High-performance forging method for titanium-aluminum alloy blade

Abstract

The invention provides a high-performance forging method for a titanium-aluminum alloy blade, and relates to the technical field of forging of titanium-aluminum alloys. The method comprises the following steps that S10, a forging die is obtained; obtaining a preset shape size of the forge piece according to the target titanium-aluminum alloy blade; the forge piece comprises a blade root part and a blade body part; wherein the cross section of the blade body part comprises at least one group of parallel edges; preparing a forging die according to the preset shape and size of the forge piece; s20, a blank is obtained, specifically, the blank is prepared according to the preset shape and size of the forge piece in the step S10; s30, the blank is forged through a forging die, and a forged piece is obtained; and the forge piece is machined to obtain the target titanium-aluminum alloy blade. According to the forging method, the performance of the titanium-aluminum alloy blade can be greatly improved.

Description

Technical Field

[0001] The invention relates to the technical field of forging of titanium-aluminum alloys, and in particular to a high-performance forging method for titanium-aluminum alloy blades. Background Art

[0002] With the rapid advancement of the global aviation industry, more stringent requirements have been placed on the performance standards of high-temperature structural materials in aircraft engines. Titanium-aluminum alloys, with their outstanding characteristics - low density, high specific strength, high specific stiffness, and excellent creep and oxidation resistance, can operate stably for a long time in a high-temperature oxidizing environment above 600°C, becoming an important candidate material for achieving engine lightweighting and widely regarded as an ideal choice to replace traditional nickel-based high-temperature alloys. However, traditional polycrystalline titanium-aluminum alloy materials face the challenges of intrinsic brittleness and limited temperature resistance, which largely limit their widespread application in industrial production. The single-crystal titanium-aluminum alloy material prepared by directional solidification technology significantly improves the strength of the material and greatly improves its plasticity, especially the plasticity performance at room temperature, solving the problem that has long plagued the industry. Therefore, single-crystal titanium-aluminum alloys are considered to be ideal high-temperature structural materials with great potential in the field of advanced aircraft engines, and are expected to promote the further development of aviation power technology in the future.

[0003] Due to the high activity of titanium-aluminum alloy melt and the limitation of induction field, it becomes extremely difficult to prepare large-sized single-crystal titanium-aluminum alloy bars by directional solidification technology, which directly limits its wide application in the manufacture of aviation parts, because aviation parts often require large-sized, high-quality raw materials. At present, aviation parts are usually prepared by precision casting or forging. 1. The direct preparation of PST (poly-sheet twinning) titanium-aluminum single crystal alloy parts by precision casting is still immature in technology and principle. 2. Forging and forming by traditional single crystal materials; for example, titanium-aluminum alloy profiles are prepared by jacket hot extrusion technology, and then the titanium-aluminum alloy profiles are subjected to high-temperature forging, so that the precision forming of titanium-aluminum alloy blade-like components can be achieved. This method of first performing jacket hot extrusion and then high-temperature forging is mainly to refine the structure of titanium-aluminum alloy by extrusion, so as to achieve the purpose of improving the hot working properties of titanium-aluminum alloy and improving the forging forming ability. However, it is a common phenomenon that recrystallization occurs when using this forging process, and it cannot be guaranteed that the single crystal structure will be maintained after forging.

[0004] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present disclosure, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0005] In view of this, the present invention proposes a high-performance forging method for titanium-aluminum alloy blades, performs process design on the cross-section of the blade body portion in the engine blade forging, and uses a matching forging die to ensure that the blade body portion of the titanium-aluminum alloy blade maintains a single crystal structure, thereby improving the performance of the titanium-aluminum alloy blade.

[0006] The technical solution of the present invention is implemented as follows: The present invention provides a high-performance forging method for titanium-aluminum alloy blades, comprising the following steps:

[0007] S10, obtaining a forging die;

[0008] Obtaining a preset shape and size of a forging according to a target titanium aluminum alloy blade; the forging comprises a blade root portion and a blade body portion; wherein a cross section of the blade body portion comprises at least one set of parallel edges;

[0009] preparing a forging die according to the preset shape and size of the forging;

[0010] S20, obtaining a blank: preparing a blank according to the preset shape and size of the forging in step S10;

[0011] S30, forging the blank using the forging die to obtain a forging;

[0012] The forging is processed to obtain the target titanium-aluminum alloy blade.

[0013] On the basis of the above technical solution, preferably, in step S20, preparing the blank includes:

[0014] Obtaining a raw material; the raw material comprises a first end portion, a middle portion, and a second end portion;

[0015] At least one end portion of the raw material is heated and subjected to upsetting deformation, while the middle portion is not deformed, to obtain a blank.

[0016] More preferably, the heating of at least one end of the raw material is performed by induction heating; the induction heating temperature is 1000-1100°C, and the final forging temperature during the billet preparation process is not less than 900°C.

[0017] On the basis of the above technical solution, preferably, in step S10, the cross section of the blade body portion includes two groups of parallel edges, and any two adjacent edges are connected by an arc line.

[0018] Based on the above technical solution, preferably, in step S10, the cross section of the blade body includes a group of parallel edges, the group of parallel edges includes a first parallel edge and a second parallel edge, and the endpoints adjacent to the first parallel edge and the second parallel edge are connected by an arc line.

[0019] On the basis of the above technical solution, preferably, in step S10, the preset shape and size of the forging is: the preset size has a margin of at least 2 mm compared with the target titanium aluminum alloy blade.

[0020] On the basis of the above technical solution, preferably, in step S30, forging the blank by using the forging die is forging by using an isothermal forging process.

[0021] More preferably, the isothermal forging process is as follows: the forging temperature is 1000-1100° C., and the forging speed is 0.001-0.1 mm / s.

[0022] On the basis of the above technical solution, preferably, the target titanium aluminum alloy blade is TiAlXZ;

[0023] Wherein, X is at least one of Nb, Mo, Cr, Ta, V, and Mn; Z is at least one of Fe, C, N, O, B, and Si;

[0024] The atomic percentage of Al is 43%-48%, the atomic percentage of X is 0%-8%, and the atomic percentage of Z is 0%-1%.

[0025] The present invention provides a titanium-aluminum alloy blade, which is prepared by the forging method.

[0026] The high-performance forging method for titanium-aluminum alloy blades provided by the present invention has the following beneficial effects compared with the prior art:

[0027] By redesigning the blade body of the titanium aluminum alloy blade, the cross section of the blade body has an appropriate deformation amount, thereby reducing the degradation of target part performance caused by orientation bending or recrystallization of the single crystal layer in the forging. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0029] Figure 1 This is a comparison diagram of the cross section of the blade body of a forging and the cross section of the blade body of a target part in the related art.

[0030] Figure 2 The present invention is a flow chart of a high-performance forging method for titanium-aluminum alloy blades in one embodiment of the present invention.

[0031] Figure 3 It is a schematic diagram of a rod and a titanium-aluminum alloy blade blank without a blade crown in one embodiment of the present disclosure.

[0032] Figure 4 It is a schematic diagram of a rod and a titanium-aluminum alloy blade blank including a blade crown in one embodiment of the present disclosure.

[0033] Figure 5 It is a schematic diagram comparing the cross section of the blade body portion of a forging and the cross section of the blade body portion of a titanium aluminum alloy blade in one embodiment of the present disclosure.

[0034] Figure 6 It is a schematic diagram comparing the cross section of the blade body portion of a forging and the cross section of the blade body portion of a titanium aluminum alloy blade in one embodiment of the present disclosure.

[0035] Figure 7 It is a schematic diagram comparing the horizontal streamlines of the cross section of the bar and the horizontal streamlines of the cross section of the blade part of the forging in one embodiment of the present disclosure.

[0036] Figure 8 It is a schematic diagram comparing the vertical streamlines of the cross section of the bar and the vertical streamlines of the cross section of the blade part of the forging in one embodiment of the present disclosure.

[0037] Fig. 9 It is a schematic diagram comparing the streamline of the cross section of the bar at 45° and the streamline of the cross section of the blade part of the forging at 45° in one embodiment of the present disclosure.

[0038] Fig.10 It is a schematic diagram comparing the horizontal streamlines of the cross section of the bar and the horizontal streamlines of the cross section of the blade part of the forging in a comparative embodiment of the present disclosure.

[0039] Fig.11 It is a schematic diagram comparing the vertical streamlines of the cross section of the bar and the vertical streamlines of the cross section of the blade part of the forging in a comparative embodiment of the present disclosure.

[0040] Fig.12 This is a schematic diagram comparing the streamline of the cross section of the bar at 45° and the streamline of the cross section of the blade part of the forging at 45° in a comparative embodiment of the present invention.

[0041] The reference numerals are as follows:

[0042] 1. Bar, 11. First end, 12. Middle part, 13. Second end, 2. Billet, 21. Blade root forebody, 22. Blade body forebody, 23. Blade crown forebody, 3. Forging, 31. Blade body, 4. Target titanium aluminum alloy blade;

[0043] 01. Forging cross section, 02. Target part. DETAILED DESCRIPTION

[0044] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0045] In the related technology, the engine blade mainly includes a blade root portion and a blade body portion, and some engine blades also include a blade crown portion. The function of the blade root portion is to embed the engine blade in the groove of the impeller rim or the drum flange. During the forging process of the blade root portion, blade body portion and blade crown portion, the metal flows and fills the mold cavity, which will cause the orientation of the single crystal layer to bend or even recrystallize, affecting the overall performance of the engine blade. Among them, the blade root portion and the blade crown portion have complex shapes and sizes. During the forging process, the metal flows and fills the corresponding mold cavity, which will inevitably cause the orientation of the single crystal layer to bend or even recrystallize. However, the blade body portion is the main working part of the engine blade, and the lamellar organization of the blade body portion should be of a single orientation, that is, the single crystal organization should be maintained after deformation. For example Figure 1 The figure shows a schematic diagram of a forging cross section 01 of a blade body and a cross section of a target part 02 of a blade body in the related technology, wherein the forging is designed to expand the target part 02 outward, and the designed forging shows an increase in size compared with the target part 02. Thus, in the process of forging the blank into a forging, it is easy for the single crystal layer of the blade body to bend significantly, thereby affecting the overall performance of the target part 02.

[0046] To solve the above problems, the present invention provides a high performance forging method for titanium aluminum alloy blades, such as Figure 2 As shown, the following steps are included:

[0047] S10. Obtain forging die

[0048] A preset shape and size of the forging 3 is obtained according to the target titanium-aluminum alloy blade 4; the forging 3 includes at least a blade root portion and a blade body portion 31; wherein the cross-section of the blade body portion 31 includes at least one set of parallel edges; and a forging die is prepared according to the preset shape and size of the forging 3.

[0049] In the disclosed embodiment, the cross section of the blade body 31 refers to: the plane along the overall extension direction of the blade root and blade portion of the titanium-aluminum alloy blade is the first plane, and the cross section of the titanium-aluminum alloy blade is perpendicular to the first plane.

[0050] S20, obtaining the blank 2: preparing the blank 2 according to the preset shape and size of the forging 3 described in step S10.

[0051] S30, forging the blank 2 with the forging die to obtain a forging 3; and processing the forging 3 to obtain a target titanium-aluminum alloy blade 4.

[0052] In this embodiment, by designing the forging 3 of the blade body portion 31, the blade body can meet the shape and size requirements of the target titanium-aluminum alloy blade 4, and avoid the destruction of the single crystal structure of the blade body portion 31, thereby affecting the performance. In this embodiment, the cross-section of the blade body portion 31 is designed to be parallel to at least one set of relative edges, thereby reducing the bending of the single crystal layer orientation and even recrystallization caused by the blank 2 during the forging process. The method provided by the present disclosure can be used to manufacture small-diameter titanium-aluminum alloy (such as rods) into engine blades with large width (width exceeding the diameter of the raw material), thereby maintaining the consistent lamellar orientation of the single crystal structure of the blade body portion 31, improving the service performance of the engine blade, and solving the problem that it is difficult to prepare large-size rods from titanium-aluminum alloy single crystal materials, and cannot meet the manufacturing needs of high-quality, large-size aeroengine blades.

[0053] In one embodiment of the present disclosure, the target titanium aluminum alloy blade 4 is TiAlXZ, wherein X is at least one of Nb, Mo, Cr, Ta, V, and Mn; Z is at least one of Fe, C, N, O, B, and Si; the atomic percentage of Al is 43%-48%, the atomic percentage of X is 0%-8%, and the atomic percentage of Z is 0%-1%.

[0054] In one embodiment of the present disclosure, in step S10, the cross section of the blade body portion 31 of the forging 3 includes two sets of parallel edges, and any two adjacent edges are connected by an arc line. Figure 5 As shown, the cross section of the blade body portion 31 is a rounded rectangle.

[0055] In one embodiment of the present disclosure, in step S10, the cross section of the blade body portion 31 of the forging 3 includes a set of parallel edges, the set of parallel edges includes a first parallel edge and a second parallel edge, and the endpoints adjacent to the first parallel edge and the second parallel edge are connected by an arc line. For example, Figure 6 As shown, the cross section of the blade body 31 is drum-shaped. Figure 6 In the illustrated orientation, the upper side length is parallel to the lower side length.

[0056] In one example, in step S10 , the preset shape and size of the forging 3 is: the preset size of the forging 3 has a margin of at least 2 mm compared with the target titanium-aluminum alloy blade 4 .

[0057] In one embodiment of the present disclosure, in step S20 of the present disclosure, the preparation of the billet 2 includes: obtaining a raw material; the raw material includes a first end portion 11, a middle portion 12, and a second end portion 13; heating at least one end portion of the raw material for upsetting deformation, while the middle portion 12 is not deformed, to obtain the billet 2. In this way, the billet 2 required for the forging 3 is prepared by heating the raw material to upset and deform its ends, while keeping the middle portion 12 of the raw material undeformed. The middle portion 12 of the raw material corresponds to the blade body portion 31 in the forging 3. In the process of preparing the billet 2, the middle portion 12 is not deformed, so that the stability of the single crystal structure corresponding to the middle portion 12 can be maintained. For example, Figure 3 and Figure 4 As shown, a schematic diagram of a blank 2 prepared by using a bar 1 and performing upsetting deformation by heating the end. Figure 3 The middle blank 2 includes a blade root forebody 21 formed by deformation of the first end portion 11 and a blade airfoil forebody 22 that is not deformed. Figure 4 The blank 2 includes a blade root forebody 21 formed by deforming the first end portion 11 , a blade body forebody 22 formed by the middle portion 12 that is not deformed, and a blade crown forebody 23 formed by deforming the second end portion 13 .

[0058] In one example, the heating of at least one end of the raw material is performed by induction heating; the induction heating temperature is 1000-1100°C, and the final forging temperature during the preparation of the blank 2 is not less than 900°C.

[0059] In one embodiment of the present disclosure, in step S30, the forging of the blank 2 using a forging die is performed by using an isothermal forging process. Exemplarily, the isothermal forging process is: a forging temperature of 1000-1100° C. and a forging speed of 0.001-0.1 mm / s. Exemplarily, the isothermal forging process can be, but is not limited to: a forging temperature of 1000°C and a forging speed of 0.01 mm / s; or a forging temperature of 1100°C and a forging speed of 0.05 mm / s; or a forging temperature of 1050°C and a forging speed of 0.02 mm / s; or a forging temperature of 1020°C and a forging speed of 0.001 mm / s; or a forging temperature of 1100°C and a forging speed of 0.01 mm / s; or a forging temperature of 1000°C and a forging speed of 0.008 mm / s; or a forging temperature of 1080°C and a forging speed of 0.006 mm / s.

[0060] The disclosed embodiment also provides a titanium-aluminum alloy blade, which is forged using the forging method in any one of the above embodiments.

[0061] The high performance forging method of titanium-aluminum alloy blades provided by the present invention is further described below in conjunction with specific embodiments.

[0062] Example 1

[0063] This example takes titanium aluminum alloy Ti-45Al-8Nb as an example

[0064] S10, design of forging 3 and obtaining forging die: design the preset shape and size of forging 3 according to the size and shape requirements of target titanium aluminum alloy blade 4. The blade root is designed according to the relevant technical design method, and the cross-sectional shape of blade body 31 is designed to be a rounded rectangle (such as Figure 5 As shown in the figure, the forging 3 as a whole reserves a margin of more than 2 mm on the basis of the target titanium-aluminum alloy blade 4, and the forging die is designed and prepared according to the preset shape and size of the forging 3.

[0065] S20, blank preparation: blank 2 is designed according to the preset shape and size of forging 3, and blank 2 is prepared by upsetting method. The raw material is bar 1, such as Figure 3 The schematic diagram of the bar and the blank of this embodiment is shown. When preparing the blank 2, the first end 11 is heated by induction heating, and the deformation of the middle part 12 is limited by a mold so that the middle part 12 does not deform and serves as the blade body precursor 22 of the blank 2. The first end 11 is upset and deformed to obtain the blade root precursor 21 of the blank 2. The induction heating temperature is 1000°C, and the final forging temperature during the preparation of the blank 2 is not less than 900°C.

[0066] S30, forging: After the blank 2 is coated with glass lubricant, it is placed in a forging die and is forged by isothermal forging at a forging temperature of 1000° C. and a forging speed of 0.01 mm / s to obtain a forging 3. The forging 3 is processed to obtain a target titanium aluminum alloy blade 4.

[0067] Example 2

[0068] This example takes titanium aluminum alloy Ti-45Al-8Nb as an example

[0069] S10, design of forging 3 and obtaining forging die: design the preset shape and size of forging 3 according to the size and shape requirements of target titanium aluminum alloy blade 4. The blade root and blade crown are designed according to the relevant technical design method, and the cross-sectional shape of blade body 31 is designed to be drum-shaped (such as Figure 6 As shown in the figure, the forging 3 as a whole reserves a margin of more than 2 mm on the basis of the target titanium-aluminum alloy blade 4, and the forging die is designed and prepared according to the preset shape and size of the forging 3.

[0070] S20, blank preparation: blank 2 is designed according to the preset shape and size of forging 3, and blank 2 is prepared by upsetting method. The raw material is bar 1, such as Figure 4The schematic diagram of the bar and the blank of this embodiment is shown. When preparing the blank 2, the first end 11 and the second end 13 are heated by induction heating, and the deformation of the middle part 12 is limited by a mold so that the middle part 12 does not deform and serves as the blade body forebody 22 of the blank 2. The first end 11 is upset and deformed to obtain the blade root forebody 21 of the blank 2, and the second end 13 is upset and deformed to obtain the blade crown forebody 23 of the blank 2. The induction heating temperature is 1100°C, and the final forging temperature during the preparation of the blank 2 is not less than 900°C.

[0071] S30, forging: After the blank 2 is coated with glass lubricant, it is placed in a forging die and is forged by isothermal forging at a forging temperature of 1100° C. and a forging speed of 0.01 mm / s to obtain a forging 3. The forging 3 is processed to obtain a target titanium aluminum alloy blade 4.

[0072] According to the method provided in this embodiment, the horizontal streamlines, vertical streamlines and 45° streamlines in the cross section of the rod-shaped raw material are compared and analyzed with the horizontal streamlines, vertical streamlines and 45° streamlines in the cross section of the blade body portion 31 in the forging 3.

[0073] See also Figure 7 The horizontal streamlines of the cross section of the rod-shaped raw material (rod 1) are basically consistent with the horizontal streamlines of the cross section of the blade body portion 31 in the forging 3. The horizontal streamlines in the deformed forging 3 basically maintain a horizontal direction without any significant distortion or folding, indicating that by using the method provided in this embodiment, the single crystal layer structure can maintain its orientation without significant changes, thereby avoiding the deterioration of the performance of the single crystal layer structure.

[0074] See also Figure 8 The vertical streamlines of the cross section of the bar 1 are basically consistent with the vertical streamlines of the cross section of the blade body portion 31 in the forging 3. The vertical streamlines in the deformed forging 3 basically maintain the vertical direction without any significant distortion or folding, indicating that by using the method provided in this embodiment, the single crystal layer structure can maintain its orientation without significant changes, thereby avoiding the reduction of the performance of the single crystal layer structure.

[0075] See also Fig. 9 The 45° streamlines of the cross section of the bar 1 are basically consistent with the 45° streamlines of the cross section of the blade body portion 31 in the forging 3. The 45° streamlines in the deformed forging 3 basically maintain the 45° streamline direction without any significant distortion or folding. This indicates that by using the method provided in this embodiment, the single crystal layer structure can maintain its orientation without significant changes, thereby avoiding the reduction of the performance of the single crystal layer structure.

[0076] Comparative Example 1

[0077] This example takes titanium aluminum alloy Ti-45Al-8Nb as an example

[0078] S10, design of forging 3 and obtaining forging die: design the preset shape and size of forging 3 according to the size and shape requirements of target titanium aluminum alloy blade 4. The blade root and the blade crown are designed according to the design method of related technology, and the blade body 31 is designed according to the design of related technology, and the cross section of the titanium aluminum alloy blade is expanded by 2mm (such as Figure 1 As shown), a forging die is designed and prepared according to the preset shape and size of the forging 3.

[0079] S20, blank preparation: blank 2 is designed according to the preset shape and size of forging 3, and blank 2 is prepared by upsetting method. The raw material is bar stock, such as Figure 4 The schematic diagram of the bar and the blank of this embodiment is shown. When preparing the blank 2, the first end 11 and the second end 13 are heated by induction heating, and the deformation of the middle part 12 is limited by a mold so that the middle part 12 does not deform and serves as the blade body forebody 22 of the blank 2. The first end 11 is upset and deformed to obtain the blade root forebody 21 of the blank 2, and the second end 13 is upset and deformed to obtain the blade crown forebody 23 of the blank 2. The induction heating temperature is 1100°C, and the final forging temperature during the preparation of the blank 2 is not less than 900°C.

[0080] S30, forging: After the blank 2 is coated with glass lubricant, it is placed in a forging die and is forged by isothermal forging at a forging temperature of 1100° C. and a forging speed of 0.1 mm / s to obtain a forging 3. The forging 3 is processed to obtain a target titanium aluminum alloy blade 4.

[0081] According to the method provided in the comparative example, the horizontal streamlines, vertical streamlines and 45° streamlines in the cross section of the bar 1 are respectively detected, and compared with the horizontal streamlines, vertical streamlines and 45° streamlines in the cross section of the blade body portion 31 in the forging 3 for analysis.

[0082] See also Fig.10 Compared with the horizontal streamlines of the cross section of the bar 1 and the horizontal streamlines of the cross section of the blade body 31 in the forging 3, the horizontal streamlines in the forging 3 are greatly bent and folded, indicating that the single crystal layer structure is very easy to be destroyed, leading to recrystallization, thereby causing a sharp decline in performance.

[0083] See also Fig.11 Compared with the vertical streamlines of the cross section of the bar 1 and the blade body portion 31 in the forging 3, the vertical streamlines in the forging 3 are greatly bent and folded, indicating that the single crystal layer structure is very easy to be destroyed, leading to recrystallization, thereby causing a sharp decline in performance.

[0084] See also Fig.12Compared with the 45° streamline of the cross section of the bar 1 and the 45° streamline of the cross section of the blade body 31 in the forging 3, the 45° streamline in the forging 3 is greatly bent and folded, indicating that the single crystal layer structure is very easy to be destroyed, leading to recrystallization, thereby causing a sharp decline in performance.

[0085] It should be noted that, although the steps of the high-performance forging method for titanium-aluminum alloy blades in the present disclosure are described in a specific order in the accompanying drawings, this does not require or imply that the steps must be performed in this specific order, or that all the steps shown must be performed to achieve the desired results. Additionally or alternatively, some steps may be omitted, multiple steps may be combined into one step, and / or one step may be decomposed into multiple steps, etc.

[0086] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A high performance forging method for titanium aluminum alloy blades, characterized in that: The following steps are involved: S10, obtaining a forging die; Obtaining a preset shape and size of a forging according to a target titanium aluminum alloy blade; the forging comprises a blade root portion and a blade body portion; wherein a cross section of the blade body portion comprises at least one set of parallel edges; preparing a forging die according to the preset shape and size of the forging; S20, obtaining a blank: preparing a blank according to the preset shape and size of the forging described in step S10; S30, forging the blank using the forging die to obtain a forging; The forging is processed to obtain the target titanium-aluminum alloy blade.

2. The high performance forging method for titanium aluminum alloy blades according to claim 1, characterized in that: In step S20, the blank preparation includes: Obtaining a raw material; the raw material comprises a first end portion, a middle portion, and a second end portion; At least one end portion of the raw material is heated and subjected to upsetting deformation, while the middle portion is not deformed, to obtain a blank.

3. The high performance forging method for titanium aluminum alloy blades according to claim 2, characterized in that: The heating of at least one end of the raw material is carried out by induction heating; the temperature of the induction heating is 1000-1100°C, and the final forging temperature during the blank preparation process is not less than 900°C.

4. The high performance forging method for titanium aluminum alloy blades according to any one of claims 1 to 3, characterized in that: In step S10, the cross section of the blade body includes two groups of parallel edges, and any two adjacent edges are connected by an arc line.

5. The high performance forging method for titanium aluminum alloy blades according to any one of claims 1 to 3, characterized in that: In step S10, the cross section of the blade body includes a group of parallel edges, the group of parallel edges includes a first parallel edge and a second parallel edge, and the adjacent endpoints of the first parallel edge and the second parallel edge are connected by an arc line.

6. The high performance forging method for titanium aluminum alloy blades according to any one of claims 1 to 3, characterized in that: In step S10, the preset shape and size of the forging is: the preset size has a margin of at least 2 mm compared with the target titanium aluminum alloy blade.

7. The high performance forging method for titanium aluminum alloy blades according to claim 1, characterized in that: In step S30, forging the blank using the forging die is performed by using an isothermal forging process.

8. The high performance forging method for titanium aluminum alloy blades according to claim 7, characterized in that: The isothermal forging process is as follows: the forging temperature is 1000-1100° C., and the forging speed is 0.001-0.1 mm / s.

9. The high performance forging method for titanium aluminum alloy blades according to claim 1, characterized in that: The target titanium aluminum alloy blade is TiAlXZ; Wherein, X is at least one of Nb, Mo, Cr, Ta, V, and Mn; Z is at least one of Fe, C, N, O, B, and Si; The atomic percentage of Al is 43%-48%, the atomic percentage of X is 0%-8%, and the atomic percentage of Z is 0%-1%.

10. A titanium-aluminum alloy blade, characterized in that: A titanium-aluminum alloy blade prepared by the forging method described in any one of claims 1 to 9.

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