 <N d <Z 1. Where Nd is the design-related cycle number threshold, and assuming that the first piece is the minimum lifespan piece, the number of subsequent test cycles is greater than Z3, then multiple piece tests are carried out; if the number of subsequent test cycles is less than Z3, then the smaller number of cycles is used as the minimum lifespan piece for re-evaluation; if the evaluation cannot verify the predetermined safe cycle life, then the release life is shortened and the sampling inspection is tightened.

[0017] Preferably, the processing of multiple test results includes when - <N d < - At that time, arrange the second and subsequent tests; Let F be the predetermined number of safety cycles to be verified. The expression for the average number of test cycles that meets the verification requirements is as follows: Z d = -

[0018] Calculate the geometric mean of the number of test cycles for the completed test pieces. If the number of test cycles for the second piece is N2, the expression for the geometric mean of the number of cycles for the first piece is as follows:

[0019] like >Z d If, then the predetermined safety cycle number F is reached; if <Z d And N2 > the number of cycles for the first item, continue with the third item trial; if <Z d If N2 < the first cycle number, re-execute the pre-test evaluation for multiple trials.

[0020] Preferably, crack propagation life verification includes when - < N d < - At that time, the crack propagation life verification method was used for parts that did not show cracks; Let the predetermined number of safety cycles to be verified be . F The safe lifespan has been released. F 0, remaining lifespan is FF 0; Let the number of test cycles when the crack is detected be... Z 1. The number of test cycles at the end of the test is:Z 2. The number of test cycles used for crack propagation life calculation is: Z 1 -Z 2; The expression for crack propagation life is as follows:

[0021] like Z L > F - F If 0, then the predetermined safety cycle number F is allowed; if Z L < F - F If the value is 0, the release lifespan will be shortened and sampling inspections will be tightened.

[0022] Secondly, the present invention also provides a verification system for the life test results of key components, comprising: The parameter acquisition module is used to acquire the flight conversion rate and cycle consumption between engine flight time and cycle number. The flight conversion rate is the ratio of cycle number to flight time. The conversion rate is distinguished between deterministic and indeterminate types depending on whether the engine is equipped with a cycle parameter recorder, and the corresponding definite value or distribution range of cycle consumption is obtained. The preliminary results analysis module is used to analyze the test results of key components equipped with cycle parameter recorders after use, based on the deterministic flight conversion rate and cycle consumption number, calculate the predetermined safe cycle life of the component, and compare it with the standard cycle number given in the design to obtain the preliminary verification results. The analysis result verification module is used to verify the predetermined safe cycle life of key components of engines that have not met the initial verification standards or are equipped with cycle parameter recorders, based on the preliminary verification results. It adopts a progressive analysis method, which includes single-piece testing, multi-piece pre-test evaluation, multi-piece test result processing, and crack propagation life verification of key components under random conditions. The verification threshold is calculated by combining the life divergence coefficient.

[0023] Thirdly, the present invention also provides a mobile terminal, including 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 steps of the method for verifying the results of the life test of key components as described above.

[0024] Fourthly, the present invention also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the steps of the method for verifying the results of the critical component life test as described above.

[0025] Compared with the prior art, the present invention has the following beneficial technical effects: This invention provides a method for verifying the life test results of key components. By distinguishing whether the engine is equipped with a cycle parameter recorder, it obtains the deterministic or uncertain flight conversion rate and the corresponding definite value or distribution range of cycle consumption. For components equipped with cycle parameter recorders, it calculates the number of cycles consumed and verifies the predetermined safe cycle life based on the determined flight conversion rate. Preliminary verification results are quickly obtained by directly comparing with the design standard cycle number. This process avoids the limitations of traditional single-index evaluation by introducing key parameters such as test load coefficient and divergence coefficient. For components that fail the preliminary verification or are not equipped with cycle parameter recorders, a progressive analysis system is adopted, consisting of single-piece testing, pre-test evaluation of multiple components, processing of multi-piece test results, and crack propagation life verification. This system not only quickly completes the preliminary screening through single-piece testing but also balances the economic efficiency and data reliability of testing through divergence coefficient evaluation before multi-piece testing, covering the verification needs under different test scenarios and effectively improving the accuracy of life determination. At the same time, reasonable test design reduces test costs and cycle time. Attached Figure Description

[0026] Figure 1 This is a flowchart of a method for verifying the life test results of key components in an embodiment of the present invention; Figure 2 This is a diagram showing the log-lifetime normal distribution curve and the relationship between the divergence coefficient and reliability and confidence level in an embodiment of the present invention. Figure 3 This is a schematic diagram of the verification system for the life test results of key components in an embodiment of the present invention; In the diagram: 1. Parameter acquisition module; 2. Preliminary result analysis module; 3. Analysis result verification module. Detailed Implementation

[0027] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0028] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0029] The purpose of this invention is to provide a method and related equipment for verifying the life test results of key components, so as to solve the technical problem of low accuracy in determining the life of key components in the prior art.

[0030] The present invention will now be described in further detail with reference to the accompanying drawings: See Figure 1 This invention provides a method for verifying the life test results of key components, comprising: Step 1: Obtain the flight conversion rate and cycle consumption between engine flight time and number of cycles. The flight conversion rate is the ratio of number of cycles to flight time. Based on whether the engine is equipped with a cycle parameter recorder, distinguish between deterministic and indeterminate flight conversion rates to obtain the definite value or distribution range of the corresponding cycle consumption. Specifically, the process of obtaining the flight conversion rate includes combining the number of cycles consumed during factory testing, the number of cycles consumed during actual flight, and the clipping factor. For engines equipped with a cycle parameter recorder, the flight conversion rate is a fixed value, and the corresponding number of cycles consumed by the parts after use is also a fixed value. For engines not equipped with a cycle parameter recorder, the flight conversion rate follows a log-normal distribution, with a distribution range of [-3σ, +3σ] and [γ]. min η max [, combined with engine field usage time] T The distribution range of the cycle consumption number in [-3σ, +3σ] is [γ]. min η max ].

[0031] Step 2: Based on the deterministic flight conversion rate and cycle consumption, analyze the test results of the key components equipped with cycle parameter recorders after use, calculate the predetermined safe cycle life of the component, and compare it with the standard cycle number given in the design to obtain the preliminary verification results. Specifically, the analysis of test results for key components after using a cyclic parameter recorder includes: Assume the conversion rate for engine field flight equipped with a cyclic parameter recorder is [value missing]. E Take and use until T If an engine is tested for 24 hours with a test load factor of α, the expression for the number of cycles consumed is as follows: ; Let the number of cycles of the part testing machine after use be... N 2. The divergence coefficient is Y The verified predetermined safe cycle life is expressed as follows: =

[0032] Among them, if F r1 If the number of cycles exceeds the standard cycle number given in the design, the safe life of the part can be extended to that standard cycle number; if F r1 If the number of cycles is less than the standard number given in the design, it will be processed according to the result analysis method under random conditions.

[0033] Step 3: Based on the preliminary verification results, for the key components of the engine that failed the preliminary verification or were equipped with a cycle parameter recorder, a progressive analysis method is adopted, which includes single-piece testing of the key components under random conditions, pre-test evaluation of multiple components, processing of multiple test results, and verification of crack propagation life. The verification threshold is calculated by combining the life divergence coefficient to complete the verification of the predetermined safe cycle life of the key components.

[0034] Specifically, single-piece testing and verification includes: Assume that the field usage time of the engine without a cycle parameter recorder when it returns to the factory is... T The distribution range of the number of cycles consumed [γ] min η max The corresponding minimum value expression is as follows:

[0035] The maximum value expression is as follows:

[0036] Where α is the test load factor; Let F be the predetermined number of safe loops to be verified. The total number of loops is expressed as follows:

[0037] Where Y is the lifetime divergence coefficient; The number of test cycles required to meet the verification requirements is expressed as follows: Z1= -

[0038] Among them, if the number of tester cycles obtained from the verification test N>Z 1, then allow the predetermined safety cycle number F; if N < Z 1. Then, perform supplementary tests using multiple test methods.

[0039] Specifically, the pre-test evaluation for multiple specimens includes the life divergence coefficient decreasing as the number of specimens increases, and the change occurring when the number of specimens approaches infinity. Y =2.45, evaluated with 3 test specimens, this is the divergence coefficient corresponding to the minimum lifetime. Y min =2.71; Let the number of cycles for the first test piece be the minimum lifespan piece. Z 3. If Z 3 <N d <Z 1. Where Nd is the design-related cycle number threshold, and assuming that the first piece is the minimum lifespan piece, the number of subsequent test cycles is greater than Z3, then multiple piece tests are carried out; if the number of subsequent test cycles is less than Z3, then the smaller number of cycles is used as the minimum lifespan piece for re-evaluation; if the evaluation cannot verify the predetermined safe cycle life, then the release life is shortened and the sampling inspection is tightened.

[0040] Specifically, the processing of multiple test results includes when - <N d < - At that time, arrange the second and subsequent tests; Let F be the predetermined number of safety cycles to be verified. The expression for the average number of test cycles that meets the verification requirements is as follows: Z d = -

[0041] Calculate the geometric mean of the number of test cycles for the completed test pieces. If the number of test cycles for the second piece is N2, the expression for the geometric mean of the number of cycles for the first piece is as follows:

[0042] like >Z d If, then the predetermined safety cycle number F is reached; if <Z d And N2 > the number of cycles for the first item, continue with the third item trial; if <Z d If N2 < the first cycle number, re-execute the pre-test evaluation for multiple trials.

[0043] Specifically, crack propagation life verification includes when - < N d < - At that time, the crack propagation life verification method was used for parts that did not show cracks; Let the predetermined number of safety cycles to be verified be . F The safe lifespan has been released. F 0, remaining lifespan is FF 0; Let the number of test cycles when the crack is detected be... Z 1. The number of test cycles at the end of the test is: Z 2. The number of test cycles used for crack propagation life calculation is: Z 1 -Z 2; The expression for crack propagation life is as follows:

[0044] like Z L > F - F If 0, then the predetermined safety cycle number F is allowed; if Z L < F - F If the value is 0, the release lifespan will be shortened and sampling inspections will be tightened.

[0045] This invention provides a method for verifying the life test results of key components. By distinguishing whether the engine is equipped with a cycle parameter recorder, it obtains the deterministic or uncertain flight conversion rate and the corresponding definite value or distribution range of cycle consumption. For components equipped with cycle parameter recorders, it calculates the number of cycles consumed and verifies the predetermined safe cycle life based on the determined flight conversion rate. Preliminary verification results are quickly obtained by directly comparing with the design standard cycle number. This process avoids the limitations of traditional single-index evaluation by introducing key parameters such as test load coefficient and divergence coefficient. For components that fail the preliminary verification or are not equipped with cycle parameter recorders, a progressive analysis system is adopted, consisting of single-piece testing, pre-test evaluation of multiple components, processing of multi-piece test results, and crack propagation life verification. This system not only quickly completes the preliminary screening through single-piece testing but also balances the economic efficiency and data reliability of testing through divergence coefficient evaluation before multi-piece testing, covering the verification needs under different test scenarios. This effectively improves the accuracy of life determination and reduces test costs and cycle time through reasonable test design.

[0046] Example 1 The testing and verification process for the high-pressure turbine disk after its use is as follows: The high-pressure turbine disk to be verified has a predetermined safe cycle count of 10,000 standard cycles and 1,000 hours of field use. When verifying the lifespan of the high-pressure turbine disk, the pin holes will still be the primary testing area. Based on the above verification method, and considering factors such as the field flight conversion rate distribution and the dispersion coefficient of the component's lifespan after use, the following two verification scenarios are obtained: (1) If it is greater than Z1, the predetermined safe cycle life can be verified. The logarithmic fatigue life normal distribution recommended by DEF STAN 00971 has a standard deviation of [missing information]. б =0.13, when a given reliability R =99.87%, then μ R =3, confidence level γ =95%, then μ γ =1.645.

[0047] Through flight conversion rate surveys and distribution studies, the range of the high-pressure rotor conversion rate for the field engine under this distribution is [10, 12]. Test load coefficient. α Taking 1.08 as the value, the number of tester cycles consumed by the parts after use is: X 1 = 10 × 1000 / 1.08 5.28 =6661 times X 2 = 12 × 1000 / 1.08 5.28 =7993 times Total number of test cycles: Q =4×10000 / 1.08 5.28 =26643 times Therefore, the number of test cycles Z1 that meets the verification requirements is: Z 1 = 26643 - 6661 = 19982 times That is, when the test completes 19,982 test cycles, it can be verified that the given high-pressure turbine disk is safe for 10,000 standard cycles.

[0048] (2) If it is less than Z2, the predetermined safe cycle life cannot be verified. When the selected test piece is the worst-case sample, the life divergence coefficient is recalculated according to the new part life distribution.

[0049] Y 1= =10 （3-1.645）×0.13 =1.5 Total number of test cycle counts: Q =1.5×10000 / 1.08 5.28 =9991 times This yields the number of test cycle counts that definitely cannot meet the verification requirements. Z 2 is: Z 2 = 9991 - 7993 = 1998 times That is, if the number of tester cycles completed is less than 1998 tester cycles, the required predetermined safe cycle life cannot be verified.

[0050] (3) Results Analysis After obtaining the target test cycle count of 19,982, the test inspection nodes can be arranged more clearly. In addition to other inspection nodes, when the test cycle of 19,982 was completed, the test piece was subjected to fluorescent flaw detection. No cracks were found in either stage disk, thus achieving the test verification purpose. At this point, the test can be terminated, and the given safe life of 10,000 standard cycles for the high-pressure turbine disk is on the safe side.

[0051] Assuming the test specimen is the worst-case scenario, the lifetime divergence coefficient is recalculated based on the new part's lifetime distribution. When the logarithmic safe lifetime population follows a normal distribution, the mean of the lifetime sample also follows a normal distribution; see details below. Figure 2 The log-lifetime normal distribution curve and the relationship between the divergence coefficient and reliability and confidence level are plotted. The mean of the lifetime sample is assumed to be... , is (-∞, The best piece within the interval, i.e.: The lifespan considered the best-case scenario (confidence level γ) is the determined safe lifespan (reliability level R), which is the worst-case scenario lifespan. Then the lifetime divergence coefficient is: Y 1=N best / N min = / =

[0052] The logarithmic fatigue life normal distribution recommended by DEF STAN 00971 has a standard deviation of [missing information]. б =0.13, when a given reliability R =99.87%, then μ R =3, confidence level γ =95%, then μ γ =1.645.

[0053] when N When = 1, the lifetime divergence coefficient is: Y 1=10 （3-1.645）×0.13 =1.5 Similarly, when N When = 2, the lifetime divergence coefficient is: Y 1=10 （3-1.645 / √2） =1.733 Thus, the life divergence coefficients for the logarithmic fatigue life normal distribution when the test specimen is the worst-case specimen are obtained, as shown in Table 1.

[0054] Table 1 Life divergence coefficients when the test specimen is the worst-case scenario.

[0055] Assume the predetermined number of safety cycles to be verified is F Then we have:

[0056] in, Q Represents the total number of loops. Y 1 represents the lifetime divergence coefficient. α This represents the stress divergence coefficient.

[0057] Therefore, the number of test cycles Z2 that satisfies the verification requirements is: Z 2= - ; That is, after the verification test is completed, if the number of tester cycles is obtained... N < Z If the result is 2, it means that the part test after this use cannot verify the provisional predetermined safe cycle life.

[0058] In summary, this embodiment focuses on the design and verification of low-cycle fatigue life tests for critical components of engines that have been overhauled and returned to the factory after a certain period of use. It proposes a method for determining the release life of critical components after use and a corresponding method for analyzing the verification test results. On the one hand, it allows for the rational planning of verification tests for components after use and provides a basis for judging the verification test results of critical components by considering conversion rates and life divergence coefficients, thus improving the critical component life release system and effectively filling the gap in domestic research in this field. On the other hand, it establishes a method for analyzing the test verification results of critical components after use. This allows for adjustments to the processing methods based on different usage states and quantities of components, and different verification test results, to achieve the goal of verifying the predetermined safe cycle life through testing. This embodiment can accelerate the release process of the predetermined safe cycle life of critical components while ensuring safe use, thus saving economic costs.

[0059] The purpose of this embodiment is to provide a method for determining the lifespan of critical components after use in an aero-engine and a corresponding method for analyzing verification test results, thereby improving the critical component lifespan release system, ensuring that the predetermined safe cycle life of the temporarily released critical engine components is reasonable and safe for field use, and accelerating the release process of the predetermined safe lifespan of critical components.

[0060] Example 2 according to Figure 3 As shown, this embodiment also provides a verification system for the life test results of key components, including: The parameter acquisition module 1 is used to acquire the flight conversion rate and cycle consumption number between engine flight time and cycle number. The flight conversion rate is the ratio of cycle number to flight time. The conversion rate is distinguished between deterministic and indeterminate types depending on whether the engine is equipped with a cycle parameter recorder, and the corresponding definite value or distribution range of cycle consumption number is obtained. Preliminary Result Analysis Module 2 is used to analyze the test results of key components equipped with cycle parameter recorders after use, based on the deterministic flight conversion rate and cycle consumption number, calculate the predetermined safe cycle life of the component, and compare it with the standard cycle number given in the design to obtain the preliminary verification results. The analysis result verification module 3 is used to verify the predetermined safe cycle life of key components of engines that have not met the initial verification standards or are equipped with cycle parameter recorders, based on the preliminary verification results. It adopts a progressive analysis method, which includes single-piece testing, multi-piece pre-test evaluation, multi-piece test result processing, and crack propagation life verification of key components under random conditions. The verification threshold is calculated by combining the life divergence coefficient.

[0061] Example 3 The present invention also provides a mobile terminal, including a memory, a processor, and a computer program stored in the memory and executable on the processor, such as a verification program for the life test results of critical components.

[0062] When the processor executes the computer program, it implements the steps of the method for verifying the life test results of the aforementioned key components, for example: The flight conversion rate and cycle consumption between engine flight time and cycle number are obtained. The flight conversion rate is the ratio of cycle number to flight time. The flight conversion rate is distinguished between deterministic and indeterminate types depending on whether the engine is equipped with a cycle parameter recorder, and the corresponding deterministic value or distribution range of cycle consumption is obtained. Based on the deterministic flight conversion rate and cycle consumption, the test results of the key components equipped with cycle parameter recorders after use were analyzed, the verification predetermined safe cycle life of the components was calculated, and the preliminary verification results were obtained by comparing them with the standard cycle number given in the design. Based on the preliminary verification results, for the key components of engines that failed the preliminary verification or were equipped with cycle parameter recorders, a progressive analysis method was adopted, which included single-piece testing of key components under random conditions, pre-test evaluation of multiple components, processing of multiple test results, and verification of crack propagation life. The verification threshold was calculated by combining the life divergence coefficient to complete the verification of the predetermined safe cycle life of the key components.

[0063] Alternatively, when the processor executes the computer program, it implements the functions of each module in the above system, for example: The parameter acquisition module 1 is used to acquire the flight conversion rate and cycle consumption number between engine flight time and cycle number. The flight conversion rate is the ratio of cycle number to flight time. The conversion rate is distinguished between deterministic and indeterminate types depending on whether the engine is equipped with a cycle parameter recorder, and the corresponding definite value or distribution range of cycle consumption number is obtained. Preliminary Result Analysis Module 2 is used to analyze the test results of key components equipped with cycle parameter recorders after use, based on the deterministic flight conversion rate and cycle consumption number, calculate the predetermined safe cycle life of the component, and compare it with the standard cycle number given in the design to obtain the preliminary verification results. The analysis result verification module 3 is used to verify the predetermined safe cycle life of key components of engines that have not met the initial verification standards or are equipped with cycle parameter recorders, based on the preliminary verification results. It adopts a progressive analysis method, which includes single-piece testing, multi-piece pre-test evaluation, multi-piece test result processing, and crack propagation life verification of key components under random conditions. The verification threshold is calculated by combining the life divergence coefficient.

[0064] For example, the computer program may be divided into one or more modules / units, which are stored in the memory and executed by the processor to complete the present invention. The one or more modules / units may be a series of computer program instruction segments capable of performing a specific function, which describe the execution process of the computer program in the mobile terminal.

[0065] For example, the computer program can be divided into a parameter acquisition module 1, a preliminary result analysis module 2, and an analysis result verification module 3; The specific functions of each module are as follows: The parameter acquisition module 1 is used to acquire the flight conversion rate and cycle consumption number between engine flight time and cycle number. The flight conversion rate is the ratio of cycle number to flight time. The conversion rate is distinguished between deterministic and indeterminate types depending on whether the engine is equipped with a cycle parameter recorder, and the corresponding definite value or distribution range of cycle consumption number is obtained. Preliminary Result Analysis Module 2 is used to analyze the test results of key components equipped with cycle parameter recorders after use, based on the deterministic flight conversion rate and cycle consumption number, calculate the predetermined safe cycle life of the component, and compare it with the standard cycle number given in the design to obtain the preliminary verification results. The analysis result verification module 3 is used to verify the predetermined safe cycle life of key components of engines that have not met the initial verification standards or are equipped with cycle parameter recorders, based on the preliminary verification results. It adopts a progressive analysis method, which includes single-piece testing, multi-piece pre-test evaluation, multi-piece test result processing, and crack propagation life verification of key components under random conditions. The verification threshold is calculated by combining the life divergence coefficient.

[0066] The mobile terminal can be a computing device such as a desktop computer, laptop, handheld computer, or cloud server. The mobile terminal may include, but is not limited to, a processor and memory.

[0067] The processor can be a Central Processing Unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor can be a microprocessor or any conventional processor. The processor is the control center of the mobile terminal, connecting various parts of the mobile terminal via various interfaces and lines.

[0068] The memory can be used to store the computer program and / or module. The processor implements various functions of the mobile terminal by running or executing the computer program and / or module stored in the memory and calling the data stored in the memory.

[0069] The memory may primarily include a program storage area and a data storage area. The program storage area may store the operating system and at least one application program required for a function (such as sound playback, image playback, etc.); the data storage area may store data created based on the use of the mobile phone (such as audio data, phonebook, etc.). Furthermore, the memory may include high-speed random access memory, and may also include non-volatile memory, such as hard disks, RAM, plug-in hard disks, SmartMediaCards (SMC), Secure Digital (SD) cards, FlashCards, at least one disk storage device, flash memory device, or other volatile solid-state storage devices.

[0070] Example 4 The present invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the steps of the method for verifying the life test results of a key component.

[0071] If the modules / units integrated in the mobile terminal are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium.

[0072] Based on this understanding, all or part of the processes in the above method can also be implemented by a computer program instructing related hardware. The computer program can be stored in a computer-readable storage medium. When executed by a processor, the computer program can implement the steps of the above-described aggregated reinforcement learning resource scheduling method. The computer program includes computer program code, which can be in the form of source code, object code, executable files, or some intermediate form.

[0073] The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording media, USB flash drive, portable hard drive, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium, etc.

[0074] It should be noted that the content contained in the computer-readable medium may be appropriately added to or subtracted from the content as required by the legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, the computer-readable medium may not include electrical carrier signals and telecommunication signals.

[0075] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A method for verifying the life test results of a key component, characterized in that, include: The flight conversion rate and cycle consumption between engine flight time and cycle number are obtained. The flight conversion rate is the ratio of cycle number to flight time. The flight conversion rate is distinguished between deterministic and indeterminate types depending on whether the engine is equipped with a cycle parameter recorder, and the corresponding deterministic value or distribution range of cycle consumption is obtained. Based on the deterministic flight conversion rate and cycle consumption, the test results of the key components equipped with cycle parameter recorders after use were analyzed, the verification predetermined safe cycle life of the components was calculated, and the preliminary verification results were obtained by comparing them with the standard cycle number given in the design. Based on the preliminary verification results, for the key components of engines that failed the preliminary verification or were equipped with cycle parameter recorders, a progressive analysis method was adopted, which included single-piece testing, multi-piece pre-test evaluation, multi-piece test result processing, and crack propagation life verification of the key components under random conditions. The verification threshold was calculated by combining the life divergence coefficient to complete the verification of the predetermined safe cycle life of the key components. Specifically, the single-piece test verification includes: Assume that the field usage time of the engine without a cycle parameter recorder when it returns to the factory is... T The distribution range of the number of cycles consumed [γ] min η max The corresponding minimum value expression is as follows: The maximum value expression is as follows: Where α is the test load factor; Let F be the predetermined number of safe loops to be verified. The total number of loops is expressed as follows: Where Y is the lifetime divergence coefficient; The number of test cycles required to meet the verification requirements is expressed as follows: Z1= - Among them, if the number of tester cycles obtained from the verification test N>Z 1, then allow the predetermined safety cycle number F; if N < Z 1. Then, perform supplementary testing using multiple test methods; The processing of multiple test results includes when - <N d < - At that time, arrange the second and subsequent tests; Let F be the predetermined number of safety cycles to be verified. The expression for the average number of test cycles that meets the verification requirements is as follows: Z d = - Calculate the geometric mean of the number of test cycles for the completed test pieces. If the number of test cycles for the second piece is N2, the expression for the geometric mean of the number of cycles for the first piece is as follows: like >Z d If, then the predetermined safety cycle number F is reached; if <Z d And N2 > the number of cycles for the first item, continue with the third item trial; if <Z d If N2 < the first cycle number, re-execute the pre-trial evaluation for multiple trials; The crack propagation life verification includes when - < N d < - At that time, the crack propagation life verification method was used for parts that did not show cracks; Let the predetermined number of safety cycles to be verified be . F The safe lifespan has been released. F 0, remaining lifespan is FF 0; Let the number of test cycles when the crack is detected be... Z 1. The number of test cycles at the end of the test is: Z 2. The number of test cycles used for crack propagation life calculation is: Z 1 -Z 2; The expression for crack propagation life is as follows: like Z L > F - F If 0, then the predetermined safety cycle number F is allowed; if Z L < F - F If the value is 0, the release lifespan will be shortened and sampling inspections will be tightened.

2. The method for verifying the life test results of a key component according to claim 1, characterized in that, The specific process for obtaining the flight conversion rate includes combining the number of cycles consumed during factory testing, the number of cycles consumed during actual flight, and the clipping factor. For engines equipped with a cycle parameter recorder, the flight conversion rate is a fixed value, and the corresponding number of cycles consumed by the parts after use is also a fixed value. For engines not equipped with a cycle parameter recorder, the flight conversion rate follows a log-normal distribution, with a distribution range of [-3σ, +3σ] and [γ]. min η max [, combined with engine field usage time] T The distribution range of the cycle consumption number in [-3σ, +3σ] is [γ]. min η max ].

3. The method for verifying the life test results of a key component according to claim 1, characterized in that, The analysis of test results for key components after use, specifically including: Assume the conversion rate for engine field flight equipped with a cyclic parameter recorder is [value missing]. E Take and use until T If an engine is tested for 24 hours with a test load factor of α, the expression for the number of cycles consumed is as follows: ； Let the number of cycles of the part testing machine after use be... N 2. The divergence coefficient is Y The verified predetermined safe cycle life is expressed as follows: = Among them, if F r1 If the number of cycles exceeds the standard cycle number given in the design, the safe life of the part can be extended to that standard cycle number; if F r1 If the number of cycles is less than the standard number given in the design, it will be processed according to the result analysis method under random conditions.

4. The method for verifying the life test results of a key component according to claim 1, characterized in that, The pre-test evaluation for multiple specimens specifically includes the following: the lifetime divergence coefficient decreases as the number of specimens increases, and when the number of specimens approaches infinity... Y =2.45, evaluated with 3 test specimens, this is the divergence coefficient corresponding to the minimum lifetime. Y min =2.71; Let the number of cycles for the first test piece be the minimum lifespan piece. Z 3. If Z 3 <N d <Z 1. Where Nd is the design-related cycle number threshold, and assuming that the first piece is the minimum lifespan piece, the number of subsequent test cycles is greater than Z3, then multiple piece tests are carried out; if the number of subsequent test cycles is less than Z3, then the smaller number of cycles is used as the minimum lifespan piece for re-evaluation; if the evaluation cannot verify the predetermined safe cycle life, then the release life is shortened and the sampling inspection is tightened.

5. A verification system for the life test results of key components, characterized in that, A method for verifying the life test results of a key component as described in any one of claims 1-4, comprising: The parameter acquisition module is used to acquire the flight conversion rate and cycle consumption between engine flight time and cycle number. The flight conversion rate is the ratio of cycle number to flight time. The conversion rate is distinguished between deterministic and indeterminate types depending on whether the engine is equipped with a cycle parameter recorder, and the corresponding definite value or distribution range of cycle consumption is obtained. The preliminary results analysis module is used to analyze the test results of key components equipped with cycle parameter recorders after use, based on the deterministic flight conversion rate and cycle consumption number, calculate the predetermined safe cycle life of the component, and compare it with the standard cycle number given in the design to obtain the preliminary verification results. The analysis result verification module is used to verify the predetermined safe cycle life of key components of engines that have not met the initial verification standards or are equipped with cycle parameter recorders, based on the preliminary verification results. It adopts a progressive analysis method, which includes single-piece testing, multi-piece pre-test evaluation, multi-piece test result processing, and crack propagation life verification of key components under random conditions. The verification threshold is calculated by combining the life divergence coefficient.

6. A mobile terminal, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the steps of the method for verifying the results of the life test of the key component as described in any one of claims 1-4.

7. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the steps of the method for verifying the results of the life test of the key component as described in any one of claims 1-4.

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