METHOD AND APPARATUS FOR LONG-TERM MONITORING OF STRESS CORROSION AND FATIGUE IN AN IN-SERVICE NUCLEAR TURBINE

Abstract

A method for long-term monitoring of stress corrosion cracking and fatigue in an in-service nuclear turbine includes: acquiring the crack depth of a monitoring component of the in-service nuclear turbine, and acquiring (S102) a crack propagation category for the component based on the crack depth; acquiring (S103) long-life monitoring data required by the monitoring component under different crack propagation categories; and performing (S104) lifetime crack propagation monitoring of the component based on the long-life monitoring data and the component's crack propagation category. FIG. 1

Description

Title of the invention: METHOD AND APPARATUS FOR LONG-TERM MONITORING OF STRESS CORROSION AND FATIGUE OF A NUCLEAR TURBINE IN SERVICE Technical field

[0001] The present disclosure relates to the field of in-service nuclear turbine technologies and, in particular, to a method and apparatus for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine, an electronic device, a storage medium and a platform. CONTEXT

[0002] As the energy shortage problem worsens, it becomes urgent to develop new energy to meet people's energy needs. Nuclear energy is a clean energy with no carbon dioxide emission and low environmental influence, an efficient energy with high energy density and low resource consumption, a stable energy with no intermittency, long usage hours and stable power supply capacity, and a safe energy with low accident probability, which is an important option for improving energy security. An in-service nuclear turbine is a key equipment in nuclear technology. According to the prior art, it is necessary to carry out safety monitoring over a crack propagation lifetime of the in-service nuclear turbine to ensure normal operation of the in-service nuclear turbine.However, the problem of stress corrosion is not considered in the safety monitoring over the crack propagation lifetime of the nuclear turbine in service. SUMMARY

[0003] According to a first aspect of the embodiments of the present disclosure, a method for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine is provided and comprises: acquiring a crack depth by phased array detection of a monitoring component of the in-service nuclear turbine, and acquiring a detected crack propagation category of the monitoring component based on the crack depth by phased array detection; acquiring long-life monitoring data required by the monitoring component under different crack propagation categories, the long-life monitoring data comprising a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life comprising at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life; and performing safety monitoring on a crack propagation life of the monitoring component on the basis of long-life monitoring data under the detected crack propagation category of the monitoring component acquired from the long-life monitoring data required by the monitoring component under different crack propagation categories.

[0004] According to a second aspect of the embodiments of the present disclosure, an apparatus for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine is provided and comprises: a first acquisition module configured to acquire a multi-element crack depth of a monitoring component of the in-service nuclear turbine, and acquire a detected crack propagation category of the monitoring component based on the multi-element crack depth;a second acquisition module configured to acquire long-life monitoring data required by the monitoring component under different crack propagation categories, the long-life monitoring data comprising a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life comprising at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life;and a monitoring module configured to perform safety monitoring of a crack propagation life of the monitoring component on the basis of the long life monitoring data under the detected crack propagation category of the monitoring component acquired from the long life monitoring data required by the monitoring component under different crack propagation categories.;

[0005] According to a third aspect of the embodiments of the present disclosure, an electronic device is provided and comprises a memory, a processor and a computer program stored in the memory and executable by the processor. The processor is configured to implement the method for long-term monitoring of stress corrosion and fatigue of the nuclear turbine in service as described in the first aspect of the embodiments of the present disclosure upon execution of the computer program.

[0006] According to a fourth aspect of the embodiments of the present disclosure, a A computer-readable storage medium having a computer program medium stored thereon is provided. The computer program is caused to implement the method for long-term monitoring of stress corrosion and fatigue of the in-service nuclear turbine as described in the first aspect of the embodiments of the present disclosure when executed by a processor.

[0007] According to a fifth aspect of the embodiments of the present disclosure, a monitoring platform suitable for an in-service nuclear turbine is provided, and comprises the long-term stress corrosion and fatigue monitoring apparatus of the in-service nuclear turbine as described in the second aspect of the embodiments of the present disclosure; or the electronic device as described in the third aspect of the embodiments of the present disclosure; or the computer-readable storage medium as described in the fourth aspect of the embodiments of the present disclosure.

[0008] The technical solution provided in the embodiments of the present disclosure provides at least the following beneficial effects. The multi-element detection crack depth of the monitoring component of the in-service nuclear turbine is acquired, and the detected crack propagation category of the monitoring component is acquired based on the multi-element detection crack depth.Long-life monitoring data required by the monitoring component under different crack propagation categories are acquired, wherein the long-life monitoring data includes a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life includes at least one of the low-cycle fatigue crack propagation life or the high-cycle fatigue crack propagation life. Safety monitoring is performed on the crack propagation life of the monitoring component on the basis of long-life monitoring data under the detected crack propagation category of the monitoring component.Therefore, safety monitoring can be carried out over the crack propagation life of the monitoring component considering stress corrosion and fatigue, to ensure long-term and safe operation of the nuclear turbine in service.

[0009] It should be noted that the details above and in the following are given by way of example and illustration, and do not constitute a limitation of the present disclosure. Brief description of the drawings

[0010] The above and / or other aspects and advantages of the present disclosure will become apparent and readily understood upon reading the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0011] [Fig. 1] is a process flow diagram illustrating a method for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine according to one embodiment of the present disclosure.

[0012] [Fig. 2] is a process flow diagram illustrating a method for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0013] [Fig. 3] is a process diagram illustrating the acquisition of a stress corrosion crack propagation lifetime in a long-term stress corrosion and fatigue monitoring method of an in-service nuclear turbine according to an embodiment of the present disclosure.

[0014] [Fig.4] is a process diagram illustrating the acquisition of a stress corrosion crack propagation lifetime in a long-term stress corrosion and fatigue monitoring method of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0015] [Fig. 5] is a process diagram illustrating the acquisition of a stress corrosion crack propagation lifetime in a long-term stress corrosion and fatigue monitoring method of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0016] [Fig. 6] is a process diagram illustrating the acquisition of a low-cycle fatigue crack propagation life in a long-term stress corrosion and fatigue monitoring method for an in-service nuclear turbine according to an embodiment of the present disclosure.

[0017] [Fig.7] is a process diagram illustrating the acquisition of a low cycle fatigue crack propagation life in a long-term stress corrosion and fatigue monitoring method for an in-service nuclear turbine according to another embodiment of the present disclosure.

[0018] [Fig.8] is a process diagram illustrating the acquisition of a low cycle fatigue crack propagation life in a long-term stress corrosion and fatigue monitoring method of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0019] [Fig.9] is a process diagram illustrating the acquisition of a low cycle fatigue crack propagation life in a long-term stress corrosion and fatigue monitoring method of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0020] [Fig. 10] is a process diagram illustrating the acquisition of a high-cycle fatigue crack propagation life in a long-term stress corrosion and fatigue monitoring method for an in-service nuclear turbine according to one embodiment of the present disclosure.

[0021] [Fig. 11] is a process flow diagram illustrating a method for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0022] [Fig. 12] is a process diagram illustrating the acquisition of a crack propagation calendar life in a long-term stress corrosion and fatigue monitoring method for an in-service nuclear turbine according to one embodiment of the present disclosure.

[0023] [Fig. 13] is a process diagram illustrating the acquisition of a crack propagation calendar life in a long-term stress corrosion and fatigue monitoring method for an in-service nuclear turbine according to another embodiment of the present disclosure.

[0024] [Fig. 14] is a process flow diagram illustrating a method for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0025] [Fig. 15] is a diagram illustrating a structure of a long-term stress corrosion and fatigue monitoring apparatus for an in-service nuclear turbine according to an embodiment of the present disclosure.

[0026] [Fig. 16] is a diagram illustrating a structure of an electronic device according to one embodiment of the present disclosure. DETAILED DESCRIPTION

[0027] Embodiments of the present disclosure are described in detail below, and exemplary embodiments are illustrated in the accompanying drawings, in which identical or similar references represent identical or similar elements or elements having identical or similar functions. The embodiments described below with reference to the drawings are examples, are intended to be configured to explain the present disclosure, and are not to be construed as a limitation of the present disclosure.

[0028] A method and apparatus for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine, an electronic device, a storage medium and a platform in embodiments of the present disclosure are described in combination with the accompanying drawings.

[0029] [Fig.l] is a process diagram illustrating a method for long-term monitoring of stress corrosion and fatigue of a nuclear turbine in service according to one embodiment of the present disclosure.

[0030] As illustrated in [Fig.l], the method for long-term monitoring of stress corrosion and fatigue of the nuclear turbine in service according to an embodiment of the present disclosure comprises the following steps.

[0031] In step S101, a crack depth by multi-element detection of a monitoring component of the nuclear turbine in service is acquired.

[0032] It should be noted that the method for long-term monitoring of stress corrosion and fatigue of the in-service nuclear turbine in embodiments of the present disclosure may be performed by an apparatus for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine in embodiments of the present disclosure, and the apparatus in embodiments of the present disclosure may be configured in any suitable monitoring platform for the in-service nuclear turbine, to implement the method for long-term monitoring of stress corrosion and fatigue of the in-service nuclear turbine in embodiments of the present disclosure.

[0033] Multi-element crack depth may refer to a depth of a crack in the monitoring component obtained by performing multi-element detection on the monitoring component. Multi-element detection may be implemented by any multi-element detection method of the related art.

[0034] In one implementation, acquiring the phased array crack depth of the monitoring component of the in-service nuclear turbine comprises: acquiring the phased array crack depth during phased array detection on the monitoring component by a phased array ultrasonic flaw detector and a phased array probe; and in response to no crack being found during the phased array detection on the monitoring component, setting the phased array crack depth to a predefined value. It should be noted that the predefined value is not limited and may be, for example, 0.002 m.

[0035] Taking, for example, a blade groove of a rotor as a monitoring component, the acquisition of a crack depth by multi-element detection of the blade groove of the rotor can be described as follows.

[0036] For example, 1000 MW in-service nuclear turbines A, B and C of a certain model can operate for 20 years. In a planned overhaul, non-destructive phased array detection and safety monitoring of the crack are performed on a fifth-stage inverted T-type blade groove of a No. 1 low-pressure rotor of an in-service nuclear turbine A, a groove of a fifth-stage inverted T-type blade groove of a No. 2 low-pressure rotor of an operating nuclear turbine B, and a fifth-stage inverted T-type blade groove of a No. 3 low-pressure rotor of an operating nuclear turbine C. The low-pressure rotor operates near a saturated steam line (Wilson) in a transition region of superheated steam and wet steam, and is prone to stress corrosion cracking. A material of the low-pressure rotor can be 30Cr2Ni4MoV (3.5% NiCrMoV). Non-destructive phased array detection can be performed on the fifth-stage blade groove of the No. 1 low-pressure rotor of the operating nuclear turbine A, and no cracks are found.In response to the fact that no crack was found in the phased array non-destructive detection, a depth of a crack in a load-bearing tooth surface of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the nuclear turbine A is defined as, for example, a; = 2 mm = 0.002 m.

[0037] Phased array non-destructive detection is performed on the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B, and a depth a; = 5 mm = 0.005 m of a crack in a load-bearing tooth surface of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is acquired.

[0038] Non-destructive monitoring is carried out on the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 3 of the in-service nuclear turbine C, and a depth a; = 10 mm = 0.010 m of a crack in a load-bearing tooth surface of the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 3 of the nuclear turbine C is acquired.

[0039] Taking, for example, a cylinder as a monitoring component, the acquisition of a crack depth by multi-element detection of the cylinder can be described as follows.

[0040] For example, 1000 MW in-service nuclear turbines A, B, and C of a certain model can operate for 20 years. In a planned overhaul, non-destructive phased array detection and safety monitoring of a crack are performed on a low-pressure inner cylinder No. 1 of in-service nuclear turbine A, a low-pressure inner cylinder No. 2 of in-service nuclear turbine B, a low-pressure inner cylinder No. 1 of in-service nuclear turbine C, and a low-pressure inner cylinder No. 2 of in-service nuclear turbine D. The low-pressure inner cylinder is made of, for example, a Q235B material and is prone to stress corrosion cracking in situations where NaOH is in the steam or seawater leaks from a condenser.For example, a short-life part of the low-pressure inner cylinder is a connecting part between the low-pressure inner cylinder and a steam extraction pipe. second stage. For example, a structural transition fillet radius at a structural discontinuity of the second stage steam extraction pipe and the low pressure inner cylinder is 20 mm. The part operates near a saturated steam (Wilson) line in a superheated steam and wet steam transition region, and is prone to stress corrosion cracking.

[0041] The non-destructive phased array detection can be performed on the low-pressure inner cylinder No. 1 of the operating nuclear turbine A, and no crack is found. In response to the fact that no crack was found in the non-destructive phased array detection, a depth of a crack in a connecting part between the low-pressure inner cylinder No. 1 of the operating nuclear turbine A and the second-stage steam extraction pipe is defined, for example, as a; = 2 mm = 0.002 m.

[0042] Multi-element non-destructive detection is carried out on the low pressure inner cylinder No. 2 of the nuclear turbine in service B, and a depth a; = 5 mm = 0.005 m of a crack in a connecting part between the low pressure inner cylinder No. 2 of the nuclear turbine in service B and the second stage steam extraction pipe is acquired.

[0043] Multi-element non-destructive detection is carried out on the low pressure inner cylinder No. 1 of the nuclear turbine in service C, and a depth a; = 5 mm = 0.005 m of a crack in a connecting part between the low pressure inner cylinder No. 1 of the operating nuclear turbine C and the second stage steam extraction pipe is acquired.

[0044] Multi-element non-destructive detection is carried out on the low pressure inner cylinder No. 2 of the nuclear turbine in service D, and a depth a; = 10 mm = 0.010 m of a crack in a connecting part between the low pressure inner cylinder No. 2 of the nuclear turbine in service D and the second stage steam extraction pipe is acquired.

[0045] In step S102, a detected crack propagation category of the monitoring component is acquired based on the crack depth acquired in step S101.

[0046] In one implementation, acquiring the detected crack propagation category of the monitoring component based on the multi-element crack depth comprises acquiring a predefined interval where the multi-element crack depth is located, and acquiring the detected crack propagation category of the monitoring component based on a mapping linking the predefined interval and the detected crack propagation category. It is understood that a plurality of predefined intervals may be classified in advance for the multi-element crack depths, and different in Predefined intervals can correspond to different crack propagation categories or the same crack propagation category.

[0047] For example, acquiring the detected crack propagation category of the monitoring component based on the multi-element crack depth comprises, in response to the multi-element crack depth being within a first predefined range, determining a first crack propagation category as the detected crack propagation category of the monitoring component, or in response to the multi-element crack depth being within a second predefined range, determining a second crack propagation category as the detected crack propagation category of the monitoring component.

[0048] In step S103, long-life monitoring data required by the monitoring component under different crack propagation categories are acquired. The long-life monitoring data includes a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life includes at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life.

[0049] It should be noted that stress corrosion crack propagation life refers to a crack propagation life in the monitoring component when a failure category supported by the monitoring component includes stress corrosion. Low cycle fatigue crack propagation life refers to a crack propagation life in the monitoring component when a failure category supported by the monitoring component includes low cycle fatigue. High cycle fatigue crack propagation life refers to a crack propagation life in the monitoring component when a failure category supported by the monitoring component includes high cycle fatigue.

[0050] It should be noted that the acquisition of the stress corrosion crack propagation life, the low cycle fatigue crack propagation life and the high cycle fatigue crack propagation life of the monitoring component can be implemented by adopting the related technique, which will not be limited in the disclosure.

[0051] In one implementation, acquiring the long life monitoring data required by the monitoring component under different crack propagation categories includes determining basic life data cor corresponding to a crack propagation category, and the acquisition of long-life monitoring data required by the monitoring component under the crack propagation category based on the basic life data.

[0052] It should be noted that the basic life data is not limited and may, for example, include a set of crack propagation sizes, basic stress calculation data of the monitoring component, basic material testing data, etc.

[0053] In one implementation, acquiring the long-life monitoring data required by the monitoring component under different crack propagation categories includes acquiring a map relating the crack propagation categories and the long-life monitoring data, and determining the long-life monitoring data required by the monitoring component under the crack propagation category based on the map. It is understood that the above relationship may be pre-calibrated based on an actual situation.

[0054] In one implementation, the method further comprises: determining that the long life monitoring data required by the monitoring component includes stress corrosion crack propagation life, low cycle fatigue crack propagation life, and high cycle fatigue crack propagation life in response to the monitoring component being a blade groove of a rotor; and determining that the long life monitoring data required by the monitoring component includes stress corrosion crack propagation life and low cycle fatigue crack propagation life in response to the monitoring component being a cylinder.

[0055] In step S104, safety monitoring is performed on a crack propagation lifetime of the monitoring component based on long-life monitoring data under the detected crack propagation category of the monitoring component.

[0056] In one implementation, performing the safety monitoring on the crack propagation life of the monitoring component based on the long life monitoring data under the detected crack propagation category of the monitoring component comprises implementing the safety monitoring on the crack propagation life of the monitoring component by determining whether the long life monitoring data under the detected crack propagation category of the monitoring component meets a monitoring acceptance condition.

[0057] It should be noted that the monitoring acceptance condition is not limited and, for example, it may be determined as a condition for monitoring acceptance that long-life monitoring data exceed a predefined threshold. The predefined threshold is not limited.

[0058] In one implementation, performing safety monitoring on the crack propagation life of the monitoring component based on the long life monitoring data under the detected crack propagation category of the monitoring component includes acquiring a monitoring criterion value of the monitoring component, and determining that the long life monitoring data under the detected crack propagation category of the monitoring component meets the monitoring acceptance condition in response to the long life monitoring data under the detected crack propagation category of the monitoring component being greater than or equal to the monitoring criterion value,and determining that the long life monitoring data under the detected crack propagation category of the monitoring component does not meet the monitoring acceptance condition in response to the long life monitoring data under the detected crack propagation category of the monitoring component being less than the monitoring criterion value.

[0059] In some examples, a mapping linking a model of the monitoring component and the monitoring criterion value may be pre-established. Acquiring the monitoring criterion value of the monitoring component includes requesting the monitoring criterion value in the above mapping based on the model of the monitoring component, and determining that the requested monitoring criterion value is the monitoring criterion value of the monitoring component.

[0060] In one implementation, in response to the long-life monitoring data under the detected crack propagation category of the monitoring component not meeting the monitoring criterion value, the method further comprises generating indication information indicating that a safety exception occurs in the monitoring component, and informing a user in time that the safety exception occurs in the monitoring component.

[0061] In summary, according to the long-life monitoring method of stress corrosion and fatigue of the in-service nuclear turbine provided in the embodiments of the present disclosure, the multi-element detection crack depth of the monitoring component of the in-service nuclear turbine is acquired, and the detected crack propagation category of the monitoring component is acquired based on the multi-element detection crack depth. The long-life monitoring data required by the monitoring component monitoring under different crack propagation categories are acquired, wherein the long-life monitoring data comprises a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life comprises at least one of the low-cycle fatigue crack propagation life or the high-cycle fatigue crack propagation life. Safety monitoring is performed on the crack propagation life of the monitoring component based on long-life monitoring data under the detected crack propagation category of the monitoring component.Therefore, safety monitoring can be carried out over the crack propagation life of the monitoring component considering stress corrosion and fatigue, to ensure long-term and safe operation of the nuclear turbine in service.

[0062] [Fig. 2] is a process diagram illustrating a method for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0063] As illustrated in [Fig.2], the method comprises the following steps.

[0064] In step S201, a crack depth by multi-element detection of a monitoring component of the nuclear turbine in service is acquired.

[0065] Step S201 can be explained with reference to the embodiments already described above, which will not be repeated here.

[0066] In step S202, a set of crack propagation sizes of the monitoring component is acquired.

[0067] It should be noted that the set of crack propagation sizes is not limited.

[0068] In one implementation, acquiring the crack propagation size set of the monitoring component comprises acquiring basic stress calculation data of the monitoring component, acquiring basic material test data of the monitoring component; and determining the crack propagation size set based on the basic stress calculation data and the basic material test data. Therefore, in the method, the crack propagation size set can be determined by taking into account the basic stress calculation data and the basic material test data.

[0069] It should be noted that the basic stress calculation data and the basic material test data are not limited.

[0070] In one implementation, determining the set of crack propagation sizes based on the basic stress calculation data and the basic data material testing includes the following possible implementations.

[0071] In a first implementation, a stress corrosion crack propagation size threshold value of the monitoring component is determined based on a crack shape parameter of the monitoring component, a stress corrosion fracture toughness of a material of the monitoring component, and a maximum stress at a crack location in the monitoring component under a steady-state, on-load operating condition of the in-service nuclear turbine.

[0072] In a second implementation, a critical low cycle fatigue crack size of the monitoring component under a predefined condition of the in-service nuclear turbine is determined based on the crack shape parameter of the monitoring component, the fracture toughness of the material of the monitoring component, and a maximum stress at the crack location in the monitoring component under the predefined condition of the in-service nuclear turbine.

[0073] In a third implementation, a high-cycle fatigue crack propagation size threshold value of the monitoring component is determined based on the crack shape parameter of the monitoring component, a test value of a high-cycle fatigue crack propagation threshold value of the material of the monitoring component, and a range of a high-cycle fatigue stress at a crack location in the monitoring component under a steady-state, on-load operating condition of the in-service nuclear turbine.

[0074] In a fourth implementation, a critical high-cycle fatigue crack size of the monitoring component is determined based on the crack shape parameter of the monitoring component, the fracture toughness of the monitoring component material, and a maximum stress at the crack location in the monitoring component under the steady-state, on-load operating condition of the in-service nuclear turbine.

[0075] Taking, for example, a blade groove of a rotor as a monitoring component, the acquisition of a set of crack propagation sizes of the blade groove of the rotor is described below.

[0076] For example, the basic stress calculation data includes a range of a high-cycle fatigue stress at the crack location in the rotor blade groove and a maximum stress at the crack location in the rotor blade groove under the steady-state condition of under-load operation of the nuclear turbine in service, a maximum stress crmaxn at the crack location in the blade groove of the rotor under the normal stop transient condition, a maximum stress 0^110% at the crack location in the rotor blade groove under the 110% overspeed test transient condition, and a maximum stress ^120% at the crack location in the rotor blade groove under the 120% overspeed test transient condition, etc.

[0077] For example, the basic rotor material test data includes a fracture toughness K1C of a rotor material, a stress corrosion fracture toughness KlsCc of the rotor material, a test value of an annual average stress corrosion crack propagation rate ( ~ ), a parameter Q of v dt ' SCC crack shape, and a test value of a high cycle fatigue crack propagation threshold value K^ of the rotor material, etc.

[0078] For example, the set of crack propagation sizes includes a threshold value of stress corrosion crack propagation size aScc, a threshold value of high cycle fatigue crack propagation size a*, a critical high cycle fatigue crack size acH, a critical low cycle fatigue crack size acn of the rotor blade groove in the transient condition of normal shutdown of the in-service nuclear turbine, a critical low cycle fatigue crack size acn0% of the rotor blade groove in a transient condition of 110% overspeed test of the in-service nuclear turbine and a critical low cycle fatigue crack size aci20% of the rotor blade groove in a transient condition of 120% overspeed operation of the in-service nuclear turbine, etc.

[0079] In some examples, determining the set of crack propagation sizes based on the basic stress calculation data and the basic rotor material test data includes the following possible implementations.

[0080] In a first implementation, the threshold value of stress corrosion crack propagation size of the rotor blade groove is determined based on the crack shape parameter of the rotor blade groove, the stress corrosion fracture toughness of the rotor material and the maximum stress at the crack location in the rotor blade groove under a steady state condition of on-load operation of the nuclear turbine in service.

[0081] In a second implementation, the high cycle fatigue crack propagation size threshold value of the rotor blade groove is determined based on the crack shape parameter of the rotor blade groove, the high cycle fatigue crack propagation threshold value test value, and the range of the high cycle fatigue stress at the crack location in the rotor blade groove under the stationary condition. operating load of the nuclear turbine in service.

[0082] In a third implementation, the high cycle critical fatigue crack size of the rotor blade groove is determined based on the crack shape parameter of the rotor blade groove, the fracture toughness of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the steady state under-load operating condition of the nuclear turbine in service.

[0083] In a fourth implementation, the critical low-cycle fatigue crack size of the rotor blade groove under the transient normal shutdown condition of the in-service nuclear turbine is determined based on the crack shape parameter of the rotor blade groove, the fracture toughness of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the transient normal shutdown condition of the in-service nuclear turbine.

[0084] In a fifth implementation, the critical low cycle fatigue crack size of the rotor blade groove under the 110% overspeed transient test condition of the in-service nuclear turbine is determined based on the crack shape parameter of the rotor blade groove, the fracture toughness of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the 110% overspeed transient test condition of the in-service nuclear turbine.

[0085] In a sixth implementation, the critical low cycle fatigue crack size of the rotor blade groove under the transient 120% overspeed operating condition of the in-service nuclear turbine is determined based on the crack shape parameter of the rotor blade groove, the fracture toughness of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the transient 120% overspeed operating condition of the in-service nuclear turbine.

[0086] For example, taking the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 1 of the in-service nuclear turbine A, the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 2 of the in-service nuclear turbine B, and the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 3 of the in-service nuclear turbine C, for example, the basic stress calculation data and the basic rotor material test data of the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 1 of the in-service nuclear turbine A are respectively shown in Table 1 and Table 2, the basic stress calculation data and the basic rotor material test data of the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 2 of the in-service nuclear turbine B are respectively shown in Table 1 and Table 2. in Table 1 and Table 2, and the basic stress calculation data and basic rotor material test data of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C are respectively shown in Table 1 and Table 2.

[0087] Table 1. Basic stress calculation data of a fifth-stage inverted T-type blade groove of a low-pressure rotor of an in-service nuclear turbine No. Item Data Value 1 Range ( ~ ) / MPa of a large fatigue stress k dt / scc Number of cycles at a crack location in a blade groove of a rotor under a steady state condition of loaded operation 3.078 2 Maximum stress crmaxH / MPa at a crack location in a blade groove of a rotor under a steady state condition of loaded operation 436.299 3 Maximum stress amaxn / MPa at a weld location on a surface of a rotor under a transient condition of normal stop 457.918 4 Maximum stress crmaxn0% / MPa at a crack location of a blade groove of a rotor under a transient condition of 110% overspeed test 481.019 5 Maximum stress omaxi2o% / MPa at a crack location of a blade groove of a rotor under a transient condition 120% overspeed operating 577.005

[0088] Table 2. Basic material test data of a low-pressure rotor of an in-service nuclear turbine No. Item Data Value 1 fracture toughness Klc / MPa( ) of a rotor material 190 2 stress corrosion fracture toughness K1Scc / MPa[di ] of a ' dt ' SCC rotor material 76 3 test value [ — 'l / mm / a of an annual average stress corrosion crack propagation rate clt 2 SCC 2 4 crack shape parameter Q steady state: 0.99976 normal shutdown: 0.98684 110% overspeed test: 0.97481 120% overspeed operation: 0.92580 5 high cycle fatigue crack propagation threshold value f due 1 / MPa \ of a material dt ' SCC ' dt ' SCC of a rotor 0.9224

[0089]

[0090]

[0091]

[0092]

[0093]

[0094]

[0095]

[0096]

[0097] The maximum stress at the rotor blade groove crack location under the normal stop transient condition includes the maximum stress crmaxn at the weld location on the rotor surface under the normal stop transient condition. A method for calculating a set of crack propagation sizes of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A, the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B, and the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is as follows: «sec = = i.SX- = 0.007980m = 7.980mm ““ y maxH _ 0(4¾)2 _ q.99976x0.92242 th 1.21^^ L2brx3.078~ = 0.023619ma ​​_ QKic _ Q99976X1902 -0.049877m eH f .21-X436.2992 a _ QKp _ 0.98684x1902 = 0.044693m ' in i.21^o-2iasn 1.21nx457.9182 ' ,, - QK'C - 0.97481X1902 -0 04001m cllUA 1.2177x481.019" _ QKîc _ 0.92580X1902 - 0 07641m — inio — — V Ifl l cl2(.> / c 1.21™^^. 1.21^x577.005" Taking, for example, a cylinder as a monitoring component, the acquisition of a set of crack propagation sizes of the cylinder is described below.

[0098] For example, the basic stress calculation data includes a maximum stress crmax0 at a crack location in the cylinder under the steady state load operating condition of the in-service nuclear turbine, a maximum stress crmaxc at the crack location in the cylinder under a transient cold start condition, a maximum stress crmaxw at the crack location in the cylinder under a transient warm start condition of the in-service nuclear turbine, a maximum stress crmaxh at the crack location in the cylinder under a transient hot start condition of the in-service nuclear turbine, etc.

[0099] For example, the basic material test data includes a fracture toughness K1C of a cylinder material, a stress corrosion fracture toughness KlsCc of the cylinder material, a test value ( — ) of an average rate v dt 7 SCC annual stress corrosion crack propagation rate, a crack shape parameter Q, etc.

[0100] For example, the set of crack propagation sizes includes a threshold value of stress corrosion crack propagation size aSCc, a critical low-cycle fatigue crack size acc of the cylinder in the transient cold start condition of the in-service nuclear turbine, a critical low-cycle fatigue crack size acw of the cylinder in the transient warm start condition of the in-service nuclear turbine, a critical low-cycle fatigue crack size ach of the cylinder in the transient hot start condition of the in-service nuclear turbine.

[0101] In some examples, determining the set of crack propagation sizes based on the basic stress calculation data and the basic material test data includes the following possible implementations.

[0102] In a first implementation, a threshold value of cylinder stress corrosion crack propagation size is determined based on a cylinder crack shape parameter, a stress corrosion fracture toughness of the cylinder material, and the maximum stress at the crack location in the cylinder under a steady-state, on-load operating condition of the in-service nuclear turbine.

[0103] In a second implementation, the critical low cycle fatigue crack size of the cylinder under the transient cold start condition of the in-service nuclear turbine is determined based on the crack shape parameter of the cylinder, the fracture toughness of the cylinder material, and the maximum stress at the crack location in the cylinder under the transient cold start condition of the in-service nuclear turbine.

[0104] In a third implementation, the critical low cycle fatigue crack size of the cylinder under the warm start transient condition of the in-service nuclear turbine is determined based on the crack shape parameter of the cylinder, the fracture toughness of the cylinder material, and the maximum stress at the crack location in the cylinder under the warm start transient condition of the in-service nuclear turbine.

[0105] In a fourth implementation, the critical low cycle fatigue crack size of the cylinder under the transient hot start condition of the in-service nuclear turbine is determined based on the crack shape parameter of the cylinder, the fracture toughness of the cylinder material, and the maximum stress at the crack location in the cylinder under the transient hot start condition of the in-service nuclear turbine.

[0106] For example, taking the low-pressure inner cylinder No. 1 of the in-service nuclear turbine A, the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B, the low-pressure inner cylinder No. 1 of the in-service nuclear turbine C and the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D for example, the basic stress calculation data and the basic material test data of the low-pressure inner cylinder No. 1 of the in-service nuclear turbine A are respectively shown in Table 3 and Table 4, the basic stress calculation data and the basic material test data of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B are respectively shown in Table 3 and Table 4, the basic stress calculation data and the basic material test data of the low-pressure inner cylinder No.1 of the in-service nuclear turbine C are respectively shown in Table 3 and Table 4, and the basic stress calculation data and basic material test data of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D are respectively shown in Table 3 and Table 4.

[0107] Table 3. Basic data for calculating low pressure internal cylinder stress No. Item Data Value 1 Maximum stress œmaxo / MPa at a crack location in a cylinder under steady state load operating condition 229.120 2 Maximum stress maxc / MPa at a crack location in a cylinder under transient cold start condition 252.970 3 Maximum stress crmaxw / MPa at a location 267.093 of crack in a cylinder under a warm start transient condition 4 maximum stress crmaxh / MPa at a crack location in a cylinder under a hot start transient condition 237.736

[0108]

[0109]

[0110] [YES]

[0112]

[0113]

[0114]

[0115] Table 4. Basic material test data of a low-pressure inner cylinder No. Item Data Value 1 Fracture toughness Kæ / MPa^j" of a cylinder material 108.23 2 Stress corrosion fracture toughness K1Scc / MPa ^7 4'of a cylinder material 43.29 3 Crack shape parameter Q 0.88 4 Test value f 4s> 1 / mm / a of an annual average rate of pro-V dt / scc paging of stress corrosion cracking of a cylinder material 1.5 A method for calculating a set of crack propagation sizes of the low-pressure inner cylinder No. 1 of the operating nuclear turbine A, the low-pressure inner cylinder No. 2 of the operating nuclear turbine B, the low-pressure inner cylinder No. 1 of the operating nuclear turbine C, and the low-pressure inner cylinder No. 2 of the operating nuclear turbine D can be described as follows: a scc = = _ o 008264m = 8.264mm 1.2173-0-^0 1.2Ltx229.12- “cc = ......= = 0.042375m - 42.375mm 1.21™^ I2I.tx252.970-- = 0.038012m = 38.012mm 1.^,17F(7niaxVv> J 2. 1 / 7x2 67.093^ «ch = ......= = 0.047979m = 47.979mm vil 1.2 1.21TTX237.736- In step S203, the detected crack propagation category of the monitoring component is acquired on the basis of the crack depth by multi-element detection and the crack propagation size set. In one implementation, acquiring the detected crack propagation category of the monitoring component based on the phased array crack depth and the crack propagation size set includes obtaining an operation result by performing operation processing on the phased array crack depth and a crack propagation size of crack in the crack propagation size set, and obtaining the detected crack propagation category based on a correspondence between the operation result and the detected crack propagation category. The operation processing may be performed by adopting at least one operation processing method of the related art, which is not limited herein, and may for example include addition, subtraction, multiplication, division, etc.

[0116] In one implementation, acquiring the detected crack propagation category of the monitoring component based on the multi-element crack depth and the set of crack propagation sizes includes acquiring a size relationship between the multi-element crack depth and at least one crack propagation size in the set of crack propagation sizes; and determining the detected crack propagation category of the monitoring component based on a correspondence between the size relationship and the crack propagation category.

[0117] Taking, for example, a blade groove of a rotor as a monitoring component, the acquisition of a detected crack propagation category of the blade groove of the rotor is described below.

[0118] In some examples, acquiring the detected crack propagation category of the rotor blade groove based on the phased array crack depth and the set of crack propagation sizes includes the following possible implementations:

[0119] In a first implementation, the detected crack propagation category is determined as a first crack propagation category in response to the multi-element crack depth being less than the stress corrosion crack propagation size threshold value and the stress corrosion crack propagation size threshold value being less than the high cycle fatigue crack propagation size threshold value.

[0120] In some examples, the detected crack propagation category is the first crack propagation category, and the first crack propagation category may comprise three phases. In this case, in a first phase, a crack size of the rotor blade groove is expanded from a phased array crack depth a; to a threshold stress corrosion crack propagation size value aSCc- In a second phase, the crack size of the rotor blade groove is expanded from a threshold stress corrosion crack propagation size value aScc to a threshold high cycle fatigue crack propagation size value a*. In a third phase, the crack size of the rotor blade groove is expanded from the threshold high cycle fatigue crack propagation size value ath up to a low cycle fatigue critical crack size acj. The low cycle fatigue critical crack size acj can be acn or acn0% or aci20%.

[0121] In a second implementation, the detected crack propagation category is determined as a second crack propagation category in response to the stress corrosion crack propagation size threshold value being less than the multi-element detection crack depth and the multi-element detection crack depth being less than the high cycle fatigue crack propagation size threshold value.

[0122] In some examples, the detected crack propagation category is the second crack propagation category, and the second crack propagation category may comprise two phases. In this case, in a first phase, the rotor blade groove crack size is expanded from the phased array crack depth a; to the high cycle fatigue crack propagation size threshold value a*. In a second phase, the rotor blade groove crack size is expanded from the high cycle fatigue crack propagation size threshold value a* to the low cycle fatigue critical crack size acj.

[0123] In a third implementation, the detected crack propagation category is determined as a third crack propagation category in response to the phased array crack depth being less than the high cycle fatigue crack propagation size threshold value and the high cycle fatigue crack propagation size threshold value being less than the stress corrosion crack propagation size threshold value.

[0124] In some examples, the detected crack propagation category is the third crack propagation category, and the third crack propagation category may comprise three phases. In this case, in a first phase, the crack size of the rotor blade groove is expanded from the multi-element crack depth a; to the high-cycle fatigue crack propagation size threshold value a*.In a second phase, the rotor blade groove crack size is extended from the high cycle fatigue crack propagation size threshold value ath to the stress corrosion crack propagation size threshold value aSCc- In a third phase, the rotor blade groove crack size is extended from the stress corrosion crack propagation size threshold value aScc to the low cycle fatigue critical crack size acj. .

[0125] In a fourth implementation, the detected crack propagation category is determined as a fourth crack propagation category in response to the that the threshold value of high-cycle fatigue crack propagation size is less than the multi-element crack depth and that the multi-element crack depth is less than the threshold value of stress corrosion crack propagation size.

[0126] In some examples, the detected crack propagation category is the fourth crack propagation category, and the fourth crack propagation category may comprise two phases. In this case, in a first phase, the rotor blade groove crack size is expanded from the phased array crack depth a; to the stress corrosion crack propagation size threshold value aSCc- In a second phase, the rotor blade groove crack size is expanded from the stress corrosion crack propagation size threshold value aSCc to the low cycle fatigue critical crack size acj.

[0127] For example, taking the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A, the stress corrosion crack propagation size threshold value aScc is 0.007980 m, the high-cycle fatigue crack propagation size threshold value a* is 0.023619 m, and the non-destructive phased array crack depth a; is 0.002 m. Since aScc = 0.007980 m is less than ath = 0.023619 m and a; = 0.002 m is less than aScc = 0.007980 m, the crack propagation category detected in the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is the first crack propagation category.

[0128] For example, taking the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B, the stress corrosion crack propagation size threshold value aSCc is 0.007980 m, the high-cycle fatigue crack propagation size threshold value ath is 0.023619 m, and the non-destructive phased array crack depth a; is 0.005 m. Since aSCc = 0.007980 m is smaller than ath = 0.023619 m and a; = 0.005 m is smaller than aSCc = 0.007980 m, the crack propagation category detected in the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is the first crack propagation category.

[0129] For example, taking the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C, the stress corrosion crack propagation size threshold value aScc is 0.007980 m, the high-cycle fatigue crack propagation size threshold value a* is 0.023619 m, and the crack depth by phased array detection not destructive a; is 0.010 m. Since aSCc = 0.007980 m is less than a* = 0.023619 m and a; = 0.010m is greater than aSCc = 0.007980 m, the crack propagation category detected in the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 3 of the in-service nuclear turbine C is the second crack propagation category.

[0130] Taking, for example, a cylinder as a monitoring component, the acquisition of a detected crack propagation category of the cylinder is described below.

[0131] In some examples, acquiring the detected crack propagation category of the cylinder based on the multi-element crack depth and the set of crack propagation sizes includes the following possible implementations.

[0132] In a first implementation, the detected crack propagation category is determined as a first crack propagation category in response to the multi-element crack depth being less than the stress corrosion crack propagation size threshold value.

[0133] In some examples, the detected crack propagation category is the first crack propagation category, and the first crack propagation category may comprise two phases. In this case, in a first phase, the crack size of the cylinder is expanded from the phased array crack depth a; to the stress corrosion crack propagation size threshold value aSCc. In a second phase, the crack size of the cylinder is expanded from the stress corrosion crack propagation size threshold value aSCc to the low cycle fatigue critical crack size acj. The low cycle fatigue critical crack size acj may be acn or acw or ach.

[0134] In a second implementation, the detected crack propagation category is determined as a second crack propagation category in response to the multi-element crack depth being greater than the stress corrosion crack propagation size threshold value.

[0135] In some examples, the detected crack propagation category is the second crack propagation category, and the second crack propagation category may comprise a phase. In a first phase, a crack size of the cylinder is extended from the phased array crack depth a; to the critical low-cycle fatigue crack size acj.

[0136] For example, taking the low-pressure inner cylinder No. 1 of the in-service nuclear turbine A, the threshold value of stress corrosion crack propagation size aScc is 0.008624 m, and the crack depth by non-destructive phased array detection a; is 0.002 m. Since a; = 0.002 m is less than aScc = 0.008624 m, the detected crack propagation category of the low pressure inner cylinder No. 1 of the in-service nuclear turbine A is the first crack propagation category.

[0137] For example, taking the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B, the threshold value of stress corrosion crack propagation size aSCc is 0.008624 m, and the crack depth by non-destructive multi-element detection a; is 0.005 m. Since a; = 0.005 m is smaller than aSCc = 0.008624 m, a detected crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B is the first crack propagation category.

[0138] For example, taking the low-pressure inner cylinder No. 1 of the in-service nuclear turbine C, the threshold value of stress corrosion crack propagation size aSCc is 0.008624 m, and the crack depth by non-destructive multi-element detection a; is 0.005 m. Since a; = 0.005 m is smaller than aScc = 0.008624 m, a detected crack propagation category of the low-pressure inner cylinder No. 1 of the in-service nuclear turbine C is the first crack propagation category.

[0139] For example, taking the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D, the threshold value of stress corrosion crack propagation size aScc is 0.008624 m, and the crack depth by non-destructive multi-element detection a; is 0.010 m. Since a; = 0.010 m is larger than aSCc = 0.008624 m, a detected crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is the second crack propagation category.

[0140] In step S204, long-life monitoring data required by the monitoring component under different crack propagation categories are acquired. The long-life monitoring data includes a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life includes at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life.

[0141] In step S205, safety monitoring is performed on a crack propagation lifetime of the monitoring component on the basis of long-life monitoring data under the detected crack propagation category of the monitoring component.

[0142] Steps S204 and S205 can be explained with reference to the embodiments already described previously, which will not be repeated here.

[0143] In summary, according to the long-term monitoring method of stress corrosion and fatigue of the in-service nuclear turbine in embodiments of the present disclosure, the crack propagation size set of the monitoring component is acquired, and the detected crack propagation category of the monitoring component is acquired on the basis of the crack depth by multi-element detection and the crack propagation size set. Therefore, the detected crack propagation category of the monitoring component can be obtained by taking into account the crack depth by multi-element detection and the crack propagation size set of the monitoring component.

[0144] Based on any embodiment above, acquiring stress corrosion crack propagation lifetimes under different crack propagation categories comprises: acquiring the stress corrosion crack propagation lifetimes under the different crack propagation categories based on a first parameter of the monitoring component, a test value of an annual average stress corrosion crack propagation rate of the material of the monitoring component, and the critical low-cycle fatigue crack size of the monitoring component under the predefined condition of the nuclear turbine in service. The first parameter is the crack depth by phased array detection or the stress corrosion crack propagation size threshold value.Therefore, in the method, the stress corrosion crack propagation lifetimes under different crack propagation categories can be determined by considering the first parameter of the monitoring component, the test value of the annual average stress corrosion crack propagation rate of the monitoring component material, and the low cycle fatigue critical crack size of the monitoring component under the preset condition of the in-service nuclear turbine.

[0145] In one implementation, determining stress corrosion crack propagation lifetimes under different crack propagation categories based on the first parameter of the monitoring component, the test value of the annual average stress corrosion crack propagation rate of the monitoring component material, and the low cycle fatigue critical crack size of the monitoring component under the predefined condition of the in-service nuclear turbine includes determining a plurality of types of stress corrosion crack propagation lifetimes in any crack propagation category based on the first parameter of the monitoring component, the test value of the annual average stress corrosion crack propagation rate of the monitoring component material, and the size of critical low-cycle fatigue crack of the monitoring component under the predefined condition of the nuclear turbine in service; and determining a stress corrosion crack propagation life under any crack propagation category based on the plurality of types of stress corrosion crack propagation lives under any crack propagation category.

[0146] In some examples, determining stress corrosion crack propagation lifetimes of the monitoring component under any crack propagation category based on the plurality of types of stress corrosion crack propagation lifetimes of the monitoring component under any crack propagation category includes determining a minimum value in the plurality of types of stress corrosion crack propagation lifetimes under any crack propagation category as a stress corrosion crack propagation lifetime under any crack propagation category.

[0147] Taking, for example, a blade groove of a rotor as a monitoring component, the acquisition of stress corrosion crack propagation lifetimes under different crack propagation categories is described below.

[0148] Based on any embodiment above, when the monitoring component is the rotor blade groove, as illustrated in [Fig.3], acquiring stress corrosion crack propagation lifetimes under different crack propagation categories may comprise the following steps.

[0149] In step S301, a stress corrosion crack propagation life under any one of the first crack propagation category, the third crack propagation category, or the fourth crack propagation category is acquired based on a threshold value of stress corrosion crack propagation size, a test value of an annual average stress corrosion crack propagation rate of the rotor material, and the critical low-cycle fatigue crack size of the rotor blade groove under the transient condition of normal shutdown of the nuclear turbine in service.

[0150] In step S302, a stress corrosion crack propagation life under the second crack propagation category is acquired on the basis of the crack depth by phased array detection, the test value of the annual average stress corrosion crack propagation rate of the rotor material, and the critical low-cycle fatigue crack size of the rotor blade groove under the transient condition of normal shutdown of the nuclear turbine in service.

[0151] In one implementation, a method of calculating the propagation lifetime of

[0152]

[0153]

[0154]

[0155]

[0156]

[0157]

[0158] stress corrosion cracking in any of the first crack propagation category, the third crack propagation category or the fourth crack propagation category is as follows: N —M —N — “^scc ■v fSCCl“iNfSCC3 ~ fSCC4 ~ j Bed <Sœ where, Nfscci is a stress corrosion crack propagation life under the first crack propagation category, NfScc2 is a stress corrosion crack propagation life under the third crack propagation category, and NfScc4 is a stress corrosion crack propagation life under the fourth crack propagation category. In one implementation, a method for calculating the stress corrosion crack propagation life Nfscc2 under the second crack propagation category is as follows: j «cn-a, ÏVfSCC2- ' <1' Iscc For example, taking the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A and the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A and the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is the first crack propagation category. The calculation method of the stress corrosion crack propagation life Nfscc under the first crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A and the fifth-stage inverted T-type blade groove of the No.2 of the nuclear turbine in service B is as follows: . N - ±£±£L _ 44.693-7.980 _ io ■ ^fscci — / <ia \ — ? — lo.do cuviëës tdïlscc For example, taking the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is the second crack propagation category. The calculation method of the stress corrosion crack propagation life Nfscc2 under the second crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the nuclear turbine in service C is as follows:

[0159] jyfSCC2 = = ^£62340 = ] 7.35 years \ dt /

[0160] Therefore, in this method, when the monitoring component is the rotor blade groove, the stress corrosion crack propagation life under any one of the first crack propagation category, the third crack propagation category or the fourth crack propagation category can be acquired by taking into account the threshold value of stress corrosion crack propagation size, the test value of the annual average stress corrosion crack propagation rate of the rotor material, and the critical low-cycle fatigue crack size of the rotor blade groove under the transient condition of normal shutdown of the nuclear turbine in service, and the stress corrosion crack propagation life under the second crack propagation category can be acquired by taking into account the crack depth by phased array detection,the test value of the annual average stress corrosion crack propagation rate of the rotor material and the critical low-cycle fatigue crack size of the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine. Taking a cylinder as a monitoring component, the acquisition of stress corrosion crack propagation lifetimes under different crack propagation categories is described below.

[0161] Based on any embodiment above, when the monitoring component is the cylinder, as illustrated in [Fig.4], acquiring the stress corrosion crack propagation life under a first crack propagation category comprises the following steps.

[0162] In step S401, a first type of stress corrosion crack propagation life under the first crack propagation category is acquired on the basis of the threshold value of stress corrosion crack propagation size, the test value of the annual average stress corrosion crack propagation rate of the cylinder material, and the critical low cycle fatigue crack size of the cylinder under the transient cold start condition of the in-service nuclear turbine.

[0163] In one implementation, a method for calculating the first type of stress corrosion crack propagation life Nfscci.is°us the first category of crack propagation is expressed as follows: [OW] ' * Acc

[0165] In step S402, a second type of crack propagation lifetime by Stress corrosion cracking under the first crack propagation category is acquired based on the threshold value of stress corrosion crack propagation size, the test value of the annual average stress corrosion crack propagation rate of the cylinder material, and the critical low-cycle fatigue crack size of the cylinder under the transient warm start condition of the in-service nuclear turbine.

[0166] In one implementation, a method for calculating the second type of stress corrosion crack propagation life NfScci,2 under the first crack propagation category is expressed as follows: [01671 N - ^'^scc 1 u JA fScc 1.2 “ 7777 dry

[0168] In step S403, a third type of stress corrosion crack propagation life under the first crack propagation category is acquired based on the threshold value of stress corrosion crack propagation size, the test value of the annual average stress corrosion crack propagation rate of the cylinder material, and the critical low cycle fatigue crack size of the cylinder under the transient hot start condition of the in-service nuclear turbine.

[0169] In one implementation, a method for calculating the third type of stress corrosion crack propagation life NfScci,3 under the first category of crack propagation is as follows: [°17°] MSCC1,3 = S^ \ dï / ,^cc

[0171] In step S404, the stress corrosion crack propagation life under the first crack propagation category is determined on the basis of the first type of stress corrosion crack propagation life under the first crack propagation category, the second type of stress corrosion crack propagation life under the first crack propagation category, and the third type of stress corrosion crack propagation life under the first crack propagation category.

[0172] In one implementation, determining the stress corrosion crack propagation life under the first crack propagation category based on the first type of stress corrosion crack propagation life under the first crack propagation category, the second type of stress corrosion crack propagation life under the first crack propagation category, and the third type of stress corrosion crack propagation life under the first category crack propagation includes obtaining the stress corrosion crack propagation life under the first crack propagation category by performing a weighted average of the first type of stress corrosion crack propagation life under the first crack propagation category, the second type of stress corrosion crack propagation life under the first crack propagation category and the third type of stress corrosion crack propagation life under the first crack propagation category.

[0173] In one implementation, determining the stress corrosion crack propagation life under the first crack propagation category based on the first type of stress corrosion crack propagation life under the first crack propagation category, the second type of stress corrosion crack propagation life under the first crack propagation category, and the third type of stress corrosion crack propagation life under the first crack propagation category includes determining a minimum value of the first type of stress corrosion crack propagation life under the first crack propagation category,of the second type of stress corrosion crack propagation life under the first crack propagation category and of the third type of stress corrosion crack propagation life under the first crack propagation category as stress corrosion crack propagation life under the first crack propagation category.,

[0174] For example, a method for calculating the stress corrosion crack propagation life NfSccoi under the first crack propagation category is expressed as follows:

[0175] Nfsccoi ~ min{ / Vfscci.b fsœt,2> Nfsccij}

[0176] For example, taking the low-pressure inner cylinder No. 1 of the operating nuclear turbine A, the low-pressure inner cylinder No. 2 of the operating nuclear turbine B and the low-pressure inner cylinder No. 1 of the operating nuclear turbine C, the detected crack propagation category of the low-pressure inner cylinder No. 1 of the operating nuclear turbine A, the low-pressure inner cylinder No. 2 of the operating nuclear turbine B and the low-pressure inner cylinder No. 1 of the operating nuclear turbine C is the first crack propagation category. A method for calculating the stress corrosion crack propagation life Nfsccoi under the first crack propagation category of the low-pressure inner cylinder No. 1 of the operating nuclear turbine A, the low-pressure inner cylinder No. 2 of the operating nuclear turbine B and the low-pressure inner cylinder pressure No. 1 of the nuclear turbine in service C can be expressed as follows: t0177l AT «œ^scc 42.375-8.264 ni 741 LU 1 / / J 2V fSCC 1,1 = 7^7.......= —73— = 22.741 years

[0178] ? / fSCC£2 = = - 19.832 years ' dt <scc

[0179] ^cci 3 = 77“- = = 26,477 years ( * ) scc

[0180] A^fSCcoi= min{Msœi.h ^fscci.2' Mscci.3} = min{22.741,19.832,26.477} = 19.832year5

[0181] Therefore, in the method, when the monitoring component is the cylinder, the first stress corrosion crack propagation life to the third stress corrosion crack propagation life under the first crack propagation category are acquired by taking into account the threshold value of stress corrosion crack propagation size, the test value of the annual average stress corrosion crack propagation rate of the cylinder material, and the critical crack size by low cycle fatigue, and the stress corrosion crack propagation life under the first crack propagation category is further determined.

[0182] Based on any embodiment above, when the monitoring component is a cylinder, as illustrated in [Fig.5], acquiring a stress corrosion crack propagation lifetime under a second crack propagation category may comprise the following steps.

[0183] In step S501, a first type of stress corrosion crack propagation life under the second crack propagation category is acquired on the basis of the crack depth by phased array detection, the test value of the annual average stress corrosion crack propagation rate of the cylinder material, and the critical low-cycle fatigue crack size of the cylinder under the transient cold start condition of the in-service nuclear turbine.

[0184] In one implementation, a method for calculating the first type of stress corrosion crack propagation lifetime NfScc2,i under the second crack propagation category can be expressed as follows: [°1851 ^2.1 = 7^

[0186] In step S502, a second type of stress corrosion crack propagation life under the second crack propagation category is acquired on the basis of the crack depth by phased array detection, the test value of the annual average stress corrosion crack propagation rate of the cylinder material, and the critical low-cycle fatigue crack size of the cylinder under the warm start transient condition of the nuclear turbine in

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[0188]

[0189]

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[0193] service. In one implementation, a method for calculating the second type of stress corrosion crack propagation life NfScc2,2 under the second crack propagation category can be expressed as follows: 2x0.5 In step S503, a third type of crack propagation lifetime by Stress corrosion cracking under the second crack propagation category is acquired based on the crack depth by multi-element detection, the test value of the annual average stress corrosion crack propagation rate of the cylinder material, and the critical low-cycle fatigue crack size of the cylinder under the transient hot start condition of the in-service nuclear turbine. In one implementation, a method for calculating the third type of stress corrosion crack propagation life NfScc2,3 under the second crack propagation category can be expressed as follows: N fnl.2 “ 2x0.5 maxn 1___1. ,r'^. lit flstc «ni In step S504, the stress corrosion crack propagation life under the second crack propagation category is determined on the basis of the first type of stress corrosion crack propagation life under the second crack propagation category, the second type of stress corrosion crack propagation life under the second crack propagation category, and the third type of stress corrosion crack propagation life under the second crack propagation category. In one implementation, determining the stress corrosion crack propagation life under the second crack propagation category based on the first type of stress corrosion crack propagation life under the second crack propagation category, the second type of stress corrosion crack propagation life under the second crack propagation category, and the third type of stress corrosion crack propagation life under the second crack propagation category may include obtaining the stress corrosion crack propagation life under the second crack propagation category by performing a weighted average of the first type of stress corrosion crack propagation life under the second crack propagation category.

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[0199]

[0200]

[0201] of crack propagation, of the second type of stress corrosion crack propagation life under the second category of crack propagation and of the third type of stress corrosion crack propagation life under the second category of crack propagation. In one implementation, determining the stress corrosion crack propagation life under the second crack propagation category based on the first type of stress corrosion crack propagation life under the second crack propagation category, the second type of stress corrosion crack propagation life under the second crack propagation category, and the third type of stress corrosion crack propagation life under the second crack propagation category may include determining a minimum value of the first type of stress corrosion crack propagation life under the second crack propagation category,of the second type of stress corrosion crack propagation life under the second crack propagation category and of the third type of stress corrosion crack propagation life under the second crack propagation category as stress corrosion crack propagation life under the , second category of crack propagation. For example, a method for calculating the stress corrosion crack propagation life NfScco2 under the second crack propagation category can be expressed as follows: ^1.3 = 2x0.5 1 For example, taking the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D in the above embodiment, the detected crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is the second crack propagation category. A method for calculating the stress corrosion crack propagation life N fscco2 under the second crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D can be expressed as follows: ^fscc2,i - = 21,583 years ' ' SCC ^fscc2Q2 = - 18^675 years (at)sœ ... 47.979-iO ... oiq Wfscc2,3 = 777— =.........B.......~ 25,319 years \ clt / ^fsccos^ ^fscc21? ^fscc2 2' ^fscci.s} “ 1^^(2158^ 18,675. 25,319} — 18.-67.5 ùiyië&s

[0202] Therefore, in the method, when the monitoring component is the cylinder, the first type of stress corrosion crack propagation life to the third type of stress corrosion crack propagation life under the second crack propagation category are acquired by taking into account the crack depth by phased array detection, the test value of the annual average stress corrosion crack propagation rate of the cylinder material, and the critical crack size by low cycle fatigue, and the stress corrosion crack propagation life under the second crack propagation category is further determined.

[0203] Based on any above embodiment of the present disclosure, the fatigue crack propagation life includes the low-cycle fatigue crack propagation life, and acquiring low-cycle fatigue crack propagation lives under different crack propagation categories includes acquiring the low-cycle fatigue crack propagation life in each of at least one phase corresponding to any crack propagation category under the predefined condition of the nuclear turbine in service based on a second parameter of the monitoring component, the crack shape parameter of the monitoring component, a low-cycle fatigue crack propagation test constant of the material of the monitoring component,and the maximum stress at the crack location in the monitoring component under the predefined condition of the in-service nuclear turbine. The second parameter is the crack depth by phased array detection or any two parameters in the crack propagation size set. In the method, the low-cycle fatigue crack propagation lifetimes under different crack propagation categories can be determined by considering the second parameter of the monitoring component, the crack shape parameter of the monitoring component, the low-cycle fatigue crack propagation test constant of the material of the monitoring component, and the maximum stress at the crack location of the monitoring component under the predefined condition of the in-service nuclear turbine.

[0204] Taking, for example, a blade groove of a rotor as a monitoring component, the acquisition of low-cycle fatigue crack propagation lifetimes under different crack propagation categories is described below.

[0205] Based on any embodiment above, when the monitoring component is the rotor blade groove, as illustrated in [Fig.6], acquiring the low-cycle fatigue crack propagation lifetimes under different crack propagation categories under a normal shutdown transient condition of the Nuclear turbine in service may include the following steps.

[0206] In step S601, a low-cycle fatigue crack propagation lifetime in a first phase of the first crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is acquired.

[0207] In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the first crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the first crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine based on the crack depth by phased array detection, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter, the rotor material low cycle fatigue crack propagation test constant, and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine.

[0208] In some examples, a method for calculating the low-cycle fatigue crack propagation life Nfni,i in the first phase of the first crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows:

[0210] where, Co, m0 are the low cycle fatigue crack propagation test constants of a rotor material.

[0211] In step S602, a low-cycle fatigue crack propagation lifetime in a second phase of the first crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is acquired.

[0212] In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the high cycle fatigue crack propagation size threshold value, the rotor blade groove crack shape parameter, the low cycle fatigue crack propagation test constant of the rotor material

[0213]

[0214]

[0215]

[0216]

[0217]

[0218]

[0219]

[0220] rotor and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the nuclear turbine in service. In some examples, a method for calculating the low-cycle fatigue crack propagation life Nfni>2 in the second phase of the first crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows: 2x0.5 At step S603, a low-cycle fatigue crack propagation life in a third phase of the first category of crack propagation in the transient condition of normal shutdown of the nuclear turbine in service is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the third phase of the first crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the third phase of the first crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine based on the threshold value of high-cycle fatigue crack propagation size, the critical low-cycle fatigue crack size of the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine, the crack shape parameter of the rotor blade groove, the low-cycle fatigue crack propagation test constant of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine. In some examples, a method for calculating the low-cycle fatigue crack propagation life Nfnij3 in the third phase of the first crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows: Nfnl,3 “ 2x0.5 ( mir2 ) C„ ( o-maxn ) ) 2 1 In step S604, a low-cycle fatigue crack propagation life in a first phase of the second crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is acquired. In one implementation, the acquisition of the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service includes acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine based on the crack depth by phased array detection, the high-cycle fatigue crack propagation size threshold value, the rotor blade groove crack shape parameter, the low-cycle fatigue crack propagation test constant of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine.

[0221] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfn2>i in the first phase of the second crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows:

[0222] ( m0-2 ) Co ( cr„,axn ) " ( )

[0223] In step S605, a low-cycle fatigue crack propagation life in a second phase of the second crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is acquired.

[0224] In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the second crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the second phase of the second crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine based on the high-cycle fatigue crack propagation size threshold value, the critical low-cycle fatigue crack size of the rotor blade groove under the transient normal shutdown condition of the in-service nuclear turbine, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the nuclear turbine in service.,

[0225] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfn2>2 in the second phase of the second crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows:

[0226] Nfn2.2 “ 2x0.5 (wo-2)Co(amaxn )”'*'( 2^^ 1___1

[0227] In step S606, a low-cycle fatigue crack propagation life in a first phase of the third crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is acquired.

[0228] In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the third crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the third crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine based on the crack depth by phased array detection, the high-cycle fatigue crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the nuclear turbine in service.,

[0229] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfn3>i in the first phase of the third crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows:

[0230] 2x0.5 r2 1.2Vr 1 1

[0231] In step S607, a low-cycle fatigue crack propagation life in a second phase of the third crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is acquired.

[0232] In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the third crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the second phase of the third crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine based on the high-cycle fatigue crack propagation size threshold value, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the nuclear turbine in service.,

[0233]

[0234]

[0235]

[0236]

[0237]

[0238]

[0239]

[0240] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfn3>2 in the second phase of the third crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows: Nfn3.2 “ 2x0.5 At step S608, a low-cycle fatigue crack propagation life in a third phase of the third category of crack propagation in the transient condition of normal shutdown of the nuclear turbine in service is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the third phase of the third crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine includes acquiring the low-cycle fatigue crack propagation life in the third phase of the third crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine based on the threshold value of stress corrosion crack propagation size, the critical low-cycle fatigue crack size of the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine, the crack shape parameter of the rotor blade groove, the low-cycle fatigue crack propagation test constant of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine. In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfn3>3 in the third phase of the third crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows: ascc «=" J In step S609, a low-cycle fatigue crack propagation life in a first phase of the fourth crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the fourth crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine includes acquiring the low-cycle fatigue crack propagation life in the first phase of the fourth crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine

[0241]

[0242]

[0243]

[0244]

[0245]

[0246]

[0247] based on the crack depth by phased array detection, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter, the rotor material low cycle fatigue crack propagation test constant, and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine. In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfn4ji in the first phase of the fourth crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows: Nfn4,l “ __________2x0.5__________ ( m0-2 ) Co ( <Tnlilx„ ) ” ( ‘ 1 In step S610, a low-cycle fatigue crack propagation life in a second phase of the fourth crack propagation category in the transient condition of normal shutdown of the nuclear turbine in service is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine includes acquiring the low-cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the transient condition of normal shutdown of the in-service nuclear turbine based on the threshold value of stress corrosion crack propagation size, the critical low-cycle fatigue crack size of the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine, the crack shape parameter of the rotor blade groove, the low-cycle fatigue crack propagation test constant of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the in-service nuclear turbine. In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfn4j2 in the second phase of the fourth crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service is as follows: 2x0.5 a,4 For example, taking the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 1 of the in-service nuclear turbine A in the above embodiment for example, the detected crack propagation category of the The fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is the first category of crack propagation, and the low-cycle fatigue stress and basic material test data of the No. 1 low-pressure rotor under the normal shutdown condition of the in-service nuclear turbine A are shown in Table 5.

[0248] Table 5. Low-Cycle Fatigue Stress and Basic Material Test Data of a Low-Pressure Rotor Under a Normal Shutdown Condition of an In-Service Nuclear Turbine No. Item Data Value 1 Maximum stress amaxn / MPa at a crack location in a rotor blade groove under a transient condition of normal stop 457.918 2 Low cycle fatigue crack propagation test constant m0 ​​of a rotor material 2.556 3 Low cycle fatigue crack propagation test constant Co of a material 1.593 x 10- ii 4 Crack shape parameter Q 0.98684

[0249] A method for calculating the low-cycle fatigue crack propagation lifetimes under the first crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor under the transient condition of normal shutdown of the nuclear turbine in service A is as follows:

[0250]

[0251]

[0252] Vnl.l ~ 2x0.5 1 i 2xü.5 F 1 î = 5725 ( m0-2 ) Co( ) ' ( — ) " 1 CÎT uscc . (2.55<>2M-59M457.9I«)25*(ij1^ 10.002 ^ 8.f. 2x0.5 1 1 2x0.5 F 1 1 j = 3177 ( ( Q ) L t ;sôc 1 (2.556-2 )xl 2593^(457.918)^( 1 0.00798“^ 0.023619^ Vf- 1 1.5 1,3 = 1466 (^2)^(^)^(^^ ."T «5 j (2.55fr2)xl.59M457.918)3s56(ü^ L 0 023619^ 0.044693^

[0253] For example, taking the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is the first crack propagation category, and the low-cycle fatigue stress and basic material test data of the No. 2 low-pressure rotor under the normal shutdown condition of the in-service nuclear turbine B are shown in Table 5.

[0254] A method for calculating the low-cycle fatigue crack propagation lifetimes under the first crack propagation category of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor under the normal shutdown condition of the nuclear turbine in service B is as follows:

[0255] Nfnij “ 2x0.5 1 1 flsCc . = 1693 ( w0-2 ) Co( <7max„ ) ” ( )2

[0256] Nfnl,2 = 2x0.5 1 1 = 3177 ( H7.Q-2 ) ( q J fh

[0257] 2x0.5 1 1 = 1466 (m,x2) Co (aœaxn) 4^) 1 «7* L ih

[0258] For example, taking the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is the second crack propagation category, and the low-cycle fatigue stress and basic material test data of the No. 3 low-pressure rotor under the normal shutdown condition of the in-service nuclear turbine C are shown in Table 5.

[0259] A method for calculating the low-cycle fatigue crack propagation lifetimes under the second crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor under the transient condition of normal shutdown of the nuclear turbine in service C is as follows:

[0260] 2x0.5 , v2.556 (2.556-2)xl.593xlO'i!xl457.918j x^)' r ----] = 2435 0.023619“ J

[0261] _ 2x0.5 fn2,2 ~ --------- ( m0-2 ) ( .,( 65,. ., . ) ____________________2x0.5____________________ (2.556-2 1x1.593x10'11x457.9182-55M 1 0.023619^ 1 0.044693 - 1466

[0262] Therefore, in the method, when the monitoring component is the blade groove of a rotor, the low-cycle fatigue crack propagation lifetimes under different crack propagation categories in the transient condition of normal shutdown of the nuclear turbine in service can be acquired by taking into account the crack shape parameter of the rotor blade groove, the constant of

[0267] low cycle fatigue crack propagation test of rotor material, the maximum stress at the crack location in the rotor blade groove under the transient condition of normal shutdown of the nuclear turbine in service and the set of crack propagation sizes of the rotor blade groove.

[0263] Based on any embodiment above, when the monitoring component is a blade groove of a rotor, as illustrated in [Fig.7], acquiring the low-cycle fatigue crack propagation lifetimes under the different crack propagation categories in the transient 110% overspeed test condition of the in-service nuclear turbine comprises the following steps.

[0264] In step S701, a low-cycle fatigue crack propagation life in a first phase of the first crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine is acquired.

[0265] In one implementation, acquiring the low cycle fatigue crack propagation life in the first phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the first phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine based on the crack depth by multi-element detection, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine.,

[0266] In some examples, a method for calculating a low cycle fatigue crack propagation life Nfno%,ii in the first phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows: 1___1_ Æ .

[0268] In step S702, a low-cycle fatigue crack propagation life in a second phase of the first crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine is acquired. 2x0.5

[0269] In one implementation, acquiring the low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the high cycle fatigue crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine.,

[0270] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfno%,i.2 in the second phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows:

[0271] 110% 1.2 “ 2x0.5 (W^ K'olcmaxî 10%) )

[0272] At S703, a low-cycle fatigue crack propagation life in a third phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is acquired.

[0273] In one implementation, acquiring the low cycle fatigue crack propagation life in the third phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the third phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine based on the high cycle fatigue crack propagation size threshold value, the rotor blade groove low cycle fatigue critical crack size under the 110% overspeed transient test condition of the in-service nuclear turbine, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine.,

[0274]

[0275]

[0276]

[0277]

[0278]

[0279]

[0280]

[0281] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfno%,i.3 in the third phase of the first crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows: A y 2x0.5 1 1 : vf 110%l,3 — ' ~~~ “ ~ “ Asd (W7)G)( ^maxliO%) L ac-IiO% - In step S704, a low-cycle fatigue crack propagation life in a first phase of the second crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine based on the crack depth by multi-element detection, the high-cycle fatigue crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine., In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfno%,2.i in the first phase of the second crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine is as follows: At step S705, a low-cycle fatigue crack propagation life in a second phase of the second category of crack propagation in the transient overspeed test condition of 110% of the nuclear turbine in service is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the second crack propagation category under the 110% transient overspeed test condition of the in-service nuclear turbine includes acquiring the propagation life of low-cycle fatigue crack in the second stage of the second crack propagation category under the transient overspeed test condition of 110% of the in-service nuclear turbine based on the threshold value of high-cycle fatigue crack propagation size, the critical low-cycle fatigue crack size of the rotor blade groove under the transient overspeed test condition of 110% of the in-service nuclear turbine, the crack shape parameter of the rotor blade groove, the low-cycle fatigue crack propagation test constant of the rotor material, and the maximum stress at the crack location in the rotor blade groove under the transient overspeed test condition of 110% of the in-service nuclear turbine.

[0282] In some examples, a method for calculating a low cycle fatigue crack propagation life Nfn0%,2.2 in the second phase of the second crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows:

[0283] 2x0.5 nax! 10% )

[0284] In step S706, a low-cycle fatigue crack propagation life in a first phase of the third crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine is acquired.

[0285] In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine based on the crack depth by multi-element detection, the high-cycle fatigue crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine.,

[0286] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfno%,3.i in the first phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows:

[0287] M'11G%3,1 ~ 2x0.5 ( W2 ) ( <*max I i 0% ) (

[0288] In step S707, a low-cycle fatigue crack propagation life in a second phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is acquired.

[0289] In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the second phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine based on the high-cycle fatigue crack propagation size threshold value, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine.,

[0290] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfn0%,3.2 in the second phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows:

[0291] 2x0.5 ( ) Q ( <7max) î 0% )

[0292] In step S708, a low-cycle fatigue crack propagation life in a third phase of the third crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine is acquired.

[0293] In one implementation, acquiring the low cycle fatigue crack propagation life in the third phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the third phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the low cycle fatigue critical crack size, and the low cycle fatigue critical crack size. cyclic stress of the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine, the crack shape parameter of the rotor blade groove, the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine.

[0294] In some examples, a method for calculating a low cycle fatigue crack propagation life Nfno%,3.3 in the third phase of the third crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows:

[0295] Nfl 10%3.3 “ 2x0.5

[0296] In step S709, a low-cycle fatigue crack propagation life in a first phase of the fourth crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is acquired.

[0297] In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the fourth crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the fourth crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine based on the phased array crack depth, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine.,

[0298] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfno%,4.i in the first phase of the fourth crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows: (m <r2) 110%))2 ai2 "sbc .

[0300] In step S710, a low-cycle fatigue crack propagation life in a second phase of the fourth crack propagation category in the 110% transient overspeed test condition of the nuclear turbine in service is acquired.

[0301] In one implementation, acquiring the low cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the rotor blade groove low cycle fatigue critical crack size under the 110% overspeed transient test condition of the in-service nuclear turbine, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 110% overspeed test condition of the in-service nuclear turbine.,

[0302] In some examples, a method for calculating a low cycle fatigue crack propagation life Nfno%,4.2 in the second phase of the fourth crack propagation category under the 110% overspeed transient test condition of the in-service nuclear turbine is as follows:

[0303] ____________2x0.5____________ (m0-2) Co(<7max ।) (Lgp) For example, taking the Fifth-stage inverted T-type blade groove of low-pressure rotor No. 1 of nuclear turbine in service A in the above embodiment for example, the crack propagation category of the fifth-stage inverted T-type blade groove of low-pressure rotor No. 1 of nuclear turbine in service A is the first crack propagation category. The low-cycle fatigue stress and basic material test data of low-pressure rotor No. 1 under the 100% overspeed test condition of nuclear turbine in service A are shown in the table 6.

[0304] Table 6. Low-Cycle Fatigue Stress and Basic Material Test Data of a Low-Pressure Rotor Under a 110% Overspeed Test Condition of an In-Service Nuclear Turbine No. Item Data Value 1 Maximum stress crmaxno% / MPa at a crack location of a rotor blade groove under condition 481.019 110% overspeed test transient 2 low cycle fatigue crack propagation test constant m0 ​​of rotor material 2.556 3 low cycle fatigue crack propagation test constant Co of material 1.593 x 10-11 4 crack shape parameter Q 0.97481

[0305] A method for calculating the low-cycle fatigue crack propagation lives under the first crack propagation category for the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor under the 110% overspeed transient test condition of the in-service nuclear turbine A is as follows:

[0306] 2x0.5 1 I (2.556-2^1.5^^1(^^481.01^^^(^^.]-^ 1 0.002“ 0.00798“ = 4970

[0307] Nfll0%l,2“ ____________2x0,5____________ (m(r2) io%) () 2x0.5 1 (XSSô^xl^axlff’b^Sl.O^5^ »• 0.00798“^ ----2758 0.023619“ J

[0308] ^fll0%l,3- _____________2x0,5_____________ 1 ( m0~2 ) 6 o ( ax ] ] 0% ) ( ) [ ath .2x0.5 1 ( 2.556-2)xl .593xlff"x481,0192'5Mx()L 0.023619-^

[0309] = 1067 For example, taking the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is the first crack propagation category. The low-cycle fatigue stress and basic material test data of the No. 2 low-pressure rotor under the 110% overspeed transient test condition of the in-service nuclear turbine B are shown in Table 6.

[0310] A method for calculating the low-cycle fatigue crack propagation lives under the first crack propagation category for the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor under the 110% overspeed transient test condition of the in-service nuclear turbine B is as follows:

[0311] 2x0.5 __________________________2x0.5_________________________i___1 (2.556-2)xl ,593xl0'!ix481 .019^^(^1^ l 0.005“^ 0.00798^' = 1470

[0312] vr _ 2x0.3 ;vfl 10%U “ i___1 ______________________2x0.5______________________ 1 (2.556-2)xl.593xl0'M81.0i92 55M «• 0.00798“^ 1 0.023619^ = 2758

[0313] W110%13 2x0.5 (H7tr2) t 0 (°max 1 î 0%) ( 2x0.5 1 ^.SSô^lxl.SgSxlOdb^Sl.O^'^S^Q^Ilî L 0.023619“^"

[0314] 1 0.0400 ] = 1067 For example, taking the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is the second crack propagation category. The low-cycle fatigue stress and basic material test data of the No. 3 low-pressure rotor under the 110% overspeed test condition of the in-service nuclear turbine C are shown in Table 6.

[0315] A method for calculating the low-cycle fatigue crack propagation lives under the second crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor under the 110% overspeed transient test condition of the in-service nuclear turbine C is as follows:

[0316] 2x0.5 has. 2x0.5 (2.556-2)xl.593xl0-'^481.0192^^ L 0.010^ 0.023619^ = 2114

[0317] N fl 10%2.2 - 2x0.5 ( mo"2) Co( CTmaxl ) 1 . 0.023619^ ____________________2x0.5____________________ (2,556-2)x 1.593x10'1 lx481.0 1 92 556x( ---] = 1067 0.04001“ J

[0318] Therefore, in the process, when the monitoring component is the groove rotor blade, the low-cycle fatigue crack propagation lifetimes under different crack propagation categories in the transient 110% overspeed test condition of the in-service nuclear turbine can be acquired by considering the crack shape parameter of the rotor blade groove, the low-cycle fatigue crack propagation test constant of the rotor material, the maximum stress at the crack location in the rotor blade groove in the transient 110% overspeed test condition of the in-service nuclear turbine and the crack propagation size set of the rotor blade groove.

[0319] Based on any embodiment above, when the monitoring component is a blade groove of a rotor, as illustrated in [Fig.8], acquiring low-cycle fatigue crack propagation lifetimes under different crack propagation categories under a transient 120% overspeed operating condition of the in-service nuclear turbine comprises the following steps.

[0320] In step S801, a low-cycle fatigue crack propagation life in a first phase of the first crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is acquired.

[0321] In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the first crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the first crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine based on the phased array crack depth, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 120% overspeed operating condition of the nuclear turbine in service.,

[0322] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi2o%,ii in the first phase of the first crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is as follows: 1___1 2x0.5 Nf 120% 1.1 “

[0324] In step S802, a low-cycle fatigue crack propagation life in a second phase of the first crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is acquired.

[0325] In one implementation, acquiring the low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine based on the threshold value of stress corrosion crack propagation size, high cycle fatigue crack propagation size threshold value, rotor blade groove crack shape parameter, low cycle fatigue crack propagation test constant of rotor material and maximum stress at the crack location in rotor blade groove under the transient 120% overspeed operating condition of the in-service nuclear turbine.

[0326] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi2o%,i.2 in the second phase of the first crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is as follows:

[0327] N fl 20% 1.2 - 2x0.5 (mQ-l) C 0 (r7mas 120%) (')

[0328] In step S803, a low-cycle fatigue crack propagation life in a third phase of the first crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is acquired.

[0329] In one implementation, acquiring the low cycle fatigue crack propagation life in the third phase of the first crack propagation category under the 120% overspeed transient operating condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the third phase of the first crack propagation category under the 120% overspeed transient operating condition of the in-service nuclear turbine based on the high cycle fatigue crack propagation size threshold value, the low cycle fatigue critical crack size of the rotor blade groove under the 120% overspeed transient test condition of the in-service nuclear turbine, the

[0330]

[0331]

[0332]

[0333]

[0334]

[0335]

[0336] rotor blade groove crack shape parameter, low cycle fatigue crack propagation test constant of rotor material and maximum stress at crack location in rotor blade groove under transient 120% overspeed operating condition of in-service nuclear turbine. In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi2o%,i.3 in the third phase of the first crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine is as follows: ____________2x0.5__________ (>«0*2) £¢(¢7,^120%) ) At step S804, a low-cycle fatigue crack propagation life in a first phase of the second category of crack propagation in the transient condition of 120% overspeed operation of the nuclear turbine in service is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine based on the crack depth by phased array detection, the high-cycle fatigue crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 120% overspeed operating condition of the nuclear turbine in service., In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi20%,2.i in the first phase of the second crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is as follows: M _ . 2x0.5 ;vfl20%2,l - ( ) C 0 ( o-nux 120% 1___1. i ih In step S805, a low-cycle fatigue crack propagation life in a second stage of the second crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is acquired.

[0337] In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the second crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the second phase of the second crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine based on the high-cycle fatigue crack propagation size threshold value, the rotor blade groove low-cycle fatigue critical crack size under the transient 120% overspeed operating condition of the in-service nuclear turbine, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient overspeed operating condition of , 120% of the nuclear turbine in service.

[0338] In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi2o%,2.2 in the second phase of the second crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is as follows:

[0339] 2x0.5 fî20%2.2 ------------------------- ( w0'2 ) Co ( j 20¾ ) [ ]

[0340] In step S806, a low-cycle fatigue crack propagation life in a first phase of the third category of crack propagation in the transient condition of 120% overspeed operation of the nuclear turbine in service is acquired.

[0341] In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the third crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the third crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine based on the phased array crack depth, the high-cycle fatigue crack propagation size threshold value, the rotor blade groove crack shape parameter, the rotor material low-cycle fatigue crack propagation test constant, and the maximum stress at

[0342]

[0343]

[0344]

[0345]

[0346]

[0347]

[0348] the crack location in the rotor blade groove under the transient 120% overspeed operating condition of the nuclear turbine in service. In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi2o%,3.i in the first phase of the third crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine is as follows: 2x0.5 / "■V 1.21?? 1 In step S807, a low-cycle fatigue crack propagation life in a second phase of the third crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the third crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the second phase of the third crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine based on the high-cycle fatigue crack propagation size threshold value, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 120% overspeed operating condition of the nuclear turbine in service., In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi20%,3.2 in the second phase of the third crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine is as follows: At step S8O8, a low-cycle fatigue crack propagation life in a third stage of the third crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is acquired. In one implementation, the acquisition of the low-cycle fatigue crack propagation life in the third phase of the third category of pro-

[0350]

[0351]

[0352]

[0353] crack propagation in the transient 120% overspeed operating condition of the in-service nuclear turbine includes acquiring the low-cycle fatigue crack propagation life in the third stage of the third crack propagation category in the transient 120% overspeed operating condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the critical low-cycle fatigue crack size of the rotor blade groove in the transient 120% overspeed test condition of the in-service nuclear turbine, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 120% overspeed operating condition of the nuclear turbine in service., In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi2o%,3.3 in the third phase of the third crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine is as follows: M'120%33 — 2x0.5 1 1 .a^C acho% In step S809, a low-cycle fatigue crack propagation life in a first phase of a fourth crack propagation category under the transient 120% overspeed operating condition of the nuclear turbine in service is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the fourth crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the fourth crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine based on the phased array crack depth, the stress corrosion crack propagation size threshold value, the rotor blade groove crack shape parameter,of the low cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient condition of func, 120% overspeed operation of the nuclear turbine in service. In some examples, a method of calculating a propagation lifetime of low-cycle fatigue crack Nfi2o%,4.i in the first phase of the fourth crack propagation category under the transient condition of 120% overspeed operation of the nuclear turbine in service is as follows:

[0355]

[0356]

[0357] at _____________2x0.5 •v fl 20%4,l “ 1 »!0"2 ) Q( <7maxl 20'; 1___1 At step S810, a low-cycle fatigue crack propagation life in a second phase of the fourth category of crack propagation in the transient condition of 120% overspeed operation of the nuclear turbine

[0358]

[0359]

[0360] in service is acquired. In one implementation, acquiring the low cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the rotor blade groove low cycle fatigue critical crack size under the transient 120% overspeed test condition of the in-service nuclear turbine, the rotor blade groove crack shape parameter,of the low-cycle fatigue crack propagation test constant of the rotor material and the maximum stress at the crack location in the rotor blade groove under the transient 120% overspeed operating condition of the nuclear turbine in service., In some examples, a method for calculating a low-cycle fatigue crack propagation life Nfi20%,4.2 in the second phase of the fourth crack propagation category under the transient 120% overspeed operating condition of the in-service nuclear turbine is as follows: Nfi2o%4.2- 2x0.5 ( hî0"2 ) C'o( ^max i 20% 1 ( ) For example, taking the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is the first crack propagation category. The low-cycle fatigue stress and basic material test data of the No. 1 low-pressure rotor under the 120% overspeed operating condition of the nuclear turbine in service A are illustrated in Table 7.

[0361] Table 7. Low-cycle fatigue stress and basic material test data of a low-pressure rotor under 120% overspeed operating condition of an in-service nuclear turbine No. Item Data Value 1 Maximum stress crmaxi20% / MPa at a crack location of a rotor blade groove under a transient 120% overspeed operating condition 577.005 2 Low cycle fatigue crack propagation test constant m0 ​​of a rotor material 2.556 3 Low cycle fatigue crack propagation test constant Co of a material 1.593 x 10-11 4 Crack shape parameter Q 0.92580

[0362]

[0363]

[0364]

[0365]

[0366]

[0367]

[0368]

[0369] A method for calculating the low-cycle fatigue crack propagation lives under the first crack propagation category for the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor under the transient 120% overspeed operating condition of the nuclear turbine in service A is as follows: Nf 120% 1,1 - ____________2x0,5____________ ( mn-2 ) Co ( CTmax 120ft ) ( ) 2x0.5 2.5? (2.556-2)xl .593x10' ^577.005^^^(0^5 P M'120%1,2 - 2x0.5 z s z X i 1 ? Irr A 1 } Co ( ctiu3x J 2(î% ) ( -^-=- ] 1 0.002^ 2x0.5 (2.556-2)xl.593xl04ïx577.0052’556x(^^ ) 2 M’120%1,3- 2x0.5 ( ) C o( 120% ) I 2x0.5 1 0.00798^ = 2922 1 0.023619^ = 1622 1 . 0.00798^ (2.556-2)xl.593x10-' 'x577.0052556x(* 1 1 0.023619^ 0.02641' For example, taking the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 2 of the in-service nuclear turbine B in the above embodiment for example, the crack propagation category of the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 2 of the Nuclear turbine in service B is the first crack propagation category. The low-pressure rotor No. 2 low-cycle fatigue stress and basic material test data under the 120% overspeed operating condition of nuclear turbine in service B are shown in Table 7.

[0370] A method for calculating low-cycle fatigue crack propagation lives under the first crack propagation category for the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor under the transient 120% overspeed operating condition of the nuclear turbine in service B is as follows:

[0371] 2x0.5 ( Ȕ0-2 ) Co ( <Tmax ; 20 S

[0372] _____________________2x0.5______________________ 1 L 0.005“^ 1 0.00798^ = 864 Nf 120% 1.2 ~ 2x0.5 ( m0-2 )C0( 2x0.5 (2.556-2)xL593klfflt(577.005)2^ 1 1. 0.00798^ 0.023619^ = 1622

[0373] Nf 120% 1.3“ 2x0.5 ( ) Q ( ^max 120% ) ( ) ________________2x0.5________________ 1___1 1-140 (2.556-2^1.59^10^(577.005)^(0½¾)^ 0-023619^ 0.02641“^ J

[0374] For example, taking the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C in the above embodiment for example, the crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is the second crack propagation category. The low-cycle fatigue stress and basic material test data of the No. 3 low-pressure rotor under the 120% overspeed operating condition of the in-service nuclear turbine C are shown in Table 7.

[0375] A method for calculating low-cycle fatigue crack propagation life under the second crack propagation category for the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor under the transient 120% overspeed operating condition of the nuclear turbine in service C is as follows: Nn20%2A~ _____________2x0.5_____________ 1 (^72)^(0-^12,^.)^(4^2.) - [ «■-

[0377] 2x0.5 novl ) M'120%2,2 - 2x0.5 F !1 1 = 1243 (2.556-2)xl.593xl0 '^577.005)2556]^^^ LOOld 0 02.3614 ' J 1___1 , „ , y , 1¾ a4?0«. _ 2x0.5 1 11 = 140 (2.556-2)xl.593xlOJ^577.005) (^}^ * 0.023619 2 0.02641 - J

[0378] Therefore, in the method, when the monitoring component is the rotor blade groove, the low-cycle fatigue crack propagation lifetimes under different crack propagation categories in the transient 120% overspeed operating condition of the in-service nuclear turbine can be acquired by considering the crack shape parameter of the rotor blade groove, the low-cycle fatigue crack propagation test constant of the rotor material, the maximum stress at the crack location in the rotor blade groove in the transient 120% overspeed operating condition of the in-service nuclear turbine, and the crack propagation size set of the rotor blade groove.

[0379] Taking, for example, a cylinder as a monitoring component, the acquisition of low-cycle fatigue crack propagation lifetimes under different crack propagation categories is described below.

[0380] Based on any embodiment above, when the monitoring component is a cylinder, as illustrated in [Fig.9], acquiring low-cycle fatigue crack propagation lifetimes under different crack propagation categories comprises the following steps.

[0381] In step S901, a low-cycle fatigue crack propagation life in a first phase of the first crack propagation category under the transient cold start condition of the nuclear turbine in service is acquired.

[0382] In one implementation, acquiring the low cycle fatigue crack propagation life in the first phase of the first crack propagation category under the transient cold start condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the first phase of the first crack propagation category under the transient cold start condition of the in-service nuclear turbine based on the crack depth by phased array detection, the stress corrosion crack propagation size threshold value, the cylinder crack shape parameter, the low cycle fatigue crack propagation test constant of the cylinder material, and the maximum stress at the crack location in the cylinder under the transient cold start condition.

[0383]

[0384]

[0385]

[0386]

[0387]

[0388]

[0389]

[0390]

[0391] cold start of the nuclear turbine in service. In some examples, a method for calculating the low-cycle fatigue crack propagation life Nfci i in the first phase of the first crack propagation category under the transient cold start condition of the in-service nuclear turbine is as follows: Nm = 1 ' tcl,l 2x0.5 1 { where, Co, m0 are the low cycle fatigue crack propagation test constants of the cylinder material. In step S902, a low-cycle fatigue crack propagation life in a second phase of the first crack propagation category under the transient cold start condition of the in-service nuclear turbine is acquired.In one implementation, acquiring the low cycle fatigue crack propagation life in the second phase of the first crack propagation category in the transient cold start condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the second phase of the first crack propagation category in the transient cold start condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the critical low cycle fatigue crack size of the cylinder in the transient cold start condition of the in-service nuclear turbine, the crack shape parameter of the cylinder,of the low-cycle fatigue crack propagation test constant of the cylinder material and the maximum stress at the crack location in the cylinder under the transient cold start condition of the nuclear turbine in service., In some examples, a method for calculating the low-cycle fatigue crack propagation life Nfcij2 in the second phase of the first crack propagation category under the transient cold start condition of the in-service nuclear turbine is as follows: Mc 1,2 “ 2x0.5 ( m <r2 ) Co ( <rmaxc ) ' " ( ) I asCc At step S903, a low-cycle fatigue crack propagation life in a first phase of the second category of crack propagation in the transient condition of cold start of the nuclear turbine in service is acquired. In one implementation, the acquisition of the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient cold start condition of the turbine

[0392]

[0393]

[0394]

[0395]

[0396] in-service nuclear turbine includes the acquisition of the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category in the transient cold start condition of the in-service nuclear turbine based on the crack depth by phased array detection, the critical low-cycle fatigue crack size of the cylinder in the transient cold start condition of the in-service nuclear turbine, the crack shape parameter of the cylinder, the low-cycle fatigue crack propagation test constant of the cylinder material, and the maximum stress at the crack location in the cylinder in the transient cold start condition of the in-service nuclear turbine. In some examples, a method for calculating the low cycle fatigue crack propagation life Nfc2>i in the first phase of the second crack propagation category under the transient cold start condition of the in-service nuclear turbine is as follows: In step S904, a low-cycle fatigue crack propagation life in a first phase of the first crack propagation category under the warm start transient condition of the in-service nuclear turbine is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the first crack propagation category under the warm start transient condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the first crack propagation category under the warm start transient condition of the in-service nuclear turbine based on the phased array crack depth, the stress corrosion crack propagation size threshold value, the cylinder crack shape parameter, the low-cycle fatigue crack propagation test constant of the cylinder material, and the maximum stress at the crack location in the cylinder under the cold start transient condition of the in-service nuclear turbine. In some examples, a method for calculating the low-cycle fatigue crack propagation life Nfwij in the first phase of the first crack propagation category under the warm start transient condition of the in-service nuclear turbine is as follows: fwl,l — 2x0.5 (m0-2 ) Co() 1 1

[0398] In step S905, a low-cycle fatigue crack propagation life in a second phase of the first crack propagation category under the warm start transient condition of the nuclear turbine in service is acquired.

[0399] In one implementation, acquiring the low cycle fatigue crack propagation life in the second phase of the first crack propagation category in the warm start transient condition of the in-service nuclear turbine comprises acquiring the low cycle fatigue crack propagation life in the second phase of the first crack propagation category in the warm start transient condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the low cycle fatigue critical crack size of the cylinder in the warm start transient condition of the in-service nuclear turbine, the crack shape parameter of the cylinder,of the low-cycle fatigue crack propagation test constant of the cylinder material and the maximum stress at the crack location in the cylinder under the warm start transient condition of the nuclear turbine in service.,

[0400] In some examples, a method for calculating the low cycle fatigue crack propagation life Nfwij2 in the second phase of the first crack propagation category under the warm start transient condition of the in-service nuclear turbine is as follows:

[0401] Nfwl,2“ 2x0.5

[0402] In step S906, a low-cycle fatigue crack propagation life in the first phase of the second category of crack propagation in the transient condition of warm start of the nuclear turbine in service is acquired.

[0403] In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category in the warm start transient condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category in the warm start transient condition of the in-service nuclear turbine based on the crack depth by phased array detection, the low-cycle fatigue critical crack size of the cylinder in the warm start transient condition of the in-service nuclear turbine, the crack shape parameter of the cylinder,of the low-cycle fatigue crack propagation test constant of the cylinder material and the maximum stress at the crack location in the cylinder under the transient start-up condition,

[0404]

[0405]

[0406]

[0407]

[0408]

[0409]

[0410]

[0411] warm from the nuclear turbine in service. In some examples, a method for calculating the low-cycle fatigue crack propagation life Nfw2>i in the first phase of the second crack propagation category under the warm start transient condition of the in-service nuclear turbine is as follows: (^2)^(^,) 1 / 72 1 In step S907, a low-cycle fatigue crack propagation life in a first phase of the first crack propagation category under the transient hot start condition of the nuclear turbine in service is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the first crack propagation category under the transient hot start condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the first crack propagation category under the transient hot start condition of the in-service nuclear turbine based on the crack depth by phased array detection, the stress corrosion crack propagation size threshold value, the cylinder crack shape parameter, the low-cycle fatigue crack propagation test constant of the cylinder material, and the maximum stress at the crack location in the cylinder under the transient hot start condition of the in-service nuclear turbine. In some examples, a method for calculating the low cycle fatigue crack propagation life Nau in the first phase of the first crack propagation category in the hot start transient condition of the in-service nuclear turbine is as follows: 2x0.5 has. In step S908, a low-cycle fatigue crack propagation life in a second phase of the first crack propagation category under the transient hot start condition of the in-service nuclear turbine is acquired. In one implementation, acquiring the low-cycle fatigue crack propagation life in the second phase of the first crack propagation category under the hot start transient condition of the in-service nuclear turbine includes acquiring the propagation life of low-cycle fatigue crack in the second stage of the first crack propagation category under the transient hot start condition of the in-service nuclear turbine based on the stress corrosion crack propagation size threshold value, the critical low-cycle fatigue crack size of the cylinder under the transient hot start condition of the in-service nuclear turbine, the crack shape parameter of the cylinder, the low-cycle fatigue crack propagation test constant of the cylinder material, and the maximum stress at the crack location in the cylinder under the transient hot start condition of the in-service nuclear turbine.

[0412] In some examples, a method for calculating the low cycle fatigue crack propagation life Nf^ in the second phase of the first crack propagation category under the hot start transient condition of the nuclear turbine in service is as follows:

[0413] Nfhl,2 - ___________2x0.5___________ ( ) £ o ( axh ) ' iq )

[0414] In step S909, a low-cycle fatigue crack propagation life in a first phase of the second category of crack propagation in the transient condition of hot start of the nuclear turbine in service is acquired.

[0415] In one implementation, acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category in the transient hot start condition of the in-service nuclear turbine comprises acquiring the low-cycle fatigue crack propagation life in the first phase of the second crack propagation category in the transient hot start condition of the in-service nuclear turbine based on the crack depth by phased array detection, the critical low-cycle fatigue crack size of the cylinder in the transient hot start condition of the in-service nuclear turbine, the crack shape parameter of the cylinder,of the low-cycle fatigue crack propagation test constant of the cylinder material and the maximum stress at the crack location in the cylinder under the transient hot start condition of the nuclear turbine in service.,

[0416] In some examples, a method for calculating the low cycle fatigue crack propagation life Nfll2,i in the first phase of the second crack propagation category under the hot start transient condition of the nuclear turbine in service is as follows:

[0417]

[0418]

[0419]

[0420] For example, taking the low-pressure inner cylinder No. 1 of the operating nuclear turbine A in the above embodiment for example, the detected crack propagation category of the low-pressure inner cylinder No. 1 of the operating nuclear turbine A is the first crack propagation category. Basic life calculation data for a crack position in the cylinder during the cold start transient process, basic life calculation data for a crack position in the cylinder during the warm start transient process, and basic life calculation data for a crack position in the cylinder during the hot start transient process of the low-pressure inner cylinder No. 1 of the operating nuclear turbine A are respectively shown in Table 8, Table 9, and Table 10. Table 8. Basic data for calculating life for a crack position in a cylinder during a transient cold start process No. Item Data Value 1 Maximum stress maxc / MPa at a crack location in a cylinder under a transient cold start condition 252.970 2 Low cycle fatigue crack propagation test constant m0 ​​of a cylinder material 3.15 3 Low cycle fatigue crack propagation test constant Co of a cylinder material 4.2 x 10 12 4 Crack shape parameter Q 0.88 Table 9. Basic life calculation data for a crack position in a cylinder during a warm start transient process No. Item Data Value 1 Maximum stress amaxw / MPa at a crack location in a cylinder under a warm start transient condition 267.093 2 Low cycle fatigue crack propagation test constant m0 ​​of a cylinder material 3.15 3 Low cycle fatigue crack propagation test constant Co 4.2¾ 1 cyclic of a material of a cylinder

[0421] Table 10. Basic life calculation data for a crack position in a cylinder during a transient hot start process

[0422]

[0423] No. Item Data Value 1 Maximum stress maxh / MPa at a crack location in a cylinder under a hot start transient condition 237.736 2 Low cycle fatigue crack propagation test constant m0 ​​of a cylinder material 3.15 3 Low cycle fatigue crack propagation test constant Co of a cylinder material 4.2 x 10 12 A method for calculating low cycle fatigue crack propagation lives under the first crack propagation category of the low pressure inner cylinder No. 1 of the in-service nuclear turbine A is as follows: V _ 2x0.5 1 1 1 ' icl,i— s sà *2 ( / wn-2)c0(o-maxt.) L'Y °stc J _________________2x0.5________________ 1___1 = 11062 (3.15-2^4^10^^252.970^(-^ 0.002 - 0.008264-

[0424] 2x0.5 (3.15-2)x4.2x 10'1 ^52.970315X( 1 0.008264"^ 1 1=5345 0.042375^ J

[0425] 2x0,5 } 1=9322 0.008264^ J

[0427]

[0426] __________________2x0,5__________________ 1 (3.15-2)x4.2xl.(r12x267.0933 '5x[^)~ 1- 0.002” ■ ' ’ b.oo / __________________2x0,5__________________ 1 (3.I5-2)x4.2xl0’l2x267.093^(-^*• 0.008264^ 1 0.0380132^ = 4318 Mhi.i - 2x0.5 (™0-2)C0(CTmaxh)'"'J(J-^ )2 1 a" i 2x0.5 =13453

[0428] (3.15-2)x4.2xl0’52x237.736? i5x( W ) 0.002^ 0.008264' 2x0.5 2x0.5 = 6788

[0429]

[0430] (3.15-2)x4.2xI0‘12x23 7.7363 15x(v L 0.008264“ 0.047979“ J For example, taking the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B in the above embodiment for example, the detected crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B is the first crack propagation category. Basic life calculation data for an in-cylinder crack position during the cold start transient process, basic life calculation data for an in-cylinder crack position during the warm start transient process, and basic life calculation data for an in-cylinder crack position during the hot start transient process of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B are respectively shown in Table 8, Table 9, and Table 10. A method for calculating the low-cycle fatigue crack propagation lives under the first crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B is as follows:

[0431] Mci.i - 2x0.5 maxc J ascc 2x0.5 = 2938 (3. î 5-2)x4.2xl0'l2x252.970315x( P 0.005' 0.008264"

[0432] 2x0.5 1 "I 2x0.5 = 5345

[0433] (3.15-2)x4.2xl0'I2x252.970; 2x0.5 (m0-2)C0(CT, maxw 7 / "'V 1.2 fa 0.008264' 1 1 n.f2 ” d^. 0.042375' 2x0.5 = 2476 (3.15-2) x4.2X10'12x267.0933 \ 0.88 J 0.005 2 0.008264 2

[0434] 2x0.5 (mœ2)C0( °maxw 1___ «^2 ' a 2x0.5 (3.15-2 ) x4.2xl0l2x267.0933 1 0.008264' = 4318 0.0380132’

[0435] 2x0.5 ( mo~2 ) C () ( (7maxJ1 ) ( j ________________2x0.5________________ 1___1 1 = 3574 (3.15-2^4^10^237.7363^]^)^ 10.005^ 0.008264^ J

[0436] Nfhl,2 - 2x0.5 2x0.5 f 1 (3.154l)x4.2xl0^237.736J 1 0.008264^

[0437]

[0438] ! 1=6788 0.047979^ J For example, taking the No. 1 low-pressure inner cylinder of the in-service nuclear turbine C in the above embodiment for example, the detected crack propagation category of the No. 1 low-pressure inner cylinder of the in-service nuclear turbine C is the first crack propagation category. Basic life calculation data for a crack position in the cylinder during the cold start transient process, basic life calculation data for a crack position in the cylinder during the warm start transient process, and basic life calculation data for a crack position in the cylinder during the hot start transient process of the No. 1 low-pressure inner cylinder of the in-service nuclear turbine C are respectively shown in Table 8, Table 9, and Table 10. A method for calculating the low-cycle fatigue crack propagation lives under the first crack propagation category of the low-pressure inner cylinder No. 1 of the in-service nuclear turbine C is as follows:

[0439] at _ 2x0.5 1 * te i, i - ; ( m0-2 )C0(<7maxc) 2x0.5 (3.15-2) x4.2x 10'1 2x252.970: 0.005^ 1 0.008264' = 2938

[0440] 2x0.5 maxc you. has, 2x0.5 (3.15-2)x4.2xKU'x252.970': . 0.008264' { 1 = 5345 0.042375^ J

[0441] 2x0.5 fwl J — ( WJq-2 ) Co ( Cmax w 2x0.5 (3.15 2 ,ix4.?x 10 : 2x267.093?15: 0.005“^ 0.008264" - 2476 _____________2x0.5______________[ 1___1 1—4318 (3.15-2)x4.2xl0-12x267.093^^^^ I- 0.008264^ 0.0380132^ 1

[0443] __________2x0.5___________ (»«œ2)C0(<7mæiJ^(-^) ;

[0444] (3.15-2)x4.2xlOT’2x237.7363 l5x( ! ! 1=3574 . 0.005^ 0.008264^ J Mhl,2 - 2x0.5 ________________2x0.5_______________ [ 1 _ i 1 = 6788 (3.15-2)x4.2x 10‘12x23 7.7363 15x(p L 0.008264^ 0.047979“^ J

[0445]

[0446] For example, taking the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D in the above embodiment for example, the detected crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is the second crack propagation category. Basic life calculation data for a crack position in the cylinder during the cold start transient process, basic life calculation data for a crack position in the cylinder during the warm start transient process, and basic life calculation data for a crack position in the cylinder during the hot start transient process of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D are respectively shown in Table 8, Table 9, and Table 10. A method for calculating the low-cycle fatigue crack propagation lives under the second crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is as follows:

[0447] 2x0.5 1___1 2x0.5 1 (3.15-2)x4.2xl0'l2x252.9703 ^010^ 1 0.042375^” = 4434

[0448] t _____________2x0.5____________ 1 ' fw2,1 “ m ( m0-2 ) Co ( om;KW) °( ) 2 L ui2 ________________2x0.5________________[ 1___1 1 = 3551 (3.15-2^4^10^67.093^(^)-^ L 0.010"^" 0.038012” J

[0449] 2x0.5 (3.1^2^4.^10^37.736^(-^ ) '' 1 0.047979^ = 5680

[0450] Therefore, in the method, when the monitoring component is the cylinder, the low-cycle fatigue crack propagation lifetimes under different crack propagation categories can be acquired by taking into account the crack shape parameter of the cylinder, the low-cycle fatigue crack propagation test constant of the cylinder material, the maximum stress at the crack location in the cylinder, and the crack propagation size set of the cylinder.

[0451] Based on any embodiment above, the fatigue crack propagation life includes the high-cycle fatigue crack propagation life, and acquiring high-cycle fatigue crack propagation lives under different crack propagation categories includes: determining the high-cycle fatigue crack propagation lives under different crack propagation categories based on a third parameter of the monitoring component, the high-cycle fatigue critical crack size, the crack shape parameter of the monitoring component,the high-cycle fatigue crack propagation test constant of the monitoring component material and the range of the high-cycle fatigue stress at the crack location in the monitoring component under the steady-state load operating condition of the in-service nuclear turbine. The third parameter is the crack depth by phased array detection or the high-cycle fatigue crack propagation size threshold value. Therefore, in the method, the high-cycle fatigue crack propagation lifetimes under different crack propagation categories are determined by considering the third parameter of the monitoring component, the critical high-cycle fatigue crack size, the crack shape parameter of the monitoring component,the high-cycle fatigue crack propagation test constant of the monitoring component material and the range of the high-cycle fatigue stress at the crack location in the monitoring component under the steady-state condition of loaded operation of the in-service nuclear turbine.

[0452] Taking, for example, a blade groove of a rotor as a monitoring component, the acquisition of propagation lifetimes of high-cycle fatigue cracking under different crack propagation categories.

[0453] Based on any embodiment above, when the component of monitoring is the rotor blade groove, as shown in [Fig.10], the acquisition of high-cycle fatigue crack propagation lifetimes under different crack propagation categories includes the following steps.

[0454] In step S1001, a high-cycle fatigue crack propagation life under any one of the first crack propagation category, the second crack propagation category, or the third crack propagation category is acquired based on the high-cycle fatigue crack propagation size threshold value, the high-cycle fatigue critical crack size, the rotor blade groove crack shape parameter, a high-cycle fatigue crack propagation test constant of the rotor material, and a range of a high-cycle fatigue stress at the rotor blade groove under the steady-state load operating condition of the nuclear turbine in service.

[0455] In step S1002, a high-cycle fatigue crack propagation life under a fourth crack propagation category is acquired on the basis of the crack depth by phased array detection, the high-cycle fatigue critical crack size, the crack shape parameter of the rotor blade groove, the high-cycle fatigue crack propagation test constant of the rotor material, and the range of the high-cycle fatigue stress at the rotor blade groove under the steady-state load operating condition of the nuclear turbine in service.

[0456] In one implementation, a method of calculating stress corrosion crack propagation life in any of the first crack propagation category, the second crack propagation category, or the third crack propagation category is as follows:

[0457] A'fHi - ? / fH2 - fH3 - i -HA I

[0458] where, Coh and m0H are the high cycle fatigue crack propagation test constants of the rotor material.

[0459] where, Nfm is a high cycle fatigue crack propagation life under the first crack propagation category, NfH2 is a high cycle fatigue crack propagation life under the second crack propagation category, and N® is a high cycle fatigue crack propagation life under the third crack propagation category of crack.

[0460]

[0461]

[0462]

[0463]

[0464] In one implementation, a method for calculating the propagation lifetime of high cycle fatigue crack NfH4 under the fourth category of pro crack pagation is as follows: For example, taking the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A and the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A and the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is the first crack propagation category. The high-cycle fatigue stress and material test basis data of the No. 1 low-pressure rotor of the in-service nuclear turbine A and the No. 2 low-pressure rotor of the in-service nuclear turbine B are respectively shown in Table 11. Table 11. High-cycle fatigue stress and material test base data of a low-pressure rotor of an in-service nuclear turbine No. Item Data Value 1 Range ^h! MPa of high-cycle fatigue stress at a crack location in a rotor blade groove 3.078 2 Constant m0H of high-cycle fatigue crack propagation test of a rotor material 2.889 3 Constant C0H of high-cycle fatigue crack propagation test of a rotor material 6.859 x 10-12 4 Parameter Q of crack shape 0.99976 A method for calculating the high-cycle fatigue crack propagation life NfHi under the first crack propagation category for the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A and the fifth-stage inverted T-type blade groove Low pressure rotor stage No. 2 of the nuclear turbine in service B is as follows: ( / ^2)¾^) t" / " it ■ ____________________2________________F 1___1 1 = 2.77 x 109 2.SR9 1 2ÀK9-2 I (2.889-2)^.85^10-^(3.078)2^^^ )” L 0.023619” 0.049877” J

[0466] For example, taking the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is the second crack propagation category. The high-cycle fatigue stress and material test basis data of the No. 3 low-pressure rotor of the in-service nuclear turbine C are respectively shown in Table 11.

[0467] A method for calculating the high-cycle fatigue crack propagation life NfH2 under the second crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is as follows: I0468! N 2 [1 ! ' fH2 , , I '''w- L "fl? °cH . ____________________2_________________[ 1 1 1 = 2.77 x K)9 ““ - , z , 2.S89 I 2 S89-2 ” 2.889-2 I ( 2.889-2)x6.859xl() i2( 3.(^^ 2 10.023619 1 0.049877 J

[0469] Therefore, in this method, when the monitoring component is the rotor blade groove, the high-cycle fatigue crack propagation life under any one of the first crack propagation category, the second crack propagation category, or the third crack propagation category can be acquired by taking into account the high-cycle fatigue crack propagation size threshold value, the high-cycle fatigue critical crack size, the crack shape parameter of the rotor blade groove, the high-cycle fatigue crack propagation test constant of the rotor material, and the range of the high-cycle fatigue stress at the rotor blade groove under the steady-state load operating condition of the nuclear turbine in service.The high-cycle fatigue crack propagation life under the fourth crack propagation category can be acquired by considering the crack depth by phased array detection, the high-cycle fatigue critical crack size, the crack shape parameter of the blade groove. of the rotor, the high-cycle fatigue crack propagation test constant of the rotor material, and the high-cycle fatigue stress range of the rotor blade groove under the steady-state loaded operating condition of the nuclear turbine in service.

[0470] [Fig. 11] is a process diagram illustrating a long-term monitoring method duration of stress corrosion and fatigue of a nuclear turbine in service according to another embodiment of the present disclosure. As illustrated in [Fig.l 1], the method may comprise the following steps.

[0471] In step S1 101, a multi-element crack depth of a monitoring component of the in-service nuclear turbine is acquired, and a crack propagation category of the monitoring component is acquired based on the multi-element crack depth.

[0472] In step S1102, long-life monitoring data required by the monitoring component under different crack propagation categories are acquired. The long-life monitoring data includes a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life includes at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life.

[0473] Steps SI 101 and SI 102 can be explained with reference to the above embodiments, which will not be repeated here.

[0474] In step S1 103, a crack propagation calendar life of the monitoring component is acquired based on the long life monitoring data under the detected crack propagation category of the monitoring component.

[0475] In one implementation, acquiring the crack propagation calendar life of the monitoring component based on the long life monitoring data under the detected crack propagation category of the monitoring component comprises, in response to the monitoring component being a blade groove of a rotor, acquiring the crack propagation calendar life of the blade groove of the rotor based on the stress corrosion crack propagation life, the low cycle fatigue crack propagation life, and the high cycle fatigue crack propagation life under the detected crack propagation category of the blade groove of the rotor.

[0476] In one implementation, acquiring the crack propagation calendar life of the monitoring component based on the long life monitoring data under the detected crack propagation category of the component monitoring comprises, in response to the monitoring component being a cylinder, acquiring the calendar crack propagation life of the cylinder based on the stress cycle fatigue crack propagation life and the low cycle fatigue crack propagation life under the detected crack propagation category of the cylinder.

[0477] In one implementation, acquiring the crack propagation calendar lifetime of the monitoring component based on the long-life monitoring data under the detected crack propagation category of the monitoring component includes inputting the long-life monitoring data under the crack propagation category of the monitoring component into a predefined model and outputting the crack propagation calendar lifetime by the predefined model. It should be noted that the predefined model is not limited and may include, for example, a deep learning model.

[0478] In one implementation, acquiring the crack propagation calendar lifetime of the monitoring component based on the long life monitoring data under the detected crack propagation category of the monitoring component includes acquiring calendar lifetimes of the monitoring component in a plurality of phases based on the long life monitoring data under the detected crack propagation category of the monitoring component; and acquiring the crack propagation calendar lifetime based on the calendar lifetimes of the monitoring component in the plurality of phases. Note that phase refers to a crack propagation phase of the monitoring component.There are a plurality of phases, and different crack depths by phased array detection and different sets of crack propagation sizes of the monitoring component can correspond to different categories and different phases.

[0479] In some examples, acquiring the crack propagation calendar lifetime based on the calendar lifetimes of the monitoring component in the plurality of phases includes determining a sum value of the calendar lifetimes of the monitoring component in a plurality of phases as the crack propagation calendar lifetime.

[0480] In step SI 104, safety monitoring is performed on the crack propagation lifetime of the monitoring component based on the calendar crack propagation lifetime.

[0481] In one implementation, performing safety monitoring over the crack propagation lifetime of the monitoring component based on the calendar crack propagation lifetime includes acquiring a monitoring criterion value of the monitoring component, determining that no exceptions of safety occurs in the monitoring component in response to the crack propagation calendar lifetime being greater than or equal to the monitoring criterion value, and determining that a safety exception occurs in the monitoring component in response to the crack propagation calendar lifetime being less than the monitoring criterion value.

[0482] In some examples, a mapping linking a model of the monitoring component and the monitoring criterion value may be pre-established. Acquiring the monitoring criterion value of the monitoring component includes requesting the monitoring criterion value in the above mapping based on the model of the monitoring component, and determining that the requested monitoring criterion value is the monitoring criterion value of the monitoring component.

[0483] In summary, according to the long-term monitoring method of stress corrosion and fatigue of the in-service nuclear turbine in embodiments of the present disclosure, the crack propagation calendar life of the monitoring component is acquired on the basis of the long-life monitoring data under the detected crack propagation category of the monitoring component; and the safety monitoring is performed on the crack propagation life of the monitoring component on the basis of the crack propagation calendar life. Therefore, the safety monitoring is performed on the crack propagation life of the monitoring component by considering the influences of stress corrosion and fatigue on the life of the monitoring component, to ensure long-term and safe operation of the in-service nuclear turbine.

[0484] Taking, for example, a blade groove of a rotor as a monitoring component, the acquisition of the crack propagation calendar life of the blade groove of the rotor can be described below.

[0485] As illustrated in [Fig. 12], in response to the monitoring component being the rotor blade groove, acquiring the crack propagation calendar life of the rotor blade groove may comprise the following steps.

[0486] In step S1201, the calendar crack propagation life under the first crack propagation category is acquired on the basis of a stress corrosion crack propagation life, a plurality of phases of low-cycle fatigue crack propagation lives, and a high-cycle fatigue crack propagation life under the first crack propagation category.

[0487] In one implementation, acquiring the crack propagation calendar lifetime under the first crack propagation category based on the duration stress corrosion crack propagation life, low cycle fatigue crack propagation lives in the plurality of phases and high cycle fatigue crack propagation life under the first crack propagation category includes acquiring a calendar life in each phase of the first crack propagation category based on the stress corrosion crack propagation life, low cycle fatigue crack propagation lives in the plurality of phases and fatigue crack propagation life implemented under the first crack propagation category, and acquiring the crack propagation calendar life under the first crack propagation category based on the calendar life in each phase of the first crack propagation category.

[0488] In some examples, a calendar life in a first phase of the first crack propagation category is acquired based on a low-cycle fatigue crack propagation life in the first phase of the first crack propagation category in the transient normal shutdown condition of the in-service nuclear turbine, a low-cycle fatigue crack propagation life in the first phase of the first crack propagation category in the transient 110% overspeed test condition of the in-service nuclear turbine, a low-cycle fatigue crack propagation life in the first phase of the first crack propagation category in the transient 120% overspeed operating condition of the in-service nuclear turbine, an annual average number of normal shutdowns,an average annual number of overspeed tests of 110% and an average annual number of overspeed operations of 120% of the nuclear turbine in service.

[0489] In some examples, a calendar life in a second phase of the first crack propagation category is acquired based on a stress corrosion crack propagation life under the first crack propagation category, a low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine, a low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient 120% overspeed test condition of the in-service nuclear turbine, a low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient 120% overspeed test condition of the in-service nuclear turbine,the annual average number of normal stops, the annual average number of 110% overspeed tests and the annual average number,

[0490]

[0491]

[0492]

[0493]

[0494]

[0495]

[0496]

[0497] 120% overspeed operation of the nuclear turbine in service. In some examples, a calendar life in a third phase of the first crack propagation category is acquired based on the stress corrosion crack propagation life under the first crack propagation category, a high cycle fatigue crack propagation life under the first crack propagation category, a low cycle fatigue crack propagation life in the third phase of the first crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine, a low cycle fatigue crack propagation life in the third phase of the first crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine,of a low-cycle fatigue crack propagation life in the third phase of the first crack propagation category in the transient condition of 120% overspeed operation of the nuclear turbine in service, of the annual average number of normal shutdowns, of the annual average number of 110% overspeed tests and of the annual average number of 120% overspeed operations of the nuclear turbine in service and of an annual average number of high-cycle fatigues of the rotor blade groove. A crack propagation calendar life under the first crack propagation category is acquired based on the calendar life in the first phase of the first crack propagation category, the calendar life in the second phase of the first crack propagation category, and the calendar life in the third phase of the first crack propagation category. In some examples, a method of calculating a crack propagation calendar lifetime tCli under the first crack propagation category is as TC[J - TCL 1,1 + rCLl,2 + rCLl,3 where, Tcli.i is a calendar lifetime in a first phase of the first crack propagation category, tCli,2 is a calendar lifetime in a second phase of the first crack propagation category, tCli,3 is a calendar lifetime in a third phase of the first crack propagation category

[0498]

[0499]

[0500]

[0501] crack, yn is an annual average number of normal shutdowns of the in-service nuclear turbine, y110% is an annual average number of 110% overspeed tests of the in-service nuclear turbine, yi20% is an annual average number of 120% overspeed operations of the in-service nuclear turbine, and yH is an annual average number of high-cycle fatigues of the rotor blade groove. In some examples, the annual average number yH of high-cycle fatigues of the rotor blade groove may be acquired based on an annual average number ty of operating hours of the nuclear turbine in service and a working speed n0 of the nuclear turbine in service. For example, it may be implemented based on the following equation: 3600^ / ¾ 6Ô For example, taking the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A in the above embodiment for example, the crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is the first crack propagation category. The basic design monitoring calendar data of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A are as shown in Table 12. Table 12. Basic calendar data for design monitoring of a blade groove of an in-service nuclear turbine rotor No. Item Data Value 1 Annual average number yn / normal shutdown periods 99 2 Annual average number yn0% / 110% overspeed test periods 1 3 Annual average number yi20% / 120% overspeed operation periods 0.2 4 Annual average number of operating hours tyÆl 7000 5 Working speed n0 / r / min 1500 6 Monitoring criterion value To / year for safety of crack propagation life 60 7 planned overhaul interval rm / year of a nuclear turbine in service 10

[0502]

[0503]

[0504]

[0505]

[0506]

[0507]

[0508]

[0509]

[0510] A method for calculating an annual average number of high-cycle fatigues of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is as follows: 36001^, 3600x7000x1500 _ A o _ ln8 yH = —6Ô~ =----6Ô---- = 63 x 10 A method for calculating the crack propagation calendar life tCli under the first crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is as follows: 77 ( t [ i , yy ।} ) 5725 -4970^2922 [8.36^3177^2758^5622 d-------— = 56.94 + 11.61 + 2.84 = 71.39 liked es 1. 6.3x50' ■ 99 t 1. 0.2 18.36 2 77x30^' M66 +1067 * 140 For example, taking the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is the first crack propagation category. The basic design monitoring calendar data of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B are as shown in Table 12. A method for calculating the annual average number of high-cycle fatigues of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is as follows: _ 36001^ _ 3600x7000x1500 _ A ov ln8 y H “ 60 - 60 — OJ X 1U A method for calculating the crack propagation calendar life tCli under the first crack propagation category of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is as follows: ~ 99 . 1 ■ 02 । . 99 .__1 . 0.2 1693 + 1470 ' 864 36.71 +3177+2758 +1622 -———7“ = 16.84+11.61 + 2.84 = 31.29 years 1, 6.3x10, 99. 1, 0.2 36.71 "U 77xirf} +1466 + 1067 140

[0511] In step S1202, a crack propagation calendar lifetime under the second crack propagation category is acquired based on stress corrosion crack propagation life, low cycle fatigue crack propagation lives in a plurality of phases and high cycle fatigue crack propagation life under the second crack propagation category.

[0512] In one implementation, acquiring the propagation calendar lifetime crack propagation under the second crack propagation category based on the stress corrosion crack propagation life, the low cycle fatigue crack propagation lives in the plurality of phases and the high cycle fatigue crack propagation life under the second crack propagation category includes acquiring a calendar life in each phase of the second crack propagation category based on the stress corrosion crack propagation life, the low cycle fatigue crack propagation lives in the plurality of phases and the fatigue crack propagation life implemented under the second crack propagation category,and acquiring the calendar life of crack propagation under the second crack propagation category on the basis of the calendar life in each phase of the second crack propagation category.

[0513] In some examples, a calendar life in a first phase of the second crack propagation category is acquired based on the stress corrosion crack propagation life under the second crack propagation category, the low cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine, the low cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine, the low cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient 120% overspeed test condition of the in-service nuclear turbine,the average annual number of normal shutdowns, the average annual number of 120% overspeed tests and the average annual number of 120% overspeed operations of the nuclear turbine in service.

[0514] In some examples, a calendar lifetime in a second phase of the second crack propagation category is acquired on the basis of stress corrosion crack propagation life under the first crack propagation category, large fatigue crack propagation life

[0515]

[0516]

[0517]

[0518]

[0519]

[0520]

[0521]

[0522] number of cycles under the second crack propagation category, of the low-cycle fatigue crack propagation life in the second phase of the second crack propagation category under the transient condition of normal shutdown of the nuclear turbine in service, of the low-cycle fatigue crack propagation life in the second phase of the second crack propagation category under the transient condition of 110% overspeed test of the nuclear turbine in service, of the low-cycle fatigue crack propagation life in the second phase of the second crack propagation category under the transient condition of 120% overspeed test of the nuclear turbine in service, of the annual average number of normal shutdowns,of the annual average number of 110% overspeed tests and the annual average number of 120% overspeed operations of the nuclear turbine in service and an annual average number of high cycle fatigues of the rotor blade groove. In some examples, a crack propagation calendar life under the second crack propagation category is acquired based on the calendar life in the first phase of the second crack propagation category, and the calendar life in the second phase of the second crack propagation category. In some examples, a method of calculating a crack propagation calendar life tCl2 under the second crack propagation category is as follows: ^CL2,1 “ T CL2 = T CL2.1 + T CL2.2 where, tCl2,i is a calendar lifetime in the first phase of the second crack propagation category, and Tn .72 is a calendar lifetime in the second phase of the second crack propagation category. For example, taking the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C in the above embodiment for example, the detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is the second crack propagation category, and the basic design monitoring calendar data of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C are as shown in Table 12. A method for calculating the average annual number of high-cycle fatigue events

[0523]

[0524]

[0525]

[0526]

[0527]

[0528] of the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 3 of the in-service nuclear turbine C is as follows: _ 36OOtvwo _ 3600x7000x1500 _ zov ln8 JH “ 60 “ 60 “ J A method for calculating a crack propagation calendar life rn.7 under the second crack propagation category for the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is as follows: = 1 +__________!__________= 10.11 + 2.82 = 12.93 years 1 I 99 I 1 II , 99 , I ,02 '1735*2435*2114* 1243 'T^+îj^+T^+îW+W. In step S1203, a calendar crack propagation life under the third crack propagation category is acquired on the basis of a stress corrosion crack propagation life, low cycle fatigue crack propagation lives in a plurality of phases, and a high cycle fatigue crack propagation life under the third crack propagation category. In one implementation, acquiring the crack propagation calendar life under the third crack propagation category based on the stress corrosion crack propagation life, the low cycle fatigue crack propagation lives in the plurality of phases, and the high cycle fatigue crack propagation life under the third crack propagation category includes acquiring a calendar life in each phase of the third crack propagation category based on the stress corrosion crack propagation life, the low cycle fatigue crack propagation lives in the plurality of phases, and the implemented fatigue crack propagation life under the third crack propagation category,and acquiring the calendar life of crack propagation under the third crack propagation category on the basis of the calendar life in each phase of the third crack propagation category. In some examples, a calendar life in a first phase of the third crack propagation category is acquired based on a low-cycle fatigue crack propagation life in the first phase of the third crack propagation category in the transient condition of normal shutdown of the nuclear turbine in service, a low-cycle fatigue crack propagation life in the first phase of the third crack propagation category in the transient condition of overspeed test of 110% of the nuclear turbine in service, with a low-cycle fatigue crack propagation life in the first phase of the third crack propagation category under the transient overspeed test condition of 120% of the nuclear turbine in service, an annual average number of normal shutdowns, an annual average number of overspeed tests of 110% and an annual average number of overspeed operations of 120% of the nuclear turbine in service.

[0529] In some examples, a calendar life in a second phase of the third crack propagation category is acquired based on a high cycle fatigue crack propagation life under the third second crack propagation category, a low cycle fatigue crack propagation life in the second phase of the third propagation category under the transient normal shutdown condition of the in-service nuclear turbine, a low cycle fatigue crack propagation life in the second phase of the third propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine, a low cycle fatigue crack propagation life in the second phase of the third propagation category under the transient 120% overspeed test condition of the in-service nuclear turbine,the annual average number of normal shutdowns, the annual average number of 110% overspeed tests and the annual average number of 120% overspeed operations of the nuclear turbine in service and an annual average number of high cycle fatigues of the rotor blade groove.

[0530] In some examples, a calendar life in a third phase of the third crack propagation category is acquired based on the stress corrosion crack propagation life under the third crack propagation category, a high cycle fatigue crack propagation life under the third crack propagation category, a low cycle fatigue crack propagation life in the third phase of the third crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine, the low cycle fatigue crack propagation life in the third phase of the third crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine,of the low-cycle fatigue crack propagation life in the third phase of the third crack propagation category under the transient condition of 120% overspeed test of the nuclear turbine in service, the annual average number of normal shutdowns, the annual average number of 110% overspeed tests and the annual average number of 120% overspeed operations of the nuclear turbine in service and the annual average number of high-cycle fatigues of the rotor blade groove.

[0531] In some examples, a calendar crack propagation life under the third crack propagation category is acquired based on the calendar life in the first phase of the third crack propagation category, the calendar life in the second phase of the third crack propagation category, and the calendar life in the third phase of the third crack propagation category.

[0532] In some examples, a method for calculating the crack propagation calendar life tCl3 under the third crack propagation category is as follows: [°533] rcLai - I fl fC!fÀU! ï°534l

[0535] tCL33 = ^---v--------v--- Vfl 20^.3

[0536] rCL3 “ rCI3J + ^^3,2+^^3,3

[0537] where, tCl3,i is a calendar life in the first phase of the third crack propagation category, tCl3,2 is a calendar life in the second phase of the third crack propagation category, and tCl3,3 is a calendar life in the third phase of the third crack propagation category.

[0538] In step S1204, a calendar crack propagation life under the fourth crack propagation category is acquired on the basis of a stress corrosion crack propagation life, low cycle fatigue crack propagation lives in a plurality of phases, and a high cycle fatigue crack propagation life under the fourth crack propagation category.

[0539] In one implementation, acquiring the crack propagation calendar life under the fourth crack propagation category based on the stress corrosion crack propagation life, the low cycle fatigue crack propagation lives in the plurality of phases, and the high cycle fatigue crack propagation life under the fourth crack propagation category includes acquiring a calendar life in each phase of the fourth crack propagation category based on the stress corrosion crack propagation life, the low cycle fatigue crack propagation lives in the plurality of phases, and the fatigue crack propagation life implemented under the fourth crack propagation category, and acquiring the calendar life crack propagation lenary under the fourth crack propagation category based on the calendar life in each phase of the fourth crack propagation category.

[0540] In some examples, a calendar life in a first phase of the fourth crack propagation category is acquired based on a high cycle fatigue crack propagation life under the fourth crack propagation category, a low cycle fatigue crack propagation life in the first phase of the fourth propagation category under the transient normal shutdown condition of the in-service nuclear turbine, a low cycle fatigue crack propagation life in the first phase of the fourth propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine, a low cycle fatigue crack propagation life in the first phase of the fourth propagation category under the transient 120% overspeed test condition of the in-service nuclear turbine,the annual average number of normal shutdowns, the annual average number of 110% overspeed tests and the annual average number of 120% overspeed operations of the nuclear turbine in service and an annual average number of high cycle fatigues of the rotor blade groove.

[0541] In some examples, a calendar life in a second phase of the fourth crack propagation category is acquired based on the stress corrosion crack propagation life under the first crack propagation category, a high cycle fatigue crack propagation life under the fourth crack propagation category, a low cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the transient normal shutdown condition of the in-service nuclear turbine, a low cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the transient 110% overspeed test condition of the in-service nuclear turbine,of a low-cycle fatigue crack propagation life in the second phase of the fourth crack propagation category under the transient condition of 120% overspeed test of the nuclear turbine in service, the annual average number of normal shutdowns, the annual average number of 110% overspeed tests and the annual average number of 120% overspeed operations of the nuclear turbine in service and an annual average number of high-cycle fatigues of the rotor blade groove.

[0542] In some examples, a crack propagation calendar life under the fourth crack propagation category is acquired based on the calendar life in the first phase of the fourth crack propagation category,

[0543]

[0544]

[0545]

[0546]

[0547]

[0548]

[0549]

[0550]

[0551]

[0552] and calendar life in the second phase of the fourth crack propagation category. In some examples, a method for calculating the crack propagation calendar life tCl4 under the fourth crack propagation category is as follows: _ 1 1 CL4.2 - Î 7 >777 777“ —4—^—I—î-2—H— * 4-- fl J ^120^4.2 rCL4 = rCL4,l + rCL42 where, tCl4,i is a calendar lifetime in the first phase of the fourth crack propagation category, and tCl4,2 is a calendar lifetime in the second phase of the fourth crack propagation category. Therefore, in the method, when the monitoring component is the rotor blade groove, the calendar crack propagation life under the detected crack propagation category can be acquired by taking into account the annual average number of normal shutdowns, the annual average number of 110% overspeed tests and the annual average number of 120% overspeed operations of the nuclear turbine in service, and the annual average number of high-cycle fatigues of the rotor blade groove, the stress corrosion crack propagation life, the low-cycle fatigue crack propagation lives in the plurality of phases and the high-cycle fatigue crack propagation life under a certain crack propagation category of the rotor blade groove. Taking, for example, a cylinder as a monitoring component, the acquisition of a calendar life of crack propagation of the cylinder can be described below. As illustrated in [Fig. 13], in response to the monitoring component being the cylinder, acquiring the crack propagation calendar life of the cylinder may include the following steps. In step S1301, a calendar crack propagation life under the first crack propagation category is acquired on the basis of a stress corrosion crack propagation life and low cycle fatigue crack propagation lives in a plurality of phases under the first crack propagation category. In some examples, the method further includes determining a calendar life in a first phase of the first crack propagation category based on an oligo-fatigue crack propagation life.

[0553]

[0554]

[0555]

[0556]

[0557]

[0558]

[0559] cyclic in the first phase of the first crack propagation category in the transient cold start condition of the nuclear turbine in service, a low-cycle fatigue crack propagation life in the first phase of the first crack propagation category in the transient warm start condition of the nuclear turbine in service, a low-cycle fatigue crack propagation life in the first phase of the first crack propagation category in the transient hot start condition of the nuclear turbine in service, an annual average number of cold starts, an annual average number of warm starts and an annual average number of hot starts of the nuclear turbine in service. In some examples, the method further includes determining a calendar life in a second phase of the first crack propagation category based on a stress corrosion crack propagation life under the first crack propagation category, the low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient cold start condition of the in-service nuclear turbine, the low cycle fatigue crack propagation life in the second phase of the first crack propagation category under the transient warm start condition of the in-service nuclear turbine,of the low-cycle fatigue crack propagation life in the second phase of the first crack propagation category in the transient hot start condition of the nuclear turbine in service, the annual average number of cold starts, the annual average number of warm starts and the annual average number of hot starts of the nuclear turbine in service. In some examples, the method further includes determining the calendar crack propagation life under the first crack propagation category based on the calendar life in the first phase of the first crack propagation category, and the calendar life in the second phase of the second crack propagation category. In some examples, a method for calculating the crack propagation calendar life tCli under the first crack propagation category may be expressed as follows: 1 rcLU - , , - 1 ' CLU - —;--- ~ — A(Sœo / rCLl where, Tcli.i is a calendar lifetime in the first phase of the first crack propagation category, tCli,2 is a calendar life in the second phase of the first crack propagation category, yc is an annual average number of cold starts of the nuclear turbine in service, yw is an annual average number of warm starts of the nuclear turbine in service, and yh is an annual average number of hot starts of the nuclear turbine in service.

[0560] For example, taking the low-pressure inner cylinder No. 1 of the operating nuclear turbine A in the above embodiment for example, the detected crack propagation category of the low-pressure inner cylinder No. 1 of the operating nuclear turbine A is the first crack propagation category. The basic design monitoring calendar data of the low-pressure inner cylinder No. 1 of the operating nuclear turbine A are as shown in Table 13.

[0561] Table 13. Basic calendar data for monitoring a cylinder's design internal low pressure No. Item Data Value 1 Annual average number yc / periods of cold starts 4 2 Annual average number yw / periods of warm starts 20 3 Annual average number yh / periods of hot starts 75 4 Monitoring criterion value r0 / year for safety of crack propagation life 60

[0562] A method for calculating the crack propagation calendar life tCli under the first crack propagation category of the low pressure inner cylinder No. 1 of the nuclear turbine in service A can be expressed as follows:

[0563] tcli - _____________________1_____________________ 1 ■ ____________________1___________________ 1. >7. . 7(. 4 , M . 75 i , 4 , 20 | 75 11062 9322T 13453 19.832*5345 431S T6788 = 123.73 + 14.96 = 138.69 years

[0564] For example, taking the low-pressure inner cylinder No. 2 of the operating nuclear turbine B in the above embodiment for example, the detected crack propagation category of the low-pressure inner cylinder No. 2 of the operating nuclear turbine B is the first crack propagation category. The basic design monitoring calendar data of the low-pressure inner cylinder No. 2 of the operating nuclear turbine B are as shown in Table 13.

[0565] A method for calculating the crack propagation calendar life tCli under the first crack propagation category of the low pressure inner cylinder

[0566]

[0567]

[0568]

[0569]

[0570]

[0571]

[0572] No. 2 of the nuclear turbine in service B can be expressed as follows: T _.................1................ . ______________1_______________ 1.__1 TCL1 - ¢1¾¾ + 2938*2476+3574 t9.832*5345 *43.1«*S788 = 32.87 + 14.96 = 47.83 years For example, taking the low-pressure inner cylinder No. 1 of the operating nuclear turbine C in the above embodiment for example, the detected crack propagation category of the low-pressure inner cylinder No. 1 of the operating nuclear turbine C is the first crack propagation category. The basic design monitoring calendar data of the low-pressure inner cylinder No. 1 of the operating nuclear turbine C are as shown in Table 14. Table 14. Basic calendar data for monitoring the design of a low-pressure internal cylinder No. Item Data Value 1 Average annual number yc / periods of cold starts 4 2 Average annual number yw / periods of warm starts 20 3 Average annual number yh / periods of hot starts 75 4 Planned overhaul interval rm / year of a nuclear turbine in service 10 A method for calculating the crack propagation calendar life tCli under the first crack propagation category of the low-pressure inner cylinder No. 1 of the in-service nuclear turbine C can be expressed as follows: _ 1__,__1____________ _ i__, ______________1_____________ 1CL1—y. y„. + , >■ y„. i-,, — 4, 20, 75 i, 4, 20, 75 + 2938*2476+3S74 m32 + 5345+43M + 67SS = 32.87 + 14.96 = 47.83 years In step S1302, a calendar crack propagation life under the second crack propagation category is acquired on the basis of the stress corrosion crack propagation life and low cycle fatigue crack propagation lives in a plurality of phases under the second crack propagation category. In some examples, the method further includes determining a calendar lifetime in a first phase of the second propagation category of crack based on a stress corrosion crack propagation life under the second crack propagation category, a low cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient cold start condition of the nuclear turbine in service, a low cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient warm start condition of the nuclear turbine in service, a low cycle fatigue crack propagation life in the first phase of the second crack propagation category under the transient hot start condition of the nuclear turbine in service, the annual average number of cold starts,the average annual number of warm starts and the average annual number of hot starts of the nuclear turbine in service.

[0573] In some examples, the method further includes determining the calendar lifetime of crack propagation based on the calendar lifetime in the first phase of the second category of crack propagation.

[0574] In some examples, a method for calculating the crack propagation calendar life tCl2 under the second crack propagation category may be expressed as follows:

[0575]

[0576] where, tCl2,i is a calendar lifetime in the first phase of the second category of crack propagation.

[0577] For example, taking the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D in the above embodiment for example, the detected crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is the second crack propagation category. The basic design monitoring calendar data of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D are as shown in Table 14.

[0578] A method for calculating the crack propagation calendar life tCl2 under the second crack propagation category of the low pressure inner cylinder No. 2 of the nuclear turbine in service D can be expressed as follows:

[0579] T 9 - —;---—1—---— - —----4.......—~ -13.65 years K-1, , -K, A ----:--1--±_ (4.__ùù_ 18,675 ^4434 <3551. 5680

[0580] Therefore, in the method, when the monitoring component is the cylinder, the crack propagation calendar life of the cylinder can be acquired by taking into account the annual average number of cold starts, the annual average number of warm starts, the annual average number of hot starts of the nuclear turbine in service, stress corrosion crack propagation life and low cycle fatigue crack propagation lives in the plurality of phases under the cylinder category propagation category.

[0581] [Fig. 14] is a process flow diagram illustrating a method for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine according to another embodiment of the present disclosure.

[0582] In step S1401, a multi-element detection crack depth of a monitoring component of the in-service nuclear turbine is acquired, and a detected crack propagation category of the monitoring component is acquired based on the multi-element detection crack depth.

[0583] In step S1402, long-life monitoring data required by the monitoring component under different crack propagation categories is acquired. The long-life monitoring data includes a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life includes at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life.

[0584] Steps S1401 and S1402 can be explained with reference to the embodiments already described previously, which will not be repeated here.

[0585] In step S1403, a planned overhaul interval of the in-service nuclear turbine is acquired, and a safety factor is acquired based on the crack propagation calendar life and the planned overhaul interval.

[0586] In step S1404, it is determined whether the safety factor satisfies a monitoring acceptance condition.

[0587] In one implementation, acquiring the safety factor based on the crack propagation calendar life and the planned overhaul interval of the in-service nuclear turbine includes determining a ratio of the crack propagation calendar life to the planned overhaul interval or a difference value between the crack propagation calendar life and the planned overhaul interval as a safety factor.

[0588] In one implementation, the safety factor is positively correlated with the crack propagation calendar life and negatively correlated with the planned overhaul interval.

[0589] It should be noted that the monitoring acceptance condition is not limited and, for example, it may be determined that the monitoring acceptance condition is that the safety factor is greater than a second predefined threshold. The second predefined threshold is not limited and, for example, may be 2.

[0590] Taking, for example, a blade groove of a rotor as a monitoring component, there can be described below the realization of safety monitoring over a crack propagation lifetime of the blade groove of the rotor.

[0591] For example, taking the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 1 of the in-service nuclear turbine A, the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 2 of the in-service nuclear turbine B, and the fifth-stage inverted T-type blade groove of the low-pressure rotor No. 3 of the in-service nuclear turbine C in the above embodiment for example, the planned overhaul interval rm of each of the in-service nuclear turbine A, the in-service nuclear turbine B, and the in-service nuclear turbine C is, as shown in Table 12, rm = 10 years.

[0592] The detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is the first crack propagation category, and a crack propagation calendar life tCli under the first crack propagation category of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is 71.39 years, in which case, a method for calculating the safety factor SR is as follows:

[0593] ç At 1 m HJ

[0594] It can be seen that the safety factor of the fifth-stage inverted T-type blade groove of the No. 1 low-pressure rotor of the in-service nuclear turbine A is greater than 2, and it is thus determined that the safety factor SR satisfies the monitoring acceptance condition.

[0595] The detected crack propagation category of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is the first crack propagation category, and a crack propagation calendar life tCli under the first crack propagation category of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is 31.29 years, in which case, a method of calculating the safety factor SR is as follows:

[0596] =

[0597] It can be seen that the safety factor of the fifth-stage inverted T-type blade groove of the No. 2 low-pressure rotor of the in-service nuclear turbine B is greater than 2, and it is thus determined that the safety factor SR satisfies the monitoring acceptance condition.

[0598] The detected crack propagation category of the fifth stage inverted T-type blade groove of the No. 3 low pressure rotor of the in-service nuclear turbine C is the second crack propagation category, and a crack propagation calendar life tCl2 under the second crack propagation category of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is 12.93 years, in which case, a method of calculating the safety factor SR is as follows:

[0599] = 1.29

[0600] It can be seen that the safety factor of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is less than or equal to 2, and it is thus determined that the safety factor SR does not meet the monitoring acceptance condition.

[0601] Taking, for example, a cylinder as a monitoring component, the realization of safety monitoring over a lifetime can be described below.

[0602]

[0603]

[0604]

[0605]

[0606] of cylinder propagation. For example, taking the No. 1 low-pressure inner cylinder of in-service nuclear turbine A, the No. 2 low-pressure inner cylinder of in-service nuclear turbine B, the No. 1 low-pressure inner cylinder of in-service nuclear turbine C, and the No. 2 low-pressure inner cylinder of in-service nuclear turbine D in the above embodiment for example, the planned overhaul interval rm of each turbine among in-service nuclear turbine A, in-service nuclear turbine B, in-service nuclear turbine C, and in-service nuclear turbine D is, as shown in Table 14, tm = 10 years. The detected crack propagation category of the No. 1 low-pressure inner cylinder of the in-service nuclear turbine A is the first crack propagation category, and a crack propagation calendar life tCli under the first crack propagation category of the No. 1 low-pressure inner cylinder of the in-service nuclear turbine A is 138.69 years, in which case, a method of calculating the safety factor SR is as follows: 5 = = 13.87 K ' mj U It can be seen that the safety factor of the low-pressure inner cylinder No. 1 of the operating nuclear turbine A is greater than 2, and it is thus determined that the safety factor SR meets the monitoring acceptance condition. The detected crack propagation category of the No. 2 low-pressure inner cylinder of the in-service nuclear turbine B is the first crack propagation category, and a crack propagation calendar life tCli under the first crack propagation category of the No. 2 low-pressure inner cylinder of the in-service nuclear turbine B is 47.83 years, in which case, a method of calculating the safety factor SR is as follows:

[0607] = =^=4.78

[0608] It can be seen that the safety factor of the low pressure inner cylinder No. 2 of the operating nuclear turbine B is greater than 2, and it is thus determined that the safety factor SR satisfies the monitoring acceptance condition.

[0609] The detected crack propagation category of the No. 1 low-pressure inner cylinder of the in-service nuclear turbine C is the first crack propagation category, and a crack propagation calendar life tCli under the first crack propagation category of the No. 1 low-pressure inner cylinder of the in-service nuclear turbine C is 47.83 years, in which case, a method of calculating the safety factor SR is as follows:

[0610] 5^ = ^ = 4^2=4.73

[0611] It can be seen that the safety factor of the low-pressure inner cylinder No. 1 of the operating nuclear turbine C is greater than 2, and it is thus determined that the safety factor SR satisfies the monitoring acceptance condition.

[0612] The detected crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is the second crack propagation category, and a crack propagation calendar life tCl2 under the second crack propagation category of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine B is 13.65 years, in which case, a method of calculating the safety factor SR is as follows:

[0613] ^ = -^=-^^ = 1.37

[0614] It can be seen that the safety factor of the low pressure inner cylinder No. 2 of the nuclear turbine in service D is less than or equal to 2, and it is thus determined that the safety factor SR does not satisfy the monitoring acceptance condition.

[0615] In step S1405, abnormal data of the monitoring component during a use phase is acquired in response to the safety factor not satisfying the monitoring acceptance condition.

[0616] In step S1406, the abnormal data of the monitoring component during the use phase is optimized and improved, and it is returned to execute a safety factor acquisition process until the acquired safety factor satisfies the monitoring acceptance condition.

[0617] Taking a blade groove of a rotor as a monitoring component, the optimization and improvement of the blade groove of the rotor can be described below.

[0618] It should be noted that the abnormal data of the rotor blade groove during the use phase is not limited in the disclosure and may include, for example, technological parameters of use of the rotor blade groove, basic data of rotor blade groove stress calculation during the use phase, basic data of nuclear turbine rotor material test in service during the use phase, etc.

[0619] In some examples, optimizing and improving abnormal data of the rotor blade groove in the use phase includes turning or grinding the crack in the rotor blade groove; turning to increase a fillet radius of a location where the rotor blade groove is located for the purpose of not influencing the structural strength of the rotor blade groove; performing a local repair weld; eliminating a welding residual stress by a local heat treatment technology; finishing and polishing a repair weld part; improving a machining accuracy and eliminating a machining stress concentration; performing phased array nondestructive monitoring again to determine the depth of a crack in the blade groove; and performing shot peening on the blade groove to improve fatigue performance..

[0620] For example, taking the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C in the above embodiment, in response to the safety factor SR not satisfying the monitoring acceptance condition, the abnormal data of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C during the use phase can be optimized and improved, and no cracks can be found when conducting phased array non-destructive monitoring on the optimized and improved fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C, and the crack depth is set to a; = 2 mm = 0.002 m.

[0621] Safety monitoring is carried out again on the crack propagation life under a combined action of stress corrosion cracking, high-cycle fatigue damage and low-cycle fatigue damage, and a crack propagation calendar life of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is recalculated. When the recalculated crack propagation calendar life is a crack propagation calendar life tCli under the first crack propagation category, i.e., 71.39 years, and rm = 10 years, a calculation method of the safety factor SR is as follows:

[0622] = =ZU2 =7 <i4

[0623] It can be seen that the safety factor of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is greater than 2, and it is thus determined that the safety factor SR satisfies the monitoring acceptance condition, and the safety monitoring on the crack propagation life of the fifth-stage inverted T-type blade groove of the No. 3 low-pressure rotor of the in-service nuclear turbine C is completed.

[0624] Taking a cylinder as a monitoring component, the optimization and improvement of the cylinder can be described below.

[0625] It should be noted that the abnormal data of the cylinder during the use phase is not limited in the disclosure and may include, for example, technological parameters of use of the cylinder, basic data of stress calculation of the cylinder during the use phase, basic data of material test of the nuclear turbine in service during the use phase, etc.

[0626] In one implementation, optimizing and improving the abnormal data of the cylinder in the use phase includes turning or grinding the crack in the cylinder of the in-service nuclear turbine; turning to increase a fillet radius of a location where the cylinder is located for the purpose of not influencing the structural strength of the cylinder of the in-service nuclear turbine; performing a local repair weld; eliminating a welding residual stress by a local heat treatment technology; finishing and polishing a repair weld part; improving a machining accuracy and eliminating a machining stress concentration; performing phased array non-destructive monitoring again to determine the depth of a crack in the cylinder; and performing shot peening on the cylinder to improve fatigue performance;optimizing a cold start parameter change curve of the in-service nuclear turbine to reduce a cylinder thermal stress under the transient cold start condition; optimizing a warm start parameter change curve of the in-service nuclear turbine to reduce a cylinder thermal stress under the transient warm start condition; optimizing a hot start parameter change curve of the in-service nuclear turbine to reduce a cylinder thermal stress under the transient hot start condition; improving water technology supervision to ensure that the quality of condensate water meets the requirements; and blocking a condenser pipe bundle in time after a leak, to prevent a large amount of circulating water from flowing into the condensate water.

[0627] For example, taking the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D in the above embodiment for example, the safety factor SR does not satisfy the monitoring acceptance condition. The data abnormalities of the No. 2 low-pressure inner cylinder of the in-service nuclear turbine D during the use phase can be optimized and improved, for example, by a combination of strategies selected from at least one of turning or grinding the crack in the cylinder of the in-service nuclear turbine, performing local repair welding, eliminating a welding residual stress by local heat treatment technology, finishing and polishing a repair welding part, improving a machining accuracy, and eliminating a machining stress concentration. The non-destructive phased array detection is performed again on the No. 2 low-pressure inner cylinder of the in-service nuclear turbine D, and no cracks are found.In response to the fact that no crack was found during the non-destructive phased array detection, the crack depth in a connecting part between the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D and a second-stage steam extraction pipe is defined as a; = 2 mm = 0.002 m.

[0628] Safety monitoring is carried out again on the crack propagation life under a combined action of stress corrosion cracking and low-cycle fatigue damage, and the crack propagation calendar life of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is recalculated. When the recalculated crack propagation calendar life is a crack propagation calendar life tCli under the first crack propagation category, i.e., 138.69 years, and rm = 10 years, a method for calculating the safety factor SR is as follows:

[0629] 5 = 13.87

[0630] It can be seen that the safety factor of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is greater than 2, and it is thus determined that the safety factor SR satisfies the monitoring acceptance condition, and the realization of safety monitoring on the crack propagation life of the low-pressure inner cylinder No. 2 of the in-service nuclear turbine D is completed.

[0631] In summary, according to the long-term monitoring method for stress corrosion and fatigue of the in-service nuclear turbine in embodiments of the present disclosure, the safety factor is acquired based on the crack propagation calendar life and the planned overhaul interval of the in-service nuclear turbine. It is determined whether the safety factor satisfies the monitoring acceptance condition, and the abnormal data of the monitoring component during the use phase is acquired in response to the safety factor not satisfying the monitoring acceptance condition. The abnormal data of the monitoring component during the use phase is optimized. and improved, and they are returned to perform the safety factor acquisition method until the acquired safety factor meets the monitoring acceptance condition, which helps to improve the safety of the monitoring component during the use phase and is suitable for monitoring the monitoring component of the nuclear turbine in service.

[0632] In order to implement the above embodiment, an apparatus for long-term monitoring of stress corrosion and fatigue of a nuclear turbine in service is further provided in the disclosure.

[0633] [Fig. 15] is a diagram illustrating a structure of a long-term stress corrosion and fatigue monitoring apparatus for an in-service nuclear turbine according to an embodiment of the present disclosure.

[0634] As illustrated in [Fig.15], the apparatus 100 for long-term monitoring of stress corrosion and fatigue of a nuclear turbine in service according to an embodiment of the present disclosure comprises a first acquisition module 110, a second acquisition module 120 and a monitoring module 130.

[0635] The first acquisition module 110 is configured to acquire a multi-element crack depth of a monitoring component of the in-service nuclear turbine and to acquire a detected crack propagation category of the monitoring component based on the multi-element crack depth.

[0636] The second acquisition module 120 is configured to acquire long-life monitoring data required by the monitoring component under different crack propagation categories. The long-life monitoring data includes a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life includes at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life.

[0637] The monitoring module 130 is configured to perform safety monitoring over a crack propagation lifetime of the monitoring component based on the long-life monitoring data under the crack propagation category of the monitoring component acquired from the long-life monitoring data required by the monitoring component under different crack propagation categories.

[0638] In one implementation of the disclosure, the second acquisition module 120 is further configured to acquire a map linking the crack propagation categories and the long-life monitoring data, and to determine the long life monitoring data required by the monitoring component under the crack propagation category from this mapping.

[0639] In one embodiment of the disclosure, the second acquisition module 120 is further configured to determine that the long life monitoring data required by the monitoring component includes stress corrosion crack propagation life, low cycle fatigue crack propagation life, and high cycle fatigue crack propagation life in response to the monitoring component being a blade groove of a rotor; and determine that the long life monitoring data required by the monitoring component includes stress corrosion crack propagation life and low cycle fatigue crack propagation life in response to the monitoring component being a cylinder.

[0640] In one embodiment of the present disclosure, the first acquisition module 110 is further configured to: acquire the crack depth by phased array detection by performing phased array detection on the monitoring component by a phased array ultrasonic flaw detector and a phased array probe; and in response to no crack being found during the phased array detection on the monitoring component, set the crack depth by phased array detection as a predefined value.

[0641] In one embodiment of the present disclosure, the first acquisition module 110 is further configured to: - Acquire a set of crack propagation sizes from the monitoring component; and - acquire the detected crack propagation category of the monitoring component based on the crack depth by multi-element detection and the set of crack propagation sizes.

[0642] In one embodiment of the present disclosure, the first acquisition module 110 is further configured to: acquire a size relationship between the crack depth by multi-element detection and at least one crack propagation size in the set of crack propagation sizes; and determine the detected crack propagation category of the monitoring component based on a correspondence between the size relationship and the detected crack propagation category.

[0643] In one embodiment of the present disclosure, the first acquisition module 110 is further configured to: - acquire basic stress calculation data from the monitoring component; - acquire basic rotor material test data from the monitoring component; and - determine the set of crack propagation sizes based on the basic stress calculation data and the basic rotor material test data.

[0644] In one embodiment of the present disclosure, the first acquisition module 110 is further configured to: - determining a threshold value of stress corrosion crack propagation size of the monitoring component based on a crack shape parameter of the monitoring component, a stress corrosion fracture toughness of a material of the monitoring component and a maximum stress at a crack location in the monitoring component under a steady state condition of under-load operation of the nuclear turbine in service; and - determining a critical low-cycle fatigue crack size of the monitoring component under a predefined condition of the in-service nuclear turbine based on the crack shape parameter of the monitoring component, a fracture toughness of the monitoring component material and a maximum stress at the crack location in the monitoring component under the predefined condition of the in-service nuclear turbine.

[0645] In one embodiment of the present disclosure, the first acquisition module 110 is further configured to: - determining a high-cycle fatigue crack propagation size threshold value of the monitoring component based on a crack shape parameter of the monitoring component, a test value of a high-cycle fatigue crack propagation threshold value of a material of the monitoring component, and a range of a high-cycle fatigue stress at a crack location in the monitoring component under a steady-state, on-load operating condition of the in-service nuclear turbine; and - determining a critical high-cycle fatigue crack size of the monitoring component based on the crack shape parameter of the monitoring component, a fracture toughness of the monitoring component material and a maximum stress at the crack location in the monitoring component under the steady-state operating condition under load of the nuclear turbine in service.

[0646] In one embodiment of the present disclosure, the second module acquisition device 120 is further configured to: determine stress corrosion crack propagation lifetimes under different crack propagation categories based on a first parameter of the monitoring component, a test value of an annual average stress corrosion crack propagation rate of the monitoring component material, and the critical low-cycle fatigue crack size of the monitoring component under the predefined condition of the in-service nuclear turbine. The first parameter is the phased array crack depth or the stress corrosion crack propagation size threshold value.

[0647] In one embodiment of the present disclosure, the second acquisition module 120 is further configured to: determine a plurality of types of stress corrosion crack propagation lifetimes under any crack propagation category based on the first parameter of the monitoring component, the test value of the annual average stress corrosion crack propagation rate of the material of the monitoring component, and the low cycle fatigue critical crack size of the monitoring component under the predefined condition of the nuclear turbine in service; and determine the stress corrosion crack propagation lifetime under any crack propagation category based on the plurality of types of stress corrosion crack propagation lifetimes under any crack propagation category.

[0648] In one embodiment of the present disclosure, the second acquisition module 120 is further configured to: determine a minimum value in the plurality of types of stress corrosion crack propagation lifetimes under any crack propagation category as a stress corrosion crack propagation lifetime under any crack propagation category.

[0649] In an embodiment of the present disclosure, the second acquisition module 120 is further configured to: acquire a low-cycle fatigue crack propagation life in each of at least one phase corresponding to any crack propagation category in the predefined condition of the in-service nuclear turbine based on a second parameter of the monitoring component, the crack shape parameter of the monitoring component, a low-cycle fatigue crack propagation test constant of the material of the monitoring component, and the maximum stress at the crack location in the monitoring component in the predefined condition of the in-service nuclear turbine. The second parameter is the crack depth by phased array detection or any two parameters in the set of crack propagation sizes.

[0650] In one embodiment of the present disclosure, the second acquisition module 120 is further configured to: determine the high-cycle fatigue crack propagation lifetimes under different crack propagation categories based on a third parameter of the monitoring component, the high-cycle fatigue critical crack size, the crack shape parameter of the monitoring component, a high-cycle fatigue crack propagation test constant of the material of the monitoring component, and the range of the high-cycle fatigue stress at the crack location in the monitoring component under the steady-state, on-load operating condition of the in-service nuclear turbine.The third parameter is the crack depth by multi-element detection or the threshold value of crack propagation size by fatigue at high number of cycles.

[0651] In one embodiment of the present disclosure, the monitoring module 130 is further configured to: acquire a crack propagation calendar life of the monitoring component based on the long life monitoring data under the detected crack propagation category of the monitoring component; and perform safety monitoring of the crack propagation life of the monitoring component based on the crack propagation calendar life.

[0652] In one embodiment of the present disclosure, the monitoring module 130 is further configured to: acquire calendar lifetimes of the monitoring component in a plurality of phases based on the long-life monitoring data under the detected crack propagation category of the monitoring component; and acquire the crack propagation calendar lifetime based on the calendar lifetimes of the monitoring component in the plurality of phases.

[0653] In one embodiment of the present disclosure, the monitoring module 130 is further configured to: acquire a planned overhaul interval of the in-service nuclear turbine, and acquire a safety factor based on the crack propagation calendar life and the planned overhaul interval; and perform safety monitoring of the crack propagation life of the monitoring component by determining whether the safety factor satisfies a monitoring acceptance condition.

[0654] In one embodiment of the present disclosure, the monitoring module 130 is further configured to: - acquire abnormal data from the monitoring component during a usage phase in response to the safety factor not being satisfied on condition of acceptance of monitoring; - optimize and improve the abnormal data of the monitoring component during the usage phase, and - return to perform a safety factor acquisition process until the acquired safety factor satisfies the monitoring acceptance condition.

[0655] It should be noted that, for undisclosed details of the apparatus for long-term monitoring of stress corrosion and fatigue of the in-service nuclear turbine in embodiments of the present disclosure, reference should be made to the disclosed details of the method for long-term monitoring of stress corrosion and fatigue of the in-service nuclear turbine in embodiments of the present disclosure, which will not be repeated herein.

[0656] In summary, by means of the long-term stress corrosion and fatigue monitoring apparatus of the in-service nuclear turbine provided in embodiments of the present disclosure, the multi-element detection crack depth of the monitoring component of the in-service nuclear turbine is acquired, and the detected crack propagation category of the monitoring component is acquired based on the multi-element detection crack depth.Long-life monitoring data required by the monitoring component under different crack propagation categories are acquired, wherein the long-life monitoring data includes a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life includes at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life. Safety monitoring is performed on the crack propagation life of the monitoring component based on the long-life monitoring data under the detected crack propagation category of the monitoring component.Therefore, safety monitoring can be carried out over the crack propagation life of the monitoring component considering stress corrosion and fatigue, to ensure long-term and safe operation of the nuclear turbine in service.

[0657] In order to carry out the above embodiments, as illustrated in [Fig. 16], an electronic device 200 is provided in embodiments, and comprises a memory 210, a processor 220 and a computer program stored in the memory 210 and executable by the processor 220. The processor 220 is configured to implement the method for long-term monitoring of stress corrosion and fatigue of the nuclear turbine in service during execution of the program.

[0658] In one embodiment of the present disclosure, the electronic device 200 further comprises a wireless communication component. The wireless communication component is connected to the operating nuclear turbine, and data transmission is performed between the electronic device and the operating nuclear turbine via the wireless communication component.

[0659] In one embodiment of the present disclosure, the memory 210 is configured to store long-life monitoring data required by the monitoring component of the in-service nuclear turbine; the processor 220 is configured to acquire a crack propagation life safety monitoring instruction, and acquire long-life monitoring data to be monitored required by a target monitoring component of the in-service nuclear turbine from the memory 210 based on the crack propagation life safety monitoring instruction, and perform safety monitoring on the crack propagation life of the target monitoring component based on the long-life monitoring data required by the target monitoring component.

[0660] In one embodiment of the present disclosure, the electronic device 200 further comprises: a remote client. The remote client is connected to the processor 220; and the remote client is configured to send the crack propagation lifetime safety monitoring instruction to the processor 220, and receive a monitoring result returned by the processor 220.

[0661] In one embodiment of the present disclosure, the remote client is further configured to acquire control information from a user to operate the remote client, and generate the crack propagation lifetime safety monitoring instruction based on the control information.

[0662] In one embodiment of the present disclosure, the processor 220 is further configured to determine the in-service nuclear turbine monitoring component associated with the remote client as the target monitoring component.

[0663] The electronic device provided in embodiments of the disclosure executes a computer program stored in memory by a processor, to acquire a phased array crack depth of a monitoring component of the in-service nuclear turbine, and acquire a detected crack propagation category of the monitoring component based on the phased array crack depth; and acquire long-life monitoring data required by the monitoring component under different crack propagation categories, the long-life monitoring data including a stress corrosion crack propagation life and a life fatigue crack propagation life, and the fatigue crack propagation life including at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life; and performing safety monitoring on a crack propagation life of the monitoring component based on long-life monitoring data under the detected crack propagation category of the monitoring component. Therefore, safety monitoring can be performed on the crack propagation life of the monitoring component by taking stress corrosion and fatigue into account, to ensure long-term and safe operation of the in-service nuclear turbine.

[0664] In order to implement the above embodiment, a computer-readable storage medium having a computer program stored thereon is provided in embodiments of the present disclosure. The computer program is caused to implement the method for long-term monitoring of stress corrosion and fatigue of the in-service nuclear turbine as described above when executed by a processor.

[0665] The computer-readable storage medium provided in embodiments of the disclosure stores a computer program and is executed by a processor, for acquiring a phased array crack depth of a monitoring component of the in-service nuclear turbine, and acquiring a detected crack propagation category of the monitoring component based on the phased array crack depth;and acquiring long-life monitoring data required by the monitoring component under different crack propagation categories, the long-life monitoring data comprising a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life comprising at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life;and performing safety monitoring over a crack propagation lifetime of the monitoring component based on long-life monitoring data under the detected crack propagation category of the monitoring component. Therefore, safety monitoring can be performed over the crack propagation lifetime of the monitoring component by considering stress corrosion and fatigue, to ensure long-term and safe operation of the in-service nuclear turbine. ;

[0666] In order to achieve the above embodiments, a monitoring platform suitable for an in-service nuclear turbine is provided and includes the long-term stress corrosion and fatigue monitoring apparatus of the operating nuclear turbine as described in [Fig. 15]; or the electronic device as described above; or the computer-readable storage medium as described above.

[0667] The monitoring platform suitable for an in-service nuclear turbine provided in embodiments of the disclosure is suitable for acquiring a crack depth by phased array detection of a monitoring component of the in-service nuclear turbine, and acquiring a detected crack propagation category of the monitoring component based on the crack depth by phased array detection;and acquiring long-life monitoring data required by the monitoring component under different crack propagation categories, the long-life monitoring data comprising a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life comprising at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life;and performing safety monitoring over a crack propagation lifetime of the monitoring component based on long-life monitoring data under the detected crack propagation category of the monitoring component. Therefore, safety monitoring can be performed over the crack propagation lifetime of the monitoring component by considering stress corrosion and fatigue, to ensure long-term and safe operation of the in-service nuclear turbine. ;

[0668] In describing the present disclosure, it is understood that an orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is merely an orientation or positional relationship shown in the accompanying drawings, and does not indicate or imply that the apparatus or element mentioned must have a specific orientation for its construction and operation in a specific orientation, and therefore this cannot be construed as a limitation to the present disclosure.

[0669] Furthermore, the terms "first" and "second" used in the present disclosure are for descriptive purposes only and should not be construed to indicate or imply relative importance or to imply a number of implicitly stated technical features. Therefore, the features limiting "first" and "second" may explicitly or implicitly include one or more of the features. In the description of this disclosure, “a plurality of” means two or more, unless otherwise indicated.

[0670] In the present disclosure, terms such as "mounted", "linked", "connected", "fixed" and the like are to be interpreted broadly, unless expressly indicated and defined otherwise, and may, for example, be a fixed connection, a detachable connection, or a whole; or may be a mechanical connection or an electrical connection; or may be a direct connection or an indirect connection via an intermediate support, or may be a communication relationship between two elements or an interaction relationship between two elements. For those skilled in the art, the specific meanings of the above terms in the present disclosure may be understood based on specific situations.

[0671] In the present disclosure, unless expressly indicated and defined otherwise, the first feature "on" or "under" the second feature may be that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature via an intervening medium. In addition, the first feature "on" and "above" the second feature may be that the first feature is directly above or obliquely above the second feature, or simply indicates that the horizontal height of the first feature is greater than that of the second feature.The first feature "below", "under" and "below" the second feature may be that the first feature is directly below or obliquely below the second feature, or simply indicates that the level height of the first feature is lower than that of the second feature.

[0672] In the descriptions of the specification, descriptions referring to the terms "an embodiment", "certain embodiments", "examples", "specific examples" or "some examples", etc. mean that specific elements, structures, materials or features described in conjunction with the embodiment or example are included in at least one embodiment or example of the present disclosure. In the present description, schematic representations of the above terms do not necessarily refer to the same embodiment or example. In addition, the specific features, structures or materials described may be suitably combined in any one or more embodiments or examples.Furthermore, one skilled in the art may combine different embodiments or examples and features of different embodiments or examples described in this description without them contradicting each other.

[0673] It is understood that, although the embodiments of the present disclosure are presented and described above, the above embodiments are exemplary in nature and should not be construed as a limitation of the present disclosure. Those skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present disclosure.

Claims

Claims

1. A method for long-term monitoring of stress corrosion and fatigue of an in-service nuclear turbine, comprising steps of: - acquiring (S101) a crack depth by multi-element detection of a monitoring component of the in-service nuclear turbine; - acquiring (S102) a detected crack propagation category of the monitoring component based on the crack depth by multi-element detection;and - acquiring (S 103) long-life monitoring data required by the monitoring component under different crack propagation categories, wherein the long-life monitoring data comprises a stress corrosion crack propagation life and a fatigue crack propagation life, and the fatigue crack propagation life comprises at least one of a low-cycle fatigue crack propagation life or a high-cycle fatigue crack propagation life;and - performing (S 104) safety monitoring over a crack propagation lifetime of the monitoring component on the basis of long-life monitoring data under the detected crack propagation category of the monitoring component acquired from the long-life monitoring data required by the monitoring component under different crack propagation categories.;

2. The method of claim 1, wherein acquiring (S 103) the long-life monitoring data required by the monitoring component under different crack propagation categories comprises: - acquiring a map linking the crack propagation categories and the long-life monitoring data; and - determining, based on said map, the long-life monitoring data required by the monitoring component under the crack propagation categories.

3. The method of claim 1 or 2, further comprising: - determining that the long-term monitoring data of life required by the monitoring component includes stress corrosion crack propagation life, low cycle fatigue crack propagation life, and high cycle fatigue crack propagation life in response to the monitoring component being a blade groove of a rotor; and - determining that the long life monitoring data required by the monitoring component includes stress corrosion crack propagation life and low cycle fatigue crack propagation life in response to the monitoring component being a cylinder.

4. The method according to any one of claims 1 to 3, wherein the step of acquiring (S102) a detected crack propagation category of the monitoring component based on the crack depth by multi-element detection comprises: - a step of acquiring (S202) a set of crack propagation sizes of the monitoring component; and - a step of acquiring (S203) the detected crack propagation category of the monitoring component based on the crack depth by multi-element detection and the set of crack propagation sizes.

5. The method of claim 4, wherein the step of acquiring (S203) the detected crack propagation category of the monitoring component based on the multi-element crack depth and the crack propagation size set comprises: - acquiring a size relationship between the multi-element crack depth and at least one crack propagation size in the crack propagation size set; and - determining the detected crack propagation category of the monitoring component based on a correspondence between the size relationship and the crack propagation category.

6. The method of claim 4 or 5, wherein the step of acquiring (S202) the set of crack propagation sizes of the monitoring component comprises: - acquiring basic stress calculation data of the monitoring component; - acquiring basic material test data of the monitoring component;

7. surveillance; and - determination of the set of crack propagation sizes based on the basic stress calculation data and the basic material test data. The method of claim 6, wherein determining the set of crack propagation sizes based on the basic stress calculation data and the basic material test data comprises at least one of: - determining a threshold value of stress corrosion crack propagation size of the monitoring component based on a crack shape parameter of the monitoring component, a stress corrosion fracture toughness of a material of the monitoring component and a maximum stress at a crack location in the monitoring component under a steady state condition of under-load operation of the nuclear turbine in service; - determining a critical low-cycle fatigue crack size of the monitoring component under a predefined condition of the nuclear turbine in service based on the crack shape parameter of the monitoring component, a fracture toughness of the material of the monitoring component and a maximum stress at the crack location in the monitoring component under the predefined condition of the nuclear turbine in service; - determining a threshold value of a high-cycle fatigue crack propagation size of the monitoring component based on a crack shape parameter of the monitoring component, a test value of a threshold value of a high-cycle fatigue crack propagation of a material of the monitoring component, and a range of a high-cycle fatigue stress at a crack location in the monitoring component under a steady-state, under-load operating condition of the in-service nuclear turbine; and - determination of a critical high-cycle fatigue crack size of the monitoring component based on the crack shape parameter of the monitoring component, a fracture toughness of the monitoring component material and a maximum stress at the crack location in the monitoring component under the steady-state operating condition under load

8. of the nuclear turbine in service. The method of claim 7, wherein acquiring the required long-life monitoring data by the monitoring component under different crack propagation categories comprises: - acquiring the stress corrosion crack propagation lifetimes under the different crack propagation categories based on a first parameter of the monitoring component, a test value of an annual average stress corrosion crack propagation rate of the monitoring component material, and the critical low-cycle fatigue crack size of the monitoring component under the predefined condition of the nuclear turbine in service, wherein the first parameter is the crack depth by phased array detection or the stress corrosion crack propagation size threshold value; - acquiring a low-cycle fatigue crack propagation life in each of at least one phase corresponding to any crack propagation category in the predefined condition of the in-service nuclear turbine based on a second parameter of the monitoring component, the crack shape parameter of the monitoring component, a low-cycle fatigue crack propagation test constant of the material of the monitoring component, and the maximum stress at the crack location in the monitoring component in the predefined condition of the in-service nuclear turbine, wherein the second parameter is the crack depth by phased array detection or any two parameters in the crack propagation size set; or - determining the high-cycle fatigue crack propagation lifetimes under different crack propagation categories based on a third parameter of the monitoring component, the critical high-cycle fatigue crack size, the crack shape parameter of the monitoring component, a high-cycle fatigue crack propagation test constant of the material of the monitoring component and the range of the high-cycle fatigue stress at the crack location in the monitoring component under the steady-state condition of turbine operation under load nuclear power in service, in which the third parameter is the crack depth by multi-element detection or the threshold value of crack propagation size by fatigue at high number of cycles.

9. A method according to any one of claims 1 to 8, wherein the step of performing (S104) safety monitoring on the crack propagation life of the monitoring component on the basis of the long life monitoring data under the detected crack propagation category of the monitoring component comprises: - a step of acquiring (SI 103) a calendar lifetime of crack propagation of the monitoring component on the basis of the long-life monitoring data under the detected crack propagation category of the monitoring component; and - a step of carrying out (SI 104) the safety monitoring over the crack propagation lifetime of the monitoring component on the basis of the calendar crack propagation lifetime.

10. An electronic device (200), comprising a memory (210), a processor (220) and a computer program stored in the memory (210) and executable by the processor (220), wherein the processor (210) is configured to implement the method for long-term monitoring of stress corrosion and fatigue of the nuclear turbine in service according to any one of claims 1 to 9 during execution of the program.

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