CN112899526A - Alpha + beta type two-phase titanium alloy for fan blade of aero-engine and preparation method thereof - Google Patents
Alpha + beta type two-phase titanium alloy for fan blade of aero-engine and preparation method thereof Download PDFInfo
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- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
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Abstract
The invention relates to an alpha + beta type two-phase titanium alloy for an aircraft engine fan blade and a preparation method thereof, wherein the preparation method of the alpha + beta type two-phase titanium alloy for the aircraft engine fan blade comprises the following steps: s1, obtaining the following chemical components: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements; s2, carrying out first-stage upsetting on the titanium alloy ingot; s3, reversing under the conditions of preset temperature and preset deformation, and then carrying out second-stage upsetting on the titanium alloy ingot; s4, heating the titanium alloy ingot to a temperature above the phase transition point, and then carrying out third-stage upsetting on the titanium alloy ingot; s5, heating the titanium alloy ingot to be below the phase transition point, and then carrying out fourth-stage upsetting on the titanium alloy ingot to obtain a titanium alloy material; and S6, performing heat treatment on the titanium alloy material. The invention is applied to the technical field of titanium alloy.
Description
Technical Field
The invention relates to the technical field of titanium alloy, in particular to an alpha + beta type two-phase titanium alloy for an aircraft engine fan blade and a preparation method thereof.
Background
Titanium alloys have become one of the major structural materials for advanced aircraft and engines due to their excellent combination of high specific strength, modulus, toughness, high damage tolerance, corrosion resistance, and weldability.
Increasing thrust-to-weight ratio and efficiency are continuing goals for aircraft engines, and fan blades are one of the key rotating components of advanced aircraft engines. Since 60 and 70 years of the last century, the aeroengine companies in western countries such as the united kingdom, the united kingdom and the united states began to develop titanium alloy materials and special forming processes to manufacture wide-chord hollow fan blades, and after a great deal of design, processing and experimental research work, the wide-chord hollow fan blades gradually developed and matured and were successively applied to military and civil aeroengines. The titanium alloy wide-chord hollow blade has excellent structural characteristics and weight advantages, and becomes one of the main schemes of the fan blade of the current advanced aviation turbofan engine. With the development of the technology, at present, the titanium alloy wide-chord hollow fan blade scheme is competitive and challenged in the aspects of reducing oil consumption, reducing weight, improving efficiency, reducing noise, resisting bird strike and the like by the aero-engine full-composite fan blade scheme represented by GE and CFMI companies.
Currently, titanium alloy wide chord hollow fan blades are typically made of a moderate strength Ti-6Al-4V alloy. Ti-6Al-4V is a typical alpha + beta type two-phase titanium alloy developed in 1954 in the United states, and is the titanium alloy which is most widely applied in the aerospace industry due to excellent comprehensive properties. The Ti-6Al-4V alloy not only has good obdurability matching, the long-time working temperature can reach 400 ℃, but also has good process plasticity and superplasticity, and is suitable for various processing and forming, thereby being a preferred material for blades at the cold end of an engine. However, the tensile strength of Ti-6Al-4V alloys is generally applied at a level not exceeding 1000MPa, and it has become increasingly difficult to meet the strength requirements for lightweight hollow fan blades.
In the prior art, most high-strength titanium alloys belong to beta titanium alloys, a large amount of needle-like secondary alpha phases are precipitated in the beta phases after solution aging treatment, and high strength performance can be obtained, but the high-strength titanium alloys are generally low in elastic modulus and difficult to meet the requirement on blade rigidity. Moreover, the beta titanium alloy material has high alloying element types and contents, is relatively difficult to smelt, is easy to generate component segregation, and is difficult to meet the requirements of rotating parts on material structure and performance uniformity. In addition, the core process of blade forming is superplastic forming/diffusion bonding, the ideal microstructure state is equiaxial structure, and beta titanium alloy needs to be regulated and controlled to obtain lamellar structure containing a large amount of secondary alpha phase when high strength is obtained, the superplasticity is poor, the types and contents of alloying elements of the beta titanium alloy material are high, the diffusion bonding control difficulty is high, and the forming process requirements of the blade are difficult to meet.
Therefore, the invention provides an alpha + beta type two-phase titanium alloy for an aircraft engine fan blade and a preparation method thereof.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides an alpha + beta type two-phase titanium alloy for an aircraft engine fan blade and a preparation method thereof, wherein the plasticity of the alpha + beta type two-phase titanium alloy is equivalent to that of a Ti-6Al-4V alloy by designing chemical components and regulating and controlling a microstructure, the tensile strength of the alpha + beta type two-phase titanium alloy is greater than 1100MPa, and the structural uniformity is improved by adopting a method combining reversing upsetting and high-low forging, so that the technical problems of poor superplasticity and high diffusion connection control difficulty are solved.
(2) Technical scheme
The embodiment of the invention provides an alpha + beta type two-phase titanium alloy for an aircraft engine fan blade, which comprises the following chemical components in percentage by mass: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements.
The embodiment of the invention also provides a preparation method of the alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine, which comprises the following steps:
s1, obtaining the following chemical components according to the mass ratio: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements;
s2, melting the raw materials of each chemical component through vacuum consumable melting to prepare a titanium alloy ingot, measuring the beta transition temperature of the titanium alloy ingot, heating the titanium alloy ingot to a beta phase region above a phase transition point, and carrying out first-stage upsetting on the titanium alloy ingot to fully crush the as-cast structure of the titanium alloy ingot;
s3, under the conditions of preset temperature and preset deformation, reversing, and then carrying out second-stage upsetting on the titanium alloy ingot to enable the edge and the center of the bar blank of the titanium alloy ingot to deform uniformly;
s4, heating the titanium alloy ingot to a temperature above the phase transformation point, and then carrying out third-stage upsetting on the titanium alloy ingot to generate new beta grains;
s5, heating the titanium alloy ingot to below the phase transition point, and then carrying out fourth-stage upsetting on the titanium alloy ingot to completely crush the fine and uniform blank tissue to obtain a titanium alloy material;
and S6, performing heat treatment on the titanium alloy material.
Preferably, in step S1, the following chemical components are obtained by mass ratio: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.18 to 0.24 percent of oxygen, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements;
in step S2, measuring the beta transition temperature of the titanium alloy ingot to 925-930 ℃; heating the titanium alloy ingot to 1150 ℃, preserving heat for 120min, wherein the heating time is 90min, then carrying out two-time first-stage upsetting and drawing on the titanium alloy ingot, and cooling the titanium alloy ingot by water after forging; heating the titanium alloy ingot to 1050 ℃ again, preserving the heat for 150min, then carrying out two-time first-stage upsetting and drawing, and cooling by water after forging; heating the blank to 980 ℃, preserving heat for 150min, still carrying out two-time first-stage upsetting and drawing, and cooling by water after forging;
step S3, heating the titanium alloy ingot to 20-60 ℃ below the beta transformation point, reversing under the condition of preset deformation, and then carrying out three-fire second-stage upsetting on the titanium alloy ingot to enable the edge and the center of a bar blank of the titanium alloy ingot to deform uniformly;
step S4, heating the titanium alloy ingot to a temperature of 50 ℃ above the transformation point, and carrying out third-stage upsetting on the titanium alloy ingot to generate new beta grains;
in step S5, the titanium alloy ingot is heated to 40-60 ℃ below the beta transformation point, and is upset and drawn in the alpha + beta two-phase area for five times of the fourth stage, so that the fine and uniform blank structure is completely crushed, and the titanium alloy material is obtained.
Preferably, in step S6, the titanium alloy material is heated to 900 ℃ ± 10 ℃, the temperature is maintained for at least 20min, and the titanium alloy material is air-cooled to room temperature; then heating to 640 +/-5 ℃, preserving the temperature for at least 60min, and cooling to room temperature in air.
Preferably, in step S3, the titanium alloy ingot is heated to a temperature within a range of 30 to 50 ℃ below the β -transus, and after reversing the direction under a predetermined deformation amount, the titanium alloy ingot is subjected to five-fire second-stage upsetting to uniformly deform the edge and the center of the billet of the titanium alloy ingot.
Preferably, in S5, the titanium alloy ingot is heated to 50-80 ℃ below the beta transformation point, and the fourth stage of upsetting is carried out for six times in the alpha + beta two-phase region, so that the fine and uniform blank structure is completely crushed, and the titanium alloy material is obtained.
Preferably, the first stage upsetting, the second stage upsetting, the third stage upsetting and the fourth stage upsetting respectively comprise upsetting and elongation.
Preferably, the titanium alloy ingots subjected to the first-stage upsetting and drawing, the second-stage upsetting and drawing, the third-stage upsetting and the fourth-stage upsetting are respectively cylindrical.
Preferably, in step S1, based on the calculation of the CALPHAD method, the contents of Al and V elements are adjusted, the electron work function is increased, and the following chemical components are obtained according to the mass ratio: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements.
(3) Advantageous effects
In conclusion, the alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine and the preparation method thereof realize the plasticity equivalent to that of Ti-6Al-4V alloy and the tensile strength greater than 1100MPa by carrying out chemical component design and microstructure regulation and control, and simultaneously, the superplasticity and diffusion connection performance meet the requirements of the superplastic forming/diffusion connection process of the fan blade of the aero-engine, thereby further improving the voidage of the fan blade of the aero-engine, reducing the weight, increasing the diameter of the fan blade of the aero-engine, improving the pneumatic efficiency and being more beneficial to realizing the aims of weight reduction and efficiency improvement of the fan blade of the aero-engine. In addition, the invention provides the alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine and the preparation method thereof, the phase change point of the alpha + beta type two-phase titanium alloy is obviously reduced compared with Ti-6Al-4V alloy, so that the heating temperature of the superplastic forming/diffusion bonding process in the manufacturing process of the fan blade of the aero-engine is reduced, the manufacturing cost can be further reduced, and the production efficiency is improved. In the forging process of the titanium alloy ingot, a method combining reversing upsetting and high-low forging is adopted to improve the uniformity of the structure. In combination with the three points, the alpha + beta two-phase high-strength titanium alloy for the fan blade of the aero-engine and the preparation method thereof provided by the invention have the advantages that the plasticity, the rigidity and the process performance can meet the manufacturing requirements of the fan blade of the aero-engine, so that the hollow rate of the fan blade of the aero-engine is further improved, the weight is reduced, the diameter of the fan blade is increased, the pneumatic efficiency is improved, and the purposes of weight reduction and efficiency increase of the fan blade of the aero-engine are better achieved. The technical competitive advantage of the titanium alloy wide-chord hollow fan blade can be improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a microstructure diagram of an α + β type two-phase titanium alloy in example 1 of the present invention.
FIG. 2 is a microstructure diagram of an α + β type two-phase titanium alloy in example 2 of the present invention.
FIG. 3 is a microstructure diagram of an α + β type two-phase titanium alloy in example 3 of the present invention.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, alterations, and improvements in the parts, components, and connections without departing from the spirit of the invention.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example 1
An alpha + beta type two-phase titanium alloy for an aircraft engine fan blade comprises the following chemical components in percentage by mass: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements.
A preparation method of an alpha + beta type two-phase titanium alloy for an aircraft engine fan blade comprises the following steps:
s1, obtaining the following chemical components according to the mass ratio: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements;
s2, carrying out three-time vacuum consumable melting on raw materials of all chemical components to prepare a titanium alloy ingot, measuring the beta transition temperature of the titanium alloy ingot, heating the titanium alloy ingot to a beta phase region above a phase transition point, and carrying out first-stage upsetting on the titanium alloy ingot to fully crush the as-cast structure of the titanium alloy ingot and improve the structure uniformity and directionality of the titanium alloy ingot;
s3, under the conditions of preset temperature and preset deformation, reversing, and then carrying out second-stage upsetting on the titanium alloy ingot to enable the edge and the center of the bar blank of the titanium alloy ingot to deform uniformly;
s4, heating the titanium alloy ingot to a temperature above the phase transformation point, and then carrying out third-stage upsetting on the titanium alloy ingot to generate new beta grains;
s5, heating the titanium alloy ingot to below the phase transition point, and then carrying out fourth-stage upsetting on the titanium alloy ingot to completely crush the fine and uniform blank tissue to obtain a titanium alloy material;
s6, performing heat treatment on the titanium alloy material, and further performing synergistic regulation and control on the microstructure and the performance of the titanium alloy material to realize that the plasticity and the rigidity of the titanium alloy material are equivalent to those of Ti-6Al-4V alloy, and the tensile strength of the titanium alloy material is more than 1100 MPa.
The alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine and the preparation method thereof realize the plasticity equivalent to that of Ti-6Al-4V alloy by carrying out chemical component design and microstructure regulation and control, the tensile strength is more than 1100MPa, and meanwhile, the superplasticity and diffusion connection performance meet the requirements of the superplastic forming/diffusion connection process of the fan blade of the aero-engine, so that the hollow rate and the weight of the fan blade of the aero-engine can be further improved, the diameter of the fan blade of the aero-engine is increased, the pneumatic efficiency is improved, and the aims of weight reduction and efficiency improvement of the fan blade of the aero-engine are better fulfilled. In addition, the embodiment provides the alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine and the preparation method thereof, compared with the Ti-6Al-4V alloy, the phase change point of the alpha + beta type two-phase titanium alloy is obviously reduced, so that the heating temperature of the superplastic forming/diffusion bonding process in the manufacturing process of the fan blade of the aero-engine is reduced, the manufacturing cost can be further reduced, and the production efficiency is improved. In the forging process of the titanium alloy ingot, a method combining reversing upsetting and high-low forging is adopted to improve the uniformity of the structure. In combination with the three points, the alpha + beta two-phase high-strength titanium alloy for the fan blade of the aero-engine and the preparation method thereof provided by the invention have the advantages that the plasticity, the rigidity and the process performance can meet the manufacturing requirements of the fan blade of the aero-engine, so that the hollow rate of the fan blade of the aero-engine is further improved, the weight is reduced, the diameter of the fan blade is increased, the pneumatic efficiency is improved, and the purposes of weight reduction and efficiency increase of the fan blade of the aero-engine are better achieved. The technical competitive advantage of the titanium alloy wide-chord hollow fan blade can be improved.
Further, in an embodiment, in step S1, the following chemical components are obtained by mass ratio: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.18 to 0.24 percent of oxygen, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements;
in step S2, measuring the beta transition temperature of the titanium alloy ingot to 925-930 ℃; heating the titanium alloy ingot to 1150 ℃, preserving heat for 120min, wherein the heating time is 90min, then carrying out two-time first-stage upsetting and drawing on the titanium alloy ingot, and cooling the titanium alloy ingot by water after forging; heating the titanium alloy ingot to 1050 ℃ again, preserving the heat for 150min, then carrying out two-time first-stage upsetting and drawing, and cooling by water after forging; heating the blank to 980 ℃, preserving heat for 150min, still carrying out two-time first-stage upsetting and drawing, and cooling by water after forging;
step S3, heating the titanium alloy ingot to 20-60 ℃ below the beta transformation point, reversing under the condition of preset deformation, and then carrying out three-fire second-stage upsetting on the titanium alloy ingot to enable the edge and the center of a bar blank of the titanium alloy ingot to deform uniformly;
step S4, heating the titanium alloy ingot to a temperature of 50 ℃ above the transformation point, and carrying out third-stage upsetting on the titanium alloy ingot to generate new beta grains;
in step S5, the titanium alloy ingot is heated to 40-60 ℃ below the beta transformation point, and is upset and drawn in the alpha + beta two-phase area for five times of the fourth stage, so that the fine and uniform blank structure is completely crushed, and the titanium alloy material is obtained. And during upsetting at the fourth stage, upsetting at the reversing stage is performed again at the fourth stage of the last but one fire, so that fine and uniform blank tissues are completely crushed, the tissues are further refined and homogenized, and the microstructure of the material is regulated and controlled.
Further, in an embodiment, in step S6, the titanium alloy material is heated to 900 ℃ ± 10 ℃, kept warm for at least 20min, and air-cooled to room temperature; then heating to 640 +/-5 ℃, preserving the temperature for at least 60min, and cooling to room temperature in air. Referring to FIG. 1, the performance test results show that the tensile strength, yield strength, elongation, reduction of area and elastic modulus are 1118MPa, 1060MPa, 13.1%, 46.9% and 115GPa, respectively, i.e. the plasticity and rigidity are equivalent to those of Ti-6Al-4V alloy, and the tensile strength is more than 1100 MPa. The research on the adaptability of the blade forming process shows that the superplasticity and diffusion bonding performance of the blade meet the requirements of a superplastic forming/diffusion bonding process.
Further, in one embodiment, the first stage upset, second stage upset, third stage upset, and fourth stage upset comprise upset and elongation, respectively.
Further, in one embodiment, the first stage upset, the second stage upset, the third stage upset, and the fourth stage upset titanium alloy ingots are cylindrical.
Further, in an embodiment, in step S1, based on the calculation of the CALPHAD method, the contents of Al and V elements are adjusted to reduce the stacking fault energy, so as to improve the plasticity and creep resistance of the titanium alloy; the electron work function is improved, so that the strength and the hardness of the titanium alloy are improved. The following chemical components are obtained according to the mass ratio: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements.
Example 2
This example differs from example 1 in that: in step S3, the titanium alloy ingot is heated to a temperature of 30-50 ℃ below the beta transformation point, and is subjected to five-fire second-stage upsetting and drawing after reversing under the condition of preset deformation amount, so that the edge and the center of the bar blank of the titanium alloy ingot are deformed uniformly. The modification of the present embodiment with respect to step S3 is an alternative to step S3 in embodiment 1. Referring to FIG. 2, the test results show that the tensile strength, yield strength, elongation, reduction of area and elastic modulus are 1137MPa, 1063MPa, 12.3%, 46.9% and 116GPa, respectively, the plasticity and rigidity are equivalent to those of Ti-6Al-4V alloy, and the tensile strength is more than 1100 MPa. The adaptability research of the blade forming process shows that the superplasticity and the diffusion bonding performance of the blade also meet the requirements of the superplasticity forming/diffusion bonding process.
Example 3
This example differs from example 1 in that: and S5, heating the titanium alloy ingot to 50-80 ℃ below the beta transformation point, and carrying out six-time fourth-stage upsetting in an alpha + beta two-phase region to completely crush the fine and uniform blank tissue to obtain the titanium alloy material. The modification of the present embodiment with respect to step S5 is an alternative to step S5 in embodiment 1. Referring to FIG. 3, the test results show that the tensile strength, yield strength, elongation, reduction of area and elastic modulus are 1121MPa, 1033MPa, 13.6%, 44.7% and 112GPa, respectively, the plasticity and rigidity are equivalent to those of Ti-6Al-4V alloy, and the tensile strength is more than 1100 MPa. The adaptability research of the blade forming process shows that the superplasticity and the diffusion bonding performance of the blade also meet the requirements of the superplasticity forming/diffusion bonding process.
The above description is only an example of the present application and is not limited to the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
Claims (9)
1. The alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine is characterized by comprising the following chemical components in percentage by mass: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements.
2. A method for preparing an α + β type two-phase titanium alloy for an aircraft engine fan blade according to claim 1, comprising the steps of:
s1, obtaining the following chemical components according to the mass ratio: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements;
s2, melting the raw materials of each chemical component through vacuum consumable melting to prepare a titanium alloy ingot, measuring the beta transition temperature of the titanium alloy ingot, heating the titanium alloy ingot to a beta phase region above a phase transition point, and carrying out first-stage upsetting on the titanium alloy ingot to fully crush the as-cast structure of the titanium alloy ingot;
s3, under the conditions of preset temperature and preset deformation, reversing, and then carrying out second-stage upsetting on the titanium alloy ingot to enable the edge and the center of the bar blank of the titanium alloy ingot to deform uniformly;
s4, heating the titanium alloy ingot to a temperature above the phase transformation point, and then carrying out third-stage upsetting on the titanium alloy ingot to generate new beta grains;
s5, heating the titanium alloy ingot to below the phase transition point, and then carrying out fourth-stage upsetting on the titanium alloy ingot to completely crush the fine and uniform blank tissue to obtain a titanium alloy material;
and S6, performing heat treatment on the titanium alloy material.
3. The method for preparing the alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine as claimed in claim 2, wherein in the step S1, the following chemical components are obtained according to mass ratio: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.18 to 0.24 percent of oxygen, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements;
in step S2, measuring the beta transition temperature of the titanium alloy ingot to 925-930 ℃; heating the titanium alloy ingot to 1150 ℃, preserving heat for 120min, wherein the heating time is 90min, then carrying out two-time first-stage upsetting and drawing on the titanium alloy ingot, and cooling the titanium alloy ingot by water after forging; heating the titanium alloy ingot to 1050 ℃ again, preserving the heat for 150min, then carrying out two-time first-stage upsetting and drawing, and cooling by water after forging; heating the blank to 980 ℃, preserving heat for 150min, still carrying out two-time first-stage upsetting and drawing, and cooling by water after forging;
step S3, heating the titanium alloy ingot to 20-60 ℃ below the beta transformation point, reversing under the condition of preset deformation, and then carrying out three-fire second-stage upsetting on the titanium alloy ingot to enable the edge and the center of a bar blank of the titanium alloy ingot to deform uniformly;
step S4, heating the titanium alloy ingot to a temperature of 50 ℃ above the transformation point, and carrying out third-stage upsetting on the titanium alloy ingot to generate new beta grains;
in step S5, the titanium alloy ingot is heated to 40-60 ℃ below the beta transformation point, and is upset and drawn in the alpha + beta two-phase area for five times of the fourth stage, so that the fine and uniform blank structure is completely crushed, and the titanium alloy material is obtained.
4. The method for preparing the alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine according to claim 3, wherein in the step S6, the titanium alloy material is heated to 900 +/-10 ℃, is at least kept warm for 20min, and is cooled to room temperature in an air cooling mode; then heating to 640 +/-5 ℃, preserving the temperature for at least 60min, and cooling to room temperature in air.
5. The method for preparing the α + β type two-phase titanium alloy for the fan blade of the aircraft engine according to claim 3, wherein in step S3, the titanium alloy ingot is heated to a temperature within a range of 30 ℃ to 50 ℃ below the β transformation point, and after reversing under the condition of a predetermined deformation amount, the titanium alloy ingot is subjected to five-fire second-stage upsetting so that the edge and the center of the bar blank of the titanium alloy ingot are deformed uniformly.
6. The method for preparing the alpha + beta type two-phase titanium alloy for the fan blade of the aero-engine as claimed in claim 3, wherein in S5, the titanium alloy ingot is heated to a temperature of 50-80 ℃ below the beta transformation point, and the fourth stage upsetting is carried out for six times in the alpha + beta two-phase region, so that the fine and uniform blank structure is completely crushed, and the titanium alloy material is obtained.
7. The method of making an α + β two-phase titanium alloy for an aircraft engine fan blade according to any of claims 2 to 6, wherein said first stage upsetting, said second stage upsetting, said third stage upsetting and said fourth stage upsetting each comprise upsetting and elongation, respectively.
8. The method for producing an α + β type two-phase titanium alloy for an aircraft engine fan blade according to any one of claims 2 to 6, wherein the first-stage upset, the second-stage upset, the third-stage upset, and the fourth-stage upset titanium alloy ingots are each cylindrical.
9. The method for preparing the α + β type two-phase titanium alloy for the fan blade of the aircraft engine according to any one of claims 2 to 6, wherein in the step S1, based on the calculation of the CALPHAD method, the contents of Al and V elements are adjusted to increase the electron work function, and the following chemical components are obtained by mass: 4.2 to 5.6 percent of aluminum, 7.5 to 8.8 percent of vanadium, 0.18 to 0.24 percent of oxygen, less than or equal to 0.5 percent of iron, less than or equal to 1 percent of niobium, 0.4 to 0.8 percent of silicon, less than or equal to 0.05 percent of carbon, less than or equal to 0.05 percent of nitrogen, less than or equal to 0.015 percent of hydrogen, and the balance of titanium and impurity elements.
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