JP6578250B2 - Turbine component strain estimation method and apparatus, and turbine component evaluation method - Google Patents

Description

  The present invention relates to a turbine component strain estimation method and apparatus for estimating inelastic strain in a member used as a turbine component in a steam turbine, a gas turbine, or the like, and a turbine component evaluation method.

  For example, a gas turbine includes a compressor, a combustor, and a turbine. The air taken in from the air intake port is compressed by the compressor to become high-temperature and high-pressure compressed air. In the combustor, the fuel is supplied to the compressed air and burned, so that the high-temperature and high-pressure is burned The combustion gas (working fluid) is obtained, the turbine is driven by the combustion gas, and the generator connected to the turbine is driven. In this gas turbine, the rotor blades used in the compressor and turbine are damaged by the influence of centrifugal force and heat acting during rotation. For this reason, we are striving to maintain soundness by conducting predictive analysis of damage to used rotor blades and conducting inspections such as predicting damage and the presence or absence of cracks.

  As a method for evaluating damage by the amount of creep deformation with respect to a moving blade, for example, there is one described in Patent Document 1 below. The method for determining the creep capability of a turbine component described in Patent Document 1 is applied to a plurality of turbine components until a measurable amount of tensile stress, centrifugal stress, and thermal stress is obtained. Compared to known creep properties for the materials used, components that exhibit a creep greater than a defined amount are separated and removed from service.

JP2013-253599A

  In the conventional method for determining the creep capability of the turbine component, creep deformation is induced by applying tensile stress, centrifugal stress, and thermal stress to the rotor blade with a test device. The blade is evaluated by comparing the quantity or its accumulation rate with a tolerance value defined from a material having creep properties. However, there is a difference in the amount of strain between the moving blades that have been subjected to various stresses by the test equipment and the moving blades that have been subjected to various stresses during actual plant operation, and the creep damage of the moving blades is highly accurate. It is difficult to predict.

  SUMMARY OF THE INVENTION An object of the present invention is to solve the above-described problems, and to provide a turbine component strain estimation method and apparatus and a turbine component evaluation method capable of accurately estimating inelastic strain generated in a turbine component. To do.

  In order to achieve the above object, a turbine component strain estimation method according to the present invention includes a step of three-dimensionally measuring a turbine component before deformation, a step of creating an analysis model of the turbine component, and the turbine component before deformation. Dividing the plurality of meshes divided into unit regions of a predetermined size, and inputting the uniform inelastic strain to the plurality of meshes in the unit regions using the analysis model Forming an analytical model shape of the component; three-dimensionally measuring the turbine component after deformation; comparing the analytical model shape of the turbine component with the shape of the turbine component after deformation; and the turbine component Analytical model shape and deformation A step of changing an inelastic strain input to the analysis model when a result of comparison with the shape of the subsequent turbine component does not satisfy a convergence condition; and an analysis model shape of the turbine component and a shape of the turbine component after deformation And determining the inelastic strain input to the analysis model when the comparison result satisfies the convergence condition.

  Therefore, a plurality of meshes obtained by dividing the turbine component before deformation are divided into unit regions of a predetermined size, and uniform inelastic strain is input to each mesh in the unit region using an analysis model. An analytical model shape is formed and compared with the turbine component after deformation. If the comparison result does not satisfy the convergence condition, the inelastic strain input to the analysis model is repeatedly changed so that the comparison result satisfies the convergence condition, and the inelastic strain that satisfies the convergence condition is determined. Output. Therefore, by inputting uniform inelastic strain to the unit area, the number of variables (parameters) at the time of inverse analysis can be reduced and divergence can be prevented, and analysis can be performed by freely inputting inelastic strain. This makes it possible to accurately estimate the inelastic strain generated in the turbine component.

  The turbine component strain estimation method of the present invention is characterized in that a plurality of unit regions are set for the turbine component, and different inelastic strains are input to the plurality of unit regions.

  Accordingly, by inputting inelastic strains having different sizes to the plurality of set unit regions, it is possible to form an appropriate analysis model shape corresponding to the deformation of the turbine component.

  The turbine component strain estimation method of the present invention is characterized in that the uniform inelastic strain input using the analysis model is the same inelastic strain.

  Therefore, by inputting the same inelastic strain to a plurality of meshes in one unit region, the number of variables (parameters) can be reduced and divergence can be prevented.

  The turbine component strain estimation method of the present invention is characterized in that the uniform inelastic strain input using the analysis model is a linearly varying inelastic strain.

  Therefore, by inputting linearly changing inelastic strain to a plurality of meshes in one unit region, the number of variables (parameters) can be reduced and divergence can be prevented.

  In the turbine component strain estimation method of the present invention, the convergence condition is such that the deformation difference between the analysis model shape of the turbine component and the shape of the turbine component after deformation measured three-dimensionally is within a preset specified value. It is characterized by that.

  Therefore, when the deformation difference between the shape of the analytical model and the shape of the turbine component after deformation is within the specified value, the inelastic strain that satisfies the convergence condition and is input to the analytical model is determined, thereby marking the turbine component. There is no need to attach or process, and the difference in deformation can be easily compared.

  In the turbine component strain estimation method of the present invention, the deformation difference is a displacement volume amount between a volume shape of an analysis model of the turbine component and a volume shape of the turbine component after deformation measured three-dimensionally. It is said.

  Therefore, the deformation difference can be obtained with high accuracy by setting the deformation difference as the displacement volume amount between the volume shape of the analysis model and the volume shape of the turbine component after the deformation.

  In the turbine component strain estimation method of the present invention, a step of three-dimensionally measuring a turbine component before deformation, a step of creating an analysis model of the turbine component, and inputting a plurality of types of deformation conditions into the analysis model. Forming a plurality of analytical model shapes of the turbine component, measuring a three-dimensional measurement of the turbine component after deformation, and comparing the plurality of analytical model shapes of the turbine component and the shape of the turbine component after deformation And determining an inelastic strain input to the analysis model shape that minimizes a deformation difference between the plurality of analysis model shapes of the turbine component and the shape of the turbine component after deformation. Features .

  Accordingly, a plurality of types of deformation conditions are input to the analysis model to form a plurality of analysis model shapes of the turbine component and compared with the shape of the turbine component after the deformation. Here, the inelastic strain that minimizes the deformation difference between the plurality of analysis model shapes of the turbine component and the shape of the turbine component after the deformation is determined and output. Therefore, the number of variables (parameters) at the time of inverse analysis can be reduced to prevent divergence, and the inelastic strain generated in the turbine component can be accurately analyzed by inputting inelastic strain freely and performing analysis. Can be estimated.

  In addition, the turbine component strain estimation apparatus of the present invention includes a measurement unit that three-dimensionally measures a turbine component, and a plurality of meshes obtained by dividing the turbine component before deformation measured by the measurement unit in units of a predetermined size. A calculation unit that divides into regions and inputs uniform inelastic strain to the plurality of meshes of the unit region using an analysis model to obtain an analysis model shape of the turbine component; and an analysis model of the turbine component A comparison unit that compares the shape and the shape of the turbine component after deformation measured by the measurement unit, and the comparison unit repeats the processing of the calculation unit when a comparison result of the comparison unit does not satisfy a convergence condition. A determination unit that determines the inelastic strain to be input to the analysis model when the comparison result of It is characterized in further comprising.

  Therefore, a plurality of meshes obtained by dividing the turbine component before deformation are divided into unit regions of a predetermined size, and uniform inelastic strain is input to each mesh in the unit region using an analysis model. An analytical model shape is formed and compared with the turbine component after deformation. If the comparison result does not satisfy the convergence condition, the inelastic strain input to the analysis model is repeatedly changed so that the comparison result satisfies the convergence condition, and the inelastic strain that satisfies the convergence condition is determined. Output. Therefore, by inputting uniform inelastic strain to the unit area, the number of variables (parameters) at the time of inverse analysis can be reduced and divergence can be prevented, and analysis can be performed by freely inputting inelastic strain. This makes it possible to accurately estimate the inelastic strain generated in the turbine component.

  The turbine component evaluation method of the present invention is characterized in that the turbine component is evaluated using inelastic strain estimated by the turbine component strain estimation method.

  Therefore, the number of variables (parameters) at the time of inverse analysis can be reduced and divergence can be prevented, and the inelastic strain generated in the turbine component can be accurately analyzed by inputting inelastic strain freely and performing analysis. As a result, the turbine component can be evaluated with high accuracy.

  According to the turbine component strain estimation method and apparatus and turbine component evaluation method of the present invention, the number of variables (parameters) at the time of inverse analysis can be reduced to prevent divergence, and inelastic strain can be freely reduced. By inputting and analyzing, inelastic strain generated in the turbine component can be accurately estimated.

FIG. 1 is a block configuration diagram illustrating a turbine rotor blade strain estimation apparatus according to a first embodiment. FIG. 2 is a flowchart showing a method for evaluating a turbine rotor blade after use. FIG. 3 is a flowchart showing a method for evaluating the turbine rotor blade after the deformation process. FIG. 4 is a flowchart showing the turbine blade distortion estimation method of the first embodiment. FIG. 5 is a schematic diagram for explaining a method for estimating the distortion of the turbine rotor blade. FIG. 6 is a flowchart showing a turbine blade distortion estimation method according to the second embodiment.

  Exemplary embodiments of a turbine component strain estimation method according to the present invention will be described below in detail with reference to the accompanying drawings. In addition, this invention is not limited by this embodiment, and when there are two or more embodiments, what comprises combining each embodiment is also included.

[First Embodiment]
In the first embodiment, a turbine blade is used as a turbine component. The turbine blade evaluation method using the turbine blade distortion estimation method is to perform three-dimensional (3D) measurement on the deformed turbine blade and perform inverse analysis (FEM analysis) using the three-dimensional measurement result. By performing the above, the amount of inelastic strain generated in the turbine blade is predicted, and the turbine blade is evaluated.

  There are the following three factors that cause deformation of the turbine blade. The first factor is various stresses acting on the turbine blades during operation of the gas turbine when the turbine blades are mounted on an actual gas turbine. Elastic strain occurs. The second factor is a bending process (strain correction) performed for shape correction in the manufacturing process of the turbine blade, and residual stress is generated at this time because plastic deformation is applied to the turbine blade. The third factor is shot peening performed in the manufacturing process of the turbine rotor blade in order to apply residual stress due to plastic deformation, and the blade may bend even if uniform residual stress is applied to the entire surface of the turbine rotor blade. Residual stress is generated because plastic deformation is applied to the turbine blade pole surface at this time.

  In the turbine blade evaluation method using the turbine blade distortion estimation method of the first embodiment, the amount of inelastic strain generated in the turbine blade deformed due to the above-described factors is estimated. Is to evaluate.

  FIG. 1 is a block configuration diagram illustrating a turbine rotor blade strain estimation apparatus according to a first embodiment.

  As shown in FIG. 1, the turbine blade distortion estimation device 10 of the first embodiment includes an analysis device 11, which includes a measurement unit 12, a display unit 13, a storage unit 14, and the like. Is connected. The analysis device 11 includes a calculation unit 21, a comparison unit 22, and a determination unit 23.

  The measuring section 12 is a turbine blade (hereinafter referred to as a moving blade) 31 (see FIG. 5) before being manufactured and mounted on a gas turbine (before deformation) or before deformation processing (see FIG. 5), and a moving blade 33 after use or after deformation processing. Is measured three-dimensionally (3D). The analysis device 11 sets a predetermined inelastic strain and performs forward analysis (FEM analysis) to form an analysis model of the moving blade 31, and compares the analysis model of the moving blade 31 with the deformed moving blade 31. Then, the amount of inelastic strain generated in the moving blade 31 is predicted by performing inverse analysis. The display unit 13 displays the amount of inelastic strain generated in the moving blade 31 estimated by the analysis device 11, and the storage unit 14 stores data obtained by the sequential calculation by the analysis device 11.

  In addition, the calculation unit 21 divides a plurality of meshes obtained by dividing the surface and the inside of the moving blade 31 before deformation measured by the measurement unit 12 into unit regions of a predetermined size, and uses the analysis model to determine the unit regions. A uniform inelastic strain is input to each mesh to obtain an analysis model shape of the moving blade 31. The comparison unit 22 compares the analysis model shape of the moving blade 31 with the deformed shape of the moving blade 31. The determination unit 23 repeats the processing of the calculation unit 21 when the comparison result of the comparison unit 22 does not satisfy the convergence condition, while the inelastic strain input to the analysis model when the comparison result of the comparison unit 22 satisfies the convergence condition. It will be confirmed.

  First, a method for evaluating a turbine blade after deformation will be described. FIG. 2 is a flowchart showing a turbine blade evaluation method after use, and FIG. 3 is a flowchart showing a turbine blade evaluation method after deformation processing.

  As shown in FIG. 2, the moving blade 31 is manufactured in step S11, and the three-dimensional shape of the moving blade 31 before deformation is measured by the measuring unit 12 in step S12. In step S13, the rotor blade 31 is mounted on a gas turbine and used by operating the gas turbine. In step S14, the operation of the gas turbine is stopped, the moving blade 31 is removed from the gas turbine, and the three-dimensional shape of the deformed moving blade 31 is measured by the measuring unit 12. In step S15, FEM analysis (finite element analysis) of inelastic strain in the moving blade 31 is performed, and in step S16, the creep strain amount (strain generation amount) of the moving blade 31 is estimated. In step S17, the rotor blade 31 is evaluated based on the estimated creep strain amount. The evaluation of the moving blade 31 is to determine the continued use of the moving blade 31 by comparing the estimated creep strain amount with a preset specified value.

  As shown in FIG. 3, the moving blade 31 is manufactured (during manufacture) in step S <b> 21, and the three-dimensional shape of the moving blade 31 before deformation is measured by the measuring unit 12 in step S <b> 22. Here, when the measurement unit 12 cannot measure the three-dimensional shape of the moving blade 31 before deformation, the design model may be used instead. In step S23, deformation processing is performed on the moving blade 31. This deformation process includes a bending process performed for the above-described shape correction, work hardening by plastic deformation, and shot peening performed for imparting residual stress. In step S <b> 24, the measurement unit 12 measures the three-dimensional shape of the deformed moving blade 31 that has undergone the deformation process. In step S25, FEM analysis (finite element analysis) of inelastic strain in the moving blade 31 is performed, and in step S26, the plastic strain amount (the amount of plastic strain generated) of the moving blade 31 is estimated. In step S27, the rotor blade 31 is evaluated based on the estimated amount of plastic strain.

  Next, a method for estimating the distortion of the turbine blade will be described. Specifically, in FIG. 2 and FIG. 3, the processing of steps S12 and S22 to steps S16 and S26 will be described. FIG. 4 is a flowchart illustrating a turbine blade distortion estimation method according to the first embodiment, and FIG. 5 is a schematic diagram for explaining the turbine blade distortion estimation method.

  As shown in FIGS. 4 and 5, in step S <b> 31, the measurement unit 12 measures the three-dimensional shape of the moving blade 31 before deformation, and in step S <b> 32, the calculation unit 21 analyzes the analysis model of the moving blade 31. Create Then, in step S33, the calculation unit 21 partitions a plurality of meshes obtained by dividing the surface and the interior of the moving blade 31 before deformation into unit regions of a predetermined size, and uses the analysis model in step S34. The uniform inelastic strain is input to a plurality of meshes in the unit area.

  That is, the space and the inside of the moving blade 31 before deformation are divided by a plurality of meshes to discretize the space, and the space formed by the plurality of meshes is partitioned as a unit region of a predetermined size. For example, when the region S is enlarged, a plurality of meshes are divided by a predetermined number, and unit regions A1, A2, A3,... Are set. In this case, in a region where the amount of inelastic strain generated by experiments or forward analysis is large, it is desirable that the unit region is divided finely by reducing the area of one unit region. Further, in a region where cracks or the like that are obtained in advance by experiments or forward analysis are likely to occur, it is desirable to reduce the area of one unit region and to divide the unit region finely. Furthermore, in a region where the difference (gradient) in the generation amount of inelastic strain obtained in advance by experiments or forward analysis is large, it is desirable to make the unit region finely divided by reducing the area of one unit region.

  When performing reverse analysis of creep strain during operation of the rotor blade 31, it is necessary to provide a unit region on the entire surface and inside of the blade surface. On the other hand, when performing reverse analysis of plastic strain for strain correction, It is only necessary to finely divide only the periphery where the press jig comes into contact. Also, since shot peening causes plastic deformation only on the pole surface, the unit region may be set only on the pole surface.

  Then, uniform inelastic strain is input to each mesh of a plurality of unit regions. Here, the uniform inelastic strain is an inelastic strain having the same magnitude set corresponding to a predetermined condition. The uniform inelastic strain is an inelastic strain that changes (increases or decreases) linearly (directly) from one corner of the unit region to the other corner (control point). In this case, the magnitude of inelastic strain is obtained by inverse analysis.

  Further, by dividing a space formed by a plurality of meshes as unit areas of a predetermined size, a plurality of unit areas are set for the surface and the inside of the moving blade 31, and each unit area is different. The magnitude of inelastic strain will be input. In step S <b> 34, when an inelastic strain having a predetermined size is input to each mesh in the plurality of unit regions using the analysis model, the calculation unit 21 obtains the analysis model shape 32 of the moving blade 31.

  In step S35, the measurement unit 12 measures the three-dimensional shape of the deformed moving blade 33. In step S36, the comparison unit 22 determines the analysis model shape 32 of the moving blade 31 and the deformed moving blade 33. Compare the shape. In step S <b> 37, the determination unit 23 determines whether the comparison result between the analysis model shape 32 of the moving blade 31 and the shape of the deformed moving blade 33 satisfies the convergence condition.

  Here, the convergence condition is that the deformation difference between the analysis model shape 32 of the moving blade 31 and the shape of the deformed moving blade 33 is within a predetermined value set in advance. Specifically, the deformation difference is a deviation volume amount between the volume shape of the analysis model shape 32 of the moving blade 31 and the volume shape of the deformed moving blade 33 measured in three dimensions. The displacement volume may be a square sum of the displacement lengths. When the three-dimensional shape of the analysis model shape 32 of the moving blade 31 and the three-dimensional shape of the deformed moving blade 33 are superimposed, the volume does not overlap.

  If it is determined in step S37 that the deformation difference between the analysis model shape 32 of the moving blade 31 and the shape of the deformed moving blade 33 is not within the specified value (No), the process returns to step S34 and input to the analysis model. The magnitude of the inelastic strain to be changed is changed (increased or decreased), and the processes of steps S5, S36, and S37 are repeated. On the other hand, if it is determined in step S37 that the deformation difference between the analysis model shape 32 of the moving blade 31 and the shape of the deformed moving blade 33 is within the specified value (Yes), the analysis model is determined in step S38. The magnitude of the inelastic strain input to is determined and output as an estimated value.

  As described above, in the method for estimating the distortion of the turbine component according to the first embodiment, the step of three-dimensionally measuring the moving blade 31 before deformation, the step of creating an analysis model of the moving blade 31, and the moving blade before deformation. A step of dividing a plurality of meshes of which the surface and the interior of 31 are divided into unit areas of a predetermined size, and inputting a uniform inelastic strain to the plurality of meshes of the unit areas using an analysis model The step of forming the analysis model shape 32 of the moving blade 31, the step of three-dimensionally measuring the deformed moving blade 31, and the step of comparing the analysis model shape 32 of the moving blade 31 and the shape of the deformed moving blade 33. Changing the inelastic strain input to the analysis model when the comparison result between the analysis model shape 32 of the moving blade 31 and the shape of the deformed moving blade 33 does not satisfy the convergence condition; And a step of comparison between the shape of the blade 33 after deformation analysis model shape 32 is fixed strain inelastic entered into the analysis model when the convergence condition is satisfied.

  Therefore, by inputting a uniform inelastic strain in the unit area, the number of variables (parameters) at the time of inverse analysis can be reduced and divergence can be prevented. By performing the above, it is possible to accurately estimate the inelastic strain generated in the moving blade 31.

  In the turbine component strain estimation method of the first embodiment, a plurality of unit regions are set with respect to the surface and the inside of the moving blade 31, and different inelastic strains are input for each of the plurality of unit regions. Therefore, an appropriate analysis model shape 32 corresponding to the deformation of the moving blade 31 can be formed.

  In the turbine component strain estimation method of the first embodiment, the same inelastic strain is set as the uniform inelastic strain input using the analysis model. Therefore, the number of variables (parameters) can be reduced and divergence can be prevented.

  In the turbine component strain estimation method of the first embodiment, linearly changing inelastic strain is set as the uniform inelastic strain input using the analysis model. Therefore, the number of variables (parameters) can be reduced and divergence can be prevented.

  In the turbine component strain estimation method according to the first embodiment, as a convergence condition, the deformation difference between the analysis model shape 32 of the moving blade 31 and the shape of the deformed moving blade 33 is within a preset specified value. It is set. Accordingly, when the deformation difference between the analysis model shape 32 and the shape of the deformed moving blade 33 is within a specified value, the inelastic strain that satisfies the convergence condition and is input to the analysis model is determined, thereby moving the moving blade 31. It is not necessary to mark or process the pattern, and the difference in deformation can be easily compared.

  In the turbine component strain estimation method of the first embodiment, the displacement volume between the volume shape of the analysis model of the moving blade 31 and the volume shape of the deformed moving blade 33 is set as the deformation difference. Therefore, the deformation difference can be obtained with high accuracy.

  In the turbine component strain estimation apparatus of the first embodiment, the measurement unit 12 that three-dimensionally measures the moving blade 31 and the surface and the inside of the moving blade 31 before deformation measured by the measuring unit 12 are divided. A plurality of meshes are divided into unit regions of a predetermined size, and uniform inelastic strain is input to the plurality of meshes in the unit region using the analysis model to obtain the analysis model shape 32 of the moving blade 31. When the comparison result of the calculation unit 21, the analysis model shape 32 of the moving blade 31 and the shape of the deformed moving blade 33 measured by the measuring unit 12 does not satisfy the convergence condition And a determination unit 23 that determines the inelastic strain to be input to the analysis model when the comparison result of the comparison unit 22 satisfies the convergence condition.

  Therefore, by inputting a uniform inelastic strain in the unit area, the number of variables (parameters) at the time of inverse analysis can be reduced and divergence can be prevented. By performing the above, it is possible to accurately estimate the inelastic strain generated in the moving blade 31.

  In the turbine component evaluation method of the first embodiment, the moving blade 31 is evaluated using the inelastic strain estimated by the turbine component strain estimation method. Accordingly, the number of variables (parameters) at the time of inverse analysis can be reduced to prevent divergence, and the inelastic strain generated in the moving blade 31 can be accurately analyzed by freely inputting inelastic strain. As a result, the rotor blade 31 can be evaluated with high accuracy.

[Second Embodiment]
FIG. 6 is a flowchart showing a turbine blade distortion estimation method according to the second embodiment. The basic configuration of the present embodiment is substantially the same as that of the first embodiment described above, and a member having the same function as that of the first embodiment described above will be described with reference to FIG. The same reference numerals are attached and detailed description is omitted.

  In the second embodiment, as shown in FIG. 1, the turbine blade inelastic strain estimation device 10 of the second embodiment is configured by connecting a measurement unit 12, a display unit 13, and a storage unit 14 to an analysis device 11. The analysis device 11 includes a calculation unit 21, a comparison unit 22, and a determination unit 23.

  The measuring unit 12 performs three-dimensional measurement of the moving blade 31 before use (before deformation) and the moving blade 33 after use (after deformation). The analysis device 11 sets a predetermined inelastic strain and performs forward analysis (FEM analysis) to form a plurality of analysis model shapes of the moving blade 31, and the analysis model of the moving blade 31 and the deformed moving blade 31. Is used to predict the amount of inelastic strain generated in the rotor blade 31. The display unit 13 displays the amount of inelastic strain generated in the moving blade 31 estimated by the analysis device 11, and the storage unit 14 stores a plurality of analysis model shapes calculated by the analysis device 11.

  Here, a method for estimating the distortion of the turbine rotor blade will be described. As shown in FIG. 6, in step S41, the measurement unit 12 measures the three-dimensional shape of the moving blade 31 before deformation, and in step S42, the calculation unit 21 creates an analysis model of the moving blade 31. . In step S43, the calculation unit 21 inputs and analyzes a plurality of types of deformation conditions (deformation modes) in the analysis model, thereby forming a plurality of analysis model shapes of the moving blade 31 in the storage unit 14. Remember and create a database. Here, the multiple types of deformation conditions (deformation modes) include, for example, stress and temperature acting on the moving blade 31.

  In step S44, the measurement unit 12 measures the three-dimensional shape of the deformed moving blade 33. In step S45, the comparison unit 22 performs a plurality of analyzes of the moving blade 31 stored in the database of the storage unit 14. The model shape is compared with the shape of the rotor blade 31 after deformation. In step S46, the determination unit 23 determines the magnitude of the inelastic strain input to the analysis model shape that minimizes the deformation difference between the plurality of analysis model shapes and the shape of the deformed rotor blade 31. Output as an estimated value.

  As described above, in the turbine component strain estimation method according to the second embodiment, the step of three-dimensionally measuring the blade 31 before deformation, the step of creating an analysis model of the blade 31, and a plurality of types of analysis models are included. The step of forming a plurality of analysis model shapes of the moving blade 31 by inputting the deformation conditions of the above, a step of three-dimensionally measuring the moving blade 31 after deformation, the plurality of analysis model shapes of the moving blade 31 and the movement after deformation The step of comparing the shape of the blade 31 and the step of determining the inelastic strain input to the analysis model shape that minimizes the deformation difference between the plurality of analysis model shapes of the blade 31 and the shape of the blade 31 after deformation. And have.

  Accordingly, a plurality of types of deformation conditions are input to the analysis model to form a plurality of analysis model shapes of the moving blade 31 and compared with the shape of the moving blade 31 after deformation. Here, the inelastic strain that minimizes the deformation difference between the plurality of analysis model shapes of the moving blade 31 and the shape of the deformed moving blade 31 is determined and output. Therefore, the number of variables (parameters) at the time of inverse analysis can be reduced and divergence can be prevented, and inelastic strain generated in the moving blade 31 can be accurately analyzed by inputting inelastic strain freely and performing analysis. It can be estimated well.

  In the above-described embodiment, the turbine blade 31 is used as a turbine component. However, the turbine blade 31 is not limited to the turbine blade 31, and may be a compressor blade, another rotating body, or other member. It is effective for members having a dimensional shape.

DESCRIPTION OF SYMBOLS 10 Turbine blade distortion estimation device 11 Analysis device 12 Measurement unit 13 Display unit 14 Storage unit 21 Calculation unit 22 Comparison unit 23 Judgment unit 31, 33 Turbine blade (turbine component)
32 Analysis model shape

Claims (9)

Three-dimensional measurement of turbine components before deformation;
Creating an analytical model of the turbine component;
Partitioning a plurality of meshes obtained by dividing the turbine component before deformation into unit regions of a predetermined size;
Inputting uniform inelastic strain to the plurality of meshes in the unit region using the analysis model to form an analysis model shape of the turbine component;
Three-dimensional measurement of the turbine component after deformation;
Comparing the analytical model shape of the turbine component with the deformed shape of the turbine component;
When the result of comparison between the analytical model shape of the turbine component and the deformed turbine component shape does not satisfy the convergence condition, the inelastic strain input to the analytical model is changed and the analytical model shape of the turbine component is changed again. Forming step;
Determining the inelastic strain input to the analytical model when a comparison result between the analytical model shape of the turbine component and the shape of the turbine component after deformation satisfies a convergence condition;
A strain estimation method for a turbine component, comprising:   2. The turbine component strain estimation method according to claim 1, wherein a plurality of unit regions are set for the turbine component, and different inelastic strains are input to the plurality of unit regions. 3.   The turbine component strain estimation method according to claim 1, wherein the uniform inelastic strain input using the analysis model is the same inelastic strain.   The turbine component strain estimation method according to claim 1, wherein the uniform inelastic strain input using the analysis model is a linearly varying inelastic strain.   2. The convergence condition according to claim 1, wherein a deformation difference between an analysis model shape of the turbine component and a shape of the turbine component after deformation measured in three dimensions is within a predetermined value set in advance. The turbine component strain estimation method according to claim 4.   6. The turbine component according to claim 5, wherein the deformation difference is a deviation volume amount between a volume shape of an analysis model of the turbine component and a volume shape of the turbine component after deformation measured three-dimensionally. Strain estimation method. Three-dimensional measurement of turbine components before deformation;
Creating an analytical model of the turbine component;
Inputting a plurality of types of deformation conditions into the analysis model to form a plurality of analysis model shapes of the turbine component;
Three-dimensional measurement of the turbine component after deformation;
Comparing a plurality of analytical model shapes of the turbine component with shapes of the turbine component after deformation;
Determining an inelastic strain input to the analytical model shape that minimizes a deformation difference between the plurality of analytical model shapes of the turbine component and the shape of the turbine component after deformation;
A strain estimation method for a turbine component, comprising: A measurement unit for three-dimensional measurement of turbine components;
A plurality of meshes obtained by dividing the turbine component before deformation measured by the measurement unit are partitioned into unit regions of a predetermined size, and uniform with respect to the plurality of meshes in the unit regions using an analysis model A calculation unit for inputting an inelastic strain to obtain an analysis model shape of the turbine component;
A comparison unit for comparing the analysis model shape of the turbine component and the shape of the turbine component after deformation measured by the measurement unit;
A determination unit that determines the inelastic strain to be input to the analysis model when the comparison result of the comparison unit does not satisfy a convergence condition and repeats the processing of the calculation unit, while the comparison result of the comparison unit satisfies a convergence condition; ,
A strain estimation device for a turbine component, comprising:   A turbine component evaluation method, wherein the turbine component is evaluated using inelastic strain estimated by the turbine component strain estimation method according to any one of claims 1 to 7.

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