1. A prediction method for microstructure change of a near-alpha type titanium alloy aviation die forging is characterized by comprising the following steps of: the method comprises the following specific steps:

s1, measuring the microstructure of the section center of the material under different process conditions, and analyzing the primary alpha phase in the microstructure of the section center;

s2, analyzing the microstructure of the core part of the test piece and the content change of the primary alpha phase under different treatment processes in the step S1 through statistics;

s3, establishing a prediction model of the primary alpha phase change, which comprises the following steps:

s31, establishing a prediction model of the content of the primary alpha phase after heat treatment:

based on the statistical results of the primary alpha phases after different heat treatment in step S2, the residual content omega of the static phase change primary alpha phase obtained after heat treatment is determined by using the classic JMA theory, wherein the JMA theory is shown as formula (1)_ΗΤ-α(T) the relationship between the holding temperature T and the heating time T, as shown in formula (2);

ω_α(t)＝1-exp[-(kt)ⁿ] (1)

wherein K is a rate coefficient related to the test temperature, T is the effective time of the test, n is a model coefficient, T is the test temperature, and the unit K;

s32, establishing a prediction model of the primary alpha phase consumed by dynamic phase change in the deformation process:

determining the amount of the primary alpha phase consumed by the dynamic phase transition based on the statistical result of the step S2 on the primary alpha phase consumed by the dynamic phase transition obtained after the high-temperature compression testAnd strain rateThe relationship between them is shown in formula (3);

in the formula (I), the compound is shown in the specification,is the strain rate, in units of s^-1；

S33, establishing a prediction model of the residual primary alpha phase content after high-temperature deformation:

based on the residual content omega of the static phase change primary alpha phase obtained after the heat treatment in the step S3_ΗΤ-α(t) obtaining the amount of nascent alpha phase consumed by dynamic phase transition after high temperature compression testObtaining the initial alpha phase residue omega after mixed phase change_αAs shown in formula (4);

ω_α＝100ω_HT-α+ω_DT-α (4)

wherein, ω is_HT-αNamely the residual content omega of the static phase change nascent alpha phase obtained after heat treatment_ΗΤ-α(t)，ω_DT-αObtaining the amount of primary alpha phase consumed by dynamic phase change after high-temperature compression testA negative value of (d);

s4, die forging test: performing a die forging test to obtain relevant data after die forging;

and S5, based on the prediction model of the primary alpha phase change, carrying out numerical simulation analysis on a finite element and comparing the result with the die forging test result of the step S4 to realize visual prediction of the microstructure change of the near alpha titanium alloy die forging.

2. The method for predicting the microstructure change of the near-alpha type titanium alloy aviation die forging according to claim 1, wherein the method comprises the following steps: step S1 specifically includes the following substeps:

s11, heat treatment test: obtaining a plurality of samples from the near alpha type titanium alloy forged rod by adopting linear cutting, carrying out a heat treatment test on the samples in a box type furnace, selecting more than 3 discrete temperature points from the range of 900-1000 ℃, and keeping the temperature for 0-180 min;

s12, high-temperature compression test: obtaining from near alpha type titanium alloy forged rod by adopting linear cuttingTaking a plurality of samples, carrying out high-temperature compression test on the samples on a thermal simulation testing machine, selecting more than 3 discrete temperature points from the range of 900-1000 ℃, keeping the temperature for 10min, and setting the deformation rate to 0.001s^-1-10s^-1The deformation is 0-70%;

s13, determining the microstructure characteristics under different process conditions: and separating the samples under different process conditions along the radial direction to form a semi-cylindrical shape, analyzing the microstructure of the section center, and analyzing the nascent alpha phase in the microstructure of the section center.

3. The method for predicting the microstructure change of the near-alpha type titanium alloy aviation die forging according to claim 2, wherein the method comprises the following steps: step S11 was conducted for heat treatment tests under different processes, step S12 was conducted for thermal compression tests under different deformation processes, and step S13 was conducted for microstructural processing of the samples in step S11 and step S12.

4. The method for predicting the microstructure change of the near-alpha type titanium alloy aviation die forging according to claim 2, wherein the method comprises the following steps: the step S32 includes the following steps:

s321, obtaining the content of the primary alpha phase at the same deformation time and deformation temperature based on the content of the residual primary alpha phase obtained in the step S3 due to the static phase change and the content of the residual primary alpha phase obtained in the step S1 and the step S2 due to the dynamic phase change in the microstructure after the high-temperature compression;

s322, analyzing the content of the primary alpha phase and the strain rateThe relationship between the alpha phase and the alpha phase, and the content of the primary alpha phase consumed by dynamic phase change after the high-temperature compression testModel, obtainingAnd strain rateThe inter-relationship model is shown in formula (3).

5. The method for predicting the microstructure change of the near-alpha type titanium alloy aviation die forging according to claim 1, wherein the method comprises the following steps: in step S4, the specification of the blank for the die forging test is 45X 90mm, the forging temperature is 930-.

Background

The titanium alloy is an extremely important light structural material, has the outstanding characteristics of high specific strength, good corrosion resistance, good high and low temperature performance and the like, and has very important application value and wide application prospect in the fields of aviation, aerospace, navigation, medical treatment and the like. With the rapid development of the aviation industry, the requirements on the comprehensive performance of the aircraft are higher and higher, and the requirements on the components of the aircraft are also increased. In order to meet the requirements of light weight and light weight of the airplane, structural parts of the airplane, particularly force-bearing structural parts, are generally formed by titanium alloy through high-temperature forging. The titanium alloy die forging piece has good mechanical properties in the use occasions, so that strict requirements are provided for the microstructure of the titanium alloy die forging piece. For example, the aviation die forging made of the near alpha type TA15 titanium alloy is required to have a primary alpha phase volume fraction of nearly 20% when in use.

In recent years, researchers in the relevant field have found that titanium alloys undergo a particular phenomenon, namely dynamic phase transformation, when subjected to hot deformation in the two-phase region. The dynamic transformation refers to the transformation of the primary alpha phase into the beta phase when the titanium alloy is subjected to thermal deformation in a two-phase region, which is an unbalanced state at a deflection temperature. When the titanium alloy die forging is subjected to hot die forging, dynamic phase change occurs, so that the content of primary alpha phase in the titanium alloy die forging is low, and even completely disappears in severe cases, and immeasurable loss is caused in the production and use of the die forging.

The forming process of the titanium alloy die forging piece determines the microstructure of the titanium alloy die forging piece, and the microstructure plays a decisive role in the mechanical property of the titanium alloy die forging piece. The forging temperature, the deformation amount and the deformation speed are the three most important factors influencing the microstructure of the titanium alloy die forging, and the influence of the heat preservation time before the forging of the titanium alloy die forging on the microstructure after the forging is often ignored. In particular to a (super) large aviation die forging, a certain time gradient exists when the surface to the core of an original blank reaches a specified forging temperature, so that the microstructure of each part of the titanium alloy die forging is uncertain after the titanium alloy die forging is formed.

Therefore, a prediction method for evaluating the microstructure change of the near-alpha type titanium alloy aviation forging is urgently needed to be invented, so that the evolution law of the microstructure of the titanium alloy die forging is obtained, and further guidance is provided for actual production.

Disclosure of Invention

In order to overcome the defects of the prior art, the invention aims to provide a prediction method for microstructure change of a near-alpha type titanium alloy aviation die forging, the method can effectively predict the content of primary alpha phase at different positions of the titanium alloy die forging and reduce the content of the primary alpha phase in the hot die forging process, solves a series of problems caused by dynamic phase change, and further can provide an optimization thought for the deformation process of the titanium alloy die forging, increase the yield of the forging, reduce the production cost and improve the production efficiency.

Specifically, the invention provides a method for predicting microstructure change of a near-alpha type titanium alloy aviation die forging, which is characterized by comprising the following steps of: the method comprises the following specific steps:

s1, measuring the microstructure of the section center of the material under different process conditions, and analyzing the primary alpha phase in the microstructure of the section center;

s2, analyzing the microstructure of the core part of the test piece and the content change of the primary alpha phase under different treatment processes in the step S1 through statistics;

s3, establishing a prediction model of the primary alpha phase change, which comprises the following steps:

s31, establishing a prediction model of the content of the primary alpha phase after heat treatment:

based on the statistical results of the different heat treatment post-process nascent alpha phases in step S2, the residual content omega of the post-heat treatment nascent alpha phase is determined by using the classic JMA theory, which is shown as expression (1)_ΗΤ-α(T) a relationship with the holding temperature T and the heating time T, as shown in the expression (2);

ω_α(t)＝1-exp[-(kt)ⁿ] (1)

wherein K is a rate coefficient related to the test temperature, T is the effective time of the test, n is a model coefficient, T is the test temperature, and the unit K;

s32, establishing a prediction model of the primary alpha phase consumed by dynamic phase change in the deformation process:

based on the statistical result in step S2 regarding the primary alpha phase consumed by the dynamic phase transition obtained after the high-temperature compression test, it was determinedAnd strain rateThe relationship therebetween, as shown in expression (3);

in the formula (I), the compound is shown in the specification,is the strain rate, in units of s^-1；

S33, establishing a prediction model of the residual primary alpha phase content after high-temperature deformation:

based on the residual content omega of the static phase change primary alpha phase obtained after the heat treatment in the step S3_ΗΤ-α(t) obtaining the amount of nascent alpha phase consumed by dynamic phase transition after high temperature compression testObtaining the initial alpha phase residue omega after mixed phase change_αAs shown in formula (4);

ω_α＝100ω_HT-α+ω_DT-α (4)

wherein, ω is_HT-αNamely the residual content omega of the static phase change nascent alpha phase obtained after heat treatment_ΗΤ-α(t)，ω_DT-αObtaining the amount of primary alpha phase consumed by dynamic phase change after high-temperature compression testA negative value of (d);

s4, die forging test: performing a die forging test to obtain relevant data after die forging;

and S5, based on the prediction model of the primary alpha phase change, carrying out numerical simulation analysis on a finite element and comparing the result with the die forging test result of the step S4 to realize visual prediction of the microstructure change of the near alpha titanium alloy die forging.

Preferably, step S1 specifically includes the following sub-steps:

s11, heat treatment test: obtaining a plurality of samples from the near alpha type titanium alloy forged rod by adopting linear cutting, carrying out a heat treatment test on the samples in a box type furnace, selecting more than 3 discrete temperature points from the range of 900-1000 ℃, and keeping the temperature for 0-180 min;

s12, high-temperature compression test: obtaining a plurality of samples from a near alpha-type titanium alloy forged rod by adopting linear cutting, carrying out high-temperature compression test on the samples on a thermal simulation testing machine, selecting more than 3 discrete temperature points from the range of 900-1000 ℃, keeping the temperature for 10min, and setting the deformation rate to 0.001s^-1-10s^-1The deformation is 0-70%;

s13, determining the microstructure characteristics under different process conditions: and separating the samples under different process conditions along the radial direction to form a semi-cylindrical shape, analyzing the microstructure of the section center, and analyzing the nascent alpha phase in the microstructure of the section center.

Preferably, the step S11 performs heat treatment tests under different processes, the step S12 performs heat compression tests under different deformation processes, and the step S13 subjects the sample in the step S11 and the step S12 to microstructural treatment.

Preferably, the step S32 includes the following steps:

s321, obtaining the content of the primary alpha phase at the same deformation time and deformation temperature based on the content of the residual primary alpha phase obtained in the step S3 due to the static phase change and the content of the residual primary alpha phase obtained in the step S1 and the step S2 due to the dynamic phase change in the microstructure after the high-temperature compression;

s322, analyzing the content of the primary alpha phase and the strain rateThe relationship between the two phases, the dynamic phase of the high-temperature compression testVarying the content of the consumed nascent alpha phaseModel, obtainingAnd strain rateThe inter-relationship model is shown in formula (3).

Preferably, the specification of the blank for the die forging test in the step S4 is 45X 90mm, the forging temperature is 930-

Compared with the prior art, the invention has the following beneficial effects:

the invention provides a prediction method for microstructure change of a near-alpha type titanium alloy aviation die forging, which can effectively predict the primary alpha phase content of different positions of the titanium alloy die forging and reduce the primary alpha phase content in a hot die forging process, solves a series of problems caused by dynamic phase change, further provides an optimization thought for the deformation process of the titanium alloy die forging, increases the forging yield, reduces the production cost, improves the production efficiency and reduces the waste of manpower and material resources.

Drawings

FIG. 1 is a schematic diagram of the consumption of nascent alpha phase content by dynamic phase transition in accordance with the present invention;

FIG. 2 is a schematic diagram showing the change of the content of nascent alpha phase after heat preservation at 960 ℃ for different time in the embodiment of the present invention;

FIGS. 3a to 3d are schematic structural diagrams of microstructures at different strain rates of 960 ℃ according to an embodiment of the present invention;

FIG. 4 is a schematic illustration of a forged part after forging of an embodiment of the present invention;

FIG. 5 is a diagram showing the distribution of the primary alpha phase content and a point diagram after the simulation of the embodiment of the present invention;

FIG. 6 is a comparison diagram of actual forging test values of primary alpha phase content and finite element simulation values according to an embodiment of the present invention.

Detailed Description

Exemplary embodiments, features and aspects of the present invention will be described in detail below with reference to the accompanying drawings. In the drawings, like reference numbers can indicate functionally identical or similar elements. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.

The invention provides a method for predicting microstructure change of a near-alpha type titanium alloy aviation die forging, which comprises the following specific steps of:

s1, microscopic structure determination of the material under different process conditions, which comprises the following substeps:

s11, heat treatment test: obtaining a plurality of samples from the near alpha type titanium alloy forged rod by adopting linear cutting, carrying out a heat treatment test on the samples in a box type furnace, selecting more than 3 discrete temperature points from the range of 900-1000 ℃, and keeping the temperature for 0-180 min;

s12, high-temperature compression test: obtaining a plurality of samples from a near alpha-type titanium alloy forged rod by adopting linear cutting, carrying out high-temperature compression test on the samples on a thermal simulation testing machine, selecting more than 3 discrete temperature points from the range of 900-1000 ℃, keeping the temperature for 10min, and setting the deformation rate to 0.001s^-1-10s^-1The deformation is 0-70%;

s13, determining the microstructure characteristics under different process conditions: separating the samples under different process conditions along the radial direction to form a semi-cylindrical shape, and carrying out microstructure analysis on the section center;

s2, analyzing the microstructure of the core part of the test piece and the content change of the primary alpha phase under different treatment processes in the step S1 through statistics;

s3, establishing a prediction model of the primary alpha phase change, which comprises the following steps:

s31, establishing a prediction model of the content of the primary alpha phase after heat treatment:

based on the statistical results of the primary alpha phase after different heat treatment processes in the step S2, the residual content omega of the primary alpha phase after heat treatment is determined by using the classic JMA theory, wherein the JMA theory is shown as an expression (1)_ΗΤ-α(T) the relationship between the holding temperature T and the heating time T,as shown in expression (2);

ω_α(t)＝1-exp[-(kt)ⁿ] (1)

s32, establishing a prediction model of the primary alpha phase consumed by dynamic phase change in the deformation process:

based on the statistical result in step S2 regarding the primary alpha phase consumed by the dynamic phase transition obtained after the high-temperature compression test, it was determinedAnd strain rateThe relationship therebetween, as shown in expression (3);

s33, establishing a prediction model of the residual primary alpha phase content after high-temperature deformation:

based on the residual content of the primary alpha phase (recorded as static phase transition) omega after the heat treatment in the step S3_ΗΤ-α(t) obtaining the amount of nascent alpha phase consumed by dynamic phase transition after high temperature compression testObtaining the initial alpha phase residue omega after mixed phase change_αAs shown in expression (4);

ω_α＝100ω_HT-α+ω_DT-α (4)

wherein, ω is_HT-αNamely the residual content omega of the static phase change nascent alpha phase obtained after heat treatment_ΗΤ-α(t)，ω_DT-αObtaining the amount of primary alpha phase consumed by dynamic phase change after high-temperature compression testNegative values of (c).

The content of the primary alpha phase remaining due to the occurrence of the static phase transition obtained based on the formula (2) in the step S3 and the content of the primary alpha phase remaining due to the occurrence of the dynamic phase transition in the microstructure after the high-temperature compression in the steps S1 and S2 can be obtained at the same time as the primary alpha phase content at the same deformation time and deformation temperature, as shown in FIG. 1, and these values and the strain rate are analyzed at the same timeThe relationship between the alpha phase and the alpha phase, and the content of the primary alpha phase consumed by dynamic phase change after the high-temperature compression testThe model provides basis for subsequent simulation,and strain rateThe inter-relationship model is shown in expression (3).

S4, die forging test: performing a die forging test to obtain relevant data after die forging;

and S5, based on the prediction model of the primary alpha phase change, carrying out numerical simulation analysis on a finite element and comparing the result with the die forging test result of the step S4 to realize visual prediction of the microstructure change of the near alpha titanium alloy die forging.

DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION

Specifically, the invention provides a prediction method for evaluating the microstructure change of a near-alpha type titanium alloy die forging, which comprises the following steps:

s1, determination of microstructure of the material under different process conditions:

(ii) Heat treatment test

Several titanium alloy cylindrical samples with a specification of phi 10 x 15mm were subjected to heat treatment tests.

And (3) a heat treatment system: and (3) heating the box furnace to a specified temperature, then putting the sample into the box furnace until the temperature is stable, and starting timing. The heat treatment temperature is 900 deg.C, 940 deg.C, 960 deg.C, 980 deg.C, and the heat treatment time is 0min, 5min, 10min, 30min, 60min, 120min, and 180 min. And air cooling after the heat treatment is finished.

And cutting the sample after air cooling along the radial direction for subsequently observing the heart microstructure and measuring the quantized value. FIG. 2 shows the change in the primary alpha phase content after different periods of incubation at 960 ℃.

The method aims to obtain the content change of the primary alpha phase under different heat treatment processes and provide data for establishing a quantitative prediction model of the content of the primary alpha phase after heat treatment.

② high temperature compression test

The high-temperature compression test is carried out on a thermal simulation testing machine, the deformation temperature is consistent with the heat treatment temperature, the deformation is 60 percent, and the deformation rate is 0.001s^-1-1s^-1. And after the shift is finished, air cooling to room temperature.

The method aims to obtain the content change of the primary alpha phase under different deformation processes and provide data support for establishing a quantitative prediction model of the primary alpha phase consumed by dynamic phase change in the deformation process.

The method specifically comprises the following steps:

cutting a plurality of samples with the specification of phi 10 multiplied by 15mm from the near alpha type titanium alloy forged rod, and welding a platinum/rhodium galvanic couple wire at the middle position of a spot welding machine along the height direction of the samples for feeding back signals and acquiring a rheological curve with a computer. The end part of the sample is uniformly covered with a high-temperature lubricant before high-temperature compression, and then tantalum sheets with the thickness of 1mm and graphite sheets with the thickness of 0.1mm are adhered to the two ends of the sample to reduce the friction force between the hard alloy pressure head and the sample, so that the uniformity and the stability of the sample in the high-temperature deformation process are ensured. After the sample was placed in the working chamber of a thermal simulation tester, the chamber was evacuated to about 0.01torr and then filled with argon.

And (3) rapidly heating the sample to a specified deformation temperature, then preserving the temperature for 10min, and then deforming at different strain rates according to preset strain. And air cooling to room temperature after the deformation is completed. The heating rate is 10 ℃/s, the deformation temperature is 900 ℃, 940 ℃, 960 ℃, 980 ℃, and the strain rate is 0.001s^-1、0.01s^-1、0.1s^-1And 1s^-1And the deformation is 0-70%.

And cutting the sample after air cooling along the radial direction for subsequently observing the heart microstructure and measuring the quantized value. FIG. 3 shows the microstructure at different strain rates at 960 ℃.

Third, determining the microstructure characteristics of the sample under different processes

And (4) carrying out microstructure analysis on the samples after the heat treatment test and the high-temperature compression test.

The method comprises the following specific implementation steps:

half of the cut samples are used for storing original data, and the other half of the samples are ground by 150-. And etching for about 9s by using a mixed solution of hydrofluoric acid, nitric acid and water after polishing. The microstructure of the sample is obtained by adopting a metallographic microscope.

S2, analyzing the microstructure of the core of the sample after different treatment processes, especially the content of the primary alpha phase by statistics.

The content of the primary alpha phase after heat preservation at 960 ℃ for different time is counted in table 1, and the content of the primary alpha phase consumed by dynamic phase transition at 960 ℃ for different strain rates is counted in table 2.

TABLE 1960 ℃ Heat preservation time after primary alpha phase content

TABLE 2960 deg.C dynamic phase transition consumption nascent alpha phase content at different strain rates

S3, establishing a quantitative prediction model of the nascent alpha phase

Based on the statistical results of the different heat treatment post-process nascent alpha phases in step S2, the remaining content of the thermally treated nascent alpha phases (denoted as static phase transition) ω is determined using the classical JMA theory, i.e. expression (1)_ΗΤ-α(T) temperature T and heating time TThe relationship between them, such as expression (2);

ω_α(t)＝1-exp[-(kt)ⁿ] (1)

based on the statistical result in step S2 regarding the primary alpha phase consumed by the dynamic phase transition obtained after the high-temperature compression test, it was determinedAnd strain rateThe relationship between them, as in expression (3);

based on the residual content of the primary alpha phase (recorded as static phase transition) omega after the heat treatment in the step S3_ΗΤ-α(t) obtaining the amount of nascent alpha phase consumed by dynamic phase transition after high temperature compression testObtaining the initial alpha phase residue omega after mixed phase change_αThe model takes into account the deformation temperature, strain rate and deformation time, as in expression (4);

ω_α＝100ω_HT-α+ω_DT-α (4)

s4, die forging test

The method comprises the following specific implementation steps:

the specification of a die forging test blank is 45 multiplied by 90mm, the forging temperature is 960 ℃, the pressing speed of a press is about 1.6mm/s, and the underpressure is 3mm when the forging is finished.

The blank is kept warm for more than 30min in a box type furnace before die forging, high-temperature glass protective agent is evenly coated on the surface layer of the blank before charging and heat insulation cotton is wrapped, so that the rapid temperature drop during die forging is prevented. During forging, the die is preheated to about 300 ℃, a graphite sheet with the thickness of 3mm is padded in advance in the lower die cavity before the blank is filled into the die, and the graphite sheet is padded on the upper surface of the blank after the blank is filled. FIG. 4 is the forging after forging is complete.

S5 visual prediction of microstructure change of near-alpha type titanium alloy aviation die forging

And (4) based on the prediction model of the primary alpha phase change in the step S3, realizing the visual prediction of the microstructure change of the near alpha titanium alloy die forging through finite element numerical simulation analysis. The model can predict the microstructure of the near-alpha type titanium alloy aviation die forging, gives out related coefficients and errors, and can verify the accuracy of the model. The model output results were compared with the actual forging results, see fig. 5, table 3, and table 4. The error analysis result shows that the average relative error absolute value of the content of the primary alpha phase obtained by the model and the content of the primary alpha phase after actual forging is 2.46 percent, as shown in figure 6. The model can predict the microstructure change of the near alpha type titanium alloy aviation die forging, and the accuracy of the model is verified.

TABLE 3 comparison of the as-formed alpha phase content of actual forgings and simulated predictions

TABLE 3 comparison of the as-formed alpha phase content of actual forgings and simulated predictions

The method comprises the following specific implementation steps:

and establishing a three-dimensional model. And drawing the upper die, the lower die and the blank by adopting CATIA, storing the upper die, the lower die and the blank as stl files which can be identified by DEFORM-3D software, then carrying out related setting in finite element software, and finally generating a DB file for simulation.

And determining material parameters and a forming process. Selecting proper constitutive equation from finite element software material library, setting the density of the near alpha type titanium alloy to be 4.5 multiplied by 10³kg/m³The heat conduction coefficient is 11N/sec/mm/DEG C, and the heat diffusion coefficientTake 0.02W/(m.cndot.). The upper and lower molds are rigid bodies capable of heat transfer, the material is selected from H-13, the preheating temperature is 300 ℃ and 350 ℃, the friction coefficient is 0.3,

and (4) visualizing the microscopic structure. Embedding the prediction models (namely expression (2), expression (3) and expression (4)) into a finite element USER-defined module by adopting an FORTRAN language, establishing a USER module, further realizing the visual prediction of the microstructure of the near-alpha type titanium alloy aviation die forging, and then comparing the result with the actual forging test result for verification, as shown in figure 5.

Compared with the prior art, the invention has the following beneficial effects:

a prediction method for microstructure change of a near-alpha type titanium alloy aviation die forging is established, so that the distribution rule of a nascent alpha phase of a near-alpha type titanium alloy blank after high-temperature die forging and the content of the nascent alpha phase consumed by dynamic phase change can be effectively predicted. The prediction method has very important reference value for the titanium alloy hot forming, and according to the prediction method, an optimization thought can be provided for the deformation process of the titanium alloy die forging, the production cost is reduced, the production efficiency is improved, and the forging yield is increased.

Finally, it should be noted that: the above-mentioned embodiments are only used for illustrating the technical solution of the present invention, and not for limiting the same; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.