CN114091315B - High-temperature alloy stress and damage evolution method and device, storage medium and electronic equipment - Google Patents
High-temperature alloy stress and damage evolution method and device, storage medium and electronic equipment Download PDFInfo
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Abstract
The invention discloses a method and a device for evolving stress and damage of a high-temperature alloy, a storage medium and electronic equipment, and belongs to the technical field of metallurgy. The method comprises the following steps: acquiring creep curves of test pieces with different pretreatment degrees; obtaining finite element models of the matrix-oxidation heat influence layer of the test piece with different pretreatment degrees; obtaining an oxidation-creep damage constitutive model of the test piece according to a creep deformation coordination theory; implanting a subprogram which is programmed with the oxidation-creep damage constitutive model into finite element software; calculating in finite element software by combining a creep curve and a finite element model to obtain parameters of the oxidation-creep damage constitutive model; and obtaining a stress and damage evolution analysis conclusion of the corresponding test piece according to the parameters of the oxidation-creep damage constitutive model. The apparatus, the storage medium, and the electronic device can implement the method. The effect of oxidation on the creep property of the high-temperature alloy can be determined, and the failure mechanism difference of the oxidation heat influence layer and the matrix layer is revealed.
Description
Technical Field
The invention relates to the technical field of metallurgy, in particular to a method and a device for evolving stress and damage of a high-temperature alloy, a storage medium and electronic equipment.
Background
The nickel-based single crystal superalloy has excellent creep deformation, fatigue and oxidation resistance at high temperature, and is widely applied to hot-end structural components. However, in the prior art, the research on the stress and damage evolution process of the high-temperature alloy considering the oxidation is less, so that the service life of the nickel-based single-crystal high-temperature alloy is difficult to predict.
Disclosure of Invention
In view of the above, the present invention provides a method, an apparatus, a storage medium, and an electronic device for stress and damage evolution of a superalloy, which are capable of determining an effect of oxidation on creep performance of the superalloy, and revealing a difference in failure mechanism between an oxidation heat-affected layer and a substrate layer, thereby being more practical.
In order to achieve the first object, the technical scheme of the method for evolving the stress and damage of the high-temperature alloy provided by the invention is as follows:
the high-temperature alloy stress and damage evolution method provided by the invention is realized based on test pieces with different pretreatment degrees, and comprises the following steps:
acquiring creep curves of the test pieces with different pretreatment degrees;
obtaining finite element models of the matrix-oxidation heat influence layer of the test piece with different pretreatment degrees;
obtaining an oxidation-creep damage constitutive model of the test piece according to a creep deformation coordination theory;
implanting a subprogram which is coded with the oxidation-creep damage constitutive model into finite element software;
obtaining an oxidation-creep damage constitutive model of the test piece according to a creep deformation coordination theory;
implanting a subprogram which is coded with the oxidation-creep damage constitutive model into finite element software;
calculating in the finite element software by combining the creep curve and the finite element model to obtain parameters of the oxidation-creep damage constitutive model;
and obtaining a stress and damage evolution analysis conclusion of the corresponding test piece according to the parameters of the oxidation-creep damage constitutive model.
The method for evolving the stress and the damage of the high-temperature alloy can be further realized by adopting the following technical measures.
Preferably, the step of obtaining the finite element models of the matrix-oxidation heat affected layer of the test pieces with different pretreatment degrees specifically comprises the following steps:
obtaining a layered geometric model of the matrix-oxidation heat affected layer according to the oxidation test results of the test pieces with different pretreatment degrees;
and according to the characteristics of each layer of the layered geometric model, carrying out grid division on the matrix-oxidation heat affected layer to obtain the finite element models of the matrix-oxidation heat affected layer of the test piece with different pretreatment degrees.
Preferably, the subroutine into which the constitutive model of oxidation-creep damage is programmed is implanted into a finite element software, which is ABAQUS.
Preferably, the step of obtaining the stress and damage evolution analysis conclusion of the corresponding test piece according to the parameters of the oxidation-creep damage constitutive model specifically comprises the following steps,
obtaining the optimal parameters of the oxidation-creep damage constitutive model according to the parameters of the oxidation-creep damage constitutive model;
and under the optimal parameters, obtaining the stress and damage evolution analysis conclusion of the corresponding test piece under the condition corresponding to the optimal parameters.
Preferably, the step of obtaining the optimal parameters of the oxidation-creep damage constitutive model according to the parameters of the oxidation-creep damage constitutive model specifically includes the following steps:
the creep curves of the test pieces with different pretreatment degrees are given to different mechanical parameters of the matrix-oxidation heat influence layer of the corresponding finite element models of the test pieces with different pretreatment degrees for calculation to obtain a calculation result;
and comparing according to the calculation result to obtain the optimal parameters of the oxidation-creep damage constitutive model.
Preferably, the step of obtaining a stress and damage evolution analysis conclusion of the corresponding test piece according to the parameters of the oxidation-creep damage constitutive model specifically comprises the following steps:
and under the condition of the optimal parameters of the oxidation-creep damage constitutive model, presetting different processing conditions aiming at the oxidation-creep damage constitutive model, and analyzing to obtain a stress and damage evolution analysis conclusion of the corresponding test piece.
Preferably, in the step process of obtaining the stress and damage evolution analysis conclusion of the corresponding test piece according to the parameters of the oxidation-creep damage constitutive model, the stress and damage evolution analysis conclusion of the corresponding test piece is represented by a stress-time change curve graph of the corresponding test piece and a damage-time change curve graph of the corresponding test piece.
Preferably, in the step of obtaining the oxidation-creep damage constitutive model of the test piece according to the creep co-deformation theory, the oxidation-creep damage constitutive model satisfies formula (1):
（1）
in the formula (1), the reaction mixture is,
-creep shear strain rate of the test piece,
-the initial creep rate of the test piece,
the slip system of the test piece, n-the temperature creep parameter of the test piece, is an index related to the creep shear,
-hole damage in the creep damage mechanism,
material degradation in the creep damage mechanism;
wherein the content of the first and second substances,
in the formulas (2) and (3),
-initial damage rate, m-temperature creep parameter, being an index related to the hole damage rate, C, p-oxidation-creep damage constitutive model parameter;
carrying out resolution finishing according to formulas (1), (2) and (3) to obtain:
under the condition of formula (4), the creep shear strain rate is considered
And the stress of cutting
And (3) performing integral splitting and sorting at time t to obtain:
in the formula (5), the reaction mixture is,
-a creep damage of the steel sheet,
representing the value of no damage to the original material,
representing the damage value when the material is broken;
for macroscopic strain rate
Integrating to obtain macroscopic deformation
：
According to the principle of the covariant theory that the deformation of the inner and outer materials is equal, namely the displacement is equal, the following principles are provided:
in the formula (7), the reaction mixture is,
、
-inner and outer material displacement;
damage to creep
Time integration is performed, and when the damage reaches 1, creep rupture occurs in the test piece, so that there are:
（8）
the number of N-slippage systems in the formula (8),
creep life.
In order to achieve the second objective, the technical solution of the apparatus for evolving stress and damage of superalloy provided by the present invention is as follows:
the invention provides a high-temperature alloy stress damage evolution device which is realized based on test pieces with different pretreatment degrees, and the high-temperature alloy stress and damage evolution device comprises:
the creep curve acquisition module is used for acquiring creep curves of the test pieces with different pretreatment degrees;
the finite element model acquisition module is used for acquiring the finite element models of the matrix-oxidation heat influence layers of the test pieces with different pretreatment degrees;
the oxidation-creep damage constitutive model obtaining module is used for obtaining an oxidation-creep damage constitutive model of the test piece according to a creep deformation coordination theory;
the subprogram implantation module is used for implanting the subprogram which is programmed with the oxidation-creep damage constitutive model into finite element software;
the parameter acquisition module is used for calculating in the finite element software by combining the creep curve and the finite element model to obtain the parameters of the oxidation-creep damage constitutive model;
and the stress and damage evolution analysis conclusion generation module is used for obtaining a corresponding stress and damage evolution analysis conclusion of the test piece according to the parameters of the oxidation-creep damage constitutive model.
In order to achieve the third object, the invention provides a computer-readable storage medium having the following technical solutions:
the computer readable storage medium provided by the invention stores a high-temperature alloy stress and damage evolution program, and when the high-temperature alloy stress and damage evolution program is executed by a processor, the steps of the high-temperature alloy stress and damage evolution method provided by the invention are realized.
In order to achieve the fourth object, the present invention provides an electronic device comprising:
the electronic equipment provided by the invention comprises a memory and a processor, wherein the memory is stored with a high-temperature alloy stress and damage evolution program, and the steps of the high-temperature alloy stress and damage evolution method provided by the invention are realized when the high-temperature alloy stress and damage evolution program is executed by the processor.
On one hand, the preoxidation layering damage model can specifically reveal the failure mechanism difference of an oxidation heat influence layer and a substrate layer, can be popularized to the revealing of a multi-layer material structure creep mechanism and the prediction of service life, and provides reference for a test of a nickel-based single crystal material; on the other hand, the design of the material performance is optimized based on the oxidation behavior, the influence on the mechanical behavior of the material is reduced, and a theoretical basis is provided for researching the actual service performance of the alloy.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a flow chart of steps of a method for evolving stress and damage of a superalloy provided by an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a test piece applied to the superalloy stress and damage evolution method provided by the embodiment of the present invention;
FIG. 3 is a creep curve diagram of test pieces with different pretreatment degrees related to the superalloy stress and damage evolution method provided by the embodiment of the present invention;
FIG. 4(a) is a fracture morphology diagram of a matrix-oxidation heat affected layer of a test piece related to a high temperature alloy stress and damage evolution method provided by an embodiment of the invention;
FIG. 4(b) is a schematic diagram of a finite element model of an oxidation heat-affected layer as a matrix of a test piece according to the method for evolving stress and damage of a superalloy provided in an embodiment of the present invention;
FIG. 5 is a schematic diagram of creep test simulation results under different pre-oxidation conditions related to a high-temperature alloy stress and damage evolution method provided by the implementation of the invention;
fig. 6(a) is a stress distribution diagram of a test piece related to the superalloy stress and damage evolution method provided by the embodiment of the present invention under the condition of optimal parameters;
fig. 6(b) is a schematic diagram of the distribution of the slitting stress of a test piece under the condition of optimal parameters, which is related to the method for evolving the stress and damage of the superalloy provided by the embodiment of the present invention;
fig. 6(c) is a schematic diagram of the distribution of the slitting strain of a test piece under the optimal parameter condition, which is related to the superalloy stress and damage evolution method provided by the embodiment of the present invention;
fig. 6(d) is a schematic diagram of damage distribution of a test piece under an optimal parameter condition, which is related to the superalloy stress and damage evolution method provided by the embodiment of the present invention;
fig. 7(a) is a schematic diagram of creep stress distribution of a two-phase model related to a high-temperature alloy stress and damage evolution method under a pre-oxidation condition of 50h according to an embodiment of the present invention;
fig. 7(b) is a schematic diagram of creep stress distribution of a two-phase model related to the high-temperature alloy stress and damage evolution method under the pre-oxidation condition of 200h according to the embodiment of the invention;
fig. 7(c) is a schematic diagram of creep stress distribution of a two-phase model related to the high-temperature alloy stress and damage evolution method under the pre-oxidation condition of 500h according to the embodiment of the invention;
FIG. 8 is a stress curve diagram of a test piece related to the method for evolving stress and damage of a high-temperature alloy according to an embodiment of the present invention under pre-oxidation conditions of 50h (thickness of the heat-affected layer is 19 μm), 200h (thickness of the heat-affected layer is 42 μm), and 500h (thickness of the heat-affected layer is 70 μm);
FIG. 9 is a graph showing the damage evolution of the substrate and the heat affected layer after pre-oxidation for 500h of a test piece according to the method for evolving stress and damage of a high-temperature alloy provided by the embodiment of the invention;
fig. 10 is a schematic diagram illustrating a signal flow direction relationship between functional modules of a superalloy stress and damage evolution device according to an embodiment of the present invention;
fig. 11 is a schematic structural diagram of a high-temperature alloy stress and damage evolution device in a hardware operating environment according to an embodiment of the present invention.
Detailed Description
In view of the above, the present invention provides a method, an apparatus, a storage medium, and an electronic device for stress and damage evolution of a superalloy, which are capable of determining an effect of oxidation on creep performance of the superalloy, and revealing a difference in failure mechanism between an oxidation heat-affected layer and a substrate layer, thereby being more practical.
To further illustrate the technical means and effects of the present invention adopted to achieve the predetermined objects, the following detailed description, with reference to the accompanying drawings and preferred embodiments, describes specific embodiments, structures, features and effects of a method, an apparatus, a storage medium and an electronic device for stress and damage evolution of a superalloy proposed by the present invention. In the following description, different "one embodiment" or "an embodiment" refers to not necessarily the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
The term "and/or" herein is merely an association describing an associated object, meaning that three relationships may exist, e.g., a and/or B, with the specific understanding that: both a and B may be included, a may be present alone, or B may be present alone, and any of the three cases can be provided.
On one hand, an oxidation layer and a heat affected layer are formed on the surface of the alloy material under the condition of high temperature for a long time due to oxidation, and on the other hand, the alloy material has a non-negligible influence on the evolution of the microstructure of a matrix, so that the mechanical property of the alloy material is seriously degraded. The heat affected layer and the base body of the material have different mechanical properties, the damage evolution of the heat affected layer is different from that of the base body under the creep condition, and the layer is easy to generate micro cracks and micro defects, so that the creep fracture of the sample is accelerated. Based on the existing literature, most researches only stay in the specific mechanism description of oxidation and creep, and the modeling research of the system is lacked. Therefore, how to evaluate the influence of different pre-oxidation degrees on the material performance, how to quantitatively characterize the creep behavior of the material, and based on the evaluation, a creep damage prediction model considering the oxidation effect is also an urgent problem to be solved.
In order to solve the above problems, embodiments of the present disclosure provide a pre-oxidation layered damage model for a high-temperature alloy, which can obtain a high-temperature creep stress and damage evolution result of a multilayer structure.
For example, the test piece may be an i-shaped test piece made of a second generation nickel-based single crystal alloy, and will not be described in detail herein.
Embodiments of a method for stress and damage evolution in high temperature alloys
Referring to fig. 1 to 9, a method for evolving stress and damage of a superalloy provided by an embodiment of the present invention includes the following steps:
s110, carrying out a pretreatment test on a target test piece, and carrying out a creep test on test pieces with different pretreatment degrees to obtain corresponding creep curves;
s120, establishing a two-phase geometric model and a grid model of the matrix-oxidation heat influence layer of the test piece according to the oxidation test result;
s130, providing an oxidation-creep damage constitutive model based on the creep deformation theory, and programming a user subprogram (UMAT) to be implanted into finite element software ABAQUS;
s140, calculating, comparing and fitting in ABAQUS to obtain model parameters on the basis of creep test curve results and finite element calculation results;
and S150, analyzing under the optimal model parameters to obtain stress and damage evolution under corresponding conditions.
Thus, the pre-oxidation delamination damage model of the present application establishes a relationship between the degree of pre-oxidation and creep damage, by which the difference in the failure mechanism of the oxidation heat affected layer and the matrix layer can be specifically revealed. Compared with the existing high-temperature alloy creep damage model, the pre-oxidation layered damage model considers the actual service environment of the material, so that the result obtained by model simulation is closer to the real test data.
The following describes a pre-oxidation delamination damage model of a superalloy provided by an embodiment of the present disclosure in detail:
in step S110, a pretreatment test is performed on the target test piece, and creep tests are performed on test pieces with different pretreatment degrees to obtain corresponding creep curves.
Specifically, the test pieces are grouped to be subjected to high-temperature oxidation tests at the same temperature for different time periods, the influence of heat treatment on creep behavior needs to be separately researched, and the creep test is performed on the test pieces after a surface oxidation layer and a heat-affected layer of the test pieces are removed by grinding after oxidation. At least 3 valid test data were obtained for each condition.
And step S120, establishing a two-phase geometric model and a grid model of the matrix-oxidation heat influence layer of the test piece according to the oxidation test result.
Specifically, according to the actual creep damage condition of the test piece in an oxidative corrosion environment, the size of the bearing section of the test piece is the original area, and the outer layer area generated by oxidation influence is removed.
Therefore, a two-phase geometric model of the matrix-oxidation heat affected layer with different thicknesses is established by combining the oxidation test result and the creep fracture morphology. In addition, on the basis of a geometric model, a heat affected layer and a matrix are subjected to proper grid division through debugging, and a two-phase interface is locally refined, so that the result accuracy is improved.
And step S130, putting forward an oxidation-creep damage constitutive model based on the creep deformation theory, and programming a user subprogram (UMAT) and implanting the model into finite element software ABAQUS.
Specifically, on the basis of continuous damage models proposed by Kachanov and Ravbotnov and damage evolution rate proposed by Yeh, a creep damage model with slitting stress and shear strain rate being dominant at the same time is established:
in the formula (I), the compound is shown in the specification,
as the creep shear strain rate of the test piece,
for the purpose of the initial rate of creep,
the different slip systems of the test piece are shown in the table, n is the temperature creep parameter of the test piece,
and
respectively represent hole damage and material deterioration in the creep damage mechanism, and
in the formula
For initial damage rate, m is the temperature creep parameter, and C and p are model parameters.
The creep damage model is split and sorted to obtain:
integration over time t:
taking into account creep shear strain rate
And the stress of cutting
For the relationship of (a), the above equation is modified to yield:
wherein
Is a damage to the material or the like,
it represents that the original material is not damaged,
representing the damage value at the time of material fracture.
Substituting into a creep damage model with dominant slitting stress and shear strain rate to obtain:
for macroscopic strain rate
Integration is performed:
according to the principle of equal deformation of the inner and outer materials, namely equal displacement, of the covariant theory,
the deformation of the phase-disappearing layer and the matrix is uniform, so that there are:
in addition, the original loading stress of the specimen was
As the creep progresses, the amount of creep,
the phase-lost layer bears a stress of
The base body bears a stress of
Then there is
Damage to creep
Time integration is performed, and when the damage reaches 1, creep rupture occurs in the test piece, so that there are:
n is the number of the slip system,
creep life is considered.
The creep damage constitutive equation based on the covariant theory is programmed into a user sub program (UMAT) through a FORTRAN language and is supplemented into an ABAQUS software package.
And S140, calculating, comparing and fitting in ABAQUS to obtain model parameters on the basis of the creep test curve result and the finite element calculation result.
Specifically, considering that the thermal influence layer material is easy to generate defects under an oxidative corrosion environment, the mechanical property of the thermal influence layer material is obviously degraded, and the thermal influence layer material has different mechanical properties with the matrix of the material, so that different creep mechanical parameters are given to each layer.
In addition, the matrix of the material may also be pre-damaged by heat treatment during creep. Based on the test results of different pretreatment conditions, namely the test results of the creep test of the test sample after the surface oxidation layer and the heat affected layer are removed by grinding after the test sample is oxidized, the initial damage of the substrate in the corresponding heat treatment time can be obtained by combining the creep damage theory.
The geometric models under different oxidation time have heat affected layers with different thicknesses, and oxidation layers with different thicknesses are fitted to obtain corresponding model parameters based on the numerical values of matrixes with different initial damages after heat treatment evolution.
And comparing the obtained model parameter calculation result with the creep test curve result and the finite element calculation result on the basis, and if the result is not met, properly adjusting to the optimal model parameter.
And S150, analyzing under the optimal model parameters to obtain stress and damage evolution under corresponding conditions.
Specifically, the optimal parameters obtained by finite element analysis are substituted into a user subprogram (UMAT), and ABAQUS is used for calculating and analyzing to obtain the corresponding stress and damage evolution of the matrix and the oxidation heat affected layer under different pre-oxidation conditions.
High temperature alloy stress and damage evolution apparatus embodiments
Referring to fig. 10, the apparatus for stress and damage evolution of superalloy provided by the present invention includes:
the creep curve acquisition module is used for acquiring creep curves of the test pieces with different pretreatment degrees;
specifically, the test pieces are grouped to be subjected to high-temperature oxidation tests at the same temperature for different time periods, the influence of heat treatment on creep behavior needs to be separately researched, and the creep test is performed on the test pieces after a surface oxidation layer and a heat-affected layer of the test pieces are removed by grinding after oxidation. At least 3 valid test data were obtained for each condition.
The finite element model acquisition module is used for acquiring the finite element models of the matrix-oxidation heat influence layers of the test pieces with different pretreatment degrees;
specifically, according to the actual creep damage condition of the test piece in an oxidative corrosion environment, the size of the bearing section of the test piece is the original area, and the outer layer area generated by oxidation influence is removed.
Therefore, a two-phase geometric model of the matrix-oxidation heat affected layer with different thicknesses is established by combining the oxidation test result and the creep fracture morphology. In addition, on the basis of a geometric model, a heat affected layer and a matrix are subjected to proper grid division through debugging, and a two-phase interface is locally refined, so that the result accuracy is improved.
The oxidation-creep damage constitutive model obtaining module is used for obtaining an oxidation-creep damage constitutive model of the test piece according to a creep deformation coordination theory;
specifically, on the basis of continuous damage models proposed by Kachanov and Ravbotnov and damage evolution rate proposed by Yeh, a creep damage model with slitting stress and shear strain rate being dominant at the same time is established:
in the formula
For initial damage rate, m is the temperature creep parameter, and C and p are model parameters.
The creep damage model is split and sorted to obtain:
integration over time t:
taking into account creep shear strain rate
And the stress of cutting
For the relationship of (a), the above equation is modified to yield:
wherein
Is a damage to the material or the like,
it represents that the original material is not damaged,
representing the damage value at the time of material fracture.
Substituting into a creep damage model with dominant slitting stress and shear strain rate to obtain:
for macroscopic strain rate
Integration is performed:
according to the principle of equal deformation of the inner and outer materials, namely equal displacement, of the covariant theory,
the deformation of the phase-disappearing layer and the matrix is uniform, so that there are:
in addition, the original loading stress of the specimen was
As the creep progresses, the amount of creep,
the phase-lost layer bears a stress of
The base body bears a stress of
Then there is
wherein S0, S1 and S2 respectively refer to original sections,
effective stress area of the phase-disappearing layer and the base body.
Damage to creep
Time integration is performed, and when the damage reaches 1, creep rupture occurs in the test piece, so that there are:
n is the number of the slip system,
creep life is considered.
The subprogram implantation module is used for implanting the subprogram which is programmed with the oxidation-creep damage constitutive model into finite element software;
specifically, the creep damage constitutive equation based on the covariant theory is programmed into a user sub-program (UMAT) through FORTRAN language and supplemented into an ABAQUS software package.
The parameter acquisition module is used for calculating in the finite element software by combining the creep curve and the finite element model to obtain the parameters of the oxidation-creep damage constitutive model;
specifically, considering that the thermal influence layer material is easy to generate defects under an oxidative corrosion environment, the mechanical property of the thermal influence layer material is obviously degraded, and the thermal influence layer material has different mechanical properties with the matrix of the material, so that different creep mechanical parameters are given to each layer.
In addition, the matrix of the material may also be pre-damaged by heat treatment during creep. Based on the test results of different pretreatment conditions, namely the test results of the creep test of the test sample after the surface oxidation layer and the heat affected layer are removed by grinding after the test sample is oxidized, the initial damage of the substrate in the corresponding heat treatment time can be obtained by combining the creep damage theory.
The geometric models under different oxidation time have heat affected layers with different thicknesses, and oxidation layers with different thicknesses are fitted to obtain corresponding model parameters based on the numerical values of matrixes with different initial damages after heat treatment evolution.
And comparing the obtained model parameter calculation result with the creep test curve result and the finite element calculation result on the basis, and if the result is not met, properly adjusting to the optimal model parameter.
And the stress and damage evolution analysis conclusion generation module is used for obtaining a corresponding stress and damage evolution analysis conclusion of the test piece according to the parameters of the oxidation-creep damage constitutive model.
Specifically, the optimal parameters obtained by finite element analysis are substituted into a user subprogram (UMAT), and ABAQUS calculation and analysis are used for obtaining the corresponding stress and damage evolution analysis conclusion of the matrix and the oxidation heat affected layer under different pre-oxidation conditions.
Electronic device embodiment
Referring to fig. 11, fig. 11 is a schematic structural diagram of a superalloy stress and damage evolution apparatus according to an embodiment of the present invention.
As shown in fig. 11, the superalloy stress and damage evolution apparatus may include: a processor 1001, such as a Central Processing Unit (CPU), a communication bus 1002, a user interface 1003, a network interface 1004, and a memory 1005. Wherein a communication bus 1002 is used to enable connective communication between these components. The user interface 1003 may comprise a Display screen Display, an input unit such as a Keyboard, and the optional user interface 1003 may also comprise a standard wired interface, a wireless interface. The network interface 1004 may optionally include a standard wired interface, a WIreless interface such as a WI-FI interface, for example, a WIreless FIdelity (WI-FI) interface. The Memory 1005 may be a high-speed Random Access Memory, a RAM Memory, or a Non-Volatile Memory, a NVM, such as a disk Memory. The memory 1005 may alternatively be a storage device separate from the processor 1001.
Those skilled in the art will appreciate that the configuration shown in FIG. 11 does not constitute a limitation of the superalloy stress and damage evolution apparatus, and may include more or fewer components than shown, or some components in combination, or a different arrangement of components.
As shown in fig. 11, the memory 1005, which is a storage medium, may include an operating system, a data storage module, a network communication module, a user interface module, and a superalloy stress and damage evolution program.
In the superalloy stress and damage evolution apparatus shown in fig. 11, the network interface 1004 is mainly used for data communication with a network server; the user interface 1003 is mainly used for data interaction with a user; the processor 1001 and the memory 1005 in the superalloy stress and damage evolution device of the present invention may be disposed in the superalloy stress and damage evolution device, and the superalloy stress and damage evolution device invokes the superalloy stress and damage evolution program stored in the memory 1005 through the processor 1001, and executes the method for evolving superalloy stress and damage provided in the embodiments of the present invention.
Examples
The implementation flow of the preoxidation delamination damage model of the superalloy of the embodiment is shown in fig. 1, the test piece may be an i-shaped test piece manufactured by using a second-generation nickel-based single crystal alloy, and the structural size is shown in fig. 2. The specific operation comprises the following steps:
(1) and (3) subjecting multiple groups of I-shaped test pieces to 980 ℃/270MPa creep tests after different oxidation times at 1100 ℃. At least 3 valid test data were obtained for each condition.
(2) A curve with the creep life as a middle value is taken for analysis and fitting, and the creep curve of the test piece is shown in FIG. 3.
(3) According to the test results, a two-phase model of the matrix-oxidation heat affected layer of the test piece is established in ABAQUS software, and appropriate meshing and local refinement are carried out at the same time, as shown in FIG. 4.
(4) The oxidation-creep damage constitutive model was embedded in the finite element software ABAQUS by the user subroutine (UMAT). Subsequently, the substrate is given an initial damage at the corresponding heat treatment time. And based on the numerical values of the matrixes with different initial damages after the heat treatment evolution, giving a larger numerical value to the oxide layer, and fitting the oxide layers with different thicknesses to obtain a proper numerical value. The calculation results are compared with creep test curve results and finite element calculation results (fig. 5), and the parameters are adjusted to the optimal model parameters repeatedly.
(5) The distributions of stress, strain and damage of the base body and the oxidation heat-affected layer obtained by using the optimum parameters are shown in fig. 6(a), 6(b), 6(c) and 6 (d). The heat affected layer thicknesses of the pre-oxidation 50h, 200h and 500h are respectively 19 μm, 42 μm and 70 μm, and the respective stress evolution is shown in FIGS. 7(a), 7(b), 7(c) and 8. Taking the pre-oxidation time of 500h as an example, the damage variation curve is shown in FIG. 9.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. A superalloy stress and damage evolution method is characterized in that the superalloy stress and damage evolution method is realized based on test pieces with different pretreatment degrees, and the superalloy stress and damage evolution method comprises the following steps:
acquiring creep curves of the test pieces with different pretreatment degrees;
obtaining finite element models of the matrix-oxidation heat influence layer of the test piece with different pretreatment degrees;
obtaining an oxidation-creep damage constitutive model of the test piece according to a creep deformation coordination theory;
implanting a subprogram which is coded with the oxidation-creep damage constitutive model into finite element software;
calculating in the finite element software by combining the creep curve and the finite element model to obtain parameters of the oxidation-creep damage constitutive model;
obtaining a stress and damage evolution analysis conclusion of the corresponding test piece according to the parameters of the oxidation-creep damage constitutive model;
wherein, in the step of obtaining the oxidation-creep damage constitutive model of the test piece according to the creep deformation theory, the oxidation-creep damage constitutive model satisfies formula (1):
in the formula (1), the reaction mixture is,
-creep shear strain rate of the test piece,
-the initial creep rate of the test piece,
the slip system of the test piece, n-the temperature creep parameter of the test piece, is an index related to the creep shear strain,
-hole damage in the creep damage mechanism,
material degradation in the creep damage mechanism;
wherein the pores are damaged
And material deterioration
The evolution equation of (c) is as follows:
in the formulas (2) and (3),
-initial damage rate, m-temperature creep parameter, being an index related to the hole damage rate, C, p-oxidation-creep damage constitutive model parameter;
carrying out resolution finishing according to formulas (1), (2) and (3) to obtain:
under the condition of formula (4), the creep shear strain rate is considered
And the stress of cutting
And (3) performing integral splitting and sorting at time t to obtain:
in the formula (5), the reaction mixture is,Ais a material parameter obtained by curve fitting of creep experiment results under different stress conditions,
-a creep damage of the steel sheet,
representing the value of no damage to the original material,
representing the damage value when the material is broken;
for macroscopic strain rate
Integrating to obtain macroscopic deformation
：
According to the principle of the covariant theory that the deformation of the inner and outer materials is equal, namely the displacement is equal, the following principles are provided:
in the formula (7), the reaction mixture is,
、
displacement of the inner and outer materials;
damage to creep
Time integration is performed, and when the damage reaches 1, creep rupture occurs in the test piece, so that there are:
the number of N-slippage systems in the formula (8),
creep life.
2. The superalloy stress and damage evolution method according to claim 1, wherein the obtaining of the finite element model of the matrix-oxidation heat affected layer of the test piece with different pretreatment degrees specifically comprises the steps of:
obtaining a layered geometric model of the matrix-oxidation heat affected layer according to the oxidation test results of the test pieces with different pretreatment degrees;
and according to the characteristics of each layer of the layered geometric model, carrying out meshing division on the matrix-oxidation heat affected layer to obtain a finite element model of the matrix-oxidation heat affected layer of the test piece.
3. The superalloy stress and damage evolution method of claim 1, wherein the step of implanting the subroutine programmed with the constitutive model of oxidation-creep damage into a finite element software, the finite element software being ABAQUS.
4. The superalloy stress and damage evolution method of claim 1, wherein obtaining a stress and damage evolution analysis conclusion of a corresponding test piece according to the parameters of the oxidation-creep damage constitutive model specifically comprises:
obtaining the optimal parameters of the oxidation-creep damage constitutive model according to the parameters of the oxidation-creep damage constitutive model;
and under the optimal parameters, obtaining the stress and damage evolution analysis conclusion of the corresponding test piece under the condition corresponding to the optimal parameters.
5. The superalloy stress and damage evolution method of claim 4, wherein the obtaining of the optimal parameters of the oxidation-creep damage constitutive model according to the parameters of the oxidation-creep damage constitutive model specifically comprises the following steps:
giving different mechanical parameters to the matrix-oxidation heat affected layer of the corresponding finite element model of the test piece with different pretreatment degrees, and calculating in the finite element software compiled with the subprogram of the oxidation-creep damage constitutive model to obtain a calculation result;
and comparing the calculation result with creep curves of test pieces with different pretreatment degrees to obtain the optimal parameters of the oxidation-creep damage constitutive model.
6. The superalloy stress and damage evolution method of claim 5, wherein obtaining a stress and damage evolution analysis conclusion of a corresponding test piece according to the parameters of the oxidation-creep damage constitutive model specifically comprises the following steps:
and under the condition of the optimal parameters of the oxidation-creep damage constitutive model, presetting different processing conditions aiming at the oxidation-creep damage constitutive model, and analyzing to obtain a stress and damage evolution analysis conclusion of the corresponding test piece.
7. The superalloy stress and damage evolution method according to claim 1, wherein during the step of obtaining the stress and damage evolution analysis conclusion of the corresponding test piece according to the parameters of the oxidation-creep damage constitutive model, the stress and damage evolution analysis conclusion of the corresponding test piece is represented by a stress-time change curve of the corresponding test piece and a damage-time change curve of the corresponding test piece.
8. A superalloy stress damage evolution device, characterized in that, superalloy stress and damage evolution device is realized based on test pieces of different pretreatment degree, the superalloy stress and damage evolution device includes:
the creep curve acquisition module is used for acquiring creep curves of the test pieces with different pretreatment degrees;
a finite element model acquisition module for acquiring a finite element model of the matrix-oxidation heat-affected layer of the test piece;
the oxidation-creep damage constitutive model obtaining module is used for obtaining an oxidation-creep damage constitutive model of the test piece according to a creep deformation coordination theory;
the subprogram implantation module is used for implanting the subprogram which is programmed with the oxidation-creep damage constitutive model into finite element software;
the parameter acquisition module is used for calculating in the finite element software by combining the creep curve and the finite element model to obtain the parameters of the oxidation-creep damage constitutive model;
the stress and damage evolution analysis conclusion generation module is used for obtaining a stress and damage evolution analysis conclusion of the corresponding test piece according to the parameters of the oxidation-creep damage constitutive model;
wherein, in the step of obtaining the oxidation-creep damage constitutive model of the test piece according to the creep deformation theory, the oxidation-creep damage constitutive model satisfies formula (1):
in the formula (1), the reaction mixture is,
-creep shear strain rate of the test piece,
-the initial creep rate of the test piece,
slip system of test pieces, n-temperature of test piecesThe creep parameter, which is an index related to creep shear strain,
-hole damage in the creep damage mechanism,
material degradation in the creep damage mechanism;
wherein the pores are damaged
And material deterioration
The evolution equation of (c) is as follows:
in the formulas (2) and (3),
-initial damage rate, m-temperature creep parameter, being an index related to the hole damage rate, C, p-oxidation-creep damage constitutive model parameter;
carrying out resolution finishing according to formulas (1), (2) and (3) to obtain:
under the condition of formula (4), the creep shear strain rate is considered
And the stress of cutting
And (3) performing integral splitting and sorting at time t to obtain:
（5）
in the formula (5), the reaction mixture is,Ais a material parameter obtained by curve fitting of creep experiment results under different stress conditions,
-a creep damage of the steel sheet,
representing the value of no damage to the original material,
representing the damage value when the material is broken;
for macroscopic strain rate
Integrating to obtain macroscopic deformation
：
According to the principle of the covariant theory that the deformation of the inner and outer materials is equal, namely the displacement is equal, the following principles are provided:
in the formula (7), the reaction mixture is,
、
-inner and outer material displacement;
damage to creep
Time integration is performed, and when the damage reaches 1, creep rupture occurs in the test piece, so that there are:
the number of N-slippage systems in the formula (8),
creep life.
9. A computer readable storage medium having stored thereon a superalloy stress and damage evolution program, the program when executed by a processor implementing the method of superalloy stress and damage evolution of any of claims 1-7.
10. An electronic device comprising a memory and a processor, the memory having a superalloy stress and damage evolution program stored thereon, wherein the superalloy stress and damage evolution program when executed by the processor performs the steps of the method of any of claims 1-7.
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