A high-performance forging method for titanium-aluminum alloy blades

Abstract

The application provides a high-performance forging method for a titanium-aluminum alloy blade, and relates to the field of titanium-aluminum alloy forging technology.The method comprises the following steps: 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 part and a blade body part; wherein the cross section of the blade body part comprises at least one group of parallel edges; the forging die is prepared according to the preset shape and size of the forging; S20, obtaining a blank; the blank is prepared according to the preset shape and size of the forging in step S10; S30, using the forging die to forge the blank to obtain the forging; and the target titanium-aluminum alloy blade is obtained by processing the forging.The forging method provided by the application can greatly improve the performance of the titanium-aluminum alloy blade.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of forging technology of titanium-aluminum alloy, and particularly relates to a high-performance forging method for titanium-aluminum alloy blades. BACKGROUND

[0002] With the rapid advancement of the global aviation industry, more stringent requirements are put forward for the performance standards of high-temperature structural materials in aero-engines. Titanium-aluminum alloy, with its outstanding characteristics of low density, high specific strength, high specific stiffness, and excellent creep resistance and oxidation resistance, can operate stably in a high-temperature oxidation environment above 600 DEG C for a long time, and has become an important candidate material for realizing the lightweight of the engine and is widely regarded as an ideal choice to replace traditional nickel-based high-temperature alloys. However, the traditional polycrystalline titanium-aluminum alloy material is challenged by intrinsic brittleness and limited temperature resistance, which to a large extent limits its wide 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 at room temperature, solving the long-standing problem in the industry. Therefore, single-crystal titanium-aluminum alloy is considered to be an ideal high-temperature structural material with great potential in the field of advanced aero-engines, and is expected to promote the further development of aviation power technology in the future.

[0003] Due to the high activity of the titanium-aluminum alloy melt and the limitation of the induction field, it is extremely difficult to prepare large-size single-crystal titanium-aluminum alloy rods by directional solidification technology, which directly limits its wide application in the manufacturing of aviation parts, because aviation parts often require large-size and high-quality raw materials. At present, aviation parts are usually prepared by precision casting or forging forming method. 1. Directly preparing PST (poly-twin) titanium-aluminum single-crystal alloy parts by precision casting method, which is still immature in technology and principle. 2. Using traditional single-crystal material forging forming; for example, titanium-aluminum alloy profiles are prepared by canning hot extrusion technology, and then the titanium-aluminum alloy profiles are subjected to high-temperature forging, so as to realize the precision forming of titanium-aluminum alloy blade components. The method of canning hot extrusion and then high-temperature forging is mainly to refine the microstructure of titanium-aluminum alloy through extrusion, so as to improve the hot working property of titanium-aluminum alloy and improve the forging forming ability. However, the recrystallization phenomenon occurs universally when the forging process is adopted, which cannot guarantee that the single-crystal structure is maintained after forging.

[0004] It should be noted that the information disclosed in the above background section is only used to strengthen the understanding of the background of the present disclosure, and therefore can include information that does not constitute prior art known to those of ordinary skill in the art. SUMMARY

[0005] Therefore, the application provides a high-performance forging method for a titanium-aluminum alloy blade.

[0006] The technical scheme of the application is as follows: the application provides a high-performance forging method for a titanium-aluminum alloy blade, comprising the following steps:

[0007] S10, obtaining a forging die;

[0008] obtaining a preset shape and size of the forging according to the target titanium-aluminum alloy blade; the forging 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;

[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 by using the forging die to obtain a forging;

[0012] processing the forging to obtain the target titanium-aluminum alloy blade.

[0013] In the above technical scheme, preferably, in step S20, the preparation of the blank comprises:

[0014] obtaining a raw material; the raw material comprises a first end part, a middle part and a second end part;

[0015] heating at least one end part of the raw material to perform upsetting deformation, and the middle part is not deformed to obtain the blank.

[0016] More preferably, the heating of the at least one end part of the raw material is induction heating; the temperature of the induction heating is 1000-1100 DEG C, and the final forging temperature in the blank preparation process is not lower than 900 DEG C.

[0017] In the above technical scheme, preferably, in step S10, the cross section of the blade body part comprises two groups of parallel edges, and any two adjacent edges are connected by an arc line.

[0018] In the above technical scheme, preferably, in step S10, the cross section of the blade body part comprises one group of parallel edges, and one group of the parallel edges comprises a first parallel edge and a second parallel edge; the end points adjacent to each other of the first parallel edge and the second parallel edge are connected by an arc line.

[0019] On the basis of the above technical solutions, preferably, in step S10, the preset shape and size of the forging piece is that 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 solutions, preferably, in step S30, the forging of the blank by using the forging die is that the forging is performed by using an isothermal forging process.

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

[0022] On the basis of the above technical solutions, preferably, the target titanium-aluminum alloy blade is TiAlXZ.

[0023] In the formula, X is at least one of Nb, Mo, Cr, Ta, V and Mn, and 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 application provides a titanium-aluminum alloy blade prepared by using the above forging method.

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

[0027] By newly designing the blade body part of the titanium-aluminum alloy blade, the cross section of the blade body part has a suitable deformation amount, so that the performance reduction of the target part caused by the orientation bending or recrystallization of the single crystal layer in the forging piece is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description only show some embodiments of the application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

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

[0030] Figure 2 It is a flow chart of the titanium-aluminum alloy blade high-performance forging method in one embodiment of the present disclosure.

[0031] Figure 3 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 Schematic diagram of a rod and a titanium-aluminum alloy blade blank including a blade shroud in one embodiment of the present disclosure.

[0033] Figure 5 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 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 Schematic diagram comparing the horizontal streamlines of the cross section of a bar and the horizontal streamlines of the cross section of a blade part of a forging in one embodiment of the present disclosure.

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

[0037] Figure 9 Schematic diagram comparing the 45° streamline of the cross section of the bar and the 45° streamline of the cross section of the blade part of the forging in one embodiment of the present disclosure.

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

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

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

[0041] The reference numerals are as follows:

[0042] 1. Bar, 11. First end, 12. Middle part, 13. Second end, 2. Blank, 21. Blade root forebody, 22. Blade airfoil forebody, 23. Blade crown forebody, 3. Forging, 31. Blade airfoil, 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 embodiments described 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 making creative efforts are within the scope of protection of the present invention.

[0045] In the relevant technology, the engine blade mainly includes a blade root part and a blade body part, and some engine blades also include a blade crown part. The function of the blade root part 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 part, the blade body part and the blade crown part, the metal flows to fill 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 part and the blade crown part have complex shapes and sizes. During the forging process, the metal flows to fill the corresponding mold cavity, which will inevitably cause the orientation of the single crystal layer to bend or even recrystallize. However, the blade body part is the main working part of the engine blade, and it should be ensured that the lamellar tissue orientation of the blade body part is single, that is, the single crystal structure is still maintained after deformation. Such as Figure 1 The figure shows a schematic diagram of the cross section 01 of the blade body forging and the cross section of the target part 02 of the blade body in the related art. The forging is designed to expand the target part 02 outward. The designed forging shows an increase in size compared with the target part 02. In this way, in the process of forging the blank into the forging, the single crystal layer of the blade body is easily bent significantly, 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 embodiment of the present disclosure, 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 by using the forging die to obtain a forged piece 3; and processing the forged piece 3 to obtain the target titanium-aluminum alloy blade 4.

[0052] In this embodiment, the design of the forged piece 3 of the blade body 31 makes the blade body meet the shape and size requirements of the target titanium-aluminum alloy blade 4 and avoids the damage of the single crystal structure of the blade body 31 and the impact on the performance. In this embodiment, the cross section of the blade body 31 is designed to have at least one set of opposite parallel edges, so as to reduce the bending of the single crystal layer orientation of the blank 2 during the forging process or even the recrystallization. The method provided in the present disclosure can manufacture a small-diameter titanium-aluminum alloy (for example, a bar) into a large-width (the width is greater than the diameter of the raw material) engine blade, so that the blade body 31, which is the main working part of the engine blade, maintains the same layer orientation of the single crystal structure, improves the service performance of the engine blade, and solves the problem that the titanium-aluminum alloy single crystal material is difficult to prepare large-size bars and cannot meet the manufacturing requirements of high-quality and large-size aviation blades.

[0053] In an embodiment of the present disclosure, the target titanium-aluminum alloy blade 4 is TiAlXZ. In the formula, 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% to 48%, the atomic percentage of X is 0% to 8%, and the atomic percentage of Z is 0% to 1%.

[0054] In an embodiment of the present disclosure, in step S10, the cross section of the blade body 31 of the forged piece 3 includes two sets of parallel edges, and any two adjacent edges are connected by an arc-shaped line. For example, as shown in FIG. 2, the cross section of the blade body 31 is a circular rectangle. Figure 5

[0055] In an embodiment of the present disclosure, in step S10, the cross section of the blade body 31 of the forged piece 3 includes one set of parallel edges, and the set of parallel edges includes a first parallel edge and a second parallel edge, and the end points of the first parallel edge and the second parallel edge are connected by an arc-shaped line. For example, as shown in FIG. 3, the cross section of the blade body 31 is a drum shape. Figure 6 Figure 6 In the schematic orientation, the length of the upper edge is parallel to the length of the lower edge.

[0056] In an example, in step S10, the preset shape and size of the forged piece 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 blank 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 to perform upsetting deformation, while the middle portion 12 is not deformed, to obtain the blank 2. In this way, the blank 2 required for the forging 3 is prepared by heating the raw material to perform upsetting deformation on its end portion, 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 blank 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 portion. Figure 3 The intermediate blank 2 includes a blade root forebody 21 formed by deforming 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 airfoil 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, forging the blank 2 with a forging die is performed by isothermal forging. For example, the isothermal forging process is as follows: 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 embodiments of the present disclosure also provide 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 for titanium-aluminum alloy blades provided by the present disclosure is further described below with reference to specific embodiments.

[0062] Example 1

[0063] This example takes the 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), 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: according to the preset shape and size of the forging 3, the blank 2 is designed and made by upsetting. The raw material is bar 1, such as Figure 3 The figure shows a schematic diagram of the bar and blank of this embodiment. During the preparation of blank 2, the first end portion 11 is heated using induction heating. A die is used to limit deformation of the middle portion 12, preventing deformation and serving as the blade airfoil precursor 22 of blank 2. The first end portion 11 is then upset to produce the blade root precursor 21 of blank 2. The induction heating temperature is 1000°C, and the final forging temperature during the preparation of blank 2 is no less than 900°C.

[0066] S30, forging: After applying glass lubricant, the blank 2 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 the target titanium-aluminum alloy blade 4.

[0067] Example 2

[0068] This example takes the 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 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), 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: according to the preset shape and size of the forging 3, the blank 2 is designed and made by upsetting. The raw material is bar 1, such as Figure 4The bar and the blank are shown in the schematic diagram of the embodiment. When the blank 2 is prepared, the first end 11 and the second end 13 are heated by induction heating, the deformation of the middle part 12 is limited by a mold, so that the middle part 12 is not deformed and serves as a precursor 22 of the blade body part of the blank 2, the first end 11 is upset to deform to prepare a precursor 21 of the blade root part of the blank 2, the second end 13 is upset to deform to prepare a precursor 23 of the blade crown part of the blank 2, the induction heating temperature is 1100°C, and the final forging temperature in the preparation process of the blank 2 is not lower than 900°C.

[0071] S30, forging forming: after the blank 2 is smeared with glass lubricant, the blank 2 is placed into a forging mold, and is formed by isothermal forging, the forging temperature is 1100°C, the forging speed is 0.01mm / s, and the forged piece 3 is obtained. The target titanium-aluminum alloy blade 4 is obtained by processing the forged piece 3.

[0072] According to the method provided in the embodiment, the horizontal flow lines, the vertical flow lines and the 45° flow lines in the cross section of the bar-shaped raw material are compared and analyzed with the horizontal flow lines, the vertical flow lines and the 45° flow lines in the cross section of the blade body part 31 of the forged piece 3.

[0073] Referring to Figure 7 , the horizontal flow lines in the cross section of the bar-shaped raw material (the bar 1) are basically consistent with the horizontal flow lines in the cross section of the blade body part 31 of the forged piece 3, the horizontal flow lines in the deformed forged piece 3 basically maintain the horizontal direction and do not occur large distortion and folding, which indicates that the single crystal layer structure can maintain the orientation without large change by using the method provided in the embodiment, so that the performance of the single crystal layer structure is avoided from being deteriorated.

[0074] Referring to Figure 8 , the vertical flow lines in the cross section of the bar 1 are basically consistent with the vertical flow lines in the cross section of the blade body part 31 of the forged piece 3, the vertical flow lines in the deformed forged piece 3 basically maintain the vertical direction and do not occur large distortion and folding, which indicates that the single crystal layer structure can maintain the orientation without large change by using the method provided in the embodiment, so that the performance of the single crystal layer structure is avoided from being deteriorated.

[0075] Referring to Figure 9 , the 45° flow lines in the cross section of the bar 1 are basically consistent with the 45° flow lines in the cross section of the blade body part 31 of the forged piece 3, the 45° flow lines in the deformed forged piece 3 basically maintain the 45° flow line direction and do not occur large distortion and folding, which indicates that the single crystal layer structure can maintain the orientation without large change by using the method provided in the embodiment, so that the performance of the single crystal layer structure is avoided from being deteriorated.

[0076] Comparative Example 1

[0077] In the embodiment, the titanium-aluminum alloy Ti-45Al-8Nb is taken as an example

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

[0079] S20, blank preparation: the blank 2 is designed according to the preset shape and size of the forging 3, and the upsetting method is used to prepare the blank 2. The raw material is a bar, as shown in Figure 4 The bar and the blank of the embodiment are shown in the figure. When the blank 2 is prepared, 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 the die, so that the middle part 12 is not deformed and serves as the blade body precursor 22 of the blank 2. The first end 11 is upset to deform to prepare the blade root precursor 21 of the blank 2, and the second end 13 is upset to deform to prepare the blade crown precursor 23 of the blank 2. The induction heating temperature is 1100℃, and the final forging temperature during the preparation of the blank 2 is not less than 900℃.

[0080] S30, forging forming: after the blank 2 is smeared with glass lubricant, it is put into the forging die and formed by isothermal forging method. The forging temperature is 1100℃, and the forging speed is 0.1mm / s. The forging 3 is obtained. The target titanium-aluminum alloy blade 4 is obtained by processing the forging 3.

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

[0082] Referring to Figure 10 , the horizontal flow lines of the cross section of the bar 1 are compared with the horizontal flow lines of the cross section of the blade body 31 of the forging 3. The horizontal flow lines of the forging 3 are greatly curved and folded, indicating that the single crystal layer organization is easily damaged, leading to recrystallization, thereby causing a sharp decline in performance.

[0083] Referring to Figure 11 , the vertical flow lines of the cross section of the bar 1 are compared with the vertical flow lines of the cross section of the blade body 31 of the forging 3. The vertical flow lines of the forging 3 are greatly curved and folded, indicating that the single crystal layer organization is easily damaged, leading to recrystallization, thereby causing a sharp decline in performance.

[0084] Referring to Figure 12Compared with the 45° streamline of the cross section of bar 1 and the 45° streamline of the cross section of the blade body 31 in forging 3, the 45° streamline in 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 disclosed herein 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 steps shown must be performed to achieve the desired results. Additionally or alternatively, certain steps may be omitted, multiple steps may be combined into one, and / or one step may be broken down into multiple steps.

[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 scope of protection 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 includes a blade root portion and a blade airfoil portion; wherein a cross-section of the blade airfoil portion includes two sets of parallel edges, and any two adjacent edges are connected by an arc line; 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; Processing the forging to obtain a target titanium-aluminum alloy blade; In step S20, the blank preparation includes: Obtaining a raw material; the raw material includes a first end portion, a middle portion, and a second end portion; Heating and upsetting at least one end portion of the raw material while leaving the middle portion undeformed to obtain a blank; 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.

2. The high performance forging method for titanium aluminum alloy blades according to claim 1, 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.

3. The high performance forging method for a titanium aluminum alloy blade according to any one of claims 1 to 2, characterized in that: In step S10 , the cross section of the blade airfoil includes a group of parallel edges, the group of parallel edges includes a first parallel edge and a second parallel edge, and adjacent endpoints of the first parallel edge and the second parallel edge are connected by an arc line.

4. 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 using an isothermal forging process.

5. The high performance forging method for titanium aluminum alloy blades according to claim 4, 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.

6. 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%.

7. A titanium aluminum alloy blade, characterized in that: The titanium-aluminum alloy blade is prepared by the high-performance forging method according to any one of claims 1 to 6.

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