Non-uniform temperature field decoupling correction method and system for containment integrity test during containment construction period

Abstract

The application discloses a non-uniform temperature field decoupling correction method and system for a containment shell construction period inner shell integrity test, and the method comprises the following steps: S1: first temperature sensors and displacement sensors are arranged on the outer surface of the inner shell of the containment shell and the inner surface of the outer shell of the containment shell respectively, and time history data of the first temperature sensors and the displacement sensors are synchronously collected in the whole process of the inner shell integrity test; S2: a three-dimensional transient temperature field of the inner shell is constructed, and a solar radiation model is introduced to correct the temperature data in the three-dimensional transient temperature field in an azimuth difference manner, so that a corrected three-dimensional transient temperature field is obtained; and S3: a thermal displacement calculation model is established, thermal displacement components of each measuring point are calculated according to the corrected three-dimensional transient temperature field data, the thermal displacement components are subtracted from the total displacement measured in step S1 point by point, and pure mechanical displacement is obtained. The application can correct the temperature data of the non-uniform temperature field, ensure the accuracy of the test data, and lay a data foundation for long-term trend analysis and aging evaluation of the structural performance of the containment shell.

Description

Technical Field

[0001] This invention belongs to the technical field of nuclear power plant containment structure integrity testing, specifically relating to a method and system for decoupling and correcting non-uniform temperature fields during containment construction integrity testing. Background Technology

[0002] The double containment structure is a crucial safety barrier structure of a nuclear power plant reactor building, typically consisting of a prestressed concrete inner shell and a reinforced concrete outer shell. During construction, before the outer shell is completed, the inner shell structure must undergo structural integrity testing (including strength and structural integrity tests) according to nuclear safety regulations and standards. This involves applying compressed air into the inner shell to simulate the loads under design accident conditions, verifying the load-bearing and sealing performance of the inner shell structure. During this test, temperature changes generate significant thermal displacements within the structure (including temperature rises from solar radiation and compressed air). These thermal displacements are superimposed on the mechanical displacements caused by pressure, making the measured displacement data unsuitable for direct evaluation of the inner shell structure. Currently, with the outer shell not yet completed, some methods for structural integrity testing of the inner shell employ simple temperature compensation. While this method can eliminate free thermal displacements when the temperature field is uniform, it is difficult to eliminate them with simple compensation when the temperature field is non-uniform. Other methods completely ignore the influence of temperature; some rely heavily on finite element analysis software, but this software has long calculation cycles, a high learning curve, and is difficult for field test engineers to operate independently. To date, there are no specifications, standards, or simple and easy-to-implement methods that provide temperature correction solutions for the special working conditions during the construction period. Summary of the Invention

[0003] To address the shortcomings of existing technologies, this invention provides a method for correcting the non-uniform temperature field during the integral test of the inner shell in the containment construction period, which solves the problem that the temperature field is uneven and cannot be accurately evaluated when the inner shell is subjected to integral testing.

[0004] To achieve the above objectives, the technical solution adopted by this invention is: to provide a method for decoupling and correcting the non-uniform temperature field during the integrity test of the inner shell in the containment construction period, comprising the following steps: S1: Temperature field monitoring setup and data acquisition; that is, several first temperature sensors and displacement sensors are set up on the outer surface of the inner shell and the inner surface of the outer shell of the containment, and the time history data of the first temperature sensors and displacement sensors are collected synchronously throughout the entire process of the inner shell integrity test. S2: Construct a three-dimensional transient temperature field and correct the data; that is, based on the time history data of the first temperature sensor at different measuring points collected in step S1, the radial basis function interpolation method is used to construct the three-dimensional transient temperature field of the inner shell, and a solar radiation model with local meteorological data is introduced to differentiate and correct the temperature data of the three-dimensional transient temperature field to obtain the corrected three-dimensional transient temperature field. S3: Temperature-displacement decoupling correction; that is, establishing a thermal displacement calculation model, calculating the thermal displacement components of each measuring point based on the corrected three-dimensional transient temperature field obtained in step S2, and then subtracting the thermal displacement components point by point from the total displacement collected in step S1 to obtain the pure mechanical displacement.

[0005] Furthermore, in the non-uniform temperature field decoupling correction method for the inner shell integrity test during the containment construction period as described above, in step S1, the position of the displacement sensor is close to the position of the corresponding first temperature sensor.

[0006] Furthermore, in the non-uniform temperature field decoupling correction method for the inner shell integrity test during the containment construction period as described above, in step S2, the radial basis function interpolation formula is:

[0007] in: For any point in space At any moment Temperature value, For the first Each temperature sensor measuring point at time [time] The weighting coefficients, For radial basis functions, interpolation point To the Each measuring point The Euclidean distance.

[0008] Furthermore, in the non-uniform temperature field decoupling correction method for the inner shell integrity test during the containment construction period as described above, in step S2, the solar radiation model calculates the solar radiation intensity of each circumferential surface of the inner shell at different times based on the solar altitude angle and azimuth angle in the local meteorological data.

[0009] Furthermore, in the non-uniform temperature field decoupling correction method for the inner shell integrity test during the containment construction period as described above, in step S3, the thermal displacement calculation model calculates the thermal displacement components at each measuring point using the following formula:

[0010] in: This is the coefficient of linear expansion of concrete. For the measurement point at time The amount of temperature change relative to the reference temperature. This represents the constraint thermal displacement component caused by structural constraints.

[0011] Furthermore, in the non-uniform temperature field decoupling correction method for the inner shell integrity test during the containment construction period as described above, step S2 also introduces the shading coefficient of the shading object during the construction period to correct the temperature data in the three-dimensional transient temperature field.

[0012] Furthermore, in the non-uniform temperature field decoupling correction method for the inner shell integrity test during the containment construction period as described above, in step S1, a second temperature sensor is also provided in the inner shell space to monitor the temperature of the pressurized air during the inner shell integrity test.

[0013] Furthermore, in the non-uniform temperature field decoupling correction method for the inner shell integrity test during the containment construction period as described above, in step S3, the temperature data of the second temperature sensor is also introduced into the thermal displacement calculation model to correct the temperature of the three-dimensional transient temperature field.

[0014] Furthermore, as described above, the non-uniform temperature field decoupling correction method for the inner shell integrity test during the containment construction period involves verifying and iteratively optimizing the correction effect after step S3. This is achieved through three types of evaluation indicators: the coefficient of variation of displacement values ​​at each circumferential azimuth measuring point under the same pressure level after correction; the linear correlation coefficient between the corrected pure mechanical displacement and pressure; and the percentage deviation between the corrected displacement value and the finite element design prediction value. When all three evaluation indicators meet the preset engineering acceptance threshold, the correction is deemed effective. If any indicator fails to meet the engineering acceptance threshold, the process returns to step S3 to adjust the relevant parameters until the engineering acceptance threshold is met.

[0015] The present invention also provides a non-uniform temperature field decoupling correction system for the inner shell integrity test during containment construction, comprising: The data acquisition module is used to acquire time history data from the first temperature sensor and displacement sensor deployed on the inner and outer surfaces of the containment vessel and the outer surface of the outer shell. The temperature field reconstruction module is connected to the data acquisition module and is used to construct the three-dimensional transient temperature field of the inner shell. The solar radiation model is introduced to differentiate the temperature in different directions in the three-dimensional transient temperature field to obtain the corrected three-dimensional transient temperature field. The temperature-displacement decoupling module is connected to the temperature field reconstruction module and is used to establish a thermal displacement calculation model. The thermal displacement components of each measuring point are calculated by establishing the thermal displacement calculation model, and the pure mechanical displacement is obtained by subtracting the thermal displacement components from the total measured displacement. A memory storing instructions; and a processor configured to execute the instructions to implement the non-uniform temperature field decoupling correction method described above.

[0016] The present invention also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the above-described non-uniform temperature field decoupling correction method.

[0017] The beneficial technical effects of this invention are as follows: (1) The correction method of the present invention involves arranging temperature sensors and displacement sensors on the outer surface of the inner shell and the inner surface of the outer shell, and arranging a temperature sensor for monitoring the pressurized air inside the inner shell. Then, by introducing a solar radiation model and a shading correction coefficient, the surface temperature in different circumferential orientations is differentiated and corrected. Finally, the thermal displacement components at each measuring point are calculated using a thermal displacement calculation model, thereby obtaining the pure mechanical displacement. This pure mechanical displacement can be used for evaluating the behavior of the inner shell structure and can ensure the accuracy of the evaluation results, laying a data foundation for the long-term trend analysis and aging assessment of the containment structure performance.

[0018] (2) The correction method of the present invention replaces the fully coupled numerical simulation method that relies on professional finite element software in the prior art. This method can be used directly by field test engineers without the need for professional finite element analysts, which significantly reduces the threshold for use and the computational cost.

[0019] The correction system of the present invention has the beneficial technical effects of the above-described correction method, which will not be elaborated here. Attached Figure Description

[0020] Figure 1 The following is a flowchart of the overall process of the modified method of the present invention, showing the sequential relationship of steps S1 to S4.

[0021] Figure 2a This is a vertical layout diagram of the first temperature sensor of the present invention on the inner shell structure, showing the vertical layout distribution points.

[0022] Figure 2b This is a diagram showing the circumferential layout of the first temperature sensor of the present invention within the inner shell structure, illustrating the circumferential distribution points.

[0023] Figure 3 This is a schematic diagram of the circumferential partitioning of the inner shell of the present invention, showing the division of the four directional zones (east, west, south, and north) and the direction of solar radiation.

[0024] Figure 4 This is a schematic diagram of the three-dimensional transient temperature field reconstruction process of the present invention, showing the RBF interpolation process from finite measurement point data to the full structure temperature field, as well as the introduction of solar radiation model and shading correction coefficient.

[0025] Figure 5 This is a schematic diagram of the calculation process for the temperature-displacement decoupling correction of the present invention, showing the structure of the thermal displacement calculation model, the decomposition relationship of each displacement component, and the compressed air temperature rise correction term.

[0026] Figure 6 This is a schematic diagram of the evaluation index system for verifying the correction effect of the present invention, showing the calculation method, judgment logic and iterative feedback path of the three types of evaluation indexes.

[0027] Figure 7 This is a schematic diagram of the structure of the correction system of the present invention, showing the connection relationship between the data acquisition module, temperature field reconstruction module, decoupling correction module, verification and evaluation module, processor and memory.

[0028] Figure 8 This is a comparison chart of pressure-displacement curves before and after the correction of this invention, showing the discrete distribution of data in each direction before the correction and the effect of the data in each direction becoming more consistent after the correction. Detailed Implementation

[0029] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings.

[0030] It should be noted that the terms "first," "second," etc., used in the specification, claims, and drawings of this application are used to distinguish similar objects, rather than to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented in sequences other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion.

[0031] like Figure 1 The diagram shows a method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test provided by this invention, comprising the following four steps: S1: Temperature field monitoring deployment and data acquisition Several first temperature sensors and displacement sensors (at different measuring points) are deployed on the outer surface of the inner shell and the inner surface of the outer shell of the containment structure, respectively. Time-history data from the first temperature sensors and displacement sensors are simultaneously collected throughout the entire integrity test of the inner shell structure, and the temperature and displacement time-history data are timestamped and aligned. It should be noted that the displacement sensors are positioned close to their corresponding first temperature sensors to ensure a clear spatial correspondence during subsequent point-to-point decoupling. In addition, to ensure the accuracy of the inner shell evaluation data, a second temperature sensor is also deployed in the pressurized air space (pressurized air is applied to the inner shell to simulate the load under design accident conditions, verifying the load-bearing and sealing performance of the inner shell structure) to monitor the pressurized air temperature; the number of sensors deployed is determined as needed. This invention also deploys an atmospheric monitoring system outside the containment structure to simultaneously collect time-history data on atmospheric temperature, irradiance, and wind speed.

[0032] S2: Construct a three-dimensional transient temperature field and correct the data. Based on the temperature time history data of the first temperature sensor collected in step S1, the three-dimensional transient temperature field of the inner shell structure is constructed using the radial basis function (RBF) interpolation method. A solar radiation model with local meteorological data is introduced to correct the azimuth difference of the temperature data in the three-dimensional transient temperature field. At the same time, a shading correction coefficient during the construction period is also introduced to correct the local shading caused by scaffolding, formwork and construction equipment. Finally, the corrected three-dimensional transient temperature field is obtained.

[0033] S3: Temperature-Displacement Decoupling Correction A thermal displacement calculation model is established. Based on the corrected three-dimensional transient temperature field obtained in step S2, the thermal displacement components of each monitoring point are calculated. Then, the thermal displacement components are subtracted point by point from the total displacement collected in step S1 to obtain the pure mechanical displacement. It should be noted that when calculating the thermal displacement, different reference temperatures and correction parameters are used for different circumferential orientations, and the compressed air temperature rise data during the pressurization process is introduced for correction.

[0034] S4: Verification and Iterative Optimization of the Correction Effect The correction effect was verified using three types of evaluation indicators: the coefficient of variation of the displacement values ​​of each circumferential azimuth measuring point under the same pressure level after correction; the linearity of the pressure-displacement curve, which is the linear coefficient between the corrected pure mechanical displacement and pressure; and the percentage deviation from the design prediction value, which is the percentage deviation between the corrected displacement value and the predicted value. When all three evaluation indicators meet the preset engineering acceptance thresholds, the correction is deemed effective, and pure mechanical displacement data is output to evaluate the behavior of the inner shell structure.

[0035] like Figure 7 The figure shows the decoupling correction system provided by the present invention. The system includes a data acquisition module, a temperature field reconstruction module, a decoupling correction module, a verification and evaluation module, a memory, and a processor.

[0036] The data acquisition module includes a temperature acquisition unit, a displacement acquisition unit, a time synchronization unit, and a data storage unit. The temperature acquisition unit acquires data from a first temperature sensor deployed on the outer surface of the inner shell and the inner surface of the outer shell of the containment vessel, and data from a second temperature sensor deployed in the pressurized air space. The displacement acquisition unit acquires data from displacement sensors deployed on the outer surface of the inner shell and the inner surface of the outer shell of the containment vessel. The time synchronization unit synchronously acquires the first temperature sensor data and the displacement sensor data, and aligns the timestamps of the temperature sensor and the displacement sensor via GPS or NTP protocol. The data storage unit stores the historical data of the first temperature sensor, the second temperature sensor, and the displacement sensor.

[0037] The temperature field reconstruction module, connected to the data acquisition module via a data bus, includes a radial basis function interpolation unit (spatial interpolation unit), a solar radiation calculation unit, an occlusion correction unit, and a filtering unit. The radial basis function interpolation unit acquires data from the first temperature sensor in the data acquisition module and constructs a three-dimensional transient temperature field of the inner shell structure based on this data. The solar radiation calculation unit performs differential correction on the surface temperature at different locations within the three-dimensional transient temperature field. The occlusion correction unit corrects local occlusion caused by scaffolding, formwork, and construction equipment. The filtering unit processes time-dimension filtering and outliers, and finally outputs the corrected three-dimensional transient temperature field.

[0038] The decoupling correction module, connected to the temperature field reconstruction module via a data bus, includes a thermal displacement calculation unit, an azimuth difference processing unit, a compressed air correction unit, and a mechanical displacement extraction unit. The thermal displacement calculation unit calculates the thermal displacement components at each measuring point; the azimuth difference processing unit corrects for azimuth differences in different circumferential directions; the compressed air correction unit corrects for the temperature effect caused by compressed air; and the mechanical displacement extraction unit subtracts the thermal displacement component from the measured total displacement to obtain the pure mechanical displacement.

[0039] The verification and evaluation module, connected to the decoupling correction module via a data bus, includes an isotropic consistency evaluation unit, a linearity evaluation unit, a design value consistency unit, and a comprehensive judgment unit. The isotropic consistency evaluation unit calculates the coefficient of variation of displacement values ​​at each circumferential azimuth measuring point under the same pressure level after correction; the linearity evaluation unit calculates the linear correlation coefficient between the corrected pure mechanical displacement and pressure; the design value consistency unit calculates the deviation between the corrected displacement value and the finite element design prediction value; and the comprehensive judgment unit determines whether the three types of indicators meet the preset engineering acceptance thresholds. If the thresholds are met, the correction is deemed effective; otherwise, an adjustment parameter command is sent back to the decoupling correction module.

[0040] Memory and processor A memory that stores instructions; A processor configured to execute the instructions to implement the above-described non-uniform temperature field decoupling correction method.

[0041] The present invention also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the aforementioned non-uniform temperature field decoupling correction method. The computer-readable storage medium includes, but is not limited to, ROM, RAM, magnetic disks, optical disks, USB flash drives, and solid-state drives.

[0042] The method of the present invention will be further described below through specific embodiments: Example This invention focuses on the integrity test of the inner shell structure during the construction phase of a nuclear power plant's double-containment system. The nuclear power plant employs a double-containment design. The inner shell is a prestressed concrete structure with an inner diameter of approximately 44 meters, a wall thickness of 1.3 meters, and a height of approximately 80 meters. The outer shell is a reinforced concrete structure, which was not yet completed during the inner shell integrity test. The design pressure of the inner shell is 0.42 MPa (absolute pressure), and the integrity test pressure is 1.15 times the design pressure, i.e., 0.483 MPa.

[0043] The experiment was conducted in summer, during which the ambient temperature varied from 22 to 35°C between day and night, with significant temperature differences in the east, west, south, and north directions caused by solar radiation. The outer surface of the inner shell was directly exposed to the environment without any outer shell for insulation and buffering.

[0044] Step 1: Temperature field monitoring deployment and data acquisition (a) Deployment of the first temperature sensor and displacement sensor network.

[0045] Vertical Layout: The first temperature sensor and displacement sensor are deployed vertically along the inner and outer shells in L=5 layers, forming a vertical temperature and displacement monitoring layer. These layers are located at elevations +10.0m (bottom layer), +30.0m (lower middle layer), +45.0m (upper middle layer), +60.0m (near the dome arch), and +70.0m (near the semi-dome top). The vertical measuring points are numbered L1-L5. Figure 2a As shown.

[0046] Circumferential Layout: Temperature and displacement sensors are installed at P=4 points along the inner and outer shell circumferentially, forming a circumferential temperature and displacement monitoring section. This means one measuring point every 90°, numbered P1-P4. P1 is located due east, P2 due south, P3 due west, and P4 due north, as shown below. Figure 2b As shown.

[0047] Double-sided deployment: The above-described deployment method is used on both the outer surface of the inner shell and the inner surface of the outer shell to form a double-sided monitoring network. The total number of measuring points for the first temperature sensor is 2 × L × P. Additionally, a temperature sensor is deployed on the inner surface of the dome to monitor the dome temperature. The total number of measuring points for the first temperature sensor is 2 × 4 × 5 + 2 = 42.

[0048] Synchronous data acquisition: Both the first temperature sensor and the displacement sensor are connected to a unified data acquisition system to ensure that the temperature data and displacement data correspond in time.

[0049] (ii) Deployment of the second temperature sensor During the structural integrity test of the inner shell, compressed air needs to be pumped into the inner shell. Five second temperature sensors are installed in the compressed air space. The five second temperature sensors are distributed in different positions to monitor the temperature rise of the compressed air.

[0050] Step 2: Construct a three-dimensional transient temperature field and correct the data, such as... Figure 4 As shown.

[0051] (a) Spatial interpolation of radial basis functions Based on the temperature time history data of 42 first temperature sensors at a limited number of measuring points collected in step S1, a three-dimensional transient temperature field of the inner shell structure is constructed using the radial basis function (RBF) interpolation method. The RBF interpolation function is:

[0052] in: For any point in space exist Temperature value at any given time; For the first Each measuring point is at Weighting coefficients at time points, weighting coefficients It is determined by solving a system of linear equations consisting of known temperature values ​​at each time step; For radial basis functions, interpolation point To the Each measuring point Euclidean distance; radial basis functions Use multiquadric functions: , The shape parameter is set to 0.5-2.0 times the average spacing of the first temperature sensors, preferably 1.0 times. In this embodiment, the average spacing of the first temperature sensors is approximately 3.7m. .

[0053] It should be noted that at each time step, the weighting coefficients are calculated using the temperature values ​​from 42 known measuring points. Then, the temperature value at any spatial point of the inner shell structure is calculated to obtain the time. The three-dimensional temperature field is obtained. The above process is repeated for all time steps to obtain the time history of the three-dimensional transient temperature field.

[0054] (ii) Introduce a solar radiation model based on local meteorological data to differentiate the surface temperature in different circumferential directions.

[0055] A solar radiation model with local meteorological data is introduced to differentiate the surface temperature at different circumferential orientations of the inner shell. The core of the solar radiation model is based on the solar altitude angle. and azimuth Calculate the incident intensity of the sun on the outer surface of the inner shell at any given time in all directions.

[0056] Solar altitude angle and azimuth The calculation formula is as follows:

[0057] in: The latitude is the local latitude (30.5°N in this example). The solar declination is calculated based on the date of the experiment; It is the hour angle, with 0° at noon and a deviation of 15° per hour.

[0058] Formula for calculating solar radiation intensity:

[0059] in: for The intensity of solar radiation on a horizontal surface after atmospheric attenuation at any given time is determined by actual measurement at the local meteorological station or based on the solar constant. The atmospheric transparency coefficient and cloud correction coefficient are calculated. This refers to the circumferential azimuth angle of the inner shell; Sun azimuth.

[0060] Calculate the radiative temperature rise of the outer surface of the inner shell at various locations based on the solar radiation intensity:

[0061] in: The surface solar radiation absorption coefficient is 0.6 (for concrete surfaces). The surface convective heat transfer coefficient (take) ), This refers to the thermal conductivity of concrete.

[0062] It should be noted that the solar radiation model of the present invention can correct the inner shell surface temperature in the four directions of east, west, south and north. The corrected temperature can reflect the real-time changes of solar radiation and solve the problem of circumferential temperature difference in non-uniform temperature field.

[0063] (iii) Introducing a construction-period shading correction factor for local shading correction To address the shading effect of scaffolding, formwork, and construction equipment on solar radiation during the construction period, a shading correction factor k is introduced. s k s The method for determining it is as follows: 1. For each circumferential orientation zone of the inner shell, obtain the projected area of ​​scaffolding, formwork and construction equipment on the structural surface through on-site photography or laser scanning; 2. Calculate the shading area ratio V = shading projected area / surface area of ​​the structure in that azimuth region; 3. Determine k according to the following mapping table.s :

[0064] The corrected solar radiation temperature rise is:

[0065] This invention further improves the accuracy of temperature data by introducing a construction-period shading correction coefficient to correct for local shading.

[0066] Step 3, temperature-displacement decoupling correction, such as Figure 5 As shown.

[0067] (a) Establishing a thermal displacement calculation model It should be noted that the thermal displacement caused by temperature includes two components: 1. Free thermal displacement: The free expansion or contraction displacement of structural materials due to temperature changes. ,in This is the coefficient of linear expansion of the material. This refers to the change in temperature. 2. Constrained thermal displacement: Additional displacement caused by the inability of the structure to undergo free temperature deformation due to restrictions such as prestress and boundary constraints.

[0068] Establish a thermal displacement calculation model, and calculate the thermal displacement using the thermal displacement calculation model:

[0069] in: The coefficient of linear expansion of concrete is given, and its value range is [value range missing]. In this embodiment, it was determined through on-site sampling and testing that it was... ; For the measuring point at time The amount of temperature change relative to the reference temperature.

[0070] Reference temperature The average temperature of each measuring point during the steady-state phase before the test (2 hours before the start of the test) is taken; The additional thermal displacement component caused by structural constraints is calculated using a simplified model based on thin-shell theory:

[0071] in: The constraint coefficient is determined by field calibration tests or by a correlation model based on the prestress level, shell curvature radius, and wall thickness; this embodiment uses the field calibration method: during the pressure-free reference stage 2 hours before the test, the temperature change is approximately Measured displacement increment ,but

[0072] For the circumferential direction of the inner shell The value range is 0.3-0.5; for the vertical direction of the inner shell, The value range is 0.1-0.3. Due to the strong circumferential constraint of the prestressed concrete, the value is taken as... For the inner shell in the vertical direction, the constraint is relatively weak, so we take... .

[0073] Therefore, the total thermal displacement is:

[0074] Circumferential direction:

[0075] Vertical direction:

[0076] (ii) Differential treatment of temperature in different circumferential orientations (east, west, south, north) of the inner shell like Figure 3 As shown, the inner shell is divided into four azimuth zones: east, west, south, and north, each covering a 90° circumferential range. For the azimuth zones on the direct sunlight side (east, west, and south), the surface temperature corrected by the solar radiation model is used as the correction temperature for that azimuth zone. For the azimuth zone on the shaded side (north), the ambient temperature is used as the correction reference temperature for that azimuth zone. A reference temperature, constraint coefficient η, and construction-period shading correction coefficient k are independently established for each azimuth zone. s .

[0077] Eastern position zone: azimuth 315-45° (0° is due east); Southern orientation region: azimuth 45-135°; Western location region: azimuth 135-225°; Northern location region: azimuth 225-315°.

[0078] Establish independent reference temperatures and correction parameters for each directional region:

[0079] (iii) Correction for additional temperature effect of compressed air temperature rise During the pressurization process, the compressed air pressure increases from 0 MPa to 0.40 MPa. Due to the adiabatic or near-adiabatic compression process, the air temperature rises. An additional temperature effect correction formula is introduced for the compressed air temperature rise:

[0080] in: For a moment The measured temperature of the compressed air. To begin the experiment The initial temperature of the compressed air at all times (23.5°C in this example).

[0081] The additional temperature effect mainly acts on the measuring points on the inner surface of the inner shell. The thermal displacement correction formula for the measuring points on the inner surface is:

[0082] in: This represents the temperature change at the measuring point on the inner surface relative to the reference temperature. The air-structure heat exchange coefficient has a range of values. .

[0083] (iv) Calculation of purely mechanical displacement For each measuring point, the purely mechanical displacement is:

[0084] For measuring points on the outer surface:

[0085] For measuring points on the inner surface:

[0086] Perform the above calculations on all measuring points and all time steps to obtain the corrected pure mechanical displacement time history data.

[0087] Step 4, verification and iterative optimization of the correction effect, such as... Figure 6 As shown.

[0088] Structural behavior was evaluated based on the corrected pure mechanical displacement, and the correction effect was verified using three types of evaluation indicators: (a) Coefficient of uniformity C V Under the same pressure rating of the inner shell, calculate the coefficient of variation of the displacement values ​​at each circumferential azimuth measuring point:

[0089] in, The standard deviation of the displacement values ​​in each direction, This is the average of the displacement values ​​in each direction.

[0090] In this embodiment, under the design test pressure of 0.40 MPa, the C values ​​of the displacements in each direction before correction are... V It is 18.3%, and the corrected C V It dropped to 6.7%, which met the requirements. Threshold requirements. C V The engineering basis for the threshold: If C V If the error rate exceeds 10%, it indicates that the temperature correction in each direction is inadequate or there are local anomalies, and it is necessary to return to step S3 for inspection. ,or Parameters. When When the time is right, the indicator is deemed qualified.

[0091] (ii) Linearity of pressure-displacement curve Linear regression analysis was performed on the corrected pure mechanical displacement and pressure data to calculate the linear correlation coefficient. .

[0092] In this embodiment, the pressure-displacement curve before correction is... It is 0.872, after correction Increased to 0.971, meeting the requirements. Threshold requirements. The engineering basis for the threshold is that the inner shell should be in an elastic working state within the design test pressure range, and the pressure-displacement relationship should be approximately linear. This ensures that pressure is the primary driver of displacement, and residual temperature interference is sufficiently small. When the time is right, the indicator is deemed qualified.

[0093] (iii) Deviation in design value consistency δ Calculate the percentage deviation between the corrected displacement value and the finite element design prediction value:

[0094] In this embodiment, the maximum deviation before correction was 27.5%, and the maximum deviation after correction was reduced to 11.2%, meeting the threshold requirement of δ≤15%. The engineering basis for the δ threshold is: considering the uncertainty of the finite element model (approximately 5%-10%), the uncertainty of the measurement system (approximately 3%-5%), and the design margin, 15% is the acceptable upper limit for engineering deviation. When the time is right, the indicator is deemed qualified.

[0095] like Figure 8 The table shown is a comparison of pressure-displacement curves before and after correction. Before correction, the displacement data in the four directions of east, west, south, and north were discretely distributed with significant directional differences. After correction, the data in each direction tended to be consistent, and the pressure-displacement relationship showed good linearity.

[0096] (iv) Comprehensive evaluation and iterative optimization of the correction effect If all three types of evaluation indicators meet the preset threshold ( , , The temperature correction was deemed valid. The corrected pure mechanical displacement data can be used for internal shell structure behavior assessment.

[0097] If a certain indicator fails to meet the threshold, iterative optimization will be performed using the following method: Exceeding the standard: Check the reference temperature in each direction area and Get the value and recalibrate. ; Low: Check Check for data anomalies by determining the values ​​and inner surface temperature correction items. Too large: Check the differences between the structural parameters of the finite element design model and this embodiment, and adjust if necessary. and .

[0098] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art based on the technical solutions and inventive concepts disclosed in the present invention should be covered within the scope of protection of the present invention.

Claims

1. A method for decoupling and correcting non-uniform temperature fields during containment construction integrity testing of the inner shell, characterized in that, Includes the following steps: S1: Temperature field monitoring setup and data acquisition; that is, the first temperature sensor and displacement sensor are set up at different measuring points on the outer surface of the inner shell and the inner surface of the outer shell of the containment, and the time history data of the first temperature sensor and displacement sensor are collected synchronously throughout the entire process of the inner shell integrity test. S2: Construct a three-dimensional transient temperature field and correct the data; that is, based on the time history data of the first temperature sensor at different measuring points collected in step S1, the radial basis function interpolation method is used to construct the three-dimensional transient temperature field of the inner shell, and a solar radiation model with local meteorological data is introduced to differentiate and correct the temperature data of the three-dimensional transient temperature field to obtain the corrected three-dimensional transient temperature field. S3: Temperature-displacement decoupling correction; that is, establishing a thermal displacement calculation model, calculating the thermal displacement components of each measuring point based on the corrected three-dimensional transient temperature field obtained in step S2, and then subtracting the thermal displacement components point by point from the total displacement collected in step S1 to obtain the pure mechanical displacement.

2. The method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test as described in claim 1, characterized in that, In step S1, the position of the displacement sensor is close to the position of the corresponding first temperature sensor.

3. The method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test as described in claim 1, characterized in that, In step S2, the radial basis function interpolation formula is: in: For any point in space At any moment Temperature value, For the first Each temperature sensor measuring point at time [time] The weighting coefficients, For radial basis functions, interpolation point To the Each measuring point The Euclidean distance.

4. The method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test as described in claim 1, characterized in that, In step S2, the solar radiation model calculates the solar radiation intensity of each circumferential surface of the inner shell at different times based on the solar altitude angle and azimuth angle in the local meteorological data.

5. The method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test as described in claim 1, characterized in that, In step S3, the thermal displacement calculation model calculates the thermal displacement components at each measuring point using the following formula: in: This is the coefficient of linear expansion of concrete. For the measurement point at time The amount of temperature change relative to the reference temperature. This represents the constraint thermal displacement component caused by structural constraints.

6. The method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test as described in claim 1, characterized in that, In step S2, the shading coefficient of the obstruction during the construction period is also introduced to correct the temperature data in the three-dimensional transient temperature field.

7. The method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test as described in claim 1, characterized in that, In step S1, a second temperature sensor is also provided in the inner space of the inner shell to monitor the temperature of the compressed air during the inner shell integrity test.

8. The method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test as described in claim 7, characterized in that, In step S3, the thermal displacement calculation model also incorporates temperature data from a second temperature sensor to correct the temperature of the three-dimensional transient temperature field.

9. The method for decoupling and correcting the non-uniform temperature field during the containment construction period inner shell integrity test as described in any one of claims 1-8, characterized in that, After step S3, the correction effect is verified and iteratively optimized; that is, the correction effect is verified through three types of evaluation indicators, namely: the coefficient of variation of the displacement values ​​of each circumferential azimuth measuring point after correction under the same pressure level; and the linear correlation coefficient between the pure mechanical displacement and pressure after correction. The percentage deviation between the corrected displacement value and the finite element design prediction value; when all three evaluation indicators meet the preset engineering acceptance threshold, the correction is deemed effective; If any indicator fails to meet the project acceptance threshold, return to step S3 to adjust the relevant parameters until the project acceptance threshold is met.

10. A non-uniform temperature field decoupling correction system for an integral test of the inner shell during containment construction, characterized in that, include: The data acquisition module is used to acquire time history data from the first temperature sensor and displacement sensor deployed on the inner and outer surfaces of the containment shell and the inner surface of the containment shell. The temperature field reconstruction module is connected to the data acquisition module and is used to construct the three-dimensional transient temperature field of the inner shell. The solar radiation model is introduced to differentiate the temperature of different measuring points in the three-dimensional transient temperature field to obtain the corrected three-dimensional transient temperature field. The temperature-displacement decoupling module is connected to the temperature field reconstruction module and is used to establish a thermal displacement calculation model. The thermal displacement components of each measuring point are calculated through the thermal displacement calculation model, and the pure mechanical displacement is obtained by subtracting the thermal displacement components from the total measured displacement. A memory that stores instructions; as well as A processor configured to execute the instructions to implement the non-uniform temperature field decoupling correction method according to any one of claims 1 to 9.

11. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the non-uniform temperature field decoupling correction method as described in any one of claims 1 to 9.

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